cessna citation ii y v

HoneywellCOMMERCIALFLIGHTSYSTEMSGROUPBUSINESSANDCOMMUTERAVIATIONSYSTEMSDIVISIONGLENDALE,ARIZONA

SPZ-500C Integrated FlightControl System

Cessna Citation WV

MaintenanceManual

22-14-00

PRINTED IN U.S.A. Al 5-1146-47REVISED 25 MAY 1990

15 MARCI-I 1989

PROPRIETARYNOTICE

ThisreviseddocumentandtheinformationdisclosedhereinareproprietarydataofHoneywellInc.Neitherthisdocumentnortheinformationcontainedhereinshallbeused,reproduced,ordisclosedtootherswithoutthewrittenauthorizationofHoneywellInc.,excepttotheextentrequiredforinstallationormaintenanceofrecipient’sequipment.

NOTICE-FREEDOMOF INFORMATIONACT(5USC552)ANDDISCLOSUREOFCONFIDENTIALINFORMATIONGENERALLY(18USC1905)

Thisreviseddocumentisbeingfurnishedinconfidenceby HoneywellInc.Theinformationdisclosedhereinfallswithinexemption(b)(4)of5USC552andtheprohibitionsof18USC1905.

S14

IMPORTANT NOTICE

The avionicsbusinessunitsformerlyowned by UNISYS Corp.andidentifiedwiththeSperryname or logohave been acquiredbyHoneywellInc.Publications,products,and componentsmarkedoridentifiedhereinwiththeSperryname orlogoarepublications,products,and componentsofHoneywellInc.AllreferencestotheSperryname orlogoshouldbe takenasreferringtoHoneywellInc.

Copyright 1990 Honeywell Inc.All Rights Reserved

Honeywell M!&?’’””CITATIONn/V

RECORDOF REVISIONS

Retainthisrecordin frontof manual.On receiptofrevision,insertrevisedpagesin themanual,andenterrevisionnumber,dateinsertedand initial.

Revision Revision Insertion Revision Revision InsertionNumber Date Date By Number Date Date By

May25/90 Jun25/90 &

22-14-00Recordof Revisions

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Honeywell MKR’ANC’CITATION n/V

SUBJECT PAGE

Title

RecordofRevisions

ListofEffectivePages

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Contents1

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ListofIllustrations

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LISTOF EFFECTIVEPAGES

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Introduction1

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SystemDescription

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SystemDescription(cent)

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ComponentDescription(cent)

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ComponentDescription(cent)

198.77198.78198.79198.80198.81198.82Blank198.83198.84Blank198.85198.86198.87198.88Blank198.89198.90198.91198.92198.93198.94198.95198.96198.97198.98Blank198.99198.100198.101198.102198.103198.104198.105198.106198.107198.108198.109198.110198.111198.112198.113198.114198.115198.116198.117198.118198.119198.120198.121198.122198.123

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SystemOperation

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Interconnects(cent)

590591592593594595596597598598.1598.2598.3598.4598.5598.6598.7598.8598.9598.10598.11598.12598.13598.14598.15598.16598.17598.18598.19598.20598.21598.22598.23598.24598.25598.26598.27598.28598.29598.30598.31598.32598.33598.34598.35598.36598.37598.38598.39

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Interconnects(cent)

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SystemSchematics

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Removal/ReinstallationandAdjustment

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Honeywell WR’AN’ECITATION n/V

Section

1

9

2

Parama~h

TABLEOF CONTENTS

Subject

SystemDescri~tion

1. General2. SystemDescription

1!.B.

c.D.

E.F.G.H.I.J.

AttitudeandHeadingReferenceSystemADZ-241AirDataSystemor OptionalADZ-81OAir DataSystemAA-300RadioAltimeterSystemEDZ-605ElectronicFlightInstrumentSystem(EFIS)FlightControlSystemPRIMUS@650WeatherRadarSystemMDZ-605MultifunctionDisplaySystem(Optional)FMZ-800FlightManagementSystem(Optional)SRZ-850IntegratedRadioSystem(Optional)LSZ-850LightningSensorSystem(Optional)

Coml)onentDescritItion

1. General2. AttitudeandHeadingReferenceSystem

andRateGyro

A. VG-14AVerticalGyroB. C-14DDirectionalGyroc. CS-412DualRemoteCompensatorD. FX-220FluxValveE. RG-204RateGyro

3. ADZ-241andOptionalADZ-81OAir DataSys’~em

A. AZ-241Air DataComputerB. BA-141BarometricAltitudeIndicatorc. VN-212VNAVComputer/ControllerD. AZ-81ODigitalAirDataComputerE. VN-800VNAVControl/Display

4. OptionalAA-300RadioAltimeterSystem

A. RT-300RadioAltimeterReceiver/TransmitterB. AT-223RadioAltimeterAntenna

5. ElectromechanicalFlightInstruments

A. RD-450HorizontalSituationIndicator

Paqe

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118

;:

2020

212222232426

101

101102

102108114116118

120

120130134138144

148

148151

152

152- Copilot’s 22-14-00

Contents(Page1)May25/90

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Section

2

Honeywell WWI!AN’ECITATION n/V

TABLEOF CONTENTS(cent)

Paraqra~h Sub.iect

Comr)onentDescription(cent)

6. EDZ-605ElectronicFlightInstrumentSystemandOptionalMQZ-605MultifunctionDisplaySystem

A.B.

c.

D.E.F.

!:I.J.K.L.

ED-600ElectronicDisplayED-600Usedas an ElectronicAttitudeDirectorIndicator(EADI)ED-600Usedas an ElectronicHorizontalSituationIndicator(EHSI)CompositeDisplayEFISSelfTestED-600Usedas a MultifunctionDisplay(MFD)ED-600FunctionalOperationDC-811DisplayControllerRI-106SInstrumentRemoteControllerSG-605SymbolGeneratorMC-800MFDControllerMG-605MFD SymbolGenerator

7. FlightControlSystem

A. SP-200AutopilotComputerB. FZ-500FlightDirectorComputerc. MS-205ModeSelectorD. PC-500AutopilotControllerE. AG-222AccelerometerF. RZ-220RollRateMonitor- CitationV OnlyG. SM-200ServoDriveandSB-201Bracket

8. PRIMUS@650WeatherRadarSystem

A. WU-650AntennaandReceiver/TransmitterUnitB. WI-650WeatherRadarIndicator

&

156

156157

168

185186187193198

198.6198.8198.14198.22

198.28

198.28198.30198.42198.46198.52198.54198.58

198.62

198.62198.66

C. OptionalWC-650WeatherRadarController 198.70.2

9. OptionalFMZ-800FlightManagementSystem(FMS) 198.72

A. NZ-61OB. CD-800c. DL-800D. OZ-800E. AT-801

NavigationComputer 198.72ControlDisplayUnit 198.76DataLoader 198.86ReceiverProcessorUnit 198.90H-FieldBrickAntenna 198.93

22-14-00Contents(Page2)

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Section

2


Paraqra~h Sub.iect

Com~onentDescription(cent)

10. OptionalSRZ-850IntegratedRadioSystem

A. RNZ-850IntegratedNavigationUnitB. RCZ-850IntegratedCommunicationUnitC. ML-850MicrowaveLandingSystem(MLS)

ReceiverD. RM-850RadioManagementUnit(RMU)E. AV-850AAudioControlUnitF. CD-850ClearanceDeliveryControl/

DisplayUnitG. D1-851DMEIndicatorH. AT-860ADFAntennaI. AT-851MLSAntenna

11. OptionalLSZ-850LightningSensorSystem

A. LP-850LightningB. LU-850LightningC. AT-850AntennaD. AT-855Antenna

SvstemODeration

1. General

SensorProcessorSensorController

SystemPerformance/OperatingLimits:: FlightDirectorFunctionalDescription

A. GeneralB. ControlFunctionsc. FlightDirectorModeFlowDescription

4. AutopilotComputerFunctionalDescription

A. Autopilot/YawDamperEngageB. RollAxisC. PitchAxisD. YawAxis

5. C-14DCompassSystemFunctionalDescription

6. EDZ-605EFISandOptionalMDZ-605MFD System

A. AttitudePortInterconnectsB. HeadingPortInterconnectsc. ShortRangeNavigation(SRN)Port

~

198,94

198.94198.100198.104

198.108198.114198.118

198.122198.126198.128

198.130

198.130198.134198.138198.140

201

201202207

207207210

259

259260264268

288

291

291291293

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Section

3

Honeywell WMYANCECITATION n/V


Paraqrar)h Sub.iect

SYstemOt)eration(cent)

D. LongRangeNavigation(LRN)PortInterconnects

E. RadioAltimeterPortInterconnectsF. WeatherRadarPortInterconnectsG. Rateof TurnPortInterconnectsH. MicrowaveLandingSystem(MLS)Port

InterconnectsMiscellaneousProgrammingFunctions

;: FlightDirectorSignalsK. EFISBackupMode

GroundCheck

General:: EquipmentandMaterials3. Procedure

FaultIsolation

1. General2. Procedure

Interconnects

SystemSchematics

Removal/ReinstallationandAd.iustment

1. General2. EquipmentandMaterials3. ProcedureforAll IndicatorsandElectronic

Displays4. ProcedureforSelectorsandControllers

A. MS-205ModeSelector,PC-500AutopilotController,RI-106SInstrumentRemoteController,DC-811DisplayController,MC-800MFDController,AV-850AAudioControlUnit,CD-800ControlDisplayUnit,andWC-650WeatherRadarController

B. VN-212VNAVComputer/Controller,VN-800VNAVControl/Display,and LU-850LightningSensorController

294

294295295295

296296297

301

301301301

401

401401

501

601

701

701701701

702

702

702

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Section

8



Paraqrar)h Sub.iect

Removal/ReinstallationandAd.iustment(cent)

5. ProcedureforSensorsandGyros

A. AG-222AccelerometerandRG-204RateGyroB. VG-14AVerticalGyroandC-14DDirectional

Gyroc. FX-220FluxValveD. CS-412DualRemoteCompensator

6. ProcedureforSP-200Autopilot,FZ-500FlightDirector,NZ-61ONavigation.andAZ-241/AZ-810AirDataComputers,SG-605/MG-605SymbolGenerators,OZ-800ReceiverProcessorUnit,RNZ-850NAVUnit,RCZ-850COMUnit,ML-850MLSReceiver,anclLP-850LightningSensorProcessor

7. ProcedureforSM-200ServoDriveandSB-201DrumandBracketAssembly

A. ServoDriveAssemblyB. DrumandBracket

8. ProcedureforRT-300Transmitter

9. ProcedureforRZ-220

10. ProcedureforWU-650TransmitterUnit

11. ProcedureforWI-65012. ProcedureforRM-85013. ProcedureforCD-850

As;embly

RadioAltimeterRece?ver

RollRateMonitor

AntennaandReceiver;

WeatherRadarIndicatorRadioManagementUnit(RMU)ClearanceDeliveryCDU

702

702703

703705

706

707

707707

709

709

710

710711711

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Ei9.w

1

12

4

5

6

7

2-1

2-2

2-3

2-4

2-5

2-6

2-7

2-8

2-9

2-1o

3-1

3-2

3-3

3-4

3-5

LISTOF ILLUSTRATIONS

W

SystemFlowDiagram

OptionalMultifunctionDisplay(MFD)SystemFlowDiagram

OptionalFMZ-800FlightManagementSystem(FMS]FlowDiagram

OptionalRNZ-850IntegratedRadioSystem

OptionalLSZ-850LightningSensorSystem

ComponentLocations

LightningSymbols

VG-14AVerticalGyro

VG-14AVerticalGyroBlockDiagram

C-14DDirectionalGyro

C-14DDirectionalGyroBlockDiagram

CS-412DualRemoteCompensator

CS-412DualRemoteCompensatorBlockDiagram

FX-220FluxValve

FX-220FluxValveSchematic

RG-204RateGyro

RG-204RateGyroBlockDiagram

AZ-241AirDataComputer

AZ-241AirDataComputerBlockDiagram

BA-141BarometricAltitudeIndicator

BA-141BarometricAltitudeIndicatorBlockDiagram

VN-212VNAVComputer/Controller

en

&

5

9

11

13

14.1

15

26

102

103

108

111

114

115

116

117

118

119

120

123

130

133

134

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Mu!E

3-6

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3-8

3-9

3-1o

4-1

4-2

4-3

5-1

5-2

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6-2

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6-4

6-5

6-6

6-7

6-8

6-9

6-10

6-11

6-12

6-13

Honeywell MVJEFANCECITATION n/V

LISTOF ILLUSTRATIONS(cent)

m

VN-212VNAVComputer/ControllerBlockDiagram

AZ-81ODigitalAirDataComputer

AZ-81ODigitalAirDataComputerBlockDiagram

VN-800VNAVControl/Display

VN-800VNAVControl/DisplayBlockDiagram

RT-300RadioAltimeterReceiver/Transmitter

RT-300RadioAltimeterReceiver/TransmitterBlockDiagram

AT-223RadioAltimeterAntenna

RD-450HorizontalSituationIndicator

RD-450HorizontalSituationIndicatorBlockDiagram

ED-600EADIDisplaysandAnnunciators

ED-600EADICautionandFailureAnnunciations(Amber/

ED-600EADICautionandFailureAnnunciations(Red)

ED-600InternalSystemFailure(Red)

ED-600EHSIDisplaysandAnnunciators

ED-600EHSICautionandFailureAnnunciations(Amber!

ED-600EHSICautionandFailureAnnunciations(Red)

ED-600EHSIPartialCompassDisplays

LRNMapModewithMultipleWaypoints

SRN (VOR)MAPMode

CompositeDisplaySymbolDefinition

MFDMapMode

MFD PlanMode

Paqe

135

138

140

144

147

148

150

151

152

155

161

165

166

167

173

176

177

179

182

184

185

190

192

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Honeywell M!M!!ANCECITATION V

6-14

6-15

6-16

6-17

6-18

6-19

6-20

6-21

6-22

6-23

6-24

7-1

7-2

7-3

7-4

7-5

7-6

7-7

7-8

7-9

7-1o

7-11


&

ED-600ElectronicDisplayBlockDiagram

DC-811DisplayController

DC-811DisplayControllerBlockDiagram

RI-106SInstrumentRemoteController

RI-106SInstrumentRemoteControllerSchematic

SG-605SymbolGenerator

SG-605SymbolGeneratorBlockDiagram

MC-800MFDController

MC-800MFDControllerBlockDiagram

MG-605MFDSymbolGenerator

MG-605MFDSymbolGeneratorBlockDiagram

SP-200AutopilotComputer

FZ-500FlightDirectorComputer

FZ-500FlightDirectorComputerBlockDiagram

MS-205ModeSelector

MS-205ModeSelectorSchematic

PC-500AutopilotController

PC-500AutopilotControllerBlockDiagram

AG-222Accelerometer

AG-222AccelerometerBlockDiagram

RZ-220RollRateMonitor

RZ-220RollRateMonitorBlockDiagram

PacJg

195

198

198.3

198.6

198.7

198.8

198.11

198.14

198.19

198.22

198.25

198.28

198.30

198.33

198.42

198.43

198.46

198.49

198.52

198.53

198.54

198.55

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Honeywell MMR’AN’ECITATION n/V

7-12

7-13

8-1

8-2

8-3

8-4

I8-58-6

9-1

9-2

9-3

9-4

9-5

9-6

9-7

9-8

9-9

1o-1

10-2

10-3

10-4

10-5

10-6


W

SM-200ServoDriveandSB-201Bracket

SM-200ServoDriveBlockDiagram

WU-650AntennaandReceiver/TransmitterUnit

WU-650AntennaandReceiver/TransmitterUnitBlockDiagram

WI-650WeatherRadarIndicator

WI-650WeatherRadarIndicatorBlockDiagram

WC-650WeatherRadarController

WC-650WeatherRadarControllerBlockDiagram

NZ-61ONavigationComputer

NZ-61ONavigationComputerBlockDiagram

CD-800ControlDisplayUnit

CD-800ControlDisplayUnitBlockDiagram

DL-800DataLoader

DL-800DataLoaderBlockDiagram

OZ-800ReceiverProcessorUnit

OZ-800ReceiverProcessorUnitBlockDiagram

AT-801H-FieldBrickAntenna

RNZ-850IntegratedNavigationUnit

RNZ-850IntegratedNavigationUnitBlockDiagram

RCZ-850IntegratedCommunicationUnit

RCZ-850IntegratedCommunicationUnitBlockDiagram

ML-850MLSReceiver

ML-850MLSReceiverBlockDiagram

Paqe

198.58

198.61

198.62

198.65

198.66

198.69

198.70.2

198.70.7

198.72

198.75

198.76

198.83

198.86

198.89

198.90

198.92

198.93

198.94

198.99

198.100

198.103

1980104

198.107


May 25/90Lh3 or disclosure of mtormatlon on this pageE subtecl to the restrtcttons on the tttle pageOfthisdt,Curnerll

Honeywell WWANC’CITATION n/V


m m

10-7

10-8

10-9

1o-1o

10-11

10-12

10-13

10-14

10-15

10-16

10-17

11-1

11-2

11-3

11-4

11-5

11-6

201

202

203

204

205

206

RM-850RadioManagementUnit

RM-850RadioManagementUnitBlockDiagram

AV-850AAudioControlUnit

AV-850AAudioControlUnitBlockDiagram

CD-850ClearanceDeliveryControl/DisplayUnit

CD-850ClearanceDeliveryControl/DisplayUnitBlockDiagram

DI-851DME Indicator

DI-851DME IndicatorBlockDiagram

AT-860ADFAntenna

AT-860ADFAntennaBlockDiagram

AT-851MLSAntenna

LP-850LightningSensorProcessor

LP-850LightningSensorProcessorBlockDiagram

LU-850LightningSensorController

LU-850LightningSensorControllerSchematic

AT-850Antenna

AT-855Antenna

FlightDirectorModeLogic

FD OFF Logic

EHSI

EFIS

EFIS

EFIS

HeadingandCourseSelectInterface

Rollor PitchAttitudeandCommandInterface

ED-600EADIInterconnects

ED-600EHSIInterconnects

Pag_e

198.108

198.112

198.114

198.117

198.118

198.121

198.122

198.124

198.126

198.127

198.128

198.130

198.133

198.134

198.137

198.138

198.140

221

227

229

231

233

235


May25/90Use or disclosure of mformahon on Ihm page IS subject to the restnct!ons on the utle page >f fhts documenl

Honeywell WE’’””CITATION 11~

Euu!E

207

208

209

210

211

212

213

214

215

216

I217

217.1

218

I219219.1

220

221

222

223

Heading

VOR and


M

SelectandGo AroundModeFlowDiagram

VORApproachModeFlowDiagram

Localizer,LocalizerApproach,andBackCourseModeFlowDiagram

InstrumentLandingSystem(ILS)Diagram

Altitude,VerticalSpeed,and IndicatedAirspeedHoldModeFlowDiagram

GlideslopeApproachandGo AroundModeFlowDiagram

AltitudePreselectModeFlowDiagram

VerticalNavigationModeFlowDiagram

VNAVSampleProblem

FailureWarningFlagsandBarBiasLogicDiagram

Autopilot/YawDamperEngageInterlockDiagramforCitationV


AutopilotComputerSignalFlowDiagram

TorqueSwitchingSignalFlowDiagramforCitationV

TorqueSwitchingSignalFlowDiagramforCitationII

Pilot’sC-14DCompassSystemSignalFlowDiagram

SG-605andOptionalMG-605AttitudePortInterconnects

SG-605andOptionalMG-605HeadingPortInterconnects

SG-605andOptionalMG-605ShortRangeNavigation(SRN)PortInterconnects

~

237

239

241

243

245

247

249

251

253

255

271

274.1

275

287

288

289

298.1

298.3

298.5


May25/90Use Or disclosure of mformatlon on Ih!s page IS subject 10 the restrictions on the [Itle pageOf!hls document

Ei9!u

224

225

226



Name

SG-605andOptionalMG-605LongRangeNavigation(LRN)PortInterconnects

SG-605andOptionalMG-605RadioAltitude,Rateof Turn,WeatherRadar,andMicrowaveLandingSystem(MLS)PortInterconnects

PaQe

298.7

298.9

FlightDirectorValidandNavigationSignals 298.11

22-14-00Listof Illustrations(Page7/8)

May25/90Useordisclosureofmformatlon on thts pageIS subject to the reslr!cllons on the tttle pacj ! of thm documenl

Honeywell WE’’AN’ECITATION n/V

Table

1

2

,3

2-1

2-2

2-3

2-4

2-5

3-1

3-2

3-3

3-4

3-5

4-1

4-2

5-1

6-1

6-2

6-3

6-4

LISTOF TABLES

Name

SystemComponents

OptionalSystemComponents

EquipmentRequiredbutnotSuppliedby Honeywe”’1

VG-14AVerticalGyroLeadingParticulars

C-14DDirectionalGyroLeadingParticulars

CS-412DualRemoteCompensatorLeadingParticulars

FX-220FluxValveLeadingParticulars

RG-204RateGyroLeadingParticulars

AZ-241AirDataComputerLeadingParticulars

BA-141BarometricAltitudeIndicatorLeadingParticulars

VN-212VNAVComputer/ControllerLeadingPartic~llars

AZ-81ODigitalAirDataComputerLeadingParticulars

VN-800VNAVControl/DisplayLeadingParticular;

RT-300RadioAltimeterReceiver/TransmitterLeadingParticulars

AT-223RadioAltimeterAntennaLeadingParticulars

RD-450HorizontalSituationIndicatorLeadingParticulars

ED-600ElectronicDisplayLeadingParticulars

DC-811DisplayControllerLeadingParticulars

RI-106SInstrumentRemoteControllerLeadingParticulars

SG-601SymbolGeneratorLeadingParticulars

~

1

3

17

102

109

114

116

118

121

130

134

139

144

148

151

153

156

198

198.6

198.8

22-14-00Listof Tables(Page1)

May25/90Use or disclosure 0! Information on this page IS subject 10 the reslrlctlons on the Iltle pag( of Ihm document

Honeywell !NLE?AN’ECITATION n/V

Table

6-5

6-6

7-1

7-2

7-3

7-4

7-5

7-6

7-7

7-8

8-1

8-2

8-3

I8-4

8-5

9-1

9-2

9-3

9-4

9-5

1o-1

10-2

MC-800

MG-605

SP-200

FZ-500

MS-205

PC-500

AG-222

RZ-200

SM-200

LISTOF TABLES(cent)

W

MFDControllerLeadingParticulars

MFDSymbolGeneratorLeadingParticulars

AutopilotComputerLeadingParticulars

FlightDirectorComputerLeadingParticulars

ModeSelectorLeadingParticulars

AutopilotControllerLeadingParticulars

AccelerometerLeadingParticulars

RollRateMonitorLeadingParticulars

ServoDriveandSB-201BracketLeadingParticulars

SM-200ServoDriveDashNo.Differences

WU-650AntennaandReceiver/TransmitterLeadingParticulars

WI-650WeatherRadarIndicatorLeadingParticulars

IndicatorControlFunctions

WC-650WeatherRadarControllerLeadingParticulars

WC-650ControlFunctions

NZ-61ONavigationComputerLeadingParticulars

CD-800ControlDisplayUnitLeadingParticulars

DL-800DataLoaderLeadingParticulars

OZ-800ReceiverProcessorUnitLeadingParticulars

AT-801H-FieldBrickAntennaLeadingParticulars

RNZ-850IntegratedNavigationUnitLeadingParticulars

RCZ-850IntegratedCommunicationUnitLeadingParticulars

~

198.14

198.23

198.29

198.31

198.42

198.46

198.52

198.54

198.59

198.59

198.63

198.66

198.67

198.70.2

198.70.3

198.73

198.77

198.86

198.91

198.93

198.94

198.100

22-14-00Listof Tables(Page2)

May25/90Use or ckclosure of mformatlon on thm page !s subject to the restrrct!ons on the tttle page of Ihm d )cument

Honeywell W!MR’ANCECITATION n/V

Table

10-3

10-4

10-5

10-6

10-7

10-8

10-9

1o-1o

11-1

11-2

11-3

11-4

11-5

201

301

401

501

LISTOF TABLES(cent)

W

ML-850MLSReceiverLeadingParticulars

ML-850MLSReceiverARINC429Outputs

RM-850RadioManagementUnitLeadingParticulars

AV-850AAudioControlUnitLeadingParticulars

CD-850ClearanceDeliveryControl/DisplayUnitLeadingParticulars

DI-851DME IndicatorLeadingParticulars

AT-860ADFAntennaLeadingParticulars

AT-851MLSAntennaLeadingParticulars

LP-850LightningSensorProcessorLeadingParticulars

LU-850LightningSensorControllerLeadingParticulars

LU-850SwitchFunctions

AT-850AntennaLeadingParticulars


SystemPerformance/OperatingLimits

GroundCheckProcedure

FaultIsolation

InterconnectInformation

~

198.104

198.106

198.108

198.114

198.118

198.122

198.126

198.128

198.131

198.134

198.135

198.138

198.140

202

303

403

503

22-14-00Listof Tables(Page3/4)

May 25/90Use or disclosure of Information on this page IS subject to the reslrlcllons on the ttlle pagr of thm document

Honeywell WW’’ANCECITATION n/V

INTRODUCTION

ThismanualprovidesgeneralsystemmaintenanceinstructionsandtheoryofoperationfortheSPZ-500CIntegratedFlightControlSystem(System),forthe

I CessnaCitationII or V aircraft.

Thismanualprovidesblockdiagraminformationandinterconnectcliagramstopermitgeneralunderstandingof Systeminterface.

CommonSystemmaintenanceproceduresarenotpresentedin thismanual.Thebestestablishedshopandflightlinepracticesshouldbe used.

Informationon shipping,storage,andhandlingof allsystemcomponentsiscontainedinmanual,HoneywellPub.No.09-1100-01.

Abbreviationsusedin thismanualaredefinedas follows:

Abbreviation Equivalent

ACCELADCADFADIA/DAGCAILALTANNANTAOSSAP,A/PAPP,APRAPSAPSBKARMASASCBATTBAROB/ABCBCDBRGCAPCBCDSCDUCE

AccelerometerAirDataComputerAutomaticDirectionFinderAttitudeDirectorIndicatorAnalogto DigitalAutomaticGainControlAileronAltitudeAnnunciatorAntennaAfterOverStationSensorAutopilotApproachAltitudePreselectAPS BracketArmedAirspeedAvionicsStandardCommunicationBusAttitudeBarometricBankAngleBackCourseBinary-Coded-DecimalBearingCaptureCircuitBreakerDifferentialResolverControlDisplayUnitCourseError

22-14-00Introduction(Paqe1)

May25/90Use or disclosure of InformalIon on this page IS subject to the restrictions on the title page of this documenf

Honeywell MWFAN’ECITATION n/V

Abbreviation

CKTCLKCMDCMPTRCOMCOMP,COMPTRCONTCORRCosCPLCRSCsCTD/ADEGDEMODDETDEV, DEVNDGDHDIFFDISPLDMEDNDRCDUPEADIEHSIEFISEL,ELEVEMIENGEOE OFFEX LOCEXTFD,F/DFDCFLTFMSFR,FRMGA,G/AGND

I GPGS,G/SHDGHORIZHSIIASIDENT

Equivalent

CircuitClockCommandComputerCommon,CommunicationCompensation,Compass,or ComparatorControllerCorrectionCosineCoupleCourseElectricalResolverControlTransformerDigitalto AnalogDegreeDemodulatorDetector,DetentDeviationDirectionalGyroDecisionHeightDifferentialDisplacementDistanceMeasuringEquipmentDownDualRemoteCompensatorDuplicateElectronicAltitudeDirectorIndicatorElectronicHorizontalSituationIndicatorElectronicF1ElevatorElectromagnetEngageEasy-OnEasy-OffExpandedLoca

ght InstrumentSystem

c Interference

izerExtend,ExternalFlightDirectorFlightDirectorComputerF1ightFlightManagementSystemFromGo-AroundGroundGlidepathGlideslopeHeadingHorizontalHorizontalSituationIndicatorIndicatedAirspeedIdentification

22-14-00Introduction(Page2)

May 25/90Use or disclosure of Information on this page IS sub~ect to the restrictions on the tttle page of thm do ;umenl

Abbreviation Equivalent

IFIFCSILSINC-DECINDINSINTLKINTGLINVIVVKN,KTSLLATLBSL/CLHLOCLRNLSSLTGMFDMMMOMMONNAVNCNCDNMNONOCNORMOBSo/cOM0ssPATTPewsPECOPITCHSYNCPRIPROGP/sPwPWRRRA,R/A,RADALTRAMRCVRRBBRCPL

IntermediateFrequencyIntegratedFlightControlSystemInstrumentLandingSystemIncrease-DecreaseIndicatorInertialNavigationSystemInterlockIntegralInverterInstantaneousVerticalVelocityKnotsLeftLateralLateralBeamSensorInductive/CapacitiveLeftHandLocalizerLongRangeNavigationLightningSensorSystemLightingMultifunctionDisplayMiddleMarkerMomentaryMonitorNavigationalNo Connectionor NormallyClosedNo ComputedDataNauticalMileNormallyOpenNAVon CourseNormalOmniBearingSelectorOn CourseOuterMarkerOverStationSensorPitchAttitudePitchControlWheelSteeringPitchErectionCut-OffPitchSynchronizationPrimaryProgrammerPitotSwitchPitchWheelor PulseWidthPowerRightRadioAltimeterRandomAccessMemoryReceiverRollBarBiasRollCouple

22-14-00Intrclduction(Page3)

May25/90Use or disclosure of mformat!on on thts page IS subject to lhe restr,cl(ons cn the title page of th!s documenl

Honeywell i!i};k~ANcECITATION V

Abbreviation

RCVRRCWSRECOREFRETRREV

!!IRN,RNAVRNAPPRSBRT,R/TRUDSBYSECSELSIGSINSPDSRSRNSSECSTAELSTCSTPSYNCTASTCSTKTPTSOTTLVAVALVANGVAPPVBSVGVORVORTACVRVRT,VERT

[?,W/LXMTRYD,Y/D

Equivalent

ReceiverRollControlWheelSteeringRollErectionCut-OffReferenceRetractReverseCourse(Sameas BackCourse)RightHandRadioMagneticIndicatorAreaNAVRNAVApproachRadioSystemBusReceiver/Transmitter,Rateof TurnRudderStandbySecondarySelectSignalSineSpeedSoftRideShortRangeNavigationStaticSourceErrorCorrectionStationElevationSensitivityTimeControlSteepSynchronizationTrueAir SpeedTouchControlSteeringTurnKnobTestPointTechnicalStandardOrderTunedto LocalizerVoltAmpereValidVerticalAngleVORApproachVerticalBeamSensorVerticalGyroVHFOmniRangeColocatedVOR andTacanStationsVoltsRegulatedVerticalVerticalSpeedWingsLevelTransmitterYawDamper

22-14-00Introduction(Page4)

Mar 15/89Use or disclosure of mformatlon on thm page IS subject to the restrictions on the trtle page of this dd:umenl

Honeywell Wi’JkI!’ANcECITATION V

L...2E----COMPLIANCE REQUIRED

Honeywellhasan AirworthinessAnalysisprocedureperformedforall itsairborneproductsto ensurethatequipmentdesignedby Honeywellwillnotcreateahazardousin-flightcondition.As a resultof theAnalysis,certaininstallationshavebeendesignatedINSTALLATIONCRITICAL,and 100percentcompliancewiththoseinstallationsis required.

INSTALLATIONCRITICALis definedas:

Specificmethodsof installationarerequiredto ensurethateitherthefailureof theassemblyor partisextremelyimprobableor thatitsfailurecouldnotcreatea hazardouscondition.

22-14-00Introduction(Page5/6)

Mar 15/89Use or disclosure of mformatlon on thts page IS subJecl to Ihe restrlcttons on the Mle page of this document

SECTION1SYSTEMDESCRIPTION

1. General

ThisSPZ-500CIntegratedFlightControlSystem(Figure1) providesflightdirector,automaticpilot,flightinstrumentation(includinggyroreferencesandflightinstruments),an airdatasystem(includingairdatadisplays,altitudealerting,altitudepreselect,andaltitudereporting}anda weatherradarsystem.

I

Optionalsubsystemsprovidemultifunctiondisplay(Figure2),flightmanagement(Figure3),radiocommunicationandnavigation(Figure4),andlightningdisplay(Figure5).

Table1 liststhecomponentsandpartnumbersthatcomposea standardSystem

IandTable2 listsoptionalsubsystemcomponents.Figure6 showstheapproximatecomponentlocationsfora typicalinstallation.Table3 listsequipmentrequiredbutnot suppliedby Honeywell.

I

Honeywell A/CRefSystemComponent PartNo. Des

VG-14AVerticalGyro

ED-600ElectronicDisplay(EHSI)

RD-450HorizontalSituationIndicator

ED-600ElectronicDisplay(EADI)andInclinometerKit

FX-220FluxValve*

CS-412DualRemoteCompensator

C-14DDirectionalGyro*

FZ-500FlightDirectorComputer

MS-205ModeSelector

AZ-241Air DataComputer

SP-200AutopilotComputer

7000622-901 1

7003430-901 2

7002493-903 C2

7003430-901 37005400-901

2594484 4

2593379-1 5

4020577-3 6

4018369-905 7

4020570-905 8

4013241-931 9

4008519-941(CitationII)10-952(CitationV)

* Denotesdualcomponents.

SystemComponentsTable1

22-14-00Page1

May25/90use or disclosure ‘d Informailon on Ihls page IS sub)ect to the reslrlcllons on [he title paq ! 01 this document

Honeywell M!KYANCECITATION Ii/v

I

Honeywel1 A/CRefSystemComponent PartNo. Des

PC-500

SM-200

S6-201

SM-200

SB-201

SM-200

S6-201

RG-204

VN-212

AG-222

6A-141

AutopilotController

ServoDrive(Aileron)

ServoBracket(Aileron)

ServoDrive(Elevator)

ServoBracket(Elevator)

ServoDrive(Rudder)

ServoBracket(Rudder)

RateGyro

VNAVComputer/Controller

Accelerometer

BaroAltitudeIndicator

RI-106SInstrumentRemoteController

1 RZ-220RollRateMonitor(CitationV only)

IWU-650AntennaandReceiver/TransmitterUnit

WI-650WeatherRadarIndicator

SG-605SymbolGenerator

DC-811DisplayController

4018639-909 11

4006719-906 12

4005842 12A

4006719-904(CitationII)13-914(CitationV)

4005842 13A

4006719-906 14

4005842 14A

7007453-903 15

4020571-904 16

7000992 17

4016341-905 18

4026206-973 23

4015901-920 57

7008470-902,-912 59

7007700-301 63

7011672-606 65

7012977-753 115

SystemComponentsTable1 (cent)

22-14-00Paae2

May 2~/90Use or disclosure of mformatlon on this page IS sublecl to the reslnct!ons on the Mle page of Ihls locument

Honeywell WMR’ANC’CITATION n/V

Honeywel1 A/CRefSystemComponent Qty PartNo. Des

AA-300RadioAltimeterSystemCom~onents

RT-300RadioAltimeterReceiver/TransmitterAT-223RadioAltimeterAntenna(Receive)AT-223RadioAltimeterAntenna(Transmit)

FMZ-800FliqhtManagementSystemComt)onents

CD-800ControlDisplayUnitNZ-61ONavigationComputer ;DL-800DataLoader(CarryOn) 1OZ-800ReceiverProcessorUnit 1AT-801H-FieldBrickAntenna 1

MDZ-605MultifunctionDistIlaY(MFD)Com~onents

MG-605MFDSymbolGenerator 1MC-800MFDControllerED-600ElectronicDisplay(MFD) I

SRZ-850IntegratedRadioSystemComponents

ML-850MLSReceiver 2AT-851MLSAntenna 4RCZ-850IntegratedCommunication 2UnitRM-850RadioManagementUnit 2AT-860ADFAntenna 2AV-850AAudioControlUnit 2DI-851DME Indicator

I

2RNZ-850IntegratedNavigationUnit 2CD-850ClearanceDelivery 1Control/DisplayUnit

ADZ-81ODiqitalAirDataSystemCom~onents

~ AZ-81ODigitalAirDataComputer 1VN-800VNAVControl/Display 1

7001840-91540105044010504

7004403-9017004402-6547004607-9037004608-9017011103

7011673-6067007062-9337003430-901

7510600-9017510638-9017510700-901

7012100-9437510300-9017511001-9017513006-9017510100-9117513000-911

7000700-9487000472-901

120121123141142

125126127

116118143

144158160163164165

916

OptionalSystemComponentsTable2

22-14-00Page3

May”25/90Use or disclosure of mformwon on thts page IS subjecl to the restncl!ons on the tttle pag! of thm document

Honeywell WU’NANCECITATION n/V

Honeywel1 A/CRefSystemComponent Qty PartNo. Des

LSZ-850LiqhtninaSensorSvstemComponents

LP-850LightningSensorProcessor 1 7011822-903 145LU-850LightningSensorController 1 7011865-903 146AT-850LightningAntenna(Teardrop) 1 4057697-901 147

ORAT-855LightningAntenna(Brick) 1 7014062-901 147

PRIMUS@650WeatherRadarComponents

WC-650WeatherRadarController 1 7008471-605 61

NOTE: TheWC-650replacestheWI-650andLU-850.WithouttheWI-650,weatherinformationwouldbe displayedon theEHSIandMFDdisplays.

OptionalSystemComponentsTable2 (cent)

22-14-00Page4

May25/90Use or dmclosure of mtormatlon on thm page IS sub)ect 10 the restrictions on the title page of this document

Honeywell MAINTENANCEMANUALCITATION n/V

WI-SW WEATHER RADAFE INDICATOR8A-141 BAROALTITUDE INO

VN.212 V-NAVCOMPUTER/CONTROLLER

ml

~ VISUAL ALERT“a~~g’e, -

,, 0)..“’ ,,~

DC-S11 DISPLAY CONTROLLERRI-1OSS INSTRUMENTREMOTE CONTROLLER

-~1 1

SELECTEDCOURSE ANDHEADING ED-500 EADI

WU-SSO ANTENNAAND RECEIVER/TRANSMITTER

L

/ ====. -. \

7

L1

.

‘Iii]ED-600 EHSI

.—,“ “! ..!

y ~<j “$7/5, ‘;.’, .

0 !’!... ... . . . . <.@. .:-!“c,, ....-~,,: q,,,, ,,,,.O’.’.,-

CQ2 400,,,

trffi kROMRD-450 HSI(SH2)

AZ241AIR DATA COMPUTER AG-222

ACCELEROMETER-=’==-/ ,/>

.<. e~‘“..,>9/~P. ,;-’

KALTITUDE SYNCHRO OATA

~“/;~ AIRSPEED SIGNAL

.

-

7/

,..--’ ALTITUOE ANO AIRSPEEO SIGNALS

n7!.Ir—————CRS ERROR

.9 mAUTOPI LOT COMPUTER

-..

*

d’ 4

~11P“T’’E’’’’cJR+ * -

~ ++”’’.’”

MODE LOGIC .:., .

0,

4 )

, ,...,,..:, %.

w..+ .

. , . .. .. ..., ,>:, %... Fz-m

FLIGHT

d 7

SWl%%NG

~lt

DIRECTORCOMPUTER

*

ASCB TOOPTIONAL MG-S05(FIG. 2) OR NZ-S1O (FIG. 3)

~rrAIR OATA ERROR SIGNALS

1

TO/FROM SIGNAL TO VN-212

NAV ~AND SG-S05

RAOIOS RAOIO OEVIATION SIGNALS

TO VH-212AND SG-S05

OME OME OISTANCE

RECEIVER

RAOIO AL TITuOE SIGNALS

RT300 RAOIO ALTIMETERREcEIvER/TRANSMITTER w

@. I ‘b]I

,:

ATTITuOE SIGNALS

7

1. .

/.HEAOING SIGNALS

/’”MODE MODE AUTOPILOT

‘. ANN SELECTAUTOPILOT PITCH ANO ROLL

d l“.

Q

LOGIC LOGIC TCAS AND LOGIC COMMANOS.= .;., ,

~i.% * .AP DISENGAGE

,=. . ,r,& -:GO AROUND

(7!!P

-.,...,.-;’-.“ ,

-.. ..’

‘J.

)T’ mPC-5G0 AUTOPILOT CONTROLLER

+&k+&RECEIVE ANT TRANSMIT ANT ““’:GyRO d-”-k

rEEz5xl“..*. “.-,mr . . . .,---- I c1r

w=FLUX VALVE

s-al 2

m.?-... “.””. . ...”. ““

Qlal IITHROTTLES CONIROI

WHEEL

RZ.220 ROLL RATE MONITOR(CIT V ONLY)

DUAIREMOTECOMPENSATOR

C.140DIRECTIONAL GVRO

SystemF1ow DiagramFigure1 (Sheet1 of 2)

22-14-00Page5/6May-25/90lfseor dmclosure Of information on this pageis subject to the reslricllons on the title pageof this document.

Honeywell lNKR’ANcECITATION V

RD-450 HSI

NAVIGATION DATA FROMOPTIONAL RNZ-850 ~NAV UNIT

HEADING OUTPUT~ TO SG-605

SYMBOL GI=NERATOR(SH1)

CS-412DUAL REMOTECOMPENSATOR

m

C-14DDIRECTIONALGYRO

e

I0.s TO SI’-2OO. .

0 AP COMPUTER(SH1:I

COPILOT’SSIDEFX-220FLUX VALVE AD-18742 ?’

SystemFlowDiagramFigure1 (Sheet2)

22-14-00Paae7/8Mar-15/89Use or disclosure of Information on this page K subjeci to the restrictions on the Mle pacje of thts document

DATAFROMDC-811

PILOT’SSENSORS

Honeywell W’W’ANCECITATION V

ED-600MFD

f +

“(~’DTw MAGOlomfi

HD6 FMS1I 2s NE

,jcAEt ~

~Rc IN6S

o y, @J’ o

150310

142.DN 3W 24.2, I’!ANZYU112C6.S, W.] L 20 HIM

GENERATOR

m

WX FROMWU-650FIG.1

ASCBTOSG-605(FIG.1)ANDNZ-61O(FIG.3)

BACKUPFOREFIS

AD-18743MC-800MFD CONTROLLER

OptionalMultifunctionDisplay(MFD)SystemF1ow Diagram

Figure222-14-00

Page9/10Ma~ 15/89

Use or disclosure of information on this page IS subject to the restntiions on the title pal e of this document.

429LS

429LS AT-801ANTENNA

RECEIVERPROCESSORUNIT

TOOPTIONAL

NO.l&2 ‘=RNZ-850

NZ-81OCOMPUTER I i

IIW-422 I

CD-800CONTROLDISPLAYUNIT

I I

I

i L–.RS-422----

~DL-SOODATA

]LOADER

I●

●.6

AZ-81ODIGITAL*COMPUTER

*NOTPART3FFMZ-800COMPONENTS

AD-18744

OptionalFMZ-800FlightManagementSystem(FMS)FlowDiagram

Figure3 22-14-00Page11/12Mar 15/89

Use or disclosure of information on this page IS subject to the restrictions on the title pa~~ of this document.

Honeywell WUY’NCECITATION V

Ki

I

)

FrM-sm RADIOMANAGEMENT

LrNrT W 2

ql-

,

mm m0m ~4- FMa

m m TUNS4Gm m

ncmnoonn

RM-e50 RADs)MANAGEMENT UNIT

D

- (,

m ~-RS422

FMsTUNING

(0/ .. W- , , “.\o ii w 44

I NO. 1 DIGITAL AUDIO BUS 1

T I Ill Alum 42s~ k--o ‘Q-AII I NO 2 DffilTAL AIJDkY BUS, 1

ordsooMElNDrCATORII I

8 I—--- ——-

1 1- 1[!RAOUl SYSTEM BUS

1 I

Iml, y;::

UEAIW4CE-== OELIVEFY

od~ ~L m.—

vFrcz.sYl

INTEGRATEDCOMMUNICATION

UNIT NO 1i

II I IRSA22BuSES

rceNAV DATATO RD-4S0 HSI

rL%sa

RNZ.BW INTEGRATED

w. “/Rcz4.so F .--%’- ““;%’NAVIGATION UNIT ND. 2

L=IleIML-SE41MIS

RECEIVERNo. 1

-f%”’~,~,“----I&GLIDE SLOPE

ANTENNA

T

T!7 T?... 0.........Cl!flGLIDE SLOPE

ANTENNA

a A,,MLS ANTENNASMI-SANTENNAS

tiDME ANTENNA

TRANSPONOEHANTENNA

TRANSPONDERANTENNA

OME ANTENNA

?’11.VofvLocANrEr4NA

\

h.

VorwmcANTENNA

A

\

MARKER SEACONANTENN4\

i

\MARKER SEACON

ANTENNA oCOMM

.00 ANTENNA o-.00 ANTENNA

h-:==&+AT-&30 AOF ANTENNA

AD1622$R1

OptionalRNZ-850IntegratedRadioSystemFigure4 22-14-00

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Honeywell WI’LWANCECITATION n/V

AT-850 LIGHTNING ANTENNA

429 LS DATA

DG VALIDAND 3-WIRESYNCHRO DATAFROM C-1 4DDIRECTIONALGYRO

I MODE

~ TO SG-605 ANDMG-605 SYMBOLGENERATORS

429 LS DATAFROM AZ-81 O

~ DIGITAL AIRDATA COMPUTER

LP-850 LIGHTNINGSENSOR PROCESSOR

IDISCRETES

.

[clo

ST9Y ‘x C,, T!3T 0

a‘“ Q

o 0LU-850 LIGHTNINGSENSOR CONTROLLER

OptionalLSZ-850LightningSensorSystemFlowDiaqram

Figure5 -

AD-21740

22-14-00Page14.1/14.2

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Honeywell MME’*NCECITATION n/V

m

I.-, ...

/.- 4C ‘=-----R-T-T-5A

ITEMNO. NOMENCLATURE

1 LEFT SIDE NOSE COMPARTMENT COMPONENTS:. SP-200AUTOPILOT COMPUTER. AZ-241 OR AZ-810 AIR DATA COMPUTER. C-14D DIRECTIONAL GYRO NO. 1● VG-14A VERTICAL GYRO. AG-222 ACCELEROMETER

(UNDER VG-14A)● RG-204 RATE GYRO. RNZ-850 INTEGRATED NAVIGATION UNIT NO. 1. RCZ-860 INTEGRATED COMMUNICATION

UNIT NO 1.

2 RIGHT SIDE NOSE COMPARTMENT COMPONENTS:. FZ-500 FLIGHT DIRECTOR COMPUTER. SG-605 SYMBOL GENERATOR. RZ-220 ROLL RATE MONITOR. C-14D DIRECTIONAL GYRO NO. 2. RNZ-850 INTEGRATED NAVIGATION UNIT NO. 2. RCZ-850 INTEGRATED COMMUNICATION

UNIT NO. 2

3 WU-650 ANTENNA AND RCVFUXMTR UNIT

ITEMNO.

4

5

6

7

8

9

1011

12

13

14

15

18

17

NOMENCLATURE

Y \ \\

ITEMNO. NOMENCLATURE

ML-850 MLS RECEIVERS

CS-412DUALREMOTECOMPENSATORAT-223RADIOALTIMETERANTENNA(TRANSMITTER)AT-223RADIOALTIMETERANTENNA(RECEIVER)RT-300RADIOALTIMETERRCVR/XMTRAT-660ADFANTENNASOZ-800RECEIVERPROCESSORUNITNZ-61ONAVIGATIONCOMPUTERSM-200SERVODRIVE(ELEVATOR)SM-200SERVODRIVE(RUDDER)SM.200SERVODRIVE(AILERON)SB-201SERVODRUMANDHOUSINGASSYFX-220FLUXVALVESAT-801H-FIELDBRICKANTENNA

ComponentLocationsFigure6

22-14-00Paqe15/16

19

18 INSTRUMENTPANELANDPEDESTALMOUNTEDCOMPONENTS:......

.

.

.

.

.

.

.

.

.

.

ED-600EHSIED-600EADIED-600MFDMS-205MODESELECTORPC-500AUTOPILOTCONTROLLERVN-212VNAVCOMPUTER/CONTROLLERORVN-801CONTROUDISPLAY6A-141BAROALTITUDEINDICATORR1-106SINSTRUMENTREMOTECONTROLLERDC-811DISPLAYCONTROLLERWI-650WEATHERRADARINDICATORRD-450HSICD-800CONTROLDISPLAYUNITMC-800MFDCONTROLLERRM-850RADIOMANAGEMENTUNITSAV-850AAUDIOCONTROLUNITSDI-851DMEINDICATORSCD-850CLEARANCEDELlVERYCONTROIJDISPLAYUNIT

19 MG-605MFDSYMBOLGENERATORAD 18745-R 1

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Honeywell W!’WAN’ECITATION n/V

Functionand Quantity RecommendedDesignation Required Description Source

FastErectSwitchS1

AneroidSwitch*

DirectionalGyroFree/SlaveSwitchS3

DirectionalGyroManualSyncSwitchS4

Pilot’sAP DisengageSwitchS5

TorqueWarningLight

FlapTransitionSwitch

Copilot’sAP DisengageSwitchS6

TouchControlSteeringSwitch,S7,S8

Go-AroundRelayK4

TrimRelaysKl,K2,K3

TCS/TrimRelayK5

l/VG

1

l/DG

l/DG

1

1

1

1

2

1

3

1

SPSTMOM.PushbuttonRatedat 1/2ampInductive

GornPressSW No. ConsolidatedGBC300-55 AirborneSystems

SPSTToggleRatedat 1/2amp Inductive

SPDTMOM.ToaalewithCenterOFF 1~~amprating

NC andNo Rated@ 283 ampsInductive

TradeNo.734165 mA@28V

DPDT

v

MicroSwitch

NC Rated@ 28 V 3 ampsInductive

MOM.N.O.SPSTSwitch ControlsCo.ofRatedat 1/2ampat AmericaSeries28 V dc B9000

NC Rated@ 28 V 3 ampsInductive

DPDTRelaysRated@ 28 V3 ampsInductive

SPDTRelayRated@ 28 V1 amp

* Theaneroidswitchis locatednearthecopilot’srightrudderpedal.

EquipmentRequiredbutnotSuppliedby Honeywell

Table3

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Honeywell U’R’AN’ECITATION n/V

2. SvstemDescription

TheSPZ-500CIFCSconsistsof thefollowingsubsystemswhicharedescribedinI Paragraphs2.AthroughJ.

. Attitude/HeadingReferenceSystem

. ADZ-241AirDataSystemor OptionalADZ-81ODigitalAirDataSystem

. AA-300RadioAltimeterSystem

. EDZ-605ElectronicFlightInstrumentSystem(EFIS)

. FlightControlSystem

. PRIMUS@650WeatherRadarSystem

● MDZ-605MultifunctionDisplaySystem(Optional)

● FMZ-800FlightManagementSystem(Optional)

. SRZ-850IntegratedRadioSystem(Optional)

i ● LSZ-850LightningSensorSystem(Optional)

TheSystemprovidesthree-axisaircraftattitudestabilizationandpathcontrol.Theautomaticpathmodecommandsaregeneratedby theFi!-500FlightDirectorComputerwhichintegratesthe attitudeandheadingreference,airdata,andEFISintoa completeaircraftcontrolsystemthatprovidesthestabilizationandcontrolneededto ensureoptimumperformancethroughouttheaircraftflightregime.

TheSystemdisplaysheading,course,radiobearing,pitchandrollattitude,barometricaltitude,radioaltitude,coursedeviation,glideslopedeviation,to-fromandDME indications.Lightedannunciatorsdenoteselectedflightmodeandaltitudealert. Pitchandrollsteeringcommandsdevelopedby theFlightDirectorComputerinconjunctionwiththeModeSelectoraredisplayedby steeringpointersto enablethepilotto reachand/ormaintainthedesiredflightpathor attitude.

An AvionicsStandardCommunicationsBus (ASCB)is usedto interfacebetweentheSG-605SymbolGeneratorandtheoptional’MG-605MFDSymbolGeneratorortheoptionalNZ-61ONavigationComDuter.Otherdatais transmitt[?don thefollowing

● DC-811bus)

● SG-605buses)

● MC-800bus)

● MG-605bus)

privatelineb~ses: “

DisplayControllerto SG-605SymbolGenerator(privatelineserial

SymbolGeneratorto ED-600EFISdisplays(privatelineparallel

MFDControllerto MG-605MFD Symbo-

MFDSymbolGeneratorto ED-600MFD

Generator(private!ineserial

display(privatelineparallel

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Honeywell [WR’”c’CITATION V

2. A. Attitudeand

TheAttitudecomponents:

HeadingReferenceSystem

andHeadingReferenceSystemis comprisedof thefollowing

. VG-14AVerticalGyro

. C-14DDirectionalGyro

. FX-220FluxValve

. CS-412DualRemoteCompensator

TheVG-14AVerticalGyroprovidesa pitchandrollattitudesignalto theFZ-500FlightDirectorComputerandtheSP-200AutopilotComputerforusein controllingtheverticalandlateralmodesof operation.TheVG-14Aalsoprovidesa 50-millivolt/degreesignalto theMU-650AntennaandReceiver/Transmitterforuse in antennastabilization.Thethree-wirepitchor rollattitudesignalis alsoroutedto theSG-605SymbolGeneratorto providepitchandrollsphereindicationson theED-600EAD1.

TheC-14DDirectionalGyroprovidesthree-wireheadingdatato theSP-200AutopilotComputerforuse inyaw axiscontrolandto t?eSG-605SymbolGeneratorforpositioningtheheadingdialon the ED-60’3EHSI. TherearedualC-14DDirectionalGyrosin thesystem.Undernormaloperationthepilot’sC-14DdrivestheED-600EHSIandthecopilot’slL-14DdrivestheRD-450HSI. Theheadinginputto the SG-605SymbolGeleratorandautopilotcanbe switchedbetweenthepilot’sor copilot’sC-14DwiththeremoteHDGREV switch.

The FX-220FluxValvedetectsthemagnitudeanddirecti~nof theearth’smagneticfieldforuse in aligningtheC-14Dto magneticnorth. TheCS-412DualRemoteCompensatorprovidessinglecycleN-S,E-Wcompensationforthefluxvalve.

B. ADZ-241AirDataSystemor OptionalADZ-81OAirDataSystem

TheADZ-241AirDataSystemis comprisedof thefollowingcomponents:

. AZ-241Air DataComputer

● BA-141BaroAltitudeIndicator

● VN-212VNAVComputer/Controller

TheAZ-241AirDataComputerprocessespitotandstaticpressureinputsandprovidesairspeed,altitude,andholdoutputsto thsflightcontrolsystemandbaroaltitudeto theBA-141.Also,altitudeencodingoutputsareprovidedfortransponderuse.

The VN-212VNAVComputer/Controllerprovidesselectionanddisplayforaltitudealerting,altitudepreselect,andverticalnavigation.

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TheoptionalADZ-81OAirDataSystemis comprisedof the fol””owingcomponents:

. AZ-81ODigitalAir DataComputer(DADC)

. 6A-141BaroAltitudeIndicator

. VN-800VNAVControl/Display

TheAZ-81OAir DataSystemis requiredif theFMZ-800FlightmanagementSystemis installed.TheAZ-81ODADCprovidesthe samefunctionsasdescribedfortheAZ-241butalsoprovidesARINC429datafo!useby theNZ-61ONavigationComputer.

WhenusingtheAZ-81ODADC,theVN-212needsto be replacedby theVN-800VNAVControl/Display.TheVN-800providesthesamefunctionsasdiscussedfortheVN-212. Thedifferenceis thatthecomputationsforthesefunctionsof theVN-800areperformedby theAZ-81ODADC.

2. c. AA-300RadioAltimeterSystem

TheAA-300RadioAltimeterSystemis comprisedof thefollowingcomponents:

● RT-300RadioAltimeterReceiverTransmitter

. AT-223Antenna

The radioaltimetersystemprovidesan absolutealtitudedisFlayforO to2500feetdecisionheightselection,failureannunciation,and internalself-test.

D. EDZ-605ElectronicFlightInstrumentSystem(EFIS)

The EFISis comprisedof thefollowingcomponents:

. ED-600ElectronicDisplay(EADIandEHSI)

. SG-605SymbolGenerator

. DC-811DisplayController

. RI-106SInstrumentRemoteController(IRC)

The EFISdisplayspitchandrollattitude,heading,courseorientation,flightpathcommands,weatherpresentations,andmodeand sourceannunciations.

The SG-605SymbolGeneratoris theheartof thesystemand processesallthedatafordisplayon theED-600EADIor EHSI. TheSG-605alsoprovidesswitchingforback-updatafromtheoptionalMG-605YFDSymbolGeneratorduringthereversionarymode.

The RI-106SIRCprovidesheadingandcourseselectinformationthroughtheSG-605to theFZ-500FlightDirectorComputer.

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Honeywell WE!!’””CITATION n/V

TheDC-811DisplayControllerprovidesthemeansforcontrollingthedisplayformatsandthe intensityof eachED-600display.TheDC-811alsocontainsthebearingselectknobs.

In thecaseof an ED-600displayfailure,a compositeattitude/headingdisplayformatcanbe displayedon theremainingdisplay.

The switchingof navigationsensordatato be displayedis providedelectronically.Allcomparisonmonitoringof criticaldisplayinformationis donewithintheEFIS.

2. E. FlightControlSystem

The FlightControlSystemiscomprisedof thefollowingcomponents:

● FZ-500

● SP-200

● MS-205

● PC-500

● AG-222

s SM-200

● RZ-220

FlightDirectorComputer

AutopilotComputer

ModeSelector

AutopilotController

Accelerometer

ServoDrive(Aileron,Elevator,Rudder)

RollRateMonitor(CitationV only)

The FZ-500FlightDirectorprocessescourseandheadingselect,attitude,airdata,DMEandradionavigationdatato providerolljpitchsteeringcommandsfordisplayon theED-600EADIand roll,airdata,andglideslopecommandsto theSP-200Autopilotforautomaticcontrolof theaircraftsurfacesviatheSM-200ServoDrives. Flightdirectormodeselectionisprovidedby theMS-205ModeSelectorandAP andYDengagement,turnknob,andpitchwheelinputsareprovidedby thePC-500AutopilotController.

TheRZ-220RollRateMonitoris usedto preventtheoccurrenceof anexcessiverollhardoverif an autopilotmalfunctionresultsin asaturatedservoamplifierduringrolloperation.If theRZ-220detectsrollanglesgreaterthan40 degreesandrollratesin excessof 20degrees/see,itwillcausetheautopilotto disengage.

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2. F. PRIMUS@650WeatherRadarSystem

The PRIMUS@650 DigitalWeatherRadarSystemconsistsof the followingcomponents:

. WU-650AntennaandRCVR/XMTRUnit

. WI-650WeatherRadarIndicator

The PRIMUS@650 is an X-Bandradardesignedforweatherdetectionandanalysis.The Indicatordisplaysstormintensitylevelsin b:-ightcolorscontrastedagainsta deepblackbackground.Areasof heaviestrainfallappearinmagenta,nextheaviestappearin red,rainfallof mediumintensityappearsyellow,andareasof weakestrainfallappearin green.Afterproperevaluation,thepilotcancharthiscoursearoun~ithesestormareas. Theradarcanalsobe usedforgroundmapping. IntheGMAPmode,prominentlandmarksaredisplayedwhichenablesthepilottoidentifycoastline,hillyor mountainousregions,cities,or even largestructures.In groundmappingmode,videolevelsof increasingreflectivityaredisplayedas cyan,yellow,andmagenta.Whe~lthePRIMUS@650 is operatedin conjunctionwiththeEFIS,radarvideoisprovidedfordisplayon theEHSI.

G. MDZ-605MultifunctionDisplaySystem(Optiona”

TheMDZ-605MultifunctionDisplaySystemconscomponents:

. MG-605MFD SymbolGenerator

. MC-800MFD Controller

s ED-600ElectronicDisplay(MFD)

)

stsof thefollt)wing

TheMultifunctionDisplaySystem(MFD)presentsdatato the f“ightcrewthatwillenhancetheoperationof theaircraft.Thisdatairlcludesnormalandemergencychecklists,navigationmaps,andweatherradar. Inaddition,theMFD providesbackupcapabilityfortheEFISSG-b05SymbolGeneratorandEFISdisplaytubefailures.

TheMG-605SymbolGeneratoris thefocalpointof informationflowin theMDZ-605System.Thesymbolgeneratorperformstheconversion:necessaryto interfacethismicroprocessor-basedsystemto thesensorsintheaircraft.Thisinformationis thenprocessedusingcomputerTechniquesto filter,scale,storeandreconvertthe informationto the videoanddeflectionsignalsrequiredto controltheelectronbeamon theED-600ElectronicDisplay.

TheMC-800MFD Controllerprovidesa meansforpilotselectiotof displaymodesandformats.

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Honeywell M!’WANC’CITATION V

2. H. FMZ-800FlightManagementSystem(Optional)

TheFMZ-800FlightManagementSystem(FMS)consistsof thefollowingcomponents:

● CD-800

● NZ-61O

● DL-800

. OZ-800

● AT-801

ControlDisplayUnit

NavigationComputer

DataLoader

ReceiverProcessorUnit

H-FieldBrickAntenna

TheFMSprovideslateralandverticalnavigationguidancefordisplayandcouplingto the IFCS. TheCD-800ControlDisplayUnit(CDU)providestheprimarymeansforpilotinterfacewiththe systemanddisplaystheselectedflightplandata.

TheNZ-61ONavigationComputercaninterfacewiththreelongrangesensors,oneviaan ARINC429busandtwoovertheASCBbus. EachNavigationComputercanalsoconnectto dualDME Receiversanda singleVORReceiver.The interfaceto theMFDand EFISis overtheAvionicsStandardCommunicationsBus (ASCB).The interfaceto theAZ-81ODADCandOZ-800RPU is overanARINC429bus. Thelinkto theCDU is overan RS-422private-lineinterface.Withlinksto theon-boardnavigationsensors,theNavigationComputerdevelopsan FMSpositionbasedon ablendor mixof thesensors.TheFMSdoesnotdirectlydisplaynavigationmapson theCDU;however,theFMS is the sourceof mapdataforothercockpitdisplayssuchas EFISor MFD. Displayof mapdataisachievedby theutilizationof the internaldatabaseandASCB1/0. Alargeportionof thenavigationdatabaseis subjectto updatingon a 28-dayinterval.TheDL-800DataLoaderisusedforthispurpose.

Thenavigationpartof the FMSmaybe consideredan areanavigationsystemor RNAV. Itsfundamentalpurposeis to providenavigationinformationrelativeto a selectedgeographicallylocatedpoint.Navigationmanagementwillallowthepilotto definea routefromtheaircraftpresentpositionto anypointin theworld. The systemwilloutputadvisoryinformationandsteeringsignalsto al”lowthepilotorIFCSto steertheaircraftalongthedesiredroute. Routesaredefinedfromthe aircraftpresentpositionto a destinationwaypointviaa directgreatcirclerouteor viaa seriesof greatcircleleg:,connectedbyintermediatewaypoints.

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Honeywell W!’URANCECITATION V

2. I. SRZ-850IntegratedRadioSystem(Optional)

TheSRZ-850IntegratedRadioSystemconsistsof thefollowingcomponents:

. RNZ-850IntegratedNavigationUnit

. RCZ-850IntegratedCommunicationUnit

. ML-850MLSReceiver

. RM-850RadioManagementUnit

● AV-850AAudioControlUnit

● CD-850ClearanceDeliveryControl/DisplayUnit

. DI-851DME Indicator

● AT-860ADFAntenna

. AT-851MLSAntennas(2per system)

Theradiosystemprovidescommunicationandnavigationinformationto theflightcrew. It is a dualsystemconfiguration,withsystemNo. 1 beingthepilot’ssideandsystemNo.2 beingthecopilot’sside.

TheRNZ-850IntegratedNavigationUnitprovidesVHFNAVandPDF receiverandDME transceiverfunctions.TheRCZ-850IntegratedCommunicationUnitprovidesVHFCOMtransceiverandMODES transponderfunction!..Microphoneselection,radioheadsetandspeakeraudioselectionandvolumecontrolareprovidedby theAV-850AAudioControlUnit.

Thebasicradiocontrolfunctionsare:

. VHFCOMmodeandchannel

● VHFNAVmodeandchannel

. ADFmodeandchannel

. Transponderreplycodeandmode

● MLS azimuth,elevation,andchannel

. AudioPanel

. DME (IndependentChannelingintheSplitMode)

Frequencyandmodecontrolof theradioscanbe inputby theoperatorfromeithertheRadioManagementUnit,viatheFMS,or by theClearanceDeliveryCDU.

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Honeywell MNRANCECITATION n/V

Withtheexceptionof theaudiosignalsandemergencytuningcommands,alldataforthesecontrolfunctionsaretransmittedviaa RadioSystemBus (RSB).Audioswitchingcontrolis inputby meansof controAudioPanelitself.The audiosignalsaretransmittedfromtheunitsto theaudiopanelviaa dedicateddigitalaudiobus.

Withtheexceptionof a DME Indicator,allthenavigationdatadisDlavedon theEFIS. A seDarateDME indicatoris ~rovidedwh

s on theremote

sch

displa~sthedistance,groundspeed,time-to-station;and stationidentifier.

Basicto theoverallsystemdesignareclustermodulesin theCOMandNAVremoteunits. Theclustermoduleis an interfacingelementwhichcollectsdatafromtheRSB,distributesthisdatato therespectivefunctionalmodules(ADF,DME,etc.)viaRCB,andalsocollectsdataviaRCBfromthefunctionalmodulesto be broadcaston theRSB.

TheRM-850RMUbroadcastsmessagesaddressedto radiofunctionalmodulesandreceivesdatafromtheradiosviatheRSB. ThreemajorfunctionsoftheRMUareto outputtuning(channelor frequency)controldata,outputoperationalmodecontroldatafortheradios,anddisplaythetunedactivechannelor frequencyandoperationalmode.

The RSBis a highspeed(667kHz)multi-userbusthatallowsallradiosandcontrolheadsto broadcastdataon thebusforthe aurposeof tuningradiosto thedesiredchannelor frequencyforaircraftcommunicationandnavigation.Threebusesareusedforredundancyin theeventthatoneormorebusesbecomeinoperativeforanyreason.

Physically,RSBconsistsof threeseparatemulti-userserialhalf-duplex,digitalcommunicationsbuses. Eachbusis electricallyisolatedfromtheothers,andallbusesareelectricallyisolated(transformercoupled)fromthecircuitryinsidetheunitsinstalledon thebus. Eachbus isterminatedat eachendwithan appropriateterminationnetworkasshowninSection6, Table501,Figure4-9.

The busisconnectedin a mannerthatoneprimarybusservesallof theradios.Twosecondarybuses,oneforeachside,servetheradioson thatsideonly. By connectingthebusesas shown,onlythreecontrolbusconnectionsthroughthepressurebulkheadareusuallyrequired.

TheRSBhasno buscontrollerscommandingusersto transmitdata. Usercomponentsknowwhentheyshouldtransmitby havingsynchronizedthemselvesto broadcastson thebusandarecontinuallydesynchronizingtheirclocksto validbroadcastson thebus. A validbroadcastisdefinedas a transmissionthathasthecorrecttransmitaddressandhasoccurredin a timeslotdefinedforthataddress.

Lossof theprimarybusonlyeliminatesthecross-sidecontrolfeature.InthateventtheRMUSor controlheadscanno longertunetheiroffsideradios.However,no radiofunctionsarelost. Theradioson bothsidesarestillfullyfunctionalviatheirsecondarybuses.

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Honeywell MVJEJANC’CITATION n/V

2. J. LSZ-850LightningSensorSystem(Optional)

The LSZ-850LightningSensorSystemconsistsof thefollowingcomponents:

. LP-850LightningSensorProcessor

. AT-850/855Antenna

. LU-850LightningSensorController

. WC-650WeatherRadarControllercontainingLSSswitch(usedinplaceof LU-850)

The LightningSensorSystemdetectslightningactivityin theregionaroundtheaircraftwithin100NM anddeterminestherangeandbearingofeachlightningdischarge.A symbolplandisplayisgeneratedwithspecialsymbols,as shownin Figure7, andthesesymbolsareIdisplayedinconjunctionwithweatherradardisplayson theEHSIor MFD.

The LU-850or WC-650Controllercontainstheswitchusedfor theselectionof themodesof operation.

9WHITE

LEVEL 1

BWHITE $WHITE

LEVEL 2 LEVEL 3

LightningSymbolsFigure7

bMAGENTA

ALERT

AD 13983R4

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Honeywell W’E’ANcECITATION n/V

SECTION2COMPONENTDESCRIPTION

1. General

Thissectionprovidesan illustration,leadingparticulars,a briefdescription,anda blockdiagramor schematicof eachcomponentusedintheSystem. The informationisonlyforthespecificcomponentslistedinSection1, Table1. Whena componentpictureutilizescallouts,thedescriptionforeachcalloutis presentedwithupperleft-handcalloutdescribedfirstandproceedingclockwiseunlessit is a minoritemgroupedwitha majorcallout.

Thecomponentsareseparatedintothefollowinggroupsor subsystems:

Subsvstem Paraqra~h

AttitudeandHeadingReferenceSystem 2

ADZ-241andOptionalADZ-81OAirDataSystem 3

OptionalAA-300RadioAltimeterSystem 4

ElectromechanicalFlightInstruments 5

EDZ-605ElectronicFlightInstrumentSystemandOptionalMDZ-605MultifunctionDisplaySystem 6

FlightControlSystem 7

PRIMUS@650WeatherRadarSystem 8

OptionalFMZ-800FlightManagementSystem 9

OptionalSRZ-850IntegratedRadioSystem 10

OptionalLSZ-850LightningSensorSystem 11

NOTE: Referto thecontentssectionin thefrontof thismanualforalistingof eachcomponentcontainedin eachsubsystem.

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Honeywell URVJEPANCECITATION V

2. AttitudeandHeadinqReferenceSystemandRateGvro

A. VG-14AVerticalGyro(SeeFigures2-1 and2-2,andTable2-l.)

The Gyroprovidesthree-wiresynchrooutputsthatareelectricalanalogsof theaircraftDitchandrollattitudes.Pitchqimbalfreedomis t80degreesandroll’gimbalfreedomis unlimited. -

VG-14AVerticalGyroFigure2-1

Dimensions:

Length......................................... 9.38in.(238.3mm)Width.......................................... 6.75in. (171.5mm)Height......................................... 6.19in. (157.2mm)

Weight(maximum)....................................... 7.3lb (3.3kg)

PowerRequirements:

Primary.................... 115V, 400Hz,80 VA startand40 VA run

MatingConnector:

lJ1 ................................................. MS3126F22-55SY

Mounting.................................................... HardMount

VG-14AVerticalGyroLeadingParticulars

Table2-122-14-00

Page102Mar 15/89

Use or dkclosure of information on this page is sub)ect to the restrictions on the title page of thi: document.

Honeywell WR’AN’ECITATION V

1J21 ) F 5V, 400 Hz OUTPUT

26 V. 400 HZ OUTPUTI ) E

1 J2

c++-

,115 V,400HZINPUT POWER

<l,& 26VAC I

F+28VDC

1> D1

III

I

I

I

+28VDC OUTPU1

- +20VDCUNREGULATED

J*+10VDC

POWERSUPPLY +15VDC PRECISION

REFERENCE

J-~ POWERSUPPLY

–15Voc* B+(+13VOC)

——_r—— ‘-’-’”’”;

MONITORFLAGINTLK

AUTOPILOT INTLK

+10 Voc

POWER GN13 J

EXTERNALPECO INTLK

R

r-rL+28vDc!1-

1I

II

CHASSISGND+28VocI I *

GYROMOTOR

WHEELSPEED

MONITORr

115 V,400 Hz

I * I

I

+?+MEXTERNALFASTERECT

I

EXTERNALPECO PITCHTOFKNJER

CONTROLFIELDAMPLIFIES

>?

B5 PITCHTORQUER

W/kPITCHERECTLEVELSWITCH DIFF ~ !@

S1 * AMPL *

L hKi

+28VDC

I

I

IIIT 26 VA’ I( I

4)w

,

ROLLTORCIUEFICONTROL FIELO

ROLL ERECTLEVELQIIVITCH

OIFF+ AMPL

1

NOTES:

1.ALLRELAYSARESHOWNINDE-ENERGIZEDPOSITION.

2. UNDERLINEDLETTERDESIGNATESA LOWERCASELETTER

3.PINS1J2.A,G K M AND~ARE TESTPOINTS#_, _,ANDARENOTNORMALLYCONNECTEOWHENTHEGYROISINSTALLEOINTHEAIRCRAFT.TESTPOlNTSlJ2-~ANDQ,NOTSHOWN,AREALSONOTCONNECTEDINTHEAIRCRAFT.

4. EXTERNALGRADIENTADJUSTMENT

5.PlNSlJ2.sAND ~AND,lJ2-AAAND BBARENORMALLYJUMPEREDTOGETHERTOOBTAINTHE200mVAC/DEGOUTPUTGRADIENT.

EXTERNALRECOINTLK

RECOCONTROLlNORMALLyJUMPEREOTO1J2-J)

AOl19@R2oA

VG-14AVerticalGyroBlockDiagramFigure2-2 (Sheet1 of 2) 22-14-00

Paae103/104“Mar15/89

Use or disclosure Of reformation on Ihm page !s subject 10 the restrictions on the tttle page of Ihls documenl.

Honeywell Mi’E’ANcECITATION V

RECOOISABLE

i% ~tilNALR ECO

1J2A <,

1A

I

tROLL

I+ ERECTION

CUTOFF1J2

I

DETECTOR 1)

I

~ <u

T t

26 VAC

26 VAC

+15VIX-vv%-J

ROLLSYNCHRO

9

7

10

JT2B 13

3I

I

‘(N0TE4)(H)

T (c)%&&

(c) >

(H)

(x)I :

* i-

PITCHSYNCHRO

s

*

1

72 I(c) \1“

I

Ilx) .1

1 (Y)I >

A (z)II T >

VG-14AVerticalGyroBlockDiagramFigure2-2 (Sheet2)

22-14-00Page105/106

RECOCONTROLJ (NORMALLyJuMPEREO

TO 1J2-H)

ccBBAA

EE

llo

ROLLFDOUTPUT(200mVAC/DEG)(SEENOTE5)

ROLLRADAROUTPUT(50mVAC/DEG)

ROLLSYNCHROSTATOROUTPUT@OOmVAC/DEG)

PITCHFDOUTPU1(200mVAC/DEG)(SEENOTE5)

PITCHRADAROUTPUT(50mVAC/DEG)

PITCHSYNCI-IROSTATOROUTPUT(200mVAC/DEG)

ADl19@

‘Mar15/89Use or dmclosureOf reformationon this page is sublect to the restrictionson the I!tle page of this document.

Honeyell H!HRANCECITATION V

Thispageis intentionallyleftblank.

22-14-00Paqe107Mar-15/89UseordisclosureOf mformatlon on thK page is sub!ect to the restrictions on the title pag ? of this document.

Honeywell M!Ml!’”c’CITATION V

2. B. C-14DDirectionalGyro(SeeFigures2-3and2-4,andTable2-?.)

TheC-14DDirectionalGyroprovidesthree-wiresynchroheadinginformationto theED-600EHSI,copilot’sRD-450HSI,andtheAutopilot.In addition,a remotelymountedAUTO/MANswitchcontrolscompassslavedor nonslavedmodesof operation.A remotelymountedslewswitch(LH/RH)is usedto aligngyroheadingin caseof lossof theslavingamplifier.

A powersupply/staticinverter,whichoperatesofftheaircraft28 voltsdc power,is housedin thebaseof thegyro. The staticinverterprovidesoutputsof 115volts,400Hz and26 volts,400Hz.

(==I

C-14DDirectionalGyroFigure2-3

22--14-00Page108Mar-15/89Use or disclosure Of information on this page is subject to the restrictions on the tttle page of this document.

Honeywell UNJEPANCECITATION V

Dimensions

Length

(maximum) :

......................................... 9.03in. (229.4mm)Width.......................................... 6.25in. (158.8mm)Height......................................... 7.22in. (183.4mm)Height(shockmountsextended)................. 7.50in. (190.5mm)

Weight(approximate)................................. 6.7lb (3.04kg)

PowerRequirements:

primary ............................................... 28f3VdcStarting................................................... $~~~Running......................................................

GimbalFreedom:

Vertical(Azimuth)........................................ 360degHorizontal(PitchandRoll) ................................ ~85 degSlavedaccuracy............................................. *2 degGyrofreedrift(exclusiveof earthrate)............... *24deg/hrSlavingrate(normal)........................... 2.5to 5.0deg/minSlewrate(automaticfastor manual).................... 30 deg/min

MatingConnector.......................................... MS3126F20-41S


C-14DDirectionalGyroLeadingParticularsTable2-2

22-14-00Page109/110

Mar 15/89Useordisclosure Of information on thts page is sub~ect to the restrictions on the Mle pagl! of lhls document.

Honeywell WW’ANcECITATION V

~

—— —— —— —— ——- —— —— —C-14DGYROSYNCOMPASS

——1 ~2——— ——— ——— ——— ——— ——— ——— ——

GYROAND SYNCHRONIZER

I11

-i{

+ u(+)I ANN

AMPLANNUNCIATOR

r-——— —-—— ———— —--— ———— —--- ; +V(-)I 1 I

--tr SLAVING—— ——— —_—

1Lb”

—— -- -— -- —Ill

I

I

I ~ 11I I

I I u--tDEMOD I

!11

I

CIRCUITI

1 I

:~

n~:&R ‘~+24v”MANUALSYNCSW (+)

# -~ -rPOWERADEQUACYI

WHEELSPEED

MONITOR

IIll

yIIII

iI IL —— —— —— —— —

POWER

HGYRO

SUPPLYAND CIRCUITRECTIFIER (Bl AND B5)CIRCUIT (L1 THRU L4)

q--

Il.

–1 II

I

e

{}+ H 26V,400Hz (FROMBASE)

I CXNO.1

II

I +’II

t{}

~ jK(Z)-. 62 ● L (X) HEADINGOUTPUTNO.1

II II , +“(y)

~ p+-i-j-{3:}2’v‘--~*{~E]HEADINGOUTPUTNO.Z

1 I1>,

S 26 VAC FLUX VALVE EXCITATION

*s16 I

I I11 I

-—; IK2

I

l!

=1 Ill——— ——. — . —–—–—–i- I I

POWERWARNING(VALID)

AUTOPILOTINTERLOCK

i

I I —— —— —— —— —— .— ————— —— —— —— —POWERSUPPLY/STATICINVERTER (BASE)Ir -IiI 7~, I III

+26VDC c FILTER 400 Hz 1 STAGE PUSH-PULL AU~OMATIC POWER

‘1T

AND PUSH-PULL ~ PUSH-PULL CLASSB LEVEL TRANSFORMERVOLTAGE CONTROL 1m ~

LIC OSC CLASSB POWER AND26 VDC GND B LIMITER AMPL AMPL AND ZENER 1 1

REFERENCEOUTPUT A

l— I t II

,II

I ~

LL

J——— ——— ——— ——— —-—— ——— ——— ————— —— ..— ——— —— ——— — J

C-14DDirectionalGyroBlockDiawamFigure~-4

I 1i

1W 5V,400HZ LIGHTING

22-14-00

115V, 400 Hz

26V, 400 Hz (TO CX1,CX2ANDSYSTEM)ACPOWERRETURN

FREO/PHASELOCK

25755-R4

Page111/112Mar 15/89

UseordisclosureofInformationon this page is subject to the restrictions on the Idle page of Ihm document.

Honeywell !NJRANCECITATION V


22-14-00Page113Mar 15/89

Useordisclosureofln~orma~iononthfspage1ssubjecttotherestrictionsonthetitlepag~?ofthisdocument.

Honeywell M!iKR’ANcECITATION V

2. c. CS-412DualRemoteCompensator(SeeFigures2-5and2-6,andTable2-3.)

The DualRemoteCompensatorcompensatesthefluxvalveby insertingsmalldc voltagesto canceltheerrorscausedby magneticdisturbarlces.

CS-412DualRemoteCompensatorFigure2-5

Dimensions(maximum):

Length......................................... 5.62in. [142.7mm)Width........................................... 2.56in. (65.0mm)Height.......................................... 2.99in. (75.9mm)

Weight(maximum)....................................... l.Olb (0.45kg)

Powerrequirements................................. 26V, 400Hz, 2.5VA

MatingConnectors:

J1 .................................................. MS3126F14-19SXJ2 .................................................. MS3126F14-19SY

CS-412DualRemoteCompensatorLeadingParticularsTable2-3

22-14-00Page114Mar-15/89Use or disclosure of information on this page is subject to the restrictions on the title page of this document

Honeywell ~#!jJErANcECITATION V

SCREWDRIVERADJUSTMENTS

r —— —— -1 ~m

26 V, 400 Hz

INPUT POWER

I+6.6VDC

[?’

J1 (H)D

I

REGULATED

DC PDWER

~ l(c)) t

SUPPLY IE

IT -6.8 VDC>

II

I I

ICURRENT

LIMITING

RESISTORS

FLUX VALVEJ

III

I I

.— —

NO. 1J1 I

r!!iiE~~~’

F.

A.

DC

B< ; A BLOCKING

CAPACITORSc

I

L —— —— —— —— —— —.,.

NOTE, THE DUAL REMOTE COMPENSATOR CONTAINS TWO IDENTICAL COMIPENSATIONCIRCUITS. CIRCUITRY AND CONNECTIONS SHOWN ARE FORTHENUMBER ONESYSTEM THROUGH CONNECTORJ1. CIRCUITRY FOR THENUWBERTWO SYSTEMISIDENTICALTO SYSTEM NUMBER ONE, EXCEPT CONNECTIONS AREMADETHROUGH CONNECTOR J2.

I

1.*1 J1 K

TO

FLUX VALVE

:~CT

J

25756. R4

CS-412DualRemoteCompensatorBlockDiagramFigure2-6

22-14-00Page115Mar-15/89Useordisclosureofinformationonthispageksubjecttotherestrictionsonthetitlepa$l~ofthisdocument.

Honeywell KIURANCECITATION V

2. D. FX-220Flux Valve (See Figures 2-7 and 2-8, and Table 2-4.)

The fluxvalvedetectsthemagnitudeanddirectionof theearth’smagneticfieldandconvertsitto electricalinformationwhichis used toalign the directional gyro to magnetic north.

w.

FX-220FluxValveFigure2-7


Bowldiameter ................................. 3.58in. (90.93mm)Mountingflangediameter....................... 4.80in. (121.9 mm)Height .......................................... 2.88 in. (73.15 mm)

Weight(maximum)....................................... 1.5lb (0.68 kg)

Power requirements ........................ 26.0f O.05V, 400Hz, 1.lVAsingle-phase

.

Mounting ........................... Nonmagnetic machine screws, 6-40 by3/8 in.roundhead,PartNo.319011

FX-220FluxValveLeadingParticularsTable2-4

22-14-00Paae116Mar”15/89UseordisclosureOfinformationonthispage is subject to the restrictions on the title page of this document.

Honeywell U2TJEFANCECITATION V

:]=i::$.F SHIELD

B

c.1800 ~Z

SIGNALOUTPUT

371s

FX-220Flux ValveSchematicFigure 2-8

%2-14-00Page 117Mar 15/89

Useordisclosureof reformation on this page IS subpct to the restrictions on the Iltle page of this document.

Honeywell lWR’ANcECITATION V

2. E. RG-204RateGyro(SeeFigures2-9and2-10,and

The RateGyror)rovidesa rate-of-turnsiqnalto

Table2-5.)

theEADIproportionaltotherateo; angulardisplacementabouta~ axisperpendicular”tothemountingsurface.

RG-204RateGyroFigure2-9


Length ......................................... 3.32in. (84.3mm)Width .......................................... 2.04 in. (51.8 mm)Height .......................................... 1.82 in. (46.2 mm)

Weight................................................. 1.0lb (0.45kg)

MotorPowerRequirements

Excitation(400Hz) ........................................ 26 V acPower (running) ............................................. 6.5 VARunuptime(maximum)......................................... 90 secPhase........................................................ Single

Sense,polarity (input axis down, cw rate)(rate viewed from top) ......................... Positive

Mating Connector .......................................... TedMfgB1700

Mounting .................................................... Hard Mount

RG-204RateGyroLeadingParticularsTable2-5

22-14-00Page118Mar-15/89

Use or dwclosure Of information on this page K subject to the restrictions on the title page of this c!ocument.

26 VAC400H2

Honeywell Mfiw;kp’”c’CITATION V

———— —— .——.‘—–—K

4([H) ,

(c)2

3

=

*mvAc.44si Hx

*FwR SUPPLY OEMoo AMPL

= GYROe WHEEL SEEO

-IToR

4

51}GYRo oc‘% ~{L] VOLTAGE

40*0.4 VOCAT60SGSEC

~}

(L)-D GVRIFLFL:Hl+ 4.S*O.SVW

——— ——— ——— ——— —— P ~sz

RG-204RateGyroBlockDiagramFigure2-10

22-14-00Page 119Mar-15/89Useordisclosureofinfofrnatlononthis page is subject to the restrictions on the title page of thm document.

Honeywell MfiWJfPANcECITATION V

3. ADZ-241andODtionalADZ-81OAirDataSystem

A. AZ-241Air DataComputer(SeeFigures3-1 and3-2,andTable3-l.)

TheAir DataComputer(ADC)receivesinputsof staticpressureandpitotpressurewhichit utilizesto produceelectricaloutputsignalsfor airdata displays, altitude transponder, flight director, and the automaticflight control system.

AZ-241AirDataComputerFigure3-1

22-14-00Page120Mar 15/89Use or disclosure of information on this page is subject to the restrictions on the title page of this drcument.

Honeywell uirJErANcECITATION V


Length......................................... 15.19Width............................................ 3.59Height.......................................... 7.63

n. (385.8mm)in. (91.3mm)n. (193.7mm)

Weight(maximum)...................................... 10.O lb (4.54kg)

PowerRequirements................................. 115V, 400Hz,40 VA

MatingConnector:

J1 ............................................... DPXBMA-67-33S-O068

Pneumatic Connectors:

Pitot (straight) ........................ MS24393-4 and Nut MS24400-4Static (straight) ....................... MS24393-6 and NutMS24400-6Pitot(90”)............................. MS24394-4andNutMS24400-4Static(90”)............................ MS24394-6andNutMS24400-6

Mounting............................ Tray,BarryPartNo.404A-38-S-DPXB

AZ-241AirDataComputerLeadingParticulars

Table3-1

22-14-00Page121/122

Mar 15/89Use or disclosure of information on this page IS subject to the restrictions on the Mle page ~f this document.

Honeywell M!E!’AN’ECITATION V

DC llME IEST

SMno [/c~----------:,~oc, ,,

+15-15vDC~( -E3 -,5

1 I —.- ,., .1 !,

I

I

, ~––––––– ——— ——— GNEJ+)A++15+0>

-Is+f>

+15 REF-p M>

~1

Ii

1 lAi A5 SENSORI ~___–––– J p:::s:N___

$==—-—A.1.

—ML.—— — ——— ——— .—— ———— ———— -

L.-’-;-534::”LII<A111-

-101.EF 9 +

8~.,:< ,. , ,,. -*5A” “z””

uI A7 AIRSPEED sENSOR +1

I––-. _.–––_____-l

fi6-sGTc FREsGnrsTNGr––– –––––––––––– –-– -,

:~ +’GNO c

+15

-15

6MD SEN

+15REF

r-FH+ ‘ ‘I HP ;

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60( , <H; (I

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=b+’ ... w--p” ‘;>16463 LC All

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SSEC INPU1BA RO (W)

8An0 LOW

OARO DISABLE

——

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54

~

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I

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L__—_—— —————— —————— ___A>-3

Al 15

44-.4:

rp,o~5——— ———1

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Figure3-2 (Sheet1 of 3)

L — — ——— —.

E4021354-1-E

22-14-00Paae123/124“Mar15/89

Use or disclosure of information On thts page is subject to the reslricllons on the title page of this document,

Honeywell Wi!!frANcECITATIONV

-i --L..———.— — —..—

1. ..— —— —————— —— —___ ______ -———,

S“PPLV I.—— — ———— —.. 1

* Efk+Q+”F’.15 “LX RCF’

● 20 —r-! ‘“+‘“RCGULA1OR-zo~+20 Vc~-23Pu+3 Pm-33PR

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{

(M) 3

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(L) ●

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I

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’15 ‘+6+- -@$ vDC !: Gwn L.’w>- J

I

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IL

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I

I

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IioLo OUTPUT (

ALT CN6AGE

AL1 RATE ENCA

A/s CNG

●?.-55

A?. 44

SL[W fMCJ

5LCW COMIP.OL

140L D REF

1;L————————.—— ——————————————————J It

1’L__———— —-———————————————J J I

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AZ.33

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.— .—. . — h3.14

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AZ-241AirDataComputerBlockDiagramFigure3-2 (Sheet2)

22-14-00Page125/126‘Mar15/89UseordisclosureOf Information on this page is subject to the restrtctlon$ on the title page 01 this document.

Honeywell FA!ME!ANCECITATION V

A6 h

W.A

————————- _—_——.————..— —___ ___ _=Oc lC TIME A*

I

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+46* s , .?I

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L!———————————

r -i 3— 7L:1U—OE—DCIIIZER — — — ———— — — — — — — ———— —-— ———— —

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E4021354-3-E

‘Mar15/89UseordisclosureofIntormatlononthispage is subject 10 the restrictions on the title page of Ihls document.

Honeywell !fA!W’”c’CITATION V


22-14-00Page129Mar 15/89

UseordisclosureofInformationon~hkpageIS subjecttotherestrictionsonthetttlepage of fhls document

Honeywell WVR!ANC’CITATION V

3. B. BA-141BarometricAltitudeIndicator(SeeFigures3-3and3-4,andTable3-2.)

POINT

In’% -

ALTITUDEALEFT

,,, a ‘NNuNc’ATOR

><Q“’i,,

eq::ARNNG

/. : COUNTER

BARO

‘ETKNOBk@i!r~r

BARO COUNTERS31710

BA-141BarometricAltitudeIndicatorFigure3-3

Dimensions (maximum):

Length (from rearWidth ............

of bezel)...................... 6.65in. (168.9mm)................................. 3.28in. (83.3mm)

Height............................................ 3.28in. (83.3mmj

Weight(maximum)........................................ 2.8lb (1.27kg)

PowerRequirements:

Primary ........................................... 26V, 400Hz, 4VAAlt Alert .................................................... 28 V dcLighting ................................................ 5Vacordc

Mating Connector:

J1 .................................................... MS3126F20-41SW

Mounting .................................. Clamp, MSP Inc,PartNo.64409

BA-141BarometricAltitudeIndicatorLeadinqParticulars

T;ble 3-222-14-00

Page130Mar-15/89Useordisclosureofinformationonthispageissubject10therestrictionsonthetitlepageofthisd(,cument.

Honeywell

TheBarometricAltitudeIndicatordisplayof barometricallycorrectprovidesthefollowingdisplays:

3. B. (1)

(2)

(3)

(4)

(5)

AltitudeAlertAnnunciator-

MAINTENANCEMANUALCITATIONV

providesa servoedcounterdrum/pointerpressurealtitude.The Indicator

The liqht illuminates to ctrovide avisualindicationwhentheaircraft-iswithin1000feetof thepreselectedaltitude,andextinguisheswhen the aircraft is within250 feet of the preselected altitude. After capture, the light willilluminate if theaircraftdepartsmorethan250feetfromtheselectedaltitudeandwillextinguishif theaircraftdepartsgreaterthan1000feetfromthepreselectedaltitude.

FailureWarningFlag- Thefailurewarningflagcomesintoviewwhentheerrorbetweenthe altitudedisplayedandthealtitudesignalreceivedis toogreat,theADCgoesinvalid,or theBarometricAltitudeIndicatorlosesprimarypower.

AltitudeCounter- The four-drumcounterdisplaysaltitudefromO to50,000feet. A negative(NEG) altitude shutter obscures the 10,000and 1000 digits of the counter to annunciate altitudes belowsea1evel. The “O”positionon theten-thousandsdrumis blackandwhitecrosshatchto alertthepilotto altitudesof lessthan10,000feet.

BAROSetKnobandBAROCounters- Thebarometriccounters,setbymeansof theBAROknob,displaybarometricpressurein inchesofmercuryandmillibars.SettingtheBAROknobprovidesBAROcorrection,tothe airdatacomputer.

Pointer- Thepointerdisplaysaltitudesbetween1000-footlevelsona scalewithmajorindicesevery100feetandminorindicesevery20feet.

22-14-00Paqe131/132“Mar1’5/89

Use or disclosure of reformation on this page IS subject 10 the restrictions on the title page of thts document.

Honeywell H!K!!’”c’CITATION V

CCM7SE AL1FROM mc ‘r

IBARO CORRECTED)

‘2.6 Voc +0.2 rnvoc/Fr

+lSVOC ~FRDM ADC

FINE AL1

{

SIN U

FROM ADC[SARO

CosvCORRECTED)

cm w ipya IC LIMITERAND

DEMOD 1-/j!*I I ==I I

I II I

I

CHASSISGNo G

hi

““ND ‘h [=

c1WAS

MONITOR

LIGHTINGSYSTEMmwER

-10 Voc

GNO

30 Voc

GNO FROMALT ALERTCONT

28 VDC I IOATA VALIO &

I1

FROM AIJC I II L--.------—-———- ------- ——— ---- ----

5VOCISV6C A t&&.t-ki--q:’

‘“~DTm-%%---g ! @jp;:&o =

B

@

1

POINTER

I

.3241 I2 L-----

-—---——-—- . J

I

~~ K%A%:%4UY

.,,

BA-141BarometricAltitudeIndicatorBlockDiaaramFigure ~-4

22-14-00Page-133Mar 15/89

Use or disclosure of reformation on this page is subject to the restrtctlons on the title page of thts document.

Honeywell tiill~~p’”c’CITATION V

3. c. VN-212VNAVComputer/Controller(SeeFigures3-5 and3-6,andTable3-3.)

{ >

@mifE;LT:FR

\o)(1,

vANGDEG

01 M

\o o,25744-RI

VN-212VNAVComputer/ControllerFigure3-5


Length.......................................... 10.53in.(267.5mm)Width............................................ 3.37in. (85.6mm)Height........................................... 1.65in. (41.9mm)

Weight(maximum)....................................... 2.51b (1.14kg)

PowerRequirements:

Primary........................................ 115V, 400Hz, 16VALighting......................................... 5Vacordc,2VA

MatingConnector:

J1 ................................................. JT06RE16-35S(SR)

Mounting................................. Clamp,MSP Inc,PartNo.64321

VN-212VNAVComputer/ControllerLeadingParticulars

Table3-3

TheVNAVComputer/Controller(VNCC)providesdatainsertionsanddisplaysforaltitudealerting,altitudepreselect,andVNAVmode.

Altitudeis selectedby placingtheselectorswitchto ALTandslewingtothedesiredvalue,andtheALT SEL button selected on the ModeSelectorwillinitiatealtitudepreselect.To utilizetheVNAVcomputationcapability of the VNCC,thepilotmustsetthe stationelevation,to-fromdistance,andgo to the VANG position after selecting the desiredaltitude.

22-14-00Page134Mar15/89

Use or dwclosure Of Information on this page is subject to the restrictions on the Mle page of this d >cument.

Honeywell WXRAN’ECITATIONV

lJ11> 23, 22 ALT AND VERT ERROR VALID

18 ALT ALERT HORN ANO LIGHT

ALT ERROR <1000 FT GND (KALT)

TO/FROM NULL GND

I

I

I 17,TO/FROM

lJ1

TO/FROM 30 I

~

I

II

RANGE VALIO 331

I1)20

POWERREADY●

POWERSUPPLYCARD

Al

ONE-SHOT●

I 1 24

ICLK 1, 2, 4, 5● 1

3.OIGIT DEC DRIVE

RANGE VALID●

OATA BUS DO-07

-’l

DISPLAYCARD

A4

DIGITALCARD

A2 DASH AND DEC POINT DRIVE●

I

ALT AND VERT ERROR VALIO●

✍✍❉

STAEL

VANG●

POT VOLTAGES●

CLK4

STAELm*

-i

TO BIASVNAV MODE GND

RNAV MODE GND

AIR DATA VALID

COARSE ALT REF

29

32

36

14

34

37

40,

m--i

FROM BIASANALOG

CAROA3AID COMP

4TO BIAS

o

FROM BIASaDC

SLEW RATE*RANGE

DC COARSE ALT

FINE ALT(SIN AND COS)

AIR DATA AC REF

41\l

36 I4 -25 .27 ALT ANO VERT ERROR

25S66

VN-212VNAVComputer/Control1erBlockDiagramFigure3-6

22-14-00Paqe135/136‘Mar15/89

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Honeywell W!URANCECITATION V


22-14-00Page137Mar-15/89UseordisclosureofInformationonthispage IS sublecf to the reslnchons on the title page of this document.

Honeywell WNR’”c’CITATION V

3. D. AZ-81ODigitalAir DataComputer(SeeFigures3-7 and3-8,andTable3-4.)

NOTE - TheAZ-81Ois a replacementfortheAZ-241ADC when using the‘“ FMZ-800FMS.

AD 3037

AZ-81ODigitalAirDataComputerFigure3-7

22-14-00Page138Mar 15/89Useordisclosureof mformatlon on this page IS subject to the restrictions on the title page of thw d>cument.

Honeywell ~iw!FrANcECITATION V


Length......................................... 15.76in. (400.3mm)Width............................................ 3.59in.(91.2mm)Height......................................... 7.62in. (193.5 mm)

Weight(maximum)....................................... 10.01b(4.6 kg)

PowerRequirements.................................. 28Vdc, l.lAMax26 V ac Ref, 60 mA

MatingConnector:

J1 ....................................... DPX2MA-A106P-A1O6P-33B-OOO1

MatingPneumaticConnectors:

Pitot(straight)........................................ 40007-1B24*Static(straight)....................................... 40007-1A26*Pitot(90°elbow) ...................................... 40007-1B24E*Static (90” elbow) ..................................... 40007-1A26E*

*AllpartnumbersareAmericanSafetyFlightSystems.

Mounting........................ Tray,BarryPartNo.404A-38-S-l/DPX2-O

AZ-81ODigitalAirDataComputerLeadingParticulars

Table3-4

The AZ-81ODigitalAir DataComputer(DADC)is a microprocessor baseddigital computer which accepts both digital and analog inputs, performsdigital computations, and supplies both digital and analog outputs. Itreceivespitot-staticpressuresandtotalairtemperatureinputsforcomputingthestandardairdatafunctions.The airdataequationsaresolveddirectlyusinga 16/32-bitarithmeticmicroprocessorunderthecontrolof an 8-bitgeneralpurposemicroprocessor.TheDADCprovidesoutputsfordrivingtheBaroAltitudeIndicator,transponder,flightrecorder,flightdirector,andautopilot,as well as other elements ofthe flight control system. It also provides the computation fortheVN-800VNAVControl/Display.

22-14-00Paqe139Mar-15/89

Use or disclosure of Information on this page IS sub)ect to the restncttons on the title page! of this document

Honeywell M!MY’”c’CITATION V

DIGITALRANGE

I

9< I10

1

711

12 t

STATIC

kP&;Eo~E k FREOTUOENCY

SENSOR TEMPSERIAL

DIGITALCONVERTER

PAR~~LEL

CHARA~R~;ZAT IONCONVERTER

+(AR!NC 419)

[DIGITAL BUS

.—BuS (TO SH2)

/\

CHARACTERIZATIONPROM

PTPITOT

~SENSOR

‘TPRESSURE Pr

SENSORTEMP —

SENsOR TEMP INTERFACE

‘JIBVNAV

{<!

10HI

SLEWCONTROL IW< ‘o

{1AN::

51<1 “DIGIT

TO/FROM52< ‘0

CohvERT]

‘=4%=3EH

E=POWER

SIGNAL 5GROUND ~

SUPPLY

7

%OUND s

CHASSIS 9GROUND ,0

—

L

1BARO DISASLE 38

SSEC DISABLE 39

mSELF TEST 52 ,

T,4T/SAT SEL 71

ALERTER SEL 93P]LOT/COPILOT SEL lm

@

ALT 55

PILOT ALT RATE 56HOLDENG AJS 57

MACH 58

PILOT SLEW ENG 59JIBmALT 55

COPILOT ALT RATE %HOLDENG .4,,s 57

MACH 58

COPILOT SLEW ENG 59

J3A

Ma101>D2

AIRCRAFT 103INTERLOCKKEYING 1~

105

106

ASC.B DUAUSGL 99JIB

{a

94TEST INTERLOCK[DIAGNOSTIC MODEI 95

RANGE FORMAT 2.+

RANGE CORRECTION 65

RANGE VALl D S6a

DISCRETEINPUT

CON D~NINING

MULTIPLEXING

4CENTRAL

PROCESSINGUNIT(80851

t

H READ,wRITEMEMORY

(RAM) Ii 1

.5ESIVNAV ARM 92

VNAV CAPTURE 92

WAYPOINT SELECT 90

[

100

DISPLAY ’01SELECT 702

99

E

COMTORQUE LOGIC IN 1 5

TOROUE LOGIC IN 2 6

TOROUELOGICTEST 7

. ANALOG OUT (FROM SH2)

MONITOR [FROM SH2)

*c-7?d3

AZ-81ODiaitalAirDataComputer‘BlockDiagram -

Figure3-8 (Sheet1 of 2) 22-14-00

Use or disclosure of information

Page140Mar15/89

onthispageIS sublecttotherestrictionson the title page of thm :Iocurnent

Honeywell W/W’””CITATION Ilfl

JIA(H) ,1

(c) I

I;)

A LL4TA12

(H)24

(cl I;)

A CLK25

JIB

B

m

81

82VNAV

DISPLAY S2OUTPUT

REGISTER 04

85

S6

87IVNAVDISPLAYDATA

JIB

IAS SEL 91 ,

I

JIA

{ 932 “1

23 VACI AIEFE%ACE

INPUTLO

GENERATION33 7-j=fiiii

(H)

:;)

= OUTPUT(c)

ARINCz, NO 1

42s(H)

‘>)

70 o“,p(J~(c) I >,, NO 2

solJIA

FINE28

m RESOLVER

~}

cos , ~, FMRESOLVER

OUTPUT COM ALTITUDE NO 128

MO?41TOllClnCUITFiV

““c’ODE”w’7’FMooEI I I I I

DIGITAL BuSBUS (FROM Slit)— 1

1nlGtT41

H

TOANALOG

CO?4VERTEH

SAMPLE +tCkDCL3)4TRCl

JIA

-_..+ *4] 1

)COARSE DCALTITUDE NC 1a15

16

17

I18

19

m

21

ALTITUOE*EPOR’71NQREGISTER

TFIANSPONOEROUTPOT v

~----=i ‘oNT”’CIRCLIITRV OIGITAL SINTO AC FINE 1.

sOUTPUT RESOLVER

ms P89 FM

CONVERTER, REBCLVER

— CIJTPIJT COAJ, ~ ALTITUDE NO 2

ii

22

2sCOM

13

JIB

~1:1

1

TOFlOUE~ TOROUE LOGIC

Ij,OUTPUTS

LOGIC

4 TORQUE LOGIC VALIEI

r IREFJIA

~

)41IAS I ,,

MACH 1 ,5

VA40 : )484 1

A4ACHICOM 1 4)

4 AIRSPEEOWTPUTS REF

JIB

l)4?

-IAS

41MACH ! >

‘ 45

COM I >AdJIA

) 7U

}

PILOTOUTPUTS

1COPILOTOUTFllTS

---’@a

JIA

E34

}

JIB ALTITLIOE VALIDS

S4JIA49

VALIOrXITPUT

}

J1O AIRSPEED VALIOS

REGISTER 40

37 VERT PATH VALID

SAMPLWHOLO

CIRCUITS

IAS NO 3 1+ —JMONITOR

MULTIPLEXER

t3=i!’”TsO’::TspJg,,,g,~N,ToR

‘1ACIRCUITRY

HI

+51

LO

~

PILOT

5d HOLO OUTPUT

+ )61 PILOT HOLO FIEFHOLO

-OUTWTS HI J)S

1 53LO 1

~i}

COPILOT

54 I’(OLO OUTIWT

I )61 COPILOT HOLO I?EF

I,>78PRESELECT ALT VALIO

B“ “JIS

3s TO/FROM NULL

MISCOUTWT

75 ALT ALERT LIGHT

REGISTER 7s ALT ALERT HORN

e ,.74 PRESELECT ALT lSM FT

77 PRESELECT ALT CRANK

Ss WAYPOINT 1 ANN

I I i )09 WAYPOINT 2 ANN

JIA

PRESSURE

I

)78 PRESS ALT NO 1ALTITUOE JBOUTPUTS >79 PREss ALT NO 2

ANALOG OUT ~(TO SHII

MONITOR(TO SH1)

I AD 2! 7.2

AZ-81ODigitalAirDataComputerBlockDiaqram

Figure3-8 (sheet2) 22-14-00Paae141/142“May25/90

Useordisclosureofinformnllononthispage is subpct to the restrictions on the title page of this document.

Honeywell WJE!ANC’CITATION V


22-14-00Page143Mar 15/89

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Honeywell MW!YANCECITATION V

3. E. VN-800VNAVControl/Display(SeeFigures3-9and3-10,andTab”le3-5.)

VN-800VNAVControl/DisplayFigure3-9


Length........................................ 8.316 in. (211.23mm)Width.......................................... 3.275in. (83.19mm)Height......................................... 1.537in. (3$1.04mm)

Weight(maximum)........................................ 1.3lb (0.6kg)

PowerRequirements:

Primary ............................................... 28V dC, 5 WLighting........................................... 28Vdc, 3.OVA

MatingConnector:

J1 ...................................................... MS24308/2-4

Mounting................................. Clamp,MSP Inc,Part No 64321

VN-800VNAVControl/DisplayLeadingParticulars

Table3-5

The VNAVControl/Displayprovidesdisplaysfor altitude alerting,altitude preselect, and vertical navigation (VNAV) mode. Thecomputations foreachof thesemodesareperformedin theAZ-810AirDataComputer.

22-14-00Pa~e144Mar”15/89

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Honeywell WRAN’ECITATION V

Altitudeis selectedby placingtheselectorswitchto AI.TSELandslewing to the desired value, and the ALT SELbuttonselectedon the ModeSelector willinitiatealtitudepreselect.To utilizetheVNAVcomputationcapabilityof theunit,thepilotmustsetthestationelevation,to-fromdistance,andgo to theVANGposition after selectingthe desired waypoint altitude.

TheWPT switchprovidesa meansforselectingthewaypointto bet)roarammedor disDlaYed.The PROFILE switch uroyidesa meansfor;tr;nging togeascent with no

Thedisplaywi”two seconds or

he;tietwoselectedwaypoints’fora multi-legdescentorlevel off between waypoints.

1 indicate dashes if poweris interruptedformore thanif the air data computer is not valid.

22-14-00Page145/146

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Honeywell tiir~kp’”c’CITATION V

“v”c~’w , ,*—’’+%-

DISPLAYDATA

II +r

{

DDO

‘ %!!

1

BCD D’l 19

DATA DD2 14

DD3 18

(

DD4VNAV

DIGIT 11 DISPLAYSELECTORS DD5 12 ELECTRONICS

STROBE DD6 6

DISPLAYCONTROL{0 = DASHES

= DATA) ‘D’-hti

II

I III

II

II

I I

IIII

II

● p’% DIMMINGp’y} CONTROLINPUT

STA w~EL ALT ALT

@

TO SEL

FROM

VANG

9 +j+ LAMP TEST(GND = TESTI

DATASELECT

SELE’T’0MMON~21’+DISPIAY SWITCH

‘ J4i@i2+’+’’’”k”-’JAT,o”{:~d:WPT

AO.5S R3

VN-800VNAVControl/DisplayBlockDiaaramFigure3~10

22-14-00Paqe147Mar-15/89Useordisclosureofinformationonthispagem subjecttotherestrictionscmthetitlepageotthisdocument.

Honeywell MWR”c’CITATION V

4. Or)tionalAA-300RadioAltimeterSystem

RT-300RadioAltimeterReceiver/Transmitter(SeeFigures4-1Table

RT-300RadioAltimeterReceiver/TransmitterFigure4-1

4-2,


Length ......................................... 11.07 in. (Z~l.Zmm)Width ........................................... 4.56 in. (115.8 mm)Height .......................................... 4.09 in. (104.0 mm)

Weight (maximum) ....................................... 4.51b(~.05 kg)

PowerRequirements..

Transmittercharacter

Type............

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 V dc,

sties(nominal):

............................ ShortPulseModu”

0.7A

ationRF”freauenc.y................................................ 4.3GHzPeakpower....................................................... 5W

Receiver characteristics (nominal):

Type................................................ SuperheterodyneIF frequency................................................. 60 MHz

RT-300RadioAltimeterReceiver/TransmitterLeadingParticulars

Table4-1

22-14-00Pac.le148Mar-15/89

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Honeywell MAWJIPANCECITATION V

OperationalAltitude............................................. O-2500ft

DataOutputs/Accuracy:

PrecisionOutput....................... DC analogvoltag~(O - 2500ft)Gradient:-4.0mV dc/ft

O alt = O voltAccuracy: o - 100ft,*3 ft

100- 500ft,i3%500- 2500ft,t4%

Auxiliary Output .............. DC analogvoltage(O - 50tlft)Gradient:PerARINCcharacteristic552,

ALT= (0.02h+ 0.4)Vdc foraltitudesbelow480ft &(10+ 101.nh + 20)Vdc

foralt480ft

Accuracy: o - 100ft,100- 500ft,500- 2500ft

500t,udesabove

AltitudeTrips................ 100mA currentsinkprovidedat andbelow trip points indicated below:

Tri~Point Accuracy

50 ft t4ft250ft ~loft500ft *2Oft1200ft ~60ft

MatingConnectors:J1 ................................................... MS3126F16-26SJ2 - TRANSMIT....................................... GRFF4007-0002

(GRFFConnectors, GRFF Division, Solitron Devices, Inc)J3 - RECEIVE........................................ GFIFF4007-0002


RT-300RadioAltimeterReceiver/TransmitterLeadingParticularsTable4-1 (cent)

The RadioAltimeterReceiver/Transmitterprovidesa dc outputvoltagewhichis proportionalto theaircraftabsolutealtitudeaboveterrain.In addition,it providesradioaltitudetrippoints,an indicatorwarningflagoutput,andan auxiliaryradioaltitudeoutput.

The precision output is usedto drivethe EADIRADALTdisplay.Theauxiliaryoutputsuppliesabsolutealtitudeinformationto theflightdirectorsystem.

22-14-00Page149Mar-15/89

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Honeywell WiURANcECITATION V

J2

YTO TRANSMITANTENNA

J3

Y TO RECEIVEANTENNA

r-o dP/7!

--—.J--—

(-

TRANSMITTERI To ‘ULSE VIDEOMODULATOR

RECEIVER

AGC VOLTAGESPROCESSOR

STC VOLTAGE

TRACKJ1 VALID J1

II

1>W AL-F OUTPUT [EH)

SELF TEST T I 1]X AUK OUTPUT

IY FLAG WARNING

II F TRACK INVALID

I1] N OUTPUT COMMONITEST INHIBIT NO. 1 D OUTPUT

I ASSEMBLY=

I

Ii U 1200 FTTRIP

TEST INHIBIT NO. 2 Bi I

1 V 250 FTTRIP

I I > R 50 FTTRIP

OUTPUT TEST EI I L 500= TRIP

I I > P ALT TRIP COMMON

I 28 VDC FILTERED I

I + +30 VDC I+28 VDC +15 VDCINPUT PWR E

Z +15 VDC OUTPUT

‘1 POWER ~ +5 VDC 1>

I SUPPLY I–15 VDC

PWR GND Q [ a -15 VDC OUTPUT

‘ -“’’’v”:::’RT-300RadioAltimeter Receiver/Transmi tter

BlockDiacwamFigure4:2

22-14-00Paqe150Mar”15/89LJseordisclosureofinformationonthispageEsublecttotherestnctlorlsonthetitlepageofthisrocument,

Honeywell ~firl~r’”c’CITATION V

4. B. AT-223RadioAltimeterAntenna(SeeFigure4-3 andTable4-2.)

OneAT-223anotheris

antenna is usedto receive information from theRT-300andusedto transmitinformationto the RT-300.

AD-18382

AT-223RadioAltimeterAntennaFigure4-3


Width .......................................... 6.05ir. (153.7 mm)Height ......................................... 2.89 in. (73.4 mm)


Power Requirements .......................... 10 Wpeakmax, lW average

Mating Connector:

J1 ...................................................... TNC - male

Mounting......................... Flushmountedto aircraftskin,usingNo. 10 panheadscrewsandgasket,

PartNo.4010193-3

AT-223RadioAltimeterAntennaLeadingParticulars

Table4-2

22-14-00Page151Mar-15/89UseordisclosureofIntormatlononthispageIS subjecttolherestrictionsonthetitlepage]~thisdocument.

Honeywell WUR!AN’ECITATION V

5. ElectromechanicalFliqhtInstruments

A. RD-450HorizontalSituationIndicator- Copilot’s(SeeFigures5-1and5-2,andTable5-l.)

FORE HEADINGHEADING HEADING LUBBER WARNINGDIAL BUG LINE FIAG

COURSESELECTPOINTER

COURSEDEVIATIONBAR

NAVIGATIONWARNINGFLAG

AIRCRAITSYMBOL

COMPASSSYNCANNUNCIATOR

COURSE RECIPROCAL A17 HEADINGSELECT COURSE LUBBER SELECTKNOB POINTER LINE KNOB

RD-450HorizontalSituationIndicatorFigure5-1

VERTICALWARNINGFLAG

VERTICALDEVIATIONPOINTEF

TO-FROMPOINTEF?

AD-396(I

22=14-00Page 152Mar 15/89

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Honeywell W!JRANCECITATIONV


Length .......................................... 7.00 in. (177.8 mm)Width........................................... 4.07in.(103.4mm)Height.......................................... 4.07irl.(103.4mm)


PowerRequirements:

Primary ...................................... 26 V, 400Iiz,1.4VALighting....................................... 5 V ac ordc, 1.2VA

MatingConnectors:

J1 ................................................... MS3126F22-55SJ1 ................................................... MS3126F18-32S

Mounting................................ Clamp,MSP Inc,PartNo.64391

RD-450HorizontalSituationIndicatorLeadingParticulars

Table5-1

The RD-450SeriesHSIcombinesnumerousdisplaysto prov-dea map-likedisplayof theaircraftposition.The indicatordisplaysaircraftdisplacementrelativeto VORradials,localizer,andglic~eslopebeam.The indicatorprovidesthefollowingdisplays:

5. A. (1)

(2)

(3)

(4)

HeadingDialand ForeandAftLubberLine- Gyrostabilizedmagneticcompassinformationisdisplayedon theheadingdia~,whichrotateswiththeaircraftthroughout360degrees.Theazimuthringisgraduatedin 5-degreeincrements.Fixedheadingmarksareat theforeandaftlubberlinepositionsandat 45-degreebearings.

HeadingBugandHeadingSelectKnob- Thenotchedorangeheadingbugis positionedon therotatingheadingdialby theheadingknobtoselectanddisplaypreselectedcompassheading.The bugrotateswiththeheadingdialso thedifferencebetweenthebugandtheforelubberlineindexis theamountof headingerrorappliedto theflightdirectorcomputer.

HeadingWarningFlag- TheHDGflagis in viewwhentheheadingsignalfromthedirectionalgyrobecomesinvalid,primarypowertothe Indicatoris lost,or theerrorbetweentheheadingdisplayedandtheheadingsignalreceivedexceedsa specificthreshold.

VerticalWarningFlag- TheVERTflagis in viewwhuntheglideslopevalidsignalis lost.

22-14-00Page153Mar-15/89

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Honeywell IN!JRAN’ECITATIONV

5. A. (5)

(6)

(7)

(8)

(9)

(lo)

(11)

(12)

VerticalDeviationPointer- TheverticaldeviationpointerdisplaysGS deviation.Forglideslopeoperation,thepointeris in viewonlywhentheNAVis tunedto a localizerfrequency.The aircraft isbelow glidepath if the pointer is displaced upward, and each dotrepresents 75 microamps of glideslope displacement.

TO-FROMPointer- Thepointerconsistsof twoflags,180degreesapart. One alwayspointsthedirectionto thestationalongtheselectedVORradial.

ReciprocalCoursePointer- Thepointerindicates180degreesfromthecourseselectpointerindication.

CourseSelectKnobandCourseSelectPointer- Theyellowcoursepointeris positionedon therotatingheadingdialby the courseknobto selecta magneticbearingthatcoincideswiththedesiredVORradialor localizercourse.Liketheheadingbug,thecoursepointeralsorotateswiththerotatingheadingdialto provideacontinuousreadoutof courseerrorto theflightdirectorcomputer.

CompassSyncAnnunciator- Theannunciatorconsistsof the symbol.or + (dotor cross)displayedin a window.Whenthecompasssystemis in the slavedmodeandsynchronized,thedisplaywillslowlyoscillatebetweenthe ● and+, indicatingthattherotatingheadingdialis synchronizedwiththegyrostabilizedmagneticheading.

AircraftSymbol- A fixedminiatureaircraftsymbolcorrespondstothelongitudinalaxisof theaircraftandlubberlinemarkings.Thesymbolshowsaircraftpositionandheadingwithrespectto therotatingheadingdial. It alsoshowstheaircraftpositioninrelationto a radiocourse.

NavigationWarningFlag- TheNAV flagis in viewwhenthenavigationvalidsignalis lost.

CourseDeviationBar - thebarrepresentsthecenterlineof theselectedVORor localizercourse.Theaircraftsymbolshowspictoriallyactualaircraftpositionin relationto thisselectedcourse. InVORoperation,symbolrepresents5-degreeIn ILSoperation, each dotcenterline (75 microamps).

eachdoton eithersideof the aircraftdeviationfromcenterline(75microamps).representsl-1/4-degreedeviationfrom

22-14-00Page154Mar 15/89Use or disclosure of information on this page IS subject to the restrictions on the title page of th!s document.

Honeywell UN!FAN’ECITATIONV

-J+? x W’J2%%J2

I MofwroR

I*1

MEWING VALID INPUT

HOG INPUT

Y

I !

f?

L- .-—----- -- A------ +–---T

e I

I

I

I

I

vER? HI LSVELvEWl LO LEVEL

vEWl FuGTuNE?O LOC GND

uv

w

A,RESOLVERCOURSE

NAV !+1LSVEL

NM LO LEVEL

NAV FMG

Pm

s I tII

I

II

It SYNCHROCOURSEERR~I

//DC GNO

vERT WV [-)

vERl OW (-1

-2s Voc

o

c

o

a

_A+lt-?”I

iA

II

r-

1

.WJ2

SYNC l+ LEVEL J

oOlx

SYNC LO LEVEL H

SYNC ANN G - Ml

{NJ’ ‘v \ @

W LIGHTING M LIGHTINGAc OR Gc

LIGHT BLOCKASSV HS401P4G

I

B-+----y4-

11sYNcMmOHEAOINGERROR

1 IJWSR,*DI “

I I

L ----- -- +

I 4--- ~> s

I E “S2 *

~___--_J nz 34 c1

RI S2

alo~

-J%(V11>

‘+-------------

COMP4!41SONMONITOSSYNCI+RO

I

-L—-—-— —— -—---- -1

RD-450HorizontalSituationIndicatorB1ock DiagramFigure5-2

22-14-00Paqe155Mar”15/89Useordisclosureof information on this page is subjecf to the restrictions on the tttle page of this document.

Honeywell W!iVR’”c’CITATIONV

6. EDZ-605ElectronicFliqhtInstrumentSvstemandODtionalMDZ-605MultifunctionDis~lavSvstem

A. ED-600ElectronicDisplay

The ED-600 is a standard 4.6 x 5 inch display that uses a high resolutionCRTto displayADIandHSI information. A single EDZ-605systemiscomprisedof twoED-600ElectronicDisplaysthatareidenticalandinterchangeable,exceptwhenused as an ADI an inclinometeris attachedto the bezel. LeadingParticularsof theED-600arelistedinTable6-1.Paragraph6.B.describesthedisplayfeaturesof theED-600whenusedasanADI and paragraph 6.C. described HSI features.Paragraph6.D.describesthecompositedisplayforthe EDZ-605EFIS,Paragraph6.E.describesMFD features,andParagraph6.F.describesthefunctionaloperationof the ED-600.


Length ........................................ 10.50 in. (266.70mm)Width......................................... 5.070in. (127.78 mm)Height........................................ 4.695in. (119.25mm)

Weight(maximum)....................................... 9.1 lb (4.14 kg)

Power Requirements:

Primary .......................................... 28 V dc, 65 WmaxLighting.................................... 5 V ac or dc, 1.2Wmax

28 V dc, 1.2W max

MatingConnector:

J1 ................................................... MS27473E20B35Swith strain relief

MS27506-B20-2

Mounting............................ Clamp,HoneywellPartNo. 7000066-5or MSP PartNo.64483-103

ED-600ElectronicDisplayLeadingParticulars

Table6-1

22-14-00Page156Mar 15/89

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Honeywell uilJJfrANcECITATION V

6. B. ED-600Used As an Electronic Attitude Director Indicator (EADI)

TheEADIcombinesthefamiliartruesphere-typeattitudedisplaywithlateralandverticalcomputedsteeringsignalsto providethepilotcommandsrequiredto interceptandmaintaina desiredflightpath. TheEADIprovidesthefollowingdisplayinformation:

●

●

●

b

●

●

●

b

●

9

VerticalNavigation,Glideslope,or ElevationDeviationExpandedLocalizeror AzimuthDeviationRadioAltitude- RisingRunway- DigitalDecisionHeightAir DataCommandFD ModeAnnunciatorsMarkerBeaconAnnunciationRateof TurnSpeedCommandAttitudeSource

Thefollowingdiscussionis separatedintothreeparts. Paragraph6.B.(1)describestheEADIdisplaysandannunciatorswithreferencetoFigure6-1;paragraph6.B.(2)describestheambercautionandfailureannunciationswithreferenceto Figure6-2;andparagraph6.B.(3)describestheredfailureannunciationswithreferenceto Figure6-3or6-4.

(1) ED-600EADIDisplaysandAnnunciators(SeeFigure6-1.)

(a) AttitudeSphere- The sphere moves with respect to symbolicaircraft reference to display actual pitch and roll attitude.Pitch attitude marks are in 5-degreeincrements.

(b) AttitudeSourceAnnunciator- Theselectedattitudesource isnot annunciated if it is the normal source for that indicator.As other attitude sources are selected, they are annunciated inwhiteat thetop leftside of the EADI. When the pilot andcopilot sourcesarethesame,theannunciationis amber.However,when the Citation V has onlyoneattitudesource,there willnot be anyattitudesourceannunciations.

(c) RollAttitudePointerandScale- The pointerdisplaysactualrollattitudewhenalignedwiththefixedinde,~referencemarksat O, 10,20,30,45,and60 degreeson the rollscale.

22-14-00Paqe157Mar-15/89

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Honeywell WM?ANcECITATIONn/V

6. B. (1) (d) FlightDirectorModeAnnunciators- Flightdirectorverticalandlateralmodes are annunciated along thetopof theEADI.Armedverticalandlateralmodes are annunciated inwhitetotheleftof thecapturedverticalandlateralmodeannunciators. Captured modeannunciatorsaredisplayedingreen and are located to the left of top center for lateralmodes and in the upper right corner forverticalmodes. As themodestransitionas specifiedbelow,a whiteboxis drawnaroundthecaptureor holdmodeannunciatorfor5 seconds.

LateralTransitions VerticalTransitions

NAVARM to NAVCAP VNAVARM to VNAVCAP

LOCARM to LOCCAP VNAVCAPto ALTVNAVCAPto IAS

BC ARM to BC CAP ASELARM to ASELCAP

VAPPARMto VAPPCAP ASELCAPto ALT

AZ ARM to AZ CAP ASELARM to ALTGS ARMto GS CAPGPARM to GP CAP

(e) Glideslope,VerticalNavigation(VNAV),or GlidepathDeviationPointer- Theglideslopepointerandscalearein viewwhentunedto an ILSfrequencyto displayaircraftdeviationfromglideslopebeamcenter.Aircraftis belowglidepathif pointeris displacedupward.Eachglideslopedot represents0.35degree(75-microamp)displacementfromthe beamcent~?rline.IftheVNAVmodeis selected,thepointerindicatestheVNAVcomputedpathcenterto whichtheaircraftisto be flown. IfMLS is selected,thepointerwouldindicatedeviationfromtheselectedglidepathangle.

The letterG, or V is annunciatedinsidethepointertoindicatethetypeof informationbeingdisplayed.Ifthe scaleindicationbecomessaturated,thescalepointerwillgo outofviewbuttheletterG or V willremainin viewat themaximumdeflectionpositionof thescale.As the signalcomesout ofsaturation,thepointerwillpickup the letterandcarryitinsidethepointeras itmovesaboutthe scale.

(f) AircraftSymbol- Thesymbolservesas a stationaryrepresentationof theaircraft.Aircraftpitchandrollattitudesaredisplayedby therelationshipbetweenthefixedminiatureaircraftandthemovablesphere.Theminiatureaircraftis flownto alignthecommandcueto theaircraftsymbolinorderto satisfythecommandsof theselectedflightdirectormode.

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Honeywell HWJEFANCECITATION V

6. B. (1) (g) MarkerBeacon- Markerbeaconinformationis displayedon thesideof the EADIbelowtheglideslopescale. Themarkersareof thespecifiedcolorof blueforouter,amberformiddleandwhiteforinnermarker.A whiteboxidentifiesthelocationofthemarkerbeaconannunciationaftertuningto a localizer.

(h) AutopilotEngageAnnunciator- A greenAP ENG is annunciatedwhenevertheautopilotis engaged.

(i)

(j)

RadioAltitudeDisplay- Thefour-digitdisplayindicatestheaircraft’sradioaltitudefrom-20to 2500feet. Theresolutionabove200feetof altitudeis 10 feet;below200feet,theresolutionis 5 feet. Thedisplayis blankedforaltitudesgreaterthan2000or 2500feet,dependingon theoutputcapabilitiesof theradioaltimeter.Whentheradioaltitudedatais invalid,thedisplayindicatesa dashin eachof thedigits.

RisingRunway- Foraddedbackupduringthecriticalapproachphaseof flight,absolutereferenceabovetheterrainisdisplayedbelow200feetby therisingrunway. The risingrunwayappearsat 200feetandmovestowardtheminiatureaircraftsymbolas theaircraftdescendstowardtherunway,contactingthebottomof thesymbolicaircraftat touchdown.If theradioaltitudeis invalid,therisingrunwayis outofview.

(k) Inclinometer- The inclinometergivesthepilota conventionaldisplayon aircraftslipor skid,andis usedas an aidtocoordinatedmaneuvers.A meansforlevelingthe inclinometeris provided.Levelinclinometerin accordancewithprocedurein Section8.

(1) ExpandedLocalizeror AzimuthPointer- Expandedlocalizerisdisplayedby thelocalizerpointerwhenevera validlocalizersignalis available.Rawlocalizerdisplacementdatafromthenavigationreceiveris amplifiedapproximately7-1/2timestopermitthelocalizerpointerto be usedas a sensitivereferenceindicatorof theaircraft’spositionwithrespecttothecenterof thelocalizer.It isnormallyusedforassessmentonly. Duringfinalapproach,thepointerservesasan indicatorof theCategoryIIwindow.Whentunedto otherthanan ILSfrequency,theexpandedlocalizerdisplayisreplacedby therate-of-turndisplay.WhenMLS is selected,theexpandedlocalizerpointerdisplaysdeviationfromtheselectedazimuthangle.

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Honeywell WWPCECITATIONn/V

6. B. (1) (m) Rate-Of-TurnDisplay - When tuned to other than an ILSfrequency, the rate-of-turn is displayed by a pointer and scaleat the same location as the expanded localizer. The rate-of-turn of the aircraft is indicated by the position of thepointer against scale indices. Themarksat theextremeleftandrightsidesof thescalerepresenta standardrateof turn(2-minuteor 3-degreeper second turn rate).

(n) DecisionHeightDisplay- Decisionheightisdisplayedby athreedigitdisplay.The setrangeis from10 to 990feetin10 footincrements.The DH displaymay be removedb.ysettingfullcounterclockwiserotationof thesetknob. Whenat orbelowdecisionheight,an amberDH willappearinsidethewhiteboxadjacentto radioaltitude.

(o) AirDataCommandDisplay- Whenselectinga flightdirectorairdatacommandfunction(verticalspeedor indicatedairspeed)andwiththeautopilotengaged,thecommandreferencewillappearin thelowerleftcorner.The autopilotpitchwheelmaybe usedto changetheairdatacommandreference.Forotherverticalmodes,theairdatacommanddisplaywillbe removed.

(P) Fast/SlowPointer- Thepointerindicatesrelativeapproachairspeedprovidedby the angleof attacksystem.ThepointerdeflectstowardF whentheaircraftis flyingat morethanprogrammedspeed. Theoppositeis truewhenthepointerdeflectstowardS.

(q) PitchandRollCommandCue - Thecuedisplayscomputedsteeringcommandsto captureandmaintaina desiredflightpath. Alwaysflythe symbolicminiatureaircraftto theflightdirectorcue.Thecue is biasedout-of-viewif an invalidconditionoccursintheflightdirectorpitchor rollchannel.

(r) AirspeedDisplay-IndicatedAirspeed(IAS)isdisplayedon arollingdigitreadoutbetween80 and600 knotswithI knotresolution.

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Honeywell WUR!ANCECITATION11~

I LATERAL I

ROLL FLIGHT DIRECTORATTITUDE ROLL MODE ANNUNCIATORS

ATTITUDE POINTER SCALE (NOTE 3)

SPHERE \ \ \ /

?T!!ii+\ 1=PITCHAND ROLL HD ‘s mCOMMAND CUE(NOTE2)

AOA20— 20

—F

—lo o0

FASTISLOW _— o

> -

: !POINTER a“

o — olo— 10 0q

—AIRDATA 20

7

I

““’D$G~y\

H AP ENG

14 RA

+ /

DECISION EXPANDED INCLINOMETER RISING RADIOHEIGHT LOCALIZER RUNWAY ALTITUDEDISPLAY OR AZIMUTH DISPLAY

2.

3.

4

VNAV,GLIDESLOPE,

— OR GLIDEPATHDEVIATIONPOINTER

.AIRCRAFTSYMBOL

,MARKERBEACON

AUTOPILOTENGAGEANNUNCIATOR

POINTER(NOTE1)

NOTES:1.WHEN NOT TUNED TO AN ILSFREQUENCY,THE RATEOF

TURN POINTER AND SCALE IS PRESENT INPLACEOF THEEXPANDED LOCALIZERPOINTER.WHEN MLS ISSELECTED,THE EXPANDED LOCALIZERPOINTERDISPLAYSAZIMUTHDEVIATION.THECUE CAN BECHANGED TO CROSS POINTERSBYAPPLYINGA GROUND TO 115J1-7.A WHITEBOX ISDRAWN AROUND THE MODE ANNUNCIATORFOR5SECONDS WHEN AN AUTOMATICMODE TRANSITIONOCCURS.(INTHIS CASE ASEL ARM TO ALT.)

THE AIRSPEED DISPLAY IS ONLY AVAILABLE WHENUSINGTHEAZ-81ODADC.ITISCURRENTLY A NON-APPROVED OPTION.

+

LATERAL ARM(WHITE)

t .--u-.-. VAPPBC AZvOR LNAV

ED-600EADIDisplays andAnnunciatorsFigure6-1

22-14-00Page161/162

AIRSPEED=DISPLAY(NOTE4)

E[31 450 KTS J

LE!!UI-%KP-IVAPP LNAV VNAVVOR AZ ASEL VERTICALLOC HDG GS CAPTUREBC GP (GREEN)

GP VNAV

—F

1 lo— 10

+$(=-e[

lo— 10s —

nDECISIONHEIGHT(AMBER)

-KE4DEVIATION

● V FOR VNAVDEVIATION

● G FOR GPDEVIATION

I MARKER BEACON !

‘PsI1

AD-18383-R2

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Honeywell HiWJfPANcECfTATIONn/V

6. B. (2) ED-600EADIAmberCautionandFailureAnnunciations. .(See‘- - ‘-

(a)

(b)

(c)

(d)

(e)

(f)

(9)

(h),

(i)

(j)

(k)

Figure6-Z).

FlightDirectorFailure- An amber FD FAIL warning is displayedat the top left of the EADI in the event of a flight directorfailure. Also, the flight director cue and all FD modeannunciatorsareremoved.Duringself-test,if the FD modeannunciatortestis valid,the word TEST is annunciated inmagentaat thesamelocationas FD FAIL.

Excessive Deviation - Excessive glideslope/glidepath orlocalizer/azimuth deviation is indicated by changing therespective deviation scales and pointers to amber.

AutomaticFlightControlSystemSourceflightcontrolsystemswitchdiscretesreceivedduringEFISsourceswitching,willbedisplayed.

Advisory- If automaticarenotproperlyan amber “AFCS?”warning

FlightManagementSystemMessage(FMSMSG)- An amberwarningmessageto alertthepilotthatan FMSmessageis displayedontheCD-800ControlDisplayUnit.

TouchControlSteering- TouchControlSteeringmodeisindicatedby an amberTCSENG.

RadioAltitudeFailure- Intheeventof a failureof theradioaltimeter,amberdasheswillreplacethenumericalvaluesandtherisingrunwaywillbe removedfromthedisplay,if present.

DecisionHeightWarning- Whentheradioaltitudeiswithin100feetof thedecisionheight,a whiteboxwillappearto theleftof theradioaltitudedisplay.Whenat thedecisionheight,an amberDH willappearinsidethewhitebox.

DecisionHeightFailure- In theeventof an openDHpotentiometer,or duringself-test,amberdasheswillreplacethenumericalvaluesof thedecisionheightdisplay.

AirDatafailure,specific

AirspeedComputer

CommandFailure- In theeventof an airdatacomputeramberdasheswillreplacethenumericalvalueof theairdatacommanddisplayed.

DisplayFailure- In theeventof an AZ-81OAir Datafailure,thedisplayis replacedwithamberdashes.

SG BackupAnnunciator- An amberMG is displayedat thetopleftof theEADIspherewhentheSG backupmodeis selectedandtheMG-605MFDSymbolGeneratoris beingusedin placeof afailedSG-605SymbolGenerator.

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Honeywell W!RFcECITATIONn/V

6. B. (3) ED-600EADIRedFailureAnnunciations(SeeFigures6-3 and6-4.)

(a) AttitudeFailure- In theeventof a failureof theattitudedisplay,thepitchscaleandrollpointerwill be removed, thesphere will be painted blue, and a redATT FAILwillbedisplayedin the middle of the sphere upper half.

(b) G1ideslope, VNAV or G1idepath, Expanded Localizer or Azimuth,Fast/Slow Command and Rate-of-Turn failures - In theeventof afailureof anyof thesesystems,thepointeris removedandared “X”isdrawnthroughthescale. TheletterG or V remainsat thezerodeviationpositionto identifythe invalidinformation.

(c) InternalFailure- In theeventof an internalfailurewithinthedisplaysystemitself,thedisplaywillbe blank Afailureof the symbolgeneratorinput/outputprocessorwillbeindicatedby a red “X”centeredon thedisplay,withannunciation“SGFAIL.”

22-14-00Pacie164May-25/90


SGBACKUPANNUNCIATOR(WITHMFDONLY)

\

AIRSPEEDDISPLAY FAILURE-(AMBER DASHES)

AIR DATACOMMANDFAILURE(AMBER DASHES)-

~,~,s,oN/HEIGHTFAILURE(AMBER DASHES)

Honeywell !RWPAN’ECITATIONV

FD FAIL(AMBER)

/

\

fi~ ;

FD FAIL

20 — 20AOA ~ —

FG10 —lo o

0 —

“&4’ (5---

T

, /zi\ ,0

slo— 10

—

CMD 20 — 20/i---KTS H FMs MsG-–-DH ---RA

1’

~“~>

D

DE&SION

%RADIOALTITUDEFAILURE(AMBER DASHES)

HEIGHTWARNING(AMBER) AD-18384-RI

ED-600EADICautionandFailureAnnunciations(Amber)

Figure6-2 - “22-14-00

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FAST/SLOW ,FAILURE(RED)

Honeywell UNMIFPANCECtTATIONn/V

AOA

o

\NOTE: RATE OF TURN

FAILURE IS SIMILAR.

EXPANDED LOCALIZEROR AZIMUTH FAILURE(RED) (NOTE)

ED-600EADICautionandFailureAnnunciations(Red]

Figure6-3 ‘ ‘

,ATTFAILANNUNCIATOR(RED)

/ffi;;&YLFllEpATHFAILURE (RED)

AD-11436-RI

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Honeywell WitW’”c’CITATIONV

AO-5276

ED-600Internal System Failure (Red)Figure 6-4 22-14-00

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Honeywell M!URAN’ECITATIONn/V

6. C. ED-600UsedAs An ElectronicHorizontalSituationIndicator(EHSI)

The EHSI combines numerous displays to provide a map-like display of theaircraft position. The Indicatordisplaysaircraftdisplacementrelativeto VORradials,localizer,andglideslopebeam. At powerup,theEHSIpresentsa fullcompassdisplay.By pressingtheDC-811FULL~ARCor MAPbutton,thefullcompassdisplayis changedto a partialcompassformat.Also,ifweatherradarreturnsaredesired,pressingtheWX buttonon theDC-811changesthefullcompassdisplayto a partialcompassdisplayingweatherradarreturns.The EHSI,providesthefollowingfullandpartialcompassdisplayinformation:

FullCom~assDisplays

●

●

●

●

●

●

●

●

●

●

●

●

●

●

●

●

●

HeadingCourseSelectCourseor AzimuthDeviationDistanceGroundspeedTo/FromDesiredTrackBearing1 and2HeadingSelectVertical,Glideslope,or GlidepathDeviationTime-To-GoElapsedTimeHeadingandNAVSourceAnnunciatorsCompassSyncVariableGainAnnunciatorWeatherRadarModeandTiltAngleAnnunciatorFMSApproachMessage

partialComc)assDisplaysonly

. WeatherRadar

. WindVector

. NavigationMap (Rangeannunciationandwaypoints)

. MultipleWaypoints

Thefollowingdiscussionis separatedintofourparts. Paragraph6.C.(1)describestheEHSIdisplaysandannunciatorswithreferencetc Figure6-5;paragraph6.C.(2)describestheambercautionandfailureannunciationswithreferenceto Figure6-6;paragraph6.C.(3)describestheredfailureannunciationswithreferenceto Figure6-7;paragraph6.C.(4)describesthedisplayfeaturesof thepartialcompassdisplaywithreferenceto Figure6-8;paragraph6.C.(5)describesthelongrangenavigationmapmodewithreferenceto Figure6-9,andparagraph6.C.(6)describestheshortrangenavigationmapmodewithreferenceto Figure6-10.

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Honeywell !R!JRANCECITATIONV

6. C. (1) ED-600EHSIDisplaysandAnnunciators(SeeFigure6-5.)

(a) CourseSelect/DesiredTrackDisplay- A digitalreadoutindegreesof the course indicated by thecourseselectpointer.If longrangenavigationis selected,desiredtrack(DTRK)isdisplayed.

(b) Drift Angle Bug (INSonly) - Thedriftanglebugwithrespectto the lubberlinerepresentsdriftangleleftor rightof thedesiredtrack. Thedriftanglebugwithrespectto thecompasscardrepresentsaircraftactualtrack. The bugisdisplayedasa green triangle which moves around the outsicle of the compasscard (either partial or full).

(c) FMSApproachMessage- A blueAPP indicatesthatthe FMSis intheapproachmode.

(d) HeadingSourceAnnunciator- Thecurrentheadingsourceisdisplayedinwhitewhenthepilotandcopilotsourcesarenotthesame. If theheadingsourcesarethesame,theannunciationis in amber.

(e) HeadingSelectBugandHeadingSelectDisplay- Thenotchedblueheadingselectbug is positionedon the rotatingheadingdialby a remoteheadingknobto selectanddisplaypreselectedcompassheading.Thebugrotateswiththeheadingdial,thereforethedifferencebetweenthebugandtheforelubberlineindexis theamountof headingerrorappliedto theflightdirectorcomputer.A digitalheadingselectdisplayisprovidedforconveniencein settingthe headingbug.

(f) NavigationSourceAnnunciators- Annunciationof thenavigationsourceis displayedin theupperrighthandcorner. Longrangenavigationsources(INS,VLF,RNAV,FMS)aredisplayedin blueto distinguishthemfromshortrangesourcesannunciatedinwhite.

(g) DistanceDisplay- Thedistancedisplayindicatesthenauticalmilesto theselectedDME stationor waypoint.Dependingonequipment,thedistancewillbe displayedin a.O-399.9or a O-3999nauticalmileformat.DMEHOLDis indicatedby an amber“H”adjacentto thedistancereadout.

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Honeywell MW!AN’ECITATIONn/V

6. C. (1) (h) HeadingDialandForeandAftLubberLines- Gyrostabilizedmagneticcompassinformationisdisplayedon theheadingdial,whichrotateswiththeaircraftthroughout360degrees.Theazimuthringisgraduatedin 5-degreeincrements.Fixedheadingmarksareat theforeandaftlubberlinepositionsandat 45-degreebearings.

(i) VerticalNavigation,Glideslope,or GlidepathDeviationPointer- TheverticalnavigationdisplayandannunciatorcomeintoviewwhentheVNAVmodeon theflightdirectoris selected.The deviationpointerthenindicatestheVNAV’Scomputedpathcenterto whichtheaircraftis to be flown.

TheglideslopedisplayandannunciatorcomeintoviewwhenaVHFNAV sourceis selectedon theEHSIandthatNAV sourceistunedto a localizerfrequency.Thedeviationpointerthenindicatestheglideslopebeamcenterto whichtheaircraftisto be flown.

TheglidepathdisplayandannunciatorcomeintoviewwhenMLSis selected.Thedeviationpointerthenindicatesdeviationfromtheselectedglidepathangle.

The letterG or V is annunciatedinsidethepointerto indicatethetypeof informationbeingdisplayed.If thescaleindicationbecomes saturated, the scale pointer will go out ofview but the letter G or V will remain in view at the maximumdeflection position of the scale. As the signal comes out ofsaturation, the pointer will pick up theletterandcarryitinsidethepointeras it movesaboutthescale.

(j) Groundspeed,Time-To-Go,or ElapsedTimeDisplay- PressingtheGSPD/TTGbuttonon theDC-811DisplayControllerallowsgroundspeedor time-to-goto be alternatelydisplayed.Groundspeeddisplayedis thevaluecalculatedby thelongrangenavigationsystem(LRN)if an LRNis installedand itsoutputis valid. IftheLRNis invalid,theEFIScomputesgroundspeedusingDMEdistance.

PressingtheET buttonon theDC-811changesthedisplaytoelapsedtime. Whenin theelapsedtime(ET)mode,theETdisplaycanreadminutesandsecondsor hoursandminutes.Thehour/minutemodewillbe distinguishablefromtheminute/secondsmodeby an H on theleftof thedigitaldisplay.

(k) BearingPointersandSourceAnnunciators- Thebearingpointersindicaterelativebearingto theselectednavaid.Twobearingpointersareavailableandcanbe tunedto navaidsor selectedoff fromtheDC-811DisplayController.Thebearingsourceannunciationsaresymbolandcolorcodedwiththebearingpointers.Whenthebearingpointernavigationsourceisinvalidor a localizerfrequencyis chosen,therespective

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Honeywell W!O?AN’ECITATIONV

6. C. (1) (1)

(m)

(n)

(o)

(P)

(q)

bearing pointer is removed. Theannunciator:Symbols<z andOareremovedfromthedisplay,in additionto thepointersbeingremoved,ifthebearingpointersareselectedoff.

ReciprocalCoursePointer- Thepointerindicates180degreesfromthecourseselectpointer.

AircraftSymbol- A fixedminiatureaircraftsymbolcorrespondsto thelongitudinalaxisof theaircraftandlubberlinemarkings.The symbolshowsaircraftpositionandheadingwithrespectto therotatingheadingdial. It alsoshowstheaircraftpositioninrelationto a radiocourse.

Courseor AzimuthDeviationBar - Thecoursebarrepresentsthecenterlineof theselectedVORor localizercourse.Theaircraftsymbolshowspictoriallyactualaircraftpositioninrelationto thisselectedcourse. InVORoperation,eachdoton eithersideof theaircrafts~mbolrepresents5-deareedeviationfromcenterline(75mi:roamps)’.eachdotrepresentsl-1/4-degreedeviationmicroamps).WhenMLS is selected,thebarfromthe selectedazimuthangle.

Whenthebackcourse(BC)modeis selected

In ILSope~ation,fromcenterline(75indicatesdeviation

on the flightdirector,or whentunedto a localizerfrequencyandtheselectedcourseismorethan90°fromaircraftheading,thecoursedeviationis automaticallyreversedto provideproperdeviationsensingwithrespectto thecoursecenterline.Thecoursedeviationbaralwaysindicatesthelocationof thecoursecenterlinerelativeto thenoseof the aircraft.

WeatherRadarModeandTiltAnnunciator- The annunciatorindicatesthemodeof operationof theweatherradar. Theannunciationisdeterminedby themodeandfeatureselectedontheWX controller.BelowtheWX modeannunciator,theangletheweatherradarantennais positionedis displayedinpositivedegreesforup tiltandnegativedegreesfordowntilt.

NAVTo-FromAnnunciator- An arrowheadin thecenterof theEHSIindicateswhethertheselectedcourseis TO or FROMthestationor waypoint.TheTO-FROMannunciatoris not in viewduringlocalizeroperation.

CourseSelectPointer- Theyellowcoursepointeris positionedon therotatingheadingdialby a remotecourseknobto selecta magneticbearingthatcoincideswiththedesiredVORradialor localizercourse.Thecoursepointerrotates with therotating heading dial to provide a continuous readout of courseerror to the flight director computer.

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6. C. (1) (r)

Honeywell UiMfPANcECITATIONV

Whenlongrangenavigationis selected,thecoursepointernowbecomesa desiredtrackpointer.The position of the desiredtrack pointer is controlled by the long range NAV system. Adigital display of desired track (DTRK) is displayed in theupper left hand corner.

CompassSyncAnnunciator- Thecompasssyncannunciatorindicatesthestateof the compasssystemin the slaved mode.Thebarrepresentscommandsto thedirectionalgyroto slewtothe indicateddirection(+ forincreasedheadingandc fordecreasedheading).The syncannunciatoris removedduringcompassMANUALmodeand INSoperation.

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Honeywell WW!ANCECITATIONn/V

DRIFT;;:LE FMS

APPROACH

\

MESSAGECOURSE/DESIREDTRACK DISPLAY I

(HONEYWELFM~ f)NIY)

HEADING FORE HEADING

\\ .. ..\. L %:o~lAToR,:wERjHc;.:;,::::N

-,. , ,---

AND TILT ANNUNCIATOR- [ A

COURSE OR I M i“”’ “<T

BEARINGPOINTERSOURCEANNUNCIATOR

~,/

T“- /. ~. 0’; . I

~ DISTANCEDISPLAY

‘HEADING DIAL

VERTICALNAVIGATION

\g&.;;.:TH

DEVIATIONPOINTER

\ VORGANNUNCIATOR

HEAD{NG AIRCR’AFT AF? RECI>RCCAL BEA~lNG..—.SELECT- SYMBOL LUBBER COURSE POINTERSDISPLAY LINE POINTER

\ GROUND SPEEDDISPLAY (NOTE 1)

QCRSOR

DTRK E=HEADING SOURCE

ANNUNCIATOR

DG1 MAGIDG2 MAG2

BTARGETALERTARMED

TGT (GREEN)

NOTE 2>

5BEARINGSOURCESADF1ADF2VOR1VOR2FMS

mEl

VERTICALDEVIATION

ANNUNCIATOR

vG

1=ELAPSED

TIME, TIME-TO-GO, OR

GROUNDSPEED

DISPLAY

ET

E59.59ETH959TTG399 MINGSPD

L-X!Es-NOTES:1.TIME-TO-GOAND ELAPSEDTIMEISALSO DISPLAYEDATTHISLOCATION

2. TX APPEARS WHENEVER THE WEATHER RADAR ISTRANSMITTINGAND WXISNOT SELECTED FOR DISPLAY.

AD-18418-R2

ED-600EHSIDiSD1a.ysandAnnunciatorsF~gu~e6-5 22-14-00

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Honeywell WJYANC’CITATIONn/V

6. C. (2) ED-600EHSIAmberCautionandFailureAnnunciations(SeeFigure6-6.)

(a) WaypointAlertAnnunciator- An amber WPT annunciation from alongrangeNAV system is displayed to indicate waypoint passagefor the longrangenavigationsystemdisplayedon theEHSI.

(b) SameHeadingor NavigationSource- Ifthepilotand copilothave selected the same heading or navigation source, theapplicable sourceis annunciatedin amber. Otherwise theannunciation is in white. ForSRNsources,if the pilot andcopilot have both cross switched to the other’s source, theannunciator would be amber even though they would be fromdifferent sources.

(c) DMEHoldAnnunciator- WhenDME is in theholdposition,anamber“H”is displayedto theleftof thenumericalDMEreadout.

(d) WeatherRadar(WX)Failure- An amberWX indicatesa failurewithintheweatherradarsystem.

(e) WeatherTargetAlertor VariableGain- Weatherradartar-getalerts are annunciated on the EHSI above the bearing sourceannunciation.GreenTGT indicatesan armedconditionwhileamberTGT indicatesan alertcondition.An amberVAR indicatestheradaris operatingin thevariablegainmode.

(f) DisplayFailures- Whenanyof thefollowingsystemsfail,thedigitaldisplayis replacedby amberdashes:

. Groundspeed(GSPD)

. Time-To-Go(TTG)

. ElapsedTime(ET)

. DistanceMeasuringEquipment(DME)

. HeadingSelect(HDG)

. CourseSelect(CRS)

. DesiredTrack(DTRK)

(3) ED-600EHSIRed FailureAnnunciations(SeeFigure6-7.)

(a) HeadingFailure- A failureof theheadingsystemvalidresultsin theremovalof bearingannunciators,bearingpointers,To-Fromarrowselectcoursepointer,coursedeviationpointer,andcoursescale. Thedigitalselectcourseanddigitalheadingselectreadoutsaredashed,a red“HDGFAIL”isdisplayedat thetopof theheadingdial,andthe headingsourceannunciatorindicatesHDG.

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Honeywell WEJANC’CITATIONn/V

WAYPOINT ALERT SAME HEADINGANNUNCIATOR OR NAV SOURCE(AMBER) (AMBER) (NOTE 3)

COURSE SELECT\ \ AFAILURE(AMBER DASHES) \

(NOTE2)

‘mI TGT VAR I

WEATHER RADAR-FAILURE (AMBER)

HEADING SELECT—FAILURE(AMBER DASHES)

‘r/-\–\

Ih“’ CRS MAGlfl WPT IL$l——- T A “.----M

m’.‘h

“o.RJ*’’’(X.Xt:

“/0—-—-

-aloonl=-

‘as+

“/@‘/ &

VOR2 /’/,$HDG

\A-O

!\:?o

c? @ \’\‘ftl,,\\\\\‘ GSPD

I --- KTS

““’~

zDME DISPLAYFAILURE(AMBER DASHES)(NOTE 4)

\ DME HOLDANNUNCIATOR(AMBER)

>GRouND SpEED

FAILURE(AMBERDASHES)(NOTE1)

NOTES:1.TTG AND ETFAILURESARE SIMILAR.2.DTRK FAILUREISSIMILAR.3.IFBOTH THE PILOTAND THE COPILOTSELECTTHE CROSS-SIDENAV SOURCE,THE NAVANNUNCIATORSARE AMBER.

4.AN AMBER N/AISDISPLAYEDWHEN SELECTEDLRNDISTANCE AD-18419432ISNOT AVAILABLE.

ED-600EHSICautionandFai1ureAnnunciations (Amber)Figure 6-6

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Honeywell W!K?’”c’CITATIONn/V

HEADING COURSE DEVIATIONFAILURE FAILURE (RED)(RED) (NOTE 2)

(NOTE2)

o

/ I I

CRS

‘,J

Wb

HDG1 HOGFL

ILS1-—- IOONM+10 II

\\’ N\ \\:..<

~ /<

.\ Q/

‘[

o.% 6’; -

~s o om=G

“/ ~“/@ ~=,>

0/ .\ o

““/,/,p\\\’” GSPDF4MDbll m

1<

II ___ 100 KTSDASHES(NOTE2)

\

/

NOTES:1.VNAV AND GLIDEPATHDEVIATIONFAILUREISSIMILAR,2.INTHE EVENTOF A HEADINGFAILURE,THE COURSE SCALEAND RED X WILLNOT BE DISPLAYEDAND THE CRS AND HDGREADOUTS WILLINDICATEAMBER DASHES.

-GLIDE SLOPEDEVIATIONFAILURE (RED)(NOTE1)

AD-18420-R2

ED-600EHSI Display Failure Annunciations (Red]Figure 6-7 22-14-00

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Honeywell tiirJfrANcECITATION11~

16. C. (3)

(4)

(b) CourseDeviation,GlideslopeDeviation,VerticalDeviation,AzimuthDeviation,or GlidepathDeviationFailure- A failureof anyof thesesystemsresultsin theremovalof thedeviationpointer,anda red“X”drawnthroughthescale.

(c) InternalFailure- Intheeventof an internalfailurewithinthedisplaysystemitself,thedisplaywillbe blank. Afailureof thesymbolgeneratorinput/outputprocessorwillbeindicatedby a red “X”centeredon thedisplay,withannunciation“SGFAIL.” (SeeFigure6-4.)

PartialCompassFormatandWeatherRadarDisplay(SeeFigure6-8.)

The partialcompassmodedisplaysa 90 degreearcof the compasscard. Pressing the FULL/ARC button once on the DC-811 DisplayController causes the heading dial to change to the partial compassformat.. Pressing the WX button on the Weather Radar Indicatorallows weather radar returns to be displayed on the partial compass.The followingfeaturesareavailableduringpartialcompassoperation:

(a)

(b)

(c)

Target Alert (TGT)and Variable Gain (VAR) Annunciator - Thetarget alert annunciator warns of level 3 targets. A green TGTindicatesan armedcondition,whilean amberTGT indicatesaweatheralertcondition.VAR indicatestheradaris operatinginthevariablegainmode.

WeatherRadarReturns- Weatherinformationfromthe radarcanbe displayedin partialcompassmodeby pressingtheWX buttonon theWeatherRadarIndicator.The colorsusedare:

Return ~ ~

Level1 Green CyanLevel2 Yellow MagentaLevel3 Red B1ueRTC B1ue N/A

RangeRings- Rangeringsaredisplayedto aidin theuseofradarreturnsandpositionof navaids.Theouterrangeringisthecompasscardboundaryandrepresentstheselectrangeontheradar. Therangeannunciationon the innerringrepresentsone-halftherangesettingof theweatherradar. If theradaris turnedoff,thenby defaultthe outerrangeringis 100NM.

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P-650WX MODE

ANNUNCIATIONS

● WAIT (GREEN)● STBY (GREEN)● TEST (GREEN)● WX (GREEN)● RCT (GREEN)● GCR (AMBER)● CR/R (AMBER)● GMAP (GREEN). FAIL (AMBER)● CYC (GREEN)● TX (AMBER)

Honeywell Kl!lL5PNcECITATIONIt/v

TGT OR VAR ANNUNCIATOR 1

\

WX TILT ANGLE—

NAVAID=

WINDVECTOR -DISPLAY

● TGT: TARGET AI+13T

–GREEN-SELECTED–AMBER-LVL 3 TGT DETECTED

● VAR: VARIABLE GAIN (AMBER) Jf

./

\

3

/

.

/RANGE ANNUNCIATION(INNER RANGE IS 1/2 THERANGE SETTING OF THEWEATHER RADAR)

/

WEATHERRADARRETURN

RANGE7 RINGS

AD-18421-R2

ED-600EHSIPartialCompassDisplaysFigure6-8

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Honeywell M!WAN’ECITATIONV

6. C. (4) (d) WindVectorDisplay- Windvectorinformationisdisplayedleftof bottomcenter.Thewindis shownin Figure 6-9 withvelocity and direction or can be broken into head/tailcomponent and crosswind component as shown in Figure 6-8.Figure 6-8 shows a 25 knot tailwind and a 15 knot left cross-wind component. In bothcases,the arrow shows the directionand the number indicates velocity of the wind. The type ofdisplay is determined during installation. The windvectorsareavailablefromlongrangeNAV systems suchas VI..FandINS.

(e) Navaid- Navaidpositioncanbe selectedduringMAPmode. Thesourceof thenavaidpositionmarkersis selectedandannunciatedin conjunctionwiththe associatedbear~ngsourceandis colorcoded.

(f) WX AntennaTiltAngle- Theangletheweatherradarantennaispositionedisdisplayedin positivedegreesforup tiltandnegativedegreesfordowntilt.

(g) WX ModeAnnunciator- Thisannunciatorindicatesthemodeofoperationof the radar.

(5) LongRangeNavigationMapMode(SeeFigure6-9.)

The EFIShasthecapabilityof displayingmultiplewaypotntsfromalongrangenavigation(LRN) system. Thesewaypointsmustbe presentin a distance/bearing format. The systemwillnotacceptmultiplewaypointsin a latitude-longitude format.

With an LRN programmed for multiple waypoints in distance/bearingformat, and WX radar range set to a range allowing displayofmultiplewaypoints,selectingtheMAPmodeon theDC-811withtheLRN selectedwillpermitthemultiplewaypointsto be di$playedonthe EHSI.

The EHSIcandisplayup to sixLRNwaypointsandtwoVORstationnavaidsymbolsat the sametime. ThisassumesallwaypointsandVORstationsarewithinthe selectedWX rangeandallarewithinthelimitsof the headingdisplayof theEHSIin theMAPmode.

Upon

(a)

(b)

selectionof theMAPmode, the following will occur:

The course select pointer and HSI-type coursedeviationbardisplayswill be removed.

Both bearing pointers will be removed.

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Honeywell M&wJ.rANcECITATION V

6. C. (5) (c) A digitalcourse deviation display will be present on thebottom of the EHSI display. This willshowthe positionof theaircraftwithrespectto thedesiredtrack.

(d) The multiple waypoints wil1 appear on the EHSI.

● Eachwaypointwill be identified by a number 01 through 99or when the LRN communicates by the GAMA standard busforalphanumericsthewaypointwillbe identified by name.

. The waypoint to which the aircraft is flying is magenta incolor. All other waypoints are white.

● A white track lineconnectswaypointto waypoint.

● If the EFISis receiving valid VORstation and DME distance,the navaids forthetwoVOR stations will be available fordisplay on the EHSI,no matterwhere the bearing selectorswitches are set. The blue navaid will be VOR 1 (NAV 1),and the greennavaidwill be VOR 2 (NAV 2)

(e) For convenience, the actual heading indicated by the headingdial is numerically displayed at the top of the EHSI.

(f) Thedesiredtrackannunciatoranda digitalreadoutof thedesiredtrackfrompastwaypointto thenextwaypointareshownintheupperleftcornerof the EHSI.

(g) ATo-From indication is displayed to the right of the desiredtrack digital readout. It will indicate TO when the aircraftis flying to the waypoint.

(h) Thefollowingdisplaysfunctionas previouslydescribed:

●

●

●

●

●

●

●

●

●

HeadingSourceAnnunciatorNavigationSourceAnnunciatorDistanceDisplayRangeRingsAircraftSymbolGroundspeedHeadingSelectDisplayandHeadingSelectBugHeadingDialWeatherRadarandTiltAnnunciator

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VOR STATIONBLUE FOR VOR 1GREEN FOR VOR 2

\

NAVAIDSOURCEANNUNCIATOR /

Honeywell tifrlr’”c’CITATIONn/V

WIND VECTOR /DISPLAY

“-~9\TGT MANZYWx-3°A A KDVT

VOR I

\

50A&

HDG ‘l& GSPD022 25? O.OL 360 KTS

/@ @ /

\ MULTIPLE LRNWAY POINTS

AC-18422-RI

LRN Map ModewithMultipleIdaypointsFigure6-9

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Honeywell Uil!!fPANcECITATIONV

6. C. (6) Short Range Navigation MAP Mode(SeeFigure6-10).

Uponwill

(a)

(b)

(c)

(d)

(e)

selectionof theMAPmodeandthe SRN VORmode,the followingoccur:

ThecourseselectpointerandHSI-typecoursedeviationbardisplayswillbe removed.

Bothbearingpointswillbe removed.

A digitalcoursedeviationdisplaywill be present on thebottom of the EHSI display. This will show the position of theaircraft in nauticalmilesto theleftor therightof thepresenttrack.

FormapswithVOR stationsin viewon the EFI$map a selectedcourse line is drawn through the displayed navigation source.Thesolidlinerepresentstheinboundselectedcourseto thestation.Thedashedlinerepresentstheselectedoutboundradialfromthe station.If available,a navsourceidentifiermay be displayedadjacentto thenavaidsymbol.Cross-sidenavaididentifiersarenotavailable.

FormapswithVOR stationsoutof rangeof theEFISmap,eithera solidmagentaline or dashed magenta line will appear ifwithinthe90°arc. A solidmagentalinewithan arrowindicatesthe inboundcoursenecessaryto flyto the station.A dashedmagentalineindicatestheoutboundradial.

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INBOUNDSELECTEDCOURSETOVOR STATIOP

Honeywell WURANC’CITATIONn/V

3

1

VOR1 ‘A

1;.5

VOR2HDG * GSPD022 14.7R 100 KTS

SRN (VOR)Map ModeFigure6-10

. OUTBOUNDRADIAL FROMVOR STATION

AD-18423-RI

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Honeywell UNWANCECITATIONn/V

6. D. CompositeDisplay(SeeFigure6-11.)

In the event of a display unit failure, the EADI/EHSI DIMcontrol on theDC-811 Display Controller is turned to the OFF position to display acomposite attitude and NAV format on the remaining good display head.Figure 6-11 defines the location and form of the compos~te displayelements. As in normal EADI and EHSI presentations, all elements are notdisplayed at the same time. The presence or absence of each displayelement is determined by flight phase, NAV radio tuning, selected flightdirector mode,absolutealtitude,etc. The failure,caution, and warningannunciations function is much the same as for the normal display mode.

To!FRofvf ROLL ATTITUDE ROLL NAVIGATION SOURCE DISTANCE

COURSE/DESIREDTRACK DISPLAY

HEADING~DISPLAY

HEADING SELECTDISPLAY

COURSE FORE LUBBER COURSEOR COURSEOR HEADINGTPPESELECT LINE AZIMUTH AZIMUTHPOINTER

DISPLAYDEVIATION BAR DEVIATION

NOTE: DISPLAY

WHEN VSOR IAS MODESARE SELECTED, AIR DATACOMMAND INFORMATIONREPLACES THE HDGSOURCE ANN. AD-I S424- RI

CompositeDisplaySymbolDefinitionFigure6-11

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Honeywell I&MY’”c’CITATIONn/V

6. E. EFISSelfTest

The EFISsystem is continuously testing itself and therefore a manuallyinitiated selftestis notrequiredas partof theaircraftpreflighttest. The manually initiated self test is provided forthefollowingreasons:

. The EFISmanuallyinitiatedtestsymbologyprovidesa convenientmethodforthepilotto familiarizehimselfwiththeformatusedforvariousfailuremodes.

. The radioaltimetersystemcanbe commandedintotestmodeusingtheEFIStestswitch.

The EFIScanbe manuallyselftestedusingtheDC-811DisplayControllerTestswitch.Thefollowingtestroutineisdisplayed:

~: Testof the EFISis onlyfunctionalon theground.Thd radio

1altimetertestis functionalat alltimesexceptduringGS CAPorGP CAPmodes.

● Courseselect,headingselect,DH set,distanceandGSPD/TTGdigitaldisplaysarereplacedby amberdashes.

● ATT

● All

● All

andHDGdisplaysareflagged.

pointer/scalesareflaggedwitha redX.

headingrelatedbugs/pointersareremoved.

. Commandbarsarebiasedfromview.

. Radioaltimeterdigitalreadoutdisplaysradioaltimeterselftest-value. Slewsto 100feetfor Honeywell radio altimeter.

● Comparator monitor annunciates ATT, HDGand ILS(ifILSsourcesareselectedon bothsides)or MLS (IfMLS sources are selected on bothsides).

● Test(inmagentacolor)or Fail(inamber)is annunciatedin theFDLATcapturelocation.

. FD modeannunciationsareremoved.

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Honeywell ti2fJE~ANcECITATIONV

6. F. ED-600Used as a Multifunction Display (MFD)

(1) GeneralMDZ-605MFDSystemInformation

TheMDZ-605MultifunctionDisplaySystemhasthreemajorsub-functions.Oneof themostsignificantis itsabilityto backup EFISsymbolgeneratoror the EHSIdisplay.ShouldtheSG fail,thepilotcan selecttheMFDsymbolgeneratorto takeoveroperationof the failedEFISdisplayswithallfunctionsandoperationsunchanged.The EFIS DC-811 controller willcontinueto operatethedisplayformatsas before.TheMFDdisplaycanalsobe usedas abackupintheeventof an EHSIdisplayfailure.

TheMFD systemgreatlyexpandson thenavigationmappingcapabilitiesof theEFIS. This is primarily dueto thefactthattheMFDdisplayareacanbe usedexclusivelyformapformatswithouttheneedfortheessentialheadingandnavdatathi~tthe EHSIalsohasto contain.Someof theadditionalinformationthatcanbeaddedto thetraditionalmapdisplayof waypointlocationsincludeswaypointandVOR identifiers,aircraftpresentpositionin LAT/LONcoordinates,andthe “TO”waypointtimeto go or ETA,as wellasestimatedfuelremainingat the “TO”waypoint.Thisadditionaldatais suppliedby theoptionalFlightManagementSystemfordisplayontheMFD. TheMFDsystemalsohasa north-upplanfunctioninadditionto theusualheading-upmapdisplay.Bothformatsmakeuseof a designatorcontrolledby theMC-800controllerjoystick.Thepositionof thedesignatorcanbe automaticallytri~nsmittedto theFMSto be usedindefininga newwaypoint.

(2) MFDWeatherRadarMode

Theweatherradardisplayis identicalto theweatherradardisplayon the EHSIpartialcompassdisplayas shown in Figure6-8.

ColorweatherradarinformationfromthePRIMUSQ650Receiver-Transmitteris presentedin theformof an overlayby rastertechniqueson thestrokewrittendisplay.A whiteouterrangeringis provided.An innerrangeringis alsoprovidedwithitsassociatedlabelalsostrokewritteninwhitecharacterson therightside of the display. Weather intensity leve”ls aredifferentiated by the standard convention of red,yellow,green,andblueareas.

Thebluefieldisgeneratedby therain-echoattenuationcompensationcircuitryto warnthepilotthattheweatherlevelsinthisareacannotbe calibratedandarethereforeof unknownprecipitationdensity.Groundmappingmay alsobe displayedon thestandardconventionof magenta,yellow,andcyanareas. The radarmodeis annunciatedon theleftsideof thedispla:y.

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Honeywell tiiWJfPANcECITATIONV

A targetalertannunciatoris providedabovethe mode annunciator towarn of level 3 targets 7.5 degrees on either side of the aircraftflight path. A green TGT annunciates this feature, changing to anamber TGT whenactive.Whenthegainis notcalibrated,an amberVAR annunciatorwillbe displayedinthetargetalertarea.

A weatherradarfailurewillremovetherasterweatherdisDlavandforcethemodeannunciatorto displayWX in amber

A magentaTX isdisplayedwhereWX is annunciatedradaris transmittingandweatherisnot selected

6. F. (3) MFDMap Mode(SeeFigure6-12.)

charac?,e;s.”

whentheweatherforMFD display.

Two formats of NAVmappingareselectableusingthe alternateactionMAP/PLANbuttonon theMC-800MFDController.TheMAP fc~rmatexpandsthetotallyindependentEHSImap by increasingthemaximumrangebeyondthenormalradarranges,andutilizesallthedataavailablefromselectablenavigationsources.TheMAP formatisalwaysorientedto theaircraftheadingwiththeaircraftpositionat lowercenterandthemaproutemovingtowardthe aircraft.Whencoupledto a compatibleLNAVor FMS, the NAV route with up to 6waypoints can be displayed to the range limit of 1200 miles, or thenext route segment can be displayed. When weather returns areselected, the maximum selectable range is slaved to the radar WI-650setting. With a compatible NAV source,suchas the Honeywell FMSwithstoreddatabase,otherpertinentnavigationdatabeyondroutemappingsuchas VORstationlocations,fuelremaining,andtime-to-goto thenextwaypoint,canbe selectedanddisplayed.Amovabledesignatorcanaidin relocatingthenextwaypoint.Whenthedesignatorismovedfrom“home”positionthe Lat-Londisplayreflectsthedesignatorpositionwhichthencan be automaticallyloadedas thenextwaypointintocompatibleLNAVor FMS sources.Themapmodedisplaysshownon Figure6-12aredescribedbelow.

‘(a) HeadingDisplay- TheHDGdisplayindicatesthe a~of theaircraft.It isthe sameheadinginformaton theEHSI.

(b) SelectedNAV Source - The selected longrangenavis displayed.

tual headingor]displayed

gationsource

(c) Distanceto “TO”Waypoint- The distance to the designatedwaypoint is displayed in nauticalmiles.

(d) AirportAnnunciator- The airportsare identifiedas a functionof theAPTbuttonon theMC-800.

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Honeywell WNFANC’CITATIONV

6. F. (3) (e) RangeRings- Rangeringsaredisplayedto aid in the use ofradar returns and position of navaids. IfWX modeis selected,the outer range ring is the compass card boundary andrepresents the select range on the radar. Th[?rangeannunciation on the inner ring represents one half the rangesetting of the weather radar. The INC/DECswitchon theMC-800increasesor decreasestherangeif WX mode is notselected.

(f) DesignatorAnnunciations- Displaysthecourseanddistancetothedesignatorfrompresent position.

(9) WaypointandWaypointData- The number of available waypointsis dependent upon the LRN which is providing the data, whiletheselectedrangedeterminesthenumberof displayedwaypoints.Thewaypointto whichthe aircraftis flyingismagentain color. All otherwaypointsarewhite. TheDATbuttonon theMC-800willaddthefollowinginformationto thedisplayif it isavailablefromthelongrangeNAV system.

. Waypointidentification(eithernumberor rlame)

. Distanceto “TO”waypointin nauticalmile:

. ETAin GMTat the “TO”waypoint,if available,or TTG

(h) AircraftSymbol- The aircraftsymbolprovide!a visualcueasto theaircraftpositionin relationto thedesiredtrack.

(i) CrosstrackDeviation- Indicatesthedeviatiorlin nauticalmiles to the right (R) or left (L) of the desired track.

(j) DisplacementLine- Indicatesthepositionof thedesignatorrelativeto thenoseof the aircraft.

(k) Designator- Thepowerup homepositionof thedesignatoristheaircraftpresentposition.Thedesignator’slatitudeandlongitudeis continuouslydisplayedin the lower left corner ofthe presentation. Manipulation of the designator is controlledby the Joystick and the SKP,RCL,and ENT buttons on theMC-800. The designator’s latitude and longitude can betransmitted to the selected LRN as a map reference point.

(1) WX AntennaTiltAngle- The angletheweatherradarantennaispositionedis displayedin positivedegreesfclrup tiltandnegativedegreesfordowntilt.

(m) WeatherRadarMode- Displaysthestatusof theweatherradarsystem.Weatheris addedto thedisplayandMX is annunciatedby pressingtheWX buttonon theMC-800.

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Honeywell !!fi~~f~””c’CITATION V

6. F. (3) (n) TargetAlert/VariableGain- A targetalertannunciatorisprovidedto warnof level3 targets7.5degrees on either sideof theaircraftflightpath. A greenTGT annunciates thisfeature, changing to an amber TGTwhen active. Whenthegainis notcalibrated,an amberVARannunciatorwillbe displayedin thetargetalertarea.

(o) VOR/DMESymbols- Thesesymbolsareaddeduponactuationof theVOR buttonon theMC-800. TheyrepresenttheVOR stationswhicharebeingusedby the LRN.

(P) DesiredTrack(DTRK)Line- Thewaypointsareconnectedby awhitetrackline. Thedesiredtrackannunciatoranda digitalreadoutof thedesiredtrackfrompastwaypointto thenextwaypointareshownin the upperleftcornerof the[display.

HEADING SELECTEDNAVDISPLAY

\

SOURCE

/

DESIREDTRACKANNUNCIATION

WAYPOINT

DTRKLINE— “VOR/DME m

DESIGNATORANNUNCIATION

GAIN 1 /ff2”-

TARGETALERT/VARIABLE

ANNUNClATOR~><~AN150-WX MODE

/.

rDEs,GNAToRpi’R:qy~ii :j!!syWXANTENNA/TILT ANGLE

F:%%?oRe -+

“TO’’WAYPOINTIDENTIFICATION

TTGINMIN

DISPLAC~MENT CRO&STRACK AIRCkAFTLINE DEVIATION SYMBOL

AD-1 8386

MFDMapModeFigure6-12

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Honeywell M!JR’”c’CITATION V

6. F. (4) MFD Plan

A unique

(5)

Mode (See Figure 6-13.)

NAV PLAN format features a “truenorth-up”orientationinwhich“theaircraftis positionedwithrespect to the NAV route andprogresses along the route, while the maximum range is depicted by acircle around the outer perimeter. Thenorth-uporientationenhancestheflightplanningfunctionandfurtherclarifiestheaircraftrelationshipto theprogrammedroute. Inthisdisplaythedesignatoris “homed”to the “TO”waypointandbothappearin thecenterof thedisplay.The aircraft symbol is still plotted atpresent position (if present position is on the display) and isoriented with respect to heading. If the designator is movedfromthe “TO”waypoint,thedesignatorsymbolwillremainin thecenterof thedisplaywhilethedesignatorcourse/distanceannunciationinthelowerrightcornerwillbe fromthewaypoint.Thedesignatorremainsin thecenterduringSKP and joystick operations. Weatheris not available in the PLAN mode so range is controlled solely fromthe MC-800. Other operations are the same as forMAPmode.

MFDChecklistDisplay

TheMFD SymbolGeneratoris capableof storinganddisplaying200,400,or 800pagesof text. Thesepagesarestoredin controlledinternalPROMwithcontentas definedby theaircraftoperator.Pagecompositionis 12 lineswitha maximumof 24 charactersperline. All textis strokewrittenforsunlightreadability.

TheNORMbuttonon theMC-800providesentryintothenormalchecklistdisplayfunction.Thenormalchecklistsarearrangedintheorderof standardflightoperations.Buttonactuationscausepresentationof thenormalchecklistindexpagethatcontainsthelowestorderincompleteandunskippedchecklistwiththeactiveselectionat thatchecklist.

TheSKP,RCL,PAG,andENTbuttonsandthejoystickon theMC-800providecontrolof thisfunctionandaredescribedin paragraph6.K.(5).

TheEMERbuttonon theMC-800providesentryintotheemergencychecklistdisplayfunction.Actuationof EMERresultsinthepresentationof thefirstpageof theemergencychecklistindexwiththeactiveselectionat thefirstchecklist.The SKP,RCL,PAG,andENT buttons and the joystick shall provide control of this functionand are described in paragraph6.K.(5). ThesecontrolsperformasdescribedforNORMwiththeexceptionof the action taken uponcompletion of the checklist. All checklist items are removed fromthe page and “EMERGENCY PROCEDURE COMPLETE” is written belowtheamberchecklisttitle. Thiswillbe clearedwhenthe indexisselected.

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Honeywell M!RI!ANC’CITATION V

SELECTED NAVSOURCE

I

“NORTH-UP”IDENTIFIER

DTRKLINE

WAYPOINT

LAT/LON

AIRCRAflSYMBOL

MFD PIan ModeFigure 6-13

DISTANCE TO“TO- WAYPOINT

TUNED VOR/’DME

DISPUCEMENTLINE

DESIGNATOR

DESIGNATORANNUNCIATIONSCOURSE FROMWAYPOINT

DISTANCE FROMWAYPOINT

“TO WAYPOINTIDENTIFICATION

TTGIN MIN

AD-10312-R1

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Honeywell WRANcECITATION V

6. F. (6) EFISBackupModes

Selection of EFIS backup by the MFD is accomplished by the rotaryMODE selector switch on the MC-800 MFD Controller. Normal MFDfunctions are available in the MFD position, and F.FISbackupmodesare obtained by selecting the HSI or SG positions.

. HSI- Selectionof thispositionwillresultin an HSIdisplayontheMFD. Compositionof theHSIwillbe determinedby theEFISDC-811DisplayController.

● SG- Selection of this position willresultin replacement of theEFIS symbolgeneratorby theMFD symbolgeneratorfortheEFISdisplays.In thiscasetheMFD CRT will be blanked. Compositionof the EFIS displays will be determined by the EFIS DC-811Display Controller.

G. ED-600FunctionalOperation(SeeFigure6-14.)

(1) Deflection System

The ED-600displayunitiscapableof operatingineitherrasterscanor strokewritingmodes. In thestrokewriting modethedeflectionamplifiersoperateas currentoutputpowerstages.Thedeflectionyokecurrentsaresampledandfedbackto the inputofthepowerstagesto providedeflectionamplificationfor each modeof operation. The deflection amplifier output stages,in boththeverticalandhorizontalaxes,areconstructedusingcomplementarypowerFETsforhighpowergain,hencereducedcomponentcount.Circuitryis containedwithinthedeflectionsystem to provideforthe “pincushion”linearitycorrectionrequiredby theCRTphysicalgeometry.

In orderto providethehighestpossibledatathroughoutfromthesymbolgeneratorto thedisplay,a “handshake”systemis used to

tellthesymbolgeneratorwhenthe displaydeflectionamplifiersarethroughslewingandreadyto write. Thisstrokereadysignalisgeneratedby a windowcomparatorwhichmonitorsthe input/outputstatusof thedeflectionamplifiers.All of thedisplayunitdeflectionsignalsarefedthrough a multiplexer. This allows thedisplay to be driven from two different symbol generators asrequired in thereversionarymode.

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Honeywell M!UEANCECITATION V

6. G. (2) VideoandDimmingSystem

The videosystemprovidesthe individualdrivesignalsto eachofthethree(red,blueandgreen) electron guns in the CRT. Amplitudeof thegundrivesareadjustedto providetherequiredcolorselectionmenu. Four bits of colorselectiondataareusedprovidingfora possible8 colors on both raster and strokeoperation (for a total of 16).

The overallintensityof thedisplayoutputis controlledin thevideosystemby a signalfromthe auto-dimmingsystem. In theauto-dimmingsystem,thepilotselectedintensity(fromthedimmingcontrolon theDC-811controller)ismodulatedby a controlsignalgeneratedfromtwostrategicallylocatedambientlightsensors.

(3) SystemMonitor

A system monitor is incorporated in the ED-600 to provide CRTphosphorprotectionanda systeminvalidsignalto thesymbolgeneratorwheneverthefollowingconditionsaredetected:

s Lossof deflection in eitheraxes. AbnormalpowersupplyoutputsQ ImproperCRT filament

The circuitryalsoprovidesa 5-secondtimedelaybetweenapplicationof CRTfilamentcurrentandhighvoltagepowerturn-on.Thisallowsthe systemto stabilizequicklyandalsoprotectstheCRTcathodesfromtheeffectsof excessiveinitialanodecurrent.

6. G. (4) PowerSupply

All powerrequiredby the ED-600displayunitis providedfrom theaircraft 28 voltsdc busvia a power supply subsystem located withinthe display unit. This power supply subsystem consists of a highefficiency switching regulator and a solid state high voltage powersupply.

The highvoltagepowersupplyis a ferro-resonantswitchingconverterandhighvoltagemultiplierassembly.Thissupplyfeatureswellregulatedhighvoltage(14kV) to preventintensityandsizevariationsin thepicturedueto loadvariationscausedbychangesin picturecontent.The high voltage portions of the powersupplyareencapsulatedas wellas theanodeandfocusleadassembly.Thisis requiredfor unpressurized environments.

Whenan ED-600displayunitis to be usedas an EADI,aninclinometeris attachedto the frontof thedisplay.Provisionshavebeenmadeto lightthe inclinometerfromthe standa)pdaircraft5 voltslightingbus.

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Honeywell WJ?ANCECITATIONV

28VDCAIRCRAFT

(:+-# I%JE% ;!INTERNAL HIGH VOLTAGE

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22-14-00Page195)196

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Honeywell WME!!ANC’CITATION V

Thispageintentionallyleftblank.

22-14-00Page-197

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Honeywell WUWANCECITATION V

6. H. DC-811DisplayController(SeeFigures6-15and6-16,andTable6-2.)

AD-18425

DC-811Display ControllerFigure 6-15


Lenath ........................................ 6.87 in. (174.50 mm)Wi(He

Weight

~h ......................................... 5.75in. i146.05mm~. #ght

(max

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25in. (57.15mm)

mum) ...................................... 1.8 lb (0.82kg)

Power Requirements:

primary ............................................ 28Vdc,Lighting ..............................................sVdc.

Mating Connector:

J1

Mount

5 W max5 W max

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MS27473E20-B35SC

ng ............................................Unt ScrewFasteners

DC-811 Display Controller Leading ParticularsTable 6-2

22-14-00Page198

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Honeywell INKY’””CITATION V

The DC-811DisplayControllerprovidesthemeansby whichthepilotcancontrolthe EADIand EHSIdisplayformatting.Alsoincludedon theDC-811 arethe bearingselectknobsanddisplaydimmingcontrols.Thefollowing paragraphs describe the controller functions.

6. H. (1) FULL/ARCButton- The FULL/ARCbuttonisusedto c:langetheEHSIdisplayfromfullcompassto partialcompassformat. In the fullcompass mode,360degreesof headingaredisplayed.In thepartialcompassmode,90 degreesof heading are displayed. Successivetogglingof the FULL/ARCbuttonchangesthedisplayback-and-forthfromthefullcompassto thepartialcompassdisplay.

(2) MAP Button- By pressingthe button,theful1 compass display may bechanged to the partial compass format allowing one waypoint foreachbearingpointerandVOR/DMEgroundstationpositionsto bedisplayed.The informationwillonlybe displayedifwithintherangeselected.If inWX mode,activationof the buttonwillselecttheMAP formatwithweatherradarinformation.

(3) Weather(WX)Button- TheWX button is usedto callup weatherradarreturnson thepartialcompassMAPdisplayof the EHSI. Ifthe EHSIis in thefullcompassMAPmodeinitially,pressingtheWX buttonchangesthedisplayto thepartialcompassMAPmodeanddisplaysweatherradarreturnsfromtheweatherradaror a weathertestpattern.If presently in MAP mode,activationof theWX buttonwillsuperimposeweatherradarinformationovertheMAP information.Asecond push of the WX button will remove the weather information.

(4) Groundspeed/Time-To-Go (GSPD/TTG) Button - By pressing the GSPD/TTGbutton, groundspeed or time-to-go willalternatelybe displayedinthelowerrightcornerof the EHSI.

(5) ElapsedTime(ET)Button- By pressingtheET button,elapsedtimeisdisplayed.Pressingthe ET buttonthefirsttimewillresetthedisplayedtimeto zero. Thetogglingsequenceof ‘:he“ET”buttonisreset,start,stop.

(6) Navigation(NAV)Button- By pressingtheNAVbutton,VOR/LOCinformationis selectedfordisplayon theEHSI.

(7) FlightManagementSystem(FMS)Button- By pressingthe FMSbutton,flightmanagementsystem(FMS)informationis selectedfordisplayon the EHSI.

22-14-00Paqe198.1M~r 15/89

Use or disclosure of Information on this page IS subject to the restrictions on the title pag? of this document.

Honeywell WWANC’CITATIONV

6. H. (8) BearingSource Select Knobs - The EHSI has the capabilit~ ofdisplaying two independent bearing pointers. The selectable bearingsources for each pointer are as follows:

BRG O BRG <>

NAV 1 NAV 2ADF 1 ADF 2FMS1

(9) DimControls- Thedimmingsystememployedby the EFISis semi-automatic.Two inputscontributeto theoveralldisplaybrightnessof eachED-600ElectronicDisplay:

● Ambientlightsensedby thephotosensorson eachED-6C0. Settingof thedimmingcontrols

TheDIMpot setthenominalintensityforeachdisplay.Thephotosensorslocatedon eachED-600causethe lightoutp~tof eachdisplayto be modulatedaboutthenominalintensityas a functionofthelightincidenton eachdisplay.

(a) ADI DIMControl- The ADI DIM control dims the rastEr andstroke writing on the EADI. Turning the control to the OFFposition causes the EADI to go blank and the composite modetobe displayed on the EHSI.

(b) HSIDIMControl- The HSIDIMcontrol dims the raster andstroke writing on the EHSI. Turning the control to the OFFposition causes the EHSI to go blank and the composite mode tobe displayed on the EADI.

(c) WX DIMControl- TheWX DIMcontroldimsonlytherasteron theEHSIwhich contains weather radar information. Turning thecontrol to the OFFpositionremoves the weather radar display.If in thecompositemode on the EHSI, the WX DIM control isused to dim the attitude sphere intensity.

(10) DecisionHeight(DH)Knob- Rotationof the innerDH knob allows thedecision height displayed on the EADI to be adjusted between 10 and990 feet in 10-footincrements.By rotatingtheDH knob completelycounterclockwise, the decision height display may be remcved fromtheEADIdisplay.

(11) TEST(TST)Button - TheTST buttonallowsfortestingth~radioaltimeterand EFISwhen on the ground or the radio altimeter onlywhenin the air, if not in the GS capture mode. Refer tc paragraph6.E. for test procedure.

22-14-00Page198.2Mar 15/89

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Honeywell MWJRANC’CITATIONV

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Honeywell !NNJRANC’CITATION V


22-14-00Paqe 198.5M;r 15/89

UseordisclosureofInformationon this page IS sub~ecf to Ihe restrictions on the title pag ? of this document.

Honeywell MNNJFANC’CITATION V

6. I. RI-106SInstrumentRemoteController(SeeFigures6-17and6-18,andTable6-3.)

The InstrumentRemoteControllerinterfaceswiththe symbolgeneratortoprovideheadingandcourse selection. Activation of the PULL SYNC switchcauses synchronization of the heading bugto present heading (lubberline). The PULLDIR switchallowsautomaticselectionof a TO directiondesired VORcoursehavingzerodeviation.

HEADING

a0;PULL(BJO SYNC

RI-106SInstrumentRemoteControllerFigure6-17


Length .......................................... 2.75 in. (69.9mm)Width.......................................... 5.75in. (146.1mm)Height........................................ 1.50in. (38.1mm)

Weight(maximum)...................................... 0.8 lb (0.36kg)

PowerRequirements:

SynchroExcitation.............................. 26V, 40f)l-iz,2.4vABlue-White Lighting .............................. 5 V acordc, 3.3 VA

MatingConnector:

J1 .................................................... MS3126F14-19S

Mounting............................................UnitScrewF~~steners

RI-106SInstrumentRemoteControllerLeadingParticulars

Table6-3

22-14-00Page198.6Mar 15/89

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Honeywell WRANCECITATION V

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RI-106SInstrumentRemoteControl1er SchematicFigure6-18 22-14-00

Page 198.7Mar 15/89

Use or disclosure of information on this page is subject to the restrictions on the title pag~? of this document ‘

Honeywell W%”’””CITATION V

6. J. SG-605Symbol Generator (See Figures 6-19 and 6-20, and Table 6-4.)

011s41-)71

SG-605SymbolGeneratorFigure6-19


Length ........................................ 16.45 in. (417.83 mm)Width .......................................... 4.91 in. (1;?4.71mm)Height........................................ 7.62in. (193.55mm)

Weight(maximum)...................................... 16.Olb (7.24kg)

PowerRequirements.................................... 28 V dc,70 W max

MatingConnector:

J1 ........................................ DPX2MA-A106--A1O6P-33B-OO63J2 ........................................ DPX2MA-A106P-A1O6P-33B-OO64

Mounting....................... TrayModelMT-800,PartNo. 7003272-901,BoxmountTray,PartNo.8314,or

BarryTray,PartNo.93995-1

SG-605SymbolGeneratorLeadingParticulars

Table6-4 22.14-00Page198.8Mar 15/89

Use or disclosure ot information on this page is subject to the restrictions on the title pageof this document.

Honeywell M!MRANCECITATION V

The symbol generator is the heart of the EDZ-605 System. It receivesheading, attitude, and short and longrangenavigationsensorandweatherradarinputs.Italsoreceivesmodelogic inputs from the flightdirector. All inputs are processed and transmitted to the ED-600Electronic Displays as a function of the selections made on the DC-811Display Controller and RI-106S Instrument Remote Controller. In caseoffailureof thesymbolgenerator,backupis providedby theMFDSymbolGenerator.

22-14-00Page198.9/198.10

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Honeywell Hi}JfPANcECITATIONV

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Page198.11/198.12Mar 15/89

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Honeywell WiKW’”c’CITATION V


22-14-00Page198.13Mar 15/89

Use or dwclosure of inforrnattononhs pageISsubjectto the restrictions on the t}tle pa~e of this document

Honeywell M!JFAN’ECITATION V

6. K. MC-800MFD Controller(SeeFigures6-21and6-22,andTable6-6.)

AD-1 8426

MC-800MFDControllerFigure6-21


LengthWidth .:::Height ...

Weight (maximum,

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.59in. (167.39 mm)

................................... 5.75in.(146.05mm)

.................................... 2.25in.(57.15mm)

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.8lb (0.82kg)

Power Requirements:

Primary .......................................... 28Vdc, 5WmaxLighting ......................................... 28 V dc, 5 W max

MatingConnector:

J1 ................................................. MS27473E14-35S

Mounting ......................................... UnitScrewFasteners

MC-800MFDControllerLeadingParticulars

Table6-5

TheMC-800MFDControllerprovidesthemeansby whichthepilotcancontroltheMFDdisplaymodes and format. The followingparagraphsdescribethecontrollerfunctions.

22=14-00Page 198.14Mar 15/89

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Honeywell hi!ilIE~ANcECITATION V

6. K. (1) MAP/PLANButton - TheMAP/PLANbuttonalternatelyselectstheheading up MAPdisplayor theNorthup PLANmodefor display.

(2) Weather(WX)Button- The WX button is used to call up weatherradarreturnson theMFDmap display. When weather is displayed, the maprange is controlled by the WI-650 Weather Radar Indicator Rangeswitch.

(3) Normal(NORM) Button - The NORM button provides entry into the MFD’snormal checklist display function. Thenormalchecklistis arrangedin theorderof standardflightoperations.Buttonactuationscausepresentationof thenormalchecklistindexpagethatcontainsthelowestorderincompleteandunskippedchecklistwiththeactiveselectionat thatchecklist.The SKP,RCL,PAG,and ENT buttons andthe joystick provide control of this function.

(4) Emergency(EMER)Button- The EMERbuttonprovidesentryintotheMFD’semergencychecklistdisplayfunction.Actuationof EMERresultsin thepresentationof thefirstpageof thehighestprioritycallupwiththeactiveselectionat thefirstitemon thepage.

The SKP, RCL, PAG,andENTbuttonsandthejoystickprovidecontrolof thisfunction.

(5) Skip(SKP),Recall (RCL), Page (PAG),and Enter (EtiT)Buttons andJoystick - These buttons (PAGforchecklistonly) andthejoystickare usedto controlthechecklistandoperationof thedesignatoronthemap. Paragraph(5)(a)describesthechecklistcontrolandparagraph(5)(b)describesthedesignatorcontrol.

(a) ChecklistControl

. SKP - actuationskipstheactiveselectionto thenextitem.If the item skipped is the last item, the active selectionis the lowest order skipped item.

. RCL- actuationresultsinpresentationof the pagecontainingthelowestorderskippeditemwiththeactiveselectionat thatitem.

● PAG- actuation advances the page count. The activeselectionisthelowestorderincompleteitemon thatpage.if thereareno incompleteitemson the page,theactiveselectionisthefirstitemon thepage.

22-14-00Page 198.15Mar 15/89

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Honeywell WllR!’”c’CITATION V

. ENT- operation is dependent upon display if:

On an indexpage- actuationresultsin displayc]fthechecklistcorrespondingto the activeindexlineselection.Thechecklistis presentedat thepagecontainingthe lowestorderincompleteitemwiththe activeselection:Itthatitem. Ifthechecklisthadpreviouslybeencompleted,thesystemforcesall itemsinthe checklistto incompleteandpresentthefirstpageof thechecklistwiththeactiveselectionat the first item.

On a checklist page - actuation forces the active selectionto complete and advance the active selection to the nextincomplete item. If ENT is actuated with the activeselection at the last item in a checklist, the operationdepends upon the completion status of the checklist.

Ifthechecklistis notcomplete(oneor moreitemsskipped)the system presents the page containing the lowest orderincomplete item with the active selection at that item.

If thechecklistis complete(allitemscomplete)the systempresentsthe indexpagecontainingthe nexthigh~’rorderchecklistwiththeactiveselectionat thatchecl.list.

. Joystick- Thejoystickprovidesadditionalpagingandcursorcontrol.Eachactuationresultsin the actiondescribed:

- UP moves the active selection to the lower orcler item

- DOWNmovestheactiveselectionto thenexthigherorderitem(thisis identicalto SKP)

- LEFTresultsin presentationof the previouspage

- RIGHTresultsin presentationof the nextpag~’(thisisidenticalto PAG)

6. K. (5) (b) DesignatorControl

● SKP - actuatorskipsthedesignator’shomepositionto thenextdisplayedwaypoint.Whenactuatedwiththedesignatorat thelastdisplayedwaypoint,thedesignatorshallreturnto present position.

. RCL - whenthedesignatoris not at itshomeposition.actuation of RCL recalls the designator to the homeposition.Actuationwiththedesignatorat itshomepositionrecallsthedesignatorto presentposition(alreadythere).

f not

22-14-00Page198.16Mar 15/89

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Honeywell WMI!AN’ECITATION V

. ENT - when the designator is offset, actuation of ENT causesthe LAT/LON of the designator to be transmitted to theselected LRN as a requested waypoint.

. Joystick - the joystick provides four direction control ofthe designator: up, down,left,andright. The courseanddistanceto thedesignatorfromitshomepositionisdisplayedin the lowerrightcornerof thedisplay.

6. K. (6) VHFOmniRange(VOR)Button- The VOR button is us~~dto addVOR/DMEsymbolsto themapandplandisplays.

(7) Data(DAT)Button- The DATbuttonis usedto add ‘longrangenavigationinformationto themapandplandisplay:;.

. Firstactuationwilladdthe followinqdatato thelowerricihtcornerof thedisplay:

- Waypointidentification

- EstimatedTimeof Arrival(ETAat the “TO”waypointif known;the “TO”waypoint.

in GreenwichMeanTime(GMT)otherwise,Time-To-Go(TTG)to

. Secondactuation- If no destination information is known, thisstep shall be to data OFF. However,ifdestinationidentification,ETA,or TTG is known,thisstepshallreplacethe“TO”waypointdataas describedabovewith the destination data.If some destination data is known but the waypoint identificationis not, the mnemonic “DEST” shall be used in placeof thewaypointidentification.

(8) Airport(APT)Button- TheAPT buttonis usedto addairportdesignatorsto themap andplandisplays.

(9) Increase(INC)/Decrease(DEC)Range (RNG)Switch- Thisswitchincreasesor decreasestheselectedrange(5,10,25,50,100,200,300,600and 1200NM) if the weather radar (WX) mode is notselected. When WX is selected, the range is controlled by theWI-650 Weather Radar Indicator Range Switch.

22-14-00Paqe198.17Mar 15/89

Use or disclosure of information on this page is sub!ecf to the restrictions on the title page of this document.

Honeywell WJNANC’CITATION V

6. K. (10) ModeSelector- Thisis a threepositionrotary switch usedtoselectthe following MFD modesof operation:

● MFD - normal MFD operation● SG - pilot SG-605 backup● HSI - HSI backup

(11) DimControl- ThisknobcontrolsoverallMFDCRTdimmingin additionto the ED-600automaticphotoelectricdimming.

22-14-00Paqe198.18Mar 15/89

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Honeywell ~#If{ANcE

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Honeywell M!illE!ANcECITATION V

This page is intentionally left blank.

22-14-00Page 198.21Mar 15/89

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Honeywell M!U2AN’ECITATION V

6. L. MG-605MFD SymbolGenerator(SeeFigures6-23and6-24,andTable6-7.)

OPTIONAL CHECK LK3T MODULEY

AD- 10317-R1

MG-605 MFD SymbolGeneratorFigure6-23

22-14-00Paqe198.22Mar 15/89Useor disclosureof mformatton on this page IS subject to the restrictions on the title page of Ihm Jocumenl.

Honeywell KNEPANCECITATION V


Length ............................................ 16.65 in. (422.91 mm)Width............................................. 7.53in. (191.26mm)Height............................................ 7.62in. (193.55mm)

Weight (maximum) ..................................... 25.0 lb (11.34kg)

Power Requirements ................................... 28Vdc, 120Wmax

Mating Connectors:

J1 andJ3 ................................... DPX2MA-A106P-A1O6P-33B-OO99J2 ......................................... DPX2MA-A106P-A1O6P-33B-OOO1

Mounting............................................ TrayModelMT-61O,PartNo. 7007246-901

MG-605MFD Symbol GeneratorLeading Particulars

Table 6-6

TheMG-605MFD SymbolGeneratoris theheartof theMDZ-605MFD system.The symbolgeneratorinputportsareparalleledwiththeSG-605SymbolGeneratorinputports. All inputsareprocessedandtransmittedto theED-600MFDdisplayas a functionof theMC-800MFD Controllerwhenin theMFDmode. Whenin theSG backupmode,thedisplayfunctionsarecontrolledby theDC-811DisplayController.Whenin SG backupmode,theMG-605processesandoutputsthesamesignalsto theautopilotandflightdirectoras theSG-605SymbolGeneratordidbeforeit failed.However,theMG-605signalsareswitchedthroughthefailedSG. If theMFDchecklistisprovided,a checklistmoduleprogrammedto eachcustomer’soperatingrequirementsis installedin thefrontof theMFDSymbolGenerator.

NOTICE

If theMG-605MFD SymbolGeneratoris sentin forrepairor exchange,thechecklistmodulehasto be removedandretainedfor installationin thereplacementMG-605.

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Mar 15/89Use or disclosure of information on this page is subject to the restrictions on the title pa~,e of thw document.

DISCRETES

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MG-605MFDSymbolGeneratorBlockDiagram

Figure6-24 22-14-00Page198.25/198.26

Mar 15/89UseordisclosureotInlormallononthis page IS subjecl 10 the restrictionson the Mle page of this document.

Honeywell tii~;k~’”c’CITATION V


22-14-00Page 198.27Mar 15/89

UseordisclosureofinformationonIhlspageissubjecttotheres~ncllonsOntheIltlepa~~ofthmdocument.

Honeywell W!W’”c’CITATION V

7. FlicihtControlSystem

A. SP-200AutopilotComputer(SeeFigure218 (Section3), Figure7-1,andTable7-l.)

The Autopilot Computer processes information about the aircraft actualattitude versus a desired attitude as a function of selected flight modeto produce pitch, roll, and yaw control outputs. In addition to themodes selectable on the Autopilot Controller, the Autopilot will producepitch and roll outputs for any flight director mode except go-around.The computer also has torque switching, on the pitch and roll outputs, asa function of altitude.

I

SP-200 Autopilot ComputerFigure 7-1

22-14-00Paqe198.28

Mar 15/89Use or disclosureofinformationonthispageISsubjecttothe restncttons on the title page of this document.

Honeywell WiWANcECITATION V


Length ............................................ 12.65Width .............................................. 2.79Height ............................................. 7.62

n. (321.3mm)in. (70.9 mm)n. (193.5 mm)

Weight(maximum)....................................... 7.0 lb (3.18 kg)

Power Requirements ................. 115V, 400 tlz,40 VA; 28Vdc, 100W

MatingConnector:

J1 ............................. CannonPart

Mounting ................................ Tray,

No. DPX2MA-67S67S-33B-OO01

Honeywell P?rt No. 4011646

SP-200AutopilotComputerLeading Particulars

Table 7-1

22-14-00Page 198.29

Mar 15/89Useordisclosureofinformationon thm page is sublect to the restrictions on the title pag? of this document.

Honeywell F&WRANcECITATION V

7. B. FZ-500FlightDirectorComputer(SeeFigures7-2 and7-3,andTable7-2.)

The Flight Director processesinformationaboutactualaircraftattitudeversusdesiredaircraftattitudeas a functionof selectedflightmodetoproducepitchandrollsteeringcommandoutputsto the EADI. It alsoprovides flight director pitch and roll mode steering information to theautopilot computer whennotinthego-aroundmode.

@

FZ-500Flight Director ComputerFigure 7-2

22-14-00Page 198.30Mar 15/89

UseordisclosureofInformationonthispageksub)ecltotherestnc~lonsonthetitlepageofthis[~ocument.

Honeywell WWEFANCECITATION V


Length(excludinghandle)......................... 12.65in. (321.3mm)Width.............................................. 2.79in. (70.9mm)Height............................................. 7.62in. (193.5mm)

Weight(approximate)..................................... 71b(3.18 kg)

Power Requirements .................. 115 V, 400 I-tz,14 VA; 28 V dc, 15W

Mating Connector:

J1 ......................... CannonPartNo.DPX2MA-106~-106P-33B-0068

Mounting................................ Tray,HoneywellPartNo.4011646

FZ-500FlightDirectorComputerLeadingParticulars

Table7-2

22-14-00Paqe198-31/198.32

Mar 15/89Use or disclosure of reformation on this page is subject to the restrictions on the title pa~.e of thm document.

Honeywell W!URANCECITATIONV

JIAassr-+”flINS nwAv .:70 -- A

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AL TITUOE LABELEO CONDITIONS REPRESENT SWITCtS IN CL@EO WSITIm,FUNCTION

~ ~.2 RESISTOR SVMUELS INOICATE SIGNAL GAIW

GENERATORROLL AXIS

FZ-500F1ightDirectorComputerBlockDiagram

Figure7-3 (Sheet1 of 4) 22-14-00Page198.33/198.34

Mar 15/89Use or dkcbSure of informa~km on this page is subpcf 10 the restrictionson the title page of this document,

Honeywell UNlkPANcECITATIONV

A

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FZ-500FlightDirectorComputerBlockDiaaram

~d%#EFlbOp’’c”Ax’s ‘*3A”””1 I

~ TAS INTERNAL TO PITCH AXIS EM 4)

Figure7-3 (~heet2) 22-14-00Page198.35/198.36

Mar 15/89USe or dwclosure of lnfOrmatlOn on this pegeissubj@10 the restnctmnsOnthe Mle pageof Ihls documersl.

Honeywell INW’”c’CITATIONV

All 4LCR1Ct)nlnotlcn&L1 Pnfst LtcTtnnom

ALT f14nOnVWAV

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Figure 7-3 (Sheet 3)

-@l

22-14-00Page198.37/198.38

Mar 15/89Useordlscfosureofinformationonthis page IS subject fo fhe restrictionson the title page of Ihls document

Honeywell &!Af~f{ANcE

J

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22-14-00Page198.39/198.40

)-

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1=—

Mar 15/89Use or disclosure of Informetlon on this page IS subject 10 the restrictions on the title page of this document

Honeywell !%W?ANCECITATION V


22-14-00Page 198.41Mar 15/89

Use or dmclosure of mformaijon on this page is sub!eci to the restnc!~ons on the title pag ? of this document.

Honeywell MMWANC’CITATION V

7. c. MS-205 ModeSelector (See Figures 7-4 and 7-5, and Table 7-3.)

The Mode Selector provides pushbutton lateral and vertical modeselection,andmodeannunciationforthe IntegratedFlightControlsystem.The FD OFF switch, whenpressed,appliesa groundto theFDCcausingtheremovalof FD commandson the EADI. The DIMcontrolprovidesdimmingfor the ModeSelectorannunciators.

o FDOFF HDG oNAV8APR BC o...... .. - ... .........

~McAp.KJ7 ,1..., -:.”b’.:.”.:. .m

, -..

Qx ‘i- ‘-”-””- ‘ ‘“ ‘“““...........

‘ )

c)~

DIM ALT ALTSEL VN4V VS IAS——-,—..- .. ........ -.-_- ;.-—..:- --..:..:==-...

::.’:!-.~?:.“~“.’.l.:.-...,

‘=:-:‘--”=--:’”“; ~-----~‘: (b

MS-205ModeSelectorFigure7-4


Length(frombackof mountingplate) ......... 4.50Width................................11:1......... 5.17Height............................................. 2.01

Weight(maximum)......................................... 3

PowerRequirements

Primary ..............................................Lighting...............................................

MatingConnector:

J1 .....................................................

n. (114.3mm)n. (131.4mm)in. (51.1mm)

O lb (1.4kg)

28 V dc,20 W5Vacordc

MS3126F20-41S

Mounting.......................................................... Screws

Use or dwclosure of

MS-205ModeSelectorLeadinaParticulars

T~ble7-322-14-00

Page198.~2Mar 15/89

on this page IS subject to the restrictions on the title page of this cl,]cument.

Honeywell !MUYAN’ECITATIONV

+15VDC

POWER LJNO

O-28 V MODE ANIWN

MOOE SELECT GNO

HOG SELECT

---- ---- ---- -1

I

I

NAV SELEC 1

APR SELECT

B C SELECT

AL1 SEL SELECT

VNAV SEL

ALT SELECT

VS SELEC1

IAS SfLECT

DIM CONTROLExCITATION

OIM CObTROL S&NAL

o-w PANEL LIGNTING

LIGHTING GND

CHASSIS G~

-1

I

I ~Nc––––––– &-,tb

I c1 s‘1 I) NOL

I l--- —---I f==+II

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<1cl Sll

1 NOiL3

!l—— ——— —--

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II

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l=’

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I I-——— ——-— -———- —— -- —— -- NOTES

UNLESSOTHERWISESPECIFIED:1 ALLCAPACITANCEVALUESAREINMICROFARAOS.

rP~~L–,~&c~T~M~~ 2. ALLRESISTANCEVALUESAREINOHMS.

‘1 iT06;

OLK I I

67 1 I

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MS-205ModeSelectorFigure7-5

I~o:l_______j

Schematic

F D SELECT OFF

HOG GNO

NAv CAIJ LND

NAV ARM GND

APR CAP GNQ

APII ARM GNO

BC CAP GNO

B C ARM GNO

ALT SEL CAP GNl)

ALT SEL ARM (,NO

VNAV CAP GNO

VNAV ARM GNO

ALT 6N0

VS GNO

lA5 GND

AD18429

22-14-00Page198.43/198.44

Mar 15/89Use or disclosure of mformatlon on this page IS subject to the restncttons on the ttle page of thm document.

Honepe[[ WURANCECITATION V


22-14-00Page 198.45Mar 15/89

Use or disclosure of information on this page is sub)ecf to the restrictions on the title paqe of thw document.

Honeywell !t%M@ANcECITATIONV

7. D. PC-500AutopilotController(SeeFigures7-6 and7-7,andTable7-4.)

Qn ESCEND

P

+

E

T~

cH

M

CLIMBQ+

L -1

AO-2368-R1

PC-500AutopilotControllerFigure7-6


Length............................................ 4.81in. (122.2 mm)Width ............................................. 5.75 in. (146.1 mm)Height ............................................. 2.63 in. ~66.7 mm)

Weight(maximum)..................,..................... 2.0lb (0.91 kg)

PowerRequirements:

Pushbuttons................................................. 28 V dcLighting............................................... 5Vacordc

MatingConnector:

J1 .................................● ................... MS3126F18-32S

Mounting........................................... UnitScrewFasteners

PC-500AutopilotControllerLeadingParticulars

Table7-4

22-14-00Page198.46Mar 15/89Useor dsclosure of Information on this page is subject to the restrictions on the title page of this document.

Honeywell M?JE!ANCECITATIONn/V

The autopiyaw damperknob

7. D. (1)

(2)

(3)

(4)

(5)

(6)

(7)

(8)

andP

ot controllerprovidesthemeansof engagingtheautopilotandas wellas manuallycontrollingthe autopilotthroughtheTURNTCHwheel. Thefollowingparagraphsdescribeeachcontrol.

AP ENGAGESwitch- The ENGAGEswitchis usedto engagetheautopilot.Engagingthe autopilotautomaticallyengagestheyawdamper. Theautopilotmay be engagedwiththeairplanein anyreasonableattitude.The autopilotwillautomaticallycoupleto anymodesselectedon themodeselector,uponengagement.

YD ENGAGESwitch- Whentheautopilotis notengaged,theyawdampermay be utilizedby theYD engagemode.

BANKLIMITSwitch- Whenin theHDGmode,thisswitchis usedtodecreasetheflightdirectorrollcommandbanklimitto 12 degrees.

SOFTRIDESwitch- TheSOFTRIDEON switchreducesautopilotgainswhile still maintaining stability in rough air. Thismode may beused with any flight director modeselected.

ElevatorTRIMIndicator- TheelevatorTRIMindicatorshowsout-of-trimconditionby displayingUP or DNwhena susta$nedsignalisbeingappliedto theelevatorservo.

TESTEACHFLTButton- The TEST EACH FLT button provides a test forthe torque limit monitors. Also, on the Citation V theaccelerometer and roll rate monitors are tested. After engaging theautopilot, pressing the TEST button will cause the autopilot todisengage by simulating a failure in the monitors. THIS TEST SHOULDBE PERFORMEDPRIORTO EACHFLIGHT.

PITCHWheel - Rotation of the PITCH wheel results in a change ofpitch attitude proportional to the rotation of the wheel and in thedirectionof wheelmovement.Movementof thewheel,withtheautopilotengaged,willcanceltheALTholdmode.

TURNKnob- Rotationof theTURNknoboutof detentresultsin arollcommand.Therollangleis proportionalto andin thedirectionof theTURNknobrotation.TheTURNknobmustbe indetent(centerposition)beforetheautopilotcanbe engaged.Rotationof theTURNknobcancelsanylateralmodeselected.

22-14-00Paqe198,47/198.48

Miy 25/90Use or disclosure of reformation on this page K subject to the restnct!ons on the title pag,, of thm document.

Ho

ne

ywe

lltii!!!~

~~’”c

’CITATIONV

z.

T.-

—--—

----

------

-——

—— --—

---—

——

——

———

-——T

———2

—t-—

L

.E Gx.i!

----.

I

tI

.I

T

---

PC-500AutopilotController

BlockDiagram

Figure7-7

22-14-00Page198.49/198.

50

Mar15/89

Useordisclosure

ofInlormallon

on

thm

pag

eis

sub

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22-14-00Page 198.51

Mar 15/89Useordisclosure Of Informationon this page IS sublect to the restrictions on the title page of this document.

Honeywell Ml!!f?’”c’CITATION V

7. E. AG-222Accelerometer(SeeFigure7-8and7-9,andTable7-5.)

The Accelerometer is a closed loop, forcebalanceddevicewitha linearoutputproportionalto aircraftverticalacceleration.It hasself-containedelectronicsand incorporatesself-testcapabilities.

m 440

AG-222AccelerometerFigure7-8

ilimensions (maximum):

Length ............................................. 2.25 in.(57.2mm)Width .............................................. 1.03 in.(26.2mm)Height.............................................. 2.39in, (60.7mm)

Weight(maximum)........................................ 5.0oz (127gm)

PowerRequirements:

Excitation............................., (+)and (-)15 V dc, 1.0W

MatingConnector:

J1 ................................................ BendixJT06RE8-35S

Mounting..................................................... HardMount

AG-222AccelerometerLeadingParticularsTable7-5

22-14-00Page198.52Mar 15/89

Use or disclosure Of Information on this page is subject to the restnct!ons on the title page of thts document.

Honeywell MNHANCECITATION V

II SEISMIC

\

I MASS

PICKOFF AMPL

I

II

L.

T\-—————A—— ——

-- —-—

“1//TORQUE// MOTOR

.—

6K RLOAD

L

1

6

2

3

5

4—J

+13V

TESl-

SIGNALOUT

SIGANDPWRGND

-13V

SPARE

31729-R2

AG-222 Accelerometer Block DiagramFigure 7-9

22-14-00Page198.53Mar 15/89

Use or dmclosure of Information on this page m sub)ect to the restrictions on the tllle pace of Ihm document.

17. F.

Honeywell WE!ANCECITATIONn/V

RZ-220RollRateMonitor- CitationV Only(SeeFigures7-10and7-11,Table7-6.)

Therollratemonitorreceives3-wiresynchrorollattitudefromtheVG-14AVerticalGyro. Itmonitorsthisrollattitudesignalforabsoluterollanglesof greaterthan40°0 androllratesin excessof 20°0/see.Whenevertheseparametersareexceeded,a relayintherollratemonitordeenergizes,whichcausestheautopilotto disengage.

RZ-220RollRateMonitorFigure7-10


Length.● ...● ...,...● ...● ...● .............,......● 5.62in.(142.75mm)Width..● ...● ..................................... 3.93in.(99.82mm)Height.● ...........● .............................. 2.65in.(67.31mm)

Weight(maximum).● ...● ................................. 1.2lb (0.54kg)

PowerRequirements........................... 115V ac,400Hz,2 VA max

MatingConnector.............● ............................. MS3126F14-19S

Mounting.............● .................................... SolidMounting

RZ-220RollRateMonitorLeadincjParticulars

T~ble7-6 22-14-00Page198.54flay25/90

Useordisclosureof information on this page is subject to the restrictions on the t!tle page of this document.

Honeywell WW!’”c’CITATIONV

+J: >_____ -15 VDC

c

U >— SIGNAL GND

TEST ,. ~’;”

ROLLATTITUDEZ, N>50K11

1

If

+ v >— Tp,v 1/

)( )

WJ”4) , -K>

X+E>( b

TDEMOD

I

AND ~

t- q

L>

LVC20%EC 225 mS

~ %M>+ THRESHOLD TIME

DETECTOR DELAY

LVC IN>

28VRELAY ENERGIZED

K 1 ENGAGE A/P115 mS30° TIME

THRESHOLD

TEST DETECTORDELAY

Y

OR GATE FUNCTIONSAS ‘AND’ GATE DURINGTEST

! 405° 155 mSVOLTAGE TIME

z~G> *

TCosd DETECTOR DELAY

l--hI~ )

+15 VDC INPUTFOR SELF TEST - B >

M ATEST (339SEC ROLL RATE)

+

+C>—+15VDC

*

P-JLINE

vOLTAGE LVC

COMPEN.SATION

fr

P ~ CHASSIS GND

-jR>— TP,

~ S >— TPz

1=+ vDCPOWERSUPPLY

- vDC

=-J---l*

RZ-220RollRateMonitorBlockDiaqramFigure7~11

AIRCRAFTAIPINTERLOCKS

TO

AD 182S1

22-14-00Page198.55/198.56

Mar 15/89Use or disclosure of information on this page is sublect to the restrictions on the title page of this document.

Hone~el[ WUHANCECITATION V

Thispageis intentionallyleft blank.

22-14-00Page 198.57

Mar 15/89Useordisclosureofinformationon thw page IS subject 10 the restrictions on fhe title page of this document.

Honeywell lWiiE!ANcECITATION V

7. G. SM-200ServoDriveandSB-201Bracket.(SeeFigures7-12and7-13,andTables7-7 and7-8.)

TheServoDrivetranslateselectricalinputsintoa clutchedrotationalmechanicaloutput.Thisassembly,witha splineoutputon theclutch,mateswiththedrumandbracketassembly.Tachometerrateand Synchro

position signals arefedbackto theautopilotcomputerservoamplifier.Thedrumandbracketunitis boltedto theaircraftstructureandconnectedin parallelto theaircraftprimarycontrolriggingthrough.-cables.

m 221s

SM-200 ServoDrive and SB-201 BracketFigure7-12

22-14-00Page198.58Mar 15/89Use or dmclosure of mtormatlon on this page is sub@ct to the restrictions on the title page of this document

Honeywell IWLWANCECITATION V


Length ........................................... 8.825 in. (224.3mm)Width............................................ 5.065in.(128.8mm)Height ............................................ 3.97 in. (100.8 mm)

Weight(maximum)....................................... 56 lb (2.55kg)

PowerRequirements:

Clutch.................................................. ..... 28 V dcMotor Stall ............................................. 28 V dc, 56 WSynchro ............................................ 26 ~~,400 Hz, 1 VA

Stall Torque ........................................... Upto1601b-in.

Mating Connector:

J1 ................................................... P-K)6E-14-19S(SR)

Mounting .................................................. .. Hard Mount

SM-200ServoDriveandSB-201BracketLeadingParticulars

Table7-7

Power Synchro Clutch ClutchDashNo. GearRatio GearRatio Hi Pin Hi Pin

-906 38.9:1 151.1:1 F J-914 18.6:1 151.1:1 G H

SM-200ServoDriveDashNo.Differences

Table7-8

22-14-00Page198.59/198.60

Mar 15/89Use or disclosure of mformatlon on this page IS subJect to the restrictions on the title pa$e of this document.

Honeywell INKY’””CITATION V

r ——— ——— ——— ..—, SERVO ORIVE ASSEMBLY POWER LOOP 1.

II

F*CLUTCHEXCITATION

I

(CONTROLLED BYAUTO PILOT IENGAGE ANO/OR

TOUCH CONTROL

STEERINGI

SHIELD GNO

CLUTCH

VOLTAGE

x

d

I

[G<;-ORN ~

, CR1-VOLTAGE

2 I

11 IBLK BLK

‘~

I

{J ;::

+BLKTACH RATE L

FEEOBACK OUTPUT II

(POLARITY SHOWN

FOR CCW OUTPUTII I

TOORUMANO _WHTi IN

BRACKETI WI

MOTOR INPUT FROMSERVOAMPL

(POLARITY SHOWNFOR CCW OUTPUT TOORUMANDBRACKET)

‘4--I

I

J-J-

.

.I

l--

I

I TO

~+. -.AIRCRAFT

[0CONTROL

CABLES

~~ IPOWER

GEAR

TRAIN

I I

<> I

II I5

I

CHASSISGND C

% +

r.—— ——— ——— -t—

5ERv0DRlvE A55EM13Ly FEE06AcKL00P

I I SYNCHROSYNCHROTERMINALS

GEAR TRAIN

p IX BLU B@

[;!

BLUE

SERVO(SYNCHRO 61) Y WHT/VIO 9 BLKPOSITION FEEDBACK ROUTPUT

! H=q

Cx

2 YEL 10 YELLowE:1

{::

‘1 H WHT/RED 11 REo,wHTD

26 V400 Hz c WHT/BLK ‘2 BLK/WHT

E. H

I 1- ——— ——— ._ —.—

SPARES

““ fJ-

1NOTES

‘+

1

iJ-

SPARES 0

.V +J--

2$

3

$

INDICATES MECHANICALSIGNAL FLOW

INDICATES ELECTRICALINPUTS

IN OICATES ELECTRICALOUTPUTS

SM-200ServoDriveBlockDiagramFigure7-13

AD.202

22-14-00Page198.61Mar 15/89Useordisclosureofinformationonthispage!ssub}ecttothe restrictions on the title pag ! of this document.

Honeywell WJE”ANCECITATION V

8. PRIMUS@ 650 Weather Radar System

A. WU-650 Antenna and Receiver/Transmitter Unit (See Figures 8-1 and 8-2,and Table 8-l.)

TheWU-650Antenna and Receiver/Transmitter Unit generates andreceivesX-bandradiofrequencyenergy forthepurposesof weatherdet~ctionandgroundmapping.The9345i30MHztransmittedsignalsaresentdirectlyto theantennafromtransmittercircuitrymountedon therearof theantenna.Echo signals received by the antenna are applied directly to thereceiver which is also mounted directly to the antenna. The IF,video,and processing system processes these signals by encoding them into oneof four levels depending on their intensity, scan converts th~m, andoutputs the scan converted data to the various display systems.

84-88-14

WU-650Antenna and Receiver/Transmitter UnitFigure 8-1

22-14-00Pacle198.62~ar 15/89

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Honeywell tii~;?’””CITATION V


Base Diameter ................................. 10.00 in. (254.0mm)Height(Antennaflat).......................... 9.00in.(228.6mm)Height(Antennafullac) ...................... 13.20in. (335.3mm)

Weight............................................... 13.cllb(5.90kg)

Prime Power ......................... +22 to +32 V dc, 90 watts, maximum

Antenna

Size....................................... 12-inch flat plate radiatorStabilization ............................... Line-of-sight., t30 degreesTilt ....................................................... t15 degreesScan .................................. Fu1l - 120 degrees (t60 degrees)

Sector - 60 degrees (t30 degrees)

Transmitter

Frequency................................................. 9345t30MHzpower ....................................... 1.3kW, nominal, magnetronPulse Widths ................... 1.2, 1.5, 2.4, 4.8, 9, 18, and 27 usec,

determined by selected rangePRF ......................................... 120, 240, 360, and480 Hz,

determined by selected range

Receiver

Noise Figure ........................................... 8.5dB, typicalIF Frequency.................................................... 35 MHzIF Bandwidth.......................................... 0.[1MHz,nominalVideoBandwidth................. CommensuratewithselectedpulsewidthSTC ............................................... Presen”tin allmodesMDS ................................. 112.4 dBm nominal, on 300 NM range

DisplayedRanqes

WXGMAP .......................... 5, 10, 25, 50, 100, 200, and 300, NMfull scale with fiveconcentricrangerings(cyanforWX,greenfor GMAP)

Flight Plan ............. 5, 10, 25, 50, 100, 200, 300, 500, and 1000 NMfull scale with fiveconcentricrangerings

MatingConnector......................................... MS3126F20-41S

WU-650AntennaandReceiver/TransmitterLeadingParticulars

Table8-1

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MOOULATOR

1

t

IF PREAMPL IF AMPL DETECTEH AMPL

w

L.O.

+,I

=hwGNETRON

-L-EJ--

t

‘T..s’g;’rON/OFF .—l I II$)‘z

MOTORORIVE

1

AzMOTOR

I1

VIDEO

PROCESSOR

8

ELMOTORORIVE

1

ELMOTOR

—

r OIGITIZEO VIOEO

EllNO/MFO

LT EFISPICTURE

BUS

RT EFIS

-IXLPR’MAR4

—

3’”~— LT EFI’

-–i=’’”~—

‘clCONTROLBus

AD.6s7A.a3

WU-650AntennaandReceiver/TransmitterUnit Block DiagramFigure 8-2

22-14-00Page 198.65

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Honeywell !WWANC’CITATION V

8. B. WI-650WeatherRadarIndicator(SeeFigures8-3 and8-4,and“rabies8-2and8-3.)

..-. —. .-. -=.-...-=.-.==,Il(mcwt’wll

f=, A-ria.m--- ..--—.. -. , ,. ..——

. ..

#b...

-. .

#.--~

. ..._l(.I-.~

II

,---7 . ._

, .&-. .

. . ..

x.

t—— .. . .

.L.

‘F, .i.1 ,m.. Ii

.

—,. . J ,- ,. -,:~---..,- --- =!! ;

AW122QS-R3

WI-650WeatherRadarIndicatorFigure8-3


Length (from rear of bezel) .................... 11.49 in. (2!]l.85mm)Width.......................................... 6.27in. (159.13mm)Height.......................................... 4.83in. (122.68mm)

Weight(maximum)....................................... 12.Olb (5.45kg)

PowerRequirements:

Primary............................... +27.5V dc,36 watts.,maximumLighting............................ 28Vdc, at O.20A, nominal,or

5 V ac/dc,0.75A. nominal

MatingConnectors:

J101 ................................................. MS3126F22-21SJ102 ................................................. MS3126F14-19S

Mounting........................... Tray,HoneywellPartNo. 701.1359-901

WI-650WeatherRadarIndicatorLeadingParticulars

Table8-2

22-=14-00Page198.66Mar 15/89

Use or disclosure of Intormatlon on this page is subject to the restrictions on the tllle page of this document.

Honeywell WKPANcECITATION V

The indicator provides all control functions fortheweatherradarsystemanddisplaysscanconverteddata,processedby theWU-650on a 5-inchdiagonalcolorCRT. Colors provided are red, green,blue.yellow,cyan,magenta,white,andblack. Thefunctionof eachcontrolon the indicatoris listedinTable8-3.

BRT

TILT

GAIN

Mode

OFF

SBY

ON

FP

TST

TGT

Single-turndisplaybrightnesscontrolthatadjustsbrightnessof display.CW rotationincreasesdisplaybrightnessandCCWrotationdecreasesbrightness.

Single-turnrotarycontrolwhichvarie:iantennatiltbetween15degreesup and 15 degreesdown. The rangebetween +5 degrees and -5 degrees is expanded for easeof setability. When pulled, stabilization inputs aredisabled and pitch and roll are assumed to be zero.

Single-turn rotary control which varie:; the RTA receivergain. Control is active when pulled, andwhen pushed,receiver gain is preset and calibrated Selection ofRCToverrides the variable gain setting causing receivergainto be fixedandcalibrated.CW positionproducespresetgain.

Five-positionrotarycontrolwhichselectsprimaryradarmodes.

Removespowerfromsystem.

Standby.Placessystemin nonoperationalmode.

Placessystemintheoperationalmode:jelectedby WX orGMPpushbuttons.

Flight Plan. Permits the singular display ofnavigational data provided through the UDI port.

Activates the system self-test mode.

Momentary alternate-action pushbutton which enablestheTargetAlertfunction.RTAbecomesoperationalif FP modeis selectedandTargetAler:enabled.

Indicator Control FunctionsTable 8-3

22-14-00Page198.67Mar 15/89

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Honeywell MI!!!NANC’CITATION V

RTC

GMP

Wx

RANGE

AZ

SCT

Momentary alternate-action pushbutton which enables therain echo attenuation compensation technique function.

Momentary pushbutton which selects the ground mappingdisplay mode.

Momentary pushbutton which selects the weather displaymode.

Two-pushbuttonrangeselectionsystemwhichpermitsrangeselectionfrom5 to 300 NM full scale ‘n the ONMode or 5 to 1000 NM full scale in the Flighl. Plan Mode.The “uparrow”pushbuttonselectsincreasingrangeswhile the “downarrow”pushbuttonselectsdecreasingranges.Thelastrangeis rememberedwhen switchingbetween ON and FP.

Upon reaching maximum or minimum range, further pressingof the pushbutton causes the range to rollover tominimum or maximum range, respectively. If f’SBY iswired to a weight-on-wheels switch, the unit will be inForced Standby on the ground unless both RANGEpushbuttons are pressed simultaneously.

Momentary alternate-action pushbutton which permitsdisplaying and removing azimuth marks from the display.

Alternate-action pushbutton which selects either fullazimuth scan angle (120 degrees)or sectorazimuthscanangle(60degrees).

IndicatorControlFunctionsTable8-3 (cent)

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Honeywell WK5!’”c’CITATIONV

REF

VERTREF

HORIZ TIMING VERTGENERATOR SWEEP

VIDEORED

\

JDISELECT P

UDICIRCUITS

STBY +

2FORCED STBY /

/ 1

CONTROLBUS

ENCODER/DECODER

*

II ALPHA- 1 ~vlDEO 1

NUMERIC l)ECODER/GENERATOR PRIORTIZER

FRONTON/OFF+ PANEL

CONTROLS

WI-650WeatherRadarIndicatorBlockDiagramFigure8-4 22-14-00

HORIZSWEEP

3LANK vCOLORVIDEOAMPI.

NTC

P:&RSUPPLY

AO-6873-R2

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Honeywell l!fi~u%NANcECITATIONn/V

This page intentionally left blank.

22-14-00Page198.70.1

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Honeywell WWmcECITATIONn/V

8. C. OptionalWC-650WeatherRadarController(SeeFigures8-5and8-6,andTables8-4 and8-5.)

AD-15s72

WC-650WeatherRadarControl1erFigure8-5


Length (from rear of bezel) ...................... 7.0 in.(277.8mm)Width ........................................... 5.75 in. (146.1mm)Height ........................................... 1.87 in. (47.5 mm)

Weight ................................................. 12.0 lb (5.45kg)

PowerRequirements:

Primary......................... +22to +32V dc, 5.8watts,maximumLighting.......................... 28 V dc at 6.0watts,nominal,or

5 V ac/dcat 4.6watts,nominal

MatingConnectors:...................................... MS27473E14B-18SwithstrainreliefMS27506-B14-2

Mounting........................................... UnitScrewFasteners

WC-650WeatherRadarControllerLeadingParticulars

Table8-4

22-14-00Page198.70~2

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Honeywell Wllk”ANcECITATIONn/V

TheWC-650Controllersetsthemodes,range,andantennatiltusedtodisplayradarinformationon theEHSI. The controller also contains theLightningthe LSS.

The funct8-5.

SensorSystem(LSS)switchwhich

on of eachcontrolon theWC-650

is used

Control”

to con-trolthemodesof

er is listedin Table

Control Function

TILT

LSS

OFF

SBY

LX

CLR/TST -

SLV

Single-turnrotarycontrolwhichvarie:;antennatiltbetween15degrees up and15degreesdown. Therangebetween+5 degreesand -5degreesisexpandedforeaseof setability.

Four-positionrotaryswitchwhichselectstheLightningSensorSystemmodes.

AllpowerremovedfromLightningSensorSystem.

Displayof datafromthe LightningSensorSystemisinhibited,but it is accumulatingdata.

LightningSensorSystemif fullyoperationalanddisplayingon the Indicator.

Accumulateddatais clearedfrommemoryof theLightningSensorSystem.After3 seconds,thetestmodeisinitiatedin theLightningSensorSystem.

An annunciatorcenteredon theloweredgeof thepanel.Thisannunciatoris usedin a dualcontrollerinstallationandlightswheneverthiscontrolleris intheOFFmodeandtheoppositesidecontrolleris in anymodeexceptOFF.

WC-650ControlFunctionsTable8-5

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Honeywell WURANCECITATIONn/V

Control Function

RADAR

OFF

STBY

Wx

GMAP

FP

TEST

GAIN

Range

RCT

STAB

Six position rotary switchmodes.

Removespower from system.

Standby. Places system in

which selects primary radar

nonoperational mode.

Selectsthe

Selectsthe

Selectsthemode.

Selectsthe

Sinqleturn

weatherdisplaymode.

groundmapmode.

system flight plan (navigation) display

system self test mode.

rotary control which varies the RTA receivergai~. Receiver g~in is calibrated in the PRESETposition. CCW provides minimum receiver gain.Selection of REACT overrides the gain contro~ setting,causing the receiver gain to be fixed and ca~ibrated.

A two-pushbutton range selection system which permitsrange selection from 50 to 300 NM full scale in the ONmode or 5 to 1000 NM full scale in the Flight Plan mode.The “uparrow”selectsincreasingrangeswhile the “downarrow”selectsdecreasingranges.

REACT- Momentaryalternatingactionpushbuttonwhichenablesthebluebackgroundfieldto indicaterangesatwhichthereceivercalibrationhasbeenexceeded.Compensationis activeat alltimesunlessthe REACTCompensationOverridepinon theRTAconnectorisgrounded,inwhichcasethecompensationis enabledcoincidentallywiththebluefielddisplay.The REACToffconditionis annunciatedabovetheswitch.

Momentaryalternateactionpushbuttonwhichpermitsdisablingstabilizationinputs.Whendisabled,the“OFF”conditionis annunciatedabovethe switch, andpitch and rollinputsareassumedto be zero,

WC-650ControlFunctionsTable8-5 (cent)

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Honeywell MM?’””CITATIONn/V

Control Function

TGT - Momentaryalternatingactionpushbuttonwhichselectstargetalertfunction.

SECT - Sector.Momentary alternating action pushbutton switchwhich selects either full azimuth scan (120 degrees) orsector scan (60 degrees).

WC-650Control FunctionsTable 8-5 (cent)

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Honeywell tiil!il~r’”c’CITATION Ilfl

OEI

SECTTGT

‘z~ ‘g”: ‘-TM-

96 KHZ

t BINPROGRAM CTRCOUNTERS A3U6

A3U9ANDA3U1O -t-

+4A3U3 --06.144MHZ

OscA3U7,A3Y1

STAB 1 ,3 BUFFERRCT > / A3U13 TBO - TB6

iii TGAINWIPER — A2U1A

OPAMP

~“ P

~A?N TBO- T’SA3U20

CONrROL LABEL 192 KHZ

PROM PROMA3U15 A3U12

v

UART LINEINTERNAL BUS

A3U6— DRIVER

A3U2

SclTO RTA

ADCTILT

A3U19“LTW’PER+* Q

OE1

DECODER OE2

MUX OE310FB 0E4A3U21 OE5

0E6 l==%R

OE3

JlSBY

a ~

PROM IMAP (MODE) TBO-TBQFP A2U7 1

‘STU A rB2 - TB6

OE3~BUFFERA3U22

UP 7ON

A3U26OCTAL PROM

(RNG)A3U26 A3U29

FP +

a+cwf~:Rt-+5v

I PULSE k +15VDCRNG

b 4

POWER SUPPLY

LEGl

- “T L JPANEL LAMP NOTE:

CIRUIT REFERENCE DESIGNATIONS ARE AS FOLLOWS:Al = LC)W VOLTAGE powER SUPPLY CCA

JQ . LOGIC 1 CCA

~ . LOGIC 2 CCA

WC-650WeatherRadarControl1erBlockDiagramFigure8-6

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Honeywell KAWJ$PANCECITATION V


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Honeywell MWJEP’NCECITATION V

9. Or)tionalFMZ-800FliqhtManagementSystem(FMS)

A. NZ-61ONavigationComputer(SeeFigures9-1and9-2,andTabl~?9-l.)

AD-11941

NZ-61ONavigationComputerFigure9-1

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Honeywell KI!!!EPANCECITATION V


Length .......................................... 17.03 ir. (432.6mm)Width............................................ 4.91ir.(124.7mm)Height........................................... 7.62ir.(193.5mm)

Weight (approximate) ................................... 14.8 lb (6.71 kg)

PowerRequirements ...................................... 28 V dc, 65 W

Mating Connector:

J1 ........................... Cannon Part No. DPX2-67S-I06P-33B-O089

Mounting ..................................... Tray, Part No. 7003272-903

NZ-61ONavigationComputerLeadingParticulars

Table9-1

The NZ-61ONavigationComputerprovidesbothlateralandverticalnavigationguidance.The navigationcomputerhasa l12kbyteinternalnavigationdatabasethatis usedforstorageof waypoints,navaids,routes,airports,andotherNAVdataforeasyaccessby thepilot. The navigatior~ computer caninterface with three long term sensors via ARINC 429 busesandtheASCB.Eachnavigationcomputercanalsoconnectto dualDME receiversanda singleVOR receiver. The interfaceto theSG-605(EFIS),andMG-605(MFD),is overtheASCBandthelinkto the CDU is over an RS-422 ‘private-line’ interface.With links to the on-board navigation sensors, the navigatic~n computerdevelops an FMSposition based on a blend or mixof the sensors.The FMSdoesnotdirectlydisplaynavigationmapson the CDU; howev~r,theFMS is thesource of map data forothercockpitdisplayssuch as EFIS. Display of mapdata is achieved by the utilization of the internal data base and ASCB1/0.Thenavigationdatabaseis subjectto updatingon a 28 day interval.TheDL-800 data loader is used for this purpose.

The navigation functions of the system include accurate computations ofaircraft position and groundspeed. Navaid selection and tuning of the VORand DME receivers can also be accomplished through the FMS. Aircraftposition is computed using data received from the radios (VORand/or DMEand/or Omega). The navigation computer calculates groundspPed using radioinputs.

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Honeywell WKFANCECITATION V

Thenavigationcomputerselectsfrequenciesfor tuning the VORanca directedscanDMEor twosinglechannelDME’s. However, the NAV radios car be tunedby either the navigation computer supplied frequencies or a frequencytransmitted by the VHF NAVcontrol head. When in autotune,theVCIR/DMEislisteningto thenavigationcomputerfor selection of the VORfrequencyandas manyas threeDMEfrequencies.In themanualposition,theVOF./DMEislisteningto theVHF NAV control head which can select a VORand/cr DMEstation for display on the EHSI.

The aircraft position is computed as a function of logicswitchescallednavigationupdatemodes. The fourpositionupdatemodesareradic/inertial,radioonly, inertial onlyanddeadreckoning.Thenavigationmod~hierarchyis a functionof sensoranddataavailability.

Theradio/inertialpositionis computedby usingradioposition.Theradiopositionis thencombinedwiththecalculatedinertialvelocityfcrcomputingradio/inertialr)osition.If validrho/thetaor omeqadatais beirq receivedon the ground,~ radiopositionwillbe computed.-

Theradioonlymodeis activewhenthereisno validinertia”radiodatais beingreceived.

TheDeadReckoningmodeisactivatedwhenthefollowingcond

● There is a valid mag heading input.

. A radio position cannot be computed.

dataandvalid

tionsaretrue:

. A valid true airspeed is available from the air data computer.

A dead reckoning position is calculated from the last known aircraft positionusing the track and distance traveled along that track. Heading, ADC trueairspeed, and the last known wind areusedto estimateaircraftgroundspeedandtrack. Thedeadreckoningpositionupdatemodeis annunciatedon theCDU . The annunciator is automatically cleared whenthe positionupdatemodetransitionsoutof deadreckoning.

22-14-00Page198.74Mar 15/89

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GMTCLOCK

CouINTERFACE

DATALOADER

DATA ❑ASEE2 PROM

PROGRAMEPROM

RAM

Honeywell WNR’”c’CITATION V

1 I

ARINC

429— XMIT

RS422

RCVRS

RS422XMIT

DISCRETES P

OISCRETES

NZ-61ONavigationComputerBlockDiagramFigure9-2

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Honeywell MINJEPANCECITATION V

9. B. CD-800ControlDisplayUnit(SeeFigures9-3 and9-4,andTab”e9-2.)

PHOTO PHOTOSENSOR ANNUNCIATORS SENSOR

/ / I

CRTDISPLAY~

LEFTLINESELECT\KEYS

SCRATCHPA~

MODE KEYS —

ALPHA-NUMERICKEYS

-1El 34a o 4.ONM

KSLC 09IfZ~ ,,(4ARM ALTN {HEl

4560

ARRIVALD ~

11II

/— —.m

).

,,,, ,Jpq

RIGHTLINE

~SELECTKEYS

FUNCTION‘KEYS

MODE KEYS

=-BRIGHTNESSCONTROL

AD-11942-RI

CD-800 Control Display UnitFigure 9-3

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Honeywell WIMP’””CITATION V


Length .......................................... 7.50in. (190.5 mm)Width ............................................ 5.75 in. (146.1mm)Height........................................... 6.75in. (171.5mm)

Weight............................................... 9.4 lb (4.27 kg)

PowerRequirements:

Primary ............................................. 28 Vdc, 40 WLighting ..................................................... 5Vac

MatingConnector:

J1 ................................................... PS3126F22-55SX

Mounting .......................................... Unit Screw Fasteners

CD-800ControlDisplayUnitLeadingParticulars

Table9-2

TheCD-800ControlDisplayUnit(CDU) is the pilot interface with theFMS. TheCRTdisplays relative flight information to the pilot. Thepilotenters alphanumeric data into the system via the full alphanumerickeyboard. This data appears inthescratchpadto be lineselectedto theappropriatepositionon theCRTdisplay. The CDUfunction controls aredescribed in thefollowingparagraphs:

9. B. (1) CRTDisplay - A monochrome CRT is usedto displaydataon theCDU.The displays consist of 9 lines, each line containing 24 characters.The first line is a title line and the ninth line is the scratchpad.The intermediate lines and scratchpad are available fordatadisplayandentry.

(2) PhotoSensorsandBrightnessControl- CRTbrightnesscontrolisprovidedin orderto maintainreadabilityunderdim lightas wellasdirectsunlight.This is accomplished in two ways:

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Honeywell WMR’AN’ECITATION V

9. B. (2) (a) Manuallyby thebrightnessknob- The brightnessknobisprovidedto manuallyvarythe intensityof the CRT display fora given ambient light level.

(b) Automatically by the photo sensors - The photosensors sensethe ambient light and adjust the CRT brightness automaticallyto maintain the relative brightness set by the brigiltness knob.

(3) Annunciators - Thesixannunciatorslocatedat thetopo-ftheCDUkeyboardpaneloperateindependentlyfromtheCRT and keyboard.Lighting of the annunciators is initiated by the Navigation Computervia the RS422 serial data link. The twocolorsusedforannunciations are white and amber. White indicates an advisory typeannunciation, and amber indicates an alerting type annunciation.The followingparagraphsdescribeeachannunciator:

(a) Display(DSPLY)Annunciator- TheDSPLYannunciatoris anadvisorytype(white)thatlightswhentheCDU isdisplayingapagethatis notrelativeto theverticalflightpath. The DSPLYthe followingconditions:

. Whendisplayinga flightplan

current aircraft l;~teralOFannunciatorwilllightunder

page other than Page 1.

. Whendisplayinga storedflightplanpage.

● Whendisplayingthe ‘CHANGEACTIVELEG’ message.

. When defining the ‘Intercept’ waypoint on the ac”:ive leg.

(b) Dead Reckoning (DR)Annunciator - The DR annunciator is analerting type (amber) that lights whenthe FMSis ni~vigatingviatheDR modewhichis definedto be the lossof radioupdatingandthelossof allpositionsensors.TheDRannunciatorwilllightunderthe followingconditions:

. When the FMShas beenoperatingin theDR modeforlongerthan3 minutes.

. WhentheAPRCHannunciatoris illuminatedandpositionupdatingfromallsourcesis lostformore than 30 secondsand the radio is not procedure tuned.

. When the APRCH annunciator is illuminated and positionupdating from all sources is lost formore than 5 secondsandtheradiois proceduretuned.

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Honeywell MFJEPANCECITATION V

9. B. (3) (c)

(d)

(e)

(f)

I)egraded (DGRAD) Annunciator - The DGRAD annunciator is anadvisory type (white) that lights whentheFMShasenteredadegradednavigationmode. Thedefinitionof degradediswhenthe FMScannot guarantee the required accurac:f forthepresentsegmentof flight.TheDGRADannunciatorwilllightunderthefollowingconditions:

. Whentheaircraftiswithintheterminalarea,50.8NM,andtherequiredaccuracycannotbe guaranteedwiththeavailablepositionsensors.

● Whenthe aircraftiswithintheapproacharea,10 NM,andtherequiredaccuracycannotbe guaranteedwiththeavailablepositionsensors.

IftheDEGRADannunciatoris on whentheDR annunciatoristurnedon,theDEGRADannunciatorwillbe turnedoff.

Message(MSG)Annunciator- TheMSG annunciatoris an advisorytype(white)thatlightswhentheFMSis disp”!ayinga messagein thescratchpadto theflightcrew. Theannunciatorshallextinguishafterthemessage(s)havebeencleared from thescratchpad.

OFFSET Annunciator - TheOFFSETannunciatoris an advisorytype(white)thatlightswhen a laterally offset path has beenentered into the FMSusing the progress page. Theannunciatorturnsoff whentheoffsethas been removed. If there is anoffset when the APRCH annunciator is lighted, the offset willbe removed and the annunciator turned off.

Approach(APRCH)Annunciator- TheAPRCHannunciatoris anadvisorytype(white)thatlightswhenin approachmode. TheNAVComputeroutputsensitivityof lateraldeviationto theEHSIwillbe rampedto a highersensitivitywhentheannunciatoris lighted.The APRCH annunciato~’ willlightunderthefollowingconditions:

. Ifthedestinationelevationis specified,distancetodestinationis lessthan15 NM,altitudeis lessthan2500feetabovethedestinationelevation,and:he speedislessthan200 knots.

c If the destination elevation is not specified, distance todestination is less than 15 NM, and speed is less than 200knots.

. IftheAPRCHannunciatoris illuminatedandtheaircraftfliesoutof theaboveconditions,theAPRCHannunciatorwillbe extinguishedandthesensitivityrt~mpedto normal.

. When the pilot selects APP on the modeselector.

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Honeywell WNFANcECITATION V

9. B. (4) LineSelectKeys- Therearefourlineselectkeyson eachsideoftheCRT display. Forreference,thekeysaredefinedonethroughfourfromtopto bottomon eithersideof theCRT. A leftandrightis alsoassignedto definethe sideof theCRTon whichthekeyislocated.Forexample,lineselectkey ‘IL’is thetopleftlineselectkey.

In thecaseof an indexdisplay,thelineselectkeyscanbe usedtoselectsub-modeswithinthemajormodes. In displays otoer thanindex, the lineselectkeys4L and4R arePrimarilyused fordirectaccessto othermodesin~he FMS. Datacanbe cop~edto thescratchpadthroughtheuseof a lineselectkey,andonesdatahasbeenenteredintothescratchpad,eithervialineselec:manualkeyboardentry,itmay be selectedto anyof thelineselectfieldson a givenpage. Thiscanbe accomp”by depressingthe keyadjacentto thelineinwhichyouscratchpaddatato be inserted.

ion orallowableished simp”ywishthe

(5) FunctionKeys- Therearefourfunctionkeys,andthefunctionofeachisdescribedin thefollowingparagraphs:

(a) Previous(PREV)andNEXTPageKeys- Thenumberof pagesin aparticularmodeor menudisplayare shownintheupperrighthandcornerof thedisplay.The formatis ‘AA/BB.’‘AA’sicinifies the number of the current page that is displayed.‘BE’signifies the total number of pag;s that are available forpilotviewing/modification.Pagechangesshallbe donebyselectingthe PREVandNEXTkeys. Whenin thePLANmode,thesekeyswillincrementor decrementthemapcenterwaypoint.

(b) Clear(CLR)Key - TheCLR keyperformsthefollowingfunctions:

. Whena messageis presentin the scratchpad,pre:isingtheCLR keyshalldeletethatmessage.

. Whenan alpha-numericentryresidesin thescratchpad,onecharactershallbe clearedfromthescratchpad(fromrightto left)foreachtimethebuttonis pressed.

. Whenan alpha-numericentryresidesin thescratchpadandtheCLR keyis helddown,thefirstcharacteris clearedwithin100msec. After400msechaveelapsed,characterswillbe clearedat 100msecintervalsforas longas thekeyis helddown.

(c) Delete(DEL)Key - Whenthereis no messagein the $cratchpadandtheDELkeyis pressed,a “*DELETE*”willappearin thescratchpad.Thismaynowbe lineselectedto deletewaypointsandotheritemsdisplayedon theCDU. Whenthereis a messagedisplayed,thedeleteoperationwillbe inhibited.

22.14-00Paae198.80

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Honeywell YA!YRANCECITATION V

9. B. (6) Mode Keys - There are fivemode keys, and the funczion of each isdescribed in the following paragraphs:

(a) Performance (PERF) ModeKey- Pressingthe PERFmode key shallenable the pilot to access the performance page(s). Thepilotmay selector entertheapplicableinformationthroughtheuseof thelineselectkeys.

(b) Navigation (NAV) Mode Key - Pressing the NAVr~odekeyshallenablethepilotto accesstheNAV indexpage The pilot mayselect any of the sub-modesby pressingthelineselectkey.

(c) FlightPlan(FPL)ModeKey- Pressingthe FPLmodekeyshalldisplaythefirstpageof theflightplan. 1= thereis noflightplancurrentlyentered,thepilotmaymanuallyenteraflightplan, selecta storedflightplan,or createa storedflightplan.

(d) Progress(PROG)ModeKey- Pressingthe PROGmodekeyshalldisplaythefirstpageof theprogresspages. The purposeofthismode is to show the current status of the flight. Thisfirst progress page shall display the ‘to’ waypoint, thedestination, the navaids that are currently tuned for radioupdating, and the update status of each navigation computer.

(e) DirectTo/Intercept(DIR)ModeKey- PressingtheDIRmodekeyshalldisplaythe activeflightplanwiththeDIRECTandINTERCEPTprompts.

(7) AlphanumericKeys- TheControlDisplayUnitprovidesa fullalphanumerickeyboardto enablepilotinputsto thescratchpadofthe CDU. A keyis providedforeachletterof thealphabetaswellas eachnumber,decimal,minussignandslash.

(8) Scratchpad- The scratchpadprovidesa workingareaforthepilottoenterdataand/orverifythedatabeforelineselectingit to thedesiredposition.The scratchpadalsoprovidesadvisoryandalertingmessagesto be displayedto thepilot. Datashallberetainedin thescratchpadthroughoutallmodeandpagechanges.

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NAVCOMPUTER

PERFORMANCE

COMPUTER

5VLIGHTING J< ‘: + KEYBOAROLIGHTINGCOMMON 0< I - LIGHTING

CLEAR

. .I I

{ El‘ (H)

MOATABUS OUT

N(c)

RS422

{

(H) OUTDATATERMINAL pREAOYBUSOUT ~ (c)

OATABUSIN(

TO SEND BUS IN

{

CLK BUS IN(

(H)

[c)

~ , (H)

:a

RS422(c) INPUT

(H)

(c)

I

~ I(H)

OATA BUS IN( d

K

(c)

(

(H)●

CLEAR TO SENO BUS INRS422

f(c) INPUT

(

9(H)

CLK BUS INh

(c)

{

Y

=1-(H)

MTA BUS OUTz

(c)

RS422

{

(H) OUT

WTA TERMINAL aREAOY BUS OUT ~ (c)

I

I

+’I )

L 1

I 1

R f’~OTO SENSOR OUT

L PHOTO SENSOR OUT

I 1

G1 FOCUS

VIDEORAM A

&

*

-VIDEO

CRT VIDEO AMPLIFIER

CONTROLLER CONTROLLER

HEATER

VIDEORAM B

I 1x

SYNC1

DDEFLECTIONAMPLIFIERS Y

CDU VALID

I v 1

BRIGHTIDIMDISCRETE VANNUNCIATOR- * KEYBOARD

‘1

_]

ORIVERS ANNUNCIATORS

I

INPUT KEYSOARO

BUFFER OECOOE A

TEST ENABLE EEi

9

I

{:!

B(H)

*

28 VDC POWERc

(L) LVPS

LAMPTEST S<

{:;

(H)F -

2bV ANN POWER (L) ANNUNCIATORH - POWER/

.1 OIM CONTROL

ANN INTENSITY CONTROL‘~

CHASSISGND G

%

CD-800ControlDisplay610ck DiagramFigure 9-4

AOI 1970

Unit

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Honeywell tii~if~’”c’CITATION V


22-14-00Page 198.85

Mar 15/89UseordisclosureofinformationonthispageIS subjectto the restrictions on the title pag ? of this document.

Honeywell M!!WANCECITATION V

9. c. DL-800DataLoader(SeeFigures9-5 and9-6,andTable9-3.)

AD-1 2269R1

DL-800DataLoaderFigure9-5


Length ......................................... 7.87 in.Width.......................................... 13.75in.Height......................................... 14.49in.

Weight (maximum) ....................................... 14.1

PowerRequirements:

Primary .......................................... 28 VLighting.......................................... 5V

(199.90(349.25(368.05

lb (6.4

dc.dc

5W5W

mm)mm)mm)

kg)

maxmax

MatingConnector:

J1 .................................................... MS3126f’16-26$

DL-800 DataLoaderLeadingParticulars

Table9-3

22-14-00Page198.86Mar 15/89

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Honeywell W!Wi!ANcECITATION V

TheDL-800DataLoaderis used-totransfernavigationrelateddatato theNZ-61ONAV computer. TheDL-800hasthecapacityto transferin excessof320kbytesstoredon a 3-1/2inchmini-diskette.It hasan RS-422interfacewiththe NAV computer.

9. c. (1) Navigation Data Base Loading - TheDL-800DataLoaderprovidestransferof dataderivedfromtheJeppesendataba~efroma 3-1/2inchfloppydiskto theNZ-61ONAV Computer local IIEPROMmemory.This data includes navaids, waypoints, airports, airport runways,airport procedures, and jet routes organized in regionalpartitionsof theentireJeppesendatasource. Thedatabaseis updatedevery28 days. Thedatatransferrateis 312kbaud. Thetotaltimerequiredto loada fulldatabaseis approximately3 minutes.

(2) F1ightPlanLoading- TheDL-800DataLoaderalsohasthecapabilityof interfacingwitha groundbasedLockheedJet Plancomputerorequivalent.It is capableof transferringan optimizedflightplanfromthegroundbasedcomputerto thenavigationcomputerviaa3-1/2 inch floppy disk. Foreachflightplan,th~~followingdatawillbe stored:lateralwaypoints,origin,destin(ition,windsandtemperaturesat eachwaypoint.

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Honeywell MWPANC’CITATION V

{:~

DATA 3US IN GJ1 (Cl

● CENTRAL PROCESSING UNIT (CPU)FROM NAV

COMPUTER H(H) –Zao CPU

—8K B~ES RAM

{[i

CLKBUSIN J(c) —32 K BYTES EPROM

FROM NAV —RS422 INTERFACE

COMPUTER K(H)

—RS232 TEST INTERFACE

I

I

I

I r 7

(c) J1 S

‘c}

DATA BUS OUT(H)

TTO NAV COMPUTER

{ =3(L)

28VCICPOWER B(H) ●

c

LOADER

{

(R)INSTALLED DDISCRETEFROM E (L)rJAvCOMPUTER

POWER SUPPLY CARD

–-5 VDC

—z12 VDC ~

—DISCRETES FOR CPU

J

EEl-El- 4S11%S

DL-800DataLoaderBlockDiagramFigure9-6

22-14-00Page198.89

Mar 15/89Useordisclosure01ln~ormallonon this page IS subject to the restrictions on the htle paqe of this document.

Honeywell MNRAN’ECITATION V

9. D. OZ-800ReceiverProcessorUnit(SeeFigures9-7and9-8,andTable9-4.)

AD-1.5616

OZ-800ReceiverProcessorUnitFigure9-7

22-14-00Page198.90Mar 15/89UseordisclosureofintormatlononthispageISsubjecttotheresIrictlonsOnthetitlepageofthis~ocument.

Honeywell WWF’””CITATION V


Length ......................................... 14.58n. (370.33 mm)Width ........................................... 2.25 in. (57.15mm)Height ......................................... 7.60 :n. (193.04 mm)

Weight (maximum) ....................................... 65 lb (2.95kg)

PowerRequirements.................................... 28 V dc,40 W max

Frequency ............................................. 10.2 to 13.6 kHz

Mating Connector ..................... Cannon Part No. DPX13MA-57-335-0001

Mounting ................................................. ........ Tray

OZ-800ReceiverProcessorUnitLeadingParticulars

Table9-4

TheOZ-800ReceiverProcessorUnit(RPU)receivesandprocessesdatafromthegroundbasedOMEGA/VLFstationsto providelatitude,longitude,N-Svelocity,E-Wvelocity,andstationinformationto theflightmanagementsystem.The antennareceivestheOMEGA/VLFsignalsandconvertsthemforprocessing by the RPU. All signals from or to the RPU are transmitted overan ARINC 429 data bus. The RPUalsosuppliestheantennawitht12voltsdcpower.

22-14-00Page198.91Mar 15/89

Use or disclosure of information on this page IS subject to Ihe restrictions on the title pag ? of thw document.

[ 7MASTER OSC

t 1 I

OMEGAIVLF ANALOG flIVLFANTENNA *

INPUT RCVRDIGITAL

1LRCVR

SELECT~ ‘RocEssoR-––w––

GNDfOPENDISCRETE

DISCRETE

INPUTS INTERFACE

HDG,TAS SYNCHROINPUTS ~ INTERFACE

DIGITALINPUTIOUTPUT

44

13PUDC

28 VDCPOWER *VOLTAGES REQUIRED

/SUPPLY ~ =12VDC

TO ACUAO-1 5927

OZ-800ReceiverProcessorUnitBlockDiagramFigure 9-8 22-14-00

Page198.92Mar 15/89

Use or disclosureofInformationonthispageissubjecttotherestrictionsontheotlepageofthisd)cument.

Honeywell

9. E. AT-801H-FieldBrickAntenna(See


Figure9-9andTable!1-5.)

The AT-801 Antenna receives the OMEGA/VLFsignalsandconvertsthemforprocessingby theOZ-800RPU. Theantennaalsoincorporatesbuilt-intestcircuitryto monitoritsownoperation.

AT-801H-FieldBrickAntennaFigure9-9


Length......................................... 6.50in.(165.10mm)Width.......................................... 5.65in.(143.51mm)Height.......................................... 1.75in.(44.45mm)

Weight ............................................... 2.2lb (1.00kg)

MatingConnector...................................... M8:3723-86R-14-15N

Mounting .................................................... Hardmountusingsixnonmagnetic

hexheadscrews,10-32x 1.00

AT-801H-FieldBrick AntennaLeading Particulars

Table 9-5

22-14-00Page198.93

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Honeywell MNRANC’CITATION V

10. Optional 5RZ-850 Integrated Radio System

A. RNZ-850IntegratedNavigationUnit(SeeFigures10-1and 10-2, and Tablelo-l.)

AD-I 3743-R1

RNZ-850IntegratedNavigationUnitFigure10-1


Length ....................................... 14.01in. (355.9mm)Width ......................................... 8.90in. (226.1 mm)Height ........................................ 3.36 in. (85.3 mm)

Weight .............................................. 13.6 lb (6.16kg)

Power Requirements .......................... 28Vdc, 69VA (nominal),26 V, 400 Hz, 18.3VA (maximum)

Mounting ................................... Tray,PartNo. 7510124-9OX(includes mating connectors)

RNZ-850IntegratedNavigationUnitLeadingParticulars

Table10-1

22-14-00Page 198.94

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Honeywell tiiWJEPANcECITATION V

The RNZ-850IntegratedNavigationUnitis a completeself-containednavigationsystem. ItcontainstheNV-850VHF NAV Receiver module, theDF-850 Automatic Direction Finder (ADF) module and a stix-channelscanning DM-850 Distance Measurement Equipment (DME) module. Alsowithinthenavigationunitis a clustermodulewhichcontainsthecircuitrynecessaryto handleallof thedigitaloutputsof thenavigationunitmodulesandplacethemon thedigitalaudioandradiosystem buses. Another function of the cluster module ;s an MLSInterface.Theclustermodulehascircuitryanddriversto feedtheinformationcomingfromthe RSB to the ML-850 MLS Receiver in the samemanner as it feeds information to one of the internal modules.ThismakestheexternalMLS,in effect,a moduleof the NAV unit; however, itis housed separately so it may be used forindependentapplicationswherea fullNAV unit is not needed.

Eachoneof themoduleshas itsownindividualtemperature sensor,andanymodulecancallforcoolingairby notifyingthec-lustermodule,whichcontrolsthecoolingfanlocatedon themountingrackat therearof theunit. When the temperature within the unit has droppedadequately to satisfy the conditions, the cluster module willdeactivatethe fan. The fanoperationismonitoredfullyby theclustermoduleandis testedeachtimepoweris appliedto theunitas we-nas beingverifiedthatit is runningduringthenecessaryoperatingperiods.

10. A. (1) NV-850VHFNAV Receiver

TheNAVreceivercontainstheVOR/Localizer,GlideSlope,andMarkerBeaconReceivers.

TheVORportionof theNAVreceiveris usedto in+:ercepta VORradialintheradiofrequencyrangeof 108.00to 117.95MHz onchannelsspaced50 kHzapart. The VOR receiver provides radiodeviation, To-From, bearing, and flag outputs to zhe EFIS SymbolGenerator for display on the EHSI and to the FZ-500 Flight DirectorComputer forautomaticcaptureandtrackingof the selectedVORradial.

TheNAVreceiveralsocontainsthe ILScomponentswhicharethelocalizer,glideslope,andmarkerbeaconreceivers.

Thelocalizerreceiveris usedforprocessingrawlocalizerdataforuse in liningup theaircrafton thecenterlineof therunway.Thelocalizerfrequencyrangeis 108.10to 111.95MHzon channelsspaced50 kHzapart. The localizerdeviationoutputisdisplayedon the EADIandEHSIandis appliedto the FZ-500FlightDirectorComputerforuse in automaticcaptureandtrackingof thelocalizerbeam.

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Honeywell H!JR’”c’CITATION V

The glide slope receiver is used for processing glide slope datafor use in guiding the aircraft down to the runway in a lineardescent. The glide slope frequency range is 329.15 to 335.00 MHzon channels spaced 150 kHz apart. The glide slope deviation outputis displayed on the EADI and EHSI and is applied to the FZ-500Flight Director Computer for use in automatic capture and trackingof the glide slope beam. The 75 MHz marker beacon receiver detectsthe three tones of the marker beacons and provides audio and lampdrive outputs to annunciate on the EADI the outer marker (blue),middle marker (amber), and inner marker (white).

The navigation receiver has extensive built-in test circuitry.This BITE operation includes a self-test signal generator andmodulator built into the unit. When energized by flight crew orpower-up command, the injected signal is identical to a VOR/ILSsignal and starts the testing at the earliest possible stages ofthe various receivers, just after the antenna. BITE commands anextensive check of the various circuitry within the NAV receiverand will cause the various outputs to move in a very specified andregular sequence, allowing the pilot to confirm that the entirenavigation receiver is operating properly. Additionally, there areother maintenance monitor and signal monitors associated with theNAV module which continuously check for proper operation and validsignals within the unit. These circuits continuously watch overthe operation of the unit and, should any operating parameter moveoutside of its nominal range, this condition will be stored innonvolatile memory for subsequent maintenance readout.

The NV-850 also has its own self-contained power supply which isfed from a dedicated pin on the main connector of the unit allowingfor independent application of aircraft supply voltages to the NAVreceiver.

10. A. (2) DM-850 DME

The DM-850 Distance Measuring Module is a six-channel scanning DMEthat simultaneously tracks four selected DME channels for distance,ground speed, and time to station as well as tracking twoadditional channels for the IDENT functions. This gives the systemthe capability of tracking four channels and having the decodedidentifier readily available from two additional channels. Theunit dedicates two of its four channels to a Flight ManagementSystem when installed. Thus with an FMS, the flight crew has tworemaining channels to control and display IDENT, distance, time tostation, and ground speed. The IDENT only channels will havedecoded IDENT ready, so when the crew selects the preset VORchannel, the instant search capability of its DME will allow thefunctionality of 4 full-time channels for the crew.

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Use or disclosure of InformalIon on this page IS subject to the restrictions on the title page of this t:ocument.

Honeywell W%P’”c’CITATIONn/V

The ranging capability of the DME is up to 300miles,groundspeedcapabilityup to 1000knots,andtime-to-stationcapabilityup to999minutes.ThesesignalsaresentfromtheDME in severalformats,oneof whichis thenormalradiosystem+ormatappearingon thedigitalbusviatheclustermodule,anothe]-is an RS-422format.Alsoprovidedis an ARINC-568standardoutputof sixwireson whichdata,syncandclockareprovidedto outputthedistance.In additionto thedigitaloutputs,a 40 millivoltspernauticalmileanalogoutputandaudiocapableof drivingtwo600-ohmaudioloadswiththe IDENTsignalis alsoprovided.Selftestingisaccomplishedviaa builtin signalgeneratorwhichis pulsedtoprovidea completeendto enddistanceverificationcheckof theDMEunit.

10. A. (3) DF-850AutomaticDirectionFinder

TheDF-850ADF receiverandcompanionAT-860ADF mtenna comprisetheAutomaticDirectionFinderSystem.Usedtogether,thesetwounitsprovidetheADFfunctioncapabilitycontainedintheintegratedNAVunit. TheDF-850functionsoverthefrequencyrangeof 100kHzto 1799.5kHzin additionto operatingon emergencyrangeof 2181to 2183kHz. Allof thesefrequencyrangesareavailablewith0.5kHzincrements.

TheDF-850ADFdrivesconventionalanalogsynchrosandRMIsandhasstrapoptionsavailableto selectDC SIN/COSor AC synchrodrives.In additionto itscapabilityof drivingvariouspointers,theADFhasdigitaloutputswhicharesentto theRSBviatheclustermodule. TheADF alsohasan RS-422serialdataoutput.

As wellas sendingitsanaloginformationto theclustermoduleforapplicationto thedigitalaudiosystem,theADFalsohasan outputto drivestandardaudiointerfaces.

ForselftesttheADF hasa builtin oscillatorcircuitrylocatedin theantennawhich,whenenergized,couplesdirectlyintotheantennacircuitryandprovidesa completetestof theentireADFsystem.

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Honeyell lIKNJEPANcECITATION V

RADIOSYSTEM~Bus

DIGITALAUDIO ~BUS

CLUSTERMODULE—

:B

.

IiTERFAcE

—

DIGITALAUDIO

NTERFACE

KPOWERSUPPLY

—128 VDC VORILOC

INPUT POWER28 vDC DMEINPUT POWER28 VDC ADF zINPUT POWER

28 VDC M’SINPUT POWER-

DME MODULE

- RCOINTERFACE RFANC

.___>

ARINC568

SIGNAL RS422POWER PROCESSINGSUPPLY

ANALOG

ADF MODULE

RCBRFAND

~ k

ANALOG- INTERFACE

SIGNALPOWER ProcessingSUPPLY

RS-422

—}~ AUX AUDIO

INPUT

—1

+’ ~~:~,‘R;,-~ANALoGOPTIONALSEPARATE MLS UNIT

4

SIGNAL

~&a vy:rAR’Nc 42’

IAO-142S9.R3

RNZ-850IntegratedNavigationUnitBlock DiagramFiqure 10-2

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10. B. RCZ-850Integrated CommunicationTable 10-2.)


Unit (See Figures 10-3 and ,.0-4,and

AD-13744-R1

RCZ-850IntegratedCommunicationUnitFigure 10-3


Length ........................................ 14.1 in. (353.6mm)Width ......................................... 6.86in. (174.4mm)Height ......................................

Weight ..........................................

PowerRequirements ............ 28 V dc, 36.5 VA28 V dc, 227VA ~

. 3.32in. ‘(84.3mm)

. . . 11.5lb (5.22kg)

(nominal receive mode)nominaltransmitmode)

Mounting................................... Tray,PartNo.75108I4-9OX(includesmatingconnector)

RCZ-850IntegratedCommunicationUnitLeadingParticulars

Table 10-2

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Honeywell !W!K!ANCECITATION V

The RCZ-850IntegratedCommunicationUnitcontainstheTR-850VHFCommunicationTransceivermoduleandtheXS-850ModeS Transpondermodule. Also within the RCZ-850 is a cluster module that providestheinterfacebetweentheTR-850andXS-850andotherunitsof theintegratedradiosystem.Coolingis providedthesameas theRNZ-805IntegratedNavigationUnit.

10. B. (1) TR-850VHFCommunicationTransceiver

The TR-850 VHF COM Transceiver module provides air-to-ground andair-to-air voice and data communications in theradiofrequencyrangeof 118.00to 136.975MHz (or from 118.00 to 151.975 MHz inextendedfrequencyrange)on channelsspaced25 k’dzapartandutilizesamplitudemodulation.

Thesynthesizerportionof theCOM is similarin functionto otherfrequencysynthesizersin thatchannelsareselectedviatheRSBandclustermodule.The synthesizergeneratesthe internalRFsignalsnecessaryforchannelingof theCOMunit. Oneof theoptionalfeaturesof theCOM is thatwhenit receivesa channelchange,itwillputouta toneindicatingthatthe frequencyhaschangedintheCOMreceiverif thefunctionhasbeenselectedbythestrapoptions.

The audio circuitry of the COM provides a noise squelchandacarrierlevelsquelch,allowingit to operatein lconjunctionwithmulti-carriernetworks.Also, it has outputs forSELCAL,theselectivecallingsysteminwhichan individualaircraftmay beaddressedviatonesacrossa COMchannel.The audio circuitry hasan output of 100 milliwatts into a 600 ohmloadwhich is theconventional standard. It also has an isolated sidetoneoutputsothatthereceiverandtransmitteraudiooutputsmay be routed, asappropriate, to existing analog type audio systems. Thetransmitter sidetoneis derivedby actuallydetectingtheCOMtransmitter output. This provides a full checkof themodulatorandtransmitterportionsof theCOM.

TheCOMtransmitteralsohasa timeoutfeaturewhichcausestheunitto automaticallyreturnto thereceivemodeaftertwominutesof continuoustransmitting.Thisfeatureis intendedto protecttheuserandothersusingthesamefrequencyfromdisruptionofcommunicationscausedby blockingthefrequency.

Built into the COM is a self-test oscillator which,whenenergized,willcausea signalto appearin thereceiverandwillverifyitsoperation.

Otherfeaturesof theCOM includethestandardRadioSystemnonvolatilemaintenancelogand internalmonitoringto verifycircuitryperformanceandto recordanydeviationfromnominaloperationforlaterrecallby maintenancepersonnel.

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Honeywell MI!MNANC’CITATION V

The COM transmitter poweroutputis a nominal20 watts,aguaranteedminimumof 16watts,andis applicableacrosstheentirefrequencyrangeof 118.000to 151.975MHz. The receiversensitivityof theCOM is a nominal2.5 (hard)microvolt.

10. B. (2) XS-850ModeS Transponder

TheXS-850ModeS transpondermoduleworks with the Air TrafficControl Radar Beacon System (ATCRBS) to provide enhancedsurveillance and communication capability required for airtrafficcontrolautomation.TheModeS Transpondermoduleuses1030MHztoreceiveinterrogationsand 1090MHzto transmitreplies.It isfullyfunctionalwithATCRBSModesA andC andcapableof providingBasicModeS operation.ModeS allowsdigitaladdressingofindividualaircraftandthecommunicationof messagesbackandforthbetweentheairandthegroundand is a fundamentalportionof the FAAproposedTCAScollisionavoidancesystem.

Whenthetranspondersensesa changein the replycodecommandedbythecontrolhead,itwillholdthecurrentreplycodeuntilthenewcodehasremainedconstantforapproximately3 seconds.Thenitwillbeginto usethenewlyselectedreplycode. This is doneinan effortto avoidtransmittingfalsealarmsandfalseemergencysignalswhentheemergencycodesareinadvertentlyused during theprocess of tuning.

As with all the other radio units, the transponder has its ownbuilt-in self-test circuitry and its own maintenance log andmaintenance monitoring circuitry. The self-testcircuitryiscomposedof oscillatorsandpulsegeneratingcircuitrywhichwillinjectsimulatedinterrogationsintothetransponderreceivercircuitryverycloseto theantennasystemandwillcompletelycheckthetranspondercode,processing,andallof theRF circuitryby actuallysimulatinga knownsignalcomingfromtheground.

22-14-00Paae198.102‘Mar15/89

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RAOK3

SYSTEMBUS

Honeywell !WMFANCECITATION V

DIGITAL

+

DIGITAL.AUDIO AUOIOBus INTERFACE

POWERSUPPLY

COMMOOULE..—

1

I I

IJ

MODES MODULE

@ RC8INTERFACE RFANO

SIGNAL L ALTIMETERPOWER FROCESS:tdGSUPPLY

}

~ EXT DIGITAL.—~ INTERFACES

.

,NPUTPOWER=28 VOCCOM

RCZ-850IntegratedCommunicationUnitBlockDiagramFigure10-4

AO-14270-R3

22-14-00Page 198.103

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Honeywell I!AMNANC’CITATION V

10. c. ML-850MicrowaveLandingSystem(MLS)Receiver(SeeFigures10-5and10-6,andTable10-3.)

AD-l3745-Rz

ML-850 MLS ReceiverFigure10-5


Length ......................................... 14.01 in. (355.9mm)Width ........................................... 3.08in. (78.2mm)Height .......................................... 3.36in. (85.3mm)

Weight ................................................. 4.6lb (2.09kg)

Power Requirements ............................. 28 V dc, 15.5 ‘JAnominal

Mounting ..................................... Tray,PartNo.7510664-901(includesmating(connector)

ML-850MLS ReceiverLeading Particulars

Table 10-3

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Honeywell M!J?ANC’CITATION V

TheML-850MLSReceiverdecodes and processes data fronl an MLSgroundstationandprovidesan accurateindicationin bothazimuth(equivalentto localizer)andelevation(equivalentto glideslope)of thedeviationfromthedesiredflightpath. Thedeviationdatais displayedon theEADIandEHSIand isoutputto the FZ-500FlightDirectorComputerforuse intheapproachmodeof operation.

TheML-850operatesin thefrequencyrangeof 5031.0tc 5090.7MHz on200 channels spaced 3000 kHzapart. Selectionof thedesiredazimuthandelevationangleandtuningis accomplishedwiththeRM-850RMU. Inits operation, the ML-850 is fully integrated with the RNZ-850Integrated Navigation Unit and may be though of as simply another modulefor the RNZ-850.

TheML-850providesARINC429digitaloutputs(Table10-4)thatconformto thedatastandardsof ARINCcharacteristic727forNILSreceivers.Also provided is a digital DC MorseCodeoutputfor usc with a digitalaudio system.

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Honeywell MWJWANCECITATION V

Labelm

017033035036105130131132133134135136137140141142143151152153154155156157160161162163164165173174175176177256257270376377

Data Description

Runway HeadingILS/MLS FrequencyMLS/DME FrequencyMLS Channel NumberRunway HeadinqMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSMLSGenMLS

A~xiliary-DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary DataAuxiliary Data

Word1AWord 2AWord 3AWord 4AWord lBWord2BWord3BWord4BWordlCWord2CWord3CWord4C

Azimuth DeviationGlidepath DeviationSelected Azimuth AngleMaxSelectableGlidepathAngleSelectedGlidepathAngleBasic Data Word 1Basic Data Word 2Basic Data Word 3Basic Data Word 4Basic Data Word 5Basic Data Word6AbsoluteGlidepathAngleAbsoluteAzimuthAngleLocalizerDeviationGlideSlopeDeviationSelectedBackAzimuthAngleBackAzimuthAbsoluteAngleBackAzimuthDeviationGroundStationIdentification1GroundStationIdentification2DiscretesAV Equipment IdentificationSpecific Equipment Identification

ML-850MLS ReceiverARINC 429 Outputs

Table 10-4

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Honeywell M!!L?ANCECITATION V

MLS ANTENNAS

k“ CA..———— -.—— 1

,p + DPSK

4 +

I ,

ANTENNA

SWITCH

I

d TCXO - SYNTHESIZER

IRC8

II

BITETO

NAV UNIT

L ——— ——— . ——— ——

+5 +.28 +15 -15

+

r———— — ———. —— ——— ——

I

ANALOG/POWEll ANALOG

SUPPLY CARD DEVIATIONS

I

ANO

POWER

SUPPLY

FIAGS

I

ARINC 42S

1-OUTPUT

L ——— ——— ——— ——— ——— ——— --—— d.28 VDCINPUT

POWER AO-14?5?~2

ML-850MLS Receiver Block DiagramFigure 10-6

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Honeywell W?WAN’ECITATION V

10. D. RM-850RadioManagementUnit(RMU)(SeeFigures10-7and 10-&,andTable10-5.)

CURSOR\

TRANSFERKEY(LEFT~SIDE)

JLINE SELECTKEYS(LEHSIDE)

FUNCTION_KEYS

/ @\

.Honeywell

\~

WIT1(

-~ [’;:.20 ;0.25

‘iE3 131.27 109.35MEMORY-3 MEMORY-1

EATC ADF1

e

1471 162.510N+ALT ANT

IFdm>

Els

RM-850RadioManagementUnitFigure10-7

TRANSFEF/KEY (R[GHT

SIDE)

t

LINE SELECTKEYS (RIGI+TSIDE)

TUNING- KNOBS

AD-18084


Length ........................................ 11.10 in. (281.9mm)Width .......................................... 4.06 in. (103.1 mm)Height ........................................ 5.06in. (128.5mm)

Weight ................................................ 7.2 lb (3.27kg)

PowerRequirements .............................. 28 V dc, 33 VA nominal

Mating Connector ......................................... Ms3176F20-41S

Mounting .......................... Clamp, Honeywell Part No. 7[100066-11MSP PartNo.64557

RM-850RadioManagementUnitLeadingParticulars

Table10-5

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Honeywell WMR’”c’CITATION V

The RadioManagementUnit(RMU)isthecentralcontrolunitfortheentireradiosystem.Itprovidescompletecapabilityforcontrollingtheoperatingmode, frequencies, and codes within all ‘:heunits of theRadio System. Additionally, the RMU has the capability to switch itsoperation from its primary radio system to the cross-side system. TheRMU is a colorCRTbasedcontrollerfeaturingtheprovenconceptofselectinga functionby pushinga lineselectkeyadjacentto theparameterthatisto be changed.Any selectableparameter,suchas aVOR frequency,maybe changedby pressingthecorrespondinglinekeynextto thedisplayedparameterandthenrotatingthecontrollertuningknob.

Foreaseof operation,theRMUscreenis dividedintofivededicatedwindows. Eachwindowgroupsthedataassociatedwitha particularfunctionof theradiosystem.The five windows (COM,NAV,Transponder,ADF, and MLS)eachprovideforcompletecontrolof frequencyand/oroperatingmode of the associated function. The RMU also has otherdisplay modes,calledpages,whichperformadditional-Featuresandfunctionsforthecontrolof theradiosystem.

The RMUis alsotheinputto theradiosystemforexternalFMStuninginthatdigitalsignalsfromthe FMScomeintothe RMUwheretheyactinmuchthesamemanneras if thefronttuningknobwas beingoperated.ThisallowstheFMSto enterintothesystemin an organizedmanner,andwillappearto thesystemas iftheflight crew is tuning the receiver.

As a safetyfeature of the RMU, should any of the components of theradio system fail to respond to commands from the RMU, the frequenciesor operating commands associated with that particular Cunction will beremoved from the RMU and replaced with dashes. This willalertthecrewto thefactthattheradiosystemoperationis notnormal.

AlsoavailableintheRMUis a maintenancemodeof operation,whennotin flight.Duringthismode,variouspagesareutilizedto allowmaintenancepersonnelaccessto themaintenancelogdazaandoperatingconditionsof theradiosystem. Inthe aircraftmaintenancemode,parametersmay onlybe examinedandmay notbe modifiedin anyway bythe crew.

The followingparagraphsdescribeeachcontrolon theRMU:

10. D. (1) PhotoSensor- Thephotosensorsensesthe ambientlightandcausestheCRT brightnessto be automaticallyadjustedto compensateforvaryinglevelsof lightas theaircraftmaneuversin the sunlight.

(2) TransferKeys- Thetransferkeywhenpushed,flip-flopsthe activefrequency(TopLine)andthepresetfrequency(BottomLine)of theCOMor NAVwindow.

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Honeywell WMF’”c’CITATION V

10. D. (3) Line Select Keys- Thefirstpushof the lineselectkeymovestheyellow cursor to surround the data field associated with thatparticular line select key. This then electronically connects thatdata field to the tuning knobs so that frequency or modemay bechanged.Forsomefunctions,additionalpushesof the ~ineselectkeywilltogglemodesor recallstoredfrequencies.The lineselect key, if held forcertainfunctions,allowsADF andATCmemories to be recalled, and to enter and exit direct tune modefortheCOMandNAV.

(4) Tuning Knobs - The tuning knobs are used to modify the data fieldenclosedby thecursor. Thismay be frequencyor modedependinguponthedatafield.

(5) FunctionKeys

(a)

(b)

(c)

(d)

(e)

Squelch (SQ) Key - Pressing the SQ key causes the COM radio toopen its squelch and allowanynoiseor signalpresentin theradioto be heardin the audiosystem. The squelch key isstrictly a toggle. Pressing the key toggles SQ. ‘rhelettersSQ are annunciated along the top line of theCOMwindowwhenthesquelchis opened.

Dimming(DIM)Key - PressingtheDIM keyconnectstheRMUbrightnesscontrolto thetuningknoballowingthedisplaytobe adjustedto matchoverallcockpitbrightness.

Cross-Side(1/2)Key - PressingthiskeytransferstheentireRMUoperationanddisplayto thecross-sidesystem Thelegend color changes from white to magenta whenone systemisbeingcontrolledby theRMUassociatedwiththecross-sidesystem.

Store(STO)Key - PressingtheSTO keycausesa temporary(TEMP)COM/NAVpreselectfrequencyto be storedinmemoryandassigneda numberedlocation,providedthecursorhasfirstbeenplacedaroundthatfrequency.TheADFandATC each haveone memory location. Pressing the STO key causes the currentADF or ATCchannelto be storedin memory,providedthecursorhasfirstbeenplacedaroundthatfrequency.

Identification(ID)Key - Pressingthe ID keyplacesthetransponderin the identificationresponsemode. The IDsquawk terminates after 18 seconds.

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Honeywell WW’”c’CITATION V

10. D. (5) (f)

(9)

(h)

Page(PGE)Key - Pressingthe PGE key once willchange the RMUdisplay to the COM preset frequency memory page. Pressing ita secondtimewillmovethedisplayto theNAVpresetfrequenciespage. KeyingPGE a third time calls up thediscrete RADIOON-OFFpage,which is the last page of the RMUprogram. A fourth push of the PGEkeywill return the displayto the Main Page. All of thesebackpagesassigna “Return”functionto thelowerleftlineselectkey. Pressingthiskeywillbringbackthe “Front”page.

Test (TST) Key - Pressing the TST keycausesthecomponentassociatedwiththeyellowcursor’spresentpositiontoactivateitsinternalself-testcircuitsfora completeend-to-end test of the function. Hold the TST keydownforthedurationof thetest,about2 secondsforCOMtransceiver,5to 7 secondsforDME,ATC, ADF, and about 20 seconds forNAV(VOR/ILS).Releasing the TST key at any time immediatelyreturns the function to normal operation.

DME Key - TheDME keydeslavestheDME fromthe active VORfrequency, and allows tuning of a different DMEchannelwithout changing active VOR. Successivepressesof theDMEkeyenabledisplayandselectionof theDMEchannels in VHFandTACANformats.

(6) Cursor- Theyel1ow cursorenclosesthedatafieldselectedby theline select key. Theyellowcursorrevertsto theCOMwindow20secondsafterthelasttuningoperationon theRMU.

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Honeywell M;WJEPANCECITATION V

01.SPLAY

RADIO

~ ~ ‘- “

USE OISPLAY DISPLAYSYSTEM~ INTERFACE CONTROL ORIVERSBUS ~-a

n 1Rs-422

FlvlsRS-422

INTERFACEINPUT

+

FRONTCONTROL

PROCESSOR -BEZEL

CONTROLS

ATC IDENT J

COM FREO XFR +

COM MEM SELVOR MKR SENS~

S1OE SEL BIT~

TEST ENABLE %

wEIGHT-ON-WHEELS~WOW POLARITY~

SOFTWARECONFIGURATION

STRAPS (= \

,

28 VDCLOW HIGH

INPUTVOLTAGE - VOLTAGE

POWERPOWER POWERSUPPLY SUPPLY

{

ELECTRO- ELECTRO-DIMMING : U: LUMINESCENT LUMINESCENTINPUTS POWER ANO BACK

28 VDC 4 DIMMING LIGHTING

L

OISCRETEINPUTS

PDDISCRETE ~ POWER OFF

OUTPUTS CONTROLS

AO-1426W+2

RM-850RadioManagementUnitBlockDiagramFigure10-8

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Honeywell MKJE?ANCECITATION V


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10. E. AV-850AAudioControlUnit(SeeFigures10-9and 10-10,and““able10-6.)

I J k II

AV-850AAudioControlUnitFigure10-9


Length ......................................... 7.10in. (~.80.3mm)Width .......................................... 5.75in. (:,46.1mm)Height ........................................ 3.00in. (76.2mm)

Weight ............................................... 3.75lb (1.70kg)

Power Requirements .............................. 28Vdc, 28 VA nominal

MatingConnector:

J1 ................................................. MS27473E20-A41SJ2 ................................................ MS27473E20-A41SB

Mounting .............................. UnitDzusFastenersperMS-25213

AV-850AAudioControlUnitLeadingParticulars

Table10-6

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Honeywell WiKRANcECITATIONV

10. E.

TheAV-850AAudioControlUnit(AudioPanel)is usuall;yinstalledin adualsystemconfiguration,withsystemNo. 1 beingthepilot’sor leftside,andsystemNo.2 beingthecopilot’sor rightside. Communicationandnavigationinformationfortheflightcrewis receivedfromtheremoteunitsas digitizedaudioviatwo highspeeddigitalaudiobuses.The two high speeddigitalbusesconsistof Bus1 forthepilot’sdigitalaudioand Bus 2 for the copilot’s digital audio. Bus 1 input isderived from the COM1, NAV 1 andADF 1 radiofunctions,as applicableto systemoperation,andBus2 inputfor COM 2, NAV 2 and ADF 2 radiofunctions. Each Audio Panel then selects the appropriate channels fromthis digital audio busandreconstitutesheadphoneandspeakersignals.This allows the system to provide the capability to individually selectthe radio function the crew member desires to hear.

Having the audio digitized offers the advantage that when recovering theanalog information from the digital, each volumecontrolmay beindependentlysetby eachcrewmember. For instance, ‘thepilot maywishto haveCOM 1 veryloudandCOM2 very soft in his headset while thecopilot desires the VORto be loud,COM 1 to be softandCOM 2 to bemoderate.This is easily set at the audio panels simplyby adjustingthe volumes to their own-

Thefollowingparagraphsfunctions:

(1)

(2)

(3)

(4)

Micro~honeSwitches

desire.

describetheAudioPanelswitchandcontrol

- TheseswitcheswhenPressed automaticallyselectthe desired microphone and at the same time enable the ~udioassociated with that microphone, regardless of the setting of theCOM audio on/off controls that are located under the switch.

CABIN Switch - When the CABIN switch is pressed, a cabin speakeramplifier is enabled. Allotheraudios,exceptwarningaudios,aremutedduringcabinaddressoperation.

Emergency(EMER)Switch- Whenthe EMERswitchis pressed,themicrophoneis connecteddirectlyto a predeterminedVHFCOMtransceiver,andthetransceiversreceivedaudioisconnecteddirectly to”the aircrasimultaneously route ais selected, headphonevolumecontrol.All e“position.Thismodea“

AudioSourceControl-

t’sheadphone. Thesystemmay be wiredtosingleNAV audio to headphones. When EMERvolume is controlled by the master headphoneectroniccircuitryis eliminatedin the EMERsodisablesallotheraudiopanelmodes.

Eachcontrol(COM,NAV, ADF,DME,MLS)combinesthefunctionof switchandvolumecontrol.The controlenergizes a particular channel’s audio whenunlatched(outposition)andde-energizestheaudiowhenlatched(inposition).Rotationof thiscontrolwilladjusttheaudiolevelfromminimumat thefullyCCWpositionto maximumat thefullyCW position.

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Honeywell WWMCECITATIONn/V

10. E. (5) ID/VoiceSwitch- The ID/Voiceswitchis operatedby settingarotaryswitchand is used to filter the VORandADFaudiosignals.In the IDmode(CCWposition),theVOR orADF audio is filtered insucha way as to enhancetheMorseCodeidentification.IntheVOICEmode(CWposition),theaudiois filteredto reducetheMorseCodesignalforreceivedADF andVOR/ILSaudio. IntheBOTH(centerposition),theVORandADF signalsarenotsubjectedto anyfilteringin theaudiofrequencyband.

(6) SpeakerandHeadphoneControls- Thesecontrolsareusedto adjustthe speakerandheadphoneamplifier’svolume.Theyworkin serieswiththe individualaudiosourcecontrols.

(7) Marker(MKR)BeaconVolumeControl- Themarkervolumecontrolis alatchedswitchusedto controlthemarkeraudiovolume. Itdiffersfromtheothervolumecontrolsin thatitmaynotbe turneddownbelowa levelwhichis adjustedby a potentiometerinsidetheaudiopanel. Thispreventsthemarkeraudiofrombeingturneddowntoolowto be heard,causingthemarkersignalto be missed.

(8) MarkerBeaconMUTEControl- Themarkersensitivityiscontrolledby rotatingthecontrol.Pressingthecontrolactivatesthemarkermutefunctionthatis usedto temporarilysilencetheMarkerBeaconaudio(non-latching).Whenthemarkeraudioismuted,itwillremainmutedas longas theaudiolevelis abovea thresholdsetting.Whentheaudioleveldropsbelowthethreshold,a time-out sequencebeginsthatcontinuesto mutethemarkeraudioforafixedperiodof time. Afterthetime-outthemarkeraudioisunmuted.

(9) Interphone(INPH)Control- The interphonevolumecontroladjuststhe headsetaudiolevelwhenthe interphonefunctionis used. Theinterphoneaudiois notavailableoverthecockpitspeaker.Theinterphonefunctiontiestogetherthecross-sideaudiopanelandanyexternallylocatedmaintenanceaudiojacks. The interphonefunctionmaybe either“hotmic”or “push-to-talk.”

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PILOTSDIGITAL

1

Bus

AUDIORECEIVER

Honeywell INILYANCECITATION V

COCKPIT AUOIOSIGNALS

-1

WARNINGSAND

INTERCOM

DECODEAND DIGITAL

~ VOLUME = TO

CONTROL ANALOG

PROCESSOR

A

A

I

L

28 VDCINPUT

1

POWSR

POWER SUPPLY

COPILOTSDIGITAL 1 BUS “

AUDIORECEIVER

FRONTPANEL

SWITCHES

*

CONTROL+

PROCESSOR

‘!7FRONTPANEL

VOLUMECONTROL

I

DECODEANO DIGITAL

w vOLUME . TOCONTROL ANALOG

PROCESSOR

)+

—

L ——/

TO- RADIOS

AV-850AAudioControlUnitBlockDiagramFigure10-10

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Honeywell WJiW’”c’CITATIONn/V

10. F. CD-850ClearanceDeliveryControl/DisplayUnit(SeeFigures10-11and10-12,andTable10-7.)

SYSTEM INSTALLATION REMOTE TUNE TUNING NAVAUDIOONANNUNCIATOR \ ANNUNCIATOR CURSOR ANNUNCIATOR

RADIO TUNINGANNUNCIATORS

TRANSFER KEY

NORM/EMERGENCYMODE SWITCH

AD-21741

CD-850ClearanceDeliveryControl/DisplayUnitFigure10-11


Length(frombackof bezel) .................... 5.90in. (1.49.9mm)Width ........................................... 2.38in. \60.3mm)Height .......................................... 2.62in. (66.7mm)

Weight ................................................ 1.25lb. (567g)

Power Requirements ............................... 28 V dc, 4 VA maximum

DisplayType ......................... DichroicLCD,whitecharactersonblackbackground

MatingConnector........................................ MS3126F20-41SW

Mounting ........................................... UnitLockingPanels

CD-850ClearanceDeliveryControl/DisplayUnitLeadingParticulars

Table10-7

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Honeywell MW!ANC’CITATION V

TheCD-850ClearanceDeliveryCDU provides an alternat~ or emergencybackuD capability for tuninq the remote mounted VHF Communicationstrans~eiver and/~r VHFRadio System Bus (RSB)wishesto override the

TheCD-850can be usedwith low powerdrain.back-upthirdcontrol.selectedby eitherthe

Navi~ationReceiverinthe eventthattheprimarytuningis notavailable,or if thepilot/operatorbustuningforanyreason.

beforeenginestartforinitialcommunicationsIt canactas a stand-alonecontrolunitor aTheCD-850hasseveraloperatir~gmodeswhicharemodeknobor by installationstrai)pinqon the

rear conne;tor. The modes selected by installation st~appin~are:

. ClearanceDeliverymode,whichisthenormaloperatingmode.

. COMonlymode,whichmakestheunitdedicatedto COfVltuningonly.

. NAV only mode,whichmakestheunitdedicatedto NA’u’tuningonly.

Thenormalandemergencymodesaresubmodesthatares~lectedby themodeknobandareusedif theunitis strappedforclearancedelivery.

Thefollowingparagraphsdescribeeachfunctionor control:

10. F. (1) SystemInstallationAnnunciator- Eitherthe 1, 2, or 3 annunciatoris ON to indicateto whichsystemtheCD-850is ccmnected.

(2) RemoteTuneAnnunciator- Thisannunciatoris activeonlywhentheCD-850is strappedforNAVonlyor COMonlytuning. RMT isannunciatedwhentheradioistunedfromsomesourceotherthantheCD-850.

(3) TuningCursor- Thetuningcursorannunciatoriswhichis controlledby thetransferkey. It indfrequencycanbe changedby thetuningknobs.

(4) NAVAUDIOOn Annunciator- Thisannunciatorindifaudiohasbeenselectedon.

z lightedtrianglecateswhich

ateswhenNAV

(5) Emergency(EMRG)ModeAnnunciator- ThisannunciatorindicateswhentheCD-850hasbeenplacedin theemergencyback-LpmodewhichlocksoutallotherCOMandNAVtuningsourcesfor the sidetowhichit is connected.TheCOMandNAVarenowtl:nedexclusivelyby theCD-850.Thisannunciatoris notrelatedtr the emergencyfrequencyof 121.5.

(6) Squelch(SQ)Annunciator- Thisannunciatorindicttesthatthesquelchis opened.

(7) Transmit(TX)Annunciator- ThisannunciatorindicateswhentheCOMtransmitterisON.

(8) NAVAUDIOOn/OffSwitch- Thisalternateactionpl.shbuttonis usedto toggleNAVaudioON or OFF.

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Honeywell W!JR’”c’CITATION V

10. F. (9) Squelchusedto

(10) Tuning

(SQ)On/OffSwitch- ThisalternateactionpushbuttonistoggletheCOM squelchON or OFF.

Knobs - Thetuningknobsareusedto change the frequencyindicated by the tuning cursor.

(11) Normal/EmergencyMode Switch - This rotary switch knob providesalternate selection of the Normal and Emergency modes when theCD-850 is strapped for operation as a clearance delivery head.This switch is non-operating in the COM only or NAV on~y modes.

(12) TransferKey - Intheclearancedeliverymode,thetransferkeyalternatelyselectseithertheCOMfrequency(top)or I;heNAVfrequency(bottom)to be connectedto thetuningknobs

IntheNAVonlyor COMonlyconfiguration,thetransferkeytogglestheactive(top)frequencywiththepreset(bottom)frequency.In addition,holdingthe transferkey down for twoseconds will remove the preset frequency and place the CD-850 inthedirecttuningmode. To returnto theactive/presettuningmode,holddownthetransferkeyfortwo seconds.

(13) RadioTuningAnnunciators- Thesefourannunciatorsareannunciatedindividuallyto identifythe frequencyat thetopandbottomlines.

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Honeyweil WMYANCECITATION V

AUX PORT

COM AUXPORT

stllFfREGiSTE8

AND DRIVER

{“ j

DATAAUX PORT 1

CLOCK _;, ‘E’: z’=

NAV AUX Sw!=rPORT LOAD REGISTER PROCESSOR

AND DRIVER ?

PRIMARYRS8 s RSBRECEIVER

*

‘i ~::c =af+=

1 I

~u L_. I

SQUAT Sw

1 1,0 P

DISCRETE

CD.COM.NAV SEL STRAPS (2)

C“”CoN’”“RAp~ I‘AvcONF’GsTRAps‘“~

EL!ECTRO-

H

ELECTRO-LUMINESCENT LUMINESCENT?POWER AND BACK

0i<4MlNG LIGHTING

{DIMMING S VAC/DCINPUTS 28 VOC —

CD-850ClearanceDeliveryControl/DisplayUnitBlockDiagramFigure10-12

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Honeywell !!AWJEPANCECITATION V

10. G. DI-851DME Indicator(SeeFigures10-13and10-14,andTable10-8.)

RMUFREOSELECT PILOl%/COPILOT’.S MLSTUNEANNUNCIATOR (1/2)ANNUNClATOR ANNUNCIATOR

DME DISTANCE—

L~>F1’EE:21ATOR

DME CtiANNEL PAR~M~ERSELECT SELECT

DI-851DME IndicatorFigure10-13

AD-15823-RI


Length(fromback of bezel) .................... 6.27in. (159.3mm)Width .......................................... 3.26in. (82.8mm)Height ......................................... 1.54 in. (39.2mm)

Weight ................................................. 1.05111(476g)

PowerRequirements............................. 28 V dc, 2.8VA nominal

Mating Connector .................... Honeywell Kit Part No. 75(10436-901

Mounting ........................... Clamp,Honeywel1 PartNo. 7001995-1MSP64419)

DI-851DME IndicatorLeadingParticulars

Table10-8

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Honeywell WIJN””c’CITATION V

TheDME IndicatorcandisplayfourdifferentDMEdista?ces andassociated ground speed,time-to-stationor Identas selectedby thepilot. TheDMEhasmultiplescanningchannels,four(2 fromeachside)of whichareaccessibleto thepilot. TheDMEindicatorwillshowthedistancesassociatedwitheachoneof thesechannels.

The DMEdigitaldisplayis separatedintotwowindowsof liquidcrystaldisplays.The window on the left continuously displays distance innauticalmiles,andthewindowon therightdisplayseitherstationidentifier,groundspeedin knots,or time-to-goin minutes.

The

10. G. (1)

(2)

(3)

(4)

(5)

(6)

followingparagraphsdescribeeachfunctionor control:

RMUFrequencySelectAnnunciator- The annunciationNAV isdisplayedwhentheDME is associatedwiththeactiveNAVchannelselectedon theRMU. Ifthepresetchannelis selected,theannunciationis PRE.

Pilot’s/Copilot’s(1/2)Annunciator- The 1 or 2 isannunciateddependingon whetherthepilot’sside(1)or the copilot’s side(2)channelis selectedas determinedby thechannel(CH)selectbutton.

MLSTuneAnnunciator- MLSis displayedwhena DME receiverisbeingtunedby themicrowavelandingsystemrecei~er.

ParameterDisplayandSelect- TheDMEstationidentifier,thecomputedgroundspeedof theaircraftin knots,o- time-to-go(timeto reachthegroundstation)inminutesisdisplayedas a functionof theparameterselect(SEL) button. The KTS/MINannunciatoridentifieswhichparameteris beingdisplayed.EachtimetheSELbutton is pressed, the display changes as follows:

SELButton Parameter Annunciator

PowerUp Identifier 61ank1stPush GroundSpeed KTS2ndPush Time-To-Go MIN3rdPush Identifier B1ank

DMEChannelSelect- TheCH buttonselectswhichIIMEchanneltodisplay.At powerup,thesamechannelis displayedthatwas beingdisplayedat power down. IfMLS is not selected, the buttontoggles between NAV 1, NAV2, PRE1, andPRE2.

DMEHoldAnnunciator- HLDis annunciatedif the DME frequency issplit from the VOR.

22-14-00Page198.123

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Honeywell iNU?ANcECITATION V

DATA

CLOCK DISPLAY

ENABLE _

PRIMARYRSB lNPUT~ RSE +

SELECT +RSB

RECEIVER- PROCESSOR

SECONDARY~ SWITCHRS8 INPUT

[ DATA

tCLOCK

ENABLE

ONIOFF FROM NAV EPOWER

28 VDC INPUT POWER~SUPPLY

— ‘;: H

ww=g%:c~

AO-1.%Z&Rl

DI-851DME IndicatorBlockDiagramFigure10-14

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Honeywell MI!WANCECITATION V


22-14-00Paae198.125“Mar15/89

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Honeywell IWR!ANCECITATION V

10.H. AT-860 ADF Antenna (See Figures 10-15 and 10-16,

~+

AO-14 150

AT-860ADFAntennaFigure10-15


Length ......................................... 18.3 in. (~14.8Width .......................................... 8.33 in. (211.6Height ......................................... 1.51 in. [38.3

Weight ................................................ 3.7lb (1.68

mm)mm)mm)

kg)

Power Requirements .......................... +15 Vdcfrom AllFReceiver

Mating Connector ................................... Cannon KPT08P12-10S

Mounting .................................. Hard mount using fourNo. 10steelsocketheadscrews

AT-860 ADF AntennaLeadingParticulars

Table10-9

22-14-00Page198.126

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Honeywell INJR’”c’CITATION V

The AT-860 ADF Antenna performs the functions of reception,amplification, and combination of RF signalsso as to yieldlowfrequencyreceptionanddirectionalinformation.Normal reception of AMsignals is performed by the E-field element, or vertically polarizedantenna; while bearing information is provided by H-field antennas inthe formof a pairof loopantennasmountedat rightanglesto eachother. By carefullycombiningtheamplifiedsignals,bearing

information is obtained in the form of phase modulation on the received

RF whichis demodulatedandprocessedin thereceiver.

The antennaalsocontainsa selftestcircuitwhichradiatesa 120kHzsignalintothesenseandloopantennas.ThischeckstheoperationofboththeAT-860ADFAntennaandtheDF-850ADFReceive’Module. Properoperationis indicatedby a 1 kHztoneanda bearingindicationof 135degrees.

Cx >: .LOOP Cos CosANTENNA

BAIANCEDLOOPAMPL MODUUTOR

SINLOOP

SIN 50OHMAMPL OUTPUT

790DEGPHASE

EQUALIZER

120 KHZSELF TEST < TESTHAL OSC

AO-14S22-RZ

AT-860ADFAntennaBlockDiagramFigure10-16

22-14-00Page 198.127‘Mar15/89

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Honeywell M?;?’”c’CITATION V

10. I. AT-851MLSAntenna(SeeFigure10-17,andTable10-10.)

AD-1 5804

AT-851MLSAntennaFigure10-17


Length .................. 2.50in. [,62.5mm)Width .::::::::::::::::::::::::.................. 1.50in. (38.1mm)Height ......................................... 0.75 in. (19.05mm)

Weight ................................................ 1.20z (34.029)

PowerRequirements........................................... ~.KWpeak

Impedance...................................................... 50 ohms

MatingConnector.............................. TNCMale,GRFF4100-0001

Mounting ................................... Hardmountusingf[lur10-32uncflatheadscrews

AT-851MLSAntennaLeading Particulars

Table 10-10

TheAT-851MLSAntennais a verticallypolarizedC-bandantennaoperatingin the5.0to 5.1GHzfrequencyrangewitha maximumVWSRof2:1. The antenna is omnidirectional in azimuthandcosinusoidalinelevation.

22-14-00Page198.128

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Honeywell UMRANCECXTATIONn/V


22-14-00Page198.129

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Honeywell W!JYANCECITATION n/V

11. O~tionalLSZ-850LiqhtninqSensorSystem

A. LP-850LightningSensorProcessor(SeeFigures11-1.)

11-1and 11-2,andTable

LP-850LightningSensorProcessorFigure11-1

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Honeywell KKPANCECITATION Ii/v


Length ..........................................Width

14.75in.(375mm)2.42in.(61.5mm)...........................................

Height ........................................... 7.62in.(194mm)

6.75lb (2.76kg)Weight ...............................................

Power .................................................... 28Vdc, lA

MatingConnector................................... DPX2MA-67S-33B-OO01

Mounting ................................................. MountingTray

LP-850LightningSensorProcessorLeadingParticulars

Table11-1

The Processorreceivessignalswhicharenaturallygeneratedbylightningactivity,anddeterminestheirrangefromthisenergydistribution.At thesametime,bearingiscomputedby meansof Antennacrossedloopsin a mannersimilarto anADF.

Theoutputdatais convertedto an ARINC429low-speedarchitecturefordisplayon the EHSIor MFD. However,labelassignmentsdo notconformto ARINC429. Thedatastreamcontainsrange,bearing,andseveritydataforup to 50 cells. The429datacontainsalldataavailablefora360degreeareawitha radiusof 125NM aroundtheaircraft,and it isthetaskof thedisplaydeviceto determinewhichcellsfallwithinitsdisplayarea.

Modeselectionis providedby theLU-850LightningSensorControllerorWC-650WeatherRadarController.

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Honeywell M!KrANcECITATION n/V

28 VDC +POWERSUPPLY

*

I

HN, HP, E-FIELDANALOG

FROM ANTb TO DIGITAL

CONVERTER

oDATAPROCESSOR

INPUTS I lNPUTi I

fl~vDcToANTENNA

INTERNALPf3WER

LIGHTNINGFLAGVALID

RA13AR INDAND DATA NAVOLITPUTS

‘AS’TASREFIp~:J~oRI

-=’==2

LP-850LightningSensorProcessorBlockDiaciramFigureii-2

ARINC429OUTPUTSTO EFISAND MFD

AD-18249-R1

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Honeywell tiMErANcECITATION n/V

11. B. LU-850LightningSensorController(SeeFigures11-3and11-4andTables11-2and11-3.)

‘o LXSTBY

8

CLRITST

OFF @

Lo

LU-850LightningSensorFigure11-3

AD-20866

Controller


Length ......................................... 2.59in.(65.89mm)Width .......................................... 3.38in.(85.85mm)Height ......................................... 1.66in.(42.16mm)

Weight ................................................ 0.5lb {0.23kg)

LightningPower ................... 5 V ac/dcor 28 V dc,3.5VA maximum

MatingConnector......................● ● ................ MS3126F14-19SW

Mounting ................................● ....................... Screws

LU-850LightningSensorControllerLeadingParticulars

Table11-2

22-14-00Page198.134

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Honeywell WMWANCECITATION n/V

The LU-850LightningSensorControlleris usedto selectthemodesofoperationof thelightningsensorsystem.The switchfunctionsarelistedinTable11-3.

OFF All powerremoved.

STBY Displayis inhibitedbuttheprocessorisaccumulatingdata.

LX Systemis fullyoperational.Allaccumulatedlightningdatais displayed.

CLR/TST Accumulateddatais clearedfrommemory.After3 secondsthetestmodeis initiated.

LU-850SwitchFunctionsTable11-3

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Honeywell W!FANCECITATION n/V

J1

~

~ ElA

#2c

~ E3B

m’1~ C S2-B

#00/00

f ,I

?

IIII

02

IC S2-A

1-0

I 00;,..

.

H

J

K

L

+28V UGHTING

LIGHTING COMMON

+ 5V LIGHTING

PWR ON COMMAND

STBY

Lx

CLR/TST

SWITCH COMMON

AD-20867

LU-850LightningSensorControllerSchematic

Figure11-4 22-14-00Page198.137‘May25/90

Use or dmclosure of mformat!on on thw page IS subject to the restrictions on the title pag,] of this document.

Honeywell WUWANCECITATION n/V

11. C. AT-850Antenna(SeeFigure11-5,andTable11-4.)

AT-850AntennaFigure11-5


Length ....................................... 11.58in. (294.13mm)Width ......................................... 6.06in. (153.92mm)Height ......................................... 1.25in. (31.75mm)

Weight ................................................ 2.5lb (1.13kg)

Power ............................................. *12V dc fromLp-850

MatingConnector.......................................... KJ6F12A35-SN

Mounting ..................... HardMountUsingThreeNo. 10 ScrewsWithMaximumWasherDiameterof 0.455in.


Table11-4

22-14-00Page198.138

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Honeywell Wi’’r’””CITATION n/V

TheAT-850Antennacontainscrossedloop H-field antennae and an E-field

antenna similar to an ADF antenna.

Preamplifierstagesarealsobuiltintotheantennain orderto enhancethesystem’simmunityto noiseoriginatingin aircraftwiring.

TheH-fieldloopantennaearedesignatedHn andHw andareorientatedinsucha mannerthatHn willbe mostsensitiveto signalsoriginatingaheador behindtheaircraft,andtheHw antennawillbe mostsensitiveto signalsoriginatingabeamtheaircraft.

The E-fieldantennais constructedsuchas to be mostsensitivetoverticalE-fields.

tIZV dc powerforthepreamplifiersisprovidedto theantennafromtheProcessor.

The antennaalsocontainsa testwinding.Duringtestmodethiswindingis drivenwitha simulatedlightningsignalandcoupleswiththeE- andH-elementsof theantenna.Thus,thetestmodeis ableto provideanevaluationof theperformanceof theantenna,itspreamplifiers,andcablingto theLP-850LightningSensorProcessor.

TheAT-850Antennaisdesignatedformountingexternalto theaircraftand isnotto be paintedafterinstallation.Also,the antennaisencapsulatedandis notrepairable.

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Honeywell

11. D. AT-855Antenna(SeeFigure11-6,

MAINTENANCEMANUALCITATIONn/V

andTable11-5.)

AT-855AntennaFigure11-6


Length ........................................ 6.75in.Width ........................................ 6.060in.Height ......................................... 1.67in

Weight ...........................................● .... 2.5“

Power ........................................

MatingConnector.............................

Mounting...................... Hard Mount lJs”Maximum Wi

(171.45mm)(152.40mm)(42.42mm)

b (1.13kg)

fromLP-850

. . . . . . . . . . . . KJ6F12A35-SN

ng ThreeNo.8 ScrewsWithsherDiameterof 0.350in.


Table11-5

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Honeywell WKPAN’ECITATION Ii/v

TheAT-855AntennacontainscrossedloopH-fieldantennaeandan E-fieldantennasimilarto an ADFantenna.

Preamplifierstagesarealsobuiltintotheantennain orderto enhancethesystem’simmunityto noiseoriginatingin aircraftwiring.

TheH-fieldloopantennaearedesignatedHn andHw andareorientatedinsucha mannerthatHn willbe mostsensitiveto signal$originatingaheador behindtheaircraft,andtheHw antennawillbe mostsensitiveto signalsoriginatingabeamthe aircraft.

The E-fieldantennais constructedsuchas to be mostsensitivetoverticalE-fields.

~12V dc powerforthepreamplifiersis providedto theantennafromtheProcessor.

Theantennaalsocontainsa testwinding.Duringtestmodethiswindingis drivenwitha simulatedlightningsignalandcoupleswiththeE- andH-elementsof theantenna.Thus,thetestmodeis ableto provideanevaluationof theperformanceof theantenna,itspreamplifiers,andcablingto the LP-850LightningSensorProcessor.

TheAT-855Antennais designatedforradomemountingandis notto bepaintedafterinstallation.Also,theantennais encapsulatedandisnotrepairable.

22-14-00Paue198,141/198.142.

May25/90Use or disclosureof Information on this page IS subject to the restrictions on the title page of this document.

Honeywell #il!iEPANcECITATION V

SECTION3SYSTEMOPERATION

1. General

This section describes the operation of the System by separating it intothree subsystems: Flight Director Functional Description, paragraph 3;Autopilot Functional Description, paragraph 4; and Compass System FunctionalDescription, paragraph 5. Paragraph 6 describes the port connections and theprogramming pin functions of the EDZ-605 EFIS and the optional MDZ-605 MFDSystem. A table listing the system limits is contained in paragraph2.

22-14-00Page201Mar 15/89

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Honeywell MMRANCECITATION V

2. SvstemPerformance/O~eratinqLimits

The systemperformance/operatinglimitsfortheSystemarepresentedinTable201. All limitslistedhavea toleranceof f10percent.

Mode Controlor Sensor Parameter Value

Y/D Y/DEngage

A/P A/P Engage

BasicA/P Tcs

TurnKnob

PitchWheel

HeadingHold

Heading HeadingSELKnobSelect

VORor CourseKnob,VORAPR NAVReceiver,and

DMEReceiver

EngageLimit

EngageLimit

RollControlLimit

PitchControlLimit

RollAngleLimit

RollRateLimit

PitchAngle

PitchRateLimit

RollAngleLimit

RollRateLimit

RollAngleLimit

RollRateLimit

VORCapture:

Up to 45 degLeftor RightBank

Roll:Up to f45degPitch: up to f30degYaw: up to t45deg

Up to t45degRoll

Up to f20degPitch

5.5degjsec

*15deg Pitch

Variable

f35.5 deg.

&5.5 deg/sec

?27.5deg,t12degwithPC-500BankLimitSwitch

3 deg~sec

UD to ~ 90 deqBeamInterceptAngle ‘(HDGSEL)

SystemPerformance/OperatingLimitsTable201

22-14-00Page202Mar 15/89

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Honeywell U!MFANcECITATION V

Mode Control or Sensor Parameter Value

VORor CapturePointVORAPR(cent)

CourseKnob, RollAngleLimitNAVReceiver,andDMEReceiver RollRateLimitVORAPR

RollRateLimitVOR

VORCapture:CourseCut LimitDuringCapture

VOROn Course:RollAngleLimit

RollRateLimit

CrosswindCorrection

VORGainProgramming

OverStation:CourseChange

RollAngleLimit

RollRateLimitVAPR

RollRateLimitVOR

APR or BC CourseKnobandNAV LOCCapture:Receiver BeamInterceptAngle

(HDGSEL)

Functionof Beam,BeamRate,andcourseError,andDMEdistanceMinTripPointf30mV dc MaxTripPointt175mV dc

t27.5deg

5.5deg/sec

3.0deg/sec

t45degCourseErrorin VORf30degCourseErrorinVORAPR

1 deg/secin VOR5.5deg/secinVORAPI<

Up to i45degCourseErrorinVofl~30deg in VORAPR

Functionof DMEDistanceandTAS

Up to ~90deg

fl~: deg

5.!5deg/sec

3.0deg/sec

Up to t90deg

SystemPerformance/OperatingLimitsTable201 (cent)

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APRor BC CapturePoint(cent)

CourseKnoband RollAngleLimitNAVReceiver

RollRateLimit

CourseCutLimitDuringCapture

LOCGainProgramming

APR GS Receiverand GlideslopeCapture:AirDataComputer CapturePoint

PitchCommandLimit

GlideslopeDamping

PitchRateLimit:

GS GainProgrammingFirstStage(RadioAltimeterValid)

Functiorof Beam,BeamRate,andCourseErrorMinTripPoint~60mv dcMaxTripPoint~]75mv dc

~12deg

5.5deg~sec

t30deg Course

Functionof timeandTAS;Startsat1200ft radioaltitude

LOCDeviationgainreduction= 1 to0.5

~30mv dc at 150knots;beamrateandTAS programmed

tlodeg

VerticalAccelerationfromAccelerometer

~TAS (kn)deg/sec(MaxRate= 2deg/see)

Functionof Timeand TAS; Starts at

1200 ft radio

altitude

GainReduction= 1 to 0.33


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Honeywell WK?AN’ECITATIONn/V


APR (cent) FirstStage(RadioAltimeterInvalid)

SecondStage(RadioAltimeterValid)

SecondStage(RadioAltimeterInvalid)

I GA ControlSwitcheson FixedFlightDirectorThrottle(DisengagePitch-UpCommand;WingsA/P) Levelin Roll

PitchSync TCS Switchon Wheel PitchAttitudeCommandDepressed

ALT Hold ADC ALTHoldEngageRange

ALTHoldEngageError

PitchLimit

PitchRateLimit

VS Hold ADC VERTSpeedEngageRange

VERTSpeedHoldEngageError

PitchLimit

PitchRateLimit

StartsatGl~deslopeCapture

Functionof RadioAltitude;Startsat 250ft radioaltitudeGainReduction= 0.33to Zero

Functionof MiddleMarker

GainReduction= 0.33to 0.13

10°CitationV7.5°CitationII

~2~deg Maximum

o to 50,000 ft

~25ft

~2~deg

~TAS (kn)deg/sec(MaxRate= 2deg/see)

O t.of4000ft/min

~313ft/min

~2~deg

y)cJTAS (kn)deg/sec(MaxRate= 2deg/see)


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Honeywell WE!’’”c’CITATION V

Mode Control or Sensor Parameter Value

IASHold ADC IASEngageRange

IASHoldEngageError

PitchLimit

PitchRateLimit

ALT ADC and VNAV Preselect Capture RangePreselect Computer/Control ler

VNAV

Maximum VerticalSpeed forCapture

CaptureManeuver:MaximumGravitationalForce

PitchLimit

PitchRateLimit

AirDataComputer, AltitudeRangePathDME,VNAV AngleRangeComputer/ControllerElevationRange

BiasRange

PitchLimit

PitchRateLimit

80 to 45Ilkn

~TAS (kn)deg/sec

(MaxRate= 2deg/see)

o to 50,000 ft

~TM (kn)CWsec

(MaxRate= 2deg/see)

o to 50,000 ftt6 dego to 10,000ftt99,9milesfromVOR/TACorwaypoint

w kn deg/secTAS(MaxRate= 2deg/see)


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Honeywell U!KR’”c’CITATION V

3. Fliqht Director Functional Description

A. General

Paragraph 3.B. discusses conditions and functions that are referred to inthediscussionsof eachmodeof operationin paragraph3.C. Paragraph3.C.discussesthesignalflowthroughtheflightdirectorcomputerforeachflightpathmode. Figures203through214aresimplifieddiagramsthatshowtheunitsignalpathand interconnectwiringfortheapplicableselectedmode. Theyareusedin conjunctionwithFigures201and202whicharesimplifieddiagramsof themodeselectionlogicandtheFD OFFlogic,respectively.Figure215is a simplifieddiagramforthewarningflagsandbarbiaslogic.

B. ControlFunctions

(1) LateralBeamSensors(LBS)

Whenflyingto intercepttheVORor LOCbeamin theheadingselectmode,theLBSis controlledby thefollowingsignal;.Themagnitudeandpolarityof theairspeedprogrammedcourseerropsignaliscomparedwiththeDMEgainprogrammedbeamdeviationsignal. IntheLOCmode,thecourseerroris comparedwiththe beamdeviationsignalandrateof crossingthebeamto determinethe LBStrippoint.

WhentheLBStrips,theflightdirectorcommandsa turntowardthedesiredVORradialor runwayat the optimumpointfora smoothcaptureof thebeam. Ifthe interceptangleto thebeamcenterisveryshallow,the LBS wouldnottripuntilthe aircraftwas almoston beamcenter. Forthisreason,an overrideon the LBS occurs whenthe beam deviation reaches a specified minimum. TheminimumbeamsensortrippointforVORor VORAPRmodeis *3OmV, In theLOCmode,theminimumtripLBStrippointis t175

(2) NAVOn Course(NOC)

TheNOC isdefinedas:degreesandbankangletrips. IntheVORAPR

pointis t60mV. In allmodes,themaximummV.

LBStripped,courseerrorlessthan22.5lessthan6 degreesor 2 minutesafterLBSmode,thecourseerror,bankangle,andless

than75 mV beamdeviationmustexistsimultaneouslyfo~5 secondsforNOCto latchup. InVOR,LOC,BC,andAPRmodes,thecourseerrorandbankangleconditionsmustexistsimultaneouslyfor0.5secondforNOCto latchup. Whenin theNOC submode,themaximumbankanglecommandedis 12t 2 degrees.NOC startsthecrosswindwashoutfunctionintheflightdirectorcomputer.

Whenin theRNAVmode(7J1A-47grounded),NOCcanbe resetbyapplyingtheRNAVstaginggroundat 7J1A-26.Thisenablesthesystemto makelegchangesusingthe 27.5degreebankangle.

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Honeywell WNRANC’CITATION V

3. B. (3) OverStationSensor(0SS)

The0SS sensesthebeamratenoisein thezoneof confusionovertheVOR station. After the NOC submode is established, the 0SS submode

is armed. In theVORmode,if the beamdeviationratereachesapredeterminedlevel(8mV of deviationpersecondwithd~viationgreaterthan75 mV),the0SStrips. 0SSremovestheradiobeamdeviationfromtheflightdirectorrollcommandoutput. In theVORmode,the beamdeviationis removeduntilthebeamdeviationhasdecreasedbelowthetrippointfor20 seconds.In theVCIRAPl&mode,if theDME is validandlessthan1.5nauticalmilesand if 0SS,thebeamdeviationratemustreach4 mV/secwitha deviationgreaterthan30 mV forthe0SSto trip. Thedeviationis removecluntilthebeamdeviationhasdecreasedbelowthetrippointfor4 ~econds.IftheDME is notvalid,0SS is the sameas theVORmode.

(4) AfterOverStationSensor(AOSS)

AOSSis theperiodbetweenthelossof 0SSandtheoccurrenceofNOC.

(5) VerticalBeamSensor(VBS)

Theverticalbeamsensoris armedwhentheradiois tuneclto a LOCfrequency,the LOCreceiveris valid,andthe LBS has tripped. TheVBStripsas a functionof verticalspeed,TAS,andglideslopedeviation.Whentheverticalrateis zeroandTAS is 15(Iknots,theVBSwilltripat 30 mV of glideslopedeviation.Thiswillresetthepreviouslyselectedpitchmodeandchangeaircraftattitudetosmoothlycapturetheglideslopebeam.

Inthebackcourse(BC)mode,theVBS is lockedoutwhenBC isselected.

Whencapturingfromabovethebeam,theaircraftmustbe descendingat a ratethatwillcreatea suitableinterceptangle.

(6) LocalizerGainProgramming(LOCII)

ForfrontcourseILSapproaches,thissubmodeis armedaftertheLBShastrippedandNOC is engaged.Witha validradioaltimeter,LOCII engageswhentheradioaltitudeis lessthan1200feet. Ifthealtimeteris notvalid,LOC II engagesat approachcapture.Ifthealtimeterisnotvalidandan approachmodehasnot beenselected,LOCII startsas a functionof NOC andTTL.

Forbackcourseapproaches,thissubmodeis armedafterI.BShastrippedandNOChasbeenestablished.Witha validradioaltimeter,operationis as describedforfrontcourseapproach.If theradioaltimeteris notvalid,LOC II startswhenNOChasbeenestablished.

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3. B. (7)

(8)

(9)

(lo)

(11)

Honeywell

G1ideslopeOn Course(GSOC)

MAINTENANCEMANUALCITATION V

and (GSOC+15)

Glideslopeon courseis establishedwhentheVBSha;tripped,glideslopeis validandLBShastripped.At GSOC,a signalisappliedto transitiontheaircraftfromtheexistingflightpathtotheflightpathnecessaryto flytheglideslopebeam. After15seconds-(GSOC+15),thissignalis removedand’theg’lideslopedeviationgainis increased.

GlideslopeGainProgramming

(a)

(b)

True

FirstStageGainProgramming

FirststagegainprogrammingstartsaftertheVBStrips,LOC II is engaged.

Second-StageGainProgramming

AfterVBStrips,thesecondstageof gainproqramminqis

when

armed.Whentheradioaltimeteris val;d,th=second-stageis engagedwhentheradioaltitudeis lessthan250feet. Iftheradioaltimeteris notvalid,thesecondstageis engagedwhenthemiddlemarkersignalis received.

Airspeed(TAS)FunctionGenerator

An approximationof TAS iscalculatedas a functionof altitudeandindicatedairspeed.Thisfunctionis usedto programheadingselecterror,courseselecterror,airdatacommands,verticalbeamsensor,pitchratelimit,and ILSgainprogrammers.If theairdatacomputeris notvalid,theTAS programmer reverts tr~ a fixedairspeed.

Distance Measuring Equipment (DME) Gain Programmer

This function optimizes VORor VORAPR operationby changingthegainof theradiosignalas a functionof DMEdistar]ceto theVORTAC station.TheDMEprogrammerrevertsto a fixedgainlevelandremainsthereif theDMEis invalid,DME is placedin theDMEHOLDconfiguration,or the RNAVmodeis selected.

EADISingleCue

Whena commandsignalis appliedto thecue input,thecuewillmoveCW or CCW (roll)or up or down(pitch).Thisprovidestherequiredcommandto allowthepilotto maneuvertheaircraftin theproperdirectionto reachthedesiredflightpath.

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Honeywell IWFANCECITATION V

If the informationrequiredto flythedesiredflightpathbecomesinvalid,thecue is biasedfromview.

A rollmodemustbe selectedbeforethe singlecuewillbe in-view.If onlya rollmodeis selected,pitchcommandwillbe pitchattitudehold.

c. FlightDirectorModeFlowDescription

(1) HeadingSelectMode(SeeFigure207.)

The headingselectmodeis selectedby pressingtheHDGbuttononthemodeselector.TheHDGbuttonilluminateswhenthemodeisengagedandHDG is annunciatedon theEADI. Headingselectwilloverrideandresetotherpreviouslyselectedlateralmodes. Theheadingerrorsignalrepresentsthedifferencebetweenthefixedheadingindexandtheselectedpositionof theheadingbugon theEHSI.

The errorsignalfromtheSG-605SymbolGeneratoris appliedto theflightdirectorcomputer,demodulated,programmedto increasegainas a functionof increasingTASandappliedto thebankanglelimiter.Thenormalbankanglelimitis 27.5degrees.PressingtheBANKLIMITswitchon thePC-500AutopilotControllerappliesagroundto 7J1A-93to changethebankanglelimitto 12 degrees,whenin theHDGmode.

The headingselecterrorsignalis limitedto a 3-degree-per-secondrollrateandsentas rollcommandto the autopilotcomputer.Thissignalis alsosummedwitha demodulatedrollsignalfromtheverticalgyro. The resultantcommandfromthissummationis appliedto theSG-605to positiontherollcueof theEADI. Thisis thesignalusedby thepilotto flyto thedesiredheading.Ifthesignalsourcesof thecommandsignalbecomeinvalid,rollbarbiasis appliedto biastherollcommandcueoutof view.

(2) Go-AroundMode(GA)(SeeFigure207.)

Thismodeis selectedby pressinga throttle-mountedGO-AROUNDswitch.Thiscancelsanypreviouslyselectedpitchor rollmode.Thego-aroundlogicswitchopensremovingallrollcommandsignalsfromtheEADIcue. Theverticalgyrosignalremainsto drivetherollcommandinputto theSG-605SymbolGeneratorforpositioningthe EADIrollcommandcue. Itwillprovidea wings-levelcommandtothe EADIrollcommandcue. Aftergo-aroundhasbeenselected,anyrollmodecanbe selected.Thisselectionwillcancelthewings-levelsubmodeof go-aroundbutstillleavethe fixedclimbattitude.Go-aroundcanbe cancelledby selectinganotherpitchmode,pressingTCS,or engagingtheautopilot.

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Honewel[ ~f#&NANcECITATION n/V

3. c. (3) VORMode(SeeFigure208.)

The VORmodeis selectedby pressingtheNAVbuttonon theflightdirectormodeselectorwiththeRNZ-850NAVUnittunedto a VORfrequency.Whenoutsidethelateralbeamsensor(LBS)trippoint,theHDGmodeisautomaticallyselected.The HDGmodeis usedtointerceptthedesiredVORradial.At thistime,HDGandNAVARMmodesare illuminatedon themodeselectorandHDG (green)andVOR(white)areannunciatedon theEADI. Whenreachingthe LBStrippoint,thesystemautomaticallyswitchesto theVORcapturemode.TheHDGandNAVARM annunciatorsareturnedoffandtheNAVCAPmodeis illuminatedon themodeselector.On the EADI,!-lDGturnsoffandVOR (green)is annunciated.Theflightdirectorcomputernowprovidesa commandto interceptandtrackthedesiredVORradial.

ThedesiredVORradialis seton thecourseselectpointeron theEHSI. ThecourseerrorsignalfromtheSG-605SymbolGeneratorrepresentsthedifferencebetweenthefixedheadingindexandtheselectedpositionof thecourseselectpointeron theEHSI. Thissignalis demodulated,programmedto increasegainas a functionofincreasingTAS,andsummedwiththeradiodeviationsignal.Radiodeviation,fromtheRNZ-850NAVUnit,is gainprogrammedas afunctionof DMEdistancefromtheVORstation.Theresultantof thesummingof courseerrorandradiodeviationsignalsis appliedtothecoursecutlimiter.Thissignalwillbe limitedto a levelthatwillresultin a maximumcoursecutangleof 45 degreesto thedesiredVORradialaftertheLBStrips. At thistime,thebankanglelimitis 27.5degreesandtherollratelimitis 3 degreespersecond.Signalflowfromtheratelimiteris as describedin theHDGmode.

At NOC,bankanglelimitis reducedto 12degrees,rollratelimitis 1 degreepersecond,additionalfilteringis providedto minimizetrackingbeamnoiseandcourseerroriswashedoutto eliminateanysteady-statecourseerrorin thepresenceof crosswind,therebypreventingbeamstandoff.

WhenpassingovertheVORstation,the0SScircuitremovestheradiodeviationsignalfromtheflightdirectorcommandoutputuntilthedeviationsignalis no longererratic.Whileoverthestation,coursechangesaremadeby selectinga newcourseon theEHSI. IftheNAVdataisnotvalidpriorto thecapturepoint,theLBSwillnot tripandthesystemremainsin theHDGmode. Aftercapture,iftheNAVdata,compassdata,or verticalgyrogoesinvalid,therollcommandcuewillbiasfromview. Theflightdirectorcomputerwillremainin theNAVmode. A momentarylossof NAVUnitvalidwillcauseNAVCAPto turnoffon themodeselectorandVOR (green)toturnoffon theEADI. WhentheNAVvalidsignalis restored,NAVCAP andVOR (green)areagainannunciated.Withthelossof NAVCAP,lateralmodelogicis removedandtheautopilotrevertstoautomaticwingsleveling.WhenNAVCAP is restored,theautopilotwillagainflytherollcommand.

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Honeywell M!W’”c’CITATION n/V

3. c.

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(4) VOR ApproachMode(SeeFigure208.)

TheVORapproachmodeis selectedby pressingtheAPR buttonon theflightdirectormodeselectorwiththeRNZ-850NAVUnittunedto aVOR frequency.OutsidetheLBStrippoint,HDGandNAV ARM are

illuminated on themodeselectorandHDG (green)andVApp(white)areannunciatedon theEADI. At capture,-HDGandNAVCAP illuminateson themodeselector.VAPP(green)is annunciatedon the EADI. ThepreviouslydescribedfortheVORmode. Gainsapproach,crosswindwashoutismuchfasterincoursecut limitis reducedto 30 degrees.

(5) LocalizerMode(SeeFigures209and210.)

andNAVARM turnoffHDGturnsoffandmodeoperatesasareoptimizedforthismode,andthe

The localizermodeis selectedby pressingtheNAVbuttonon theflightdirectormodeselector.TheRNZ-850NAVUnitis tunedto alocalizerfrequencyandtheEHSIcourseselectis setto thepublishedfrontcourseforthe ILS. Operationoutsidethe LBStrippointbeforebeamcaptureis as describedfortheVORmode exceptLOC (white)is annunciatedon the EADI. At theLBStrippoint,NAVCAP is illuminatedon themodeselectorandtheHDGandN.4VARMannunciatorsareoff. On the EADI,HDGturnsoffandLOC (green)isannunciated.

The courseerrorsignalisgainprogrammedas a functionofcalculatedtrueairspeedandsummedwithradiodeviationfromthelateralgainprograminer.Theresultantsummedcourseerrorandradiodeviationsignalis coursecutlimitedto 30 degreesandr[ratelimited.The crosswindcorrectedcourseerrorandradiodeviationsignal,beforesummationwithrollattitude,is routedthe autopilotcomputer.

At NOC,bankanglelimitis reducedto 12 degrees,rollratelimremainsat 5.5degreespersecond,andadditionalfilteringis

11

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providedto minim;zetrackingbeamnoise. Courseerroriswashedout at a muchfasterratethantheVORmodeto quicklyeliminateanysteady-statecourseerrorin thepresenceof crosswind,thuspreventingbeamstandoff.Signaloutputsfromtheratelimiterfunctionas describedabove.

Gainprogrammingis controlledby the LOCII submode.WhenLOC IIis established,gainis reducedfrom100to 50 percentas a functionof timeandairspeed.Also,at LOC II,laggedrollis summedwiththe signalsto improvelateralcontroldamping.

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Honeywell M!R’”c’CITATION V

3. C. (6) LocalizerApproachMode(SeeFigures209and210.)

The localizerapproachmodeis usedto makea fullILSapproach.The approachmodeis selectedandthe localizerandglideslopemodesarearmedby pressingtheAPR buttonon themodeselectorwith theRNZ-850NAVUnittunedto an ILSfrequency.Whenoutsidethelateralbeamsensortrippoint,theheadingmodeis automaticallyselected;the rollcueon theEADIreceivesa headingselectcommandas describedinthe headingselectmode;and,HDG mode illuminates

along with the NAVARM andAPRARMannunciatorson themodeselector.HDG (green),LOC (white),andGS (white)areannunciatedon the EADI. Whenreachingthelateralbeamsensortrippoint,thesystemautomaticallyswitchesto theAPRmode,HDGandNAVARMannunciatorsextinguish,andNAVCAP illuminateson themodeselector.HDGextinguishesandLOC(green)andGS (white)areannunciatedon the EADI.

The courseerrorandradiodeviationsignalsareprocessedthesameas previouslydescribedforthelocalizermode.

(7) BackCourseMode(SeeFigure209.)

Thismodeis selectedby pressingtheBC buttonon theflightdirectormodeselectorwiththeRNZ-850NAVUnittunedto alocalizerfrequency.Outsidethe LBS trip point, the heading select

modeis engagedwithbackcoursearmed. The HOGandBC ARMannunciatorsareilluminatedon themodeselectorandHDGandBC(white)areannunciatedon theEADI. The EHSIcourseselectis setto thepublishedfrontcourseforthe ILS. Selectionof backcoursereversesthecourseerrorandradiodeviationsignalsforproperbackcourseapproachresponse.At beamcapture,HDGandBC ARM turnoff andBC CAP illuminateson themodeselector.On theEADI,HDGturnsoffandBC (green)is annunciated.

Backcourseoperatesthesameas thelocalizermodepreviouslydescribed.The radiodeviationsignalis attenuatedto compensateforthecloseproximityto thelocalizerantenna.Glideslopecaptureis lockedoutwhentheBC modeis selected.

(8) PitchHoldSubmode(SeeFigure211.)

Thissubmodeis engagedby selectinganyrollmodeon theflightdirectormodeselector,withoutselectinganypitchmode. Noannunciatorsareilluminatedto announcethissubmode.

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Honeywell WJ!F’”c’CITATION V

The verticalgyroinputsignalis synchronizedbeforeanymodeisengaged.When onlya lateralmodeis selected,thesynchronizerretainsthepitchattitudeto providethepitchholdfunction.Theoutputsignalis appliedto thepitchlimiterandis thensummedwiththeverticalgyrosignal.At engagement,thesesignalscanceleachotherso thecuegoesto thenullpositionon the EADI. If theaircraftchangesattitude,an errorsignalis appliedto theEADItocommanda returnto theoriginalattitude.

Whena pitchmodeis selected,thesynchronizationcircuitoperatesas a pitchattitudewashout.Thiseliminatesstandofffromdesiredpositiondue to long-termattitudechanges.

3. c. (9) AltitudeHoldMode(SeeFigure211.)

Thismodeis selectedby pressingtheALTbuttonon the flightdirectormodeselector.SelectingALTwillresetanypreviouslyselectedpitchmodes. ALT is illuminated on the modeselectorandALT (green)is annunciatedon theEADI. Onceengaged,themodewillbe resetif theairdatacomputeris notvalid. ThepitchcuewillbiasfromviewiftheVG is notvalid.

WhenALT is selected,a logicgroundis suppliedfromtheflightdirectorcomputerto theairdatacomputerto engagethemode.Afterengagement,anydeparturefromtheengagedaltituderesultsinan errorsignalfromtheairdatacomputer.Thiserrorsignalisprogrammedto decreasethegainor ratelimitas a functionof TAS.Thissignal,outof theratelimiter,is sentto theautopilotcomputer.It is alsosummedwiththewashedoutverticalgyrosignal,displacementlimited,summedwiththeverticalgyrosignal,amplified,andsentto theSG-605to drivethepitchcueof theEADI.

An absoluterollsignalis appliedto theversinecircuitstoprovideaccelerationcompensationin turns. Thisversinesignalcancelstheradialaccelerationoutputof thenormalaccelerometer.The resultantsignalis summedwiththealtituderatedampingsignalfromtheairdatacomputer.Thissignal(IVV)is scaledforproperresponseon a givenaircraftandsummedwiththealtitudeerrorsignal.

WhenTouchControlSteering(TCS)is activated,theversineanddampeningsignalsareremoved,ratelimiteris shortedout,verticalgyrowashoutis synchronizedto theexistingattitude,andthealtitudeholdmodein theairdatacomputerdesynchronizesto thenew altitude.AnyerrorsignalexistingwhenTCS is pressediswashedout in about5 seconds.WhentheTCSbuttonis released,thesystemoperatesas previouslydescribed.

If theADC becomesinvalid,theTASgainprogrammerrevertsto afixedairspeed.If theBAROsettingon thebarometricaltitudeindicatoris changed,a commandisgeneratedto flytheaircraftbackto theoriginalaltitudereference.

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Honeywell M!JR’”c’CITATION V

3. C. (10) VerticalSpeed Hold Mode(SeeFigure211.)

Thismodeis selectedby pressingtheVS buttonon theflightdirectormodeselector.This action will reset any previouslyselected pitch mode. VS is illuminated on the mode selector and VS

(green)is annunciatedon theEADI. Onceengaged,themodewillberesetif theairdatacomputerisnotvalid. The pitchcue willbias from viewif theverticalgyroisnotvalid.

WhenVS is selected,a logic ground is supplied from the flight

director computer to the air data computer to engagethemode. Iftheaircraftdepartsfromtheengagedverticalspeed,an errorsignalis sentto theflightdirectorcomputer.Thissignalfollowsthepathdescribedforthealtitudeholdsignalwithoneexception.In theVS mode,thealtituderatedampingsignalsarenot used.

Anytimethepilotdesiresto modifyhisexistingverticalspeed,pressingtheTCSbuttonwilloperatein the samemanneras theAltHoldmode. Whentheautopilotisengaged,the pilotcancommandanewVS by movingthepitchwheelon theautopilotcontroller;theEADIairdatacommanddisplaywillchangeas a functionof pitchwheelmovement.

(11) IndicatedAirspeedHoldMode (See Figure 211. )

Thismodeis selectedby pressingthe IASbuttonon the flightdirectormodeselector.Thisresetsanypreviouslyselectedpitchmode. IAS is illuminatedon themode selector and IAS (green)isannunciatedon theEADI. Onceengaged,themodewillresetiftheairdatacomputeris notvalid. Thepitchcuewillbiasfromviewif theverticalgyrois notvalid.

WhenIASis selected,a logicgroundis suppliedfromthe flightdirectorcomputerto theairdatacomputerto engagethemode. Iftheaircraftdepartsfromtheengagedairspeed,an errorsignalisappliedto theflightdirectorcomputer.ThissignalbypassestheTASgainprogrammerandis appliedto thepitchratelimiter.From

this point, the signal path is thesameas previous-lydescribedintheALTmode. The airspeedcommandedvalueon the EADIairdatacommanddisplaycanbe changedby thepilotby movingthe pitchwheelon theautopilotcontrollerwhentheautopilotis engaged.

(12) G1ideslopeApproachMode(SeeFigure212.)

Thismode is selected by pressing the APRbuttonon theflightdirectormodeselectorwiththeRNZ-850NAVUnittunedto alocalizerfrequency.Glideslopecaptureis inhibiteduntilthelocalizerhasbeencaptured.WhenAPR is selected,localizercapture,andtheVBShasnotbeentripped,APRARM andanypreviouslyselectedpitchmodeis illuminatedon themodeselector.ThepreviouslyselectedpitchmodeandLOC (green)andGS (white)areannunciatedon theEADI. Afterthelocalizerhas been captured,

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Honeywell WW!!AN’ECITATION V

thesystemautomaticallycapturestheglideslopebeamwhen the VBStrips. At thattime,APRARM andpreviouslyselectedpitchmodes

areresetandAPRCAP illuminateson themode selector. On the

EADI, any previously selected pitch modesareresetand LOC(green)andGS (green) are annunciated. If the glideslope data is not valid

prior to capture, the vertical beam sensorwill not trip and the

system will remain in thepitchmode. Aftercapture,if theglideslopedataor verticalgyrobecomesinvalid,thepitchcommandcuewillbiasoutof view. A momentarylossof glideslopevalidwillturnofftheAPR CAP annunciator on themodeselectclr.Whenthevalidsignalreturns,APR CAP is again annunciated.

Theglideslopedeviationsignalis appliedto the GS gairprogrammer.Theoutputof theGS gainprogrammerismaximum(100percentgain)at beamcapture.GlideslopecaptureisdeterminedbysummingtheGS deviationsignalwithTAS and IVV siqnals._ TAS andIVVareappliedfor15 secondsthroughswitchGSOC+15EOFF. Whenthesumof thesesignalsequalszerotheVBS trips. Duringthis15-secondduration,theTASand IVVsignalsprogramthe(S deviationcommandingtheaircraftto transitionfromlevelfliqhtto flyingtheglideslopebeam. After15 seconds,theGSOC+15EOFFswitchopensandbothGSOC+15EO switchescloseto increasethegainof theGS deviationsignalfromthecaptureto thecontrolphaseandto adda dampingsignalto improveglideslopetracking.Thiscombinedsignalis thenprogrammedto decreasetheratelimitas a functionof increasingTAS. Fromtheratelimiter,a displacementandintegralsignalissuppliedto theautopilotcomputer.Theotheroutputfromtheratelimiteris summedwithwashedoutverticalgyroto eliminateanytendenciesforbeamstandoffdue to steady-stateattitudechanges,displacementlimited,summedwithvertical gyro,

amplified, and applied to theSG-605to drivethe pitchcueof theEAD1. Thisprovidesa commandto smoothlytracktheglideslopebeam.

At LOCII,theglideslopedeviationsignalis first-stagegainprogrammedas a functionof timeandTAS,andstartsat the1200-footradioaltimeter(RA)trippointwiththeRA valid. Thegainisreducedfrom1 to 0.33. If theRA is invalid,glideslopegainprogrammingis initiatedafterglideslopecaptureandNOC.

The secondstageof glideslopegainprogrammingbeginsat analtitudeof 250feetwhentheradioaltimeteris valid. Theglideslopesignalis programmedto a gainof zeroat zeroradioaltitude. Thisis a linearreductionfromgainof 0.33at 250feetof radioaltitude.If theradioaltimeteris invalid,thesecond-stagegainprogrammingis triggeredby themiddleImarkersignal. In thiscase,thegainreducesfrom0.33to 0.13andremainsat the0.13level. The rateof gainreductionforbothstagesis controlledby timeandtrueairspeedin additionto theradioaltimeteror middlemarkerinputsignals.

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Honeywell WWANC’CITATION V

3. C. (13) Go-Around Mode (See Figure 212.)

Whenthego-aroundmodeis initiatedby pressingtheGA buttononthethrottlehandle,theGA logicswitcheschangestate. This opensthesignalpathfromthepitchratelimiter,disablesthepitchattitudewashoutcircuitandinsertsa voltagerepresentinga fixedpitchup command.Thissignal,appliedto theSG-605to drivethepitchcueon the EADI,commandsthepilotto pullthenoseof theaircraftup to thefixedgo-aroundangle.

(14) AltitudePreselectMode (SeeFigure213.)

Thedesiredaltitudeis selectedon theVNAVComputer/Controller.Thismodeis selectedby pressingtheALT SELbuttonon theflightdirectormodeselector.Anotherpitchmode,VS, IAS,or PITCHHOLDis selectedto flythe aircrafttowardtheselectedaltitude.Whenoutsidethe altitudebracketpoint,ALTSELARM andtheengagedpitchmodesareilluminatedon themodeselector.TheengagedpitchmodeandASEL (white)areannunciatedon theEADI.

Whenreachingthebracketaltitude,thesystemautomaticallyswitchesto ALT SELCAP andthepreviouspitchmodeis cancelled.At thistime,ALT SEL CAP is illuminated on themodeselectorandASEL (green) is annunciated on theEADI. As the aircraftreachestheselectedaltitude,ALTSELCAP is cancelledandALT is engaged.TheALT SELCAPon themodeselectorandASELannunciatoron theEADIareturnedoff;thenALT is illuminatedon the mode selectorand ALT (green) is annunciated on theEADI. If the air data

computer is not valid, the altitude preselect modecannotbeselected.The commandcuewillbiasoutof viewif theverticalgyrois notvalid.

Theerrorsignal,representingthedifferencebetweenselectedandactualaltitude,is appliedto theflightdirectorcomputerfromtheVNAV. The bracketdetectoris armedby a groundfromtheVNAV.Whenthebracketdetectortrips,theerrorsignalis appliedto theTAS programmer and the gain is decreased as a function of increasing

TAS. Theerrorsignalis summedwiththe altituderatedampingsignalsbeforebeinggainprogrammed.Theprogrammeroutputisratelimitedas a functionof TASandappliedas an outputto theautopilotcomputer.It is alsosummedwithwashedoutpitchattitudeanddisplacementlimited.Thenit is summedwiththeverticalgyrosignal,amplified,andappliedto the SG-605to drivethepitchcueon theEADI. Thisprovidesthecommandto capturetheselectedaltitude.

AfterALTSEL CAPandbeforegoingintoALT hold,anychangeofpreselectedaltitudewillresultinALTSELmoderevertingbacktoARM.

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Honeywell UWUYANCECITATION V

3. C. (15) VerticalNavigationMode(VNAV)(SeeFigure214.)

To utilizetheVNAVcapabilityof theVNAVComputer/Controller(VNCC),the pilot must set selected altitude, station elevation, and

TO-FROMoffsetfromthestation.

The altitude is selected by placing the selector switch t~ ALT and

slewing the display to the desired altitude. TheSTAELswitchpositionis selectedandthe stationelevationis seton thedisplayby rotatingthesetknob. Resolutionis 100feet. TheTCIor FRposition is selected and the distance ahead of, or beyond the VOR

(along track offset) is set. Resolution is 0.1 nautical mile. Theverticalangle(VANG)positionis selectedandthecomputedverticalpathangleto thedesireddestinationis displayed.The pilotmayobservethe continuouslycomputedflightpathangle(anglecomputemode)untilthedesiredangleis displayedandthenpress the VNAVbutton on the flight director modeselector.Thiswillfreezetheangleandcapturetheverticalpath,or thesetknobmay be usedtopreseta desiredverticalangle(fixedanglemode). ThenpressingtheVNAVbuttonwill arm the system to capture the selected vertical

path angle. Should the VNAV button not be pressed before theselected angle is reached, theVNCCwillrevertto theanglecomputemode,continuouslydisplayingthecomputedangleto thedesireddestination.

Whena verticalpathhas been selected by pressing the VNAV button

on the modeselector,theverticaldeviationwithrespectto theselectedverticalpathis displayedon the EADI and EHSI. Pressingthe VNAV button willcausethe aircraftto capturetheverticalpathimmediatelyif in theanglecomputemode. Thiswillcancelanypreviouslyselectedpitchmode. VNAVCAP is illuminatedon themodeselectorandVNAV(green)is annunciatedon the EADI. IftheVNAVbutton on the modeselectoris pressedbeforethepresetangleisreachedin thefixedanglemode,theVNAVARM andpreviouslyengagedpitchmodeare illuminatedon themodeselector.Thepreviouslyselectedpitch modeandVNAV(white)is annunciatedon theEADI.Whentheselectedangleis reached,VNAVCAP illuminates on the modeselector,VNAVARM andthepreviouslyselectedpitchmodeturnoff.On the EADI,VNAV(green)turnson andthepreviouslyselectedpitchmodeis turnedoff.

Whenthe aircrafthasreachedtheselectedaltitude,ALT is

illuminatedandVNAVCAP is turned off on the mode selector. ALT isannunciated and VNAV is turned offon theEADI.

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Honeywell WUWANCECITATION V

As the aircraft passes the selected point or the desired altitude,

the vertical path problem will be cancelled. This replacesthevaluesin STAEL, TO, FR,andVANG with dashes. This prevents use of

erroneous VORTAC data for a subsequent problem. Furthermore, should

the computed angle reach a preset maximum, the provision forvertical path navigation will be cancelled in the samemanner.Thisautomaticcancellationwillbe precededby flashingof theVANGdisplayforthelastdegreeof computerverticalpathangle.

The signalrepresentingVANG/verticalerroris suppliedto theflightdirectorcomputerfromtheVNAVComputer/Controller.Intheanglecomputesubmode,theflightdirectorsynchronizesto theconstantlychangingangle.WhenVNAVis selectedandimmediatelycaptured,the synchronizerbecomesan angleholdci~cuit.Anydeviationfromtheengagedangleprovidesan errorsignalintotheTASprogrammer.

Inthefixedanglemode,theselectedangleis storedin thesynch/holdcircuitin theflightdirectorcomputer.Whentheaircraftreachesthepointwheretheactualandselectedanglesareequal,thesystemcapturesandfliesthepreviouslyselectedVANG.Anydeparturefromthisangleprovidesan errorsignalintothe TASprogrammer.

Theerrorsignalis gainprogrammedandpitchrate‘limitedas afunctionofTAS. It isthensentto theautopilotcomputer.Insidethe flight director computer, it is summed with a washed outvertical gyro signal, displacement limited, summed with the verticalgyro, amplified, and applied to the SG-605 to drive the pitch cue onthe EADI.

A sampleproblemis diagramedin Figure215. At the instantshown,the aircraft is 1000 feet above and 13.0 range miles from a VORstationwhichhasan elevationof 1500feet. The pilotdesirestogo to 10,000feetat a point10milespasttheVOR station.Iftheproblemvariables(STAEL,ALT,TO-FRM)hadalreadybeenput intothe

VN-212andthepilothadpressedtheVNAVbuttonon themodeselectorat the instantshown, the aircraft would climbto thedesiredpointat a 3-degreeangle.

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Honeywell W!!kl!ANcECITATION V

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IIS MODE Gt20

AS MGDEGND-J=4s

47

6SJZAII ((4

AIS DATA Cm(-1 a7s

so GNO FSON _1LL21A-31

ACCEL CGMPGNO

L— ——— .

I!$J1

33

3s

Ss

37

PITCH BAR GAINSENSITIVITY AGJuST

IF=== 7PITCHRATELIMIT

i AIFIDATA S&W -ml--+--(

t

PITCHCUDTO S0+06FIG. 304

I SLEW CDFATFlOL

I

I

AL1 RATE S9 1640 mVOC/lK FTWIN

NGLO ERRORALT 10 ntVGC/FTVS 1 VDC/lK FT/MINtAS3S nWGC/KN {

t

“I---41

&LT MOLD ● SYNC GNO

IS NOLD ● SYNC GND

AS HOLD ● SYNC GND 9TAS

G41NPRoGRAMMERI

al160KNDTBIAS

lGTE:ALL LABELED SWITCHESARE SNOWN IN TNE OPENPCFSMON LABELEDCGNDMGN CLOSESSWITCH.

.——————- —---- ——————--— —-4

r&4AVERTICAL

—— —— -

IGYRO

I prT

<J

Ss

cc

An

VG PITCH1 (200mVAC10EG1

b--l)v311AVG PITCH

1s ATT INPUTTO AP

16 CA6PTRFffi. 216

==)PITCHATT TOSG.605Fffi 204 [

- –13 VDC~.

P*% H% VS + APSS

/0P,lCH SAR SIAS

AD !s6s4R,

L —.— — .— —— —— .— — —— —— —— . . —— —— —— ——

Altitude,VerticalSpeed,andIndicatedAirspeedHoldModeFlowDiagram

Figure21122-1 4“00

Page245/246‘May25/90

Use or disclosure Of Information on Ihm page is subject to the restrlchons on the Itlle page of Ihm document.

Honeywell UKR!AN’ECITATION n/V

.—— ——. ——— ——. —— ——. — ——— ——— -- ~500FLIGHT DIRECT0RC0MPUTER

7J 1A

32 SEC \

WASHOUTAND

FILTER ACCE LDAMPGND

IvvFROM

++13 VDCFIG. 211

1GS DAMPINGGAIN ADJUST

lGJIA

a

2D GSOISPLACEMENT ToAp

)

CMPTII22 GS INTEGRAL FIG. 218

KG-222 NORMALACCELEROMETE~y——— ——

ITOROUE MOTOR

2

(+1.6 vGC AT ICI

/2

TO lwIA-44 (AP DISENG

I PD ?{ -

\IF ACCEL ●1.@E+ <ZERO 0)

h.. -/ 3

SEISMICGNG FOR

I MASSACCEL OAMPI!4G ~

=

~b ~ -15 VW ?Row

7.IIA-5 (CIT II)

——. —. lWiA-7 (CIT V)

IPITCH BAFI GAINSENSITIVITY AOJUS1

+

GA

-(CA

GSOC+lS EOPITCH CMOTO S0-505FIG. 204

b

)GSOC+15 EOFF

.

L ————J L.rzr

———RT.SRADIO ALTIMETER

ToTRANSMITANT

13SVGC RA VALlO Y *

INDICATOR OUTPUT w — (NOTE 2)E

10

-1‘FTE : -:

AUXILIARY*

RECEIVE OUTPUT *

ANT

LALTTRIP COMMON P 65J2A

——— — =——— —

fiZ-241 AIRDATACOMPUTER~

NOTES:

TAS GAIN

FIG. 211PROGRAMMER~ ‘J=’’’ATORI

1. ALL LABELEO SWITCHES ARESHOWN IN THE OPEN POSITIONLABELEO CONOITICLNCLOSES

2.

3.

5WITCH.

THE GRADIENT AT20J1.W IS .4.0 mVOCIFT.OALT ❑ O VGC.THE GRADIENT AT 20J1-X IS:ALT. 4s0 n. o.ozh. 0.4 vocALT.4SOIS=10+10Ln H+2DVDC

500

CITATION II= 7.5 OEG WITH A WOKRESISTOR. CITATION V =10 OEG WITHA 225S RESISTOR.

NCPITOT

IALT (0,75V DC

~ATIc J

L—————

4

.—— ———————+=x~.——FGxvERTIt2AL GyRo

— lJ1VG PITCH ATT

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*

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I TO AP CMPTR

PITCH

I

sYNcliRo x

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v

=)

PITCH ATT 5B2 y TO SO-W5

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zg

FIG, 204

d L

PITCH HOLO~-11 VDC

/0

PITCH 6AII BIAS AD 12695 R2

——— — .—. — ——. —.— ——— ——— ——. — ——.1- ——— — 2

G1ideslopeApproachandGo-AroundModeF1ow Diaqram

Figure21~ 22-14-00Paae247/248“May25/90

Use or disclosure of InformalIon on this page IS subject to the restrictions on the title page of this document.

Honeywell MAINTENANCEMANUALCITATIONV

1

#

4

4

5

5

.—— — —— ——. — .— —.— —— —.— — ——— ——. !

3

4

1

(

1

1

11

$

!2

!4

m

il

6

2

2-500FLIGHTDIRECTORCOMPUTER

FILTER

VG ROLL A71 SIGNALFROM FIG. 20S USEO TOCOS4PENSATE FOR THE

(200 mVAC DEGI

ROLL COMPONENT OF*

THE ACCELEROMETERACCE1DAMPGNIZSIGNAL

NORMALAcCELEFSOMETEFI I+ 5 VDC Al IGIINPUT FROM 17J1-2

0

(sEE FIG. 212)GND FOR rACCEL DAMpfiNG 7

r ———.—

kSG-6G5SYMBOLGENERATOR 16U2B

IAPS VALID ~1 .OUTPUT

I

6EJ1h

APB VALIO ~INPUT

L,....__ —__

— TO MOOE LOGIC CKTS

——— —-~N-212 VNAV

ICOMPUTER/CONTROLLER

10I1A

II23 AIR QATA CUDTO AP CMPTRFIG. 218

25

d~PITCHSYNC

IPRESELECTROF4 GND

UEARIZEOESELECTROR GNO

I

1PITCH SAR GAINSENSITIVITY AOJUSTu--

u 11- ——— —TAS

GAINPROGRAMMER

I

-

1PITCH CMOTO SG-605FIG. 204

r——— —-

AZ.241AIRDATACOMPUTER

(ml

I26 VAC

(c I

+2&lI

{

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RET

I (+2.6v M +0.2 mVDC/Fl

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RE1

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65(500 mVC4Xl K FT/MIN)

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q150 OJGr

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IEscc

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7VG PITCH ATT

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Ml10J1A

,5 VG PITCHAT7 INPUT

16 TO AP CMP1FIG. 218

‘)

PITCH AllTO sG-605

+FIG. 204

[

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PITCti EIAR BIAS AD 186%L—————— 2

——— —— —— —— —. ——— ——— . ——— ——— ——.

AltitudePreselectModeFlowDiagramFigure213

22-14-00Page249/250

Mar 15/89Use or dmclosureOf Informationon this page is subjad to the restrictionson the tttle page of Ihls document.

‘%==”%%=+’”‘“’’’””’=O”O==-------------------[TO MOOE LOGIC CKTS

10 VNOC CKTS

I

I

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m

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)

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L ——— ——— d

VerticalNavigationModeFlowDiagramFigure214

22-14-00Page251/252

Mar 15/89Use or disclosureof informationon this page is subject to the restrictionson the title page of thm document.

Honeywell W!!!FPANC’CITATION V

1,000 FT

DME = 13.0MILES

.1

-10,000 FT

T7,500 FT

-2,500 FT -

VOR STATION, 1,500 FTABOVE SEA LEVEL

r——T

.—— —— ——— —.— — ——— ——— —I

1,500 FT (STAEL)I

i SEALEVEL

VNAV Sample ProblemFigure 215

30567

22-14-00Page 253/254

Mar 15/89Use or disclosureof informationon this page is subject to the restrictionson the Mle pag{ of Ihm document.

Honeywell MNWAN’ECITATION V

lx-2TAlRiA R::l%s

J ; ‘: “-DE

~*212vNAvcoMpuTER/controller——— .—— ——

1COMPUTER 9J1

I

lSJ1 131SPLAYH

2BVDCADC VALID 12 36 H

m

I

I

H -—

I26VAC 30 PDwER

SUPPL v3s I

1-

MONI1OR

=—— I

NOTES:

1. (H~DENOTESHIGH FORAVALID LOGIC CONDITION;ANY INVALID LOW WILLCAUSE THE ROLL OFI PITCHBAR TO BIAS OUT OF VIEWOR THE APPLICABLE FLAGTO COME IN VIEW.I

,*

c NC

I e28 Voc

I P(3WEROG VALIO

PGWER AOEOUACVISUPPLV WMEELSPEEO

J

MC)NITOR !.

GYRO IMOTOR

I

115 VAC 05

nI

2. LOW LC3G4CCLOSES PiTCHOllROLL SAR BIAS SWITCH ASSHOWN ON FtGLSRES207 THRU214 ALLOWING FIXED BIASVOLTAGE TO SE APPLIED TOADI TO BIAS CUE OUT OF

-———— ——. —— A

—.— —~-1,1 BAROALTIT”DEINDICATOR

——— —1m

I I taJ1ll_’- H

●

H

I3. WITH ROLL MOGE SELECTED

IExCEPT NAV CAP, BC CAP,ANO VOR APR CAP.

Wsw .

1- ——. ——— ——. J I~405 SYMBOLGENERATOR

———— ———— .—

24VDCHOGVALN3INPUT)J6531A

S4

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II

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I AD 18698@

FailureWarningFlagsandBarBiasLogicDiagramFigure216 (Sheet1 of 2) 22-14-00

Page255/256‘Mar15/89

Useordisclosure01informationonthispage is subject to the restrictionson the title page of thm document,

Honeywell WKY’”c’CITATION n/V

——— —hU&::NZ4350 yJ;

I6!

\

I

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(

+ 89 *NAVDATA – 59

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+ 57

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/

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r——— —

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r——— —

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I

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J2E

40

41

42

43

68

69

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84

85

75

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+

-)

VOR/LOC ANDGS VALID

+

-)DME VALID

+-) GLIDEPATHAN[~AZIMUTH VALID

VNAV VALID

APS VALID

RADIO ALTITUDEVALID

FLIGHT DIRECTORVALID

HEADING VALID

ATTITUDE VALID

(OA VALID

FailureWarningFlagsandBarBiasLogicDiagram

Figure216 (Sheet2)

Use or disclosure of information on this page is subject to the restrictions on the title pag?

IIIIIIIIIII

b65J1A

TOED-600EADI ANDEHSI TOFLAGFAILURE

I

IIIIIIII

IIII AD-18698@FII

J

22=14=00Page257/258

ofthlS~oCu~~#25/90

Honeywell W!ijFANcECITATION n/V

~ 4. AutopilotComputerFunctionalDescription(SeeFigures217,217.1,218,and219.)

A. Autopilot/YawDamperEngage(SeeFigure217or 217.1.)

The autopilotis engagedby pressingtheAP ENGAGEbuttonon thePC-500AP Controller.Engagingtheautopilotautomaticallyengagestheyawdamper. WiththemomentaryAP ENGAGEswitchbuttonpressed,28 voltsdcfromdisconnectswitchesS5 andS6 areroutedthroughthefollowingto1OJ1B-3Oto turntransistorQ1 on.

. AP Controllerturnknobswitchto llJ1-L● AP ControllerAP ENGAGEswitchto lJ1-P. VG Validswitchto lJ1-R. Rollratemonitortestboardto 57J1-H(CitationV only). RollratemonitorrelayK1 energizedcontactto 57J1-K(CitationV

only)● Rollratemonitortestboardto 1OJ1B-3O(CitationV only)● lJ1-Rto 1OJ1B-3O(CitationII only)

WithQ1 on, 28 voltsfrom1OJ1A-5areroutedthroughtheENGseriesswitchanda diodeto 1OJ1B-33.These28 voltsdc areroutedthroughtheVG validswitchpathto 1OJ1B-3Oto latchQ1 on aftertheAP ENGAGEbuttonis released.WithTCSnotselected,the28 voltsdc from1OJ1A-5arealsoroutedthroughthe ENG and TCS seriesswitchesto 1OJ1A-3toengagethe aileronandelevatorclutchesandareroutedto llJ1-ctolighttheAP ENGAGEbutton,whichindicatesthattheautopilotisengaged.

TheYawDamperis alsoengagedwhentheAP ENGAGEbuttonis pressed.The28 voltsat 1OJ1B-3OthatturnQ1 on areroutedthrough;idiodeto turnQ2 on. WithQ2 on,28 voltsat 1OJ1B-13areroutedthroughtheENGseriesswitchto 1OJ1B-12to engagetherudderservoclutch.Thisvoltageis alsoroutedthrougha diodeto latchQ2 on andto llJ1-RtolighttheYD ENGAGEbuttonwhichindicatesthattheyaw damperisengaged.

TheYawDampercanalsobe engaged,withouttheautopilotbeingengaged,by pressingtheYD ENGAGEbuttonon thePC-500AutopilotController.TransistorQ2 is thenturnedon by 28 voltsappliedto 1OJ1B-35,Theyawdamperengagecircuitrythenoperatesthesameas previouslydiscussed.

The autopilotwilldisengageif any of the following conditions exist:

. Pressingthepilot’sor copilot’sAP disconnect switch● Pressing the go-around switch. Pressing the pilot’s or copilot’s TCS switch. Using manual electric trim. Lossof theVG or DG valid. InternalAP Computerpowersupplyfailure. Highservotorquecurrent. AP Test. Verticalaccelerationgreaterthan1.6gor lessthanO.Og(CitationV

only)● Rollgreaterthan40 degrees(CitationV only). Rollgreaterthan30 de reesandrollrategreaterthan20 degreesper

second(CitationV only7 22=14-00Page259May 25/90

Use or disclosure of information on thm page is subject to the restrictions on the t!tle page of this document.

1

4. B.

Honeywell

The Yaw damper will disengage for


the following conditions:

. Pressingthepilot’sor copilot’sAP disconnectswitch

. Pressingthego-aroundswitch

. Lossof DG valid

Roll Axis (See Figure 218, sheets 1 and 2.)

The roll axis of the autopilot receives signals from the following

components:

Attitudevalidandrollattitudesignalfromthe verticalgyro.

Headingvalidandheadingerrorsignalfromthedirectionalgyro

Rollcommandsfromtheflightdirectorcomputer.

Rollturnknobcommandsfromtheautopilotcontroller.

(1) Synchronization.Synchronizationin therollaxisis achievedwhenthenet signalto therollservosumiszero. Priorto autopilotengagement,allautopilotcommandinputsare zerobecausetheautopilotisnotyetcoupledto anymodeand theROLLCPL,HDG HOLD,andTK ● AP ENGswitchesareopen. At thistime,the inputto therollsynchronizerthroughtherollratelimiterwillalsobe zerobecauseswitchAP ENG ● TCSSEL ● ROLL HOLD is open. Rollattitudefromthe verticalgyroisdemodulatedandappliedto thesummingamplifier.Ifthesumof thesetwosignalsis notzero,qn errorsignalappearsandisamplified,andappliedto theAP ENG+ TCSSELswitch. Duringsynchronizationpriorto autopilotengagement,theswitchis closed,applyingtheerrorsicmalto therollsynchronizerintegrator.Beforeengagement,theROLLHOLDswitchis closedandtheerrorsignaldrivestheintegrator.The integratorisdrivenuntilitsoutputisequalto therollattitudeinput. Whentheyareequalthe errorto theintegratoris zeroandtherollaxisissynchronized.Synchronizingprovidestransient-freeengagementoftheautopilot.Duringsynchronization,the errorsignalis alsoappliedto therolldisplacementpathbutthe aileronservois notengaged.Therefore,no synchronizationtransientswillappearonthecontrols.

Priorto engagementof theautopilot,theservodriveclutchis notengagedto thecentralsurface;thus,the servoloopfollowsup ontheinputcommandsynchronizingto zeromotorrotation.#tengagement,theservois at a nullpositioncorrespondingto theinputcommand.

(2) Heading-Hold.If theautopilotis engagedwithno lateralmodeselectedandwitha bankangleof lessthan6 degreesandtheTURNknobin thedetentposition,theheading-holdmodeis engagedandtheHDG HOLDswitchisclosed,allowingthe outputof theheading

22-14-00Paqe260May-25/90

Use or dwclosure Of information on this page IS sub!ect to the restrictions on the title page of this dc :ument.

Honeywell WWANCECITATION V

synchronizer to be coupled into the roll rate limiter. Prior to

engagement or whenothermodesareengaged,thissignaloutputiszero. If the aircraft departs from the synchronized heading, an

error signal is applied to therollratelimitcircluit.

Therollratelimiterderivestherateof thecommanderrorsignal.Theratesignalis clippedby a diodelimiterandthen applied tothe integrator. Iftheratesignalrisesto a leve”lthatwouldcommandmorethan5.5degreespersecond,thediodescliptheerrorsignalintothe integrator,thuslimitingthe integratoroutputto5.5degreespersecond.Whentheratesignaldecreases to a level

that commands less than a 5.5 degrees per secondro’11rate,thissignaldrivesthe integratorat thatrateandthediodelimitershaveno effecton theerrorsignal.Errorcommandsignalsfromtheratelimitercircuitareappliedto therollsynchronizer.Becausetheautopilotis intheheading-holdmode,thecommandsignalpassesthroughtheROLLHOLDswitchto the integratorinthe rollsynchronizer.Whentheauto~ilotis engagedandTC:Sisnotselected,theA/P ENG ● TCS”SELswitchis closed, adding a resistor

to the feedback path around the integrator. This converts theintegrator into a lag circuit.

Thecommandsignalfromthelagcircuitis appliedto a bankanglelimiter.Thiscircuitlimitsthesignaloutputfortheheadingholdmode. The limiteris removedfromthecircuitwhentheautopilotisdisengagedor whentheTCS buttonis pressedto allowsynchronization.Intheheading-holdmode,theA/P ENG ● TCS SEL

switch is closed, placing the limiter in therollcommandcircuit.

Thelimitedcommandis amplifiedandappliedto the rolldisplacementpath. Thefeedbackpathto therolls.qnchronizerisnowopenedbecausetheA/P ENG+ TCSSELswitchis openintheheadingholdmode. Thedisplacementcommandis invertedandpassedthroughtheQ-switchingandsoft-ride,gain-changingcircuitsto besummedwithrollrate.

Rollrateprovidesa short-termdampingsignal.The resultingerrorsignalis amplifiedby therollservosumamplifierandappliedtotheservoamplifier.The resultantoutputsignald-ivestheaileronservomotor.

Theservoamplifieroutputis limitedby theelectronictorquelimiter.Intheeventof a failureof thetorquelimiter,themonitorcircuitwoulddisengagethe autopilotwhenservotorqueexceededa predeterminedlevel. The clutchis engagedso theservomotorwilldrivetheaileron.As themotordrives,a ratedampingsignalfromtheservotachometeris fedbackas a dampingsignaltostabilizetheservoloop. A positionsignalis alsofedbacktoopposethecommandsignal.Deflectingthe aileronwillbanktheairplanetowardtheheadingthatexistedwhentheaJtopilotwasengaged.As theairplanebankanglechanges,theo~tputof the

22-14-00Page261Mar 15/89

Use or disclosure of information on this page IS subject to the restrictions on the title page of this document.

Honeywell WY’””CITATION V

4. B. (3)

vertical gyro reflects the change. The inputfromthegy~oopposestheerrorsignal,thusreducingtheresultingerrorto theservodrive. As theairplanebankstowardthedesiredheading,theerrorfromthe headingsynchronizerwill be reduced. As this e-rordecreasesthecommandsignalsthroughoutthe axis will begin to rolltheairplanetowardwings-level.The final result will be a null at

the servo output with the airplaneflyingwings-levelon theheadingthatexistedat thetimeof autopilotengagement.

TouchControlSteering(TCS). WhentheTCS switchon thecontrolwheel is pressed, the error signal into the roll synchronizer is

reduced to zero because the inputswitchesto therollratelimiterareallopened,removingallcommandinputsto thesesummingpoints.Theaileronservodriveclutchisdisengaged,allowingthepilottoplacethe airplanein thedesiredrollattitude.As the attitudechanges,theoutputto therollservosumwillchange.Thisoutputrepresentsthedifferencebetweenairplaneattitudeandtlesignallevelat theoutputof therollsynchronizer.Theoutputto theservosum is fedbackintotherollsynchronizerkeepingtheservosuminputat a null.

The amplifiederrorsicmalis fedbackto therollsynchronizerthroughtheclosedA/P ENG+ TCSSEL switch.At thistirwtheA/PENG. TCS SELswitchopens,removingtheresistorfromthaoutputoftheintegrator.Withtheresistor’seffectremoved,thesynchronizeractsas an integrator,notas a lagcircuit.Theerrorsignalis appliedthroughthe ROLLHOLDswitchto drivet~eintegrator.The integratordrivesuntilitsoutputis eqJal to the

rollattitudesignal.At thistimetheerrorsignalswillbe zero,andthe systemis synchronizedto theexistingairplanebankangle.

WhentheTCS switchis released,thefeedbackpathfortheamplifiederrorsignalis openedby theA/P ENG+ TCSSEL switch. ReleasingtheTCS switchalsoclosestheA/P ENG ● TCSSEL switch,convertingthe integratorintoa lagcircuit.If no lateral modes are selected

in theflightdirectorcomputerandthebankangleis lessthan6degreeswhenTCS is released,theautopilotwillreturnto headinghold. When thebankangleis greaterthan6 degreesat TCSrelease,theROLLHOLDswitchopensandtheairplanemaintainstheselectedbankangle. Anydeviationfromthisbankanglewillgeneratean errorsignalto drivetheaileronservoto returntheairplaneto thedesiredbankangle. Thisbankangleis maintaineduntila new attitudeis selectedwithTCS. If theautopilotwascoupledto the flightdirectorwhen TCS was used,uponreleaseoftheTCS switch,theautopilotwillcoupleto theengagedflightdirectormode.

22-14-00Paqe 262Mar”15/89

Use or dwclosure of information on this page IS subject to the restrictions on the title page of this d~cument.

Honeywell tifivl”’”c’CITATION n/V

4. B. (4) TURNprev.

HOLD

Knob. WhentheTURNknobis rotatedoutof detent,anyously coupled roll modeis uncoupled.TheROLLCPL and IDG ~switches areopen,removingallinputsignals,TheTK ● AP ENG

switchclosesto applytheTURN-knobcommandsignalfromtheautopilotcontroller.-Thecommandsignalis ratelimitedto 5.5degreespersecondandpassedthroughtheROLLHOLDswitch(seelastparagraphof TCS explanation)to drivetherollsynchronizer.Thecommandsignalis limitedto *3Odegreesby knobexcitation,thensummedwiththeverticalgyroattitudesignal.Fromthispoint,theerrorsignalis appliedto thedisplacementpathto drivetheaileronservo.

ReturningtheTURNknobto detentwillreturntheairplaneto awings-levelconditionandengagetheheading-holdmode. Othermodescanbe selectedandwillbe coupledaftertheTURNknobis returnedto thedetentposition.

(5) LateralModes(HeadingSelect,NAVSelect,BackCourse,VORAPR).Whenthepilotselectsa lateralmodeon themodeselector,theROLLCPLmodeis engagedif theautopilotisengaged.Thedesiredrollcommandsarecomputedandprocessedby theflightdirectorcomputerandareappliedto theautopilotcomputerat 1OJ1A-18.

ThecommandsignalispassedthroughtheROLLCPLswitch.AllotherinputsareblockedbecausetheHDGHOLD,andTK . AP ENGswitchesareopened. Fromthispoint,therollcommandpathfollowsthesamepathas theheading-holdsignalto drivetheaileronservo.Theerrorsignalwillflytheairplaneto theselectedflightpathandrolloutto a wings-levelconditionon theselectedflightpath.

(6) LiftCompensation.Duringa turn,an airplanelosesliftandtendsto losealtitude.To compensateforthiscondition,theautopilotrollaxisappliestherollattitudesignalfromtheverticalgyrotoan absoluterollcircuit.Thiscircuitwillprovidea nose-upcommandto thepitchaxiswhentheairplaneis bankedleftor right.Theamplitudeof thiscommandshouldbe equalto thelossof liftdueto theturnso thatverylittle,if any,altitudeislostduringtheturn. Theabsoluterollcircuitoutputis alsoappliedto therolllogiccircuitsto generatea bankangleof lessthan6-degreeslogicin additionto theliftcompensationin thepitchaxis.

(7) TorqueSwitching.(SeeFigure219or 219.1.) The rollandpitchtorquelimitersandtorquemonitorsareswitchedas a functionofbarometricaltitudefromtheairdatacomputer.Thenominaltorqueswitchpointin theautopilotcomputeris 13,400i 1,100feetofbarometricpressurealtitude.Abovethisaltitude,thepitchandrolltorquelimitersandmonitorsareswitchedto a lowtorqueregime.

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Honeywell MM!’’””CITATION V

An aneroidprovidesan independentsecondsourceof altitudeinformationformonitoringtheairdatatorqueswitching.If thetorque has notbeenswitchedto lowtorqueabove16,000t 1,000feet,as determinedby theaneroid,a TORQUEWARN light willannunciatethecondition.TheTORQUEWARNfunctionis testedby theTESTEA FLTbuttonon theautopilotcontroller.

At an air data barometric altitude of about 19,000 feet, ‘themonitor

circuitry cross checkstheaneroidlogic. If the aneroid has not

switched from ground to +15 volts dc before this altitude, the

TORQUE WARN light will annunciate this condition.

Lossof the air data valid will cause the system to reverl: to the

low torque regime.

4. c. PitchAxis(SeeFigure218,sheets3 and4.)

The pitch axis of the autopilot receives signals from the following

components:

Airdatainformationfromtheflightdirectorcomputer.

Airspeedandaltitudeinformationfromthe airdatacomputerfor

Q-switching.

Pitchwheelcommandsfromtheautopilotcontroller.

Attitudevalidandpitchattitudeinformationfromthe vertical gyro.

Glideslopedeviation signal from the flight director computer.

(1) Synchronization. Synchronization in the pitch axisis achievedwhenthenetsignalto thepitchservosum iszero. Priorto autopilotengagement,theglideslope,airdata,andPITCHwheelsignalsareblockedby the open GS CPL,ADCCPL,andPW switches.

Pitchattitudefromtheverticalgyroisdemodulatedand issummedwiththeoutputof thepitchintegrator.Duringsynchronization,theoutputof the integratorfollowspitchattitudecausingtheoutputof thepitchdisplacementamplifierto be zero. Iftheairplaneattitudechanges,the sumof theintegratorand ~erticalgyrosignalsis an errorsignal. The error signal is applied to the

pitch displacement path and through the closedAP ENG+ TCSswitchandtheclosedPITCHHOLDswitchto drivethe integrator.Theintegratoris drivenuntilitsoutputisequalto the verticalgyrosignalandthenetpitchdisplacementsignalis zero.

Prior to engagement of the autopilot, the servo drive clutch is not

engaged to the central surface; thus, the servo loop followsup onthe input command synchronizing to zero motor rotation. Atengagement, the servo is at a null position corresponding to the

input command.

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Honeywell W’URANCECITATIONV

4. c. (2) PitchHold. Aftertheautopilotis engaged,ifno verticalmodeisengagedon theflightdirectorandthePITCHwheelis notrotated,theautopilotis in thepitch-holdmodeand the pitch integrator

holds the pitch attitude reference signal. Theoutputof theintegratormaintainsthe airplanepitchattitudethatexistedat thetimeof engagement.Any changein pitchattitudehillproduceanerrorsignal,andtheservodrivemotorisdrivenin thedirectionto returntheairplanepitchattitudeto thatwhichexistedat thetimeof engagement.The servodrivedeflectstheelevatorcontroltabbecausetheservodriveis coupledby theservoclutchafterautopilotengagement.The errorsignalsdrivetheservoandelevatorto returntheairplaneto thedesiredattitude.Whenthisattitudeis achieved,theelevatorwillbe at theneutralpositionandthe servosumoutputwill be at a null.

(3) RateDamping.Dampingof theaircraftcentralresponse is provided

by pitch rate. Pitch rate is derived from pitch attitude in thepitchratetaker. This signal is applied as a damping signal forpitch attitude control.

(4)

(5)

LiftCompensation.AbsoluterollsignalfromtherollaxisisshapedbeforepassingthroughtheQ-switchingandsoft-ridecircuitry.Theliftcompensationfunctiongeneratorcircuitryproducesa liftcompensationsignalwhosemagnitudeis proportionalto sec~-l,where$ is the airplanebankangle. Thissignalpitchestheaircraftup whenmakinga bankturnto compensateforthe lossof liftin a turn. Thismaintainstheaircraftneara constantaltitudein a turn. If the autopilot is in the airspeed hold mode,theliftcompensationsignalis removedcompletelyto preventtheliftcompensationandairspeedholdcommandsignalsfromopposingeachotherandcausingairspeedholdmodecontrolproblems.

TouchControlSteering(TCS). WhentheTCS switchon thecontrolwheel is pressed, the autopilot disengaged synchronization paths are

established. A feedback path is provided from the pitchdisplacementinverterintothe pitch integrator through A/P ENG+TCSandPITCHHOLDswitches.The servoclutchisdisengagedandthepilotfliestheairplaneto a desiredpitchattitude.The autopilotwillsynchronizethepitchintegratorto thenewairplanepitchattitudeandthenetservosumoutputwillbe at a null.

WhentheTCSswitchis released,thefeedbackpatharoundthepitchintegratorisopenedandthe integratorretainsthepitchattitudesignalexistingat thetimetheswitchis released.If the airplane

deviates from the synchronized pitch attitude, an error signal

appears at the integrator output and is usedto positionthe servomotorto drivetheairplanebackto thesynchronizedpitchattitude.

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Honeywell MI!MPANC’CITATIONV

4. c. (6) PITCHWheel. WhenthePITCHwheel is rotated and IASandVS modes

are not selected, the PM switch closes, allowing the output of thePITCHwheeltachometerto be applied.The PW switch remains closedas long as thePITCHwheel is being rotated. It opens when the

PITCHwheel movement stops. Rotating the PITCH wheel will close the

PITCH HOLD switch (applying the PITCH wheel signal to the pitch

integrator). If the GS is coupled, the PITCH wheel operation will

be inhibited. The rate of PITCH wheel rotation (tachometer output)

is integrated by the pitch integrator producing an attitudedisplacement command since integrated rate is displacement. If the

output of the integrator is changed, by the PITCH wheel, this upsets

the balance of the integrator and vertical gyro inputs. Ihe error

signal is routed through the displacement path to the servoamplifier, the servo drive moves the elevator and changes the

airplane attitude. The airplane attitude will be changed until the

vertical gyro signal is equal to the pitch integrator output. At

this time the airplane will be at the new commanded attitude.

(7) Air Data Modes(Altitude, Airspeed, or Vertical SpeedHold!). WhentheALT,IASor VS mode is selected in the flight director computer

with the autopilot engaged, a ground is supplied from the flight

director computer to pin 1OJ1B-38, -40, or:~l. These ground

signals control the switches labeled ALT ● PW, IASor VS. TheALT,IASor VS error signal corresponding to the mode selected isprovided from the flight director~omputer to the air director

computer input through the ALT ● PW, IASor VS and ADC CPL switches

into the pitch integrator and the pitch command amplifier, Thecombination of the pitch command and integral signals are summedwith the vertical gyro signal.

If the summation of the error and gyro signals is not zero, theerror signal will be used to drive the servo drive motor and change

the elevator control tab position in the direction to get the

airplane back on the selected air data reference. As the airplane

changes pitch attitude to obtain the desired air data reference, the

vertical gyro signal changes and the air data error signa”l

decreases. The net signal will continue to drive the servo to

change airplane attitude until the air data error signal ~rom theflight director computer is zero and the net signal is zero. The

airplane is then at the desired attitude.

The servo amplifier output is limited by the electronic torque

limiter. In the event of a failure of the torque limiter, the

monitor circuit would disengage the autopilot when servo torque

exceededa predeterminedlevel. The clutch is engaged so the servo

motor willdrivetheelevatorcontroltab. As themotordrives,arate damping signal from the servo tachometer is fed back as a

damping signal to stabilize the servo loop. A position signal is

also fed back to oppose the command signal.

If in the IASor VS modes, rotation of the PITCHwheel changes theIASor VS reference.If in the ALT holdmode, rotation of the PITCHwheel cancels the mode.

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Honeywell KWUHANC’CITATION V

4. c. (8)

(9)

Glideslope.Glideslopeinformationis appliedthroughtheGS CPLswitches. Prior to glideslope capture, the GS CPL switches are

open, blocking the glideslope signals from the flight directorcomputer. At that time the autopilot will be flyj~]g the pitch holdor airdatamode. IftheALT,IAS,or VS mode is selected, the ADCCPL switches are closed, supplying error signals. When the glide

slope beam is captured, the air data mode is disengaged, the ADC CPLswitchesareopened,andtheGS CPLswitchesareclosed,andtheglideslopecommandsignalsareapplied.

Theglideslopedisplacementsignalis invertedandlimitedto i6degreesandtheglideslopeintegralsignalis appliedthroughthePITCHHOLDswitchto the integrator.A limiteron theoutputof theintegratorlimitsthissignalto +20degreesup ancl-5degreesdownwhilein theglideslopemode. Theglideslopedisplacementandintegralsignalsarecombinedandthensummedwiththeverticalgyrosignal.

Ifthesumof theglideslopecommandsandtheverticalgyrois notzero,an errorsignalis appliedto theservomotor,followingthesamepathas describedfortheairdatamode. The servowilldrivetheelevatorcontroltabuntiltheairplaneis in thecenterof theglideslopebeam.

AutopilotandManualPitchTrimSystem.Themanualelectricandautopilotpitchtrimsystemsbothutilizethe sametrimservo. Theaircraftinterfaceprovidestheswitchingcontrolto determinewhichoperationalmodeis beingutilized.Themanualelectrictrimis theprimaryor masteroperationalmode. Theautopilottrimis utilizedif theautopilotis engagedandthemanualelectrictrimswitchisnotbeingoperated.Eitherof theoperationalmodesdrivestheelevatortrimsurfaceto reducetheloadon theelevator.

(a) ManualElectricTrimSystem. Themanualelectrictrimisoperatedby meansof a switchon eitherthepilot’sor thecopilot’scontrolwheel. In orderto activatethetrimservo,theswitchmustbe activated.Operationof themanualelectrictrimswitchwillcausethepitchandrollaxisof theautopilotto disengageby interruptingtheautopilotengagevoltage.Thetrimservoclutchis routedthroughrelaycontacts,in theinterface,whichare interruptedby pressingtheAP disconnectbutton.Thisfeatureis providedto allowdecouplingof thetrimservodrivein caseof a trimrunaway.

(b) AutopilotTrimSystem.Theautopilottrimsystemcontrolstheaircraftinstalledelectrictrimservomotor. Thetrimrateisa functionof sustainedelevatorservoforcesabovea giventhreshold.

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Honeywell WiW””c’CITATION n/V

I4. c. (lo)

1

1 (11)

Trimis requiredwhentheelevatorservois requiredto holdasustainedtorqueholdingthesurfaceoffset. Movingthetrimtabremovesthisoffset.Theelevatorservoamplifieroutputvoltageis fedto thetrimup-downsensors.Servomotorcurrentis fedto thetrimthresholdsensor.Whentheairplanerequirestrimwhilethe autopilotis engaged,eitherthedown-trimsensoror theup-trimsensor,dependingon directionof trimrequired,sensesthedirectionfromthe amplifieroutputandproducesa commandsignalforup or downl-rim.Theholdingforce(motortorque)at whichtrimoccursisdetectedby thetrimthresholdsensor.Thissensordetectsmotorcurrent,whichis proportionalto torque.The servotorquemustbe presentfor1 second(up)or 2.5seconds(down)beforethe startof trimming. Thisis establishedby theTimeDelaycircuit.Thedetectingandthresholdsignalsare“AND”anddrivetherelaywhichallowsthepulseoutputto drivethetrimmotor. Thepulsewidthmodulatorsuppliesa pulsetrain,thepulsedurationbeinga functionof airspeed,whichcontrolsthespeedof thetrimtab. Thetrimservodrivemotorw~lldriveto changetrimtabpositionuntilthetrimsensordoesnotsensea trim requirementandtheholdingforceis r[?movedfromthe servo.

FlapCompensation.Deploymentor detractingof the flaps(CitationII)or advancingor retardingthethrottles(CitationV)requiresaddedtrimresponseto limitairplane“ballooning”atdeployment.Whenthethrottlesareadvancedor retarded,a flap-upor flap-downsignalenterstheautopilotcomputerat 1OJ1B-46andstartsthe flapsinmotiontimer. Theoutputof thetimeris theflap/throttlecompensationsignal.Thissignalis appliedto theupanddowntrimsensor,thusbypassingthenormaltrimdelayin onedirection.

TorqueSwitching.(SeeFigure219or 219.1.) The pitchaxistorqueswitchingoperatesthesameas therollaxistorqueswitchingdiscussedin paragraph4.B.(7).

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Honeywell

4. D. YawAxis(SeeFigure218,sheets


5 and 6.)

Theyaw axisof theautopilotreceivesheadinginformationfromthedirectionalgyro.

(1) YawAxisSynchronization.Theyaw axisof theautopilotissynchronizedpriorto engagement.Beforetheyawdampermodeisengaged,allheadingratesignalsareblockedby theYD ENGAGEswitch,whichgroundstheoutputof theheadingratewashoutamplifier.Theservoamplifierandservodrivemakeup theservopositionservoloop. A signalat theyawservosumis amplifiedbythe servoamplifieranddrivesthetorquemotorto commanda surfaceposition.Thepositionfeedbacksynchrofeedsbacka 400-Hzsignalthatisdemodulatedandopposestheerrorsignal.Whenthe surfaceis at the position commanded, the input to the servo amplifier willbe at a null. A rate damping signal is fedbackas a dampingsignalto stabilizetheservoloop.

Priorto engagementof theautopilot,theservodrive clutch is notengaged to the central surface; thus, the servoloopfollowsUp on

the inputcommandsynchronizingto zeromotorrotation.Atengagement,theservois at a nullpositioncorrespondingto theinputcommand.The servoamplifierincludesa torquelimiterandmonitor.Thetorquelimiterlimitsthemaximumcurrentsuppliedtothemotor,andthus,limitsthemaximumtorqueoutputof themotor,sincemotortorqueis proportionalto motorcurrent.Themonitordisengagestheautopilotandyaw damperifthetorquelimiterfails,preventinga failurewhichwouldresultinno torquelimiting.

Duringthe synchronizationmodeanduntiltheheading-holdmodeisengaged,theheadingsynchronizeris inthefollow-uporsynchronizationmode. Thisheadingsynchronizeris an electronicunit,not a mechanicaldevice. In orderto achieveelectronicheadingsynchronizationandelectronicyawratecircuitoperation,a3-wire-to-2-wireconvertercircuitis employedin theyaw axisoftheautopilot.Three-wireinformationfromthedirectionalgyroisappliedto SW1andSW2andto the logicswitchingcircuitsthatactuallyperformthe3-wire-to-2-wireconversionby openingandclosingelectronicswitches.

ThedirectionalgyroX andY informationis appliedto SW1andSW2.One of theseswitcheswillalwaysbe closed,andat timesbothareclosed.The switchesareclosedwhentheirwaveformvoltageis zeroandopenwhenthewaveformis at 5 volts. The signalfromSW1andSW2 isdemodulatedandthenappliedto thelinevoltagecompensationcircuit.Anyerrorsignalsinducedby voltagechangeson the115-voltsac linewillbe eliminatedat thispoint. A signalrepresentingdynamicairplaneheadingis summedwitha signalfromthe integratorof theheadingsynchronizer.Ifthesesignalsarenotequal,theresultanterrorsignalis invertedandappliedto theintegratorthroughtheHDGHOLDswitch.The integratorwillbedrivenuntilitsoutputis equalto theairplaneheading.

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Honeywell WJRAN’ECITATION V

4. D. (2) HeadingHold. If the autopilot is engaged and the airplane is

flying wings-level with no other modesselected,theheading-holdmodeis engaged.TheHDGHOLDswitch into the heading synchronizeropens. If theairplanechangesheading,an errorsignalisdeveloped.It is invertedandappliedthroughtheNORMor INVswitchto providea headingerrorsignalto the rollaxiscircuitsto returntheairplaneto thedesiredheading.Whentheheading-holdmodeis engaged,a logicinputto the3-wire-to-2-wireconverterlocksup theconverterto maintainexistinglogicoutputs.Thislockup is necessaryto preservetheheading-holdreferenceinformation.

(3) YawDamperOperation.Thedynamicheadinginformationfromthe linevoltagecompensationamplifieris appliedto theheadingratetakercircuitandpassedthroughtheNORMor INVswitches.The ratesignalis amplifiedandthenappliedto thecrossoverholdcircuit.SwitchRT1 is closedat alltimesexceptwhenthe slopeof thedynamicheadingchangesfrompositiveto negativeor negativetopositive.At thesetimes,theratesignalwouldbe causedby theswitchingcircuitsandnotairplaneinputs.Thistransientsignalis blockedfromenteringtheheadingratewashoutcircuit.by openingswitchRT1fora 100-millisecondperiodduringthe switchingtransition.Duringthisperiod,thecapacitorin thecrossoverholdcircuitmaintainsthelastexistingsignalrateof thedynamicheadingsignal.

The crossoverholdcircuitoutputis appliedto theheadingratewashoutcircuit.Thisoutputsignalrepresentsthechangesof~amic headingrate. Whentheyawdampermodeis engaged,the~ENGswitchwillbe open,removingthegroundfromtheheadingratewashoutcircuitoutput.Thissignalwillbe appliedto theyawservosumto drivetherudderservo. The servoamplifieroutputislimitedby theelectronictorquelimiter.In theeventof a failureof thetorquelimiter,themonitorcircuitwoulddisengagetheautopilotwhenservotorqueexceededa predeterminedlevel. Theservodriveclutchis engagedso thattherudderis drivento dampoutthe changingdynamicheadingratesignals.If theairplanerollrateexceeds7 degreespersecondor if theairplanebankangleexceeds45 degrees,theheadingratesignalis removedby groundingtheoutputof theheadingratewashoutcircuit.Whentheserateandbankanglesignalsarereducedbelow7 degreesper secondandthebankangleis lessthan45 degrees,theswitchopens,removingthegroundandrestoringthecommandsignal.

The headingratesignalfromtheheadingratewashoutcircuitisgainswitchedby theMID-Qswitchto maintainuniformairplaneresponseacrosstheairspeedrangeof theairplane.

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Honeywell ti~v~~’”c’CITATION n/V

COPILOTS TCS SW

T

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INTERNAL GND DISENGAGES APFOR THE FOLLOWINGINVALID CONDITIONS:

. POWER SUPPLY ( 15 AND 5 VDC) 1 I

. HIGH TOROUE CURRENT

. AP TEST (FAULT ALL MONITORS)

. ACCELERATION> 1.@+<O @

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Autopi1et/YawDamperEngageInterlockDiagramforCitationV

Figure217(Sheet1 of 2) 22-14-00Page271/272‘Ma~25/90

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Honeywell WUFANCECITATION 11~

28 VDC AP PWR —

rPC.= AT —-

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11

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RZ-220 ROLL RATEMONITOR RELAY K1IS SHOWN IN THENORMAL ENERGIZEDPOSITION THE CONDITIONSTO THE OR GATE CAUSETHE RELAY TO DE-ENERGIZEAND THE AUTOPILOT TODISENGAGE.

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Figure217(Sheet2) 22-1 4“00Page273/274

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Honeywell WW!ANCECITATION n/V

COPILOT S TCS SW

T

PILOT’S AP TRIM 28 VOC TOAP/TRIM CB

,8vDc_n~DISCONNECTS ELEc TRIMsw

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Autopilot/YawDamperEngageInterlockDiagramforCitationII

22”14“00Paae274.1/274.2

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AD21745

Ma~25/90Use or disclosure of Information on Ihm page IS subject to Ihe restrictions on the Mle page of this docume t.

Honeywell IN!E!ANCECITATIONV

HDG ERRDRFllLLM YAWAXIS [SW 5)

7

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AD 187LM@

AutopilotComputerSignalFlowDiaqram

Figure218 (Sh~et1 of 6) 22-14-00Page275/276

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Honeywell MWRAN’ECITATIONV

——— .——~LERON SERVO DRtiVE AND BRACKET

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NOTE ALL SWITCHES ARE SHOWN IN OPEN POSITION.LABELEO CONDITION CLOSES SWITCH.

AO.1S700 2 RI

22-14-00Page277/278

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Honeywell lNUFANcECITATIONV

r————.APCONTROLLER7

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10J1A+15 VDCAPTEST INPUT ___l_<49< *

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Honeywell W%i’’’”c’CITATION n/V

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TorqueSwitchingSignalFlowDiagramforCitationII

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22=14-00Paqe288May-25/90

Use or disclosure of information on this page IS subject to the restrictions on the tttle page of thm dc cument.

Honeywell WURAN’ECITATION n/V

5. C-14DComDassSystemFunctionalDescription(Fiaure220)

Basicpowerforthesystemis the28 voltsdc inputat 6J1-Cof theC-14DDirectionalGyro. Thisprovidesinternalpowerforthegyroanda 26 voltsac poweroutputforthefluxvalveandCS-412.

Thefluxvalvesensesthehorizontalcomponentof theearth’smagneticfield.Usingthe 26 voltsac referencesignal,it providesan outputsignalthatrepresentsaircraftheadingin theearth’smagneticfield. Thissignalwillprovidea commandto keeptherotorof thegyroalignedto magneticnorthintheslavedmode.

TheCS-412DualRemoteCompensatorcompensatesthefluxvalveforsingle-cycle(hard-ironeffects)by biasingthefluxvalvecoilswitha lowleveldcvoltage.Theprocedureforadjustingthislevelof compensationisdiscussedin Section8. Two independentcompasssystemscanbe compensatedby theCS-412.

Intheslavedmodeof operation,thedirectionalgyrois slavedto a positionrelativeto themagneticheadingreferenceas suppliedby thefluxvalveandtheCS-412.

Slavingof thedirectionalgyrois accomplishedby supplyingcurrentflowthroughprecessioncoilsaffectingthesensitiveaxisof thegyro. TheMANUALSYNCHRONIZATIONswitchis usedto engagefastslavingof thedirectionalgyro. Whenfastslavingis engaged,theslavingrateisincreasedfromapproximately3.5degreesperminuteto approximately40degreesperminute. Onceengaged,fastslavingcontinuesuntilthecompasscardof the EHSIor HSI indicateswithin4 degreesof actualheading,atwhichtimethenormalslavingrateis assumed.

In thefreeor manualmodeof operation,magneticinformationfromthefluxvalveandCS-412is disabledin thegyroandno slavingis performed.Thedirectionalgyroprovidescompassinformationas a product0$ thepositionoftheaircraftwithreferenceto thepositionof theunslavedgyro. As noslavingis performed,thedisplayedheadinginformationis subjectto erroras theresultof freegyrodrift.

Duringoperationof thedirectionalgyro,anyof thefollowingconditionswillcausea lossof theheadingvalidsignalsuppliedto theSG-605SymbolGenerator:

(a) Lowvoltageto thedirectionalgyropowersupply

(b) Improperwheelspeedof thespinmotor

(c) Fastsync(manualsynchronization)

22-14-00Paqe288.1/288.2

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Honeywell WWANCECITATION n/V

C-14D DIRECTIONAL GYRO,

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Pilot’sC-14DCompassSystemSignalF1ow Diagram

Figure22022-1 4“00

Paae289/290‘May25/90

Use or disclosure Of Information On this page E subject 10 the restrictions on the Mle page of thm document.

Honeywell MPJKYANC’CITATION V

TheSG-605receivesthree-wirecompassinformationfromtheC-14Dandusesitto movethe EHSIheadingdialto theproperlocation.

Synchronizationbetweenthefluxvalveandtheactualheadingof the aircraftis indicatedby thecompasssynchronizationannunciatorof the EHSI. Whenthe+ is in viewon theannunciator,theheadingdialis rotatingin thecounterclockwisedirection(actualheadinggreaterthanindicated).Whenthe

is in view,theheadingdialis rotatingin theclockwisedirection~actualheadinglessthanindicated).Whensynchronized,the annunciatorslowlyoscillatesbetweenthe+ andthe..

6. EDZ-605EFISandOptionalMDZ-605MFDSystem

A. AttitudePortInterconnects(SeeFigure221.)

Theconfigurationshownin Figure221consistsof oneVG-14AVerticalGyro. It provides3-wirepitchandrollattitudeto theSG-605forusein drivingthe EADIattitudesphere.If theattitudevalidappliedto65J1A-85is lost,a redATT FAILis annunciatedon the EADI. Pin65J1B-92isgroundedto preventAFCS?frombeingdisplayedon the EADI.Sincethereis onlyoneattitudesource,theATT sourceandtoggleprogrammingpinsarenotapplicable.The attitudesignalsarealsoconnectedto theoptionalMG-605forusewhentheMG-605is backingup afailedSG-605SymbolGenerator.

B. HeadingPortInterconnects

TheconfigurationshowninGyrosources.Twoheading65J1B-24and-25open.

(SeeFigure222.)

Figure222consistsof twoC-14DDirectionalsourcesareindicatedby leavingprogrampins

Thedefinitionof theheadinginputisdeterminedby programpin65J1B-22(HDGport1) and65J1B-28(HDGport2). Whenpins-22or -28areopen,theheadingsourceis considereda compassandwhenthepinsaregrounded,theheadingsourceis a magneticor trueNorthreferencedsystem. Programpin65J1B-23or 29 controlsthefree/slaveormagnetic/truefunctionof theheadinginput.

Programpins65J1B-26and-27aregroundedor opento controlthetogglingsequenceof theexternalHDGREVswitch.Withpins-26and -27openthetogglingsequenceis as specifiedin Table201.

22-14-00Paqe291Mar”15/89


Honeywell M!JRANCECITATION V

HDGSourceHDGREV Using

SwitchPosition HDGREVSwitch

InitialPower Pilot’sDG1stPress Copilot’sDG2ndPress Sameas initialpower

HDGREVSwitchTogglingSequenceTable201

Headingphasingforthepilot’sport2 is identifiedby the openorgroundconditionon 65J1B-30.Whenthispin is open,thedemodacreferenceexcitationto headingport2 sourceis fromthepilot’sac bus.A groundon pin65J1B-30wouldidentifythattheheadingport2 sourceisbeingexcitedby thecopilot’sac bus.

Headinginformationis appliedto the specificSG-605headingports. Thetogglesequenceof theHDGREVswitchdetermineswhichattitudeportissupplyingtheheadingindicationson the EHSI. Theheadingsourceisannunciatedon theEHSIinwhiteif thepilotandcopilotare usingdifferentsourcesandin amberif the samesourceis used. Iftheheadingvalidappliedto theSG-605is lost,a redHDGFAILisannunciatedon theEHSI.

Thecopilot’sC-14DDirectionalGyronormallydrivestheheadingdialontheRD-450HSI. WhenHDGREV is selected,a 3-wireoutputfromtheRD-450HSIthatis appliedto HDGport2 of theSG-605is usedto drivetheheadingdialon the EHSI.

Thepilot’sC-14Dheadingsignalsarealsoconnectedto the optionalMG-605forusewhentheMG-605is backingup a failedSG-605SymbolGenerator.

22-14-00Paqe292Mar-15/89

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Honeywell W!!FANC’CITATION n/V

6. C. Short Range Navigation (SRN) Port Interconnects (See Figure 223.)

Theconfigurationshownin Figure223consistsof analogADF anddiqitalDMEandNAV sourcesforthepilot’ssideandanalogADF-andNAVsou~cesandARINC568DMEsourceforthecopilot’sside. Programpin65J1B-32openand65J1B-33isgroundedwhichindicatesthattheSRN1 sourceisdigitalRS-422. Programpins65J1B-9and-68arebothopenwhichindicatesthattheSRN2 sourcesareanalogandARINC568. Programpin65J1B-36identifieswhetherthetogglingsequenceof theNAV (VOR/LOC)buttonon theDC-811includesMLS. Thetogglingsequenceis as follows

Pin65J1B-36 SwitchSeauence

Open VOR/LOCto CS VOR/LOCthenrepeatGround VOR/LOCto MLSto CS VOR/LOCto CS MLSthenrepeat

s

Programpin65J1B-10isgroundedwhichindicatesthe systemis usingdualADFreceivers.Also,pin65J1A-103isgroundedto allocatecrosssideSRNandADF sensors.

Thepilot’sADF inputappliedto 65J2A-55through58 canbe in the3-wireX, Y, andZ or 4-wiresine/cosineconfiguration.When3-wireinformationis applied,65J1A-1OOis open;if 4-wireis applied,pin100isgrounded.TheADF validis appliedto 65J1A-82.

Crosssidecopilot’sADF bearingis appliedto 65J2A-34through37 inthe4-wiresine/cosineconfigurationas indicatedby 65J1B-81grounded.

Thebearinginputto 65J2A-51through-54canbe in the3-wireor 4-wireconfiguration.Leavingpin65J1A-99openidentifies3-wire,andgroundingpin99 identifiesa 4-wiresine/cosineinput. Thebearinginputis availablein caseor cardreference.Applyinga groundto pin65J1B-31assumestheVORbearingsignalis casereferenced(i.e.,aircraftheadinghasalreadybeensubtractedfromtheVOROMNIbearing,thusmakingit a relativebearing).Leavingpin31 openassumestheVORbearingsignalto be cardreferenced(i.e.,aircraftheadinghasnotbeensubtractedfromtheVOROMNIbearing,thusmakingit an OMNIor absolutebearing).

A groundis appliedto 65J1B-34whentheDME is tunedto thesamefrequencyas theselectedNAV. At allothertimesthisinputshouldbeleftopen.

Thepilot’ssideusesRS-422NAVandDMEdataandthecopilot’ssideusesARINC568DMEandanalogNAVdeviationdata. Selectionbetweenthepilot’sor copilot’ssensorsis by theNAVbuttonon theDC-811DisplayController.

Allsensoroutputsarealsoconnectedto theoptionalMG-605forusewhentheMG-605is backingup a failedSG-605SymbolGenerator.

22-1 4=00Paqe293May-25/90

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Honeywell WIY””c’CITATION V

6. D. LongRangeNavigation(LRN)PortInterconnects(SeeFigure224.)

Theconfigurationshownin Figure224consistsof oneARINC429 LRNsource. Programpins65J1B-66and -67identifythetypeof inputappliedto LRNport1. Withpin -66openand-67grounded,a highspeedARINC429 inputis indicated.Programpins65J1B-62through-65controltheLRNport1 sourcenameas displayedon theEHSI. TheconditionsshowninFigure224indicateFMS.

Programpins65J1B-13and -14determinethegroundspeeddatasourcewhenan LRN is notselectedfordisplay.Withpin -13groundedand -14open,theVOR/DMEwouldbe thesourceused.

Programpins65JlB/C65JlB-70and-71identifythetogglingsequenceof theDc-811LRNpushbutton.Withbothpinsopen,therewouldbe no togglingsequencesinceonlyoneLRNsourceis used.

Thegroundingof programmingpin65J1B-6disablestheautomatictransitionfromtheselectedLRNto theSRN.

The LRNoutputis alsoconnectedto theoptionalMG-605forusewhentheMG-605is backingup a failedSG-605SymbolGenerator.

E. RadioAltimeterPortInterconnects(SeeFigure225.)

TheSG-605symbolGeneratorhastwo radioaltimeterports. If a singleradioaltimeteris installed,as shownin Figure225,it is connectedtotheprimaryport. Thedisplayedradioaltitudeinformationcomesfromtheprimaryinput. The secondaryinputis onlyusedforradioaltitudecomparisonmonitoring.

Programpin65J1B-85is open,whichindicatesa singleradioaltimeterisinstalled.

Thesymbolgeneratorcanacceptseveraltypesof radioaltimetersignals.Theformatis programmedusingprogrampins65J1B-4(IDO)and65J1B-5(ID1)as shownin Table202.

RadioALTProg.Pins RadioAltimeter

JIB-4(IDO) JIB-5(ID1) Type

Open Open HoneywellAA-300Ground Open CollinsALT-50Open Ground ARINC552Ground Ground CollinsALT-55

RadioAltimeterIdentificationTable202

22-14-00Paqe294Mar-15/89

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Honeywell MI!XYANC’CITATION V

TheTESTOUTpin65J2B-76is an open/grounddiscreteoutputthatgoestogroundwhenthe EFIStestmodeis initiated.Thegroundoutputisconnectedto the primaryradioaltimeterso thatradioaltitudetestisautomaticallyselectedwheninthe EFIStestmode.

TheDH OUT pin 65J2B-75 is an open/ground discrete output that goesactive (ground) whenever radio altitude is less than the decision heightvalue displayed on the EADI. Allradioaltitudesignalsarealsoconnectedto theoptionalMG-605forusein theSG backupmode.

6. F. WeatherRadarPortInterconnects(SeeFigure225.)

Theweatherradarinformationto theSG-605SymbolGeneratoristransmittedon twoseparatedigitaldatabuses. One highspeedbus (MXVIDEO)is usedto transmitthepartiallyscanconvertedweatherradarvideo. A secondlowspeedbus (WXCONTROLDATA)is usedto transmittheradarstatusandcontrolinformation.

Pins65J1B-96and97 areonlyusedwitha P-800weatherradarsystem.OthersystemssendthisinformationovertheWX controlbus.

Theweatherradarsignalsarealsoroutedto theoptionalMG-605forusein theSG backupmode.

G. Rateof TurnPortInterconnects(SeeFigure225.)

Therateof turnsignalis providedby a rategyroandtherateof turnis displayedwhenexpandedlocalizeris notdisplayedon theEADI. Ifpin65J1A-104is grounded,therateof turndisplayis disabled.Therateof turnsignalsarealsoroutedto theoptionalMG-605foruseintheSG backupmode.

H. MicrowaveLandingSystem(MLS) PortInterconnects(SeeFigure225.)

LowspeedARINC429MLSdataisprovidedby theML-850MLS receiver.Programpin65J1B-11identifiesthenumberof MLSreceiversinstalledintheaircraft.The pinisopenforsingleinstallationsandgroundedfordualinstallations.

Programpin65J1B-36whengroundedidentifiesthatthetogglingsequenceof theNAV (VOR/LOC)buttonon theDC-811includesMLS. Thetogglingsequenceis VOR/LOCto MLSto CS VOR/LOCto CS MLSthenrepeat.

TheNAVSELECTEDpin65J2B-82is a 28 V de/Opendiscreteoutputwhichgoesto 28 V wheneitherMLS isthe selectednavigationsource. It isusedto activatea relaywhichswitchestheDMEreceivertuninginputfromtheSRNcontrolheadto theMLScontrolhead,allowingtheMLStotunetheDME.

TheMLSsignalis alsoroutedto theoptionalMG-605foruse in theSGbackupmode.

22-14-00Paqe295Mar-15/89

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Honeywell WE”’””CITATION n/V

6. I. Miscellaneous Programming Functions

Thefollowingdefinesthemiscellaneousprogrampinsas shownin Figures221through224.

(1) SG Left/Right(65J1A-97)

Thispinidentifieswhichsideof thecockpittheserves. If thepilotsitson theleftside,thison thepilot’sSG.

(2) SC-DC/DC-811(65J1A-98)

symbolqeneratorp~n would be open

Thispinidentifieswhetherthe systemis usingan SC-800andDC-800 controlleror a DC-811DisplayController.ThispinwouldbegroundedwhenusingtheDC-811.

(3) ASCBDual/Single(65J1A-101)

Thispinidentifiesthenumberof systemAvionicsStandardCommunicationBuses. Thispin is openas a singleASCBsystemisnotdefined.

(4) EFISDual/Single(65J1A-102)

ThispinprogramstheSG-605SymbolGeneratorforoperationin adualor singleinstallation.Thispin is groundedfora singlesystem.

(5) Citation11/V(65J1B-82)

The standardgenericSG-605SymbolGeneratorwas PartNo.7011672-605. Whengrounded,thispin identifiestheCitation11/VSG-605configurationthatis PartNo. 7011672-606.

FlightDirectorSignals(SeeFigure226.)

The FZ-500FlightDirectorComputerinputsareroutedfromtheSG-605.If theSG-605SymbolGeneratorfails,it canbe replacedby identicalbackupsignalsfromtheMG-605MFD SymbolGenerator.TheseMG-605signalsarerelayswitchedthroughthefailedSG-605.

Figure226doesnotshowthe inputpinsto theSG-605or MG-605.Theapplicablesignalinputis shownin Figures221through224. Forexample,theglideslopedeviationsignalis inputtedat 65J2A-67and-68and125J3A-43and -44on Figure223. Theglideslopedeviationisoutputat 65J2B-99to theFZ-500pin7J1B-16in Figure223. DuringtheSGbackupmode,theglideslopedeviationsignaloutputtedat 125J2B-11wouldbe switchedthroughthefailedSG-605to the FZ-500pin7J1B-16.

22-14-00Pacle296May-25/90

Use or disclosure of information on this page is subject to the restrictions on the title page of this dccument.

Honeywell WMEANC’CITATION V

6. K. EFISBackupMode

Selectionof EFISbackupby theMFD is accomplishedby therotaryMODselector switch on the MC-800 MFD Controller. Normal MFD functions areavailable in theMFD position,andEFISbackupmodes are. obtained by

selecting the HSI or SG positions.

● HSI- Selectionof thispositionwill result in an HSIdisplayon theMFD. Compositionof theHSIwillbe determinedby ttleEFISDC-811DisplayController.

. SG - Selectionof thispositionwillresultin replacementof theSG-605SymbolGeneratorby theMG-605MFDSymbolGeneratorfortheEFISdisplays.InthiscasetheMFDCRTwill be blarlked. Composition

of the EFIS displays willbe determinedby theDC-811DisplayController.

22-14-00Page297/298

Mar15/89Use or disclosure of information on this page is subject to the restrictions on the title pag( of this document.

Honeywell l&EtANcECITATION n/V

65J

4

5

9

A

5

6

7

18

19

?0

B

1

12

151617

181920

.—— — —VG-14A VERTICAL GYRO

ATT VALID +28v

(x)

(Y)

}

ROLL ATT

(z)

(x)

(Y)

}

PITCH ATT

(z)

‘7II

II

●

DISPLAY DATATO PILOT’S EADI

a

ATT1WRAPAROUNDlJ1

+65J1B

[3

1516

NC17

((x)PITCH ATT 1 (Y)

(z]

(

(x]ROLL ATT 1 W’

(z

IDO

)

ATTSOURCE ATTPORT1ID1

IDO

)ATTTOGGLE

ID1

CITATION110/1.

—

LF118

82 =JI .—— — —— J

(+))DC.811DATA(-)

SGLEFT/RIGHTSC-DCIDC-811

ASCBDUAUSINGLE AIT PORT 2

EFISDUAL/SINGLE

r ———MG-LM= 1

SYMBOL GENERATORI

125J2B

+

125J3Ar

(x(Y

(z

(x(Y

(z

ITTVALID,

IPITCH ATT 2

ROLL ATT 2

[x)1 I(Y) PITCHATT

(z) I

(x)

}

ROLLATTI

(Y)(z) I

r .——MG=5 =DSYMBOL GENERATOR

~=d

125J3A

I (+ 23

DC-811 DATA _ 24

I)

—-JATT2 VALI[

IL —. ——— —— --

———— —— -J1- ———— —

NOTE:INTERFACEBETWEENTHESG-605ANDMG-605IS BYTHEASCB.

AD.18703.R1

SG-605andOptionalMG-605AttitudePortInterconnects

Figure221 22”14-00Page298.1/298.2

May25/90Useordisclosureofinformationon this page is subject to the restrictionson the htle page of this document.

Honeywell W!M5ANCECITATION n/V

r ——————————~65JSG-B05 SYMBOLGENERATOR

,—— — ——PILOT’SC-14DDG 128 V13C HDG VALID I

)(+)“DG(–)SYNC I

I

I(x)1

HDG(Y) SYNCI-IRO I(z) NO 1

I

6J

i

Euv

L

M

K

IDISPLAY DATA TOPILOTS EtiSl

Q“DGISYNC’‘~‘I-J

‘ 65J65Jl B

$

24

25

lB 2A

7

1=

21

>2

:!3

23 (NOTE 2)

22 NC

/

HC!GIDO HDti PORT 1

ID1 SOURCE

100 HOG {

. .,Xj

HDG 1 (Y)

(z)

—NC

I ID1 ~ TOGGLE

CITATION WVHOG 1 FREE/SLAVEOR MAG/lRUE

~C-Sll DISPLAYCONTROLLER——— ——.

HOG 1 DEF

I(-

DC/SG BUS +

I

I HOG REV

I

I (-DC/MG BUS +

L ——— —..

OAG-SQ5MFDSYMBOLGENERATOR IHDG1 VALID IHOG 2 VALID

I

(+)

(-))DC-811 DATA 125J2B

<

34

5s

I 65J

1A

92

B

!s

‘8

10

HDG 2 VALID

J=15

$

HDG REV

36

37 )

r———— —

MG-S05 MFD

I

SYMBOLGENERATOR

l-l=J

125J3A

(

+ 23DC-811 DATA _ 24

L)

—————

3-NC 97

es

=

NC 101

102

=

I

[

(+)HOG2SYNC

(-)

(x)

HDG 2 (Y)

(z)

126J3A

a

7

8

9

13

S’ LEFT/RIGHT

x)

}

IY) HOG1

z) I

+

-)HDG1 SYNC I

-——— —— J

SC-DCIDC-S1l

r22

23

(NOTE 2)

NC

=

HDGPORT 2

ASCB DUAL/SINGLEHOG 2 FREE/SLAVE

EFIS DUAL/SINGLE

I OR MAG/TRUE

HOG 2 DEF

HDG 2 PHASE (PR1/SEC)

1- ——— ——— ——— —!

——— ———COPILOT’SC-14DDG 1[ COPILOT’SRD-450HSI I C2J2

28 VDC HDG VALID

)

I+ HDG— SYNC

I

I u=HDGVALID(IN) Y

IHDG SYNC

(

+G— H~

I

HDGvALID(OUT) X

II

I

I

I }

(x) l+fJG

(Y) SYNCHRO

(z) NO 1

I1 HDGOUTPUT~l :=

-—— ——— dy

NOTES.

I l.(x) s

L ——— —. -P 1. INTERFACE BETWEEN THE SG-605AND MG-6051SBYTHEASCB

2 THIS PIN TELLS THE SG.605WHETHER THE COMPASS ISINTHE FREE (OPEN) OR SLAVED (GNO) MODE. CONNECT TOSEPARATE POLE OF THE WAG (FREE/SIAVE) SWITCH

AD 1870&R1

SG-605andOptionalMG-605HeadingPortInterconnects

Figure22222-1 4“00Paae298.3/298.4

May”25/90useordwclosure01Inlormntlononthispage IS subject to the restrictionson the title page of this document,

Honeywell W!JFANCEr——— ———

1

CITATION 11~OC.S1l OISPLAY CONTROLLER lISJ1

A

125J.—— —.k~5 SYMBOL 1;ENERATOR

.—— — ———.MG.SOS UFO SYMBOLGENERATOR

1A

1!

t

<

5

5

5

6

6

6

6

6

6

c

E

6

I

IIII

I

I

IIIIIII

I

III

IIIIII

I

I

I

III

I

I

I

I

I

I

E

t

f

u

?,

&

o

2

e5

2

1:

5c1

1:

>

&

7

8

,7

18

3!

02

X

)2

cl

73

!3$

7;

7.

81

3A

76

77

18

79

37

36

39

40

86

87

22

e9

w

91

33

34

35

36

41

42

43

44

48

4:

54

5

b DISP18YDATATOPILO1S EAOIANDFHSII GCSG Bus

+ :~{- l=)1 NC 4

) SCSGBuS

G LEFTRIGHTCDCDC 811 I

II

I

I

I

I

I

I

i

I

I

I

I

I

I

I

I

I

I

IIIIIIIIIIIIj

i K’ql .~“c’MG’”s(~: )

1-—————.2 RS 422

NAV DATA

SCBDUALSINGLEFIS OUALSINGLEIIATION11VRN TO SRN TRANSITIONON OFFROSSSIDE SENSORDISABLE

Of SINGLEDUAL~iA&RmEr– – ,2SJ3A

I

I~ld“’’o’”{: :

:}Rs 422DME DATARN 2 BRG CARO CASE

)

N SRN 1), SOURCE

1-——— ——— -r RN TCGGLE

}M SF4N2)1 SOURCE

/;%;fATA]SRN11s 4Z2DME DATA

OF I VALl0

SIN ~

X SIN

1

V COM ADF 1

z cos BRG

COM

ARINC 1 VALID

l–

[

———

:} 1OATA

:)SYNC g% JME

:}C’K

DME 2 ~D

x SIN

1Y COM SRN z

z cos sRG

CON

:)

INNERMARKER

cm)ADF 1 BRGCos

;P COM

(DF I BRG 34 WIRE SEL

,DF 2 BRG 34 WIRE SEL~O&&O=RNZ41S0

——— —

1

C164J1

1 NAV UNIT A B

-1—————gI I

18V DME VALID

:)OATA

:)

ARINC 1SYNC SRN2 OME

:}CLX

I DME DIST VALID +28V I 48

IIIIII

I

I

I

I

-’s’”’”(: :5

~ED’s’’’~{: :

-E’’s’c’K{~ :;TL#4ED 10 NAV GNO 3

H----)ME HOLD,GNDI IN;RN 2 WIG 34 WIRE SE1

i

1 SIN 1

{

SIN

EXl GND

Cos

‘,COM )SRN 2 BRG! Cos

;PfcOM

:)INNER MAF4KER

SRN 2 TTL GNO

SRN 2 vORLW VALID

~)SRN 2 CRS DEV (LGCI

11

37

12

F ‘ :

—--+

+

———

{

—Nc—

—

SRN 2 GS VALID

~}SRN 2 GS OEV9MIDDLE MARKERlhUJEn MARKER x

MIOOLE MARKEI+ a

WTER MARKER 74

:}OUTER MARKER

SRN TOGGLE

CAA RULES

IDO

)SRN SOURCE

101IIIIIII

I

TTL GNLI

2W VORILDC VALID

CRsDEv’Lm’{~28V GIS VALID 7

S14N2 TTL GND

3RN 2 VOR LGC VALID

:)SRN 2 CfIS DEV (LOCI 4=

+,-——: =+--- -

T

-

75

79 :+ - -

SC GCOC 811

SRN WIG 34

ADF BRG34

ADF SINGLE IDUAL

LRN ‘0 SW TRANSITIG+4 ONIOFF

SRN 2 G S VALlD

:}SRN 2 G S OEV

x SIN

1YCOM ADF 2

z cos BRG

COM

ADF 2 VALID

-(qX SIN

1

Y ‘GM ADF 2

z cos BRG

‘GM

((x) 6

ADF 213RG

(Y) 3

(z) 4

ADF VALtO

-—— ——— — J.—— —— ——.I

NOTE

INTERFACE BETWEEN THE SG 6D5AND MG 6D5 IS 8Y THE ASCB

AOIB7C511,

SG-605andOptionalMG-605ShortRangeNavigation(SRN)

PortInterconnectsFigure223 22-1 4“00

Page298.5/298.6May25/90UseordisclosureofInlormallonon this page IS subject to the reslncttons on the title page of this document,

Honeywell W’UR’”c’CITATION H/V

r——— ——— .

DC-611 DISPLAYCONTROLLER——— ——. — ——SG-605 SYMBOLGENERATOR

I

PDISPLAYDATATO PILOTSEHSI

I

I

I

I

I

I ( (+)DC/SG BUS

(-)

(+)(-) )DC-811 DATA

I SG LEFT/RIGHT

SC.DC/DC-811

ASCB DUAUSINGLE

EFIS DUAUSINGLE

I

I 2-98

=

NC 101

Irx

=

J=)36

37

125J3A

)

23

242

DC/MG BUS(

(+]

(-)

L———————Ir———————

MG-605 MFD SYMBOL GENERATOR IIIII

IIIIIIIIIIIIIIIII

II

I

II (DC-811 (+

DATA (-

I J

125J1A

E

83 Nc

84

=

91 NC

92

93

94 =

65JI B

1

13

=

NC — 14

NC(=

70

71

NC — 62

— 63

164

= L 65

NC — 66

167

=

1

6

=

L82

. &

I

I

LRN 1

{

IDOPORTIDENT ID I

IDO

1

GSPDSOURCE

ID1II

III

(IDO

LRN 1 ID1SOURCEIDENT ID2

ID3

)IDO LRN

IDI TOGGLE

[Dl

I

LRN1SOURCE

ID2 IDENT125J2A

1-

66 NCFMS SINGLE/DUAL ID3J

}

IDo LRN1

PORTID1 IDENT

.

(IDO

GSPDSOURCE

ID1

68

P

=

69 NC

I

I89

t-=

sc-Dc/Dc-811 LRN TO SRN TRANSITION ON/OFF

I

II

I

LRN TO SRN TRANSITIONON/OFF CITATION n/V

125J3A

IARINC O

(

(+’

DATA (-:

L

81

r——— ———

I

—

LRN NO. 1

I

7

ARINC 429

(

(+) +

LRN DATA (-)

I

65J2B

4 (+) )ARINC O

[-)DATALRN 1

1- ——— ——— J ——— ——. — — JAD. 187C&R1

SG-605andOptionalMG-605Long Range Navigation (LRN)

Port InterconnectsFigure224

22=14-00Page298.7/298.8

May25/90Use or disclosure of reformation on this page is subpct to the restrictions on the title pag,) of this document,

——. . 1

I%-300 RADIOALTIMETER ~ml

I

-

(-4 mVDC/FT)

I

I 28 VDC RA VALID ~A

TEST T

*

NC —

.—— — ——;G-605SYMBOLGENERATOR1

——— —MG-605 MFD 1

125J6SJ

A

7

8

s

x

N

s{

7(

7

10

Ic

B

5

B

8

n

f

c

SYMBOLGENERATONB

5

4

5

3

3(

x

,,

3’

,

I

)

7

3

-}

Ik

PRIMARYRAD ALT I

‘WiiAc/AITvAllL I

I

I

I

I

I

I

I

IIIIII

I

I

I

IIIIII

q

Nc

}

‘) PRIMARY

L)ALT RAD

RAG AL.T SINGLEID!JAL

PRI RAD ALT VALIDlAD ALT SINGLE/DUAL I—

I P d [EST OUTI

RA TEST OUT

L ——— — -1 )H OUT 1RA TEST IN

}

mRAD ALT TYPE

)1

k

-}

RATE OF TURN

I

I‘c-l

r——. — —

RG-Z04RATEGYRO

}

)0RAD ALT TYPE

31

DH IN

15J1

1=

4

5 +

7

IRATE OF TURN

{

+

I0.667 vDC/DEG/SEC _

NC -1

I 45 i 0.5 VDC VALID +

-}RATE OF TURNzNC

NC

{

iOT VALID

P

DISPLAY

30T ON/OFFDATA TOPILOT’S

t

-}

EADI ANDSECONDARY EHSIRAD ALT

1- ——— —.

r————-WU-650ANTENNAANDRCVRIXMTRUNtT

ROT VALID

59J1

7

+

-}WX VIDEODATA

I

I

I{-+

IVIDEO DATA

I{-

+CONTROL DATA

I Eq=q9

h

m

n

USED FORP 800 ONLY

{

NC

i

ROT ON/OFF

+

-}

WX VIDEODATA

+

}

WX CONTROL_ DATA

WX VALID

II +)WX CONTROL

DATA—L ————- wx TARGET ALERT INAV SELECTED

IMLS SINGLE/DUAL

Ir————ML-850 MLS 1 LRECEIVER 116J1 =

I ARINC 429

(~}

+ 33

I

~

MLS DATA _ z Y~

I

L= (

1- ——— — J

WX DUAIJSINGLE

MLS SINGLE/DUAL

+

-}

ARINC 8DATA+)ARINC 8 I

DATA—

ISRN TOGGLE

I-Jr NAV SELECTED

I.————

AO 18707 RI

———— .— J

II I

SG-605andOptionalMG-605RadioAltitude,Rateof Turn,WeatherRadar,andMicrowaveLandingSystem(MLS)PortInterconnects

Fiqure225 22-14-00Page298.9/298.10

Mar 15/89Useordisclosure01Informationonthispage is subjeci 10 the restrictionson the title page of lhm document.

Honeywell MWEP*NCECITATION ii/V

,,, &2M FDC———

7

— —— ——1

25J1B c’ DISCRETE (NOTE) I 65.1?43 4 1

7

M

K

L9

,24

3

&

8!

64

8i628:9(9

9;

9:

9,

9!

%

.

HOG VALID*

II

I

I

I

{

I

I

I

I

I

I

I-—— — J

II

I

II

1

I

I

I

I

I

I

I

SGBACKUP

LAT STRG VALID

NAV SEL VALID

iKti=–TO EFIS SELECT RELAY(SEE TABLE 501, FIG All]

X 16LAT DEv VALlD

VERT DEV VALID--

l=vERT DEV VALIII

87 +~f.w,,., ,n

66 - 34

26V TK ~89 e 49

28v AP ENGAGEDso * 46

APS VALID91 *

LNAv APP92 * 40

LIME VALiLI

3 INPUTS

ARE

RELAY

SWITCHED

28V TK ~

26V AP ENGAGED

APS VALID

LNAV APP

SAME

SH&JNABOVE

TTL GNO

TTN GND

MIDDLE MARKER (5W

PW MOVED GND- r L“L

.—— — A

r ——, VN-212 165J2P

f-

i5J

1

2

w

9

w

37

19

73

02

01

i1:

I&

)7

m

00

39

u

10

—

?E

9

1(

1

1:

TO/FROM

a

(+) ,,

IIIII (-) ,2 r

———FZ-SOOFDC 1

11B

(+)

LAT DEV

(-)

-7II

-

7

I

SG ‘BACKUP

I TO FROM

((-)

I

I

I

I

1I

I

IIIIIIII

I

A

LAT DEV h- (+) ,MIIIIII

‘-) 62u[

(+ I

LRN LAT DEV

(-

[

(+

VOR LOC DEV

(-

[

(+

GS DEV

[-

[

(+

DME

(-

h VORILOC DEV i- (+) 96

J

II,1II (-) 97u

3GS DEV 4 .-.

.

1(+)

VOR LOC 23EV

(-)

1

6 (+)

GS DEv

7 (-)

INPUTSARE

RELAYSWITCHED

SAMEAS

SHOWNABOVE

-b

-m

+

-—

I NOTE

THE INTERNAL SG SIGNAL IS APPLIED TO THE SG 605

I

AND MG605 AS SHOWN ON FIGuRES 221 THRU 224WHEN THE SG FAILS. THE SIGNAL FROM THE ffiLW5

I

IS RELAY SWITCHED THROUGH THE SG 605

41(+)DME i40 MVIMI

(-)I

———

—

—

SHIELDGND

.——ALI !LIWU H!L————.

F1ightDirectorValidandNavigationSignals

Figure22622=14-00

Page298.11/298.12Ma#25/90Use or dmclosure01 mlormattonon this page is subject to the restr!chons on the htle page of thm docume 1.

Honeywell i!i~;k~’”c’CITATION V

SECTION4GROUNDCHECK

1. General

Thissectionprovidesa simplifiedprocedure(Table301)forcheckingtheSystemforcorrectinstallationandproperoperationof allcomponentsinthesystem.

NOTICE

ProceduresinTable301arebasedonHoneywellEngineeringBulletinTBA.

Shouldanyfailuresari”sewhileperformingthefollowinggroundcheck, refer

to FAULT ISOLATION as required.

2. EquipmentandMaterials

Equipment and materials are listed in Table 301.

3. Procedure

Instructionsforperformingthetestarelistedin Table301,

22-14-00Page301/302

Mar 15/89he or disclosure of information on this page IS subject to the restrictions on the title page of this document.

Honeywell Wi!!RANcECITATION V

Table301To Be Supplied.

GroundCheckProcedureTable301

22-14-00Pac7e303/304“Marl’5/89

Use or disclosure of information on this page IS subjecf to the restrictions on the title pag ? of this document.

Honeywell Mi!i%!ANcECITATION V

SECTION5FAULTISOLATION

1. General

Thissectionprovides faulty component isolation (Table 401’1 as an aid introubleshootingtheSystemshouldanyfailureoccurduring&ROUNUCHECK.

2. Procedure

Table401is to be used to isolate a faulty component of the system. Ifthesystemfailsanyustepof thesimplifiedgroundcheck, Table 401 indicates

themode flow or modelogicdiagramin Section3 thatis associatedwiththeapplicableGROUNDCHECKstepandthesediagramsidentifythecomponentsinvolvedforthatstep. Also,interconnectdiagrams,Section6, canbe usedas aidsin isolatingthefaultycomponent.

A suspectedfaultycomponentcanbe furtherverifiedby usingtheSperrySystemsTroubleshooter/Interface,if available,andperformingtheapplicableComponentProcedureon allunitsexceptEFIS,weatherradar,andradiocomponents.

22-14-00Page401/402

Mar 15/89UseordisclosureofreformationonthispageIS subjecttotherestrictionsonthetitlepageofth!sdocument.

Honeywell WiVRANcECITATION V

Table401To Be Supplied.

FaultIsolationTable401

22-14-00Page403/404‘Mar15/89

Use or disclosure Of information On lhls page IS subpt to !he reslrlcttons on the title page of thw document.

Honeywell lWJWANcECITATION n/V

SECTION6INTERCONNECTS

Thissectionprovidesinterconnectinformation(Table501)fortheSPZ-500CSystemas an aidin troubleshootingtheSystemshouldanyfailureoccurduringGROUNDCHECK.

NOTICE

ProceduresinTable501arebasedonHoneywellEngineeringBulletinEB7013894,RevisionD.

22-14-00Page501/502

May25/90Use or disclosure of reformation on thw page IS sub!ect to the restnctrons on the title page of Ih}s document.

1

2

3

Honeywell

Introduction

Thistablecontainssystemcomponent


interconnect information and lighting,

power,interlock,and-switchingschematics.

List of Tables Incorporated in thisTable:

Table &

4-1 WeatherRadarCable 508

4-2 MultiplexDataBus 508

List of Figures Incorporated in thisTable:

FigureNo.

4-1

4-2

4-3

4-4

4-5

4-6

4-7

4-8

4-9

4-1o

4-11

4-12

4-13

4-14

4-15

4-16

4-17

Pilot’s/Copilot’s28 V dc Bus

Edge Lighting

AC PowerRequirements

AOA/SpeedCommand

RadioAltimeterInterface

Air DatacommandBlockDiagram

WeightOn WheelsSwitch

AltitudeAlertHorn

PRIMUS@11 RadioSystemBusArchitecture

AudioSystemBus

Engage/Trim Interlock

Heading Switching

Autopilot Engage Select and VG Valid Switching

Aneroid Switch Wiring

Flap Transition Switch Thrust Compensation

TorqueWarnAnnunciator

VNAVDisable

InterconnectTable

Paqe

598.46

598.48

598.49

598.52

598.53

598.54

598.55

598.56

598.57

598.58

598.59

598,60

598.61

598.62

598.62

598.62

598.63

Information501

22-14-00Page503Mar 15/89

U.Se or disclosure Of lnfOrmatlOn on thm page is subject to the restrictions on the title page of thw document.

Honeywell M!M?ANC’CITATIONn/V

FigureNo.

AppendixA

A-1 28 V dc BUS

A-2 EdgeLighting

A-3 AC PowerRequirements

A-4 ReversionarySelectDiscreteSwitching3-TubeEFIS

A-5 AOA/SpeedCommand

A-6 RadioAltimeterInterface

A-7 AirDataCommandBlockDiagram

A-8 WeightOn WheelsSwitch

A-9 ASCBBusConfiguration

A-10 VNAVDisable

AppendixB

B-1 Deleted

B-2 Deleted

B-3 28 V dc Power

B-4 FMSAuto-TuneSwitches

B-5 ASCBConfiguration

B-6 NZ-61OFlightTestInterface

AppendixC

c-1 28 V dc PowerRequirements

c-2 26 V ac PowerRequirements

c-3 EdgeLighting

c-4 AuralAlerters

c-5 MiscellaneousSwitches

C-6 AirDataCommandBlockDiagram

c-7 VNAVDisable

598.132

598.133

598.134

598.135

598.136

598.137

598.138

598.139

598.140

598.141

--- -

598.155

598.156

598.157

598.158

598.168

598.168

598.168

598.169

598.170

598.171

598.172

InterconnectInformationTable501 (cent)

22-14-00Paqe504May-25/90

Use or disclosure of Information on this page is subject to the restrictions on the title page of thks document.

Honeywell iWJRANcECITATION Ilfl

FigureNo.

AppendixD

D-1 Deleted

D-2 Deleted

D-3 WeightOn Wheels

D-4 DC PWRRequirements

D-5 PanelLighting

AppendixE (CitationIIOnly)

E-1 DC PowerRequirements

E-2 AC PowerRequirements

E-3 EdgeLighting

E-4 AirDataCommandBlockDiagram

E-5 Engage/TrimInterlock

E-6 HeadingSwitching

E-7 AutopilotEngageSelectandVG ValidSwitching

E-8 AneroidSwitchWiring

E-9 FlapTransitionSwitch

E-10 TorqueWarnAnnunciator


--- -

598.186

598.186

598.186

598.194

598.194

598.194

598.195

598.196

598.197

598.198

598.199

598.199

598.199

22-14-00Page504.1/504.2

May 25/90Use or disclosure of Information on this page IS subject to the restrictions on the title pagt of thm document.

Honeywell M!JYANCECITATION V

4.0 ELECTRICALINTERCONNECTINFORMATION

Thissectioncontainsthecomponentwiringfortheelectronicflightinstrumentsystemanditsinterconnectionto variousotheraircraftsystems.

4.1 GeneralRequirements

~: EFIS/MFDusesAC powerfortheDC-811SynchroExcitation,theSG-605/805andMG-605/805DemodReferences.AllotherEFIS/MFDpowerrequirementsare28 V DC. Panelandpedestalmountedunitscanbeorderedinconfigurationsfor5 V or 28 V lighting.

4.1.1 AC Power- Theaircraftac powersupplymustbe singlephase,115t 5volts,400t 20 Hz sinewavewitha maximumtotalharmonicdistortionof5 percent.Underallloadconditions,amplitudemodulationof thepowersupplyshallnotexceed2 percentat anyfrequency.(Percentmodulationisdefinedas one-halfof thepeak-to-peakmodulationenvelopedividedby thecarrieramplitudeandmultipliedby one hundred.)Withinitsloadrating,thepowersupply’soutputimpedanceshallbe lessthan.3ohmforsinusoidalloadvariationsat allfrequenciesbelow10 Hz.

4.1.2 DC Power- Theaircraftdc powersupplymustbe 28 voltst 10 percent.

~: Forfurtherinformationaboutaircraftpower supplies, ‘refer toRadio Technical Commission forAeronauticsspecificationDO-160A.

4.1.3 Interconnect

4.1.3.1Wiring

The interconnect cabling shall be routed to minimize coupling withhigh voltage and high current circuits suchas the+28voltsdc powerfromthesymbolgenerators.

4.1.3.2InterconnectFormat

Eachconnectionis typicallyshown as indicated in FigureI-1. Wireterminationsprefacedby theletter“C”indicatethecopilot’ssideinthedualinstallation.

InterconnectInformationTable 501 (cent) 22-14-00

Page 505Mar 15/89

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Honeywell M!U?ANCECITATION V

Function Connector Pin Connects TT

------------- -----]imContrO1<~~l:~~----~~~~~~<~ld

lnit Connectordesignation Wire Gage

~: Intheaboveexampletheshieldcanbe groundedat eitherend (butnot at both ends).

InterconnectFormatFigureI-1

1.1.3.3Grounds

GOODGROUNDSAREA KEYFACTORINA GOODINSTALLATION.Eachgroundshouldbe runas a separatewire and terminated at one central point.The followingspecialrequirementsshallbe met:

A. Chassisgroundsshallbe terminatedto theframeof theaircraftfromthematingconnectorwiththeminimumwirelength.Ifchassisgroundsextendbeyond18 inches,theyshouldbemadeusinga shieldedwire.

B. ALLSHIELDEDWIRESshallhavetheshieldstiedat oneendonlytothenearestaircraftframepoint. Shieldgroundreferencesareshown only on critical functions. All other shields should begrounded at the Transmit endof theshield. (Neverat bothends).DO NOTconnectDigitalshieldsandanalogshieldstogether.

C. Twistedwiresshallhaveat leasttwofullturnsperfoot.

D. Alldc powergroundsshallbe tiedtogether,allac power groundsshall be tied together, all signal grounds shall be tied together,all discrete returns shall be tied together and all lightinggrounds shall be tied together. DC power,AC power,signaldiscreteandlightinggroundgroupsarethentiedtogetherat asinglepointandconnectedto theairframe.Insuregroundblockconnectionto theairframehascapabilityto maintaingroundreferenceundermaximumcurrentconditions.Thediagrambelowillustratesthisgroundingmethod.


Page-506Mar 15/89useordisclosureofinformationonthispageissubject to the restrictions on the title page of thts dJcument.

Honeywell MKRANCECITATION V

Itis veryimportant that this grounding technique be adhered to.Do not tie the various ground wires to multiple aircraft frame-and depend on the aircraft structure itself to provide alow impedance path for the individual grounds. ONLY chassisgrounds and shield grounds are grounded at multj~points in theaircraft.

E. If ground blocks are not adjacent to the unit and ground wires areseveral feet long, it may be necessary to splice larger gauge wireto the ground wire outputs to reduce voltage drop in these longgroundwires. Voltagedropson allgroundwiresfromLRU’Stoaircraftframeshallbe lessthan1.0volts.

F. Pin1OJ1A-4oftheautopilotandpins 12,13,and:.4J1-Cof theservosmustbeterminatedat onecommonpointwhichisalsotiedto aircraftground.The wire used to connect 10JIA-4to thecommon point must be of sufficient gauge to maintain less than 1/4ohm resistance in this path.

r——

I

I

CENTRALAIRCRAFT

IGNDBLOCKS

IL ——

— ——— ——. —— —— .— —

DISCRETERETURN

DC PWR AC PWR

I :

SIGNAL .IGHTING

GNDS GNDS GNDS GNDS GNDS

— — — -,.

‘1

I

I

I

–-l

TOVARIOUSAIRCRAFT LOCATIONSAD-3647

Interconnect InformationTable 501 (cent) 22-14-00

Page507Mar 15/89

Use or disclosure of mformatlon on this page IS subject to the restrictions on the title pacje of this document

Honeywell YAWJRANCECITATION V

4.1.3.4SpecialCabling

A. TheED-600/800Color,Video,FlybackRaster/Stroke,andStrokeReadysignalsconsistof8 twistedshieldedpairs. The maximumlength of these cables is 40 feet.

B. TheED-600/800secondaryColor,Video,Raster/StrokeandFlybacksignalsconsistsof 7 twistedshieldedpairs. Themaximumlengthof thesecablesis40 feet.

c. Theweatherradarcableto theSG-605/805andMG-605/805shallmeettheelectricalcharacteristicsof Table4-1.

Table4-1

* ElectricalProperties,WireAWG24,StrandedTwistedPair,Shielded

Impedance(PerMIL-C-915) 70 ~ 7 ohmsMutualCapacitance(PerMIL-C-915) 30 PF/FtMaxAttenuationat 1 MHz 1.408/100FtMax

* Equivalentto RaychemCorp. Twoconductors,MultiplexDataBus.DrawingNo. 10595,Rev.C, dated4-10-78whichis availablefromSperryperTable4-2.

Table4-2

CABLEMI * UNCUTLENGTH

M1585294 40 FeetM1585294-1 80 FeetM1585294-2 120FeetM1595294-3 160FeetM1595294-4 200 Feet

Interconnect Information

Table 501 (cent) 22-14-00Page 508

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Honeywell WMRANC’CITATION V

[.2 Interconnect Requirements

1.2.1 Polarities - Installing the systemin accordancewiththe interconnectinformationthephasingbetweentheautopilotsensors and aircraftcontrols willbe as follows:

o Rollright CW drumrotationviewedfromdrumend

● Pitchup CW drumrotationviewedfromdrumenci

o Yawright CW drumrotationviewedfromdrumend

If it is impossibleto maintaintheaboverelationships,servodrivedrumrotationdirectioncanbe changedby interchangingtheconnectionsto pin “A”withpin“B”andpin “L” withpin“N”on theappropriateservo. Ifthe trim servo polarity must be changed the connections topin ‘B” and pin “C” are reversed.

,.2.2 Engage Interlock - Theautopilotcomputeriselectricallykeyedtopreventthewrongcomputerfrombeinginstalledandoperatedinanaircraft.

,.2.3ServoDriveElectricalKeying- The engage clutch of the servo drive iselectrically keyedas a functionofpowergearratioto preventthewrongservofrombeinginstalled.

.2.4 PitchWheelGain- A resistorinstalledintheaircraftwiringbetween1OJ1B-28andllJ1-Uprovidedfor controlling the gain of the pitch wheel- thedegreeof pitchwheelchangeperdegreeof pitchattitudechange.

ResistorValve ~

o 10 Degrees Pitch/60e Wheel51K, 5%, 1/2 WattlOOK,5%,1/2Watt :200K,5%,1/2Watt 2470K,5%,1/2Watt 1


Paqe 509Mar”15/89

UseordisclosureofInformationonthispageIS subJecttotherestrictionsonthetitlepa~{)ofthisdocument.

Honeywell W!J.LANCECITATION V

4.2.5 Go-AroundPitchCommandAdjustment- Externaladjustmentof thego-aroundpitchangleis providedby a resistorin theaircraftwiringbetweenpins7J1A-2and7J1B-32of theflightdirector.Theresistorvaluesareas follows:

PitchAncile ~ PitchAnqle ~

4.05M 8 331K:: 1.82M 9 272K3 1.22M 10 225K4 862K 11 186K ‘

649K 12 154K: 508K 13 127K7 407K 14 103K

4.2.6 AutopilotOffAnnunciator- Thecircuitshownin Figure4-11canbe usedto annunciateinadvertentautopilotdisengage.If theautopilotdisengagesforanyreasonotherthanusingthedisengageswitches,the“autopilotoff” light will illuminate. Pressing the disengage buttonwill reset the annunciator. Everytimetheautopilotdisengagesthehornwill give a 1 sec warning.

4.2.7 TrimWarningThreshold- Theoutof trimwarningthresholdwillbe setby resistorsin theautopilotcontroller.

4.2.8 FlightDirectorPointerGain- Theflightdirectorpointergainisestablishedin theaircraftwiringforthevariousindicatorstobeused.

4.2.9 DMETuneto NAV - IftheDME/NAVfrequencyselectorallowstheDMEto betunedto a frequencyotherthanthefrequencyof theflightdirectNAVinput,a logicgndis requiredon 7J1A-50of theflightdirectorwhentheDMEis tunedto thesamestationas theNAV input.ThisinsuresthattheDMEdistanceinputto theflightdirectorrepresentsthedistanceto theVORstationtunedon theNAV selector.

4.2.10RNAV/RNAVApproachModeGrounds- When in theRNAVAPPROACHmode,bothRNAVandRNAVapproach(7J1A-47,48)groundsareto be applied.TTLgroundis notto be appliedin RNAVmodes.


Page 510Mar 15/89

Useordisclosureofinformationon thw page IS subject to the restrictions on the title page of thm document,

Honeywell I!NKYANCECITATION V

).2.11 Aircraft Relays

Ifthe requirement existsforaircraftrelaysto be drivenin parallelwiththeannunciatorlightsinthe FD/AP ModeSelector,diodeisolationis required.Suppressiondiodes should be installed across the relay

coil and a diodemustbe installedin serieswiththemodeselectorasshownbelow. Failureto installthediodesmayresultin unselectedmodeslightingas a functionof dimmingtheannunciatorlighting.

—— —

.IRECTOR~~El8-28VDCFPOMFLIGHT

7J1A-9

L —— — -1~ REM~~TEANN”NCIAT~R 1

——— —

———

1

OIODES IFDCOMPUTER REQUIRED 5VDCOR28VDC

I

IINAIRCRAFT

‘*’ ‘ ‘ <

s

‘ DIMMING

I1SUPPLYi

I

I I 1- ——— — JI $1L .—— J AD-1429 @

———‘FD/APMODE SELECTOR=

R$;:R0MLQ5L’>7J1A-9

L -J+221VDC

———

:L

——— —

DIODEI

7———1

REQUIREDFDCOMPUTER

lRCRAFT I

I‘+!7’ ‘: <

I RELAY

II

I I 1-————JIL

v——— J AD-1429 ~

AircraftRelayDiodeIsolation


22-14-00Page 511Mar 15/89

Use or disclosure of reformation on this page is subject to the restrictions on the title page of this document.

Honeywell WVFAN’ECITATION V

5.0 AVIONICSSTANDARDCOMMUNICATIONSBUS (ASCB)

TheASCBistheprimarycommunicationpathbetweensymbolgeneratorsandthsSperryFMSsystem.Physically,itconsistsof twomulti-pointserialsynchronousdigitalcommunicationsnetworks,eachelectricallyisolatedfrcmtheother,andeachcapableof maintainingfullinter-systemcommunicationin the event of a failure on the other. TheASCBcomplieswithRTCADocumentDO-160Awhichrequiresthatthefollowinginstallationrequirementsbe met:

A. Therearetwo independentASCB’Sdenoted“A”and“B”,eachconsistingof twowirepairsdenoted“Data”and“Clock”.

B. TheASCBtransmissionlinesshallbe Raychem2524E0114withathermoradjacketor Fillotex63247.

c. EachASCBtransmission line pair shall have a characteristic impedanceof 125 ohmst 5 ohms. Thecharacteristiccapacitanceshallbe 12 t 2picofarads/foot.

r). EachASCBtransmissionlinepairshallbe terminatedat itstwoendswith“non-inductive”127ohmresistorst 1%,1/4watt,metalfilm. Aminimumcablelengthof 23 inchesisrequiredbetweentheterminationresistorsandtheneareststub.

E. TheASCBtransmissionlines shall have a maximum length betwaenterminators of 150 feet.

F. Stublengthsat eachuser pickoff shall not exceed 10 inches.Buttspliceswithsolderringsshallbe utilizedforallstubinterconnections.

G. Theshieldconnectionsat eachstubshallbe accomplishedwitha buttsplice.Themaximumallowabledistancebetweenshieldconnectionsshallbe 0.3 inch.

H. Allshieldsshallbe tiedat onepointto theaircraftframeat therearof theLRUwhichis approximatelyin thecenterof thebus. A6-inch(maximum)lengthof 22gaugeinsulatedwireshallbe used.

1. Wirerunsoutsideshieldsshallbe no longer than 2 inches and shallbe configured as twisted pairs wherever possible.

5.1 Rad50SystemBus (RSB)andDiqitalAudioBus

Referto Section5.0for RSBandDigitalAudioBusinstallationrequirements.


22--14-00Page512Mar 15/89

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Honeywell lWLWANcECITATION V

Function

TEST POINTPOWER GND115 VAC, 400 HZ INPUT27 VDC OUTPUT26 VAC, 400 HZ OUTPUT(55 VA MAX)5V, 400 HZ OUTPUTEXTERNAL PECO CONTROL GNDRECO CONTROLRECO CONTROLPECO CONTROLCHASSIS GNDPECO CONTROL

[

NCw

ATTITUDE VALID

SPARES

EXTERNAL FAST ERECT CMD

SPARES

TEST POINTTEST POINT

SPARES

PILOT’S VERTICAL GYROVG-14A

Connector Pin

lJ1-A ------NCP,

{-B (22)----r-,-’-.

-c (22)----’~- --D (24)---------

-E ------NC

.------- ----

.------ -----

.------- ----

-F ------NC------NC

=fi(24)-----------------J (24)----------------1-K ------NC-L (22)----------------M ------NC h

------NC~! (24)-----1+-----------

I

;1 J-R (24)----<$--------------s-T-u

7

ORI’!

-V (24)-------- o---------w HI

NOTE : CONNECTIONS SHOWN FORVG-14ACONNECTORPOINTINGFORWARD.

Connects To

AG GNDFIG. 4-3(SHT.1)lJ1-HH

JUMPER

1OJ1B-33,11J1-P

FIG. 4-13

DC GND

Interconnect InformationTable 501 (cent)

22-14-00Paqe 513Mar”15/89Useordisclosureof information on this page IS subject to the restrictions on the title pag: of this document.

Honeywell MMRANCECITATION n/V

PILOT’SVERTICALGYRO(cent)VG-14A

Function ConnectorPin ConnectsTo

RECOGNDOUTPUT>6°OUTPUT lJ1-k------NCPECOGNDOUTPUT -m ------NCEXTERNALRECOCONTROL -n ------NC

[

x f)--P (24)---- ------------65J2A-18,57J1-EROLLATTITUDE -q (24)---- ------------65J2A-19,57J1-F

; ~!-r (24)---- -------------65J2A-20,57J1-Gc -S (24)-------n- ------ 7J1A-15,1OJ1A-10

ROLLTO F/D C -t (24)----1 ItIH -U (24)--------w-------- 7J1A-14,1OJ1A-9

ROLLTO RADAR H[

:; \;:]--fl+------------;;:;-[50MV/DEG c -- - - - - - - - - - -- - -

[

x

1

-X (24)---R-------------65J2A-15PITCHAllITUDE Y -y (24)---tt-:::::::::::::;j;~-;;

z -Z (24)---~-C

t

-AA(24)--------- ------ 7J1B-;8,1OJ1A-16PITCHTO F/D C -BB(24)---In

H 11-CC(24)------U-- ----- 7J1B-27,1OJ1A-15

PITCHTO RADAR C

1

t-DD(24)Q- -------------59J1-L

50MV/DEG H -EE (24)~- ------------- 59J1-K-GG (24)------------------ 7JlA-19, 65J1A-85

ATTITUDE VALID [C -FFNO lJ1-HH(24)------------------lJ1-D


22-14-00Page514May25/90UseordisclosureofInformatlofionthispage!ssubject10therestrictionsonthetitlepageofthisdocument

PILOT’SELECTRONICHSIED-600


PRIX DEFL(IN) +<-

t2J1-1 (24)------------------ 65J1A-61-2 (24)--------------~-~<’--65J1A-62

-- 65J1A-63SECX DEFL(OUT +

Y--3 ------NC-4 ------NC

28 V DC PWR +

1

‘~ (22)--------------------pILOT28VDC

28 VDCPWR + -6 (22)--------------------‘OWER’F1G”4-1

STROKEREADY(PRI){: A ; :::--fi----------------:::------ --------------

STROKEREADY(PRI)SHIELDGND -36------1’ IPRIY DEFL(IN) +

-(--9 (24)--------------?--C--65J1A-64-10(24)--------------~-i~--65J1A-65

Y-- 65J1A-66SECY DEFL(OUT) +

{-11------NC-12------NC

POWERRETURN - -13(22)--------------------DC PWRGNDPOWERRETURN -14(22)--------------------DC PWRGNDVALIDOUTPUT(PRI)(GND=VALID)-15(24)--------------------65J1A-46STROKEREADY(SEC) +

<--16------NC-17------NC

SECXDEFL (IN) +-(-

-18------NC-19------NC

VALIDOUTPUT(SEC)(GND=VALID)-20------NCREVSELECT(PRI) -21------NCSIGNALGND -22(22)--------------------SIGNALGNDCHASSISGND -23(22)--------------------CHASSISGNDSECY DEFL(IN) +

{--24------NC-25------NC

INCLINOMETERLIGHTING +{-

-26------NC-27------NC

SPARE 231-28------NC


22-14-00Page 515

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Honeywell WXE!ANCECITATION n/V

PILOT’SELE~:R:lf~CHSI (cent)

Function ConnectorPin Connects To

REV SELECT (SEC) 2J1-29 ------NC

DIM CONTROL

{-

+ -30 (24)------------ n- ---- 115J1-40U*-31 (24)------------ - ---- 115J1-41

SPARE -32 ------NC

{

-33 (24) -------------------- 115J1-50

RASTER DIM CONTROL I -34 (24)-------------------- 115J1-51-35 (24) -------------------- 115J1-52

STROKE READY (PRI) SHIkLD GND -36(20)--------------------SHIELDGNDFOR2J1-7,2J1-8

SPARE

A

-37------NCCOLOR3 (PRI) +

{-1 1

-38 (24)-------- -------T?- 65J1A-40-39 (24)----------------L-- 65J1A-41

t- 65J1A-42TEMP ANNUN GNDOUTPUT -40(24)--------------------ANNUNCIATORSPARE

A-41------NC

COLOR2 (PRI) +<-

1I

-42(24)---------------r~r-65J1A-37-43(24)---------------1-- 65J1A-38

9 -- 65J1A-39STROKEREADY(SEC)SHIELDGND -44------NC

SPAREA


{-1 -46(24)--------+

%.-------- 65J1A-34-47(24)----------------:<.-65J1A-35

-- 65J1A-36RESERVED -48------NCRESERVED

A-49------NC

COLORO (PRI) +{-

1 4-50(24)---------------r~t-65J1A-31-51(24)---------~------~-65J1A-32

-- 65J1A-33SPARE -52------NCSECX DEFLSHIELDGND 2J1-53------NC “

A 1 SEE PARA.4.1.3.4.A


22-14-00Page516May25/90Useordisclosureofmformatlononthispageksubjecttotherestrictionsonthetitlepageofthistiocument.

Honeywell W!KPAN’ECITATION V

PILOT’S ELE~]R{’&CHSI (cent)

Function ConnectorPin

VIDEO(PRI)<-+ A 1 42J1-54(24)------------------

-55(24)------S--------V-----

SECY DEFLSHIELDGND -56------NC

SPARERASTER/STROKE(PRI) + 1-@l

FLYBACK(PRI)<: A

LEFTPHOTOSENSOROUT +

RIGHTPHOTOSENSOROUT +

ACOLOR3 (SEC) + - 2

.{-

-57------NC

{-58(24)---------------fl---59(24)---------------$’--

1-60(24)---------------=-61(z4)---------------~1--

L --

-62------NC-63------NC-64------NC-65------NC-66------NC

-67------NC

COLOR2 (SEC) +

{-

A2 -68------NC

-69------NC

COLOR1 (SEC) +

{-

A2 -70------NC

-71------NC

COLORO (SEC) +

{A2 -72------NC

-73------NC

VIDEO(SEC)

{

+ A2 -74------NC

2J1-75------NC

A2 SEEPARA4.1.3.4.B

ConnectsTo

65J1A-2865J1A-2965J1A-30

65J1A-4765J1A-4865J1A-4965J1A-4365J1A-4465J1A-45

interconnect Information

Table 501 (cent)22-14-00

Page 517Mar 15/89

Use or disclosure of information on this page is subject to the restrictions on the title pay; of this document.

Honeywell MUR’NCECITATION V

Function

RASTE1l/STROKE

FLYBACK (SEC)

P:

(SEC) +

{.

ELECTRONICED-600

ConnectorPin

2J1-76------NC

-77------NC

A2 -78------NC

2J1-79 ------NC

(cent)

Connec;sTo——

Use or disclosure of mformatlon


22-14-00Page 518

Mar 15/89onthispageIS subjecttotherestrictionsonthetitlepageofthisl:ocument.

Honeywell WW!!ANC’CITATION V

PILOT’SELECTRONICADIED-600


PRIX DEFL(IN) +<- I

3J1-1 (24)---------------r~r- 65J1A-55-2 (24)----------------+-- 65J1A-56

SHIELD -- 65J1A-57SECX DEFL(OUT)+

{--3 ------NC-4 ------NC

28 V DC PWR + ‘5 (22)--------------------pILOT28V

28 V DC PWR -6 (22)-------------------} DC PWR,FIG.4-1+

STROKEREADY(PRI) +

{-

-7 (24)--i~l-

A i

--------------65J1A-231-8 (24)-~-J---------------65J1A-24

STROKEREADY(PRI)SHIELDGND -36------TPRIY DEFL(IN) +

{--9 (24)-------------4---=--65J1A-58-10 (24)-------------~--!--~-65J1A-59

SHIELD -- 65J1A-60SECY DEFL(OUT)+

<--11------NC-12------NC

POWERRETURN -13(22)--------------------DC PWRGNDPOWERRETURN -14(22)--------------------DC PWRGNDVALIDOUTPUT(PRI)(GND=VALID)-15(24)--------------------65J1A-19STROKEREADY(SEC) +

<--16------NC-17------NC

SECX DEFL(IN) +.<-

-18------NC-19------NC

VALIDOUTPUT(SEC)(GND=VALID)-20 ------NCREVSELECT(PRI) -21------NCSIGNALGND -22 (22)-------------------- SIGNAL GNC)CHASSIS GND -23(22)--------------------CHASSISGNDSECY DEFL(IN) i-

{--24------NC

3J1-25------NC

41 SEEPARA4.1.3.4.A.


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Honeywell WURANCECITATION n/V

PILOT’SELEj~~O#~CADI (cent)


INCLINOMETERLIGHTING +

{.

3J1-26 (22) --------------------

-27 (22) --------------------SPARE -28 ------NCREV SELECT (SEC) -29 ------NCDIM CONTROL

<+ n$-30 (24)------ - - ---------

b-31 (24) ------ -L-----------

SPARE -32 ------NC

{

-33 ------NCRASTER DIM CONTROL ; -34 ------NC

-35 ------NCSTROKE READY (PRI) SHI;LD GND -36 (24)--------------------

SPARECOLOR3 (PRI) +

<

TEMP ANNUNGNDOUTPUT

A1

SPARECOLOR2 (PRI) +

<-A 1

READY(SEC)SHIELDGND

SPARECOLOR1 (PRI) <+

RESERVEDRESERVEDCOLORO (PRI) ~+

SPAREL-

-37------NC

1-38 (24)--I?-----------T~[--39 (24)--w-----------’&-

L --

-40 (24)--------------------

-41------NC

1-42 (24)--1%-----------tar--43 (24)--@------------lfL-

---44------NC

-45------NC

/-46 (24)--r?----------i~r---47 (24)--~J-------.---lw--

L ---

-48------NC

A-49------NC

1 -50(24)--~1-1----------pT--51 (24)--~J-.----------LyL-

3J1-52------NC --

ConnectsTo

EDGELIGHTINGFIG.4-2DC GNtI

115J1-38115J1-39

SHIELCIGNDFOR3J1-7,3J1-8

65J1A-1365J1A-1465J1A-15ANNUNCIATOR

65J1A-1065J1A-1165J1A-12

65J1A-765J1A-865J1A-9

65J1A-465J1A-565J1A-6


22-14-00Page520May 25/90

Use or disclosure of mformatlon on thm page IS subject to the restrictions on the title page of this (Jocument.

PILOT’S ELE:;R#:C MI (cOnt)

ConnectorPin ConnectsTOFunction

EC X DEFLSHIELDGND 331-53

IDEO(PRI)i-+ A 1 -54

-55

EC Y DEFLSHEILDGND -56

PARE -57

{- ~ ~::!ASTER/STROKE(PRI) +

‘LYBACK(PRI) +<

A 1-60

. -61

-EFTPHOTOSENSOROUT +{-

------NC

(24)-----i--------------65J1A-1

(24)----- __---.-!.l--65JIA-2--- 65J1A-3

------NC

------NC(24)-----

1-------------65J1A-20

(24)----- ___---iql-- 65JM-21--- 65J1A-22

(24)-----I------------65J1A-16(24)----- ___---~:[-- 65J1A-17

--- 65J1A-18-62------NC-63------NC

COLOR3 (SEC) +

<-

COLOR2 (SEC) +

{

COLOR1 (SEC) +

{-

COLORO (SEC) +

{.

VIDEO(SEC) +

{

RIGHTPHOTO SENSOROUT‘+-c

-64------NC-65------NC

A -66------NC

A2 -67------NC

A-68------NC

2-69------NC

A-70------NC

2-71------NC

A-72------NC

2-73------NC

?3-74------NC

2J1-75------NC

b2 SEEPARA4.1.3.4.B.

interconnect informationTable 501 (cent) 22-14-00

Page 521Mar 15/89

Use or dwclosure of information on this page IS subject to the restrictionson the title pagw of this document.

Honeywell KNJIPANCECITATION V

PILOT’S ELECTRONIC ADI (cent)ED-600


RASTER/STROKE(SEC){: x:; ::::

FLYBACK(SEC) +

{.

A 2 -78------NC

3J1-79------NC

Connects To


Page 522Mar 15/89

Use or dwclosure of reformation on this page IS subject to the restrictions on the title page of this jocu”rnent. “

PILOT’S FLUX VALVEFX-220

Function ConnectorPin , ConnectsTo

{

z i4JI-A(24)---O--------------5J1-AFVSTATOR x -B (24)--J-!-!-------------5JI-B

Y -C (24)--JJ-?--------.----5J~-c26V,400HZ

{-------------------AC GNU

; :: !::l---;----------[----- hll-sSHIELDGND -F (24)---- ----- 5J1-il

PILOT’SDUALREMOTECOMPENSATORCS-412

FROMFLUXVALVE

26V,400HZ

PWRGNDSHIELll GNllSPARE

FLUX VALVE OUTPUT

CI-IASSIS GND

SPARES

{

z 5J1-A(24)---=-?-------------x

i-B (24)--~-~--------------

Y -C (24)--J-!--------------

1

-D (24)-----------------T -----

-E (24)--------------------~ (24)-----La

{

x I-H (24)---,~i-’-------------Y -J (24)-------------------z -K (24)--&~-------------

-L (24)--------

(

-M A

::

{-R-s

4J1-A4J1-B4J1-C6J1-S4JI-EAC GND

6J1-R6J1-N6JI-P

[

-T-u-v

~: SHIELDSON THISSHEETARENOTTIEDTOAIRCRAFTGROUND.SHIELDSMUSTBE INSULATEDFF!OMAIRCRAFTSTRUCTURE.


Page 523Mar 15/89

Use or disclosure of Inforfnatlon on thk page IS subject to the restrictions on the tttte page of this document

Honeywell M!MY’”c’CITATION Ilfl

Function

AC POWERGND28 VDCGND+28VDC INPUT

FREESLAVESW

+B TO FREESLAVESWHDGNO.1 ROTOR26V400HZ

HDGNO.1 STATOR

FLUXVALVE

26 VACFLUXVALVEEX115VACOUT

ANNUNCIATOR5 VACOUTPUT

HOGNO.2 ROTOR

HDGNO.2 STATOR

INTERLOCKNO. 1

FLUXVALVESHIELDCHASSISGND

INTERLOCKNO. 2

26 VACOUTPUT H42 VA MAX

SYNCSWITCH(w

FREQUENCY/PHASELOCK+

SPARE

PILOT’SDIRECTIONALGYROC-14D

ConnectorPin ConnectsTo

6J1-A(22)-------------------B (22)-------------------c (22)-------i-----------D~; (24)-----------

AUTO1

-G (24)--------------J-H (22)T~t

\-------------.

-J (22)&~-----X-

1

-------K (24)--------~a- -------L (24)--------ha--------M (24)--------’-’------

1

-N (24)-----------------P (24)------------+----R (24)------------J-1---S (24)-----T~+&-~+&----

AC GNDDC GNDFIG.4-1 (SHT1)

FREESLAVESWITCHFIG.4-3 (SHT3)AC GND65J2A-2365J2A-2165J2A-225J1-J5J1-K5J1-H4J1-E

-T-- i L---- 5J1-D

(-+ -U (24)-----’------------65J2A-28

1-V (24)-----------------65J2A-29-w

(

H

1

I-X (22)-r3-j------------;;::Bi7,C6J1-X,

c -y (22)-’”1--1------------AC GND

(

z -Z (24)----------------x -a (24)-----{_ij-;___

)FIG.4-12

Y -b (24)------&d-------fNC -c I

(NO -d (24)-----;------------FIG.4-1 (SHT 1)c -e (24)------------------65J1A-84

-f--–-J-g (22)------>

(c -h (24)------------------1OJ1B-28,C6J1-hNC -i

~NO ~~ (24)------------------FIG.4-12------NC

-m(24)----------------n (24)------------L:!Y;; ::Nc-p (24)---------------4-q RH

(

-r

6J1::

InterconnectInformationTable501(cent)

22-14-00Page524May 25/90

Use or disclosure of information on this page IS sub)ect to the restrictions on the Mle page of this socument

PILOT’SFLIGHTDIRECTORCOMPUTERFZ-500

Function

sIGNALGND+V oUTPUTVNAVW/OTp

-voUTPUTsPARESPARE+28VANN.POWEROUTPUT+28VANN. POWER OUTPUTDC ANN GNDDC ANN GND

sPARE

sPARE

ROLLATT

+28 NAV VALID

Fll LAT f+

Dc \-+28VG VALIDNAV/LOCRADIODEV(+RIGHT)TUNEDTO LOCGND+28HDGVALIDREVAPPGNDNOCGAINCHANGERNAV STAGING GND+28 V INS/R-NAV MOOE

ROLL AP COMMAND

ROLLFD COMMANDBIASOUTOF VIEW

OMEDIST40MV/MI

1 +V DMEVALID

IHDG ERROR.3V/DEGHDGERROR.2V/DEG

(H

c

(-+

(-+

(-

+

Connector PinConnectsTO

7J1A-I(22)--------------------SIGGND-2 (22)---------------~ ;:;6:32-3 ------NC t

-i ------NC-5 (22)__----!!!!------ 7J1B-29,7J1A-31-6-7-8 (22)--r?-

1

--------------18J1-f

-9 (22)--t-l---------------8J1-C

-10 (22)-~J---------------+

-11 (22)j DC GND,

-----------------.-

-12-13-14

-15-16-17-18-19-20-21-22-23-24-25-26-27-28

t

(24)-~~[

-------------------

[::]-ij----------l--::---------------

$(24)------------C>---(24)------------LQL----(24)--A-

I

--------------

(24)-~-r--------------[;j]-~”

---------------.-----------

~::t;;;;---------------

(24)-------------------(24)--------.-----.----(24)-------.--------.--(24)----~●-t------------t

lJI-u,1OJ1A-9lJ1-tlJ1-s,1OJ1A-1065J2B-8665J2B-1OO65J2B-9lJ1-GG,65J1A-8565J2B-9765J2B-9865J2B-9365J2B-80

7J1A-65sIGGND65J2B-841OJ1A-18

{-29 (24)------------~L---- ~~~~~~~~-30 (24)------------- ----31 (24)--------------------7J1A-5,7JIB-29

-32 (24)--------

i~ ------- ;:;;~#2’

-33(24)------------------~~jfB~:O1’

-34(24)-------------------iiiJ2B-88,FIG.4-17

-35 (24)

!

------------------ 7J1A-37

7J1A-36(24)--------------T;-65J2B-105

InterconnectInformationTable501 (cent) 22-14-00

Page 525May-25/90

Use or disclosure of mformatlonon WIIS page IS subject to the reslncttons

on the title pag, ! of this documenl

1

H

Function

IDG& CRSCOM

.28V TCSSELiPARE;RSERROR.3V/DEG:RSERROR.2V/DEGFZS V ALTVALIDAIRSPEEDINPUTALTITUDEINPUT

PILOT’SFLIGHT DI};C::} COMPUTER (cont)

SPARE+28V AP ENGAGE

R-NAVMODEGND INPUTR-NAVAPPMODEGND INPUT+28V TK DETENTDMETUNEDTO NAV GND

TASOUTPUT+28V TASVALIDINPUTSPARESBYSEL INPUT

HDGSEL INPUTNAVSEL INPUTBC SEL INPU

FDOFF SEL INPUTROLLPTRGAIN(C)

[HI

1ROLLPTRGAINSELECT LOCOMM

SPARESPARENAVCAP ● ~ GNDNAVCAP ● TTL GND

BC CAP GND

BC ARM GNDSBYGNDPITCHMODEGNDHDGMODEGND

LNAVMODEGNDNAVARM GND#lNAV CAP GND#l

~:~ (24)------------NCi---------l--‘lG”4-1’

-40(24)------]-U+-41 (24]-------------- 65J2B-103

-42(24)___----------:: 9J1-12-43(24)---<3 -------------9JI-64,1OJ1A-39

-44(24)-------CT----------9J1-63-45------Nc-46(24)-------------------::;2B;:$

.

-47 (24)--------------------SIGGND

-48(24)-------------------65J2B-92

-49 (24)-------------------65J2B-89-50(24)-------------------65J2B-94,

F“IG.4-17

“ -51------Nc-52(24)-------------------9J1-12

-55(24)-------------------M;-;~;;~::~-------------------

-------------------8Jl~i

-58 (24)-------------------8JI-N

-59------NC;:;(24)--.---------------

1 JUMPER

~::(24)------------------J

-64-65(24)-------------------7J1A-25-66------NC-67(24)-------------------~~~-~;~~~~~-~~-68(24)--------------------69------NC-70 ------Nc-71 (24)-------------------8J1-r,65J1B-43,

llJ1-d

-72(24)------------------- 65JlB-39

-73 (24)-------------------8J1-n

7J1A-74(24)-------------------8J1-pi


Page526May25/90

useordisclosure of mformat!on on this page is sub]ect to the restrictions on the I!tle page of this dljcument.

Honeywell WJRANCECITATION n/V

PILOT’SFLIGHTDIRECTORCOMPUTER(cent)FZ-500


+28V BC OUTPUT 7J1A-75------NCVORAPP GND -76------NCLATERALMODELOGIC -77(24)-------------------1oJ1B-37LOC IITESTPT -78------NC0SSTESTPT -79 ------NCNOC TEST PT -80 ------NCAOSS TEST PT -81 ------NCROLL TP C -82 ------NCROLL TP D -83------NCSPARE -84NAV ARM GND#2 -85(24)-------------------65J1B-55NAV CAP GND#2 -86(24)-------------------65J1B-56VORAPP ARMGND -87(24)-------------------&jJIB-59VORAPP CAP GND -88(24)-------------------65J1B-60VORAPP SEL INPUT -89 (24)------------------- FIG. 4-17ROLL DEVTP E -90 ------NCSPARE -91ROLL TP A -92------NC17 DEG BANK LIMIT -93 (24)------------------- llJ1-NEX ROLL LIMIT JUMPER 1 -94 (24)------------------EX ROLL LIMIT JUMPER 2 -95 (24)------------------1SPARE -9628V DISPLAY IN VIEW -97------NCG/SDISPTP -98------NCNAV CAP “ NOC DELAY TP -99 ------NC

-1oo

-101SPARES -102

-103LATSTRGVAL -104------NCRATELIMITDISABLEGND -105(24)------------------TJIA-11

SPARE 7J1A-106


22-14-00Paae527Ma~”25/90

Use or dwclosure Of Information on thm page IS subject to the restrictions on the title page of this docum nt

Honeywell MF;:FANCECITATION n/V

PILOT”sFLIWT D\~cT# coMf’WH?(Cent)

Function

115VAC 400HZ (H(c

+28V INPUTNO. 1F28V INPUTNO.2k26VACOUTPUT(20VA MAX)‘ITCHHOLDBUTTON~28V GS VALIDI TO TERNN~ AV VALID:HASSISGND

{

HI‘ITCHPTR LOWIAINSSEL COMMERTICAL PATH ERROR

+ UP)LIDESLOPEDEVIATION+ UP)

IMIIOALT

!T ENGTO TERNIRMALACCEL

: PRESELECTERROR#1iRT ENG TO TERN

.TERR<1OOOFTNAV MODEGND:PRSELERR#l

‘ITCHATTITUDE

IIASOUTOF VIEW

‘DPITCHCOMMANDIO-AROUNDBIAS

DC COMMANDO AP

GND

28VRADIOALTVALIDOLDERRORROM ADC

2TE 1: CITATION VONLY.

I++++{Hc[--t

(-+

(+

ConnectorPin ConnectsTO

7J1B-I(22)--c2--2 (22)-J-J-t

--------------FIG4-3,(SHT1)

-3 (22)-:~-‘-------------ACGND

-4 (22)-----7--------------FIG4-1, (SHT1)

-5 ------NC------NC

‘~ (24)-8

---------.----------65J2&87

-11-12-13-14-15-16-17-18-19-20

-9 (24)--------------------16JI-22,65JIA-76-lo (22)-----*

(24)------------------1

(24)-----------------

I

J(24)--Z-~--------------(24)-!C;-------------

$(24)-------C>---------(24)------{;-?-------(24)

l-:t------------------

(24)---------------- -----:--NC \J

16J1-28,65J2B-3816JI-27,65J2B-3965J2B-9965J2B-7320J1-X20J1-N,65J2A-70

-21 (24)-------------------17J1-2,10J1A-44.

-22 (24)---------------____-23------NC-24 [24)--------------------25 (24)--------------------26 (22j-------------------

!

-27 (24)--:;--------------

-28 (24)-+-------~:::::-29 (24)-------------------

(NOTE1) ‘16JI-25

16J1-2016J1-29SIGGNDlJ1-CC,1OJ1A-15lJ1-BBlJ1-AA,1OJ1A-167J1A-5,7J1A-31

-30 (24)-~~--31 (24)-+-;-!

-------------fjCjJ2A-73-------------65J2A-74

-32 (24)-------------- 7J~A-~, 8J1-E

225K-33 (24)-34 (24)

‘------------------~OJ~A-23

‘------------------1OJ1A-25-35 (24)--;<---------------zOJ~-~, 65JIA-78

I[- 7JlB::;[;;;:~;;:=:::::::::::::;;:;; 65J2A80>

InterconnectInformation -Table501 (cent)

22-14-00I%ge528May25/90

Use or disclosure of mformatlon on this page is subject to the restrictions on the title page of this cjocument.

Honeywell tifiWJErANcECITATION n/V

PILOT’S FLIGHT DIRECTOR COMPUTER (cent)FZ-500

Function Connector Pin Connects To

+28V ALT PRESELECT VALID 7J1B-38 (24)------------------- 65J2B-91TO/FROM NULL DISCRETE ~~; (24)------------------- 16J1-24IVV OUTPUT ------NCMODE SELECT RETURN -41(22)------------------8J1-FGS DISPCMDTOAP -42(24)--~i

#--------------1OJ1A-2O

GS INTCMDTO AP -43 (24)--U- -------------- 10JIA-22

VERT SPEED #1 .5V/lKFT/MIN -44 (24)----------C’ ------- 9J1-65VERT SPEED #2 .5V/lKFT/MIN -45 ------NC1200 FT RA GND -46(24)-------------------20J1-U+28VFDCVALID -47(24)-------------------65J1A-83LOW LEVEL FDCVALIDDISCRETE -48------NCPITCHWHEELMOVEDISCRETE -49(24)-------------------1OJ1A-33,

65J2B-96DAY-NITE28V=DIM -50(24)-------------------FIG4-1DC PRESELECTERROR#2 -51(24)-------------------SIG.GND.250FT RA GND -52(24)-------------------20J1-VAPPSELECTINPUT -53(24)-------------------FIG.4-17GA SELECTINPUT -54(24)-------------------FIG4-11O-28VLIGHTINGCONTROLINPUT -55(24)-------------------8J1-LALTHOLDSEL INPUT -56(24)-------------------8J1-aIASHOLDSEL INPUT -57(24)-------------------8J1-WVS HOLDSEL INPUT -58(24)-------------------8J1-YMACHHOLDSEL INPUT -59------NCALT SEL INPUT -60(24)-------------------8J1-cV-NAVSEL INPUT -61(24)-------------------8J1-RGNDFORACCELCOMP -62 (24) ------------------- 1OJ1A-31, NOTE2

V/SMODEGNDTOAP -63(24)-------------------1OJ1B-41ALTMODEGNDTOAP -64(24)-------------------10JtB-38IAS+ MACHGNDTO AP -65(24)-------------------1OJ1B-4OALTSWITCHGND -66------NCK GND -67GA GND -68 (24)-------------------65J1B-40APPARM GND -69(24)-------------------8J1-g,65J18-49APPCAP GND -70 (24) ------------------- 8J1-h,65J1B-50,

1OJ1B-21ALTSELARMGND -71(24)-------------------8J1-d,65J1B-41ALTSELCAPGND -72(24)-------------------8J1-e,65J1B-42VNAVARM GND -73(24)-------------------8J1-S,65J1B-51VNAVCAPTGND 7J1B-74 (24)------------------- 8J1-T, 65J1B-52

NOTE 2: CITATION V ONLY. IT IS NOTCONNECTEDFORCITATIONII.


22-14-00Paqe529Ma~-25/90

Use or disclosure of Information on th!s page IS subject to the restncttons on the title page of this docum nt.

Honeywell W!!M!ANCECITATION V

PILOT’S FLIGHT DIRECTOR COMPUTER (cent)FZ-500

Function Connector Pin Connec?s To——

ALT HOLD GND 7J1B-75 (24)------------------- 8J1-b, 65J1B-45V/S HOLD GND -76 (24)------------------- 8J1-Z, 65J1B-46,

115J1-4?

IAS HOLD GND -77 (24)------------------- ;;3;;,4;5J1B-47,

14ACHHOLD GND -78 (24)------------------- 65Jl&e~

SPARE. -79

MIDDLE MARKER INPUT -80 (24)------------------- 65J2B-95ALT HOLD ● SYNC TO ADC -81 (24)------------------- 9J1-31V/S HOLD ● SYNC TO ADC -82 (24)------------------- 9J1-34MACH HOLD ● ~TO ADC -83 ------NCIAS HOLD ● SYNC TO ADC -84 (24)------------------- 9J1-35

{

4 -85 ------NCALT HOLD 2 -86 (24)--------------

-87 (24)--------------; -88 (24)-------------- 1

{

4 -89 ------NCG/S 2 -90 (24)--------------DAMPING -91 (24)--------------

: -92 (24)-------------- 1RNAV IAS/MACH -93 ------NCASC GND INPUT -94 ------NCVERT STRG VAL -95 ------NCLNAV SEL INPUT -96 ------NCG/S OC +10TEST POINT -97 ------NCVNAV COMMAND TEST POINT -98 ------NCSPARE -99m -1oo ------NCEXT GND FOR ACCEL DAMPING -101(24)------------------ SIG GNDGND FOR ALTALERTER -102 ------NC-10 REF TEST POINT -103 ------NCVERT STRG TO TERN -104 ------NC

NORMAL ACCEL TEST POINT -105 ------NC

VERT CHANGE “7J1B-106 ------NC

Interconnect InformationTable501 (cent)

22-14-00Page 530

Mar-15/89Use or disclosure of mformatlon on this page Ls subject to the restrictions on the trtle page of this document.

Honeywell tiilllr’”c’CITATION 11/’V

(

PILOT’SFD MODE SELECTORMS-205

Function Connector Pin ConnectsTo

O-5LIGHTINGCONTROL 8J1-A(22)------------------~i;V4E;GELIGHTING

LIGHTINGGND -B (22)------------------AC GN;28 VDC MODE ANN POWER -C (22)------------------7J1A-9CHASSISGND -D (22)------

h+V POWERFROMFDC -E (22)------------------7LilA-2,7J1B-32MODESELRETURN -F (22)------------------7J1B-41

-GSPARE -HNAVSWITCHINGGND -JDIM

[HI -K (24)------------------FIG.4-1

CONTROL WIPER -L (24)------------------7J1B-55DC POWERGND -M (22)------------------DC GNDFD OFFSELECT -N (24)------------------7J1A-58NAV1REMOTEGND -P ------NCVNAVSELECT -R (24)------------------7J1B-61VNAVARM GND -S (24)------------------7J1B-73,65J1B-51VNAVCAP GND -T (24)------------------7J1B-74,65J1B-52NAV2REMOTEGND -u ------NCSPARE -v ------NCIASSEL -W (24)------------------7J1B-57IAS GND -X (24)------------------7J1B-77,65J1B-47,

115J1-48VS SEL -Y (24)------------------7J1B-58VS GND -Z (24)------------------7J1B-76,65J1B-46,

115J1-47ALTHOLDSELECT -a (24)------------------7J1B-56ALTHOLDGND -b (24)------------------ 7J1B-75, 65J1B-45ALT SELECT -C (24) ------------------ 7J1B-60ALT SELARM GND -d (24)------------------7J1B-71,65J1B-41ALT SELCAPGND -e (24)------------------7J1B-72,65J1B-42APP SEL -f (24)------------------FIG.4-17APPARM GND -g (24)------------------ 7J1B-69, 65J1B-49

APP CAPGND -h (24)----------------- 7J1B-7O,1OJ1B-2I

[----- 65J1B-50BC SEL -i (24) ------------------ 7J1A-57BC ARM GND -j (24)------------------ 7J1A-68, 65J1B-57BC CAPGND 8J1-k(24)------------------7J1A-67,65J1B-58


Page531May 25/90

Use or disclosure of reformation on this page is subpct to the restrictions on the tdle paqe of thw document.

Honeywell Y&!&!!ANcECITATION V

Function

NAVSELNAVARMGNDNAVCAPGNDHOGSELHDGGND

SPARESPARE

PILOT’SFDMODESELECTORMS-205


8J1-m(24)------------------7J1A-56-n (24)------------------7J1A-73-p (24)------------------7J1A-74-q (24)------------------7J1A-55-r (24)------------------7J1A-71,65J1B-43,

llJ1-d------NC

8J1::------NC


22-14-00Page 532Mar 15/89

Use or disclosure of information on this page is subject to the restrictions on the tttle page of this document

Honeywell MI!!!RANCECITATIONV

AIRDATACOMPUTER(PILOT’S/COPILOT’S)AZ-241


26 VAC400Hz OUTPUT H<

9J1-1 (22)------------------ 16J1-3~,18Jl-E26 VAC400Hz OUTPUT C -2 (22)------------------16J1-X),18J1-F115VAC400 tiZ INPUT H

{-3 (22)------------------FIG.4-3 (SH1)

115VAC400HZ INPUT C -4 (22)------------------AC P14RGND

{

SIGNAL -5 (24)------------------18JI-TCOARSEALTNO.1 +15V REF -6 (24)------------------18J1-R

RETURN -7 (24)------------------18J1-P

{

SIN -8 (24)------------------18J1-uFINEALTNO.1 Cos -9 (22)------------------18J1-V

RETURN -lo(22)-----------------18J1-WCHASSISGND -11------+28V ADCVALID -12(24)-*-------------16J1-36,7J1A-42

18J1-a,7J1A-52ALTALERTHORN1OJ1B-44

SPARE -13SPARE -14SIGNAL GND

“[

-15 (22)-----------------SIGNALGND-16---------143J1-85,C143JI-85

;: -17---------I43J1-1OO,CI43J1-1OOcl -18---------143J1-1,C143JI-1C2 -19---------143J1-26,C143J1-26

ALTITUDE Al -20---------143J1-98,C143J1-98ENCODING A2 -21---------143J1-99,C143J1-99

A4 -22---------143J1-97,C143J1-97-23---------143J1-86,C143J1-86

l? -24---------143J1-84,C143J1-84SPARE -25SPARE -26ALTENCODINGD4 -27---------143J1-13,C143J1-13IILTENCODINGCOMMON -28---------143J1-69,C143J1-69PREASSIGNED -29------NCPREASSIGNED -30------NC

{

ALTHOLDENGGND

I

-31(24)----------------7J1B-81HOLDOUTPUTS

{H -32(24)-r~-------------7J1B-36

-33(24)-vs--------------7Jlg-37,65J2A-80Vo.1 VERTSPEEDHOLDENiGND -34 (24)-----------------7J1B-82

AIRSPEEDHOLDENGGND -35(24)-----------------7J~B-84PREASSIGNED -36------NCSLEWENGAGE 9J1-37(24)-----------------115J1-57,F1G.4-6

InterconnectInformationTable 501 (cent)

22-14-00Page-533

Mar 15/89Use or disclosure of mformahon on this page IS subject 10 the restnctrons on the Mle pa~e of this document


AIR DATACOMPUTER(~;L~]~S/COPILOT’S)(cent)


{SLEWCONTROL 9J1-38(24)-----------------FIG.4-6,115J1-58

NO.1 HOLDREFOUTPUT -39(24)-----------------FIG.4-6,65J2A-79fALT HOLDENGGND -40------NC

HOLDOUTPUT ~ -41------NC-42------NC

NO. 2

VERTSPEEDHOLDENG -43------NCAIRSPEEDHOLDENG -44------NCPREASSIGNED -45------NCSLEWENGAGE -46------NCSLEWCONTROLINPUT -47------NC.HOLDREF -48------NC

{

SINFINEALT CosNO.2 COMMON

{

SIGNALCOARSE +15 V REFALT NO. 2 GND

SPARE

TESTPOINTS

{

EXCITATIONBARO POT WIPER

LOW

4-49(24)--1~,-----50(24)---------51(24)-+-J----52(24)----------53(24)----------54(24)---------

-- -- -- - -------- --- - -i- - - -

“-l------II-------L-Ll---

-55

{

------NC-% ------NC-58------NC

{-59(24)----------Q-’-----60(24)---------!-(------61(24)---------L=I-?----

16J1-4016J1-4116J1-4216J1-37,1OJ1A-2116J1-1416J1-15

18J1-Z18J1-Y18J1-X

BAROCORRECTIONDISABLE -62------NCDCALTITUDE -63(24)-----------------7J1A-44AUTOPILOTAIRSPEED -64(24)-----------------7J1A-43

1OJ1A-39ALTRATEOUTPUT -65(24)-----------------7JIB-44ALTRATEREF+ -66------NCALTRATEREF - 9J1-67------NC


22-14-00Page 534

Mar-15/89Use or disclosure of reformation on this page !s sub)ect to the restrlcttons on the title page of this document

Honeywell W!JR’”c’CITATION n/V

AUTOPILOTCOMPUTERSP-200


+15VDC 10JIA:~(24)------------------;;;;-!,FIG4-14,+5 VDC ------NC

+28V A/P ENG . TCSSEL -3 (20)------------------llJ1-C,12J1-F,13J1-G.FIG.4-11

SERVOPWRGND -4 (18)------------------i2J1-C;13J1-C14J1-C,SERVOPWRGND

+28VDC FROMA/PDISENGSW -5 (20)------------------FIG.4-11SPARE -6-15VDC -7 (24)------------------llJ1-A,17J1-5CHASSISGND -8 --------

*,

ROLLH!

-9 (24)-------2--------ROLLC ;;:(24)------~L4--------ROLLHOLDANN GND ------NCPITCHCOUPLEANNGND -12------NCAP OFF LIGHTGND -13(24)-----------------AP OFFHORNGND -14(24)------X--------PITCHH -15(24)------P+

!-------

PITCHC -16(24)------!&--------ROLLCOUPLEANN GND -17------NCROLLA/P PATHCOMMAND -18(24)-----------------(ROLLLEFT= -)

V/LRADIODEVIATION -19--:---NCG/SDISPLACEMENTCMD

!

-20(24)~-6– ---------ADCALT INPUT -21(24)----- .-------.G/S INTCMD -22(24)1-&-----------:~~R:ATACOMMAND(+)

I

-23(24)---------,=------24 ,1

AIRDATACOMMAND(-) -25(24)--------@---TURNKNOBCOMMANDW

}

-26(24)-------------~~j-(+ROLLLEFT)

TURNKNOBCOMMANDCT -27(24)-----:-------U-

PITCHWHEEL+ CLIMB I-28(24)=’~&!-----PITCHWHEEL+ DIVE -29(24)JOL--.-----------~ Q OUTPUTGAINCONTROL -30------NCAPE 1OJ1A-31(24)-----------------

lJ1-u,7J1A-14lJ1-s,7J1A-15

FIG.4-11FIG.4-11lJI-CC,7J1B-27lJI-AA,7J1B-28

7JIA-28

7JIB-429JI-52,16J1-377J1B-437J1B-33

7J1B-34llJ1-B

llJ1-D

FIG.4-6

7JIB-62


Page535May 25/90

Use or disclosure of mformatlon on thm page IS subject to the restrictions on the Otle page of this document

Honeywell ~fi~J~~ANcECITATION n/V

AUTOPILOTj~[l~ER (cent)


ANEROIDSWITCHINPUTPITCHWHEELLOGICINHIBITSPAREVOROSS OUTPUT(+5V 0SS)ROLLSPARE#8SPARESPAREAIRSPEEDINPUT

[COURSEERROR ~

PITCHCOUPLESEL GND

NORMAL ACCELERATION

ROLLINTEGRALDISABLE

{

xHEADING Y

A/PTEST (t15V)

AUTOPILOTVALIDINTLK

+28V PULSETRIMUPINTERLOCKSPARE+28V PULSETRIMDOIIIN

HDG ERROR

YAW RATE

PITCH DISPLACEMENT

PITCH RATELIFTCOMPROLLDISPLACEMENTROLLRATEROLLINTROLLCOORDINATION

1OJ1A-32(24)-----------------FIG.4-14-33 (24)-----------------7J1B-49,65J2B-96-34-35------NC-36------NC-37-38-39 (24)-----------------7J1A-43,9J1-64-40------NC-41------NC-42------NC-43------NC-44(24)-----------------17J1-2,

7J1B-21-45------NC

i-46(24)---------------

~}-47(24)-----!-J-------- FIG.4-12-48(24)-----!Cj---------49(24)-----------------57J1-L,FIG.4-13

[

-50------NC-51(24)-----------------1OJ1B-36-52------NC-53(24)-----------------FIG.4-12-54------NC-55 (22)-----------------FIG.4-11-56------NC-57-58(22)-----------------FIG.4-11-59------NC-60------NC-61------NC-62------NC-63------NC-64------NC-65------NC-66------NC

1OJ1A-67------NC

T-A-..----_-L T—I?-..--L, –.-

lnvercunnec~ lnTormaLlon

Table501 (cent)22-14-00

Paqe536May-25/90

Use or disclosure Of Information on th!s page IS subject to the restrictions on the tttle page of this oocument

Honeywell ~fivJk~ANcECITATION n/V

AUTOPILOTCOMPUTER(cent)SP-200


SIGNALGND 10JIB:~(20)-----------------SPARE+28V INPUTPOWER -3 (18)-----------------115 VAC, 400HZ (H) -4 (22)----------

{

-----

AC POWER GND -5 (22)-------=------1,

SPARE -6 ;:26 VACOUTPUT -7 (22)-------U-------DC POWERGND -8 (20)-----------------SPARE -9SPARE -lo+28 VDCA/P ENG -11 (22)----------------+28VDC Y/D ENG -12 (22)----------------+28VDC FROMDISENGAGE -13 (22)----------------SW (Y/D)

28 VDC PULSETRIMDRIVE -14 (22)----------------+28VDCTK OUTOF DETENT -15 (24)----------------TTL GND -16------NCHDGHOLDANN ● GND -17------NCTORQUEWARNING -18 (24)----------------28 VDCTCS SELECT -19 (24)----------------APPARM GND -20------NCAPP CAPGND -21 (24)----------------

AIL SYNCHROEXCC -22 (22)----------------HDGGND -23------NCV/LGND -24------NCREVCRSGND -25------NCSBYGND -26---T--NCSOFTRIDEMODEGND -27(24)----------------ENG INTLKTODG VALIDRELAY -28 (24)----------------

AIL SYNCHROEXC H -29(22)----------------+28V A/P ENGSELECTSYNCHRO -30(24)----------------RUDDERSYNCHROEXC C -31(24)----------------RUDDERSYNCHROEXC H -32 (24)----------------+28V A/P ENG INTERLOCK -33(24)----------------

FLAPINPUTNO.2 -34------NC+28VDC Y/D ENGSELECT 1OJ1B-35(24)----------------

ConnectsTo

SIGNALGND

FIG.4-1 (SH1)FIG.4-3 (SH1)AC POWERGND,13JI-E

13J1-D,6J1-X,C6J1-XDC POWERGND

65J1A-94,FIG.4-614J1-FFIG.4-11

FIG. 4-11FIG.4-11

FIG.4-16FIG.4-11,65J1A-90

7J1B-70,65J1B-50,8J1-h12J1-E

llJ1-Z6J1-h,C6J1-h,FIG.4-1212J1-DFIG.4-1314J1-E14J1-DlJ1-P,llJ1-P,FIG.4-13

llJ1-R


22-14-00Paae537Ma~”25/90

Use or disclosure of mformatlon on th!s page IS sub!ect to the restrictions on the ttle pag ? of this docum nt.

Honeywell tiil!l!~l!’”c’CITATION n/V

AUTOPILOT~f~l\TER(cent)


ENGINTERLOCK 1OJ1B-36(24)-----------------1OJ1A-51LATERALMODELOGIC -37 (24)-----------------7J1A-77ALTHOLDMODEGND -38 (24)-----------------7J1B-64+28V ALTVALIDOUTPUT -39------NCIASHOLDMODEGND -40(24)-----------------7J1B-65V/SMODEGND -41 (24)-----------------7J1B-63ALTHO~= SYNCGND -42------NCIAS ● SYNCGND -43------NCADCVALID -44(24)-----------------9J1-12v/s ● SYNCGND -45------NCGEAR+ FLAPSDOWN -46 (24)-----------------FIG.4-15RESERVEDSPARE -47HEADINGRATEDISABLE -48(24)----------------FIG.4-12ELEVTACH(+)

I-49(24)-5--------------13J1-.N

ELEVTACH(-) -50(24)-’=~-fi------------13J1-tELEVSERVOPOSITION(X)

1-51 (24)----------------13J1-P

ELEVSERVOPOSITION(Y) -52(24)---& -- ------ 13J1-RELEVSERVOAMPLOUTPUT(+)

1

-53 (20)-------1~1------- 13J1-A,llJ1-WACCELEROMETERTEST -54(24)-------::------- ~::~A;:4,17J1-2,

ELEVSERVOAMPLOUTPUT(-) -55(20)-------’=1--- --- 13Jl~B,llJ1-XAILERONTACI-I(+)

1-56 (24)---------------- 12J1-L

AILERONTACH(-) -57 (24)---------J=!-- 12J1-NAILERONSERVOAMPLOUTPUT(+) -58 (20)--------------=-

~1

12J1-BAILERONSERVOPOSITION(X) -59(24)--=---------~-’-12J1-PAILERONSERVOAMPLOUTPUT(-) -60(20)-!-~--------~1- 12J1-AAILERONSERVOPOSITION(Y) -61(24)-1=’------------ 12J1-RRUDDERSERVOAMPL(+) o-62(20)------ -- -- --- 14J1-ARUDDERSERVOPOSITION(X)

j#-63(24)fi-- ---------- 14J1-P

RUDDERSERVOAMPL (-) u-64 (20)----- - -- -- --- 14J1-B

RUDDER SERVO POSITION - (Y) -65 (24)~-------------- 14J1-R

RUDDER TACH (+) 0+-66 (24)---------- -- -- 14J1-L

RUDDER TACH(-) 1OJ1B-67(24)----------W -- 14J1-N


Page538Ma~25/90

Use or dmclosure of Information on this page IS sub)ect to the restrictions on the title page of this ~ocum nt,

Honeywell WME!AN’ECITATION n/V

AUTOPILOTCONTROLLERPC-500


llJ1-A(24)-----------------

I

-B (24).fi.-------------c (24)-,-;-------------

1OJ1A-7,17J1-51OJ1A-261OJ1A-1,17J1-1

TURNKNOB CWTURNKNOB WTURNKNOB CCW

4-D (24)--& -------------E (22)-------------------F (22)-------------------G (22)-------------------H (24)------------------

1OJ1A-27FIG4-I (SH1)FIG4-11IIJ1-L,FIG.4-11FIG.4-11

TURNKNOB CT28VANNPOWER(NIGHT)TURNKNOBOUT

{

cOF DETENTSWITCH NO

NC

O-28VEDGELIGHTINGLIGHTINGGNDA/P ENGINPUT+28VYD ENG

LOWBANKLIMITA/PENGSELECT

-J ------NC-K ------NC-L (22)------------------llJ1-G,FIG.4-11-M (22)------------------F1G4-11-N (24)------------------7J1A-93-P (24)------------------::~-P~~:JIB-33,

-R (24)------------------10JiB-35-s-T

YD ENGSELECTSPARESPARE

+]-U (24)------------R-- FIG.4-6

------------ -- -

[-+ :! [:;}--~-$-----:Y-----

1OJ1B-53,13J1-A--- - ------------ 1OJ1B-55,13J1-B

PITCH WHEEL +PITCH WHEEL [ELEV SERVO AMPL-ELEV SERVO AMPL

A/PTEST+15VDCSOFTRIDEMODEGNDPOWERGND

-Y (24)------------------FIG.4-13-Z (24)------------------1OJ1B-27-a (20)------------------DC POWERGND-bSPARE

+28V DC A/P ENG ● TCSSEL -C (24)---;--------------1OJ1A-3,12J1-F,13J1-G7J1A-71,8J1-r,HDGMODEGND -d (24)------------------65J1B-43

SPARELAMPTESTGND

-e-f (24)------------------7J1A-54,

16J1-16,LAMPTESTSWITCHFIG.4-2FIG.4-1 (SH1)

-g (22)-------------------h (22)------------------

llJ1-j(22)------

h

O-5VLIGHTING28VANNPOWER(DAY)CHASSISGND


Page539May 25/90

Use or disclosure of InformalIon on this page IS subject to the restnct!ons on the title pag~ of thts document.

Honeywell UAYJIPANCECITATION n/V

Function

MOTOR INPUT{

+(CCW DRUM ROTATION) -SERVO POWER GND

POSITION SYNCHROEXC26 VAC,400 HZ { :

CLUTCH EXCITATION

TACH SHIELDTACHOMETER OUTPUT

{+

(CCM DRUM ROTATION) -

{

xPOSITION SYNCHROOUTPUT Y

z

SPARES

* Refer to Para 4.1.3.3.F.

AILERONSERVOSM-~00

ConnectorPin

$12Jl:~~~:j---------------

u----------------c (20)------------------

-D (24)-------------------E (24)------------------

[

-F (22)-------------------G ------NC-H ------NC

1-J-K-L-N-P

3

(22)------------7-----

------NL

Connects To

1OJ1B-6O1OJ1B-58SERVOPWRGND, 1OJIA-4*1OJ1B-291OJ1B-221OJIA-3, llJ1-~

IOJIB-561OJ1B-571OJ1B-591OJ1B-61


22-14-00Page540May 25/90

Use or disclosure of Information on thw page IS subject to the restrictions on the title page of this oocument.

Honeywell W!!WANCECITATION n/V

ELEVATORSERVOSM-200


MOTORINPUT[+

t13J1-A(20)--;-------------

(CCWDRUMROTATION)- -B (20)_~ -------------SERVOPOWERGND -c (20)------------------

POSITION SYNCHROEXC H[

-D (24)------------------26 VAC,400HZ c -E (24)------------------

-F (22)------------------CLUTCHEXCITATION -G (22)------------------

-H (22)-------------------J ------NC

TACHSHIELD -K (24)----TACHOMETEROUTPUT

[ t-L (24)----R ----------~

(CCWDRUMROTATION)~ -N (24)----o -----------

{

x $-P (24)----~-----------POSITION SYNCHROOUTPUT Y -R (24)---~~-----------

z -s ------NC

[

-MSPARES -T

-u13J1-V

* Referto Para4.1.3.3.F.

A1 CITATIONII ONLY.

A2 CITATION V ONLY.

Connects To

1OJ1B-53,llJ1-W1OJ1B-55, llJ1-XSERVOPWRGND, 1OJ1A-4*DC POWER GND1OJ1B-71OJ1B-5

2

1OJ1A-3, llJ1-c1OJ1A-3, llJ1-cDC PWRGND

1OJ1B-5O10JIB-49

lc1Jlf3-51lCJIB-52


Page541May 25/90

Use or dwclosure of Information on th!s page IS subject to the restrictions on lhe title pagE of this document

Honeywell MNE!ANCECITATION V

RUDDER SERVOSM-200

Function Connector Pin1

MOTOR INPUT{

+#

14J1-A (20)-71- -------------(CCW DRUM ROTATION) - -B (20)-& -------------SERVO POWER GND -c (20)------------------

POSITION SYNCHRO EXC ii<

-D (24)------------------26 VAC, 400 HZ c -E (24)------------------

-F (22)-------------------G ------NC

CLUTCH EXCITATION -H ------NC-J (22)------------------

Connects To——

1OJ1B-621OJ1B-64SERVO PWRGND, 1OJIA-4*1OJ18-321OJ1B-311OJ1B-I2

DC PWR GND

TACH SHIELD.. -K (24)---------XTACHOMETER OUTPUT

<+’ -L (24) 1---------j-+- ----- 1OJ1B-66

(CCW DRUM ROTATION) - -N (24)___-+~-;_- 10JIB-67

{

x -1-P (24)--------7= ----- 1OJ1B-63POSITION SYNCHRO OUTPUT Y -R (24)--------J~------- IOJIB-65

z -s ------NC “

{

-MSPARES -T

-u14J1-V

* Referto Para4.1.3.3.F.


22-14-00Page 542

Mar-15/89Use or disclosure of u’tformatton on this page is subject to the restrictions on the title page of this document.

Function

YAWRATEGYRORG-204


26 VAC,400HZ 15J11~{~~]l~l~[~jjll~~~l~l~FIG.4-3 (SHT3)POWERGND AC GNDCHASSISGND -3 (22)---,-------,RATEOF TURN

{

+

1

-4 (24)--j~i--------- 65J2A-77(RTTURN)

-5 (24)--~1-------------65J2A-78RATEOF TURNVALID -

{-6 (24)------------------DCGND

(4.5V) + 15J1-7(24)----C+------------65J1B-3


Page 543Mar 15/89

Use or dmclosure of intormatlon on this page w subject to the restrtctlons on the title pag ? of this document.

Honeywell tiAWJEPANcECITATION n/V

V-NAVDISPLAY/CONTROLLER(PILOT’S)VN-212


115V 400Hz[H 16J1-1(24)------------------FIG.4-3 (SH1)c -2 (24)------------------ACGND

[O-5V LIGHTINGPOWER : -3 (22)------------------FIG.4-2

-4 (22)------------------ACGNDSPARE -5ALTERRORAC -6 ------NC

SPARES{:;-9

+28V DC INPUT -10(22)-----------------FIG4-1 (SH1)CHASSISGND -11(22)-------

*SIGNALGND -12 (22)-----------------SIGGNDSPARE -13------NCCOARSEALT

[+15 V REF

1-14(24)-----~T---------9J1-53

RETURN -15(24)-----~---------9J1-54SHIELDEDWITH16J1-37

LAMPTESTGND -16 (24) ----------------- 7J1A-54, llJ1-f,LoAD5mA@15v LAMP TEST SWITCHALT ALERT HORN GND -17(24)-----------------TO ALERTHORN(-)120m’ MAXALTALERTLAMPGND -18 (24)-----------------18J1-g120mA MAXSPARE -19ALT<1000FT -20(24)-----------------7J1B-24V-NAVMODEARM -21------NCVERTICALDEVIATIONVALID -22(24)-----------------65J1A-76,7J1B-9ALTITUDEPRESELECTVALID -23(24)-----------------65J1A-96TO/FROMNULL -24 (24)-----------------7J1B-39ALTERROR -25 (24)-----------------7J1B-22ALTERROR -26------NC

[+

J-27 (24)----~1----------7J1B-15,65J2B-39VERTICALDEVIATION _-28 (24)---------------7J1B-14,65J2B-38

VNAVMODEGND -29(24)-----------------7JIB-25TO/FROM

[+ TO

1-30(24)---F?-----------65J2B-11

MINLOAD5,000OHMS + FROM -31(24)---v-----------65J2B-12RANGE FROM R-NAV GND -32 ------NC+V RANGE VALID MIN 16J1-33(24)-----------------FIG.4-17LOAD 5,000 OHMS


22-14-00Page544Ma~-25/90

Use or disclosure of mformatlon on this page s sub!eci to the restrictions on the title page of this :~ocum nt.

Honeywell klNWYANcECITATION V

Function

V-NAV DISPLAY/CONTROLLER (PILOT’S) (con~)VN-212

RANGE 40 MV/MI

{

+

MIN LOAD 10,000 OHMS -

ADC VALID +28V

COARSE ALT SIG

{

HADC REF 26 V AC

c

{

SINFINE ALT INPUT Cos

RET

Connector Pin I Connects To

J16J1-34 (24)--7~} ----------- 7J1A-32,65J2B-102l;i

-35 (24)--*------------ 7:1A-33,65J2B-101

-36 (24)-----------------9dl-12SHIELDEDITI-I16J1-14

Y-37(24)----------------9;1-52,1OJ1A-21-38(24)-----------------9(1-1,18J1-E

-39(24)--

]1

----------- - 9;1-2,18J1-F-40 (24)-----------ffiy- 9J1-49-41(24)-------------~- 9J1-50

16J1-42(24)----------w-- 9J1-51

L JUMPER AT CONNECTORNOTE 1

NOTE: 1. Jumper is provided so that when VNCC is removed.The demods in the ADC have a reference.


22-14-00Page-5~5

Mar 15/89Use or dwclosure of reformation on this page IS subject to the restrictions on the title pa~g,? of this document.

Honeywell #NNIFANcECITATION n/V

Function

PILOT’SNORMALACCELEROMETERAG-222

ConnectorPin ~ects To

+15VDC POWER 17J1-1(24)------------------IOJIA-1,llJ1-COUTPUT1.5V/G -2 (24)--

1--------------7J1B-21,1OJ1A-44

SIGNAL GND-VDC POWER

L-m-_ SIGNALGND

20K,l/2W-3 (24)------------------SIGNALGND-5 (24)------------------llJ1-A,1OJ1A-7

TEST 17J1-6(24)------------------1OJ1B-54


22-14-00Page 546Ma~-25/90

Use or dmclosure of mformatlon on thw page IS subject to the restrtcttons on the title page of Ihls ~ocum nt.

,10J1B-54

Honeywell KNM!!AN’ECITATION V

BAROMETRICALTITUDEINDICATOR(PILOT’S)BA-141


{

HO-5VAC INSTLIGHTS

cSPARESPARE

{

H26 V AC 400HZ

cCHASSIS

SPARES

18J1-A(24)------------------

-B (24)-------------------c-D-E (24)------------------

-F (24)-------------------G (22)--------

/%

(-H-J

[NSIGNALGNDTOADC

1

:P (22)--,=-------------ACT COARSE +15REF -R (24)--r+-------------SPARE -sALT COARSE SIGNAL -T {z4)-JUi-?------------

{

SIN

i

-U (24)-------=--------FINEALT Cos -V (24)------J-!--------

COM -W (24)-------’=’--------BARO

{

LOW

I

-X (24)-----------9-- ---CORRECTION WIPER -Y (24)----------J-4- ---

EXCITATION -Z (24) ----------~uJ- ---

+28V DC ALTVALID

{

-a (24)-------------------b

SPARES::-e

ALT ALERT

{

-f (24)------------------

LIGHT 18J1-g(24)------------------

Connects To

AC LIGHTINGCONTROLFIG4-2AC PWRGND

9J1-1,16J1-38

9J1-2,16J1-39

9J1-79J1-6 “

9J1-5

9J1-89J1-99J1-109J1-619JI-609J1-59

9JI-12

7JIA-8

16J1-18


22-14-00Page 547

Mar 15/89UseordisclosureofInformationonthispage IS subject to the restrictions on the title pag: of this document.

Honeywell MIURANCECITATION V

PILOT’SRADIOALTIMETERRECEIVER/TRANSMITTERRT-300


{

20J1-ASPARES -B

-cTESTINHIBIT -DOUTPUTCIRCUITTEST “ -E (22)------------------DC GNDTRACKINVALIDGND -F

[

-GSPARES

:!L-K

400 OR 500 FTTRIP (TRIP PT #4) -Lf15 VDC COM -M ------NCOUTPUT COM I-N (24)------------J~F --

1ALTTRIPCOM

I

-P (24)-----------------50 FTTRIP (TRIPPT #3) ------NCSPARE :; ------NCTEST -T (24)-----------------

1200FTTRIP (TRIPPT#l)

+

-U (24)-----------------250FTTRIP (TRIPPT #2) -V (24)----------------ALT OUT -W (24) ------------4GL---

AUX OUTPUT -X (24)------------------

7J1B-19,65J2A-70DC GND

65J2B-76

7J1B-467J1B-5265J2A-69

7J1B-18

FLAGWARN -Y (24)------------------7J1B-35,

+15VDC65J1A-78

-z ------NC-15VDC -a ------NCPWRGND -b (24)------------------DCGND+28VDC 20J1-c(24)------------------FIG4-1 {sHTI)


22-14-00

I

Page 548Mar 15/89

UseordisclosureofinformationonthispageISsubjecttotherestrictionsonthetitlepageofthisjocument

PILOT’SR;~O]&ONTROLLER

Function ConnectorPin ConnectsTO——

sIGNALGND 23J1-A(22)-------------------SIGNALGND

CRS26 VAC<

H i-B (22)--------- --~[--- [;GFW#-;ND

cl?S 26 V AC c -c (22)--------- --u----

{

x -D

RS SELECT Y -E

z -F

(24)----------~-=- 65J2A-4~Ill

T~24)-------.-.--fl-~--65J2A-46

(24)------------%1--65J2A-47

;RSPULLDCT\DGPULLSYNC

~DG26 V AC<H

IDG26 V AC c

{

x

HDGSELECT Y

{-+5 V LIGHTING “+

CHASSISGND

SPARES

-G,(24)------------------1I5J1-10-H (24)------------------115JI-12

~-J (22)--------- ------- ]:Gp:~3GND-K (22)---------1-&’----

1-L (24)-----------‘-in;-65J2A-48

-M (24)-----------‘:-;-- 65J2A-49

-N (24)------------~~-- 65J2A-50

-P (22)------------------F]G.4-2-R (22)------------------AC GND

-s (22)------------------cHASSISGND


Paae 549

Mar”15/89

Use or disclosure of mtormation on this page IS subject to the restrictions on the title paqe of thw document

Honeywell WMRANCECITATION V

Function

115VAC,400HZ PWRSELFTEST

+15VDCPWRGND

/x

ROLLATTITUDE Y

{

wRELAYCONTACT1

!:

[

NC

RELAYCONTACT2 NOw

CHASSISGND

TESTPOINT1TESTPOINT2-15VDCSIGNAL GNDTEST POINT 3

ROLLRATEMONITORRZ-220

ConnectorPin ConnectsTo1

I57J1-A(22)----------------- FIG.4-3 (SH1)-B (22)------------------- FIG.4-13,

57J1-N-c‘---::!!-------~--f---Ac p~~ GN~-D (22)-E (24)--------------------lJ1-P.65J2A-18-F (24)--------------------lJ1-q-,

65J2~-19-G (24)-------------------- lJ1-r, 65J2A-20

-H (22)--------------------FIG. 4-13,1J1-R-J (22)-------------------- FIG.4-13-K (22)--------------------FIG.4-13,

1OJ1B-3O-L (22)--------------------FIG.4-13,

1OJ1A-49-M -----NC-N (22)--------------------FIG.4-13,

57J1-B-P (22)-------

A

-R -----NC-s -----NC -

-----NC1

57J1-V-----NC


22-14-00Paue 550Mar”15/89Useordisclosureofinformationonthis page IS subfect to the restncttons on the title page of thts ~.locument.

Honeywell WMFANC’CITATION n/V

PILOT’S WEATHERRADARR/T/AWU-650


28 VDC PRIMARYPOWER 59J1-A(20)--------------------28VDCPOWER,FIG4-1

28 VDC PRIMARYPOWER -B (20)--------------------28VDC POWER,FIG4-1

DC PWRGND -X (20)--------------------DC PWRGNDDC PWRGND -W (20)--------------------DC PWRGNDALTERNATECONTROLBUS (HI) -a ------NCALTERNATECONTROLBUS (LO) -b ------NC

PRIMARYCONTROLBUS(HI)#

-C (24)-----------------O-63J1-FPRIMARY CONTROL BUS (LO) -d (24) ---------------- J -1

CONTROL BUSSHIELD -p (24)-------a Y-: :;:;::

REMOTEON -U (24)--------------------63J1-E

GNDFOR429STABTRANSMITONKEYSPAREEA ROM ERASESPAREGNDFORINVERTEDMT

REACT COMPENSATION OVERRIDEGNDFOR200mv/DEGSHIELDGNDSIN PITCH(HI)OR429SIN PITCH(LO)OR429

-T -----NC-c -----NC-v -----NC

-----NC1 -----NC-Y -----NC

-----NC1; [24)‘-------------------GND

:: iiii:~:-------------q -

1-K (24) ----------------t-l - lJ1-EE

-L (24) ----------------v - lJ1-1)11

SINROLL(HI) h

i-M (24)----------------id- lJ1-v

SINROLL(LO) -N (24)------------------ lJ1-w+-- s~IELDGND

STBLN400HZ REF IN 10V -H ------NCSTBLN400HZ REF IN 26V -z ------NCSTBLN400HZ REF IN 115V

k-D (24)-----------------OFIG4-3 (SH1)

STBLN400HZ REF INCOM -G (24)----------------!-~-- ~~I~~~GND

LEFTEFISCONTROLBUS (P) -m (24)-T~$---------------65J2B-32,1

LEFTEFISCONTROLBUS (N) k59J1-n(24)-+-L---------------65J2&33

ii


22-14-00Pacie551May-25/90

Use or disclosure of !nformatlon on this page IS subject to the restrictions on the title pagt, of this document,

Honeywell ~iwJfrANcECITATION n/V

Function

PILOT’S WEATHER RADAR R/T/A (cent)WU-650

CENTER CONTROL BUS (P)CENTER CONTROL BUS (N)RIGHT EFIS CONTROL BUS (P)RIGHT EFIS CONTROL BUS (N)

PICTURE BUS SHIELD GNDLEFT EFIS PICTURE BUS (P)

LEFT EFIS PICTURE BUS (N)

CENTER PICTURE BUS (P)

CENTER PICTURE BUS (N)RIGHT EFIS PICTURE BUS (P)RIGHT EFIS PICTURE BUS (N)

Connector Pin Connects To—,

59J1-t -----NC-r -----NC

-----NC:; -----)JC

-q @~)---T I-9(2+--1-1------------- 65J2E’-30Jlt-h (24)-------------------65J2E-31

<I

-i (24)--------t-r-----~o--63J1-M-j ~::~:~~-----LCh-------- 63J1-L-k

59J1-s-----NC


22-14-00Page552May-25/90useor disclosure of !nformat!on on thts page is sub!ect to the restrictions on fhe title page of th!s Iocument.

Honeywell W!UN’”c’CITATION V

Function

+28 VDC

+28 VDC RTNLIGHT GND+28 V LIGHTS+5 V LIGHTSMASTER FAULTCTRL BUS HICTRL BUS LOSHIELD GNDREMOTE ONPICTURE BUS HIPICTURE i3USLOPICTURE BUS SHIELDFSB1FSB2SPARESPARECHASSIS GNDRESERVEDRESERVEDSPARE

PILOT’S WEATHER RADAR INDICATORWI-650

ConnectorPin

63J1-N (20)---------------------A (20)---------------------D (22)---------------------c -----NC-s (22)---------------------J ------NC-F (24)---1C~

$------------

-G (24)------------------------- - J

:: (24)----------1 ---------

[-M (24)-------R- ----------L (24)------* - ----------w -----------?-H (24)---------------------K ------NC-u-v-B (20)__--_---P &-R

63J1-X

ConnectsTo

FIG. 4-1 (SH 1)DC PWR GNDLIGHT GND

FIG. 4-2

59J1-c59J1-d

59J1-U59J1-i59J1-j

FIG. 4-7


Table 501 (cent)22-14-00

Pa~e 553Mar”15/89UseordisclosureofIntormatlonon this page is subject to the restrictions on the title page of Ihls document,

Honeywell IM!E!!ANCECITATION V

PILOT’S WEATHER RADAR INDICATOR (cent)

WI-650


HORIZ REF HI 63J2-L ------NCHORIZ REF LO -A ------NCVERT REF HI -M ------NCVERT REF LO -K ------NCDC RTN -G ------NCSTBY -N ------NCBLUE VIDEO INPUT HI -T ------NCBLUE VIDEO INPUT LO -D ------NCGREEN VIDEO INPUT HI ------NCGREEN VIDEO INPUT LO x ------NCRED VIDEO INPUT HI ------NCRED VIDEO INPUT LO :: ------NCSHIELD COMMONRANGE CODE OUTPUT RO :: :-----NCRANGE CODE OUTPUT RI -P ------NCRANGE CODE OUTPUT R2 -B ------NC

RANGE CODE OUTPUT R3 -v ------NCVIDEO SEL (P) -H ------NCVIDEO SEL(N) 63J2-R------NC


22-14-00Page 554

Mar 15/89Use or disclosure of information on this page is subject to the restrictions on the title page of lhls document.

Honeywell MUFF*””CITATION V

PILOT’S SYMBOL GENERATORSG-605/805


ADI VIDEO (+) 65J1A-1I

(24)q~-- ~~~~~-jl=~~ ;:;-;;ADI VIDEO (-) ~$ (24)-1-1--ADI VIDEO SHIELD GND (24)-~Z 1ADI COLOR O (+) ~~ (24)---4-;----------- 3J1-50ADI COLOR O (-) (24) ----------------- 3J1-51ADI COLOR O SHIELD GND ~; (24)--Y ‘ADI COLOR 1 (+)

7(Z4)-Zt- ----------- 3J1-46

ADI COLOR 1 (-) ~~ (24)--1-1------------- 3J1-47ADI COLOR 1 SHIELD GND (24)--Y ~ADI COLOR 2 (+) -lo (24)-T~l-i----------- 3J1-42

ADI COLOR 2 (-) -11 (24)-A-’------------- 3J1-43ADI COLOR 2 SHIELD GND -12 (24)--Y ‘ADI COLOR 3 (+) -13 (24)--=;----------- 3J1-38ADI COLOR 3 (-) -14 (24)-J-1------------- 3J1-39ADI COLOR 3 SHIELD GND -15 (24)--YADI FLYBACK (+)

t-16 (24)-7=- ----------- 3J1-60

ADI FLYBACK (-) -17 (24)-A-[- ----------- 3J1-61

ADI FLYBACK SHIELD GND ;;; ::;]--fADI VALID

i

----- ----------- 3J1-15ADI R/S (+) ~~~ @~\-JC~- ----------- 3J1-58ADI R/S (-) --- ------------- 3J1-59ADI R/S SHIELD GND -22 (24)--YADI SR (+)

/

-23 (24)----------- -+;- 3J1-7

ADI SR (-) I i- 3J1-8-24 (24)---------------~-- 3J1-3fj

ADI CS SR (+) -25 ------NCADI CSSR (-) -26 ------NC

ADI CS VALID -27 ------NC

HSI VIDEO (+) -28 (24)--a--1

----------- 2J1-54HSI VIDEO (-) -29 (24)-J-1------------- 2J1-55HSI VIDEO SHIELD GND -30 (24)--VHSI COLOR O (+)

t-31 (24)--= ----------- 2J1-50

HSI COLOR O (-) -32 (24)-~-l------------- 2J1-51HSI COLOR O SHIELD GND -33 (24)--YHSI COLOR 1 (+) -34 (24)--~

+----------- 2J1-46

HSI COLOR 1 (-) -35 (24)-J-!------------- 2J1-47HSI COLOR 1 SHIELD GND -36 (24)--~#HSI COLOR 2 (+) 65J1A-37 (24)-l~T------------- 2JI-42


Page 555Mar 15/89

Useordisclosureofinformationon thm page IS sub!ecf to the restncttons on the Mle paq! of thts documenf.

Honeywell WNRANCECITATION V

Function

HSI COLOR 2 (-)HSI COLOR 2 SHIELD GNDHSI COLOR 3 (+)HSI COLOR 3 (-)HSI COLOR 3 SHIELD GNDHSI FLYBACK (+)HSI FLYBACK (-)HSI FLYBACK SHIELD GNDHSI VALIDHSI R/S (+)HSI R/S (-)HSI R/S SHIELD GNDHSI SR (+)HSI SR (-)

HSI CS SR (+)HSI CS SR (-)HSI CS VALID

ADI X DEF OUT (+)ADI X DEF OUT (-)ADI X DEF SHIELD GNDADI Y DEF OUT (+)ADI Y DEFOUT (-)ADI Y DEF SHIELD GNDHSI X DEF OUT (+)HSI X DEF OUT (-)HSI X DEF SHIELD GNDHSI Y DEF OUT (+)HSI Y DEF OUT (-)HSI Y DEF SHIELD GNDDC811 DATA (+)DC811 DATA (-)

RESERVED

PILOT’S SYMBOL GENERATOR (cent)

SG-605/805

Connector Pin 1

65J1A-38-39-40-41-42-43-44-45-46-47-48-49-50-51

(24)-@-----------(24)--(24)--C*

4-----------

(24)-~1- -----------(24)--Y[;:;-~~fI

-------------- -------------

(24)--’(24j----

t

-----------(24)-i? .-----------(24).-Y---------(24)--

$(24)----------- ++..(24)----------- --=-

L_-

-52 ------NC-53 ------NC-54 ------NC

I-55 (24)-+ ------------56 (24)-- -+ ------------57 (24)---Y

I-58 (24)--1; ---------59 (24)-- ------------60 (24)=J-61 (24)--T= ------------62 (24)----ii____-63 (24)---Y-64 (24)---=

!----------

-65 (24)--J-1-------------66 (24)---Y

I-67 (24)------ ------ _-r-68 (24)-------------~1--

L --

65J1A-69 ------NC

Connects To——

2J1-4:!

2J1-382J1-39

2J1-602J1-61

2J1-IL2J1-582J1-51!

2J1-72J1-82J1-3fi

3J1-13J1-2

3J1-93J1-lC

2J1-12J1-2

2J1-92J1-lC

115J1-34115J1-35SHIELD GND


22-14-00Page 556

Mar 15/89UseordisclosureofinformationonthispageIS subject to the restrictions on the title page of this document.

Honeywell WWI!A”CECITATION n/V

PILOT’S SYMBOL GENERATOR (cent)SG-605/805


RESERVED 65J1A-70------NCRESERVED -71 ------NCRESERVED -72 ------NCVALIDIN 1 SRNDMEVLD -73 (24)-----------------C164J1A-46VALIDIN 2 SRNVRTDV VLD -74 (24)-----------------:~5:~~A-74,

VALIDIN3 SPDDEVVLD -75 (24)-----------------FIG4-4VALIDIN4 VNAVDEVVLD -76 (24)-----------------16J1-22,7J1B-9

VALIDIN 5 SRN LATDV VLD -77 (24)-----------------UM:J;B-91,

VALIDIN 6 RADALT 1 VLD -78 (24)------------:----20J1-Y,FIG.4-57J1B-35

VALIDIN 7 RADALT 2 VLD -79 ------NCVALIDIN8 LRN1LATDV VLD -80 (24)-----------------C164J1B-99(ADF2VALIDWHENDIN6= GND)VALID IN 9 LRN1VRTDV VLD -81 ------NCVALIDIN1OADFVLD -82 (24)-----------------164J1B-99

VALIDIN1lFDC VLD -83 (24) ----------------- 7J1B-47

VALID IN12 HDG 1 VLD -84 (24) ----------------- 6J1-eVALID IN13 ATT 1 VLD -85 (24) ----------------- lJ1-GG,7J1A-19

VALID IN14 CS/SG VLD -86 ------NCVALID IN15 ARINC O VLD -87 - -----NCVALID IN16 LRN 1 28 V WPTALERT -88 ------NCVALIDIN17ROTVLD -89 ------NCVALIDIN18TCS 65J1A-90(24)-----------------1OJ1B-19

~: ALLVALIDSARE+28V DC.


22-14-00Page 557May25/90

Use or dmclosure of mformatlon on this page IS subject to the restrlcttons on the tttle pag ? of this document.

Honeywell !H!WY’”c’CITATION V


Function Connector Pin

VALID IN19 SPARE 65J1A-91 ------NCVALID IN20 HDG 2 VLD -92 (24)-----------------

VALID IN21 ATT2 VLD -93 ------NCVALID IN22 AP ENGAGED IN -94 (24)-----------------

VALID IN23 TK DETENT IN -95 (24)-----------------

VALID IN24 APS VLD IN -96 (24)-----------------

DIN O SYMGEN L/R IDO -97 ------NCDIN 1 DC811 -98 (24)-----------------DIN 2 Si7BRG3/4 -99 (24)-----------------DIN 3 ADFIBRG 3/4 -100 (24)-----------------DIN 4 ASCB D/S -101 ------NCDIN 5 EFIS D/S -102 (24)-----------------DIN 6 CROSSIDE SENSOR DISABLE-103 (24)-----------------DIN 7 ROT ON/OFF -104 ------NCDIN GND -105 (24)-----------------ATT PULSE OUT 65J1A-106 ------NC

NOTE : ALL VALIDS ARE +28 V DC.

Connects To.—

C2J2-X

1OJ1B-11

llJ1-H,IOJIB-15FIG. 4-11

16J1-;?3

65J1A-10565J1A-10565J1A-105

65J1A-10565J1A-105

PROG GND


22-=14-00Page558

Mar 15/89Use or disclosure of information on this page IS sub!ect to the restrictions on the title page of thm jocument

Honeywell W!UF’NCECITATION V


SG-605/805


DIN 8 CPMN ON/OFF 65J1B-1 (24)----------------- 65J1A-105DIN 9 WIND PO/XY -2 ------NCDIN 10 +5V ROT VAL -3 (24)----------------- 15J1-7DIN 11 R ALT IDO -4 ------NCDIN 12 R ALT ID1 -5 ------NCDIN 13 TRANSITION ON/OFF ~; (24)----------------- 65J1A-105DIN 14 LRN1 PHASE (P/S) ------NCDIN 15 ADI ON HSI (OFF/ON) -8 ------NCDIN 16 SRN2 ID1 ------NCDIN 17 ADF 1/2 ~?O (24)----------------- 65,J1A-105DIN 18 MLS 1/2 -11 ------NC

DIN 19 wow -12 (24)----------------- FIG 4-7DIN 20 GSPD IDO -13 (24)----------------- 65J1A-105DIN 21 GSPD IDI -14 ------NCDIN 22 ATT # IDO -15 ------NCDIN 23 ATT# ID1 -16 ------NCDIN 24 AT TGL IDO -17 ------NCDIN 25 AT TGL ID1 -18 ------NCDIN 26 ATT2 P/S -19 ------NCDIN 27 RESERVED -20 ------NCDIN 28 FLIP -21 ------NCDIN 29 HDG1 DEF -22 ------NCDIN , 30 HDG1 F/S-M/T -23 (24)----------------- TO :/S SWITCHDIN 31 HDG # IDO -24 ------NCDIN 32 HOG # ID1 -25 ------NCDIN 33 HD TGL IDO -26 ------NCDIN 34 HD TGL ID1 -27 ------NCDIN 35 HDG2 DEF -28 ------NCDIN 36 HDG2 F/S-M/T -29 (24)----------------- TO F/S SWITCHDIN 37 HDG2 P/s -30 ------NCDIN 38 S BRG CD/CS 65J1B-31 ------NC


Table 501 (cent) 22-14-00Page 559

Mar-15/89Use or disclosure of information on this page is subject to the restrictions on the title pag: of this document,

Honeywell U2M?*NCECITATION n/V

PILOT’S SYMBOLGENERATOR(cent)

Function

DrhlDINDINDIN

DINDINDINDINDINDINDINDIN

DINDINDIN

DIN

DINDINDIN

DINDINDINDINDINDINDINDINDIN

DINDIN

A 1

39404142

4344454647484950

515253

54

555657

5859606162636465666768

.

SRNSRC IDOSRNSRC 101DMETTNTTL

SRNTGL A 1HSI MODERESERVEDLNAVMODEGNDGA MODEGNDASELARMMODEGNDASELCAPMODEGNDtJDGSELMODEGND

RESERVEDALT HOLDMODEGNDV/SHOLDMODEGND

IASHOLDMODEGND

MACHHOLDMODEGNDGS ARMMODEGNDGS CAPMODEGND

VNAVARMMODEGNDVNAVCAPMODEGNDLRN1SRCNORM/ALTLRN1BRGCARD/CASENAVARMMODEGNDNAV CAPMODEGNDBC ARMMODEGNDBC CAPMODEGNDVORAPRARMMODEGNDVORAPRCAPMODEGND

SG-605/805


65J1B-32------NC~:: y;-----------------

- . - - - - -- - - - - - - -- -

-35(24)-----------------

-36------NC-37------NC-38------NC-39(24)------------------40(24)------------------41(24)------------------42(24)------------------43(24)-----------------

-44 ------NC-45 (24)------------------46 (24)-----------------

-47(24)-----------------

-48(24)------------------49(24)------------------50(24)-----------------

-51 (24)------------------52 (24)------------------53 ------NC-54 ------NC-55 (24)------------------56 (24)------------------57 (24)------------------58 (24)------------------59 (24)------------------60 (24)-----------------

65J1A-105C164JIA-3C164ilB-64,C2J1-:{.

7J1A-7’27J1B-M37J1B-?l, 8J1-d7JIB-72, 8J1-e;;;:-;1, 8J1-r,

7JIB-75, 8J1-b7J1B-76, 8JI-Z,l15t11-477J1B-77, 8J1-X,115J1-487J1B-787JIB-69, 8J1-g7JlB-70,8Jl-h,ICIJIB-217J1B-73, 8J1-S7JlB-74, 8J1-T

7J1A-857J1A-857JlA-6f3, 8J1-J7JIA-67> 8J1-K7J1A-877J1A-83

LRN1BG/DA 65J1B-61~--~--NC

tiroundthispinif MLS is installed.

InterconnectInformationTable501(cent) 22-14-00

Page560May25/90

Use or disclosure Of information on thts page IS sublect to the restrictions on the ttle page of this c ocument.

Honeyell ##~{(ANcE



DINDINDINDINDINDINDINDINDIN)IN)IN)IN)IN)IN

6970717273747576777879808182

LRN1 IDOLRN1 ID1LRN1 ID2LRN1 ID3LRN1 SRC IDOLRN1 SRC ID1SRN2 IDOLRN1 DT/OALRN TGL IDOLRN TGL IDlLRN1 MG/TULRN2 IDOLRN2 ID1LRN2 ID2

65J1B-62-63-64-65-66-67-68-69-70-71-72-73-74

65J1B-75

------NC(24)--------------------65J1A-105

(24)----------------- 65J1A-105(24)------------------ 65J1A-105------NC@:~::~-------------- 65JlA-~05------NC------tic------NC------NC------NC------NC------NC


Page 561Mar 15/89

Use or disclosure of information on this page IS subject to the restrictions onthe title pagf of tfis document.

Honeywell WWANCECITATION ii/V

PILOT’S SYMBOLGENERATOR(cent)SG-605/805


DIN 83 LRN2 ID3 65J1B-76 ------NCDIN 84 LRN2SRC IDO -77------NCDIN 85 LRN2SRC ID1 -78------NCDIN 86 AIRDATACMDDISABLE -79------NCDIN 87 SPARE -80------NCDIN 88 LRN1BRG3/4 -81(24)-----------------65J1A-105(ADF2BRG3/4WHENDIN6= GND)DIN 89 CITATION11/V -82(24)-----------------65J1A-105DIN 90 IRS1AN/DIG -83------NCDIN 91 IRS2AN/DIG -84------NCDIN 92 RADALT S/D -85------NCDIN 93 A/S,AOA,SPD IDO -86(24)-----------------65J1A-105DIN 94 A/S,AOA,SPDID1 -87(24)-----------------65J1A-105DIN 95 CS IN -88------NCDIN 96 COUPLE1/2 -89------NCDIN 97 STBYSELMODEGND -90------NCDIN 98 SPARE -91------NCDIN 99 ATT#1 WRAP -92 (24)----------------- 65JlA-105DIN 100ATT#2 WRAP -93------NCDIN 101ATT#3 WRAP -94------NCDIN 102ATT #4 WRAP -95------NCDIN 103RESERVED -96------NCDIN 104RESERVED -97------NCDIN 105FMSSINGLE/DUAL -98------NCDIN 106 A/S,AOA,SPDID2 -99------NCDIN 107CAARULES -1oo------NCDIN 108SPARE -101------NCDIN 109SYMGEN L/RIDI -102------NCRESERVEDDC IN (+) -103------NCRESERVEDDC IN (-) -104------NCRESERVEDDC OUT (+) -105------NCRESERVEDDC OUT (-) 65J1B-106------NC


Page562May-25/90

Use or disclosure of information on this page IS sub!ecl to the restrictions on the title page of this :]ocument

Honeywell WM!ANcECITATION V

Function

+28 V DC POWER

+28 V DC POWERHDG VALID IN28 V DC RETURN28 V DC RETURNCHASSIS GNDCHASSIS GNDSIGNAL GNDSIGNALGNDDISCRETEGNDTO/FRDC IN (+)TO/FRDC IN (-)

ONSIDEACREF (+)

ONSIDEAC REF (-)

#l PITCHX#1 PITCHY

#l PITCHZ

#1 ROLLX

#1 ROLLY

#l ROLLZ

#l HDGX

#l HDGY

#1 HDG Z

PILOT’SSYMBOLGENERATOR(cent)SG-605/805


}

65J2A-1(22)------------------PILOT28VDCPOWER,

-2 (22)------------------FIGURE4-1-3 ------NC-4 (22)------------------DC PWRGND-5 (22)------------------DC PWRGND-6 (24)------------------CHASSISGND-7 (24)------------------CHASSISGND-8 (24)------------------SIGNALGND-9 (24)------------------SIGNALGND-10(24)------------------CIISCRETEGND

-11------NC-12------NC

t

-13(24)------:-]---------26VAC,1, FIG4-3 (SH3)

+Ii

-14(24)------L---------ACGNDt-L-

!

----- SHIELDGND-15 (24)------------ -T=(- lJl_x-16 (24)------------ ----- lJ1-y

tii-17(24)---------------W-lJ1-z

!1-- SHIELDGND

-18(24)----------------- lJ1-p,57J1.E

1’-19(24)-------------~~-- lJ1-q,57J1-Ft:

-20(24)--------------L-- lJ1-~, 57J1-G?

IL-- SHIELDGND

-21(24)-------------[~-- 6J1-L

IL-22(24)---------------- 6J1-M

+ i65J2A-23(24)--------------IV--6J1-K

1 -- SHIELDGND


22-14-00Paae563

Mar”15/89UseordisclosureofinformationonthispageK subjecttotherestrictionsonthetitlepagtofthisdocument.

Honeywell WWFANcECITATIONV



SYS ASCBA DATA (+) 65J2A-24 ------NC

SYSASCBA DATA (-) -25 ------NC

SYS ASCBACLK (+) -26 ------NC

SYSASCBACLK (-) -27 ------NC

#1 HDGSYNC+ I-28(24)-------------1~~-

#1 HDGSYNC- b-29(24)--------------1-1-Y

L --

MFD G/S DEV DC IN (-) -30------NC

#1 LRN DSRTRK X -31 ------NC

#1 LRN DSRTRK Y -32 ------NC

??1 LRN DSRTRKZ -33 ------NC

#l LRN BRGX/SIN

I

-34(24)-----------fi----(ADF2X/SINWITHDIN6 = GND)#1 LRNBRGY/COM -35(24)-----------1-1---(ADF2Y/COMNWITHDIN6 = GND)#1 LRNBRGZ/COS I-36(24)------------ - --(ADF2Z/COSWITHDIN6 = GND) ,r#1 LRNBRGCOM

+-37(24)---------------

(ADF2COMWITHDIN6 = GND) -----

#l LRNTO/FROM(+) -38------NC#l LRNTO/FROM(-) -39------NC#1 LRNLATDEV (+) -40------NC#1 LRNLATDEV (-) -41------NCDH H -42(24)------------------

DHW 65J2A-43(24)------------------

ConnectsTo

6J1-U

6J1-V

SHIELDGND

C164J1A-61

C164J1A-33

C164J1A-47

C164J1A-33SHIELD GND

l15J1-53

115J1-54


Table 501 (cent)

22-14-00Paae 564

Mar”15/89Use or disclosure of mformatton on this page is sub]ecf to the restrictions on the !Itle page of this jocument.

Honeywell MllR”c’CITATIONV

Function

DH L

CRS SEL X/TACH +

.CRSSELY/TACH-

CRS SEL Z

SHIELDGNDHDGSELXTACH +

HDGSELY TACH-

HDGSELZ

SHIELDGNDVORBRGX/SINVORBRGY/COMVORBRGZ/COSVORBRGSP/COM

#1 ADF BRGX/SIN

#l ADF BRGY/COM

#l ADF BRGZ/COS

#1 ADF BRGSP/COM


ConnectorPin JonnectsTo

65J2A-44(24)------------------115J1-55

!-45 (24)-1?-------------23J1-D

-46 (24)-------------------23J1-Elit

-47 (24)--4--------------23J1-F

Y(24)--

i-48 (24)-l~i-------------~3J1.L

-49 (24)-j-;--------------23J1-MI]*

-50 (24)--III--------------23J1-N

J

I

-51 (24)~~------l~r-------C164J1B-11-52 (24)-----------------C164J1B-37

1[-53 (24)--------I:.I- ----- C164J1B-12-54 (24)-------b------- C164J1B-37

t-- -----

TSHIELD GND

-55 (24)-------=------- 164J1A-61

iit

-56 (24)-------1-[--------164J1A-33

-57 (24)-------~-!--------164J1A-47~lt

65J2A-58(24)-------- --------164J1A-33Y ------ --- SHIELDGND


Table 501 (cent) 22-14-00Page-565

Mar 15/89Use or disclosure of reformation on this page IS subject to the restrictions on the title pag? of this document.

Honeywell !WJJFANCECITATION V

Function

INNERMKR (+)MARKERCOMMON

MIDDLEMKR (+)

MFDLATSTEER

~LI~J~MKR(+)

SRNCRSDEV (+)SRNCRSDEV (-)

SRNGS DEV(-)

SRNGS DEV(+)

RADALT (+)RADALT (-)

SPEEDCMD(+)SPEEDCMD(-)

PITCHCMII(+)

PITCHCMD (-)

ROLLCMD(+)



65J2A-59(24)-----------------C164J1A-73-60 (24)-------*

-61 (24)-----------------C164J1A-60

-62 ------NC

-63-64-65-66

-67

-68

-69-70

-71-72

-73

~~~~~~~~-------------C164J1B-74

I(24)------~~r-------C164J1B-78,C2J2-E(24)------t-~------- :;::J;B-75,

Y - -------SHIE~DGND

!(24)------j~r-------C2J2-C,65J2A-66,

i IjC164J1B-75

(24)--------------- C164J1B-79,C2J2-DY

1-------- SHIELDGND

(24)---------------(24)-----------~-~fL-) FIG.4-5

-- SHIELDGND

{)(24) ----------- -----(24) ----------- -;-[- FIG= 4-4

i

<-- SHIELD GND

(24) ----------- -i?-- 7J1B-30

~ ‘ ‘ 7J1B-31-74 (24)-------------i-~-

( L SHIELDGND65J2A-75(24)-----------~-r~T-7JIA-29


Table 501 (cent)

22=-14-00Page 566

Mar 15/89Use or disclosure of Information on thm page IS subject 10 the restrictions on the title page of this document.

Honeywell WMR!’”c’CITATION n/V


Function Connector Pin Connects ToI

ROLL CMD (-) 65J2A-76(24)-------------*-4-L- 7J1A-30

Y--SHIELDGNDRATE OF TURN (+)

t-77 (24) ------------ ---- 15J1-4

RATE OF TURN (-) -78 (24)------------ t-!d-- 15J1-5

T -- SHIELD GNDAIR DATA CMD (+)

!-79 (24)------------ ----- 9J1-39

~1

AIR DATA CMD (-) -80 (24)------------*-!-l--9J1-33,7J1B-37.5VL-- SHIELD GND

STEER IN (+) -81 ------NCSTEER IN (-) -82 ------NCMFD LRNSELVALIN(P-ID2) -83 ------NC

MFD LAT STEER VALIN -84 ------NC

MFDNAV SELVALIN(P-IDO) -85 ------NC

MFD V/LDEVVALIN -86 ------NC

MFDGS DEVVALIN -87 ------NC

MFDDMEVALIN -88 ------NC

MFDTK DETENTVALIN -89 (22)------------------FIG ~-11 .

MFDAP ENGAGEDVALIN J-90 (22)------------------(SHT1)

MFDAPS VALIN -91 ------NC

MFD LNAV APP DOUT -92 ------NC

MFDTTLDIN 65J2A-93------NC


22-14-00Paqe 567May”25/90

Use or disclosure of mformatlon on this page IS subject to the restrictions on the title pa~; e of this document.

Honeywell M!WANCECITATION Ilfl



MFDDME TTN DIN 65J2A-94 ------NC

MFDMIDMARKDIN (5V) -95 ------NC

MFD PW MOVEDIN -96 (24)------------------ DCGND

MFDV/LDEVDC IN (-) -97 ------NC

MFDV/LDEVDC IN (+) -98 ------NC

MFDGS DEVDC IN (+) -99 ------NC

MFD LRNLAT IN -1oo ------NC

MFDDME IN (-) -101 ------NC

MFDDME IN (+) -102 ------NC

MFDCRS ERR (+) IN -103 ------NC

MFDCRS ERR (-) IN -104 ------NC

MFDHDG ERR (+) IN -105 ------NC

MFDHDG ERR (-) IN 65J2A-106 ------NC


Page-568May 25/90

Use or disclosure of Information on thm page m subject to the restrictions on the title page of this :!ocument,

Honeywell W!W!ANCECITATIONV

Function

DIN 112 SPL SEL ODIN 113 SPL SEL 1DIN 114 SPL SEL 2DIN 115 SPL SEL 3DIN 116 SPL IN ODIN 117 SPL IN 1DIN 118 SPL IN 2DIN 119 SPL IN 3FD LP.TDC OUT (-)SG PWR ONFD TO/FR DC OUT (+)FD TO/FR DC OUT [-)SHIELD GiWlCROSS SIIIEAC REF (+)

CROSS SIDE AC REF (-)

#2 PITCHX#2 PITCHY#2 PITCHZ .#2 ROLLX#2 ROLLY#2 ROLLZ#2 HDG X#2 HDG Y#2 HDG ZSYS ASCB B DATA (+)SYS ASCB B DATA (-)

SYS ASCB B CLK (+)SYS ASCB B CLK (-)


SG-605/805


65J2B-1 -----NC-2 -----NC-3 -----NC-4 -----NC-5 -----NC-6 -----NC-7 -----NC-8 -----NC TS WITH 65J2B-10[I

+-9 (24)-Tc ---n--------- 7,11A-18

~;; ?;;T~!:73&----- I,6J1-30-12 (24)---+--J------------ 16J1-31

---

1

-13 (24)------------- --~ 26 V AC,I \ FIG. 4-3 (SH 2)Ii

-14 (24)---------------+-t

AC PWR GND-- SHIELD GND

-15 ------NC-16 ------NC

-17 ------NC-18 ------NC-19 ------NC-20 ------NC

-21 (24)------------------ C2J1-S-22 (24)------------------ t2J1-t-23 (24)------------------ C2J1-U-24 ------NC-25 ------NC

-26 ------NC65J2B-27 ------NC


Table 501 (cent)22-14-00

Page 569Mar 15/89

Use or disclosure of information on thm page IS subject to the restrictions on the htle pag; of this document.

Honeywell WWANC’CITATIONV



#2 HDGSYNC(+) 65J2B-28(24)-------------------C6J1-1#2 HDGSYNC(-) -29(24)------------------ C6J1-VWX VIDEODATA(P)

!

-30 (24)-------------;?- 59J1-9

14XVIDEODATA(N) 1 1- 59J1-h-31 (24)----------------

!

Y -- SHIELDGNDWX CONTROLDATA(P) -32 (24)-------------T~r- 59J1-Iri

iL- 59J~-~WX CONTROLDATA(N) -33 (24)--------------+-

Y -- SHIELClGNDIASSET (+) -34 ------NCIASSET (-) -35 ------NCRA #2 (+) -36 ------NCRA#2 (-) -37 ------NCVNAVDEV (+) -38 (24)------------’‘-t~i- 16J1-28>7J1B-14

i -!-~- 16JI-27,7J1B-15VNAVDEV (-) -39 (24)------------

I

Y--SHIELDGNDPROLINENAV (+) -40 (24)------------ ---- 164Jl13-89PROLINE NAV (-) -41 (24)--------------!-$-164J1A-59

-- SHIELDGNDPROLINEDME (+) ,-42 (24)------------:q~--164J1A-57PROLINEDME(-) -43 (24)------------JO%--164J1A-44SHIELD -- SHIELDGNDARINCO DATA(+)

1}

-44”(24)-------------~,-- 429HS DATAARINCO DATA(-) 65J2B-45(24)------------- -J--FROMLRN1

~-- SHIELDGND


Page 570Mar 15/89

Use or dsclosure of Information on this page is subject to the restrictions on the title page of this jocument.

Honeywell M!MEI!ANCECITATIONV

Function

ARINC O SYNC (+)ARINC O SYNC (-)SHIELD GNDARINC O CLK (+)ARINC O CLK (-)SHIELDGNDARINC 1 DATA (+)ARINC 1 DATA (-)SHIELD GNDARINC1 SYNC (+)ARINC1 SYNC (-)SHIELD GNDARINC1 CLOCK (+)ARINC1 CLOCK (-)SHIELD GNDARINC2 DATA (+)ARINC2 DATA (-)SHIELD GNDARINC3 DATA (+)ARINC3 DATA (-)SHIELD GNDARINC4 DATA (+)ARINC4 DATA (-)SHIELD GNDARINC5 DATA (+)ARINC5 DATA (-)SHIELD GNDARINC6 DATA (+)ARINC6 DATA (-)SHIELD GND


Connector Pin Connects To

65J2B-46 ------NC-47 L-----NC

-48 ------NC-49 ------tic

-50 (24)------------------ C164J1A-5-51 (24)------------------ C164J1A-15

-52(24)------------------C164J1A-26-53(24)------------------C164J1A-45

-54 (24)------------------ C164J1A-19-55 (24)------------------ C164J1A-17

-56 ------NC-57 ------NC

-58 ------NC-59 ------NC

-60 ------NC-61 ------NC

-62 ------NC-63 ------NC

-64 ------NC65J2B-65 ------NC


22-14-00Page 571

Mar-15/89Use or dmclosure Of Information on this page IS subject to the restrictions on the title pag~, of this document.

Honeywell MI!!?*NCECITATION n/V



ARINC7DATA(+) 65J2B-66------NCARINC7DATA(-) -67------NC

ARINC8DATA(+)t

-68(24)------------F--- 116J1-33ARINC8DATA(-) -69(24)------------- --- 116J1-2SHIELDGND Y ----- 116J1-35ARINC9DATA(+) -70------NCARINC9DATA(-) -71------NCSHIELDGNDOVERTEMPWARN -72(24)------------------AIRCRAFT

TS WITH65J -99 ANNUNCIATORFD GS DEVDC OUT (-) $-73(20)---------L----- 7J1B-17

DOUT 1 MST CMPWRN

/

-74------NCDOUT 2 DH

A

-75 ------NC

DOUT 3 RAD/FDTEST 1 -76 (24)------------------ 20J1-’r

DOUT 4 HDG CMP MON -77------NCDOUT 5 ATT CMP MON -78------NCDOUT 6 DME/GROUNDRANGE -79 (24) ------------------ FIG.4-17VALOUT3 FD HDG VLDOUT -80(24)------------------7J1A-23VALOUT 1 SG -81------NCVALOUT 2 NAVSEL (P-ID1) -82(24)------------------FIG.4-18FD LRNSELVALOUT(P-ID2) -83(24)------------------FIG.4-18FD LATSTRGVALOUT -84(24)------------------7J1A-27NAVSEL (P-IDO) -85(24)------------------FIG.4-18FD LATDEVVALOUT -86(24)------------------7J1A-:16FD VERTDEVVALOUT -87(24)------------------7J1B-7FD DME VALOUT -88(24)------------------7JlA-34,FIG.4-17FDTK DETENTVALOUT -89(24)------------------7J1A-49FDAP ENGAGEDVALOUT -90(24)------------------7J1A-46,FIG.4-6FDAPS VALOUT -91(24)------------------7J1B-38FD LNAVAPPDOUT

}A

-92(24)------------------7J1A-48FDTTL DOUT 1 -93(24)------------------7J1A-22FD DME TTN DOUT -94 (24) ------------------ 7J1A-50, FIG.4-17FD MID MARK (5V) -95 (24) ------------------ 7J1B-f30FD PW MOVE -96 (24)------------

#

----- 7J1B-49,1OJ1A-33FDV/L DEVOUT (-) -97 (24)----------FDV/L DEVOUT (+)

fi ----- 7JlA-~o65J2B-98(24)----------~----- 7J1A-21

A1 CAUTION!100ma MAX LOAD.


22-14-00Page572May 25/90

Use or dwclosure of information on thw page IS subject to the restrictions on the title page of thm document,

Honeywell INR’’”c’CITATION V

Function

FD G/S DEV OUT

FD LRN LAT DC OUT

FD DME DC OUT (-)

FD DME DC OUT (+)

FD CRS ERROR (+) OUTFD CRS ERROR (-) OUTSHIELDFD HDG ERROR (+) OUTFD HDG ERROR (-) OUTSHIELD



TS-WITH 65J2B-7365J2B-99 (24)----I-+---*------- i’JIB-16

TS WITH,65J2B-9-100 (24)---+:+---W-------- 7J1A-17

t

-101(24)-----------!--:& 7J1A-33,16J1-35

*II

?

-102 (24)-------------- -- “7J1A-32,16JI-34-- SHIELD GND

!-103 (24)----------- ----- 7J1A-41-104 (24)----------- --kq-- ?JIA-37. .

I‘L-- SHIELD GND

-105 (24)----------- ---- 7J1A-36

65J2B-106 (24)-------------4- -- 7J1A-374 -- ~;HIELD GND


Table 501 (cent) 22-14-00Page 573

Mar 15/89Use or disclosure Of Information on this page is subject to the restrictions on the title pag” ! of this document,

Function

SIGNALGNDLIGHTING28V (H)LIGHTING5V (H)

LIGHTINGCOM+28V DC POWER

FIG4-1DC POWERGNDsc/cPPB~;~P~~DTIMEPB

;OURSE SYNCPBUC REVSWiEADINGSYNCpB;PAREPB/ESERVED-!DGREV PB!TTREV PB

RESERVEDNAV REV PBFLIPPBRESERVEDSPARESPAREWX PB

TESTcs REV SW

SPARE

SPARERESERVED

HDGSillHDG SW2

ATT SWlATTSW2SPAREDC/SGBUS (H)DC/SGBUS (L)SHIELDGND--DC/MGBUS (H)DC/MGBUS (L)SHIELDGND

PILOT’SEFISREMOTECONTROLLERDC-811

connector Pin Connects TO—,,

115J1-1 (22)--------------------SIGNALGND-2 ------NC-3 (22)--------------------PILOT5 V

LIGHTING,FIG4-2

-4 (22)--------------------LIGHTINGCOM-5 (22)--------------------;:;::28VDC

,

-6 (22)--------------------‘c ‘wilGND-7 ------NC-8 ------NC-9 ------NC-10 (24)--------------------23J1-[~-11------NC-12 (24)--------------------23J1-li

-13 ------NC-14 ------NC-15 ------NC-i6------NC-17------NC-18------NC-19------NC-20------NC-21------NC-22------NC-23------NC-24------NC-25------NC-26------NC-27------NC-28------NC-29 (24)---------------------30------NC-31------NC-32------NC-33------

$1#-34 (24)--Y(-1--------------

-35(24)--N --------------

FIG.4-12

65J1A-6765J1A-68

-36-----NC115J1-37-----NC


Paae574May-25/90

Use or disclosure of reformation on this pageis subject to the restrictions on the title page of this document.

Honeywell U%!JFPANCECITATION V

PILOT’SEFISREMOTECONTROLLER(cent)DC-811


ADIDIM (H) t115Jlj;~~~~]------------r?-----3J1-30ADIDIM (L) ------.---

1

---- 3J1-31HSIDIM (H) -40(24)-------G-~~~~---- 2J1-30HSIDIM (L) -41(24)-------~d----l--~u-2J1-3~AP PITCHWHEELINPUT+ -42(24)--------------AP PITCHWHEELINPUT- {‘T-l_-~FIG.4-6-43(24)--------------- - -~

I

Y -- SHIELDGNDAP PITCHWHEELOUTPUT+ -44(24)-----fi-AP PITCHWHEELOUTPUT- -45(24)-----

‘---------->FIG.4-6

Y-------------

SHIELDGND---+28 VDCAP ENGAGEINPUT -46(24)--------------------FIG.4-6VS HOLDMODEGND -47(24)--------------------FIG.4-6IAS HOLII MODE GND -48(24)--------------------FIG.4-6MACHHOLDMODEGND -49------NCWX DIM (H) -50(24)--------------------2J1-33WX DIM (W) -51(24)--------------------2J1-34WX DIM (L) -52(24)--------------------2J1-35DH SET (H) -53(24)--------------------65J2A-42DH SET (W) -54(24)--------------------65J2A-43

DH SET (L) -55(24)--------------------65J2A-44

FDMODECOMMON -56(24)--------------------SIGNALGNDADCSLEWENGAGE -57(24)--------------------FIG4-6,9J1-37ADCSLEW + -58(24)--------------------FIG4-6,9J1-38ADION GND -59-----NCSPARE -60-----NCSPARE -61-----NCSPARE -62-----NCHSION GND -63-----NCSPARE -64-----NCSPARE -65-----NCSPARE -66-----NCWX ON GND -67-----NCPOSITION3 -68(24)--------------------115J1-71POSITION4 -69(24)--------------------115J1-72POSITION5 -70-----NCADF (L) -71(24)--------------------115J1-68LRNA (L) CIRCLEPTR -72(24)--------------------115J1-69LRNB (L) 115J1-73-----NC


Table 501 (cent)22-14-00

Page575Mar 15/89

Use or disclosure of mformatlon on this page is subject to the restrictions on the title paqe of this document.


PILOT’S

Function

POSITION 3’POSITION 4POSITION 5ADF (R)LRN A -(“R)LRN B (R) ~

DIAMOND PTR

EFIS REMOTE CONTROLLER (cent)DC-811

Connector Pin Connects To——

115J1-74-75-76-77-78

115J1-79

(24)-------------------- 115J1-77(24)-------------------- 115J1-78-----NC(24)-------------------- 115J1-74(24)-------------------- 115J1-75-----NC


22-14-00Page 576

Mar-15/89Use or dwclosure of mformatlon on this page IS subject to the restrictions on the title page of this locument.

Honeywell !NJEPAN’ECITATION n/V

INSTALLATIONBULLETINFOR REMOTE RADIOS

PILOT’S MLS UNIT MLZ-850


EL DEVIATIONLO 116J1-1-------NC

429LO

1

-2 (24)----------t~r------ 65J2B-69

[I33---------v

------35--------

AZ DEVIATIONRTN -3-------NC

+28VDCRET -4 (22)--------------------DC GND

+28 VDC INPUT -5 (22)-------------------- pILOT!j 2SVDC

FIG.4-1BACKAZ SELECTED -6-------NCMLS OFF -7-------NCANALOGVIDEO -8-------NCMORSEAUDIOHI -9-------NC

AZ DEVIATIONLO -lo------NC

EL DEVIATIONHI -11------NC

EL LOWLEVELFLAG -12------NCSPARE -13------NCEL HIGHLEVELFLAG -14------NCBACKAZ AVAILABLE -15------NCFRONTPREAMPPRESENT -16 (24)-------------------lMJI-36

(IFFRONTPRE)EL CHANNELCHANGE -17------NCDPSKDATA -18------NCSPARE -19------NCAZ DEVIATIONHI -20------NC

MORSEAUDIOLO -21------NC

EL DEVIATION RETURN -22------NCAZ LOW LEVEL FLAG -23 ------NCAZ HIGH LEVEL FLAG -24 ------NCAZ CHANNEL CHANGE 116J1-25------NC


22-14-00Paqe577

May-25]90Use or disclosure of mformatlon on this page IS sub!ect to the restncttons on the Mte pag ? of !hls document.

Honeyell IKWJEPANCECITATION 11/’V

Function

IDOREARPREAMPPRESENT

SPAREBOARDTESTSYNC4SPARESYNC3429HIGH

SPARESHIELDGROUND

STRAPGROUND

RCBSHIELDGNDMSA 1MLSRCBRX (-)

MLSRCBTX (-)

TESTBUTTONINPUTMLS RCBTX (+)

INSTALLATIONBULLETINFORREMOTERADIOS

PILOT’SMLSUNITMLZ-850(cent)

ConnectorPin

116J1-26------NC-27(24)-------------------

-28------NC-29------NC-30------NC-31------NC-32------NC

t-33(24)---------~-------

II2-------_~-l-*--:---

Y-34------NC

1-35(24)-----------

-36(24)-------------------

-37(24)--------------------38(24)----fi-------------‘39--------‘i

i------------

67-J- ------------37--f

41-40 -------i-, ------------42-<~ ------------

-41------NC

!-42-----------------C-----

40---------J-1-----%37----------

Conn6ctsTo

116J1-36(IFREARPRESET)

65J2$-68

116J1-16,116J1-27GNDSEENOTE1164J1,4-34164J1A-21

164J1A-38164J1A-25

164J1A-25164J1A-38

MSA 7 -43------NC

MORSE IDENT (H)!

116J1-44 (24)------------? ---- 164J1B-3260----------$ ---- 164J1[I-13


Page578May 25/90

Use or disclosure of mformatlon on this page is sub!ecf 10 the restrictions on the htle page of this document.

Honeywell M!KRANCECITATION n/V


PILOT’S MLSUNITMLZ-850(cent)


SPARE 116J1-45------NCSYNC2 (EL) -46------NCSPARE -47------NCSPARE -48------NCMSA3 -49(24)-------------------MSA 2

t

-50 (24)------------------- NOTE 1MSA PARITY -51(24)-------------------SPARE -52------NCSPARE -53------NCSPARE -54------NCSYNC1 -55------NCAGC VOLTAGE -56------NcCHANGEINHIBITNOT -57------NCMSA4 -58(24)-------------------SEENOTE1MSA6 -59(24)------------------SEENOTE1CHASSISGND

)-60 (24)-------O----------164J1B-13

44----4-!---------164J1B-32MSA 5 -61 (24)-------J ----------- SEE NOTE 1SPARE -62------NCSPARE -63 ------NCMSA O -64 (24) ------------------- SEE NOTE 1ID1 -65------NCTESTOUTPUT -66------NCMLS RCB RX (+)

!116J1-67---------------~[ ------ 164J1A-21

39---------Y

------ 164J1A-34

37--------

FORE ANTENNA 116J2-1----2142U4/U ------------ - FORE ANTFORE ANTENNA SHAD --------------------------- - FORE ANTAFT ANT 116J3-1----2142U4/U ----------- -- AFT ANTAFT ANT SHAD---------------------------- AFTANT

NOTE1: SEE PAGE580.


Paqe579Ma~-25/90

Use or disclosure of mformatlon on this page IS subject 10 the restrictions on fhe title Pa;e Of this docume t.

Honeywell W!WFANCECITATION 11~

NOTE1:

Maximum Selectable Angle

MSA7

MSA6

MSA5

MSA4

MSA3

MSA2

MSA1

MSAO

Parity

Pin #

45

59

61

58

49

50

38

64

51

OpenCircuit

o

0

0

0

0

0

0

0

Jumperedto 116J1-36

1 = 12.8(Deg)

1 = 6.4

1 = 3.2

1 = 1.6

1 = 0.8

1 = 0.4$

1 = 0.2

1 =0.1

The ParityPin (51)shouldbe jumpered (or not jumpered) to Pin 116J1-62to giveoddparity.


22-14-00Paae580May”25/90

Use or disclosure of information on this page is subject to the restrictions on the title page of this document,

Honeywell ~ir~~ANcECITATION n/V


PILOT’SCOMUNITRCZ-850


ENCALTCIN 143J11:~;:]--------------------9J1-18,C143J1-1+28VDCFAN --------------------FANREDSPARE -3-------NC+28VDCCOM -4 (22)--------------------+28 VDC COM -5 (22) -------------------- PILOT 28 VDC+28 VDC COM

}

-6 (22) -------------------- FIG.4-1+28VDCTDR RET -7 (22)--------------------DC GND

+28VDCTDR -8 (22)--------------------PILOT28 VDC+28VDCTDR 1-9 (22)--------------------FIG.4-1

RSBPRIMARY(+)}]

-lo--------------

Y

------- FIG.4-9RSB PRIMARY (-) -11------------ --------

BOBBIN----

SELCAL/ACARSRET -12-------NC

ENCALTD4N -13(24)-------------------9J1-27,C143J1-13

ACH POWER+28VDC -14-------NCRCBSPARE1 RX - -15-------NC+5 VDC -16(24)-------------------STRAPP3 RED+28VDCCOMRET -17(20)-------------------DC GND+28VDCCOMRET -18(20)-------------------DC GND+28VDCCOMRET -19(20)-------------------DC GND+28VDCTDR RET -20(20)-------------------DCGND

VHF1PTT -21(24)-------------------160J1-F,C160J1-B,C160J1-F,

SELCAL/ACARS -22-------NC 160J1-BSPARE -23-------NC

SIMULCOMRET -24-------NC

COMMACHDATA(-)y$

-25(24);;---------- ---- 165J1-J-------- -- .--- 165J1-H

BOBBIN--------ENC ALT C2N 143J1-26 (24) ------------------- 9J1-19,

C143J1-26


22-14-00Page580.1/580.2

May 25/90Use or dwclosure of !nformatlon on this page is subject to the restrictions on the title pagf of thw document

Honeywell &MF.ANcECITATION n/V


PILOT’S COMUNITRCZ-850(cent)

Function

ENCALT D2NRCB SPARE 1 RX +

EMER PHONE LO

RECPH AUO HIEMERPHONEHISPARE

COMM ACH OATA +

AUX AUD 4 LOSIMULCOMSPARE3HF COMXMITAUX AUD 2 HItlFCOMSQUELCHGNO (AUDIOSHIELDS)COMMACH +28 VDC RET

AUDIO BUS SHIELD(GND)

+5 VDCRET (GND)GNDGND

GND

SPARESPARE2AUX AUD 2 LO

AUXAUD 1 LO (INPUT)

AUX AUD 3 LO

AUX AUD 3 HIRCBSPARE2 RX -+28 VDC FAN RET

TDR-DLP TD +

DIGAUDIOBUS 1 (+)


143J1-27-------NC-28-------NC

I

-29(24)-------------;---- 160J1-m,-30-------NC C160J1-m-31 (24)------------!~---- 160J1-G,-32-------NC

YC160J1-G

BOBBIN-----

-33 (24)------ii--:T?i1---- 165J1-H

Y---- 165J1-J

BOBBIN~-----34-------NC-35-------NC-36-------NC-37 (24)-------------------“FIG.4-19-38-------NC-39-------NC-40 (24)-------------------BOBBIN-41-------NC-42------------------------AUDIOBUS SHLD

-43 (24)-------------------STRAPP4 BLK-44 (22)-------------------BOBBIN-45(22)------BOBBIN-46(22]------BOBBIN

-47-------NC-48-------NC-49

1-50----------------1~r---- HF1

66-------------- - ----Y]BOBBIN----

-51-------NC.

-52-------NC-53-------NC-54(24)-------------------FANBLU-55-------NC

143J1-56 n

!----------------- ----IT FIG.4-IO

70

d

---------- ---42----------


Page581May25/90

Use or disclosure of mformatlon on thm page IS subject to the restncttons on the title pag! of this document.

Honeywell !MIM!!ANC’CITATIONV


PILOT’SCOMUNITRCZ-850(cent)


SIDETONEPHONEAUDIOHI 143J1-57-------NCGND -58(24)-------------------BOBBIN

SPARE -59-------NCGND -60(24)-------------------BOBBIN

RSBSECONDARY(-) -61v}----;~----------t-t- -- FIG.4-9

J--------- - - --

BOBBIN-----+

AUXAUD 4 HI -62-------NCSPARE -63-------NC

SPARE -64-------NCSPARE -65-------NC

AUXAUD.1HI -66(24)----------+:f------HF150 (24)---+-------

?GND 1-67(24)------------------BOBBIN

RCBSPARE2 RX + -68-------NC

ENCALT COMMON -69 (24)------------------- 9J1-213,,

C143J1-69

DIG AUDIO BUS1 (-)!)

-70---------------l~T-l--- FIG.4-1056 --------v-----42----------J

ATCOFF/ON -71-------NC

GND (SQUAT SklITCH RET) -72 -------NC

SPARE

RSBSECONDARY(+)

-73-------NC

-74 t----;i---------~~F-f--->FIG.4-9

Y-------- - -----

BOBBIN-----

SPARE -75-------NCSPARE -76-------NCSPARE 143J1-77-------NC


Table 501 (cent)22-14-00

Paqe 582Mar”15/89

UseordisclosureofinformationonthispageISsubjecttotheTestnctionsonthetitlepageofIhlslocument

Honeywell M!JFPANCECITATIONV


PILOT’SCONUNITRCZ-850(cent)


SPARE 143J1-78------NCSPARE -79------NC

MUT SUPRET -80(24);;-i;;j-----------A

4-/---- 164J1A-42

C164J1A-42C143J1-94

RCBSPARE1 TX + -81------NCRCB SPARE 2 TX + -82 ------NC

SQUAT SW IN -83(24)-------------------FIG.4-7ENCALTC4N -84(24)-------------------9J1-24

C143J1-84ENCALTB2N -85(24)-------------------9J1-16,

C143J1-85ENC ALT BIN -86(24)-------------------9J1-23,

C143J1-86TDR-DLPTD- -87------NCCLOCK -88 (24)-----;------------- STRAPP6 BLUSIDEAO -89(24)-------------------STRAP P1 GRNDLP-TDR TD(+) -90------NC~~~I~lENABLE -91(24)-----------------J--143J1-105

i

-92--------------------- 160J1-RIi C160J1-RII

106---------!-1+ :::::i~;u ---

ON/OFFVHFCOMREMOTE -93-------NC

MUTSUP IN -94(24)-----t--)-----------C164J1A-42

1

164J1A-42C143J1-94

80-----

RCBSPARE1 TX - -95-------NCRCB SPARE 2 TX - -96-------NC

ENCALTA4N 143J1-97(24)-------------------9J1-22,C143J1-97


Page 583Mar 15/89

Use or disclosure of tnformatlon on this page is subjecl to the restrictions on the title pag? of this document,

Honeywell MIM!!’”c’CITATION V


PILOT’S COM UNIT RCZ-850 (cent)


ENC ALTAIN 143J1-98(24)-------------------9J1-2C,C143J1-98

ENCALTA2N -99(24)-------------------9J1-21,C143J1-99

ENCALT B4N -100(24)------------------9J1-17,C143J1-1OO

SERIALDATA -101(24)------------------STRAPP7WHTPARLOADNOT -102(24)------------------STRAPP20RNSIDEAl -103(24)------------------STRAPP8YELDLP-TDRTD (-) -104-------NCRETURN -105(24)------------------143J1-91

MICLO

,!

-106(24)---------------- 160J1-E,II 160J1-H11 C160JI-E,lJ C160JI-H

92 --------v----

TRANSPONDERANTENNA 143J2-1-------RB-214/U-:---------XPONDERANTTRANSPONDERANTENNA JSHAD--------------------------XPONDE.RANT

(SEENOTE)

CC)MANTENNA 143J3-l-------RG-58/U~-’--------COMANTrSHAD---------------------------COMANT

(SEE NOTE)

~: MAX COAX LENGTH 30 FT.


Table 501 (cent) 22--14-00Page-584

Mar 15/89Use or disclosure of mformatlon on this page IS sub)ect to the restrictions on the title page of this document.

Honeywell MINJfPANcECITATION n/V

INSTALLATION BULLETIN FOR REMOTE llADIOS

PILOT’S RMU RM-850


+28 VDC LIGHTING 144JI-A-------NC

+28VDC LIGHTINGRET -------NC+28 VDC :: (20)-------------------- PILOT’S 28V

FIG. 4-1+28 VOC RETURN -D (20)-------------------- DCGND

FMCSBUS (+) (RS 422)

I

-E (24) -----fl ------------ 121 J1A-40FMCS BUS (-) (RS 422) -F (24) -----U ------------ 121 J1A-41

5 VDC LIGHT -G (22)--------------------FIG.4-25 VDCLIGHTRET -H (22)--------------------LIGHTGND

5 VAC LIGHT -J -------NC5 VAC LIGHT RET -K-------NC

CHASSIS GND -L (24)--------------------CHASSISGND

RSB SECONflARY (+) -M ------------pi

‘1

--------- FIG.4-9RSBSECONDARY(-) -N -----..----- -- ----.----.

t Y-------

W.o.w. -P (24)--------------------A/CWOW SWITCHM.O.M.POLARITY -R (24)--------------------WOW = GNO

ATC IDEI’JT -S (24)-------------------- C144J1-S

GND SWITCH

MBU INHIBIT -T-------NC

CHASSISGND -U (24)--------------------CHASSISGND

RSB PRIMARY (+)n

:: -----------’-’-

‘}

------ ------ ---- ----- .- FIG.4-9RSBPRIMARY(-)

b---------

t-------

SPAREDIG IN -------NCON/OFF PAGE DELETE ~? (24)-------------------- 144J1-DSPARE DIG IN -Z-------NCSPARE 144J1-a-------NC


Page585May-25/90UseorUwclosure of mformatlon on this page E subject to the restrtctlons on the title pag( of this document.

Honeywell MKMRANCECITATION V

INSTALLATIONBULLETINFORP.EMOTERADIOS

PILOT’SRMURM-85C(cent)


SIDE SELECT BO 144J11~ ~j$------------------- 144J1-USIDE SELECT B1 -------------------- 144JI-USIDE SELECT EV PARITY -d (24)--------------------144J1-U

TESTENABLE ~;:-e-------l:COMMFREQXFER -f-------ii:

COMMMEMSELECTO -9-------E:MKRSENSELEFTSIDE -h-------tin

MKRSENSERIGHTSIDE -i-------tic

COMMPOWEROFF -j-------N~ATCPOWEROFF -k-------N:VORPOWEROFF -m-------~~DMEPOWEROFF -n-------zADFPOWEROFF ,-P---.---;;MLSPOWEROFF -q-------N:

SPAREDIGOUT -r-------NCSPAREDIGOUT -s-------NC

,RSBSHLDGND 144J1-t-------------------------RSBSHLDFIG.4-9


Table 501 (cent) 22=-14-00Page 586Mar15/89

Useordisclosureof mformatlon on thw page IS sub)ect to the restrictions on the t!tle page of this document

Honeywell MKMYANCECITATION Ilfl

Function

AOF MODSHLD

ADF COSMOD

ADFANTTEST

ADF OUTERSHLD

ADF INNERSHLD

ADF RF INPUT

ADF +15VDC

ADF SINMOD

ADF+15VDCGND

ADF LOOPEN


PILOT’SADFANTENNAAT-860


158J1-A-------NC

-’----------~-t--- 164J’A-’1-c---------

t t----------- --- 164J1A-77

-D-------NC I-E-----

AdI-F---{<:,?RCR505Z-Z------- 164J2-1

--

{-G------------------------ 164J1B-1

i-H------------------------ 164J1A-104

-J-------------------------164J1B-27

158J1-K-------------------------164J1A-101

NOTE: ADFANTENNATRIAXIALCABLESHALLBE TROMPETERPN TRC-50-2OREQUIVALENTTRIAXIALCABLE.

ALL WIRESSHALLBE STANDARD#22AWG PERMIL-W-B1044ORMIL-W-22759/16EXCEPTAS NOTED.


Paqe587May-25/90

Use or disclosure of information on thw page IS sub~ect to the restrictions on the title pagi! of this document.

Function

HANDMIC PTTEMERGENCYCOMPTT

IHF2 PTT

VHF2MIC HI

VHF 1 MIC LO

VHF 1 PTT


PILOT’SAUDIOPANELAV-850

Connector Pin connects TO

160J1-A(24)-------------------- PILO’TSMIC

-B (24)---------------------160J1-FC160J1-BC160J1-F143J.I-21

-C (24)--------------------C143,11-21C160J1-C

1

-D (24)---------F;-‘----- j;~;j~-:2

w --.---l~--------

I

--0B

-E (24)---------~-l--

!

------ 143JI-106,

II160J1-Hc160J1-E,1{ C160J1-H

R-------!~--------

-F (24)--------------------143J1-21,160J1-BC160J1-F,C160J1-B

EMERCOM PHONEHIn

!

-G (24)-----------q-r-‘--- ~~~~~~3~II

m_------~-~---~~~ SHIELDGND

EMERCOMMIC LO -H (24)-------

[

p- ---------l&)J1-EII C160J1-HII 143J1-106

C160J1-EP-----;----------

HANDMIC LO -J (24)--------------‘--- ~:~~~sJ~~~EB;~DHANDMIC HI 61160J1-K(24)------------------

11


Page588May 25/90

use or disclosure of mformatlon on this pageIS sub!ect to the restrictions on the Iltle Page of thl~ ~oCumenl

Hone~eiI !%fii!ANcECITATION Ilfl

INSTALLATION BULLETIN FOR REMOTE RADIOS

PILOT’S AUDIO PANEL AV-850 (cent)

Connector Pin Connects TOFunction

iBIN/COCKPIT SPKR LO 160J1-L (24)-------------------- LtiCKPT/CAB SPKR LO

?8 VDC RTN -M (20)--------------------DCGND

-N (24)---.---------------— --0B4LDGND

-P (24)-------~[

1

160J1-R‘4ERCOM MIC HI

--------C160J1-P

([ C160J1-R

II 143J1-92H ?----------------

HF 1 MICHI-

{F2 MICLO -s

{F2 MICHI -T

+28 VDC -u

t28 VDC -v

VHF 2 MIC LO -w

HF 2 PTT -x

II L C160J1-R,[1 C160J1-P

E-----t~----------

f(24).------.7----------C160J1-S,HF2

(24)-------J.;~::-G---- c160J1-T,HF2

(20)--------------------PILOTS 28 VDC

(20) 1-------------------- FIG. 4-1

A----0

I(24)-----.-~j---B-----c143J1-106

C160J1-WII

D-----: -- -------

(24)--------------------c160J1-x’‘F*

COCKPITSPKR HI 160JI-Y(24)-;----Q------------)LH CKPT SPKR

---- ------------

JInterconnectInformation

Table501 (cent) 22-14-00Page589May 25/90

Useordl?.closureofInformationonthispage!ssublecttotherestnc~lonson(he!ltlepag~ofthisdOCUKIent.

Function

F 1 MICLO

F 1 MICHI

F 1 PTT

IGAUDIOBUS2 (+)

IIGAUDIOBUS1 (+)

;ABIN SPKRHI

Y4ERNAVPHONEHI

)lMMINGRTN

I

,qASK/BOOM PTTMASK/BOOM HI

INTERPHONELO

PHONELO

INSTALLATION BULLETIN FORREMOTERADIOS


Connector PinConnects TO—.

h----

0

I160J1-2(24)-------l-r--------- C160J1-Z,HF1

-a (24)-------’~’-------‘-- c160’]1-a’‘F1

-b (24)--------------------C160J1-b,HF1

-c !]~------ ---- FIG. 4-10-----; ::---l ] _

--------- --- --

1---- @

-di]

------ ---------;-----1 ~

FIG. 4-10----- ----- ----

‘J

9}

-e (24)-L--:----- - ‘------ ~~R------ ------ --

t

-f (24)_-=~--_-~~---- ----- C160J1-fc164J1B-36

,1m-----1“-------- ---

~-------- SHIELD GND_.. —

-g (24)--------------------flS~~,~~Gp~N-h (24)--------------------To~EADSET

91-i (24)-i1----------------

-------- -------JACK~---:@@J--JC160:1 j

-j (24)-------1---i

,-

kj

-------- ------ C160J1-S

-k------~-----,(--------- TO LFPHONEJACK

C164J1B-51

6

----@

DIG AUDIO BUS 2 (-) 160J1-n----_------t]

----------- FIG.4-10c---.-JJ---_------

It-----To-----------

EMERNAV/COMPHONELO -m (24)--------------------~~~~~~z~

JInterconnect Information

Table 501 (cent) 22-14-00Page590

May 25/90

Use or disclosure of mformatlon on this pageIS subject to the restrictions on the title page of this 40Cement.

Honeywell W!UY’”c’CITATION V

Function

DIGAUDIO BUS 1 (-)

INSTALLATIONBULLETINFORREMOTE RADIOS

PILOT’SAUDIOPANELAV-850(cent)


1}160J1-p -----i----’p --------- --

$

FIG.4-10----- -----------

----Q

+5 VAC/DC DIMMINGS -q (22)---------------------FIG.4-2+28 VDCDIMMINGS -r-------

1

INTERPHONE HI -S (24) t------,c+.-i--------C160J1-:

j ~~--;--------C160J1-J----+-

PHONE HI

1

160J1-t-----------f~-w---------TO LHPHONE JACK

k ----j--[- --------

t ---@


Page 591

Mar 15/89Use or disclosure of Information on thw page IS subject to the restrictions on the tttle pagt ! of this documenf.

Honeywell INK!!’””CITATIONV



Furtction Connector Pin Connects To

WARNING 5 AUDIO 160J2-A -------NCWARNING 1 LO -B-------NCSPAREGND -------NCSHLDGND $-------NCRESERVED -E-------NCSPARE -------NCWARNINGAUDIO2 LO ::-------NCCABINDISABLE -H-------NCWARNINGAUDIO3 LO -J-------NCRESERVED -K-------NCMARKERSENS -L-------NCSTEROMUTE -M-------NCSPARE -N -------NCSERVICE PHONE LO

t}-P (24); ---------F~-- ----- TO SEI?VICE

------- -- ‘ti-- ----- PHONE JACKRESERVED -R-------NCRESERVED -S-------NCRESERVED -T-------NCRESERVED -U-------NCVOICERECORDERHI

“1 }-V (24)----------f~------TO VOICE

------------------- RECORCIERWARNING 1 AUDIO -W-----!-NCWARNING2 AUDIO -X-------NCRESERVED -Y-------NCWARNINGAUDIO4 LO . -Z-------NCWARNINGAUDIO5 LO

.-a-------

MASKINTERCOMENABLE -b (24)--------------------TO PILOT’SHEADSETOXYGENMASKSWITCH

MKRDISABLE -C (24)--------------------C160J2-CSPARE -d-------NCSERVICEMICLO t

1-e (24)----------i~t------ TO SERVICE

---------

1

~h - ----- MICSERVICEPHONEHI -f (24);---------T=------

J- }

TO SERVICE---------b- - ----- PHONEJACK

RESERVED -9-------NCRESERVED -h-------NCRESERVED -i-------NCRESERVED -j-------NCSERVICEMIC PTT -k (24)-------------------- SERVICE PTT

-1-------NOT USED IN CONNECTORWARNING 3 AUDIO -------NCRESERVED 160J2~;-------NC


22=14-00Page 592

Mar 15/89UseordmclosureofInformationon this page is subject to the restrictions on the title page of thm ~ocument.

Honeywell MR!!YANC’CITATION n/V


PILOT’SAUDIOPANELAV-850(cent)


INTERPHONE PTT 160J2-p------------------------- INTERPHONE pTT

SERVICE MIC HIi

-q (24)--f’~ -------------- TO SERVICEe--~ 1------------- MIC

VOICE RECORDERLO ‘r (24)--+’Tt-------------TO VOICE

v--1-- 1-------------RECORDER

RESERVED -s-------NC

WARNING4 AUDIO 160J2-t-------NC


Page593May 25/90

Use or disclosure of mformatlon on thw page IS sub!ect to the restrtct!ons on the tttle pag{ ! of thts document.

“~


PILOT’S DME INDICATOR DI-850


RESERVED 163J1-1-------NC

RSB PRIMARY (-) -2 ~>‘----~~---------ir?--‘-FIG. 4-9

--------Y- -----

10 ---------

RIB SEGONDARY (+)t?

-3 ----------------n~~- --- FIG. 4-9

14 -------- - - --Y10 ---------

RESERVED -------NC

RESERVED ~;-------NC

+28 VDC P14R -6 (22)-------------------- :’~oT&28vDc.-

5 V AC/DC LIGHTING INPUT -7 (24)-------------------- ;l: D;M~~NGs.-

SPARE -8-------NCSPARE -9-------NC

CHASSIS GND -lo (22)------------------- RSB s~LD

SPARE -11------NC

IICGROUND -12 (22)-------------------Dc Gf’J!)

LIGHTINGCOMMON -13 (24)------------------- LIGHT~NG GND

RSB sECoNDARy (-) -14 ----;----------f; 1}--- --- FIG. 4-9

-’r--------- -----

10 --------- ,

RSB PRIMARY (+) -15 ----.-- --------\>

s- --- FIG. ~L92 ‘l__---------

Y10 ---------

-16------KCSPARES -17------NC

163J1-18------NC

Interconnect InformationTable 501 (COnt)

I

22-14-00Page 594

Mar 15/89Useordisclosureof mformatlon on th!s page IS subject to the restrictions on the title page of thw jocument

Honeywell WJW’”c’CITATIONV


PILOT’S DME INDICATOR DI-850 (cent)


SPARE 163J1-19------NC

28 VDC LIGHTING INPUT -20------NCPOWER ON/OFF INPUT -21------NC

-22------NCSPARES -23------NC

-24------NC28 VDC RTN 163J1-25 (22)------------------- DC GND

.


Table 501 (cent)22-14-00

Page 595Mar 15/89

Use or disclosure of Information on this page IS sub!ecl to the restrictions on the title pat; e of this document,

Honeywell WXYAN’ECITATION n/V


PILOT’SNAVUNITRNZ-850


CLUSPARE 164J1A-1-------NCDMEHOLDNOT -2--- ----NCDME HOLD -3 -------NCDME SPARE -4 -------NCDME 6 W 568 + DATA -5 -------NCDME SPARE -6-- -----NCADF SHLD -7 (24)-------------------- ADF Stll-1)CLUSPARE -8-------NCCLUSPARE -9-------NCADF26 VAC400HZ RTN -10------NCADF26 VAC400HZ RTN

.9-11------NC

ADFSYNCHROY OUT -12------NC

CLUSPARE -13------NC

V/ION/OFF -14------NC

DME6 - 568- DATA -15------NC

DMERS 422SD - (2) -16(24)--------~T

‘}

-------A54------- -------TO LRN#1A28-----Y

DME6 W 568 - CLK -17------NCDMEACT 1 AUD OUT -18------NCDME6 W 568+ CLK -19------NC

CLUMLS RCBSHLD -20---------------CLUMLS RCBTX1 AJ164J1A-21---------------- ------ 116J1-67

A34------40L------ l16J1-39~SEENOTE5 FORSHLDINFO

11 IFTHEML-850MLSRECEIVERIS NOT INSTALLED,THEMLSRCBRX ANDTX PORTSMUSTBE JUMPEREDTOGETHERAT THE NAVUNITMATINGCONNECTORAS SHOWNBELOW:

JUMPER1: 164JIA-25TO 164J1A-21JUMPER2: 164JIA-38TO 164J1A-34


Pacie596May-25/90

Use or dwclosure of mformatlon on thw page is subject to the restncttons on the title page of this document.

Honeywell WKY’”c’CITATION n/V

Function

ADF SYNCHROX OUT

AOF26 VAC400 HZ

CLUCHANGEINHIBITCLU MLS RCBRX1

DME6 W 568+ SYNCCLUSPAREDMEGND

DMESPAREOME SPARE

CLUSPAREDMESPARE


PILOT’SNAVUNITRNZ-850(cent)

ADFSYNCHROZ OUT (GND)


164J1A-22-------NC

-23-------NC

-24-------NC

t-25----------------?-- --~h A

116J1-42 ~A38--------P------ 116J1-40

YA20---------SEENOTE8 FORSHLDINFO

-26------NC-27-------NC-28------------------------DMESHLD

SEENOTE2 FORSHLD INFO

-29-------NC-30-------NC-31-------NC-32-------NC

!164J1A-33(24)------+~--------- 65J2A-58,

II 65J2A-56,

ILRMI

A47------,--------A61---J--L---------A7-----Y

Interconnect InformationTable501(cent) 22-14-00

Page597May 25/90

Use or disclosure of information orI thw page IS sub]ecf to the restrtctlons on the tttte pagf, of ttws document.

Honeywell Hl!W!ANcECITATION n/V

Function

CLU MLS RCB TX2

CLU SPARECLU SPARE

CLU SPARE

CLU MLS RCB RX2


PILOT’S NAV UNIT RNZ-850 (cent)

ADF AUDIO OUT SHLD

DME ON/OFF

CLU AUX 1 AUD HI

DME MUT SUP

DME SPARE

DME RS 422 SD - (1)

DME 6 W 568 - SYNCDME FLAG

ADF DC COS OUT

CLU.SPARECLU SPARE

Connector Pin Connects To—,—I

164J1A-34m

t-------------- --q- -- -- ;;;::.<3;~

A21---------’------- -YA2&--------

SEE NOTE 5 FOR SHLD INFO-35-------NC-36-------NC-37-------NC

+-38--------------?- ----jt 116J1-40 ~

A25------=-’-- ---- 116J1-.42A20------- YSEE NOTE 5 FOR SHLD INFO

-39-------NC

-40-------NC

-41-------NC

-42 (24)--------<-+------- C164J?A-42

I

C143J;.-9,4143J1-94

A28------SEE NOTE 2 FOR SHLD INFO

-43-------NC

-44 (24) +----------~r ----- 65J2B-43ItI[1 1A57--------P ------- 65J2B-42

A28------- 1-45 -------NC-46 -------NC

-47 (24) ‘L

+‘----ii~i:::+- -

65J2A-57,RMI

A33 -----+-l-- -

-48-------YNC A7-------

164J1A-49-------NC


22-14-00Page598

May 25/90Use or dmclosure of mformatton on this page is subject to the restrictions on the title page of lhts [iocument.

Honeywell W!EIANcECITATION n/V

Function

ADFAUDIOHI OUT

CLU SPARE

ADF AUDIO LO OUTCLU SPARE

DME RS 422 SD + (2)

CLUAUX 1 AUD RTN

DME SPARE

DMERS422 SD+ (1)

CLUACH DATA (-)

V/IRS422 SERD lB

V/IMKIRLAMPM

ADFDC SIN/fiOUT


PILOT’SNAV UNIT RNZ-850 (cent)

CLUSPARECLUSPARECLUSPARECLUSPARE

ADFHF KEY


164J1A-50-------NC-51-------NC-52-------NC-53-------NC

t-54(24)------------------

A16-----+1--------

1TO LRN#1

A28-------55------NC-56------NC

i

-57(24)-------?~--------- 65J2B-42It

A44----l-f

---------65J2B-43

A28----~-58------NC

i-59(24)------”~---------- 65J2B-41

B89-------~~-----------65J2B-40YB50--------

-60 ------NC

i

-61(24)--------1~1------- 65J2A-55,RMIA47-----

‘-1-------A33-------Y--------

--------62----~~NC-63------NC-64------NC-65------NC

164J1A-66(24)-------------------FIG,4-19


22-14-00Pacae598.1M~y25/90

Use or disclosure of Information on this page IS sub)ec! to the restrictions on the title pag~: of this document

Honeywell MI!IL?ANC’CITATION n/V



Function

CLU AUX 2 AUO HI

CLU AUX 2 AUD RTNCLUACHNAV CLOCK+CLU ACHDATA+DME40 MV/MICLUACHNAVCLOCK-V/IMARKERLAMPI

V/IGS SUPERFLAG

CLUSPARECLUSPARE

ADFANTTEST

CLUSPAREADFMODSHLD

V/IGNDPS INCLUACHGNDCLUSPARE

DME28 VDCRET

[/1RS 422SERD 2B

V/I+28VDCDME+28VDCADF+28VDC

RSBSECONDARY(+)

CLUSPARECLUSPARE

Connector Pin Conn~cts To-

164J1A-67 ------NC-68 ------NC-69 ------NC-70 ------NC-71 ------NC-72 ------NC-73 ------NC

-74 ------NC

-75 ------NC-76 ------NC

-77 ----------------------- 158J1-CSEENOTE3 FORSHLDINFO

-78------NC-79------NC

-80------NC-81------NC-82------NC

-83(22)------------------

}A95--J-------------‘c ‘ND

‘}

-84(24)-------I?--------B102----

Y-------TO LRN#l

B50-----

-85(22)-------------------PILOT’S

}-86(22)-------------------28VDC BUS-87(20)-------------------FIG.4-1

6

‘}

-88---------------r------ FIG.4-9A102-----j-

f------

B85-------

-89-------NC164J1A-90-------NC


Page598.2May25/90

Use or disclosure of information on this page IS subject to the restrictions on the t!tle page of th!s cocument.

Honeywell M!JRANC’CITATIONV

Function

ADF COS MOD

CLU SPARECLU SPARE

ADF 28 VDC RET

DME 28 VDC RET

CLU SHLD GND

DME ACT 2 AUD OUT

V/I +28 VDCDME +28 VDCADF +28 VDC

ADF LOOP EN

RSB SECONDARY (-)

CLU GND

ADF SIN MOD

ADF MOD SHLD

CLU SPARE




t164J1A-91--------------=---- --- 158J1-B

A104---------------- --- 158J1-HYA105----------

SEE NOTE 3 FOR SHLD INFO

-92-------NC-93-------NC

-94 (22)------------------- DC GND

-95 (22)------------------- DC GND

-96 (24)---------A

IB13 (24)1-T- ------ 116J1-35B32 (24)JOA-------- 116J1-44

-97-------NC

-98 (22)------------------- PILOT’S

}-99 (22)------------------- 28 VDC BUS-100(20)------------------ FIG. 4-1

-lOJ----------------------Y 158J1-KSEE NOTE 3 FOR SHLD INFO

m h-102 ---------------- ----- FIG. 4-9A88 ----+&------f3/35-_--y----_--

-~03 (22)-.-------.--------7- DC GND

-104!

-----------------+->- - 158J1-iiA91------------------- 158J1-B

Y-105------------------SEE NOTE 3 FOR SHLD INFO

164J1A-106-------NC


Page 598.3Mar 15/89

Use or disclosure of mformatlon on lhts page IS sub)ecf to the restrictions on the title pag! of thts document,

Honeywell M!JEPANcECITATION n/V



Function Connector Pin Connects To——

ADF +15 VDC 164J1B-1-------------------------- 158J1-GSEE NOTE 3 FOR SHLD INFO

CLU FAN HI -2 (24)-------------------- FAN Rt:DCLU SPARE -3-------NCCLU SPARE -------NCCLU SPARE STAT I (DIG AUD) &----NCCLU SPARE STATRTN (DIG AUD) -6-------NCV/I SYNC COMP IN X -7-------NCCLU ACH +28 VDC -8-------NCV/I OBS D,G -9-------NCV/I OBS F -10------NCV/I OBI OSIN -11 (24)

t}

-------i%-- -----

V/I OBIO COS -12(24)ii;----+l-------- RMI

, -Y-.---

B50=:-- ‘--SEE NOTE 4 FOR SHLD DATA

CLU MLS MORSE ID RTN -13 (24)fit

i------------d- - -- 116J1-60B32---------J-T---- 116J1--44

9A96----------

CLU SPARE -14-------NCCLU SPARE -15-------NCCLU SPARE -16-------NCCLU SPARE -17-------NCCLU SPARE -18-------NCCLU SPARE -19-------NC

V/I 26 VAC 400 HZ H REF -20 (22)------------------- 26 VAC 400 HZPWR, FIG. 4-3

V/I RNAV VIDEO OUT -21-------NCV/I RNAV VIDEO GND -22-------NC

V/I 400 HZ 26 VAC RET -23 (22)------------------- AC GND

V/I VOR/LOC AUDIO CT -24-------NC

ADF GND 164J1B-25 (22)------------------- DC GND


22-14-00Page598.4May 25/90

Use or disclosure of !nformatton on this page IS subject to the restr!cttons on the title page of this :;ocument.

Honeywell WIJRANCECITATION n/V




CLU +5 VDC RTN 164J1B-26 (22) ------------------ STRAP P4 BLK

ADF +15 VDC GND -27 ----------------------- 158J1-JSEE NOTE 3 FOR SHLD INFO

CLU SPARE -28 ------NC

DIG AUDIO BUS 1 (-) -290

i---------------y+- ---

B42?]

--------- ----- FIG. 4-10I

B67 --------

CLUSPARESTATIN (DIG AUD) -30 ------NC

ICLU AUD AUX SQUELCH -31 ------NC1

CLU MLS MORSE ID -32 (24)o

t-.---------a-b- --- 116J1-44B13 (24)---J-1 ----- 116J1-60

YA96 (24)----

V/I SYNC COMP IN Y -33 ------NC

V/I OBS B -34 ------NCV/I OBS C -35 ------NC

V/I VOR/LOC AUDIO HI -36 ------NC

I V/I OBI.O GND -37 (24)------------------- RMI

IV/I PWR GND -38 (22)------------------- DC GND

V/I +28 VDC -39 (22)------------------- 28 VDC POWERFIG. 4-1

CLU CLUS +5V -40 (24)------------------- STRAP P3 RED

CLU SPARE

DIG AUDIO BUS 1 (+)

-41 ------NC f

164J1B-42n

t----------------++ --

B29 ---------1-J \Y----j

FIG. 4-10B67 ---------


22-14-00Paqe598.5M;y 25/90

Use or disclosure of mformatlon on this page IS subject to the restrictions on the title pag,, of thts document.

Honeywell MliRANcECITATIONn/V


PILOT’SNAV UNIT RNZ-850 (cent)

Function Connector Pin Conn[?cts To

CLUSPARE 164J1B-43------NC

CLU FANRTN -44(24)-------------------FAN BLU

CLUAUDAUX XMT -45------NCCLUSPARE -46------NC

V/ISYNCCOMPINZ -47------NCV/IOBSA -48------NCV/IOBS E -49------NC

V/IPWRGND -50(22)-------------------DC GND

V/IVOR/LOCAUDIOLO -51------NC

V/I28 VDC -52 (22)-------------------28VC1CPOWERFIG.4-1

CLUSPARE -53------NCCLUSPARE -54------NCCLUSPARE -55------NCCROSSSIDEMLSSEL -56------NC

CLUSIDESPARE -57(24)-------------------STRAPP1 GRN

CLUSTRAPSD DATA -58(24)-------------------STRAp P7WHT

CLUSTRAPCLK -59(24)-------------------STRilPP6 BLIJ

V/I GS FLAG -60 ------NC

V/ISYNCOUTZ -61------NC

V/ISYNCCOMPVALID -62------NCV/IMKRAUDIOCT -63------NC

V/ICC ILSMODE -64(24)-------------------RMI

V/ITO/FROM+ -65------NCV/IMKRAUDIOHI 164J1B-66------NC


Page598.6May 25/90

Use or dwclosure of Information on this page IS sub)ect to the restrictions on the title page of this : ocument.

Honeywell WJHANC’CITATIONV

INSTALLATIONBULLETINFORREMOTERADIOSPILOT’SNAVUNITRNZ-850(cent)


DIGAUDIOBUSSHLD 164J1B-67----------------1

i}B29-------------- FIG.4-10J~B42-------Z-- --

ADF26 VAC400HZ -68-------NC

CLUSPARE -69-------NCCLUSPARE -70-------NC

ADF SYNTH LOCKADFRS 422TXDBV/IMKRLAMPOV/lDEVCOMV/I ILSMODEANUCLUSPAREV/lVOR/LOCDEV+V/IGS DEV+

-72------NC-73------NC-74------NC-75------NC-76------NC-77------NC-78------NC-79------NC

CLUSIDESELECT -80(24)-------------------STRAP P8YEL

RSBPRIMARY(-) . -81 11~]n--.----------------- -

B71--------------Y

-FIG.4-9B95--------- J

CLU SPARE -82-------NCCLUSPARE -83-------NC

CLUSTRAPWD LOAD -84------------------------STRAP P20RN

RSBSHLD 164J1B-85--------------------j

A102 *-:::::::::1:2--~F*G”4-9.


22-14-00Paqe 598.7

M~r 15/89Use or disclosure of Information on this page IS subpct to the restrictions on the Mle pa~s of this document,

Honeywell WMYANCECITATION n/V

Function

CLUSPARE

ADFON/OFF

CLUACH NAVCONTROL-

V/IRS 422SERD 1A


CLU ACH NAVCONTROL+

V/I VOR SUPERFLAG

V/IVOR/LOCFLAGV/IMKRAUDIOLOCCLUSPARE

RSBSHLD

ON SIDEMLSSELCLUSPARE

CLUGND

ADF LOCK

ADF RS 422 TXD AV/ISPAREV/IRS 422SERD 2A

V/ISYNCOUTYV/ISYNCOUTXCLUSPAREV/ITO/FROM& FLAGCOM

PILOT’S NAVUNITRNZ-850

Connector Pin

164J1B-86 ------NC

-87 ------NC

-88 ------NC

cent)

Connects To

t-89(24)--------1~-------- 65J213-40

A59---------- ------- 65J2B-41Y

B50----------1-90------NC .3

-91 (24)-------------------RMI

-92------NC-93------NC-94------NC

-95-------------------B71---------1-1-~t}

FIG.4-9B81--------------

-96(24)---------------FIG.4-18-97------NC

-98(22)-------------------DC GND

-99(24)-------------------RMI,65J1A-82

-1oo------NC-101------NC

‘}

-102(24)--------1~1-------A84------------ TO LPN#1B50--_-y

-103------NC-104------NC-105------NC

164J1B-106------NC I


Page598.8May 25/90

Use or disclosure of reformation on this page IS subject to the restrlct!ons on the t!tle page of th!s jocument.

Honeywell WiW!’”c’CITATION n/V

Function

ADFRF INPUTADF INNERSHLDADFOUTERStlLD

V/lANTV/lANT

V/IGS ANTV/IGS ANT

V/IMKRANTV/lMKRANT

DMEANTDMEANT



Connector Pin

164J2-1-Tf+TRC-50-2-----@)--164J2-2_&

r

.—El

SEENOTE3 FORSHLDINFO

164J3-1?

------RG-58/U----- ------SHAD----------------------------

164J4-1?

------RG-58/U----- -------SHAD----------------------------

164J5-I?

------RG-58/U----- ------SHAD----------------------------

164J6-1------RG-214/U----9

------SHAD----------------------------

Connects To

158J1-F158J1-E

OLITERStiLDOPENAT NAV END

VOR/LOCANTVOR/LOCANT

GS ANTGS ANT

MKRANTMKRANT

DMEANTDMEANT

NOTE1: SHIELDSOF PAIRSA47-A61,ANDTRIPLEA12-A22-A33ARE TIEDTOGETHER.

NOTE2: SHIELDSOF A42 AND PAIRS A16-A54, A44-A57, ANDGROUNDA28ARETIEDTOGETHER.

NOTE 3: ADF ANTENNA TRIAXIAL CABLE SHALL BE TRUMPETER PN TRC-50-2OREQUIVALENTTRIAXIALCABLE.

ALLWIRESSHALLBE STANDARD#22AWG PER MIL-W-B1044 OR

MIL-W-22759/16 EXCEPT AS NOTED.

THEOUTERSHIELDJUMPERTO GENAT THEANTENNASIDESHALLBE 20AWGANO ITSLENGTHSHALLNOTEXCEED10 INCHES.

NOTE4: SHIELOSOFTRIPLESB1l-B12-B37,B9-B1O-B49ANO B34-B35-B48(IFUSED)ARETO BE TIEOTOGETHER.

NOTE5: SHIELOSOF PAIRSA21-A34ANDA25-A38ARE TIED TOGETHER.


22-14-00Page 598.9May25/90

Use or dwclosure Of Information on !!IIs page IS sub!ecf to the restrwtlons on the title pagr of thm document.

)\S52NN

\I

CLEARANC::~;~VERY UNIT

connector Pin Connects TOFunction

N/OFF OUTPIJT165JI-A

UD1OINPUT HIGHQUATSWITCHSENSV AC/DCLIGHTINGINPUT8V DC POWERINPUTIAVAUXSHIFT/LOADINPUTIIAVAUXSHIFT/LOAO

- BUS+I INPUTBUS-

:OMAUXOUTPUTBUS+;PARE;OMAUXOUTPUTBUS-

tAVAUXBUSSHIFT/LOADSHLDGND

ilIDEBANDSELECTINPUTNAVAUXOUTPUTBUS +NAV AUXOUTPUTBUS -

NAVAUX CLOCKINPUTBUS -

SPAREPRIMARYRSBBUS -

NAV AUDIO INPUT LOWROTORMODFILTERINPUT0/300DEG.ELECTINPUTVSMA7.9V/11.8VWX INPUTPOSTFAILANNUNOUTPUTtijcOM/NAVSELECT+SQUATSWITCHINPUTLIGHTINGCOMMON28 V DC LIGHTINGINPUTAUDIOOUTPUTHIGHAUDIOOUTPUTLOWNAVAUXOUTPUTBUSSHLDGND

SYNCHRO/RSBCOMPASSNAVAUXCLOCKINPUT

INPUTBUS +

-B-c-D-E-F-G

-H-1-J

-K

-L-M

------NC------NC(24)-.------------------(24)--------------------(22)-----X------------

#(24)-----r,------------(24)--------------------K (24)--Y

i

~::~::~~-~------------

(~q)---.!-!-------------P (24)--Y

165J1-gFIG.4-2c164J1B-8c164J18-90c164J1B-88

143JI-33

143JI-25

(24)-------I

tf \;:]---r-l--‘-------:;::::::::d-- -------------

---:--NC -

t(24)-----f~-‘---------:;:]:;;:::

-N (24)-------------------

-~ (24)--Y

t-P (24)-----,C[-‘---------:;~:;;::;

-f (24)-----------------~ (24)--Y

-Q ------NC

-R (24)

}

--------------------F*G.4-9-g (24)-----------------

-s ------NC-T ------NC

-U (24)--------------------sEENOTE1-V (24)--------------------SEENOTE1-w ------NC-x ------NC-Y (24)--------------------FIG.4-7-Z (24)--------------------LIGHTINGGND-g :--;--NC-tJ------NC-c ------NC-~ (24)-------L

$-M (24)---1-1--‘-------:;:::;~:;:-N (24)---w-----------

-g ------NC

t-~ (24)-----C--‘---------C164J1A-69-p (24) 1:-----------------c164J1A-72

165J1-~(24)--J


Paae598.10‘fray25/90

Intormatlon on this page IS subiect to the restrictions onthe title page of this document.

Use or disclosure Ot .

Honeywell M!WRANC’CITATION V

CLEARANCE DELIVERY UNIT (cent)CD-850

Function Connector=Pin Connects To

PRIMARYRSB BUS +

NAV AUDIO INPUT HIGHRMI REL/MAG BEARING INPUTPOWER GROUNDAUDIO SHLDGNDSPARECD/COM/NAV SELECTSIDE SELECTSPARECOM AUX BUSSHLDGND

JUMPERGROUNDNAVAUXBUSCLOCKSHLDGND

NAVAUDIOSHLDGNDAUDIOINPUTLOWSPARESPARESPARESPARESPARESPARE

)165J1-g(24)--------------------:~lG Q-g-R (z4)-----------------0

-h ------NC-~ (24)--------------------SEENOTE1-J.(22)--------------------DCGND-~ ------NC-~ ------NC-lJ------NC-rJ------NC-g ------NC-Q (24)-------A

t-H (24)----;1----------143J1-33-J (24)----U----------143J1-25

-g (24)--------------------165J1-C-L (24)-------I

t-P (24)----------------C164J1A-72-~ (24)---~aJ----------C164J1A-69

-~ ------NC-~ ------NC-lJ------NC-~‘------NC-y ------NC-~ ------NC

------NC165Jl~~------NC

NOTE1: CLEARANCEDELIVERYSTRAPOPTIONS

fIJl

i

T

u

e

v

L

A

DESCRIPTION

RMIREL/MAGBEARINGINPUT

ROTORMODFILTERINPUT

0/300DEG.ELECTOFFSETINPUT

SYNCHRO/RSBCOMPASSINPUT

VSMA7.9V/11.8VMAXINPUT

WIDEBANDSELECTINPUT

ON/OFFOUTPUT

FUNCTION

OPEN = MAGNETICGND = RELATIVEGND = FILTER ONOPEN= FILTEROFFOPEN = 300 DEGOFFSETGND = O DEG OFFSETGND = RSBOPEN= SYNCHROOPEN = 11.8VGND = 7.9VGND = NARROWBANDOPEN = WIDE BANDGND = OFFOPEN = ON


Table 501 (cent)22-14-00

Page 598.11Mar 15/89

Use or disclosure of Information on this page IS subJecf to the restncttons on the title pag$ of this document.

Honeywell %WEANCECITATION V

Function

COPILOT’SHORIZONTALSITUATIONINDICATORRD-450

HEADING ERROR NO. 1 HROTOR { cCHASSISGND

DC GND

SPARES

26V, 400 HZ POWER

(5V LIGHTINGPOWER :

SPARES

HDG ERROR NO. 1 XSTATOR

(Y

. 2v/DEG z

SPARES

TUNEDTO LOCGND+28 V DC

SPARES

{

(ROTOR H

CRSERROR(:

NO.1 .2V/DEGSTATOR Y


C2J1-A------NC-B ------NC-C (24)-------

A-D -------------------------DCGND

:;

:[-J-K-L (22)---------------------FIG.4-3 (SH2)-M (22)---------------------FIG.4-2-N (24j---------------------ACGND

:;

:; ------NC-u ------NC-v ------NC

:!-Y-z

---------------------C164J1B-64“l;(24)”------NC

-c-d

:;------NC

:: ------NC-i ------NC.

------NCC2Jl~~------NC


Table 501 (cent) 22-14-00Page 598.12Mar 15/89

Use or disclosure of information on this page is subject to the restrlcl(ons on the tnle page of this :iocument.

Honeywell !!Wk!ANcECITATIONV

Function

SPARES

(STATOR iz

COPILOT’SHORIZONTALSITUATIONINDICATOR(cent)RD-450

COMPARATOR/HDGTRANSMITTER Cos ;

SINHc

CRSRESOLVER

SPARE

ConnectorPin

{

C2J1-m-n

-P-q-r-S (24)----------------------t (24) ----------------------U (24)---------------------

-v ------NC------NC I~; (24)------------T~r-----

-y (24)------------ - -----Y ------

-Z (24)----------------------AA(24)---------------------66(24)---------------------CC(24)---------------------DD(24)---------------------EE(24)---------------------FF(24)---------------------GG------NC

C2J1-HH

ConnectsTo

65J2B-2165J2B-2265J2B-23

FIG.4-3 (SH2)AC PWRGNDSHIELDGNDC164J1B-9C164J1B-49C164J1B-10C164J1B-9C164J1B-48C164J1B-34C164J1B-35


Table 501 (cent)

22-14-00Page 598.73

Mar 15/89Use or disclosure of Information on this page IS subject to the restncflons on the tile pag ! of this document

Honeywell lRYiR_ANcECITATION V

COPILOT’S HORIZONTAL:HL}{TION INDICATOR (cent)


TO-FROMPOINTER{+

iC2J2-A(24)--------------------

(DEFLTO) 250LOAD - -B (24)--------$) --------GLIDESLOPEDEV

[

-C (24)----f-;-------------

II

(DEFLUP) lK LOAD i- -D (24)----~-j-------------

COURSEDEV(+

*-E (24)---------f~---------

(DEFLRIGHT)lKLOAD - -F (24)---------1-L--------

{

+ -G (24)---------------------SYNCANN lK -H (24)---------------------

10K -J ------NC

{

-K-L

SPARES:!

F(HIGHLEVEL+28V

( 1

-P (24)--------~~i---------NAV FLAG LOWLEVEL+ ------NC

COMMON - ~! (24)-------\> ----------; [SPARE -T

{

HIGH +

1

-U (24)-------;;-------------GLIDESLOPEFLAG LOW + -v ------NC

COMMON -W (24)-------l;____HDGDISPLAYVALID+28V -X (24)---------~f----------HOGVALID+28V -Y (24)---------------------

{

x -Z (24)---------------------HOGINPUT Y -a (24)---------------------

z -b (24)---------------------

SPARES{::-e

POWERGND - -f (22)---------------------

{

-9SPARES -h

C2J2-i

Connects To

C164J1B-65C164J1B-106C164J1B-75,65J2A-66,65J2A-67C164JIB-79,65J2A-68C164JIB-78C164J1B-75C6J1-UC6J1-V

C164JIB-91

C164J1B-106

C164J1A-74

CI64J1B-10665J1A-92C6J1-eC6J1-LC6J1-MC6J1-K

AC GNII


Table 501 (cant)

22-14-00Page598.14

Mar 15/89Use Or dk5C10SUre Of lnfOrmallOn on thts page !s subject to the restrictions on the title page of Ihls document.

Honeywell MNFANCECITATION V

COPILOT’S FLUX VALVEFX-220

Function Connector Pin Connects ToI

{

z 1C4J1-A (24)---~i- ------------- C5J1-AFV STATOR x ;: [;:]--j-l- ------------- C5J1-B

------ ------------- C5J1-C26V, 400 HZ

(:

7

-D (24)--- ---------------- AC GNDH -E (24)--- --------- ----- C6J1-S

SHIELD GND -F (24)--- T ----- C5J1-D

COPILOT’S DUAL REMOTE COMPENSATORCS-412

FROM FLUX VALVE

26V, 400 HZ

PWR GNDSHIELD GNDSPARE

FLUX VALVE OUTPUT

CHASSIS GND

SPARES

{

z “1C5J1-A (24)------ -------------x -B (24)--J-!- -------------Y -C (24)--~-~- -------------

-D (24)-------------------

1L----

-E (24)--- -----------------F (24)----G-H

-J-K-L

{

-M

-N-P-R

-s-T

-u

-v

. .

1(24)--=- -------------(24)--:-!- -------------(24)--IY- -------------(24)--------7

m

C4J1-AC4J1-BC4J1-CC6J1-SC4J1-EAC GND

C6J1-RC6J1-NC6J1-P

NOTE : SHIELDS ON THIS SHEET ARE NOT TIED TO AIRCRAFT GROUND. SHIELDS MUSTBE INSULATED FROM AIRCRAFT STRUCTURE.


Table 501 (cent) 22-14-00Page 598.15

Mar 15/89Use or disclosure of mformatlon on this page IS sub!ecl to the restrlcttons on the title pag ? of this document.

Honeywell MIKtfiiANcECITATION n/V

COPILOT’S DIRECTIONAL GYROC-14D

Function Connector Pin Connec:s To,—

AC POWER GNiI c6J1-A (22)------------------ AC GND28 VDC GND -B (22)------------------ DC GND+28 VDC INPUT -C (22)------------------ FIG. 4-L (SHT2)

-D9MA

FREE SLAVE SW -E (24)---- o-------F AUTO 1 FREE SLAVE

+B TO FREE SLAVE SW -G (24)---A-

1

------ -- SWITCHHDG NO. 1 ROTOR

{H -H (22)--t-~- ----------- FIG. 4-:1 (SHT 2)

26V 400HZ c -J (22)--Q----- ------- AC GND

{

z -K (24)------ ,>-

I

------- c2J2-EHDG NO. 1 STATOR -L (24)------+-T- ------- C2J2-Z

; -M (24)------a- - ---- --

1

C2J2-4

{

-N (24)-------~---r~- -- C5J1-JFLUx vALvE : -P (24)------------F-r -- C5J1-K

x -R (24)------------LO- -- C5J1-H

26 VAC FLUX VALVE EXY

-S (24)------------ ---- C4J1-E115 VAC OUT

{-

---- C5J1-D+ ~~ (24)------------------ 65J2B-28,C2J2-G

ANNUNCIATOR -V (24)------------------ 65J2B-29,C2J2-H5 VAC OUTPUT -w

<H -X (22)-T9r

HDG NO. 2 ROTOR t------------

clCLJIB-7,&ll-X,12J1-D

-Y (22)---------- ------- AC GND

{

z -Z (24)

1}

---Y---CL- ---7---HDG NO. 2 STATOR x -a (24)------~-!- ------- FIG. 4-;2

-b (24)------J-1- -------

{

;C vINTERLOCK NO. 1 NO ~~ (24)------------------ FIG. 4-: (SHT 2)

c -e (24)------------------ c2J2-yFLUX VALVE SHIELDCHASSIS GND :: (22)------%

c -h (24)------------------ 1OJ1B-28, 6J1-hINTERLOCK NO. 2 NC “

NO =; (24)------------------ FIG. 4-1226 VAC OUTPUT H -k ------NC42 VA MAX LH

-m (24) ---------------+ MANUAL $YNCSYNC SWITCH

<

i -n (24)-------------o SWITCH :3-p (24)--------------*4

FREQUENCY/PHASE LOCK+ -q ------NC RH

{

-r

SPARE6J1::


22-14-00Page 598.16May 25/90

Use or dwclosure of mformatlon on thw page is subject to the restrictions on the title page of lhm Iocument,

Honeywell W!RANCECITATION n/V


COPILOT’SMLS UNIT MLZ-850


EL DEVIATIONLO C116J1-1-------NC

429LO -2-------NC

AZ DEVIATIONRTN -3-------NC

+28VDCRET -4 (22)--------------------DC GND

+28VDC INPUT -5 (22)--------------------COPILOTS28 VDCFIG. 4-1

BACKAZ SELECTED -6-------NCMLSOFF -7-------NCANALOGVIDEO -8-------NCMORSEAUDIOHI -9-------NC

AZ DEVIATIONLO -lo------NC

EL DEVIATIONHI -11------NC

EL LOWLEVELFLAG -12------NCSPARE -13------NCEL HIGHLEVELFLAG -14------NCBACKAZ AVAILABLE -15------NCFRONTPREAMPPRESENT -16(24)-------------------C116J1-36

(IFFRONTPRE)EL CHANNELCHANGE -17------NCDPSKDATA -18------NCSPARE -19------NCAZ DEVIATIONHI -20------NC

MORSEAUDIOLO -21------NC

EL DEVIATIONRETURN -22------NCAZ LOWLEVELFLAG -23------NCAZ HIGHLEVELFLAG -24------NCAZ CHANNELCHANGE C116J1-25------NC

Interconnect InformationTable501(cent)

22-14-00Paqe598.17May25/90

Use or dmclosure of reformation on this page IS sub;ecf to the restrictions on the title pag ? of this document,


COPILOT’SMLSUNITMLZ-850(cent)

Function

IDOREARPREAMPPRESENT

SPAREBOARDTESTSYNC4SPARESYNC3429HIGH

SPARESHIELDGROUND

STRAP GROUND

RCB SHIELD GNDMSA 1MLS RCB RX (-)

MLS RCBTX (-)

TESTBUTTONINPUTMLS RCBTX (+)

MSA7MORSEIDENT(H)


C116J1-26------NC-27 (24)------------------- C116’]1-36 (lF

REAR PRESET)

-28------NC-29------NC-30------NC-31------NC-32------NC-33------NC

.>-34------NC-35

-36 (24)------------------- j~~;’~~~~:~,.

-37 (24)------------------- GND;:; (24)---------6--------- ~;;4:o:~3;

--------------I-l-t-------

67------ -

T

------- C164J1A-2137---”---

h-40--------------(;

!-------c164JlA-38

42-------v-------c164J1A-25

-41------NC

1-42----------------$~‘--- C164~lA-25

40----------’-37----------

~ ---- C164J1A-38

-43------NC

i116J1-44(24)-----------~T---- C164J1B-32

60----------U----- C164J1B-13


Page 598.18May 25/90

Useor dtSCIOSUfe of mformatton on thm page IS sub!ect 10 the restrlcilons onthe ttle page of thm :ocument.

Honeywell W!MYANCECITATION n/V

Function

SPARESYNC2 (EL)SPARE

SPARE

MSA 3MSA 2MSA PARITY

SPARESPARE

SPARE

SYNC 1

AGC VOLTAGE

CHANGE INHIBIT NOTMSA 4

MSA 6CHASSIS GND

MSA 5SPARESPAREMSA O

ID1TESTOUTPUTMLS RCBRX (+)


COPILOT’S MLSUNITMLZ-850(cent)


C116J1-45,-----NC-46------NC-47------NC-48------NC-49(24)-------------------

1-50(24)-------------------NOTE1-51(24)-------------------J-52------NC-53------NC-54------NC-55------NC-56------NC-57------NC-58(24)-------------------SEE NOTE 1-59 (24)------------------- SEE NOTE 1-60 (24)-ii::_:--:---fl

t--- C164J1B-13

---- - C164J1B-32-61 (24)-----=---~-~~- SEE NOTE 1-62------NC

-63------NC

-64 (24)------------------- SEE NOTE 1

-65------NC

-66-- ----NC

1C116J1-67---------------$’T ----- C164J1A-21

39--------- ----- C164J1A-34

37-------- Y

FOREANTENNA C116J2-1----RG-214/U-------------FOREANTFOREANTENNA SHAD---------------------------- FOREANT

AFTANT C116J3-1----RG-214/U-------------AFTANTAFTANT SHAD---------------------------- AFTANT

NOTE1: SEEPAGE580,


Paqe598.19Ray25/90

Use or disclosure of information on thm page IS subject to the restrictions on the title pag~: of this document

Honeywell W!W!!ANCECITATION V

Function

ENC ALT CIN+28VDCFANSPARE+28VDCCOM+28VDCCOM+28VDCCOMi-28VDCTDRRET

+28VDCTDR+28VDCTDR

RSBPRIMARY(+)RSBPRIMARY(-)

SELCAL/ACARSRET

ENCALTD4N

ACHPOWER+28VDC

RCBSPARE1 RX -

+5 VDC+28VDCCOMRET+28VDCCOMRET+28VDCCOMRET+28VDCTDRRET

VHF1PTT

SELCAL/ACARSSPARE

SIMULCOMRET

COMMACHDATA(-)

ENCALTC2N


COPILOT’SCOMUNITRCZ-850


C143J1-1(24)--------------------9JI-1!3,143J1-1-2 (24)--------------------FANRSD-3 -------NC-4 (22)-------------------

}

COPILOT-5 (22)-------------------- 28VOC-6 (22)------------------- FIG.4-1-7 (22)--------------------DCGN!3

-8 (22)-------------------)

COPILOT28 VDC-9 (22)--------------------FIG.4-1

-12-------NC

-13(24)-------------------9J1-27,143J1-13

-14------NC

-15------NC.

-16(24)-------------------sTRApp3RED-17(20)-------------------DCGND-18(20)-------------------DCGND-19(20)-------------------DCGND-20(20)-------------------DCGND

-21(24)-------------------160J1-cC160J1-C

-22-------NC-23-------NC

-24-------NC

-25-------NC

C143J1-26(24)-------------------9J1-19,143J1-26


Table 501 (cent)22--14-00

Page 598.20Mar 15/89

Use or disclosure of Information on this page IS subject to the restrictions on the title page of this document.

Hone~ell M!IRANCECITATIONn/V


COPILOT’S COM UNIT RCZ-850 (cent)


ENCALTD2N C143J1-27-------NCRCBSPARE1 RX + -28-------NC

EMERPHONELO -29-------NCRECPHAtJDHI -30-------NCEMERPHONEHI -31-------NCSPARE -32-------NCACHDATA+ -33------NCAUXAUD4 LO -34-------NCSIMULCOM -35-------NCSPARE3 -36-------NCHF COMXMIT -37(24)-------------------FIG. 4-19AUXAUD 2 HI -38-------NCliFCOMSQUELCH -39-------NCGND (AUDIOSHIELDS) -40 (24)-------------------BOBBIN

ACH+28VDC RET -41------NC

AUDIOBUSSHIELD(GND) -42-----------------------AUDIOBUSSHLD

+5 VDCRET (GND) -43 (24)-------------------STRAPP4BLKGND -44 (22)------BOBBINGND 4; ~~:]------BOBBINGND ------BOBBIN

SPARE -47-------NCSPARE -48-------NCAUXAUC)2 LO -49AUXAUD 1 LO

h-50---------------fJ------ HF2

66-------------!J------$“BOBBIN-------

AUXAUD3 LO -51-------NCAUXAUD3 HI -52-------NCRCBSPARE2 RX - -53-------NC+28VDCFANRET C143J1-54(24)-------------------FANBLU


Page598.21May25/90

Use or disclosure of Information on this page IS subject to the restrictions on the title pagt of thm document.

Honeywell ti%!~f~’”c’CITATION V

Function

TDR-DLP TD +

DIGAUDIOBUS2 (+)


COPILOT’SCOMUNITRCZ-850(cent)

SIDETONEPHONEAUDIOHIGND

SPAREGND

RSBSECONDARY(-)

AUXAUD4 HISPARE

SPARESPARE

AUXAUD 1 HI

GND

RCBSPARE2 RX +

ENCALTCOMMON

DIGAUDIOBUS2 (-)

ATCOFF/ON

GND (SQUATSWITCHRET)

SPARE


C143J1-55-------NC

-56t)

----------------fj---- FIG 4-10II .

---------------:!----------~

-57-------NC-58(24)-------------------BOBBIN

-59-------NC-60(24)-------------------BOBBIN

-61 ::t)---------------------- FIG.4-9

74 ---------------BOBBIN-----Y

-62-------NC-63-------NC-64-------NC-65-------NC

t}-66(24);;--;j----f------ HF2

----T?---‘-

-67(24)------------1------BOBBIN

-68-------NC

-69(24)-------------------9J1-28,143J1-69

b-70---------------------- FIG.4-10--------c-l-----

::---------(2

-71-------NC

-72-------NC

C143J1-73-------NC


Table 501 (cent) 22-J4-00Paqe 598.22

Mar 15/89UseordisclosureotInformationonth!spageissubjecttotherestrictionsonthetitlepageofthisSocument

Honeywell WE!’””CITATIONV

Function

RSBSECONDARY(+)

SPARESPARE 1SPARESPARESPARE

MUT SUPRET

RCBSPARE1 TX +RCBSPARE2 TX +

SQUATSW INENCALTC4NENCALT B2NENCALT BINTDR-DLPTD -CLOCKSIDEAODLP-TDRTD +SQUITENABLEMICHI

ON/OFFVHFCOMREMOTE



MUTSUP IN

ConnectorPin

tC143J1-74----------------(~----

61 ----e----------YBOBBIN------

-75-------NC-76-------NC-77-------NC-78-------NC-79-------NC

-80(24)i~-i;;i------7~

------c-J---

-81-------NC-82-------NC

-83(24)--------------------84(24)--------------------85(24)--------------------86(24)--------------------87-------NC-88(24)--------------------89(24)--------------------90-------NC-91(24)------------------

f-92(24)------------~-\i---

{ ii106(24)----1-,----

-93-------NC

C143J1-94(24)--------------{>---

80------------4

ConnectsTo

FIG.4-9

164J1A-42C164J1A-42143J1-94

FIG.4-79J1-24,143J1-849J1-16,143J1-859J1-23,143J1-86

STRAPP6 BLUSTRAPP1 GRN

C143J1-105160J1-DC160J1-D

C164J1A-42164J1A-42143J1-94


Table 501 (cent)22-14-00

Page 598.23Mar 15/89

Use or dwclosure of InformalIon on this page IS subject to the restrlcflons on the Mle pag: of this document.

Function

RCBSPARE1 TX -RCBSPARE2 TX -

ENCALTA4NENCALTAINENCALTA2NENCALT B4N

SE21ALDATAPARLOADNOTSIDEAIDLP-TDRTD(-)RETURN

MICLO



ConnectorPin

C143J1-95-------NC-96-------NC

-97(24)-------------------98(24)-------------------99(24)-------------------100(24)-----------------

-101(24)------------------102(24)------------------103(24)------------------104-------NC-105(24)-----------------

[

-106(24)----------f~i---

II92--------(7----

Connects To

9J1-22,143J1-979J1-20,143J1-989J1-21,143J1-999JI-17T143JI-100

STRAPP7 WHTSTRAPP2 ORNSTRAPP8 YEL

C143J1-91

160J1-14C160J1-W

TRANSPONDERANTENNA C143J2-1-------RB-214/U---------XPONDERANTTRANSPONDERANTENNA SHAD--------------------1’-----XPONDERANT

(SEENOTE)

COMANTENNA- C143J3-1-------RG-58/U--------- COMAN1SHAD------------------------- COMANT

(SEENOTE)

~: MAX COAXLENGTH30 FT.


Table 501 (cent) 22-14-00Page 598.24

Mar 15/89Use or dmcloswe Of mfofmatlon on tfw page is subject to the restrictions on the title page of thm uocu ment.

Honeywell W!J?AN’ECITATION 11~

7


COPILOT’SRMURM-850

Function

+28VDC LIGHTING

+28 VDCLIGHTINGRET+28 VDC

+28VDCRETURN

FMCSBUS (+)(RS422)FMCSBUS (-)(RS422)5 VDC LIGHT5 VDC LIGHTRET

5 VACLIGHT5 VACLIGHTRET

CHASSISGND

RSBSECONDARY(+)RSBSECONDARY(-)

W.O.!4.W.O.W.POLARITY

ATC IDENT

MBU INHIBIT

CHASSISGND

RSBPRIMARY(+)RSB PRIMARY(-)

SPAREDIG INON/OFFPAGEDELETESPAREDIG INSPARE


C144J1-A------NC

-B ------NC-C (20)--------------------;~~IL~T;S28V

-D (20)--------------------DC~ND-

-E ------NC-F ------NC-G (22)--------------------FIG.4-2-H (22)--------------------LIGHTGND

------NCI ------NC

-L (24)--------------------CHASSISGND

~:=:)FIG.~-g-M ------------1~1--fl------------

t Y-------

-P ------------------------A/CWOW SWITCH-R ------------------------W.O.W.=GND

-S (24)--------------------144J1-SGNDSWITCH

-T-------NC

-U (24)--------------------CHASSISGND

1-v -----------q~-----------w ------------ -

~FIG. 4-9

Y--------

t-------

-X-------NC-Y (24)--------------------144J1-D-z-------NC

C144J1-a-------NC


Page 598.25flay25/90

Use or dwc(osure of reformation on thw page IS sub)ect to the restrictions on the title pag!, of Ihts document.

Honeywell WIWANCECITATIONV

Function

SIDE SELECT BOSIDE SELECT B1SIDE SELECT EV PARITY


COPILOT’SRMURM-850(cent)

TEST ENABLECOMM FREQXFER

COMM MEM SELECT OMKR SENSE LEFT SIDE

MKRSENSERIGHTSIDE

COMM POWER OFFATC POWER OFFVOR POWER OFFDME POWER OFFADF POWER OFFMLS POWER OFF

SPARE DIGOUTSPAREDIGOUT

RSB SHLD GND

Connector Pin Connects To—-

C144J1-b-------NC-C (24)--------------------C144J]-U-d-------NC

-------NC%------NC

-9-------NC-h-------NC

-i-------NC

-j -------NC-k-------NC-m-------

-------!;~;-------NC-q-------NC

-r------- NC-s-------NC

C144J1-t-------------------------RSBSHLDFIG.4-9


Table 501 (cent)

22-14-00Page 598.26

Mar 15/89Use or disclosure of Information on this page IS subject to the restrictions on Ihe title page of this I: ocument.

Hone~el[ HIRANCECITATIONn/V

Function

ADFMODSHLD

ADF COSMOD

ADF ANT TEST

AOFOUTERSHLD

ADF INNERSHLD

ADF RF INPUT

ADF+15 VDC

ADF SIN MOD

ADF+15VDC GNC’I

ADF LOOPEN


COPILOT’SADFANTENNAAT-860

Connector Pin Connects TtI

C158J1-A-------NC

-B---------- --------- 4-- C164J1A-91

-c------------------------- C164J1A-77

-D-------NC

-E----

--TRC-50-2-----’--- C164J2-1

-G------------------------- C164JlB-1

-H--------------------+AY--d

C164J1A-104

-J-------------------------C164JIB-27

C158J1-K------------------------- C164J1A-101

NOTE: ADFANTENNATRIAXIALCABLESHALLBE TROMPETERPN TRC-50-2OREQUIVALENTTRIAXIALCABLE.

ALLWIRESSHALLBE STANDARD#22AWGPERMIL-W-B1044ORMIL-W-22759/16EXCEPTAS NOTED.


Page598.27May25/90

Use or disclosure of information on this page is sub!ect to the restrtcttons on the title pag~, of this document,

Honeywell WJFANCECITATIONn/V


COPILOT’S AUDIO PANEL AV-850

Function ConnectorPin ~ects To

HANDMIC PTT C160J1-A(24)--------------------COPILOTSMIC

EMERGENCYCOM PTT -B (24)--------------------160J1-F160J1-BC160J1-F143J1-21

VHF2 PTT -C (24)--------------------C143J1-21160J1-C

VHF2 MICHI

I

-D (24)---------T?--------

wII----------------

1--a

VHF 1 MIC LO -E (24)----------l-~

!

------

~;

R___-~ ------

VHF 1 PTT -F (24)--------------------

nEMERCOMPHONEHI -G (24)--------~-,-

!

--------

IIm

v----------------

----------

C143J1-92160J1-D

143J1-106,160J1-H160J1-E,C160J1-H

143J1-21160J1-F160J1-B,C160!J1-B

143J:1-31160J:i-G

SHIELDGND

EMERCOMMIC LO

\

n ----------160J:.-E-H (24)------r,

II160J:-H143J;-106

II C160J1-EP----0- ----------

HANDMIC LO -J (24)------------------- PILOTS MIKE ANDHANDMICHI &C160J1-K(24)------------ ------ PHONEJAcK Box ,,


22-14-00Page598.28May 25/90

Use or disclosure of Information on this page IS subject to the restrictions on the t!tle page of this jocument.

Honeywell WJttp’”c’CITATION n/V


COPILOT’S AUDIO PANEL AV-850 (cent)


CABIN/COCKPIT SPKR LO C160J1-L (24)-------------------- RH cKPT/cAB

SPKR LO

+28 VDC RTN -M (20)-------------------- DC GND

SHLD GND o-N (24)-----------------------B

EMERCOMMICHI

I

-P (24)-------:;---------- 160J1-R160J1-P

!/ C160J1-R

-----~-~--- 143J1-92H -------

VHF 1 MIC HI I

I

o-R (24)-------C-;==------- 143J1-92,

II 160J1-P[1 160J1-R,

----~j C160J1-PE -- --------

<J

HF 2 MICLO

1

-S (24)-------F;---------- 160J1-s,HF2

HF 2 MICHI -T (24)------&- -------- 160J1-T,HF2

+28 vDc -U (20)--------------------COPILOTS28 t/De+28 VDC -V (20)-------------------- FIG.4-1

VHF 2 MIC LO

1

-W (24)------1’+- -------- C143J1-106----j~ 160J1-WD ~-.- --------

l-’-----0B

HF 2 PTT -X (24)-------------------- 160J1-x,HFZ

COCKPIT SPKR HI C160J1-Y(24)---- -------------? >

RH CKPT SPKRL-- ---------------


22-14-00Page598.29May 25/90

Use or disclosure of information on this page IS subject to the restrictions on the title pag!, of this document.


Function

HF 1 MIC LO

HF 1 MICHI

HF 1 PTT

DIGAUD1OBUS2 (+)

DIGAUDIOBUS1 (+)

CABINSPKRHI

EMERNAVPHONEHI

DIMMINGRTNMASK/BOOMPTTMASK/BOOMHI

INTERPHONELO

PHONELO

EMERNAV/COMPHONE

COPILOT’SAUDIOPANELAV-850(cent)

Connector Pin Connects To.—

[

04- ‘- BC160J1-2(24)-------l-r---------160J1-Z,HF1

-a (24)-------~~L--.------ 160J1-a,HF1

-b (24)------------------- -- 160J1-b,HF1

-c .;:::::~~::::,::::] FIG.4-10

---- B-d

:!O1-----;-----t-l-

------ --- FIG. 4-10----------------

-e (24)-----------e ------]CABSPKRL-------- -&-------J

i

-f (24)-------R-----------~~~~j~~36

mII

9-----------------

------------ SHIELDGND-g (24)--------------------- TO DIMMINGRTN

-h (24)-------------------- ~&[~~~ETpTT

9}

-i (24) -i-----------------

------ ----- -----

-------A --@

JACK

-j (24)

1}

--------- 160J1-j1-1----------------- 160J1-S

-k------y-----~---------TORHPHONEJACK

-----JUL---------

LO C160J1-m(24)-!------------------~60J1-m143J1-29


C164J1B-51

------

22-14-00Paae 598.30..4

May 25/90Use or disclosure of mformatlon on Ihm page IS subfect

to the resfrlctlons on fhe t!tle page of this dOCUment.

Honeywell INR’”c’CITATION V

Function


COPILOT’S AUDIO PANEL AV-850 (cent)

ConnectorPin Connects To

DIG AUDIO BUS 2 (-) C160J1-n$

}

-------- --i~----------- FIG. 4-10c-- ---------------

$

~---aDIG AUDIO BUS 1 (-) -P -------- -r~r----------- FIG. 4-10

d-- ---------------

Y---Q }

+5 VAC/DCDIMMINGS -q (22)--------------------FIG. 4-2+28 VDC DIMMINGS -r ------NC

INTERPHONE HIt

-S (24)------1=,----- ----- 160J1-sj----------- ----- 160J1-j

PHONE HI C160Jl-t----------

1}1;----- ------

TO RHPHONE JACK

kti----------- ------

LB-----0


Table 501 (cent)

22-14-00Paqe 598.31

fiar 15/89Use or disclosure of mformatlon on this page IS subject to the restrtctlons on the title pag: of this document.


COPILOT’SAUDIOPANEL AV-850 (cent)


WARSING5 AUDIO C160J2-A-------NCWA&;;lNG1 LO -B-------NCSPL<EGND -c-------NCSHL2GND -D-------NCRESSRVED -------NCSPP;?E ~~-------NCWA2X;NGAUDIO2 LO -G-------NCCAE;NDISABLEWA?.:iINGAUDIO3 LO

-H-------NC

-J -------NCRES;$UIED -K-------NCMA~;:~R SE~S -------NCSTERO MUTE ~i-------NCSPA2: -N-------NCSERVICE PHONE LO

t]-P (24)-;------:1--- ------ TO SERVICE

~i---------- ------ PHONE JACKRES;RVED -R-------NCRES=RVED -S-------NC~E~~~VED -T-------NCR~~~~VED

Voic: RECORDER HI-u-------NC

1]-V (24)--------i~---- ------ TO VOICE

------ ---- ------ RECORDER-W------~NC

GWARNING 1 AUDIOWAF:i2NG 2 AUDIO -------NCRESERVED ~i------NCWAR!:INGAUDIO 4 LO -Z-------NCWA%;INGAUDIO5 LO -a-------MASKINTERCOMENABLE -b (24)--------------------TO COPILOT’S

HEADSET OXYGENMASK SWITCH

MKE DI’jABLE -C (24)-------------------- 160J2-cSPL:: -d-------NCSE$,:.”,;CEMICLo

1)-e (24)--------,~1---------TO SERVICE

q------ ---------v MIC

SEE’;’[CEPHONE HIt

-f (24)-;------,=/--------- TO SERVICE-------~7--- ------ PHONE JACK

RE5:;?\tED-9-------NC

RES::VED -h-------NCRES:;VED -i-------NCRES;;;VED -j-------NCSEE’i’ICEMICPTT -k-------NC

-1 -------NOTUSEDINCONNECTORWAF~jNG3 AUDIO -------NCREZ~~VED C160J2~~-------NC—..

Interconnect InformationTable 501 (cent) 22-=14-00

Page 598.32

Mar 15/89Use or disclosure of information on this page is subject to the restrictions on the title page of thts document

Honeywell !U!MYANCECITATION n/V


COPILOT’SAUDIOPANELAY-850(cent)


/INTERPHONEPTT C160J2-p-------------------------INTERPHONEPTT

SERVICEMIC HI

‘1

-q (24)-------O----------”TO SERVICEe---.-~l---------- MIC

VOICERECORDERLO

‘}

-r (24)-------C---------- TO VOICEv LJ-_----- ---- ----- RECORDER

RESERVED -s-------NC

WARNING4 AUDIO C160J2-t-------NC


22-14-00Page598.33May 25/90

Use or dmclosure Of Information on this page IS subject to the restrictions on the t~tle pagt of thw document

Honeywell W%”’””CITATION V

Function

RESERVED

RSB PRIMARY (-)

RSB SECONDARY (+)

RESERVEDRESERVED

+28 VDC PWR


COPILOT’S DME INDICATOR DI-850

5 V AC/DC LIGHTING INPUT

SPARESPARE

CHASSIS GND

SPARE

DC GROUND

LIGHTING COMMON

RSB SECONDARY (-)

RSB PRIMARY (+)

SPARES

Connector Pin Connects To——

C163J1-1-------NC

t>-2 ----------------f-~ --- FIG. 4-9

15 ----------- ----10 --------bJ,

-3 i----------------;-;y---~ FIG. 4-914 ----------- ---

Y10 ---------

-------NC::-------NC

-6 (22)-------------------- COPILOT’S28 VDCFIG. 4-1

-7 (24)-------------------- FIG. 4-2

-8 -------NC-9-------NC

-10 (22)------------------- &j SHLD

-11------NC

-12 (22)------------------- DC GND

-13 (24)---------------7--- LIGHTING GND

b-14 ------------------- --3 ---------J%l- --- ‘*G” 4-910 --------- ,

t)-15---------------------- FIG. 4-9

2 II------------- ---Y10 ---------

-16------NC-17------NC

C163J1-18------NC

-.


22-14-00Page 598.34Mar 15/89

Use or disclosure Of information on thts page E subject to the restrictions on the title page of thm locument.

Honeywell W!WSANCECITATIONV


COPILOT’S DME INDICATOR DI-850 (cent)


SPARE C163J1-19------NC28 VDC LIGHTING INPUT -20------NCPOWER ON/OFF INPUT -21 ------NC

-22 ------NC

SPARES -23------NC-24------NC

28 VDC RTN C163J1-25 (22)------------------- DC GND


Table 501 (cent) 22-14-00Page 598.35

Mar 15/89Use or disclosure of mformatlon on this page IS sub)ect to the restrictions on the title paq ? of this document.

HoneyelI MMRIANCECITATION n/V


COPILOT’S NAV UNITRNZ-850


CLU SPARE C164J1A-1 -------NC

DME HOLD NOT -2-------NCOME HOLD -3 (24) -------------------- 65J1B-34

DME SPARE -4 -------NC

DME 6 W 568 + DATA -5 (24)-------------------- 65J2B-50

DME SPARE -6 -------NC

ADF SHLD -7 (24)--------------------ADF SI+LOCLU SPARE -8- ------NC

CLUSPARE -9-------NCADF 26 VAC400HZ RTN -10------NCADF 26 VAC 400 HZ RTN -11------NC

ADF SYNCHRO Y OUT -12 -----NC

CLUSPARE -13-----NCV/I ON/OFF -14-----NCDME6 - 568 - DATA -15(24)-------------------65J2B-51DME RS 422SO - (2) -16-----NCDME6 W 568- CLK

n

I

-17 (24)---------~(- ------ 65J2B-55DME ACT 1 AUD OUT -18 -----NC

OPIE 6 W 568 + CLK -19 (24)--------1-!- ------ 65J2B-54A28d’

CLU MLS RCB SHLR -20----------_----

CLU MLS RCB TX1 A-I

C164J1A-21-------------- - ----- C116JI-67A34--------!! A----- C116J1-39 1SEE NOTE 5 FOR SHLD INFO

h IF THE ML-850 MLS RECEIVER IS NOT INSTALLED, THE MLS RCB RX AND TX PORTSMUST BE JUMPERED TOGETHER AT THE NAV UNIT MATING CONNECTOR AS SHOWN BELOW:

JUMPER 1: C164JIA-25 TO C164JIA-21

JUMPER 2: C164J1A-38 TO C164J1A-34

.


Page598.36May 25/90

Use or disclosure of Information on thm page IS sub!ect to the restrictions on the title page of this dacument.

Honeywell !!f#lEPANcECITATION n/V

Function

ADF SYNCHRO X OUT

ADF 26 VAC400HZ

CLUCHANGEINHIBITCLU MLS RCB RX1

DME6 W 568+ SYNCCLUSPAREDMEGNDSHLD

DMESPAREDMESPARECLUSPAREDMESPARE


COPILOT’SNAVUNITRNZ-850(cent)

ADFSYNCHROZ OUT (GND)

CLUMLS RCBTX2


C164J1A-22 ------NC

-23------NC

-24------NC

t-25--------------------- C116J1-42

A38--------J+J-- A-- C116J1-401A20---------SEENOTE5 FOR SHLD INFO

-26 (24)------------------2 65J2B-52-27 ------NC-28------------------------ DME SHLD

SEENOTE2 FORSHLD INFO

-29 ------NC-30 ------NC-31 ------NC-32 ------NC

‘1-33(24)--------Y-------- RMI,65J2A-35,65J2A-37,

A47----+-1--------A61------

Y---------

A7------C164JlA-34---------------------- C116J1-39 ~

J;-~-- C116J1 67 ~A21-------- -A20---------SEE NOTE5 FORSHLDINFO


22-14-00Paqe598.37May 25/90Useordisclosureof Information on thm page IS subject to the restrichons on the title pagi! of this document

Honeywell UAYJEPANCECITATION ii/V

Function

CLUSPARECLUSPARECLUSPARECLUMLS RCBRX2

ADFAUDIOOUTSHLDDMEON/OFFCLUAUX 1 AUD HIDMEMUTSUP



DMESPAREDMERS 422SD - (1)DME6 W 568 - SYNCDME FLAGADFDC COSOUT

CLUSPARECLUSPAREADFAUDIOHI OUTCLUSPAREADFAUDIOLO OUTCLUSPAREDMERS 422SD + (2)CLUAUX 1 AUD RTNDME SPAREDMERS 422 SD+ (1)CLU ACH DATA (-)

V/IRS 422SERD lBV/IMKIRLAMPM


C164J1A-35------NC-36------NC-37------NC-38 ~

$--------------- --- ---

1+Cl16J1-40~

A25----------- --- C116J1-42A20-------SEE NOTE 5 FOR SHLD INFO

-39------NC-40------NC-41------NC-42(24)-------------- --- 164J14-42

T

143J1-94C143J1-94

A28 (24)------SEE NOTE 2 FOR SHLD INFO

-43------NC-44------NC-45(24)-------------------65J2B-53-46(24)-------------------65J1A-73

i

-47(24)---------~j------ RMI,55J2A-36A61---------------A33---------------A7-------Y

-48------NC-49------NC-50------NC-51------NC-52------NC-53------NC-54------NC-55------NC-56------NC-57------NC

t-58(24)--------1’------- 165J1-N

?A70-------------- 165J1-M@ ------

-59------NCC164J1A-60(24)-------------------65J2A-61


22-14-00I’age598.38May 25/90

Use or disclosure of mformatlon on this page IS subject to the restrictions on the title page of this d ]cument.

Honeywell WKYANCECITATION n/V

Function

ADF DC SIN/SINOUT

CLUSPARECLUSPARECLUSPARECLUSPARE

ADFHF KEYCLUAUX 2 AUDHICLUAUX 2 AUD RTNCLUACH NAVCLOCK+

CLUACH DATA (+)

DME40 MV/MICLUACH NAVCLOCK-

V/IMARKERLAMPIV/IGS SUPERFLAGCLUSPARECLUSPAREADFANT TEST

CLUSPAREADFMODSHLD

V/IGND PS INCLUACH GNDCLUSPAREDME28 VDCRET

V/IRS 422SERD 2BV/I+28 VDCDME+28VDCADF+28VDC




n

1-

C164J1A-61(24)--------~f--------RMI,65J2A-34A47------ -------A33---- J-[ --------A7------Y

-62 ------NC-63 ------NC-64 ------NC-65 ------NC

-66-67-68-69

-70

------ ------ ------ -----

------NC------NC(24)------~1 r~

------------------------

‘&---Y

!(24)-------O----------

A58---!-i----------e---~

-71-----:NC

t-72(24)-------G----------

---J-!---------‘g_’i

-73(24)--------------------74(24)--------------------75------NC-76------NC-77------------------------

SEENOTE3 FORSHLDINFO-78-------NC-79-------NC

FIG.4-19

165J1-f165J1-P

165J1-M165J1-N

165J1-P

65J2A-5965JIA-74,C2J2-U

C158J1-C

-80------NC

*-81(24)-------------------A-82------NC-83(22)---------

1 }---------DC GND

A95----------------84------NC-85(22)-------------------COpILOT’S

}-86(22)-------------------28 VDCBUS

C164J1A-87(20)-------------------FIG.4-1


22-14-00Page598.39May25/90

Use or disclosure of mformatlon on thw page IS subject to the restrictions on the title pag! of this document.

Honeywell WMI!ANcECITATION V


COPILOT’S NAV UNIT RNZ-850 (cent)


13

——

RSB SECONDARY (+) C164J1A-88 --------------=-- --- FIG. 4-9A102---------- ----B85-------

CLU SPARE -89 ------NCCLUSPARE -90------NCADFCOSMOD

t-91 -------------=--- ---- C158J1-B

A104--------------- ---- C158J1-HYA105----------

SEE NOTE 3 FOR SHLD INFO

CLU SPARE -92 ------NCCLU SPARE -93 ------NCADF 28 VDC RET -94 (22)------------------- DC GNDDME 28 VDC RET -95 (22)------------------- DC GND

CLU SHLD GND -96 (24)---------1

t~~~ [~~~i-i--- ---- C116J1-35

------ ---- C116J1-44L)

DME ACT 2 AUD OUT -97-------NC

V/I +28 VDC -98 (22)------------------

}

COPILOT’SDME +28 VDC -99 (22)------------------- 28 VDC BUSADF +28 VDC -100 (20)----------------- FIG. 4-1

ADF LOOP EN -~ol----------------------- C158J1-KSEE NOTE 3 FOR SHLD INFO

RSB SECONDARY (-)t

-102----------------=---

}

FIG. 4-9A88 -------LJ- ---

xB85 ------- ----

CLU GND -103 (22)---------------;-- DC GND

ADF SIN MOD4

-104------------------=- -- C158J1-HA91--------------~-1 -- C158J1-B

ADF MOD SHLD Y-105------------------SEE NOTE 3 FOR SHLD INFO

CLU SPARE C164J1A-106-------NC


Table 501 (cent)22-14-00

Paqe 598.40Mar 15/89

Use or disclosure of information on this page is subject to the restrictions on the Mle page of thw document,

Function

DF

LULULULULU

+15 VDC

FANHISPARESPARESPARE STATSPARE STAT



Connector Pin

c164J1B-1------------------------SEENOTE 3 FOR SHLD INFO

-2 (24)----.-----.---------

-3 ------NC-4 ------NC

I (DIGAUD) -5 ------NCRTN (DIG AUD) -6 ------NC

-7 ------NC

-8 (22) ..------- -------- ----

-9 (24) ------- ------- ------

-10 (24) ------ ------ ------- -

‘/1SYNCCOMPINX:LUACH+28VDC!/1OBSD,G!/IOBs F

//1OBI O SIN1/1OBI O COS

:LUMLS MORSEID RTN

CLUCLUCLUCLUCLUCLU

v/I

V/IV/I

V/I

V/IADF

SPARESPARESPARESPARESPARESPARE

26 VAC400HZ H REF

RNAV VIDEOOUTRNAV VIDEOGND

400 HZ 26 VACRET

VOR/LOC AUDIO CTGND

ConnectsTO

C158J1-G

FAN RED

165J1-Eg$;~-:bC2Jl-CC

B50-----~q-13(24)~;;---------‘- - - ;;;:;;:~

v---------- -- -

A96----------

-14 ------NC-15------NC-16------NC-17------NC-18------NC-19------NC

-20(2z)-------------------;:RVAC#04H$* .-

-21------NC-22------NC

-23(22)-------------------AC GND

-24------NCc164J1B-25(22)-------------------DC GND

InterconnectInformationTable501(cent) 22-14-00.—

Page 598.41May25/90

UseordisclosureotInformationonthispageIS sub!ecttotherestr]ciionsonthe~ltlepageofthisdocument

Honeywell W!!RANCECITATION n/V



Function Connector Pin ConnpctsTo—-

CLU+5 VDC RTN C164J1B-26 (22)------------------- STRAPP4 BLKADF+15VDCGND -27------------------------C158,J1-J

SEENOTE3 FORSHLDINFOCLUSPARE -28------NC

DIGAUDIOBUS2 (-)

‘}

-29------------------ --B42__+l_ -- FIG.4-10B67--------

CLUSPARESTATIN (DIGAUD) -30------NCCLUAUDAUX SQUELCH -31------NC

CLUMLSMORSEIDt

-32(24)-----------i~---“~C116J1-44B13--------- -- -- C116J1-60

YA96---------

V/ISYNCCOMPIN Y -33------NCV/IOBS B -34(24)-------------------C2J1-EEV/IOBSC -35(24)-------------------C2J1-FFV/IVOR/LOCAUDIOHI

t

-36(24)-------~i--------- 160J!.-f,C160J1-f

B51---t-t--------- 160J1.-m,

YC160J1-m

B50----V/IOBIOGND -37(24)-------------------RMI,65J2A-52,

65J2A-54V/I PWRGND -38(22)-------------------DC GNDV/I+28VDC -39(22)-------------------COPILOT28 VDC

POWER, FIG.4-1

CLUCLUS+5V -40(24)-------------------STRAPP3 REDCLUSPARE -41------NCDIGAUDIOBUS2 (+) -42

i}----------------------

17- -B29---------- FIG.4-10‘3’B67---------

CLU SPARE -43 ------NC

CLU FAN RTN -44 (24)------------------- FAN 13LU

CLUAUD AUX XMT -45------NCCLUSPARE -46------NCV/ISYNCCOMPINZ -47-------NCV/IOBSA -48(24)-------------------C2J1-DDV/IOBS E C164J1B-49(24)-------------------C2J1-AA


22-14-00Page598.42hay25/90

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Honeywell WjJRANcECITATION n/V




V/IPWRGNDV/IVOR/LOCAUDIOLO

V/I28 VDC

CLUSPARECLUSPARECLUSPAREON SIDEMLSSELCLUSIDESPARECLUSTRAPSD DATACLUSTRAPCLKV/IGS FLAGV/ISYNCOUTZV/ISYNCCOMPVALIDV/IMKRAUDIOCTV/ICC ILSMODE

V/ITO/FROM+V/IMKRAUDIOHIDIGAUDIOBUS SHLD

ADF26 VAC400HZ

C164J1B-50(22)-------------------DC GND

1

-51(24)---.---O--------- 160J1-m,11 C160J1-m

‘36---T-T---- ‘---- ;;;:;~f;YB50----

-52(22)-------------------COPILOT28 VDCPOWER, FIG.4-1

-53------NC-54------NC-55------NC-56------NC-57(24)-------------------STRAPP1 GRN-58(24)-------------------STRAPP7WHT-59(24)-------------------STRAP P6 BLU

-60 ------NC-61 ------NC-62 ------NC

-63 ------NC-64 (24)------------------- RMI, C2J1-a,

65J1B-35

-65 (24)------------------- C2J2-A

-66 ------NC

-67 -------- ------ --A

t~B29 --------- -- --:FIG.4-10

IJB42 --------L-- -- ~.’

-68 ------NC

CLUSPARE -69------NCCLUSPARE -70------NCRSBPRIMARY(+) -71 9------------------ --

B81 I r$-------------

1FIG.4-9

B95---------~

ADF SYNTH LOCK -72 ------NC

ADF RS 422 TXD B -73------NCV/IMKRLAMPO -74(24)-------------------65J2A-63V/IDEVCOM C164J1B-75(24)-------------------C2J2-F,C2J2-C

65J2A-67,65J2A-66


22-14-00Page 598.43May25/90

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Honeywell h&r~fANcECITATION n/V




V/IILSMODELOGIC C164J1B-76------NCCLUSPARE -77------NCV/IVOR/LOCDEV+ -78(24)-------------------C2J2-E,65J2A-65V/IGS DEV+ -79(24)-------------------C2J2-D,65J2A-68CLUSIDESELECT -80~~~~11j111111c1=j5--=-STRAPP8 YELRSBPRIMARY(-) -81

B71}

--------1-i~:-~FIG q-~Y“B95---------

CLUSPARECLUSPARECLUSTRAPWD LOADRSBSHLD

CLUSPAREADFON/OFF

CLU ACHNAVCONTROL-V/IRS 422SERD 1ACLUACH NAV CONTROL +

V/IVORSUPERFLAGV/IVOR/LOCFLAGV/IMKRAUDIOLOCCLUSPARERSBSHLD

CROSSSIDEMLS SEL

CLU SPARE

CLU GNDADF LOCK

ADF RS 422 TXDAV/ISPAREV/IRS 422SERD 2AV/ISYNCOUTYV/ISYNCOUTXCLUSPAREV/ITO/FROM& FLAGCOM

-82------NC-83------NC-84-----------------------STRAPP2 ORN-85-------------------

At}

A88 ---------------FIG.4-9A102---------JGl-

-86------NC-87------NC

!

-88(24)----------~--- --- 165JI-G-89------NC II

-90 (24)----------JY4----- 165J],-FA81--------

-91 (24)-------------------RMI,65J1A-77,-92------NC C2J2-P-93------NC-94------NC-95------------------

Be1 A

B81 t}---------]:T-- FIG.4-9--------------96------NC-97------NC-98(22)-------------------DC GND-99(24)-------------------RMI,65J1A-80-1oo-----NC-101-----NC-102-----NC-103-----NC-104-----NC’105-----NC

C164J1B-106(24)------------------C2J2-S


22-14-00Page598.44flay25/90

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Honeywell !MFANCECITATIONn/V


COPILOT’SNAV UNIT RNZ-850 (cent)


ADF RF INPUT2=-

C164J2-l-

1

-TRC-50-2--------- C158J1-FAOF INNERSHLD C164J2- --- C158J1-EADFOUTERSHLD El

OUTERSHLDOPENAT NAV END

SEE NOTE3 FORSHLD INFO

V/IANT C164J3-1------RG-58/U------~+-----VOR/LOCANTV/IANT SHAD----------------------I------ VOR/LOCANT

V/IGS ANT C164J4-1------RG-58/U------\~----- fXANT

V/IGS ANT rSHAD---------------------------- GSANT

V/IMKRANT C164J5-1------RG-58/U------fl----- MKRANTV/IMKRANT YSHAD---------------------------- MKRANT

DMEANT C164J6-l------RG-214/U-----fiJ----- DMEANTDMEANT 1SHAD--------------------------- DMEANT

NOTE1: SHIELDSOF PAIRSA47-A61,ANDTRIPLEA12-A22-A33ARE TIEOTOGETHER.

NOTE 2: StiIELDS OF A42 AND PAIRSA16-A54,A44-A57,AND GROUNDA28ARE TIEDTOGETHER.

NOTE 3: ADF ANTENt4ATRIAXIAL CABLE SHALL BE TROMPETER PN TRC-50-2 OR

EQUIVALENT TRIAXIAL CABLE.

ALL WIRES SHALL BE STANDARD#22AWG PERMIL-W-B10440?MIL-U-22759/16EXCEPTAS NOTED.

THEOUTERSHIELDJUMPERTO GNDAT THEANTENNASIDESHALLBE 20AWGAND ITSLENGTHSHALLNOT EXCEED10 INCHES.

NOTE 4: SHIELDS OF TRIPLES B1l-B12-B37, B9-BIO-B49 AND B34-B35-B48 (IF USED)

ARE TO BE TIEDTOGETHER.

NOTE5: SHIELDSOF PAIRSA21-A34ANDA25-A38ARETIEDTOGETHER.

Interconnect InformationTable501 (cent) 22-14-00

Page598.45May25/90

Use or dmclosure of mformatlon on this page 1s subject to the restncttons on the tnle pag,: of thts document.

Honeywell MRE!AN’ECITATION Ilfl

%4010 ALT

n~ 2A 2w7-C RAOIO ALT ,20WI

I t-- ‘“2’”8’

+ ‘3A’ \6J.lo ‘JNAV ,5W)

&Q?s— AF’OFFW*.WING

iL APOFCHORN

.,

J=.:;:;5= ;; ) ‘“6”’’’0”)

28 VDC OUSQ

63J1-N wl*$O[~

I ,,

Pilot’s28 V dc BUSFigure4-1 (Sheet1 of 2)

C,2W

!E4w,,.

,59WI-n

34W,

,4W)

m !6m7m

.


22-14-00Pa~e 598.46fray25/90Useordisclosureof Information on this page IS subject to the restrictions on the title page of thm document.

Honeywell !R!J?ANcECITATIONV

DIRECT GYRO 2

~*~u C-’’’K’’’’;”HDG VALID INTLK (lW)

I DME 2

L“RMU 2

5 C144J1-C RM-850 (34W)

LoMLS 2

2 C116J1-5 ML-850 (l’W)

AD-17190

Copilot’s 28 V dc 6USFigure 4-1 (Sheet 2)



UseordisclosureOfinformationonthispageIS subject10therestr!ctlonsontheI;tlepag!ofthisdocument.

Honeywell MI!!RANCECITATIONV

PILOT’S SIDEi65J1-D CD-850

163J1-7 DI-850

5 VDCCNMMING

115J1-3 DC-811 (5VW

23J1-P RI-106S (1.2 VA)

63J1 -S WI-650

3J1 -26 ED-800 (1 .2W)

18J1 -A BARO ALT (2.5 VA)

8J1 -A FD MODE SEL (6.6 VA)

1 lJ1 -g AP CONTROLLER (3 VA)

) 16J1 -3 VNAV (2.5 VA

4B 160J1 -q AV-850

144J1 -G RM-850

COPILOT’S SIDE

0-5 VDCDIMMING

w C163J1-7 DI-850

4) C2J1-M RD-450

4r C144J1-G RM-850

Cl 60J1 -q AV-850

AD-16209-R2

EdgeLightingFigure4-2


Table 501 (cent)

22-14-00Page 598.48Mar 15/89

Use or dwclosure of mformat!on on this page IS sub)ect to the restrictions on the t!tle page of this jocument.

Honeywell WURANCECITATIONV

RADAR REF

Q 59J1-D WU-650STABILIZATION REF

%~ “::: z:” ‘A)(32 VA)

VG 1

115VAC Q400 Hz - v “’J1-C VG-14A

MAX PWR

80 VA START40 VA RUN

FD 1

Q‘~JIB-l FDC (1 1.5 VA)

%~~~~~%(;~~A,

AD-16412-R2

AC PowerRequirementsFigure4-3 (Sheet1 of 3)


22-14-00Paae 598.49

fiar 15/89Use or dmclosure of mformatlon on this page IS subject to the restncttons on the title pagt of this document.

Honeywell Mii!!!fy’”c’CITATIONV

}

C- I 4D

SG-6051805~65J2&13

C6JlFLUX VALVE

Cl 4D2.4 VA i INCLUDES

26 VAC >

NAV 2

26 VACQ

C164J16-20 (.1 ‘vA)

AO-16211-R3

Copilot’s AC PowerRequirementsFigure4-3 (Sheet2)


Page 598.50Mar 15/89

Use or disclosure of information on thw page IS sub]ect to the restrictions on the I[tle page of this <Iocument.

Honeyell !ljttf~j{’”c’

EFIS 1 I 5J1-D DUAL REMOTE COMP

26 VAC‘~ “’-” ‘“D “ ‘A)

h 65J2A-13 SG-605f605 (1 VA)

23J1 -B RI-106 SEL CFCSEXCITATION (1.2 VA)

23J1-J RI-108SSEL lIDG EXCITATION (1.2 VA)

1 15J1-1 RATE GYRO8 VA START6,5 VA RUN

NAV 1

Q26 VA’ 164J1 6-20 (.1 VA)

AD-1 621 O-R2

Pilot’sAC PowerRequirementsFigure4-3 (Sheet3)


Page598.51Mar 15/89

Use or disclosure Of Information on this page IS sublect to the restrictions on the title pag? of this document.

Honeywell WNJi”ANcECITATIONV

PILOT’S SIDE

{.

+ 65J2A-71 SPD DEV (H) ‘

AOA ERROR

65J2A-72 SPD DEV (L)

I

PILOT”SDISPLAY

AOA VALID 65J1 A-75 SPD DEV VLD. I

AD-16212

AOA/Speed CommandFigure 4-4


Table 501 (cent)

22=14-00Page 598,52

Mar 15/89Use or disclosure of mformatlon on this page IS subject to the restrictions on the ttle page of this jocument.

PILOT’S RT 20J1

+28 VDC PWR C>~ +28 VDCI

I>

I n + I

III1 I ,[:=C

65J1APILOT’S SG

POWER GND 78 RA VALID IN

jg

65J2BTRIP COMMON 76 ~ RA TEST OUT

65J2ATEST SWITCH - T +

+:+ - }

RAD ALT

PRIMARY OUTPUT (H) , wINPUT

COMMON OUTPUT (C) N> w

AUX OUTPUT (H)

E~~ ,’ ‘1

‘~

7J1B

r

PILOT’S FD

OUTPUT TEST E 18 ~ +

1

RAD ALT

RA VALID Y 19+ - INPUT

TRIP POINT #1 u 35 + RA VALID IN

TRIP POINT #2 v~ 46 ~ TRIP POINT #1

t I~sz+

+

TRIP POINT #2

I

AD-I 698

Radio Altimeter InterfaceFigure 4-5


Table 501 (cent)

22-14-00Page 598.53Mar 15/89

Use or disclosure of mtormahon on thts page IS sublect to the restrictions on the title pag ? of this document.

Honeywell W!J5!!ANC’CITATION V

—

~,my=—m—— — - I GENERATOR 6N1A

1- 7J7A 6sJ2B 94

AP ENG 46——-. — —

L65.J2A

,(l,J,~ AUTOPILOT COMPUTER 190———- —

v L11 +2EW AP ENG I

r———— —

PILOT OC-S1l d

Y115.J1

———7W7A I

lIJ1 llW1

1

44r

20 HI

t1I

1 :L }

Iu 42 PITCH WHEE .

INPuTI

t 45 29 Lo Iv— 43L (A ——-. — — 4

!t (GNU]

I I “<’”———— —

J–––––< I65.JIB PILaS SYMBOL GENERATOR -A

-t-l4’1 ‘sMODEGNO 1“~

P-L47 IAS MOOE GNO

———— —

37

32

39

L--r—————

~1 PILOT MS-206 1x IA6 MOOE GNO

i

-w

~ VS MOOE GNOI

———— — A*D.,62,4..W

Air Data Command Block DiagramFigure 4-6


Table 501 (cent)

22-14-00Paqe 598.54

Mar 15/89Use or disclosure of information on this page IS subject to the restrictions on the title page of thts d ~cument.

Honeywell !WWANC’CITATION V

T a 63JI-H WI-650

65JIB12 SG-605/805

wow 143J1-83 RCZ-850

C143J1-83 RCZ-850

165J1-Y CD-850

144J1-P RM-850

C144JI-P RM-850

AD-16215-R2

WeightOn “,~iselsSwitchFig:::,:4-7


Table 501 (cent)

22-14-00Page 598.55Mar 15/89

UseordisclosureofinformationonthispageE subjecttotherestrictionsonthetitlepaq~!ofthisclocument.

Honeywell M!UR!ANCECITATION V

.

9J1-12 +

16J1-17

AD-17191-RI

Altitude Alert HornFigure 4-8

Use or disclosure of inf ormatlon


Table 501 (cent) 22-14-00Page 598,56Mar 15/89

on this page is subject to the restrictions on the title page of this jocument.

Honeywell ~i~ik!’”c’CITATIONV

Primus II Radio System BusArchitectureFigure4-9


22-14-00Page 598.57Mar 15/89

Use or disclosure of Information on this page IS sub]ecf to the festnctlons on the title pa{je of Ihm document.

Honeywell WNRANC’CITATION V

t --PILOT AUDIO PANEL --

: 7

COPILOT AUDIO PANEL

AUDIO

{

+ 160J1-Q .T In C160J1-~ + -

BUS 1 II

v }AUDIO

– 16W1-P

+1 “+. ‘

C160J1-p - BUS 1—.

16W1-N ‘—--

4—— J b C160JI-N--

AAUDIO

{

160Jl~ .BUS 2 II Ii

c160J1-~

‘}

AUDIO160J1-~

<J

— J—

- C160J1-Q , BUS 2

--< --

PILOT COMM COPILOT COMM

{

:’1 C143J1-56 yAUDIOBUS 1 II II

4}4)

\

‘ 1

> AUDIO

II II BUS 2– 143J1-70 ,

yC143J1-70

/

—-143J1-42 J l-- C14Wl_42

——

PILOT NAV COPILOT NAV

{

In C164J1B-42 ‘AUDIOBUS 1 II

b ~ ●T’ ‘1

/, AUDIO

IIJ

BUS 2Cl 64J1 B-29

164JI B-67 4 I f——

L C164J1B-67—-

127

oleu13

Audio System BusFigure 4-10


Table 501 (cent)22-14-00

Page 598.58Mar 15/89

Use or disclosure of mformatlon on this page is subject to the restrictions on the title page of thm rmcument.

Honeywell lHMRANcECITATION V

ALITOPILOT/TRIM PILOT’S APITRIM

+33

- ~.10.E1A.3A/? ENG-~ 4

e

+33 VPWR AUTWILOT

,fn

OFFc

lWIALIG14T

&No 327

+29 v UP TRW .—< 55 LAMPS

lWIAo

f17~F ~13 G

AP OFF

iWARNING

3W1B

!

1, HORN

‘“~EmR ~“ <I

~ #lM :

‘n

I*

LyAI

/

lLUIA &’$G &*4~ 2+)

+22 v ON TRIM -<58 <K3

NOTE

1. ALL REmvs snow IN LiNENEPEGIZEDPOSITION

) Z 5, 3S. K4 MUS7 CARRV EMGAGE CIRCUIT

v

CURRENTS AS S140WN TO MAINTAIN AuTO.PILOT sAFs7w, 71.IE COMPONENTS M“=BE RATEO TO SWITCH 3S WC e 3 bMP3INOWTIVE MINIMUM. ALSO K7. UJ

Engage/Trim InterlockFigure 4-11


Table 501 (cent)

22-14-00Page 598.59

Mar 15/89Use or disclosure of information on this page is subject to the restrictions on the title pag? of thm document.

NN

1

6J1

<

10JIB

ENG INTLK —< 28‘%~a’’_~’&~-~L~;

C6JI C6J I

PILOTS C-14Dh<+)

i

DIR GYRO NO. 1I

r -3I I I———

1 RMI iVALID I

I6J 1

I I

III

HDG 2 STATOR X ~ 10J1A I

I4

46 HEADING XI I

I

IHDG 2 STATOR Y B

I

I + I 47 HEADING Y

I II HDG 2 STATOR Z z

2

L

I

———!

48 HEADING Z

iI I

COPILOT’S C-14D I IDIR GYRO NO. 2

r ——— 1 -=}RMI 2=

I II

C6J 1I I

HOG 2 STATOR X ~ 10J1B

I

I

I

d

-

~ P: . . . . . ..-[- 1

48 HDG RATE DISABLE

I IHOG 2 STATOR Y B 1

I -

I

I —.— JI

I

PILOT’S HDG REV

HDG 2 STATOR Z z

L ———=

J

——.115J1 plLo~S Dc T.,)”,,,,,.

L.—.— ‘ 29;:SGP,:’.’

W_i

——. J=Al) 11928.ill

Honeywell &i!}I~~ANcE

JUNCTION BOX I ROLLRATEMONITOR

57J1

r+

B

Ill

+15 VDC, llJ1-YAP TEST

I J J I I I

-G->’:llJ1

.Z

(AP CONT)P+ +28 VDC

ENG SELVALID

10J1B

33+ %:%.LATCH

YE

THE ROLL RATE MONITOR RELAYSARE ENERGIZED DURING THE NORMALOPERATION WHEN VG IS VALID.

nAUTOPILOT

+-q- ‘c

fiJ+-1

i

10J1 B

4’~<~

+28 VDCAP ENGSEL

Autopilot Engage Select and W Valid SwitchingFigure 4-13

AO-18152



Use or disclosure of mformatlon on this page IS sub!ect to the restrictions on the tnle pag? of this document.

Honeywell M!!URANCECITATION Ilfl

TRIP BE-

E ‘E :s:;::’’O’”-’FEET ALT

AneroidSwitchWiringFigure4-14

++28’”’

AD-783-R3

LEFfTHROITLE>65% N2

RIGHT ‘ &THROTfLE>85% N2

AO-SS9S

ThrustCompensationFigure4-15

WARN

AD-785

TorqueWarnAnnunciatorFigure4-16


22-14-00Page598.62May 25/90

Use or disclosure of tnformatlon on this page IS subject to the restrictions on the title page of this : ocument.

—.

Honeywell WE!ANCECITATION n/V

‘Pp‘EL’8J’-f~

~7Jl B-53, 7JIA-89I

h.Cd I

I

DME

DME

NC II

I

-! IVALID, 65J2B-88 I

I

16J 1-33

I J

I

NC I

+28 VDC

alTN, 65J2B-94 (lx+ 28V

%5J2B-79

GROUNDRANGE

AD-1 7502-R2

VNAV Disable

Figure 4-17


Page598.63May25/90

Useordisclosureofinformationonthispageissubjecttotherestnct!onsonthetilepagtoffhlsdocument.

Honeywell W!KW’”c’CITATION n/V

I II I II IIIIII

I I II I LRN B_NCI LRN AI 1°

—NC

1B-96

“J2B-8~ ‘5J2B-8~ 65J2B-8~ AD-20073

EFIS Display Select I)iscrete Outputs

Figure 4-18


22-14-00Page 598.64May25/90

Use or disclosure of information on this page is subject to the restrictions on the title page of this rocument.

Honeywell tiiWIEPANcECITATION n/V

r —1HF~ST~NO. 1

I I r+28 V FROM HF 1

y+

I I

[T- L r(

GROUND AT CCM 1

I—.——

143J1 COM UNIT NO. 1 7

la I --- I

I I 37 HF COTJ XMIT

I

I I I

I I——— A

I I - —1164J1A NAV~ll%. 1

I 1

~ J7°=

u vI

HF #1 PIT66 ADF H[’ KEY

I

——— J L I— ——- J

-—1C164J1A NAVyNiT~. 2

‘HF%?ST~ N= 7

I

z

P“’ K =

I

66 ADF HF KEYHF #2 P7T

I II

I IL I- ——. J

I II f)+ II II I I t-

La ——.#26 V FROM

--

HF 2

A GROUND AT COU 2

4

—1Cl 43J1 CO=NI=O. 2

I\

37 HF COF4 XMIT

I

W I———JAD-20074

HF KeyConfigurationFigure 4-19.


Paqe 598.64.1May25/90UseordisclosureofInformationon this page IS subject to the restrictions on the tttle pag! of this document.

Honeywell MMRANCECITATION n/V

APPENDIX A

SINGLE EDZ-605/805 WITtlMDZ-605/805 INSTALLATION

.. .- -.


22-14-00Page598.64.2

May25/90Useordisclosureofreformation on thk page IS subject to the restrictions on the title page of this jocument.

Honeywell #$&{ANcE

APPENDIX A

ThisappendixdefinestheEFISinterconnectsfor an installation

whichhasa multifunctiondisplaysystem.


Table 501 (cent) 22-14-00Page 598.65

Mar 15/89Use or disclosure of In!orrnaoon on this page is subject to the restrictions on the Mle pag ? of this document.

Honeywell !&N~f~ANc’CITATION V

PILOT’S ELECTRONIC HSIED-6oo/t300

Function Connector Pin ~~ects To)

PRIX DEFL(Ill)+-(-

2Jl:; [;j]-------------j--:r-65J1A-61-------------------

‘i--65J1A-6265J1A-63

SECX DEFL (OUT)+{-

------NC:: ------NC

28 V DC PWR + -5 (22)--------------------PILOT28VDC28 V DC PWR + >-6 (22)--------------------POMER,FIG.A-1

STROKEREADY(PRI) +

t

-7 (24}--,c7---------------65JIA-50,

{- A -~ (24)-;-;---------------65J,A-5,125JlB-59

r’125JlB-6b

STROKEREADY(PRI)SHIELDGND -36------PRIY DEFL(IN) +

<- !-9 (24)---------------FT- 65J1A-64-10(24)------------------- 65JIA-65

‘-t--65JI~-65SECY DEFL(OUT) +

{--11------NC-12------NC

POWERRETURN -13(22)--------------------DC PIIJRGNDPOWERRETURN -14(22)--------------------DC PWRGNDVALIDOUTPUT(PRI)(GND=VALID)-15(24)--------------------65JL4-46STROKEREADY(SEC} +

{--16------NC-17------NC

SEC X DEFL(IN) +{-

i-18(24)------------------ 125JIB-13-19(24)--------------~-& 125JlB-14

I

VALIDOUTPUT(SEC)(GND=VALID)-20------NCREVSELECT(PRI)

1

-21(24)--------------------FIG.A-4SIGNALGND -22(22)------------------- SIGNALGNIICHASSISGND -23 (22)--------------F ----- CHASSISGNDSEC Y llEFL (IN) +

-(--24(24)--------------?-----125JlB-15-25(24)--------------~-~--’-125JIB-16

~- SHIELDGNDINCLINOMETERLIGHTING +

<--26------NC-27------NC

SPARE 2J1-28------NC


Table 501 (cent) 22-14-00Page 598.66

Mar 15/89Use or disclosure of Information on this page k sub!ect to the restrictions on the Mle page of this document

Honeywell t&!Mfl!ANcECITATION n/V

PILOT’S ELECTRONIC HSI (cent)ED-6oo/8oo


REV SELECT (SEC) 2J1-29 ------NCDIM CONTROL

{-+ -30 (24)----------

$n. ----

-31 (24)---------SPARE -32 ------NC

W- ‘---

H -33 (24)--------------------RASTER DIMCONTROL W -34 (24)--------------------

L -35 (24)--------------------STROKEREADY(PRI)SHIELDGND -36 (20)--------------------

SPARE

A

-37 ------NCCOLOR3 (PRI) +

{-1

I-38 (24)------------- --=---39 (24)------------- --&-

lD--

TEMPANNUN GND OUTPUT -40 (24)--------------------SPARE

A

-41------NCCOLOR 2 (PRI) +

(.

1I

-42 (24)-----D.-o-co- .j~--

-43 (24)------------- - ~--b--

STROKEREADY(SEC)SHIELDGND -44------NC

SPARECOLOR 1 (PRI) +

(-

SPARESPARECOLORO (PRI) +

(-

SPARESECX DEFLSHIELDGND

A1

A1

A1 SEEPARA.4.1.3.4.A

115J1-40215JI-41

115J1-50l15J1-51115J1-52SHIELDGND FOR2J1-7,2JI-8

65J1A-4065JIA-4165JIA-42ANNUNCIATOR

65J1A-3765JIA-3865J1A-39

-45------NC

$-46 (24)---------------=- 65J1A-34-47 (24)-------------+-- 65J1A-35

-- 65JIA-36-48------NC-49------NC

I-50 (24)---------------~j- 65J1A-31-51(24)---------------r=-- 65J1A-32

‘L 65J1A-33-52------NC

2J1-53------NC


Paqe598.67fray25/90

Use or dlscfosure of Information on this page IS subject to the restrictions on the t!tle pagf of th~s document

Honeywell PAM!’”c’CITATION V

PILOT’S ELECTRONIC HSI (cent)ED-6oo/8oo


VIDEO(PRI){-+ A 1 t

2J11~~~;~]---------------~T------------- -------

Y --SECY DEFLSHIELD6ND -56 ------NC

SPARERASTER/STROKE (PRI) + 1{-A

FLYBACK (PRI) <A

LEFTPHOTOSENSOR OUT +{-

RIGHTPHOTO SENSOR OUT +<

ACOLOR3 (SEC) + - 2

{-

-57------NC

i-58(24)---------------r~r--59(24)----------------y--

1-60(24)----------------~~~-61(24)---------------~y’--

-.-62------NC-63------NC-64------NC-65------NC

1-66(24)---------------:r-

~-67(24)--------------JVi--

ConnectsTo

65J1A-2865J1A-2965J1P:-30

65J1A-4765J1A-4865J1A-4965J1A-4365J1A-4465J1A-45

125JIB-53

125JIB-54

COLOR2 (SEC) +

{

A2

~’

-68(24)---------------.~l--125JIB-51

-69(24)---------------’Y’--125JIB-52

COLOR1 (SEC) +

{A2

t

A-70(24)---------------r:--125JIB-49

-71(24)---------------$- :25JIB-50

COLORO (SEC) +

{-A 2

1-

J-72(24)---------------r;--125J1B-47

-73(24)---------------’vi--125JIB-48

VIDEO (SEC) +

{-

A 2

I

1-74 (24)----------- -------- 125J1B-45

2J1-75 (24)----------- ----’--’--125J1B-46Y

A~-- SHIELDGND

2 SEE PARA4.1.3.4.B


Table 501 (cent)

22-14-00Page 598.68

Mar 15/89Use or disclosure of information on this page IS sub!ect to the restrictions on the Iltle page of this :,ocument.

PILOT’SELECTRONICHSI (cent)ED-6oo/8oo


RASTER/STROKE (SEC) +

{- 1

2J1-76 (24)------------ ---~~;- 125J1B-55

-77 (24)------------ ---!=!- 125J1B-56

FLYBACK(SEC) +

{-A2 I

-78(24)---------------fj--125J1B-57

2J1-79(24}------------~---~-i--125J1B-58

1 -- SHIELDGNO


Table 501 (cent) 22-14-00Page 598.69

Mar 15/89Use or dwclosure of Information on this page IS sub!ect to the restrlcfrons on the title page of thm document.

Honeywell !!;FJ.?’NCECITATION V

PILOT’S ELECTRONIC ADIED-6oo/8oo

Function Connector Pin Conn~cts To—-

PRIXDEFL (IN) +<- i

3J1-1 (24)------------------- 65JIA-55-2 (24)---------------~:]--65J1A-56

SHIELD --- 65J1A-57SEC XDEFL (OUT)+

{-------NC

:: ------NC

28 V DC P14R + -S (22)--------------------PILOT’28 V DC28 V DC PMR + )-6 (22)--------------------POWER,FIG.A-1

STROKEREADY(PRI)

STROKEREADY(PRI)PRIY DEFL(IN)~+

L-S1-lIELf)

SEC Y DEFL (OUT)+<-

SHIELDGND -36-9-lo

-11-12

I(24)-------~~j---------

(24)---~#---~#-------

!(24)---------------~r-(24)------------------

L-.

------NC---:’-NC

65J1A-23,125J1A-5965J1A-24,125J1A-60

65J1A-5865J1A-5965J1A-60

POWERRETURN -13(22)--------------------DC PMl? GNDPOWER RETURN -14 (22)-------------------- DC PMRGNDVALIDOUTPUT(PRI)(GND=VALID)d: (24)--------------------65J1A-19STROKEREADY(SEC) +

{-------NC

-17------NC

SEC X DEFL (IN) +{- I

-18(24)------------------ 125Jl13-9-19(24)---------------’vi--125J1B-10

VALIDOUTPUT(SEC)(GND=VALID)-20------NCREVSELECT(PRI)

/

-21(24)------------------- FIG.A-4SIGNALGN!I -22(22)------------------- SIGNALGNDCHASSISGND -23 (22)------------------- CHASSISGNDSECY DEFL(IN) +

<- 1-24 (24)------------------- 125Jl&ll

3J1-25(24)---------------L=’--125J1B-12I-- SHIELDGND

!L1 SEEPARA4.1.3.4.A.


Table 501 (cont.) 22-14-00Page 598.70

Mar 15/89UseordmclosureofInformationonthispageIS sub:ecttotherestrictionsonthetitlepageofthisd,jcument.

Honeywell tiiV&?’ANcECITATION n/V

PILOT’S ELECTRONIC ADI (cent)ED-6oo/8oo


INCLINOMETERLIGHTING +[

3JI-26(22)--------------------;f:E;I:HTING.-

[- ~$~ (22)--------------------DC GNDSPARE ------NCREVSELECT(SEC) -29------NCDIMCONTROL

(-+ n

t-30(24)---------- - ------ 115JI-38-31(24)---------W------” 115J1-39

SPARE -32------NC

{

H -33 (24)-------------------RASTERIJIMCONTROL W -34 (24)-------------------3

-35------NCSTROKEREADY(PRI)SHI:LDGND -36 (24)--------------------SHIELDGNDFOR

3J1-7,3J1-8

SPARE

A


(-1 -38(24)------------

!-.q.- 65J1A-13

-39 (24)--------------11-- 65JlA-14t 65J1A-15

TEMPANNUNGIWIOUTPUT -40 (24)--------------------ANNUNCIATOR

SPARECOLOR2 (PRI) +

(- A 1

STROKE READY (SEC) SHIELD GNDSPARECOLOR 1 (PRI) +

(- A 1

SPARESPARECOLORO (PRI) +

(- A 1

SPARE

-41------NC

1-42(24)-------------------43 (24)---------------’‘--

Y .--44------NC-45------NC

I-46 (24)--------------~~:---47(24)-------------- - --

Y ----48------NC-49------NC

i

..

-50(24)-------------~---51 (24)------------------

3J1-52------NC --

65J1A-1065J1A-1165J1A-12

65J1A-765J1A-865JlA-9

65JIA-465J1A-565J1A-6

.


Page598.71May25/90

Useordisclosure 01 Information on this page IS sub!ecf to the restrictions on the fltle pagt of thm document.

Honeywell W!W.R””c’CITATION V

PILOT’SELECTRONICADI (cent)ED-6oo/8oo


SECX DEFLSHIELDGND 3J1-53------NC

VIDEO(PRI) +

{-‘A 1

i-54 (24)----------- ---------55 (24)----------- ----&~-

&--

SECY DEFLSHEILDGND -56 ------NC

A ~---

FLYBACK(PRI) +<-

1 -60(24)--------------------61(24)---------------&~-

---

LEFTPHOTOSENSOROUT +{

-62------NC-63------NC

RIGHTPHOTOSENSOROUT ;{

-64------NC-65------NC

COLOR3 (SEC) + -

‘ {- A 1

-66(24)--------------l=r--2

-67(24)--------------&!--

COLOR2 (SEC) +

{- 1

L

A

-68(24)--------------;-;--2

-69(24)--------------!:!--

COLOR1 (SEC) +

{- A 1-70(24)---------------);--

2-71(24)-----------Y---:=!--

COLORO (SEC) +

{A

i

A-72(24)---------------:-1--2

-73(24)---------------’ut--

VIDEO(SEC) +

{4 I

A-74(24)---------------;-;-2

J1-75(24)---------------’----

T---42 SEE PARA4.1.3.4.B.

ConnectsTo

65J1A-165J1A-265J1A-3

65J1A-2065J1A-2165J1A-2265J1A-1665J1A-1765J1A-18

125J1A-53

125J1A-54

125J1A-51

125J1A-52

125J1A-49

125J1A-50

125J1A-47.

125JIA-48

125J1A-45

125J1A-46

SHIELIIGND


22-14-00Page 598,72Mar 15/89Useordisclosureofreformationonthmpagem subjecttotherestrictionsonthetitlepageofthisdlcument

Honeywell ~ifJkPANcECITATION V

PILOT’S ELECTRONICADI (cent)ED-6oo/8oo


RASTER/STROKE (SEC)

1{: x:; :;:::::::::::: :;::::: ::::;

AFLYBACK (SEC) + 2

{ I L-78(24)---------------j-r-125J1A-57

3J1-79(24)---------------!~--125J1A-58Y

L -- SHIELD GND


22-14-00Page 598.73Mar 15/89

Useordisclosureof Information on this page IS subject to the restrictions on the tttle pagt of !h!s document.

Honeywell WNEPANC’CITATION V

PILOT’S SYMBOL GENERATORSG-605/805

Function ConnectorPin ConnectsToI

ADIVIDEO(+)ADIVIDEO (-)ADI VIDEO SHIELD GNDADICOLORO (+)ADICOLORO (-)ADICOLORO SHIELDGNDADICOLOR1-(+)ADICOLOR1 (-)ADI COLOR1 SHIELDGNDADICOLOR2 (+)ADICOLOR2 (-)ADICOLOR2 SHIELDGNDADICOLOR3 (+)ADI COLOR 3 (-)ADICOLOR3 SHIELDGNDADIFLYBACK(+)ADIFLYBACK(-)ADIFLYBACKSHIELDGNDADIVALIDADIR/S (+)ADIR/S (-)ADIR/SSHIELDGNDADISR (+)

ADISR (-)

ADICS SR (+)ADICS SR (-)

ADHSHSHSHSHSHSHSI-ISHSHS

65J1A-1-2-3-4-5-6-7-8-9-lo-11-12-13-14-15-16-17-18-19-20-21-22-23

-24

-25-26

I(24)--O;------------(24)-J--------------(24)--Y

}(24)-l=j------------(24)--Y-------------(24)-- L

.--------(24)-1-1--1----------(24)--Y *(24’,-, ~.-.!(zfl)-----------------(24)--Y

{(24)--.=------------(24)--’.-;--------.---(Zbj.-l’

!(24)--,~1------------(24)----------------(24)--Y(24)-----------------

I(24)-:7-- ----------(24)----------------(24)--Z

I

(24)------------r~r-

(24)------------~:--T

L --

------NC------NC

3J1-543J1-55

3J1-503J1-51

3J1-463J1-47

3J1-423J1-43

3J1-383J1-39

3J1-603J1-61

3J1-153J1-583J1-59

3J1-7,125J1A-593J1-8,125J1A-603J1-36

CS VALID -27 ------NCVIDEO(+) :;; [;:]-fl-------------;;;-::VIDEO(-) ---------------- -.VIDEOSHIELDGND -30 (24)--Y iCOLORO (+)

[-31 (24)--’=7-------------2J1-WI

COLORO (-) -32 (24)----------------2J1-51COLORO SHIELDGND -33 (24)--Y ~COLOR1 (+)

J-34 (24)--=--------------2J1-~16

COLOR1 (-) -35 (24)-~-L-COLOR1 SHIELDGND

-----------2J1-47-36 (24)--Y ~

COLOR2 (+) 65J1A-37(24)-j~j-?-----------2J1-42


22-14-00Page 598.74

Mar 15/89Use or disclosure of information on this page IS subject to the restrictions on the tttle page of th!s document

Honeywell WJRANCECITATION V

Function

HSICOLOR2 (-)HSICOLOR2 SHIELDGNDHSICOLOR3 (+)HSICOLOR3 (-)HSICOLOR3 SHIELDGNDHSIFLYBACK(+)HSIFLYBACK(-)HSIFLYBACKSHIELDGNDHSIVALIDHSIR/S(+)HSIR/S(-)HSIR/SSHIELDGNDHSISR {+)

HSISR (-)

HSICSSR (+)HSICSSR (-)

HSICSVALIDADIXDEFOUT (+)ADIXDEFOUT (-)ADIXDEF SHIELDGNDADIY DEFOUT (+)ADIY DEF OUT (-)ADI Y DEF SHIELD GNDHSIX DEFOUT (+)HSIX DEFOUT (-)HSIX DEFSHIELDGNDHSIY DEFOUT (+)HSIYDEFOUT (-)HSI Y DEF SHIELD GNDDC811DATA(+)DC811DATA(-)

RESERVED


ConnectorPin11~

65J1A-38(24)-----------------39 (24)--Y

!-40 (24)--=--------------41 (24)-----------------42 (24)--Y

1-43 (24)-l=_i-------------44 (24)-----------------45 (24)--Y-46 (24)-----------------

i-47 (24)--=--------------48 (24)-J-L-------------49 (24)--Y

1

-50 (24)------------T’=’r-

-51 (24)------------~-l-

f-.-52 ------NC-53 ------NC

-54-55-56-57-58-59-60-61-62-63-64-65-66-67-68---

65J1A-69

------NC

t(24)--7~r-----(24)----------(24).--’Z’,(24)-----------(24)--J--------(24)---Y(24)--1~7------

------ ----f;:]---y~(24)---9--,----(24)--J-J-y----(24)---Y I

{

(24)--l~T-----(24)----------SHIELDGND

------NC

------------

-------- -- - -

------------

------------

------- --- - -

ConnectsTo

2J1-43

2J1-382J1-39

2J1-602J1-61

2J1-152J1-582J1-59

2J1-7,125J1B-59’2JP8,125J1B-602J1-36

3J1-13J1-2

3J1-93J1-10

2J1-I2J1-2

2J1-92J1-10

115J1-34115J1-35


Table 501 (cent)

22-14-00Page 598.75Mar 15/89UseordisclosureofInformationonthmpageissubjecttotherestrictionsonthetitlepagtofthtsdocument.

Honeywell M!!E?ANC’CITATION n/V



RESERVED 65J1A-70------NCRESERVED -71------NCRESERVED -72------NCVALIDIN 1 SRNDMEVLD -73(24)-----------------C164J1A-46,

125J2B-23VALIDIhl2 SRNVRTDV VLD -74(24)-----------------C164J1A-74,

125J2B-24VALIDIN 3 SPODEVVLD -75(24)-----------------FIGA-5VALIDIN 4 VNAVDEVVLD -76(24)-----------------16J1-22,7J1B-9

125J2B-26VALIDIN 5 SRN LATOV VLD -77 (24)----------------- C164J1B-91,

‘ 125J2B-27

VALID IN 6 RAC) ALT 1 VLD -78 (24)----------------- FIG A-6,20J1-Y7J1B-35

VALID IN 7 RADALT 2 VLD -79------NCVALIDIN8 LRN1 LAT OV VLD -80 (24)----------------- C164JIB-99(ADF 2 VALID WHENDIN6 = GND)VALIDIN9 LRN1VRTDV VLD -81 ------NCVALID IN1OADF VLD -82(24)-----------------164J1B-99,

125J2B-32

VALIDIN1lFDCVLD -83(24)-----------------7J1B-47,125J26-33

VALIDIN12HDG 1 VLO -84(24)-----------------6J1-e,125J2B-34VALIDIN13ATT 1 VLD -85(24)-----------------lJI-GG,7J1A-19

125J2B-35VALIDIN14CS/SGVLD -86(24)-----------------125J1B-18VALIDIN15ARINCO VLII -87------NCVALIDIN16LRN 1 28 V WPTALERT -88------NCVALIDIN17ROT VLD -89 ------NCVALID IN18 TCS 65J1A-90 (24) ----------------- 1OJ1B-19,

125J2B-40

~: ALL VALIDS ARE +28 V DC.


Page598.76May25/90

Use or disclosure of mformatlon on this page IS subject to the restrictions on the tllle page of this d>cument

Honeywell M!E!ANCECITATION n/V

4



VALIDIN19SPARE 65J1A-91------ NCVALIDIN20HDG 2 VLD -92 (24)----------------- C2J2-X,

125J2B-58

VALID IN21 ATT 2 VLD -93 ------ NCVALID IN22 AP ENGAGEDIN -94(24)-----------------;:;J~Bi:4,

VALID IN23 TK DETENT IN -95 (24)-----------------llJ1-H,1OJ1B-15125J2B-45

VALIDIN24APS VLI)IN -96 (24)-----------------16J1-23,125J2B-46

DIN O SYMGEN L/R IDO -97 ------ NC

DIN 1 DC811 -98(24)-----------------65J1A-105DIN2 SRBRG3/4 -99 (24)-----------------65J1A-105DIN3 ADFBRG 3/4 -100 (24) ---------------- 65J1A-105DIN4 ASCB D/S -101------ NCDIN 5 EFISD/S -102(24)----------------65J1A-105DIN6 CROSSIDESENSORDISABLE-103(24)----------------65J1A-105DIN 7 ROT ON/OFF -104------ NCDIN GND -105(24)-----------------PROGGNDATT PULSEOUT 65J1A-106”(24)-----------------125J1A-40

NOTE: ALL VALIDS ARE +28 V DC.

.


Page598.77May25/90

Use or disclosure of Information on this page IS subject to the restrictions on the title pag[ of this document.

Honeywell WMRANCECITATIONV



DIN 8 CPMNON/OFF 65JlB1~ &--~;----------- 65J1A-105DIN 9 WINDPO/XYDIN 10 +5VROTVAL -3 (24)-----------------15J1-7,

125J2A-33DIN 11 RALT IDO ------NCDIN 12 RALT ID1 :: ------NCDIN 13 TRANSITIONON/OFF ~~ (24)-----------------65J1A-105DIN 14 LRN1PHASE(P/S) ------NCDIN 15 ADIONHSI (OFF/ON) ------NCDIN 16 SRN2ID1 :: ------NCDIN 17 ADF 1/2 -10 (24)-----------------65J1A-105DIN 18 MLS 1/2 -11 (24)-----------------65J1A-105DIN 19 wow -12 (24)-----------------FIGA-8DIN 20 GSPDIDO -13 (24)-----------------65J1A-105DIN 21 GSPDID1 -14 ------NCDIN 22 ATT # IDO -15 ------NCDIN 23 ATT# ID1 -16 ------NCDIN 24 ATTGL IDO -17 ------NCDIN 25 ATTGL ID1 -18 ------NCDIN 26 ATT2P/S -19 ------NCDIN 27 RESERVED -20 ------NCDIN 28 FLIP -21 ------NCDIN 29 HDG1DEF -22 ------NCDIN 30 HDG1F/S-M/T -23 (24)-----------------TOF/SSWITCHDIN 31 HDG# IDO -24 ------NCDIN 32 HDG# ID1 -25 ------NCDIN 33 HDTGL IDO -26 ------NCDIN 34 HDTGL ID1 -27 ------NCDIN 35 HDG2DEF -28 ------NCDIN 36 HDG2F/S-M/T -29 (24)-----------------TOF/SSWITCHDIN 37 HDG2P/S -30 ------NCDIN 38 S BRGCD/CS 65J1B-31------NC


Table 501 (cent)22-14-00

Page 598.78flar 15/89

Use or disclosure of Information on thm page is sub)ect to the restrictions on the t!tle page of thm d )cument.

Honeywell %I!uYPANCECITATION n/V



DIN 39 SRNSRC IDO 65J1B-32------NCDIN 40 SRN SRC 101 -33 (24)-----------------65J1A-105DIN 41 DMETTN -34 (24)-----------------C164J1A-3,

125J2A-50DIN 42 TTL ~:~ (24)-----------------C164J1B-64DIN 43 SRN TGL ~ ------NC

DIN 44 HSI MODE -37 ------NCDIN 45 RESERVED -38 ------NCDIN 46 LNAV MODE GND -39 (24)----------------- 7J1A-72,

125J1A-63

DIN 47 GA MODEGND -40 (24)----------------- 7J1B-68,125J1A-64

DIN 48 ASEL ARM MODE GND -41 (24) ----------------- 7J1B-71, 8J1-~

125J1A-65

DIN 49 ASEL CAP MODE GND .42 (24)-----------------7J1B-72,8J1-g125J1A-66

DIN 50 HDG SEL MODE GND -43 (24)----------------- 7J1A-71, 8J1-~125J1A-67,llJ1-~

DIN 51 RESERVED -44 ------NCDIN 52 ALTHOLDMODEGND -45 (24) ----------------- 7J1B-75, 8J1-Q

125J1A-68

DIN 53 V/SHOLDMODEGND -46 (24)-----------------7J1B-76,8J1-Z,125J1A-69,115J1-47

DIN 54 IASHOLD MODE GND -47 (24)-----------------7J1B-77,8J1-X,125J1A-70,115JI-48

DIN 55 MACH HOLD MODE GND -48 (24)-----------------7J1B-78,125J1A-71

DIN 56 GS ARM MODE GND -49 (24)-----------------7J1B-69,8J1-g125J1A-72

DIN 57 GS CAP MODE GND -50 (24)-----------------7J1B-70,8J1-h125J1A-73,1OJ1B-21

DIN 58 VNAVARMMODEGND -51 (24)-----------------7J1B-73,8J1-S125J1A-74

DIN 59 VNAV CAP MODE GND -52 (24)-----------------7J1B-74,8J1-T125J1A-75

DIN 60 LRN1SRCNORM/ALT65J1B-53------NC

A1’ GROUNDTHISPIN IFMLS IS INSTALLED.


Page598.79May 25/90

Use or disclosure Of Information on thm page IS subject to the restnct!ons on the title pagt of thm documenf,




DIN 61 LRN1BRGCARD/ 65J1B-54------NCCASE

DIN 62 NAVARM MODEGND -55 (24)----------------- 7J1A-85,125J1A-76

DIN 63 NAV CAP MODE GND -56 (24)-----------------7J1A-$36,125J1A-77

DIN 64 BCARM MODEGND -57 (24)-----------------7J1A-68,8J1-~125J1A-78

DIN 65 BC CAP MODE GND -58 (24)-----------------7JIA-67, 8J1-14

125J1A-79DIN 66 VORAPR ARM MODE GND -59 (24) ----------------- 7J1A-137,

125J1A-80DIN 67 VORAPR CAP MODE GND -60 (24)----------------- 7J1A-$38,

125J1A-81DIN 68 LRN1BG/DA - -61 ------NCDIN 69 LRN1IDO -62 ------NCDIN 70 LRN1ID1 -63 (24)-----------------65J1A-105DIN. 71 LRN1ID2 -64 (24)-----------------65J1A-105DIN 72 LRN1 1D3 -65 (24)----------------- 65J1A-105DIN 73 LRN1 SRC IDO -66 ------NCDIN 74 LRN1 SRC ID1 -67 (24)----------------- 65J1A-105 “DIN 75 SRN2IDO -68 ------NCDIN 76 LRN1DT/DA -69 ------NCDIN 77 LRNTGL IDO -70 ------NCDIN 78 LRN TGL ID1 -71 ------NCDIN 79 LRN1MG/TU -72 ------NCDIN 80 LRN2IDO -73 ------NCDIN 81 LRN2ID1 -74 ------NCDIN 82 LRN2ID2 65J1B-75------NC


Table 501 (cent)

22-14-00Paqe 598,80

Mar 15/89Use or disclosure of mformatlon on this page is subject to the restrictions on the title page of thm d~cument

Honeywell WE!ANCECITATION n/V

PILOT’S SYMBOL GENERATOR (cor)t)SG-605/805


DIN 83 LRN2ID3 65J1B-76------NCDIN 84 LRN2SRC IDO -77 ------NCDIN 85 LRN2SRC ID1 -78 ------NC

DIN 86 AIR DATACMDDISABLE -79 ------NCDIN 87 SPARE -80 ------NCDIN 88 LRN1BRG3/4 -81 (24)-----------------65J1A-105(ADF2 BRG 3/4 WHEN DIN6 = GND)DIN 89 CITATION11/V -82 (24)-----------------65J1A-105DIN 90 IRS1AN/DIG ------NCDIN 91 IRS2AN/DIG :R ------NCDIN 92 RADALT S/D -85 ------NCDIN 93 A/S,AOA,SPD IDO -86 (24)-----------------65J1A-105DIN 94 A/S,AOA,SPD ID1 -87 (24)-----------------65J1A-105DIN 95 CS IN -88 ------NCDIN 96 COUPLE1/2 -89 ------NCDIN 97 STBY SELMODEGND -90 ------NCDIN 98 SPARE -91 ------NCDIN 99 ATT #1 WRAP -92 (24)-----------------65J1A-105DIN 100ATT #2 WRAP -93 ------NCDIN 101ATT #3 WRAP -94 ------NCDIN 102ATT #4 WRAP -95 ------NCDIN 103RESERVED -96 ------NCDIN 104RESERVED -97 ------NCDIN 105FMSSINGLE/DUAL -98 ------NCDIN 106A/S,AOA,SPD ID2 -99 ------NCDIN 107CAARULES -1oo------NCDIN 108SPARE -101------NCDIN 109SYMGENL/RID1 -102------NCRESERVEDDC IN (+) -103------NCRESERVEDDC IN (-) -104------NCRESERVEDDC OUT (+) -105------NCRESERVEDDC OUT (-) 65J1B-106------NC


22-14-00Page598.81May 25/90Useordisclosureofreformationonthispagem subjecttotherestrictionsonthetitlepag~ofth(sdocument

Honeywell MNR’ANCECITATION V



}’65J2A-1 (22)------------------;;~;;28 V DC

-2 (22)------------------FIGURtA-1-3 (24)------------------125JIB-82

+28VOLT POWER

+28VOLTPOWERHDGVALIDIN

28 VOLTRETURN28 VOLTRETURNCHASSISGND --CHASSISGNDSIGNALGNDSIGNALGNDDISCRETE GNDTO/FRDC IN (+)

-4-5-6-7-8-9

(22)------------------(22)------------------(24)------------------(24)------------------(24)------------------(24)------------------

DC PWRGNDDC PhlRGNDCHASSISGNDCHASSISGNDSIGNALGNDSIGNALGNDDISCRETEGND125JIB-97,

-io-11

(24)-----------------

7(24)----,:-----------Ilk

(24)----U-----------TO/FRDC IN (-) -12 125JI.B-98,

ONSIDEACREF (+) -13 PILOT26VAC,FIGA-3SHIELD GNDAC GNDSHIELDGNDlJ1-x,125J3A-1lJ1-y,125J3A-2lJI-z.,125J3A-3SHIELDGNDlJ1-p,57Jl-E125J3A-4lJ1-CI,57J1-F

ONSIDEACREF (-)

#1 PITCHX

#1 PITCHY

#l PITCHZ

-14

-15

-16

-17

t

-----

(24)-----------~--~j-

!(24)-------------+

~ II(24)-----------------

I 1’---

f(24)-------------~~r-#1 ROLLX

#1 ROLLY

#1 ROLLZ

-18

-19

-201(24)-------------~-;-

(24)---------~----+~-125J~A-5lJ1-r,57Jl-G125J3A-6

I

7(24)---------‘----+SHIELDGND6J1-L,#1 HDGX

#1 HDGY

#l HDGZ

-21

-22

65J2A-23

125J3A-76JI-M,125J2,A-86J1-K,125J3A-9SHIELDGND

1(24)-------------:-:-

(24)---------j----l~--

1L--


Table 501 (cent)

22-14-00Page 598.82

Mar 15/89Use or disclosure of !nforrnaflon on this page !s subject to the restrictions on the title page of this c ocumenl

Honeywell WUWANCECITATION n/V



SYSASCBA DATA(+) 65J2A-24 n----------------------SYSASCBA DATA(-) -25 II----------------------

VL-_

SYSASCBA CLK (+) n-26 -----------------_--.--

SYSASCBA CLK (-) -27 ----------------------;--

#1 HDGSYNC+t

-28 (24)--------------~1-

#1 HOG SYNC - -29 (24)--------------!!*-Y

MFDG/SDEV DC IN (-) -30 (24)------------------TS WITH 65J2A-99

#1 LRNDSRTRKX -31 ------NC#l LRNDSRTRKY -32 ------NC#1 LRNDSRTRKZ -33 ------NC#2 ADF BRGX/SIN

t-34 (24)---------;------

#2 ADF BRGY/COM ljt

-35 (24)---------1,------

#2 ADF BRGZ/COS -36 (24)---------+;&-

#2 ADF BRGCOMIii

-37 (24)----------J------

#1 LRNTO/FROM(+) -38 ------NC#1 LRNTO/FROM(-) -39 ------NC#1 LRNLATDEV (+) -40 ------NC#1 LRNLATDEV (-) -41 ------NCDH H -42 (24)------------------DH W 65J2A-43(24)------------------

ConnectsTo

FIG.A-9

FIG.A-9

6J1-U,125J3A-136J1-V,125J3A-14SHIELDGND125J2B-12,

C164J1A-61,125J3A-48C164J1A-33,125J3A-49C164J1A-47,125J3A-50C164J1A-33,125J3A-51

125J1B-33115J1-54,125J3A-25


22-14-00.—Page598.83May25/90

Use or disclosure Of !nformatlon on this page IS subject to the restrictions on the title pagf of this document

Honeywell WWANcECITATION n/V

Function

DH L

CRSSELX/TACH+

CRSSELY/TACH -

CRSSELZ

SHIELD GNDHDG SEL X TACH +

HDGSELY TACH-

HDGSELZ

SHIELDGND

VOR BRGX/SIN

VOR BRGY/COM

VOR BRGZ/COS

VOR BRGSP/COM

#l ADF BRGX/SIN

#l ADFBRGY/COM

#1 ADF BRGZ/COS

#1 ADF BRGSP/COM


Connector Pin

65J2A-44(24)------------------

-45 (24)------------------/1

-46 (24)-i-,-{-------------

-47 (24)-j!-

?

L ------------

(24)--n-48 (24)-1-i

+------------

t-49 (24)-;-I-------------

-50 (24)--1-!$-------------

Y

f-q-51 (24)~~~-------rl----

,?ii -----52 (24)----------1

+LI ----’53 (24)----------lj,

-54 (24)----------LJ*----

K

+

-------55 (24)--------:--------

?-56 (24)-------:+-------

-57 (24)-------~-:-f------

‘‘ *------65J2A-58(24)-------i-l-

Y-----

ConnectsTo..-

115J1-55,125J3A--2623JI-0,125J3A-2723J1-E..125J3A-28,23J1-F,125J3A-29,

23J1-L.125J3A-30,23J1-M,125J3A-31,23J1-N,125J3A-32,

C164J1E!-11,125J3A-33C164J1EI-37,125J3A-34C164J1E!-12,125J3A-35,C164J1E-37,125J3A-36SHIELD GND164J1A-61,125J3A-37164J1A-33,125J3A-38164J1A-47,125J3A-39125J3A-40,164J1A-33SHIELDGND


Page598.84May25/90

Use or disclosure of mformatlon on this page is subject to the restrictions on the title page of this I: ocument,

Honeywell WIIEPANCECITATIONn/V



INNERMKR(+) 65J2A-59 (24)------------------C164J1A-73,125J2B-75

MARKERCOMMON -60 (24)-------,

MIDDLEMKR(+) -61 (24)-----=---------325J2B-77,C164J1A-60

TS with65J2A-1OO

MFDLATSTEER f-j$-62 (24)------ -- -------1.25J1B-99

OUTER MKR (+)

SPARESRNCRSDEV (+)

SRNCRSDEV (-)

SRNGS DEV (-)

SRNGS DEV (+)

RADALT (+)RADALT (-)

SPEEDCMD (+)SPEEDCMD (-)

PITCHCMD (+)

PITCHCMD (-)

ROLLCMD (+)

-63 (24)------------------125J2B-79,C164J1B-74

-64 ------NC-65 (24)------------------C164J1B-78,

125J3A-41-66 (24)------------------C164J1B-75,

125J3A-42-67 (24)------------------C164J1B-75,

C2J2-C125J3A-43,65J2A-66

-68 (24)------------------C164J1B-79,. .

u)]125J3A-44,C2J2-D

-69 (24)------------- -- FIG A-6-70 (24)------------- --- “

-- SHIELDGND

t]’71 (24)----------- ----- FIG A-5

+-72 (24)----------- -- -L- “

t

-- SHIELD GND-73 (24)-------------m- 7J1B-30,

II 125J3A-58-74 (24)------------- -- ;7J1B-31,

T125J3A-59

t

-- SHIELDGND65J2A-75(24)-------------0-- 7J1A-29,

11 :125J3A-60


22-14-00Page598.85May25/90

Use or disclosure Of mformatlon on this page IS subject to the restrictions on the ftle pagti of thm document,

Honeywell W!WANcECITATION V



ROLL CMD (-) k65J2A-76 (24)------------ --!-!-

Y

7J1A-30,125J3A-61

1

-- SHIELD GNDRATE OF TURN (+) -77 (24)----------- --r~r- 15J1-4,

125J3A-62RATE OF TURN (-) -78 (24)----------- --!-~- 15J1-5,

Y125J3A-63

I

-- SHIELD GNDAIR DATA CMD (+) -79 (24)-------------~r- 9J1-39,

125J3A-64AIRDATACMD (-) -80 (24)-----------------

Y

9J1-33,7J1B-37125J3A-65

-- SHIELDGNDSTEER IN (+) -81 ------NCSTEER IN (-) -82 ------NCMFD LRN SEL VALIN (P-ID2) -83 (24)------------------ 125J1B-83MFD LAT STEER VALIN -84 (24)------------------ 125J1B-84MFD NAV SEL VALIN (IDO) -85 (24)------------------ 125J1B-85

MFD V/L DEV VALIN -86 (24) ------------------ 125J1!3-86

MFD GS DEV VALIN -87 (24------------------- 125J1B-87

MFD DME VALIN -88 (24)------------------ 125J1B-88

MFD TK DETENT VALIN -89 (24) ------------------ 125 J1B-89

MFD AP ENGAGED VALIN -90 (24)------------------ 125J1B-90

MFD ADS VALIN -91 (24)------------------ 125JiB-91

MFD LNAVAPPDIN -92 (24)------------------125J1B-92

MFD TTL DIN 65J2A-93 (24)------------------ 125J1B-93


Table 501 (cent)

22-14-00Page 598.86

Mar 15/89Use or disclosure of mformatlon on this page is sub)ect to the restncttons on the title page of Ih!s cocument.

Honeywell MI!W’NCECITATION V



MFD DME TTN DIN 65J2A-94(24)------------------125J1B-94

MFDMID MARKDIN (5V) -95 (24)------------------125J1B-95

MFD PW MOVE DIN -96 (24)------------------125J1B-96

MFD V/L DEV DC IN (-) -97 (24)------------------125J2B-10

MFDV/LDEVDC IN (+) -98 (24)------------------125J2B-9TSWITH 65J2A-30

MFDGS DEVDC IN (+) -99 (24)------------------125J2B-11TSWITH 65J2A-62

MFDLRNLATIN -100(24)------------------125J1B-1OO

MFDDME IN (-) -101(24)------------------125J1B-101

MFD DME IN (+) -102(24)------------------125J1B-102

MFDCRSERR(+)IN

I

-103(24)-------------y~i- 125J1B-103

MFDCRSERR(-)IN -104(24)-------------L=L- 125J1B-104

1

1-- SHIELDGNDMFDHDGERR(+)IN -105(24)--------------F;- I25J1B-105

MFIIHDGERR(-)IN 65J2A-106(24)-------------i:!--125J1B-106

L-- SHIELDGND


Table 501 (cent) 22-14-00Page 598.87

Mar 15/89Use or drs.closure of information on this page IS sub)ect to the res!rlct!ons on the Mle pag I: of this document

Honeywell MW!ANC’CITATION V


Function Connector Pin Connects To—.!—

DIN 112 SPL SEL O 65J2B-1 -----NCDIN 113 SPL SEL 1 -2 -----NCDIN 114 SPL SEL 2 -----NCDIN 115 SPL SEL 3 :: -----NCDIN 116 SPL IN O -----NCDIN 117 SPL IN 1 :: -----NCDIN 118 SPL IN 2 -----NCDIN 119 SPL IN3 :; -----NlT’jWITH65J2B-1OOFD LATDC OUT (-) %-9 (24)-5- -------------- 7J1A-18SG PWRDN -10 (24)~----------------- FIGA-4FD TO/FR DC OUT (+) -11 (24)---5-------------- 16J1-30FD TO/FR DCOUT (-) -12 (24)--~Y!------------- 16J1-31

SHIELD GND ---CROSS SIDE AC REF (+)

/

-13 (24)------------ -r~i- COP1LOT26VAC,

II FIG. A-3

CROSS SIDE AC REF (-) -14 (24)------------ -~-L- AC PWR GND~-- SHIEL[jGND

:2 PITCH X -15 ------NC#2 PITCH Y -16 ------NC#2 PITCHZ -17 ------NC#2 ROLLX -18 ------NC#2 ROLLY -19 ------NC#2 ROLLZ -20 ------NC#2 HDG X -21 (24)------------------ C2J1-S#2 HDG Y -22 (24)------------------ C2J1-1:#2 HDG Z -23 (24)--------------X-- C2J1-11SYS ASCB B DATA (+) -24 ------- --------------SYS ASCB B DATA (-) -25 ‘ 1 >FIG. A-9----------------------

Y---SYS ASCB B CLK (+) -26

______------------l~--) FIGc /~-9

SYS ASCB B CLK (-) 65J2B-27 ------------------------


Table 501 (cent)

22-14-00Page 598.88

Mar 15/89Use or disclosure of mformatlon on this page IS subject to the restrictions on the trtle page of thts ::ocument.

Honeywell W!URAN’ECITATION V

Function

#2 HDGSYNC(+)#2 HDGSYNC(-)WX VIDEODATA(P)

WX VIDEODATA(N)

WX CONTROLDATA(P)

WX CONTROLDATA(N)

IASSET (+)MS SET (-)RA #2 (+)RA #2 (-)VNAVDEV (+)

VNAVDEV (-)

PROLINENAV(+)

PROLINENAV (-)

PROLINEDME (+)

PROLINE DME (-)

SHIELDARINCO DATA(+)


ConnectorPin

65J2Bj;~[;:]------------------------------------

t

-30 (24}-------------;~r-

-31 (24)-------------~-L-‘f

f

1.-32 (24)-----------L--T=;:

-33 (24)----------JLI------

TL--

-34 ------NC-35 ------NC-36 ------NC-37 ------NC

Y-38 (24)-------------rfr-

i-39 (24)-------------!-~-

7L--

Y-40 (24)-------------r~j-

tll-41 (24)-----------------

T

t

&---42 (24)-------------;j-

~1,-43 (24)----------- --Y--

t

165J2B-44 (24)----------- --l=;:

ConnectsTo

C6J1-UC6J1-V125J3A-6859J1-g125J3A-6959J1-hSHIELDGND125J3A-7059J1-m125J3A-7159J1-nSHIELDGND

16J1-28,7J1B-14125J3A-7416J1-27,7J1B-15125J3A-75SHIELDGND164J1B-89,125J3A-76164J1A-59,125J3A-77SHIELDGND164J1A-57,125J3A-78164J1A-44,125J3A-79SHIELDGND429 HS DATAFROM LRN 1


Table 501 (cent)

22-14-00Page 598.89Mar 15/89

Use or disclosure of information on this page is subject to the restrictions on the title pagf of this document.

Honeywell UNJRAN’ECITATION V

Function

ARINCO DATA(-)SHIELDGNDARINC O SYNC (+)ARINC O SYNC (-)SHIELD GNDARINCO CLK (+)ARINC O CLK (-)SHIELD GNDARINC1 DATA(+)

ARINC 1 DATA (-)SHIELD GNDARINCISYNC(+)

ARINC1SYNC(-)SHIELDGNDARINC1CLOCK (+)

ARINC1 CLOCK(-)SHIELDGNDARINC2DATA(+)

ARINC2DATA(-)

ARINC3 DATA (+)ARINC3 DATA (-)SHIELD GNDARINC4DATA(+)ARINC4DATA(-)SHIELDGNDARINC5DATA(+)ARINC5DATA(-)SHIELDGNDARINC6DATA(+)ARINC6DATA(-)SHIELDGND



i65J2B-45 (24)----------- -~~!-- 429 tlSDATAFROM I-RN1

-46 ------NC-47 ------NC

-48 ------NC-49 ------NC

t-50

-51

-52

-53

-54

-55

-56

-57

1(24)----?;-----------

(24)----$’----.------

(24)~~~-~ri----------

(24)----~y’------------

+(24)~~~-~r----------

(24)----~1----------------

------NC

------NC

-58 ------NC-59 ------NC

-60 ------NC-61 ------NC

-62 ------NC-63 ------NC

-64 ------NC65J2B-65 ------NC

C164J1A-5,125J3A-86C164J1A-15,125J3A-87C164J1A-26,125J3A-88C164J1A-45,125J3A-89C164J1A-19,125J3A-90C164J1A-17,125J3A-91


Table 501 (cent)

22-14-00‘age 598.90Mar 15/89Use or disclosure of Information on thm page IS sub~ect to the restrictions on the trtle page of ttus ldocument.

Honeywell MWJEPANCECITATION n/V



ARINC7 DATA (+) 65J2B-66 ------NCARINC7 DATA (-) -67 ------NCSHIELD GNDARINC8DATA(+)

t-68 (24)----------~r--- 116J1-33,125J3A-102

ARINC8DATA(-) -69 (24)----------!----- 116J1-2,125J3A1-103SHIELDGND ~----- l16J~-35

ARINC9DATA(+) -70 ------NCARINC9DATA(-) -71 ------NCSHIELDGNDOVERTEMPWARN -72 (24)-----------------AIRCRAFT

TS WITH65JB-99 ANNUNCIATORFD GS DEVDC OUT (-) -73 (20)-- ------&---’ 7J1B-17

DOUT 1 MST CMP WRN

1

-74 ------NCDOUT 2 DH -----------------125J1A-23DOUT 3 RAD/FDTESTDOUT

~ ~j~ f$j]-----------------125JIA-25,FIG.A-64 HDGCMPMON -77 ------NC

DOUT 5 ATT CMPMON -78 ------NCDOUT 6 DME/GROUNDRANGE -79 (24)-----------------125J1A-31VALOUT3 FD HDGVLDOUT -80 (24)-----------------7J1A-23VALOUT 1 SG -81 (24)-----------------125J1A-17VAL OUT 2 NAV SEL (P-ID1) -82 (24)----------------- 125J1A-19FD LRNSELVALOUT(P-ID2) -83 (24)-----------------FIG.A-nFD LATSTRGVALOUT -84 (24)-----------------7J1A-27NAVSEL (P-IDO) -85 (24)-----------------FIG.A-IIFD LATDEVVALOUT -86 (24)-----------------7J1A-16FD VERTDEVVALOUT -87 (24)-----------------7J1B-7FD DMEVALOUT -88 (24)-----------------7J1A-34,FIG.A-1oFD TK DETENTVALOUT -89 (24)-----------------7J1A-49FD AP ENGAGEDVALOUT -90 (24)-----------------7J1A-46FD APSVALOUT -91 (24)-----------------7J1B-38FD LNAVAPPDOUT

}A

-92 (24)-----------------7J1A-48FD TTLDOUT 1 -93 (24)-----------------7J1A-22FD DME TTNDOUT _94 (24)-----------------7J1A-5O,FIG.A-1OFD MIDMARK(5V) -95 (24)-----------------7J1B-80FD PW MOVE -96 (24)-----------------7J1B-49,

1OJ1A-33FD V/L DEV OUT (-)

t-97 (24)------------~1-- 7J1A-20

FD V/L DEV OUT (+) 65J2B-98(24)-----------Jd--- 7J1A-21

A1 CAUTION! 100mA maximumload


22-14-00Page 598.91May25/90

Use or disclosure of mformatlon on thm page IS subject to the restrictions on the title pag[ of this document.

Honeywell WJFAN’ECITATION n/V

Function

FD G/SOEVOUT

FD LRNLATDC OUT

FD DMEDC OUT (-)

FD DMEDC OUT (+)

FD CRS ERROR(+)OUTFD CRS ERROR(-)OUTSHIELDFD HDG ERROR (+) OUTFD HDG ERROR (-) OUT

SHIELD


Connector Pin

TSWITH 65J2B-7365J2B-99 (24)-----+:q&--------

TS WI~H65J2B-9-100 (24)----+;:---------

1-101 (24)---------- --r~---

~li

-102(24)-------------+-------

I-103(24)-------------~--.~-104(24)------------LqL--

1,L ---

-105(24)-----------------65J2B-106(24)------------Lyi---

---

ConnectsTo

7J1B-16

7J1A-17

7J1A-33,16J1-35

7J1A-32,16J1-34SHIELDGND

7J1A-417J1A-37SHIELDGND7J1A-367J1A-37SHIELDGND


Page598.92May25/90UseordisclosureOfIn!ormat!ononthispageIS subject10therestrictionsonthetitlepageof~hlsC:~cument

Honeywell WKE!ANCECITATION n/V

Function

SIGNAL GNDLIGHTING 28V (H)LIGHTING 5V (H)

LIGHTING COM+28 VDC POWER

DC POWER GNDSC/CP PBELAPSED TIME PBREV PBCOURSE SYNC PBADC REV SWHEADING SYNC PBSPARE PBRESERVEDHDG REV PBATT REV PBRESERVED

NAV REV PB

FLIP PBRESERVEDSPARESPAREWX PBTESTCS REV SWSPARESPARERESERVEDHDG SW1HDG SW2ATT SW1ATT SW2SPAREDC/SG BUS (H)DC/SG BUS (L)SHIELD GNDDC/MG BUS (H)DC/MG BUS (L)SHIELD GND

PILOT’S EFIS REMOTE CONTROLLERDC-811

Connector Pin

115J1-1 (22)---------------------2 ------NC-3 (22)--------------------

-4 (22)---------------------5 (22)--------------------

-6 (22)---------------------7 ------NC-8 ------NC-9 ------NC-10 (24)---------------------11 ------NC-12 (24)---------------------13 ------NC-14 ------NC-15 ------NC-16 ------NC-17 ------NC-18 ------NC-19 ------NC-20 ------NC-21 ------NC-22 ------NC-23 ------NC-24 ------NC-25 ------NC-26 ------NC-27 ------NC-28 ------NC-29 (z4)---------------------30 ------NC-31 ------NC-32 ------NC-33 ------

1-34 (24)-~- ----------------35 (24)-IUI- ---------------

----

t-36 (24)-<- ---------------

115J1-37 (24)-!!1----------------

Connects To

SIGNAL GND

PILOT 5 VLIGHTING,FIG.A-2LIGHTINGCOMPILOT 28 V DCPWR, FIG. A-1DC PWR GND

23J1-G

23J1-H

FIG. A-12

65J1A-6765J1A-68

125J3A-23125J3A-24


22-14-00Page598,93May 25/90

Use or disclosure of mformatlon on this page IS subject to the restr!ctlons on the title pagf of th{s document.

Honeywell tiNllrANcECITATION n/V

PILOT’SEFISREMOTE CONTROLLER (cent)DC-811


ADIDIM (H)ADIDIM (L)HSIDIM (H)HSIDIM (L)AP PITCHWHEELINPUT+AP PITCHWHEELINPUT-

AP PITCHWHEELOUTPUT+AP PITCH WHEEL OUTPUT -

+28VDCAP ENGAGEINPUTVS HOLDMODEGNDIASHOLDMODEGNDMACHHOLDMODEGNDWX DIM (H)WX DIM (W)WX DIM (L)

DH SET (H)

i115J1-38(24)--------------fl--

-39(24)--------------j~--

i-40 (24)--fl---------------41 (24)--J~-------------

1-42(24)--------------------43(24)----------------’1

Y_-

I’44(24)----TGj--------------45(24)-----

Y------------

SHIELDGND---46(24)---------------------47 (24)---------------------48(24)---------------------49------NC-50(24)---------------------51(24)---------------------52(24)---------------------53(24)--------------------

DH SET (W) -54(24)--------------------

DH SET (L) -55 (24)--------------------

FD MODE COMMON

ADCSLEWENGAGEADCSLEW +ADION GNDSPARESPARESPAREHSION GNDSPARESPARESPAREWX ON GNDPOSITION3POSITION4POSITION5ADF (L)LRNA (L) CIRCLEPTRLRN B (L)

-56(24)---------------------57(24)---------------------58(24)---------------------59-----NC-60-----NC-61-----NC-62-----NC-63-----NC-64-----NC-65-----NC-66-----NC-67-----NC-68(24)---------------------69(24)---------------------70-----NC-71(24)---------------------72(24)--------------------

115J1-73-----NC

Connects To

3J1-303J1-312J1-302J1-31

FIG.4-7

SHIELDGNDFIG.A-7FIG.A-7

FIG.A-7FIG.A-7FIG.A-7

2J1-332J1-3112J1-35125J1A-33

65J2A-43,125J3A-2565J2A-44,125J3A-26.SIGNALGNDFIGA-7,9J1-37FIGA-7,9J1-38

115J1.71115J1-72

115J1-68115J1.69


22-14-00Page598.94Ray 25/90useordisclosure Of Information on thm page is subject to the restrictions on the ttle page of this cocument

Honeywell lWJRANcECITATION V

PILOT’S EFIS REMOTE CONTROLLER (cent)DC-811


POSITION 3 115J1-74 (24)-------------------- 115J1-77POSITION 4 -75 (24)-------------------- 115J1-78POSITION 5 -76 -----NCADF (R) -77 (24)-------------------- 115J1-74LRNA (R) DIAMOND PTR -78 (24)-------------------- 115J1-75LRNB (R) 115J1-79 -----NC


Table 501 (cent)22-14-00

Page 598.95Mar 15/89

Use or disclosure of information on this page IS subject to the restrictions on the title pag!, of thw document.

Honeywell WWANCECITATION ii/V

MG-605/805(SYMBOLGENERATOR)

Function

P- SEC ADI X DEFL INP- SECADIX DEFLINSHIELDP- SECADIY DEFLINP- SECADIY DEFLINSHIELDP- SECHSIX DEFLINP- SECHSIX DEFLINSHIELDP- SECHSIY DEFLINP- SECHSIY DEFLINSHIELDC- SECADIX DEFLINC- SECADI X DEFLINSHIELDC- SECADIY DEFLINC- SECADIY DEFLINSHIELDC- SECHSIX DEFLINC- SECHS]X DEFLINSHIELDC- SECHSIY DEFLINC- SECHSIY DEFLINSHIELDP SG VALIN(SGVALOUTC SG VALIN(SGVALOUTNAVSELVALIN(P-ID1)NAVSELVALIN(C-ID1)- MASTCOMPDINDOUT1MASTCOMPDINDOUTIDH DINDOUT2DH DINDOUT2

(+)(-)

(+)(-)

(+)(-)

(+)(-)

(+)(-)

(+)(-)

(+)(-)

(+)(-)

1)1}

RAD/FDTESTDINDOUT3RAO/FDTESTDINDOUT3HOG’HOGATTATTDMEDME

COMPOIN DOUT4COMPDINDOUT4COMPDIN DOUT5COMPDINDOUT5GNDRANGEDINDOUT6GNDRANGEOIN00UT6

,


125J1A-1 ------NC-2 ------NC

-3 ------NC-4 ------NC

------NC:: ------NC

-7 ------NC-8 ------NC

-9 ------NC-10 ------NC

-11 ------NC-12 ------NC

-13 ------NC-14 ------NC

-15 ------NC-16 ------NC

-17 (24)------------------ 65J2B-81-18 ------NC-19 (24)------------------ 65J2B-82-20 ~--~--NC’21 ------NC-22 ------NC-23 (24)------------------65J2B-75-24 ------NC-25-26-27-28-29-30-31

125J1A-32

(24)------------------65J2EI;’6,FIG.A-6------NC------NC------NC------NC------NC(24)------------------65J2B-79------NC


Page 598.96May 25/90

Use or dmclosure of mformatlon on this page IS sub!ect to the restrtctlons on the tttle page of this d.)cument.

Honeywell W!JRANCECITATION n/V

MG-605/805(SYMBOLGENERATOR)(cent)


P- DH SET IN (H) 125J1A1;;(24)------------------115JI-53C- DH SET IN (H) ------NC

P REV SEL IN (+) -35 (24)------------------FIGA-4

P REVSEL IN (-) -36 ------NC

C REVSEL IN (+) -37 ------NCCREVSEL IN (-) -38 ------NC

RESERVED -39 ------NCATT IN -40 (24)------------------65J1A-106

: ATT IN -41 ------NCFD 1 PWR IN -42 (24)------------------PILOTFD

28 VFD 2 PWR IN -43 ------NC

FD RESETGND

1

-44 (24)-----------------SIGNALGNDP/C-SECADI VIDEO (+) -45 (24)----i~i----------3J1-74

P/C-SECADI VIDEO (-) -46 (24)----!-1-----------3J1-75

P/C-SECADI COLOR O (+)x

I

-47 (24)----j-j ---------- 3J1-72

P/C- SEC ADI COLOR O (-) -48 (24)----[-1- ----------

1

3J1-73

P/C- SEC ADI COLOR 1 (+)

1

-49 (24)----i-~ ---------- 3J1-70

P/C- SEC ADI COLOR 1 (-) -50 (24)----L-]- ---------- 3J1-71

P/C- SECADI COLOR 2 (+)I

1

-51 (24) ----i-r ---------- 3J1-68

P/C- SEC ADI COLOR 2 (-) -52 (24)----1--1- ----------

1+

3J1-69

P/C- SECADI COLOR3 (+) 125J1A-53 (24) ----1 -( ---------- 3J1-66


22-14-00Paqe 598.97May25/90

Use or dwclosure of information on this page is sub!ect to the restrictions on the Mle page of this document.

Honeywell M!WPANCECITATION V

Function

MG-605/805 (SYMBOL GENERATOR) (cent)

P/C- SEC ADI COLOR 3 (-)

P/C- SEC ADI RAS/STRK (+)

P/C- SEC ADI RAS/STRK (-)

p/c- SECADI FLYBACK (+)

Plc-SECADIFLYBACK(-)SHIELDGND

P- PRI ADI STRK RDY (+)

P- PRI ADI STRK RDY (-)

SHIELDC- PRI ADI STRK RDY (+)

C- PRI ADI STRK RDY (-)

FD 1 LNAV MODE GND

FD 1 GA MODE GND

FD 1 ASEL ARM MODE GND

FD 1 ASEL CAP MODE GND

FD 1 I-IDS SEL MODE GND

FD 1 ALT HOLD MODE GND

FD 1 VS HOLD MODE GND

FD 1 IAS HOLD MODE GND


i

—.—

125J1A-54 (24)---~q~--,--------- 3J1-67

‘f-55 (24)---1-1-- --------- 3J1-76

Iii-56 (24)-------- --------- 3J1-77

‘f-57 (24)-------- --------- 3J1-78

il*-58 (24)---V--- --------- 3J1-79

------- J

I-59 (24)-------- -----;~r- 3J1-765J1A-23

-60 (24)-------- -----!;--) %:;:-24L-- 3J1-36

-61 ------NC-62 ------NC

-63

-64

-65

-66

-67

-68

-69

125J1A-70

(24)-----------------

(24)------------------

(24)------------------

(24)------------------

(24)------------------

(24)------------------

(24)------------------

(24)------------------

65J1B-397J1A-7265J1B-40 “7J1B-6865J1B-41, 8J1-d_7J1B-7165J1B-42, 8J1-~7J1B-7265J1B-43, 8J1-r7J1A--71, llJ1-~65J1EI-45,8J1-~7J1B-7565J1B-467J1B-76,8J1-Z,115J1-4765J1B-477J1B-77,8J1-X,115J1-48


Table 501 (cent)

22-14-00Page 598.98

Mar 15/89Use or disclosure of Information on this page IS sub)ect to the restrictions on the title page of thw LIocument.

Honeywell WURANC’CITATION V


Function

FD 1 MACHHOLDMODEGNDFD 1 GS ARMMODEGND


65J1B-48,7J1B-7[65J1B-49,8J1-g7J1B-6965JlB-50,8Jl-h7J1B-70,

125J1A-71(24)-------------------72 (24)------------------

FD 1 GS CAPMODEGND -73 (24)------------------

1OJ1B-2165J1B-51,8J1-SFD 1 VNAVARMMODEGND -74 (24)------------------7J1B-7365J1B-52,8J1-T7J1B-7465J1B-557J1A-85,65J1B-567J1A-86,65J1B-57,8J1-~7J1A-68

(24)------------------FD 1 VNAVCAP MODE GND -75

FD 1 NAV ARM MODE GND -76 (24)------------------

FD 1 NAV CAP MODE GND -77 (24)------------------

FD 1 BC ARMMODEGND -78 (24)------------------

FD 1 BC CAP MODE GND -79 (24)------------------65J1B-58,8J1-~“7J1A-67

FD 1 VORAPR ARMMODEGND -80 (24)------------------65J1B-597J1A-8765J1B-607J1A-88

FD 1 VORAPR CAPMODEGND -81 (24)------------------

MDIN81 SRNBRGCD/CSMDIN82 LRN1PORTIDOMDIN83 LRN1PORTID1MDIN84 LRN2PORTIDOMDIN85 LRN2PORTID1MDIN86 LRN3PORTIDOMDIN87 LRN3PORTID1MDIN88 LRN4PORTIDOMDIN89 LRN4PORTID1MDIN90 LRN1 IDOMDIN 91 LRN1 ID1MDIN 92 LRN1 ID2MDIN 93 LRN1ID3MDIN94 LRN2IDOMDIN 95 LRN2 ID1MDIN96 LRN2ID2MDIN97 LRN2ID3MDIN98 LRN3IDO

-82-83-84-85-86-87-88-89-90-91-92-93-94-95-96-97-98

125J1A-99

------NC------NC@~+ii--------------

------NC------NC------NC------NC------NC------NC(24)------------------(24)------------------(24)------------------------NC------NC------NC------NC------NC

125J2A-105

125J2A-105125J2A-105125J2A-105


Table 501 (cent)

22-14-00Page 598.99Mar 15/89

Use or dwclosure of Information on this page IS subject to the restncttons on the Mle pagt of thm document

Honeywell W!KWANC’CITATION V



MDIN 98 LRl13 ID1 125J1A-1OO ------NCMDIN100LRN3102 -101------NCMDIN101LRN3ID3 -102------NCMDIN102LRN4IDO -103------NC(SRN2 IDOWHENMDIN64 = GND)MDIN103LRN4ID1 -104------NC(SRN2 ID1WHENMDIN64 =GND)MDIN104LRN4102 -105------NC(RESERVEDWHENMDIN64 = GND)MDIN 105 LRN4 ID3 125J1A-106 ------NC(RESERVED WHEN MDIN 64 = GND)


Table 501 (cent)22-14-00

Page598.100Mar 15/89

Use or disclosure of mformatlon on this page IS subject to the restncttons on the title page of fhm r!ocument.

Honeywell W!WANCECITATION Ilfl

-.



C- SEC ADI X DEFL OUT (+) 125J1B-1 ------NCC- SEC ADI X DEFL OUT (-) -2 ------NC

C- SEC ADI Y DEFL OUT (+) -3 ------NC

C- SEC ADI Y DEFL OUT (-) -4 ------NC

C- SEC HSI X DEFL OUT (+) -5 ------NCC- SEC HSI X DEFL OUT (-) -6 ------NC

C- SEC HSI Y DEFL OUT (+) -7 ------NCC- SEC HSI Y DEFL OUT (-) -8 ------NCSHIELD GND

P- SEC ADI X DEFL OUT (+)i

-9 (24)-------C- ----- 3J1-18P- SEC ADI X DEFL OUT (-) -10 (24)------~-~- ----- 3J1-19

P- SEC ADI Y DEFL OUT (+) x

1-11 (24)---------- ----- 3J1-24

P- SEC ADI Y DEFL OUT (-) -12 (24)------~-~- ----- 3JI-25

P- SEC HSI X DEFL OUT (+)x

t-13 (24)---------- ----- 2J1-18

P- SEC HSI X DEFL OUT (-) -14 (24)------J-I- ----- 2J1-19

P- SEC HSI Y DEFL OUT (+) -15- (24)f~

---------- ----- 2J1-24P- SEC HSI Y DEFL OUT (-) -16 (24)------$!- ----- 2J1-25SHIELD GND -------

P SG VALOUT (SG VALOUT1) -17 ------NCC SG VALOUT (SG VALOUT1) -18 (24)---------------- 65J1A-86NAV SEL VALOUT (P-ID1) -19 (24)---------------- FIG. A-nNAV SEL VALOUT (C-ID1) -20 ------NC

P MAST COMP DOUT1

}

A

-21 ------NCC MAST COMP DOUT1

1-22 ------NC

P DH DOUT2 -23 ------NCC DH DOUT2 -24 ------NCP RAD/FD TEST DOUT3 125J1B-25 -------------------- FIG. A-6

11 CAUTION: 100ma MAX LOAD.


22-14-00Page 598.101

‘May 25/90Use or disclosure of reformation on this page IS sub!ect to the restncttons on the title pag? of th!s document.

Honeywell RMWAN’ECITATION n/V

Function

C RAD/FD TEST DOUT3P HDG COMP DOUT4

C HDG COMP DOUT4PATT COMPDOUT5C ATT COMPDOUT5P DME/GNDRANGEDOUT6C DME/GNDRANGEDOUT6P DH SETOUT (+)C DH SETOUT (+)PREV SELOUT PRI


C REVSELOUTSECC REVSELOUT PRIP REVSELOUT SECRESERVED

ATTOUT; ATTOUTC AP ENGOUTC TKODOUTSPAREP/C-SECHSIVIDEO (+)P/C-SECHSIVIDEO (-)SHIELDP/C-SECHSICOLORO (+)


1 CAUTION: 100ma MAXLOAD.

125J1B-26-27

A

-281 -29

-30-31-32-33-34-35

-36-37-38-39-40-41-42-43-44-45-46

125J1B-47

------NC------NC------NC------NC------NC(24)----------------FIG.A-10------NC~~~~~;~~------------65J2A-42

(24)----------------FIG.A-4

------NC------NC------NC------NC------NC------NC------NC------NC------NC

!(24)----O----------2J1-74(24)----’~-,--------2J1-75

+(24)----I?---------2J1-72


22-14-00Page598.102

May25/90Use or disclosure of reformation on this page IS sub!ecl to the restnct!ons on the title page of thrs d )cument

Honeywell PA!iW?ANcECITATION V

MG-605/805(SYMBOL GENERATOR) (cent)


P/C-SECHSICOLORO (-) i125J1B-48(24)-----------L~-- 2J1-73

P/C-SECHSICOLOR1 (+)

~

x-49 (24)-----------;-:- 2J1-70

P/C-SECHSICOLOR1 (-) -50 (24)-----------~-’--2J1-71


i

x’51 (24)---------”--T-;-2J1-68

P/C-SECHSICOLOR2 (-) -52 (24)-----------!-l--2J1-69


I

L-53 (24)---------’--7-r-2J1-66

P/C-SECHSICOLOR3 (-) -54 (24)-----------LC’--2J1-67

P/C-SECHSIRAS/STRK(+)

J

A-55 (24)---------‘-j-;- 2J1-76

P/C-SECHSIRAS/STRK(-) -56 (24)-----------!=’--2J1-77

P/C-SECWI FLYBACK (+)

J

A-57 (24)-----------r-r- 2JI-78

P/C-SECHSIFLYBACK (-) -58 (24)-----------!:-- 2J1-79

P- PRIHSISTRKRDY (+)f

‘1-59 (24)--------- --~-j- 2J1-7,

65J1A-50P- PRI HSISTRKRDY (-) -60 (24)---------~--L-~-2J1-8,

T65J1A-51

-- 2J1-36C- PRIHSISTRKRDY (+) -61 ------NCC- PRIHSISTRKRDY (-) -62 ------NCFD 2 LNAVMODEGND -63 ------NCFD 2 GAMODE GND 125JIB-64 ------NC


Table 501 (cent)22-14-00

Page598.103Mar 15/89

Useordisclosureofinformationonthispage is subject to the restrictions on the title pag? of this document,

Honeywell KNK!AN’ECITATION V

Function

FD 2 ASEL ARM MODE GND

FD 2 ASEL CAP MODE GND

FD 2 HDG SEL MODE GND

FD 2 ALT HOLD MODE GND

FD 2 VS MODE GND

FD 2 IASMODE GND

FD 2 MACH MODE GND

FD 2 GS ARM MODE GND

FD 2 GS CAP MODE GND

FD 2 VNAV ARM MODE GND


FD 2 VNAV CAP MODE GND

FD 2 NAV ARM MODE GND

FD 2 NAV CAP MODE GND

FD 2 BC ARM MODE GND

FD 2 BC CAP MODE GND

FD 2 VOR APR ARM MODE GND

FD 2 VOR APR CAP MODE GND

HDG VALOUT

LRN SEL VALOUT (ID2)

LAT STRG VALOUT

Connector Pin Connects To—-

125J1B-65 ------NC

-66 ------NC

-67 ------NC

-68 ------NC

-69 ------NC

-70 ------NC

-71 ------NC

-72 ------NC

-73 ------NC

-74 ------NC

-75 ------NC

-76 ------NC

-77 ------NC

-78 ------NC

-79 ------NC

-80 ------NC

-81 ------NC

-82 (24)---------------- 65J2A-3

-83 (24)---------------- 65J2A-93

125J1B-84 (24)---------------- 65J2A-84


22-14-00Page 598.104

Mar 15/89Use or disclosure of Information on thm page IS subject to the restrictions on the title page of this d.)cument

Honeywell !iNIL!’NcECITATION V

MG-605/805(SYMBOLGENERATOR) (cent)


NAVSELVALOUT(100) 125J1B-85(24)----------------V/LDEVVALOUT -86 (24)----------------

ConnectsTo

65J2A-8565J2A-86

GS DEVVALOUT -87 (24)----------------65J2A-87

DMEVALOUT -88 (24)----------------65J2A-88

P TK DETENT VALOUT -89 (24) ----------------

PAP ENG’D VALOUT -90 (24)----------------

APSVALOUT -91 (24)----------------

65J2A-8965J2A-9065J2A-91

LNAV APP DOUT> -92 (24)---------------- 65J2A-92

TTLDOUT

1

A 1 -93 (24)----------------

DMETTNDOUT -94 (24)----------------

65J2A-93

65J2A-94

MIDMARKDOUT(5V) -95 (24)----------------65J2A-95

PW MOVE DOUT

TO/FR DC OUT (+)

TO/FRDC OUT (-)

LRNLATDCOUT STRG(-)

LRNLATDCOUTSTRG (+)

DMEDC OUT (-)

DMEDC OUT (+)

-96 (24)-------r--------65J2A-96

t-97 (24)--~F ----------- 65J2A-11

-98 (24)--I---!---------65J2A-12

1-99 (24)---------------- 65J2A-62

bIt-100(24)-- ------------

I-101 (24)=-m--- --------

I

65J2A-1OO

65J2A-101

-102(24)--$-----------65J2A-102

SHIELDGND--Y

125J1B-103(24)--;:------------CRSERR (+)OUT 65J2A-103

CAUTION:100MA MAX LOAD


Page598.105Mar 15/89

Use or disclosure of information on Ws page s sub)ect to the restrictions on the tttle pagt of thts document,



J

.—

CRS ERR (-) OUT 125J1B-104 (24)------1-1- ----- 65J2A-104‘1’

-lDGERR (+) OUT

\

-105 (24)------l~~- ----- 65J2A-105

Ii~DG ERR (-) OUT 125J1B-106 (24)---------- ----- 65J2A..106

SHLD GND--1’


Page 598.106May 25/90

Use or disclosure of Information on this page k subject to the restrictions on Ihe title page of this d<~cument

Honeywell WJRANC’CITATION V

MG-605/805 (SYMBOL GENERATOR) (cent]


+28V DC POWER+28 V DC POWERSPARE28 VOLT RETURN28 VOLT RETURNSPARECHASSIS GND

CHASSIS GNDSIGNALGNDSIGNALGNDDISCRETERETURNGNDDISCRETERETURNGNDASCB SHIELD GNDASCB SHIELD GNDP AC REF (+)

PAC REF(-)

SYSASCBA DATA(+)SYSASCBA DATA(-)

SYSASCBACLK (+)SYSASCBACLK (-)

L LRN XMIT(+) .L LRN XMIT (-)MDIN 1 SPLSELOMDIN2 SPLSEL1MDIN3 SPLSEL 2MDIN4 SPLSEL3MDIN5 SPLIN OMDIN6 SPLIN 1MDIN 7 SPLIN 2MDIN8 SPLIN 3MDIN9 COMPMONON/OFFMDIN 10 C 4.5 V ROT VALID

125J2A-1-2-3-4-5

$-8-9-lo-11-12-13-14-15

-16

-17-18

-19-20

-21-22-23-24-25-26-27-28-29-30-31-32

(DO)----------------*PILOT28VPWR@~~:ii-------------~FIG.A-1

(20)----------------DC PWRGND(20)----------------DC PWRGND-----NC(22)----------------CHASSISGND(22)----------------CHASSISGND(22)----------------SIGNALGND(22)----------------SIGNALGND(22)----------------DISCRETEGND(22)----------------DISCRETEGND------NC------NC

1

(22)----------]---- PILOT26VAC1-1PWR,FIG.A-3

(22)---------u----AC GND

1J----- SHIELDGND

-----------,:,--}FIG A-g----r-~-

------- ------- --

!

Y_ “--- - - - -- - -- -__-~~-?,F~G. A-9-----------------GL-J

4L --

------NC------NC------NC------NC------NC------NC------NC------NC------NC------NC~~~!;;~;------------125J2A-105

MDIN11 P+4.5V ROTVALID 125J2A-33(24)----------------15J1-7,65J1B-3


Table 501 (cent)

22-14-00Page 598.107

Mar 15/89Use or disclosure of mformat!on on this page IS sublect to the restrictions on the title pag ~ of thm document.

Honeywell ?MW!ANC’CITATION n/V

t4G-605/805(SYMBOLGENERATOR)(cent)


MDIN12 WEIGHTON MHEELS 125J2A-34(24)----------------~~~C~F~SWITCH.-

t4DIN13 FLIP -35 ------NCMDIN14 HSIMODE -36 ------NCMDIN15 IRS1AN/DIG -37 ------NCMDIN16 HDGIFREE/SLAVE-MAG/TRU -38 (24)----------------TO F/SSWITCHMDIN17 PILOTLRNA -39 ------NCMDIN18 COPILOTLRNA -40 ------NCMDIN19 SPARE -41 ------NCMDIN20 tiDG2FREESLAVE-MAG/TRU -42 (24)----------------TO F/SSWITCH14DIN21 SPARE -43 ------NCMDIN22 CITATIONV -44 (24)----------------125J2A-lo5MDIN23 SPARE -45 ------NCMDIN24 HDG1 DEF -46 ------NCMDIN25 HDG3 DEF -47 ------NCMDIN26 SRNTGL -48 ------NCMDIN27 CAARULES -49 ------NCMDIN 28 PILOT’S DME~’ -50 - - - . -- - - - - - - . - - -- - .- C164JlA-3,

65J1B-34

MDIN 29 CO-PILOT’S DME ~ -51 ------NC

MDIN30 PILOT’STTL -52 --------------------C164JI,B-64,65JIB-35

MDIN31 CO-PILOT’STTL -53 ------NCMDIN32 IRS2AN/DIG -54 ------NCMDIN33 LRN1 MAG/TRU -55 ------NCMDIN34 SPARE -56 ------NCMDIN35 SPARE 125J2A-57------NC


Page 598.108May 25/90

Use or dwclosure of Information on th!s page IS sub)ecl to the restrictions on the title page of this Cjcument

Honeywell WJW’”c’CITATION V



MDIN36 LRNTGL IDO 125J2A-58------NCMDIN37 AIRDATACMDDISABLE -59 ------NCMDIN 38 LRN3 MAG/TRU -60 ------NCMDIN39 SPARE -61 ------NCMDIN40 SPARE -62 ------NCMDIN41 ROTON/OFF -63 ------NCMDIN42 WX DUAL/SINGLE -64 (24)----------------125J2A-105MDIN43 WX TGL -65 ------NCMDIN44 FMS S/D -66 ------NCMDIN 45 VORTGL -67 ------NCMDIN 46 MFD GSPDSRCIDO -68 (24)----------------125J2A-105MDIN47 MFDGSPDSRCID1 -69 ------NCMDIN48ATT 1 WRAP -70 (24)----------------125J2A-105MDIN49ATT2 WRAP -71 ------NCMDIN 50ATT3 WRAP -72 ------NCMDIN51 ATT4 WRAP -73 ------NCMDIN52 liDGTGL IDO -74 ------NCMDIN53 HDGTGL ID1 -75 ------NCMDIN54 LRN 1 DTRK/TKE+DA -76 ------NCMDIN 55 LRN 3 DTRK/TKE+DA -77 ------NCMDIN 56 ATTTGL IDO -78 ------NCMDIN57ATTTGL ID1 -79 ------NCMDIN58 RESERVED -80 ------NCMDIN59 RESERVED -81 ------NCMDIN60 SRNSRCIDO -82 ------NCMDIN 61 SRN SRC ID1 -83 (24)---------------- 125J2A-105MDIN 62 P STBY SEL -84 ------NCMDIN 63 C STBYSEL -85 ------NCMDIN64 EFIS5 TUBE/3TUBE -86 (24)----------------125J2A-105MDIN65 RADALT S/D -87 ------NCMDIN66 COUPLE1/2 -88 ------NCMDIN67 SCDC/DC-811 -89 (24)----------------125J2A-105MDIN68 SRNBRG3/4 -90 (24)----------------125J2A-105MDIN69ADFBRG3/4 -91 (24)----------------125J2A-105t4DIN70 MLSS/C 125J2A-92(24)----------------125J2A-105


Table 501 (cent)22-14-00

Page 598.109Mar 15/89UseordisclosureOf mformailon on this page IS sub)ect to the restrictions on the Mle page of this document.

Honeywell WRANcECITATION V

MG-605/805 (SYMBOLGENERATOR)(cent)


MDIN71 ADFS/D 125J2A14~(24)----------------125J24-105MDIN72 RADALT IDO ------NCMDIN73 RADALT ID1 -95 ------NC

MDIN 74AOA, A/S,F/S IDO -96 (24)----------------125J2A-105MDIN75AOA, A/S,F/S ID1 -97 (24)----------------125J2A-105MDIN76 AOA,A/S,F/S ID2 -98 ------NCMDIN77 WINDP8/XY -99 ------NCMDIN 78 TRANSITIONON/OFF -100(24)----------------125J2A-105MDIN79 LRN1 BRGCD/CS -101------NCMDIN80 LRN3BRG CD/CS -102 ------NC

L SG BACKUP -103 ------NC

R SG BACKUP -104 ------NC

MDIN GND -105(24)----------------PROGGNDMDIN GND 125J2A-106(24)----------------PROGGND


Table 501 (cent)22-14-00

Pdqe 598.110‘Mar 15/89

Use or disclosure of reformation on this page IS subject to the restrictions on the title page of this c~}cument.

Honeywell tifi!iifi!!ANcECITATION ii/V



+28 VOLT DC POWER 125J2B-1 (20)---------------- :& IL~T128V,

+28 VOLT DC POWER }:$ (20)---------------- CIRiUI+ BREAKERSPARE28 VOLT DC RETURN -4 (20)---------------- DC PWRGND28 VOLT DC RETURN ~~ (20)---------------- DC PWRGNDSPARERESERVEDDC OUT (+) -----NCRESERVEDDC OUT (-) :: -----NC

V/LOEVOC OUT (+) t-9 (24)-----i~l------- 65J2A-98

V/LDEV DC OUT (-)+

i-10 (24)-----’--- ----- 65J2A-97SHIELDGND - - -- - -- - - -

GS DEV DC OUT (+) -11 (24)-----~7--!--:-- 65J2A-99

GS DEV DC OUT (-)1[+-12 (22)------ --------65J2A-30

SHIELDGND Y. --- -- - -- -

ASCBSHIELDGND -13 -----NCASCBSHIELDGND -14 -----NC ‘

CAC REF (+) !-15 (22)-----, ---T~----- ~:[IL~T326VAC,

CAC REF (-)+ it

-16, (22)--------- ---- AC GND-Y--A--SHIELDGNDSYSASCBB DATA (+) -17SYSASCBB DATA(-)

----------------t-;--18 ----------------y- ) FIG.A-9

--SYSASCB BCLI((+) -19 --------.-------SYSASCBB CLK (-) -20

T~;----------------- - -

Y-) FIG.A-9

R LRNXMIT (+) -21 ------NCR LRNXMIT(-) -22 ------NCLVALIN1ARINC1 -23 [24)----------------65J1A-73,

C164J1A-46L VALIN2GS DEV -24 (24)----------------65J1A-74,

C164J1A-74L VALIN3SPD DEV -25 (24)---------------- FIG. A-5L VALIN4 VNAV DEV -26 (24) ---------------- y~:~A;j6, 7J1B-9

L VALIN5 VOR/LOC OEV 125J2B-27(24)----------------65Jl~-77,C164J1B-91


Page598.111May 25/90

UseordisclosureofInformationon Ihm page E sub!ect to the restrictions on the tile page of thm document

Honeywell WNRANC’CITATIONV



L VALIN6RADALT 125J2B-28(24)----------------L VALIN7SPARE -29 ------NCVALIN8LRN1LATDEV -30 ------NC(ADF2VLDWHENMDIN 64 = GND)VALIN9LRN1 VERT DEV -31 ------NCL VALIN1OADF -32 (24)----------------

L VALIN1lFD1 -33

VALIN 12 HDG 1 -34

VALIN13ATT 1 -35

L VALIN14 SPARE -36L VALIN15ARINC O -37L VALIN 16 LRN1 28 V WPT ALERT -38L VALIN17 ROT -39L VALIN18TCS -40

L VALIN19SPARE -41VALIN20 RESERVED -42VALIN21 SPARE -43L VALIN22AP ENG’D -44

L VALIN23TK DETENT -45

L VALIN24APS -46

RVALIN1ARINC1 -47RVALIN 2 GS DEV -48RVALIN3 SPDDEV -49R VALIN4 VNAVDEV -50R VALIN5VORLOC -51RVALIN 6 RADALT 125J2B-52

(24)----------------

(24)----------------

(24)----------------

------NC------NC------NC------NC(24)----------------

------NC------NC------NC(24)----------------

(24)”----------------

(24)----------------

------NC------NC------NC------NC------NC------NC

ConnectsTo

FIG.A-6

164J1B-99,65J1A-82

65J1A-83,7J1B-476J1-e,65J1A-84lJ1-GG,7J1A-1965J1A-85

1OJ1B-19,65J1A-90

65J1A-94,1OJ1B-11llJ1-H,65J1A-951OJ1B-1565J1A-96,16J1-23


22-14-00Paqe 598.112

‘Mar 15/89Use or dwclosure Of mformatlon on thw page IS subject to the restrictions on the Mle page of thm d >cument.

Honeywell MI!IJ?ANCECITATION V

Function

R VALIN7 SPAREVALIN8 LRN 3 LAT DEVVALIN 9 LRN 3 VERT DEVR VALIN1O ADFR VALIN1l FD2VALIN 12 HDG 3

VALIN 13 ATT 3


R VALIN14 SPARER VALIN15 ARINC OR VALIN16 LRN3 28 V UPT ALERTR VALIN17 ROTR VALIN 18 TCSR VALIN19 SPAREVALIN 20 RESERVEDVALIN21 SPARER VALIN22 AP ENG’DR VALIN23 TK DETENT

R VAL1N24 APSSPAREOVER TEMPSPARESPAREINNER MARKER (+)

INNER MARKER (-)SHIELD

MIDDLE MARKER (+)


125J2B-53-----NC-54 -----NC-55 -----NC-56 (24)----------------C164J1B-99-57 -----NC-58 (24)----------------C2J2-X

65J1A-92-59 -----NC

-60-61-62-63-64-65-66-67-68-69-70-71-72-73-74-75

-76

125J2B-77

-----NC-----NC-----NC-----NC-----NC-----NC-----NC-----NC-----NC-----NC-----NC-----NC~::~:~;-------~----- AIRCRAFT ANN

-----NC(24)---------------- ;;~;~l&73,

(24)---->

(24)---------------- 65J2A-61,C164J1A-60


Table 501 (cent)

22-14-00Page 598.113

Mar 15/89Use or disclosure of Information on this page is subject to the restrictions on the title pag( of this documenl.

Honeywell lWJRANcECITATION V

Function

MIDDLE MARKER (-)

OUTER MARKER (+)OUTER MARKER (-)

MFMF

M:MF

M?MF

M?MF

3X llEFL OUT (+)J X DEFL OUT (-)~IELD GNDIY DEFL OUT (+)3 Y DEFL OUT (-)-IIELDGND) VIDEO (+)1 VIDEO (-)iIELD CIN13; pm} : ~+;

MFD RAS/STRK (+)

MFD RAS/STRK (-)

MFDSTRK RDY (+)MFD STRK RDY (-)

MC/MGDATA (+)MC/MGLATfi(-)

SPARESPARE



125J2B-78

-79-80

-81-82-83-84-85-86-87-88

(24)------L

(24)-----------------(24)-------L

1(24)--- ---;=’l------(24)--- ------------(24)----.----Y(24)---{---ID;------(24)---------------(24)------Y

{(24)------i~;-------(24)------+--------

- - . -; - --i.

(24)---~j--~j-------(24)--- ---.%--------

65J2A-63,C164JIB-74

127J1-1127J1-2

127J1-9127J1-10

127J1-54127J1.=55

127J1-50127J1-51

A-91 (24)---~l--l-i------- 127J1-46-92 (24)------->-------- 127J1-47

‘k$-93 (24)--- ~:l:i------- 127J1-42-94 (24)--- ~------- 127J~-43

yA-95 (24)--- ------------ ~27J1-38-96 (24)---j=!j=!------- 127J1.39

yA-97 (24)--- ------------ 127J1-58-98 (z+--~--+------- 127J1-59

I-101 (24)---------- --=-- 127J1-7-102(24)-----------~$- 127J1-8

I

‘-- 127J1-36-103(24)-------------- 126J1-24-104(24)-----------~+’--126JI-25

‘-- SHIELDGND-105-----NC

I25J2B-106-----NC


Table 501 (cent)

22-14-00Page 598,114

Mar 15/89Use or disclosure of Information on this page IS subject to Ihe resmct!ons on the Mle page of this c ocumenl.

Honeywell !MNRANCECITATION V

Function

#1 PITCHX

#1 PITCH Y

#1 PITCHZ

#1 ROLLX

#1 ROLLY

#1 ROLLZ

HDG 1

HDG 1

HDG 1

RESERVEDRESERVEDRESERVEDHDG1SYNC

HDG1SYNC

RESERVEDRESERVEDP- RADALT

P- RADALT

(x)

(Y)

(z)

MG-605/805(cent)


1:

125J3A-1 (24)---------- --~;- lJ1-z,65J2A-15

-2 (24)-----------~-;--lJ1-y,65J2A-16

-3 (24)-----------:-- lJ1-~,65J2A-17

-4

-5

-6

-7

-8

-9

-lo-11-12

(+) -13

(-) -14

-15-16

(+) -17

(-) 125J3A-18

1&--

(24)------------~r-

(24)-----------~-;--

(24)-----------L-’--

t

Yk--(24)-----------~{--

!,(24)-----------~--;--

(24)-----------$--

!---------NC------NC------NC

11(24)-----------~;-

(24)-----------$

>-. .

------NC

SHIELDGNDlJ1-p,57Jl-E65J2A-18lJ1-q,57Jl-F65J2AL19lJ1-r,57Jl-G65J2A-20SHIELDGND6J1-L.65J2A~216J1-M,65J2A-226J1-K,65J2A-23SHIELDGND

6J1-U,65J2A-286J1-V,65J2A-29SHIELDGND

------NC~ ~(24)-----------: ~.~FIG.

i(24)-----------~ -~A-6

[.. SHIELD GND


22-14-00Page 598~li5

Mar 15/89Use or disclosure of Information on this page IS subject to the restrmflons on the title pagfi of this document.

Honeywell W!!URANCECITATION V

MG-605/805 (cent)

Function Connector Pin Connects To.—

RESERVED 125J3A-19 ------NCRESERVED -20 ------NCRESERVED -21 ------NCRESERVED -22 ------NCP- DC81O DAT (+)

$-23 (24)--------- ---- 115J1-36

P- DC81O DAT (-) -24 (24)--------- -~-’-- 115J1-37~-- SHIEL~ GND

P-DH SET (W) IN -25 (24)---------------- 115J1-54,65J2A-43

P- OH SET (L) -26 (24)---------------- 115J1-55,

1

65J2A-44P- CRS SEL X/TACH (+) -27 (24)--Y~-- -------- 23J1-D,

65J2A-45P- CRS SEL Y/TACH (-) -28 (24)------ -------- 23J1-E,

65J2A-46P- CRS SEL Z -29 (24)----------------

1’

23J1-1:,65J2A-47

SHIELD GNII ------P- HDG SEL X/TACH (+)

[

-30 (24)--7=7-- -------- 23J1-:.,

65J2A-48P- HDG SEL Y/TACH (-) -31 (24)--;-;-- -------- 23J1-M,

65J2A-49P- HDG SEL Z 125J3A-32 (24)--J-J-- -------- 23J1-N,

1’65J2A-50

SHIELD GND ---...-


Table 501 (cent)

22-14-00Page 598.116

Mar 15/89Use or disclosure of mformahon on this page IS sub!ect to the restrictions on the title page of this ,Iocument.

Honeywell UNRANCECITATIONV

MG-605/805 (cent)


#1 VORBRG X/SIN 125J3A-33(24)----------Q--J

#l VOR BRGY/COM ‘4 ~-34 (24)----------jT--

#1 VOR BRG Z/COS‘!

-35 (24)----------l j---

#l VORBRGCOM -36 (24-----------G-!

1

1----#l ADFBRGX/SIN -37 ~24)--q- ---------

#l ADF BRG Y/COM -38 (24)-- -,- ---------

#l ADF BRG Z/COS1

-39 (24) --1-------------

$1ADFBRGCOM -40 (24)--J~l-----------

1------ ----#l SRNCRSDEV (+)

-T-41 (24)-------- ------1[

#l SRNCRSDEV (-) -42 (24)-------4-i------

v

I

-------#l SRNGS DEV (-) -43 (24)---fi----------

#l SRNGSDEV (+)

‘11J II

-44 (24)---t-t----------

#1 LRNDSRTRKX -45#1 LRNDSRTRK Y -46#1 LRNDSRTRKZ -47#l LRNBRGX/SIN -48(ADF2X/SINWHENMDIN64 = GND)#1 LRN BRGY/COM -49(ADF2Y/COMWHENMDIN64 = GND)#1 LRN BRG Z/COS -50

(ADF2 Z/COS WHEN MDIN64 = GND)#1 LRNBRGCOM 125J3A-51(ADF2COMWHENMDIN64 = GND)

I

I’-----------------NC------NC------NC

I

I(24)----fi--------

(24)----;-!--------

(24)----l-r--------

(24)----1-]---------vL - - ------ --

ConnectsTo

C164J1B-11,65J2A-51C164J1B-37,65J2A-52C164J1B-12,65J2A-53C164J1B-37,65J2A-54SHIELDGND65J2A-55,164J1A-6165J2A-56,164J1A-3365J2A-57,164J1A-4765J2A-58,164J1A-33SHIELDGNDC164J1B-78,65J2A-65

C164J1B-75,65J2A-66SHIELD GNDC164J1B-75,C2J2-C,65J2A-67,65J2A-66C164J1B-79,C2J2-D,65J2A-68SHIELDGND

C164J1A-61

C164J1A-33

C164J1A-47

C164J1A-33SHIELDGND


22-14-00Page 598.117

‘Mar 15/89Useordisclosureof Information on this page is subject to the restncttons on the t!tle pagt of this document.

Honeywell MI!UPAN’ECITATION V

-.

MG-605/805 (cent)


#l LRN TO/FROM (+) 125J3A-52 ------NC#l LRN TO/FROM (-) -53 ------NC#1 LRN LATDEV (+) -54 ------NC$1 :~: ::;DEV (-) -55 ------NC

(+) -56 (24)-----------_i~~- FIG. A-E

P- SPD DEV (-) -57 (24)------------!-~-

Y

FIG. A-E

-- SHIELD GNDP PITCH CMD (+) -58 (24)------------~-i- 65J2A-73,

7J1B-30P PITCH CMD (-) -59 (24)---------------- 65J2A-7~,

T7J1B-31

-- SHIELD GNDP ROLL CMD (+) -60 (24)------------=- 65J2A-75, 7J1A-29P ROLL CMD (-) -61 (24)---------------- 65J2A-76, 7J1A-30

%- SHIELD GNDP ROT (+) -62 (24)------------~r- 15J1-4,

65J2A-77P ROT (-) -63 (24)----------------

T

15J1-5,65J2A-78

-- SHIELD GN!Ip- AIR DATA CMD (+) -64” (24)------------~r- 65J2A-79,

9J1-39p- AIR DATA CMD (-) -65 (24)---------------- 65J2A-80, 7JIB-37

T9J1-33

-- SHIELD GNDP- AC STEER IN (+) -66 ------NCP- AC STEER IN (-) 125J3A-67 ------NC


22-14-00Page 598.118

Mar 15/89Use or disclosure of information on thts page IS sub)ect to the restrictions on the Ittle page of this :]ocument

Honeywell WMRANcECITATION V

.

MG-605/805(cent)

Function ConnectorPin ConnectsToI

PWX VIDEODATA(P)

/

125J3A-68(24)------------~i- 5!~J1-g,65J2B-30

PWX VIDEODATA(N) -69 (24)-----------L-!-

1

59J1-h,65J2B-31

i-- SHIELDGND

P WX CONTROLDATA(P) -70 (24)----------l-j-r-59J1-m,

i65J2B-32

P WX CONTROLDATA(N) -71 (24)-----------!!]--59J1-n,65J2B-33

P IAS SET (+)’ -72 ------NCP IASSET (-) -73 ------NC

P- VNAV DEV (+)

1

-74 (24) ---------- -j~~- 65J2B-38,

ii7J1B-14,

16J1-28P- VNAVDEV (-) -75 (24)-----------l-~-

r

65J2B-39,7JlB-15,

1

16J1-27-- SHIELDGND

P PROLINENAV (+) -76 (24)-----------i~i- 164J1B-89,6$iJ2B-40

P PROLINENAV(-) -77 (24)-----------!-!- 164J1A-59,

I

Y65J2B-41

-- SHIELDGNDP PROLINEDME (+) -78 (24)-----------~-r- 164J1A-57,

65J2B-42P PROLINEDME (-) -79 (24)-----------L-L-

T

164J1A-44,65J2B-43

I

-- SHIELDGNDPARINC O DATA(+) -80 (24)-----------fi-- 429 HSDATA

P ARINCO DATA(-) -81 (24)-----------1----FF!OMLRN1~.- SHIELDGND

PARINC O SYNC(+) -82 ------NCPARINC O SYNC(-) 125J3A-83------NC


Table 501 (cent)

22-14-00Page 598.119

Mar 15/89Use or disclosure Of lnfOrmatlOn on this page is sublect to the restrictions on the title page of this document.

Honeywell M!JRANCECITATION V

Function

P ARINCO CLK (+)P ARINC O CLK (-)

P ARINC 1 DATA (+)

P ARINC 1 DATA (-)

P ARINC1 SYNC(+)

P ARINC1 SYNC(-)

PARINC 1 CLOCK (+)

PARINC 1 CLOCK (-)

PARINC2 DATA (+)

P ARINC2 DATA (-)

PARINC3 DATA (+)P ARINC3 DATA (-)

PARINC5 DATA (+)PARINC5 DATA (-)



PARINC8 DATA (+)P ARINC8 DATA (-)


SPARE

MG-605/805 (cent)

Connector Pin

125J3A-84------NC-85 ------NC

I-86 (24)---------l~f-----l]

-87 (24)---------1-1------

Y

Jlt-89 (24)---------,-T ------

Y

?

------90 (24)---------1+ -----

jlt-91 (24)---------,-j------

r--------92 ------NC

-93 ------NC

-94 ------NC-95 ------NC

-96 ------NC-97 ------NC

ConnectsTo

C164J:1A-5,65J2B-50C164JIA-15,65J2B-=51SHIELIIGNDC164JI.A-26,65J2B-52C164JIA-45>65J2B-53SHIELDGNDC164JIA-19,65J2B-54C164J1A-17,65J2B-55SHIELDGND

-98 ------NC-99 ------NC

-1oo------NC-101------NC

1-102 (24)----------R- ---- 116J1-33-103(24)----------- ---- 116J1-2

Y ------- SHIELDGND

-104------NC-105------NC

125J3A-106------NC


Table 501 (cent)22-14-00

Page 598.120Mar 15/89

UseordisclosureofinformationonthispageIS subjecttotherestrictionsonthetttlepageofthis:ocumenl

Honeywell iWiik~ANcECITATION V

Function

#3 PITCH X

#3 PITCH Y

#3 PITCH Z

#3 ROLL X

#3 ROLL Y

#3 ROLL Z

HDG2 X

HDG2 Y

HDG2 Z

RESERVEDRESERVEDRESERVEDtiDG2 SYNC (+)

HDG2 SYNC (-)

RESERVEDRESERVEDC- RADALT (+)

C- RADALT (-)

MG-605/805(cent)


125J3B-1 ------NC

-2 ------NC

-3 ------NC

-4 ------NC

-5 ------NC

-6 ------NC

1-7 (24)-------1~~----- C2J1-S

-8 (24)-------:-~----- C2J1-tI’*

-9 (24)------- ------ C2J1-UY -------SHIELDGND

-lo ------NC-11 ------NC-12 ------NC

I

-13 (24)-------~~r----- C6J1-UII

-14 (24)-------- ------ C6J1-VY -------SHIELDGND

-15 ------NC-16 ------NC-17 ------NC

125J3B-18------NC


Page 598.121

Mar 15/89Useordisclosureof mformatlon on this page IS sublect to the restrictions on the Mle pag,~of this document.

Honeywell M!iK~ANcECITATION V

Function

RESERVEDRESERVED

RESERVEDRESERVED

C- DC811DAT (+)C- DC811DAT (-)

C- DH SET (W) INC-DHSET (L) IN

C- CRS SEL X TACH (+)

C- CRS SEL YTACH (-)

C- CRS SEL ZSHIELD GND

C- HDG SEL X TACH (+)

C- HDG SEL Y TACH (-)

C- HDG SEL ZSHIELD GND

MG-605/805 (cent)

Connector Pin Connects To.—

125J3B-19 ------NC-20 ------NC

-21 ------NC-22 ------NC

-23 ------NC-24 ------NC

-25 ------NC-26 ------NC

1-27 (24)---~r---------23J2-9

!-28 (24)--~r;--- ------- 23J2-E

-29 (24)---&--i------- 23J2-Z-------

-30 (24)--T=;--

t

------- 23J2-L

-31 (24)--;-;--- ------- 23J2-hl

125J3B-32(24)--~Y~---t-------23J2-N-------


Table 501 (cent)

22-14-00Page 598.122

Mar 15/89Use or disclosure of mformatlon on Ihts page IS subject to the restrictions on the htle page of this d >cument.

Honeywell W!WANCECITATION V

MG-605/805 (cent)


#2 VOR BRG X/SIN 125J3B-33 ------NC#2 VOR BRG Y/COM -34 ------NC

#2 VOR BRG Z/COS -35 ------NC:2 VOR BRG COM -36 ------NC

#2 ADF BRG X/SIN -37 ------NC

#2 ADF BRG YICOM -38 ------NC

#2 ADF BRG Z/COS -39 ------NC

#2 ADF BRG COM -40 ------NC

#2 SRN CRSDEV (+) -41 ------NC#2 SRN CRS DEV (-) -42 ------NC#2 SRN GLIDE SLOPE DEV (+) -43 ------NC#2 SRN GLIDE SLOPE DEV (-) -44 ------NC#3 LRN DSR TRK X -45 ------NC#3 LRN DSR TRK Y#3 LRN DSR TRK Z

-46 ------NC-47 ------NC

#3 LRN BRG X/SIN -48 ------NC#3 LRN BRG YjCOM -49 ------NC#3 LRN BRG Z/COS -50 ------NC#3 LRN BRG COM 125J3B-51 ------NC


22-14-00Page 598;123

Mar 15/89Use or disclosure of Information on thm page IS subject to the restrictions on the title pag? of this document.

Honeywell W!M!ANCECITATION V

MG-605/805 (cent)

Function Connector Pin Connects To——

#3 LRNTO/FROM(+) 125J3B-52------NC+3 LRNT()/FRoM(-) -53 ------NC:3 LRNLATDEV(+) -54 ------NC#3 LRNLATDEV (-) -55 ------NCC- SPD DEV (+) -56 ------NC

G= SPDDEV (-) -57 ------NC

C PITCH CMD (+) -58 ------NC

C P~TcH cMD (-) -59 ------NC

C ROLL CMD (+) -60 ------NC

C ROLLCMD (-) -61 ------NC

c ROT (+) -62 ------NC

C ROT (-) -63 ------NC

C- AIR DATA CMEI (+) -64 ------NC

c- AIR DATAcMD (-) -65 ------NC

C- AC STEER IN (+) -66 ------NCC- AC STEER IN (-) 125J3B-67 ------NC

— —-


22-14-00Page598.124

Mar 15/89Use or disclosure Of Information on Ihts page IS sub)ecf to the restrictions on the tdle page of this r.ocument

Honeywell MWJF!ANC’CITATION V

Function

CWX VIDEODATA (P)

CWX VIDEO DATA (N)

C WX CONTROLDATA(P)

C WX CONTROLDATA(N)

C IASSET (+)C IASSET (-)C- VNAVDEV (+)

C- VNAVDEV (-)

C PROLINENAV (+)

C PROLINENAV (-)

C PROLINEDME (+)

C PROLINEDME(-)

MG-605/805 (cent)


125J3B-68------NC

-69 ------NC

-70 ------NC

-71 ------NC

-72 ------NC-73 ------NC-74 ------NC

-75 ------NC

-76 ------NC

-77 ------NC

-78 ------NC

125J3B-79------NC


Table 501 (cent)22-14-00

Page 598.125Mar 15/89

Use or disclosure of mformatlon on this page IS subject to the restrictions on the t[tle pay ? of thm document

Honeywell MMRAN’ECITATION V

MG-605/805 (con~)


C ARIllC O DATA (+) 125J3B-80 ------NCC ARINC O DATA (-) -81 ------NC

C ARINC O SYNC (+) -82 ------NCCARINCO SYNC (-) -83 ------NC

C ARINCO CLK (+) -84 ------NCCARINCO CLK (-) -85 ------NC

C ARINC 1 DATA (+) -86 ------NCC ARINC 1 DATA (-) -87 ------NC

C ARINC 1 SYNC (+) -88 ------NCCARINC 1 SYNC (-) -89 ------NC

C ARINC 1 CLOCK (+) -90 ------NCC ARINC 1 CLOCK (-) -91 ------NC

C ARINC2 DATA (+) -92 ------NCC ARINC2 DATA (-) -93 ------NC






C ARINC9 DATA (+) -104 ------NCCARINC9 DATA (-) -105 ------NC

SPARE 125J3B-106 ------NC

I


22-14-00.—Page 598.126

Mar 15/89Use or disclosure of information on this page is sub)ecl to the restrictions on the Mle page of this uocurnent

Honeywell H%i!i?’””CITATION V

Function

+28V DC PWR

DC PWR GROUNDSIGNAL GROUNDCHASSIS GROUNDO-28 V DC LIGHTING POWER(H)O-5V AC/DCLIGHTINGPWR (H)

LIGHTING POWER COMMONREMOTE PAGE BUTTON INPUTREMOTE RECAL BUTTONINPUTREMOTESKIPBUllONINPUTREMOTEENTERBUTTONINPUTREMOTENORMALCHECKLISTREMOTEEMERGENCYCHECKLISTDI 1 DISCRETEINDI 1 DISCRETEINREMOTESWITCHCOMMONRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDRESERVEDMC-MGDATABUS (H)

PILOT’SMC-800

ConnectorPin

126J1-1 (22)------------------

-2 (22)-------------------3 (22)-------------------4 (22)-------------------5 ------NC-6 (22)------------------

-7 (22)-------------------8 ------NC-9 ------NC-lo------NC-11------NC-12------NC-13------NC-14------NC-15------NC-16------NC-17------NC-18------NC-19------NC-20------NC-21------NC-22------NC-23------NC ‘

126J1-24(24)-----,+----------

ConnectsTo

PILOT28VDCPWR,FIG.A-1DC POWER GNDSIGNALGNDCHASSISGND

PILOT5V *LIGHTINGLIGHTINGGND

125J2B-103


Table 501 (cent)22-14-00

Page 598:127Mar 15/89

Use or disclosure of ln~ormatlon on this page IS subject to the restr!ctlons on the tile pag~ of this document.

Honeywell B!iW’”c’CITATION V

PILOT’SMC-800(cent)


M~;M4L~AMDBUS (L) 11~126J1-25(24)-----------------125J2B-104-26~::~::ii~

RESERVEDRESERVED -27------NCMFDDISPLAYDIM (H) -28(24)------------------127J1-30MFDDISPLAYDIM (L) -29(24)------------------127J1-31RESERVED -30------NCRESERVED -31------NCWX DIMH -32------NCWX DIMW -33------NCWX DIML -34------NCLEFTSG BACKUP -35(24)------------------;:~~;Ai;5,

FIG.~-4’RIGHTSG BACKUP -36------NCSPARE 126J1-37------NC


Table 501 (cent)

22-14-00Page 598.128

Mar 15/89Use or disclosure Of mformatton on this page IS sub~ect to the restnctjons on the t!tle page of this c~cument.

Honeywell WNE~ANcECITATION n/V

ED-600 (MFD)


PRI X DEFL (IN) +

[

127J11~ ~:~~11:1111:1111:1:11~-$PRI X DEFL (IN) -

Y .-

SEC X DEFL (OUT) +

[

--”--NC

SEC X DEFL (OUT)- :: -----NC28 V DC PWR + -5 (22)--------------------

28 V DC PWRSTROKEREADY(PRI; +

[STROKEREADY(PRI) -

PRIY DEFL(IN) +[-

SECY DEFL(OUT)+[

POWERRETURN -POWERRETURNVALIDOUTPUT(PRI)STROKEREADY(SEC)STROKEREADY(SEC)SECX DEFL(IN) +

[SECX DEFL(IN) -VALIDOUTPUT(SEC)REVSELECT(PRI)

[-

+

SIGNALGND - -CHASSISGNDSECY DEFL(IN) +

[SECY DEFL(IN) -INCLINOMETERLIGHTING +

(INCLINOMETERLIGHTING -SPARE

- -- - - -- - - - -- - -

:? l;f]::5;~--------------8 (24)-~y----------------36------ I

$-9 (24)----------------=--10(24)----------------Q-

L-.

-11 -----NC-12-----NC-13 (22)--------------------:!: (22)--------------------

-----NC-16-----NC-17-----NC-18-----NC-19-----NC-20-----NC-21-----NC-22(22)---------------------23~::~:~-------------------24-25-----NC-26-----NC-27-----NC-28-----NC

REVSELECT (SEC) -29 -----NCDIMCONTROL

[+ -30(24)------------------

DIMCONTROL - il-31~::~:i;------~G-ii---G!SPARE -32RASTERDIMCONTROL Ii

{

-33.-.--------wvv---RASTERDIMCONTROL W -34-----------------------1RASTERDIM CONTROLSTROKEREADY(PRI)SHLbGND127J1% ~iij:~------------------

ConnectsTo

125J2B-81125J2B-82125J2B-83

PILOT 28V,FIG.A-1

125J2B-101125J2B-102

125J2B-84125J2B-85125J2B-86

DC PWRGNDDC PWRGND

SIGNALGNDCHASSISGND

126J1-28126J1-29

SHIELD GNDFOR127JI-7,127J1-8


22-14-00Page 598.129

May25/90Use or disclosure of information on This page E subject to the restrtctlons on the title page of thm document.

Honeywell tiiWJEPANcECITATION 11/’V

ED-600 (MFD) (cent)


SPARE 127J1-37-----NCCOLOR3 (PRI) +

[ t-38 (24)-----------------10125J23-95

COLOR3 (PRI) - -39 (24)------------------Y

125J23-96-- SHIEL9GND

TEMPANNUNGNDOUTPUT -40-----NCSPARE -41-----NCCOLOR2 (PRI) +

[J

-42(24)----------------1~1-125J23-93COLOR 2 (PRI) - -43 (24)------------------ 125J2!3-94

-- SHIELD GNDSTROKEREADY(SEC)SHLDGND -44-----NCSPARE -45-----NCCOLOR 1 (PRI) +

[ ?-46 (24)------------------ - 125J2B-91

COLOR1 (PRI) - -47(24)----------------!-1125J213-92$?-- SHIELI)GND

SPARE -48-----NCSPARE -49-----NCCOLORO (PRI) +

[ !-50 (24)-----------------f, - 125J2B-89

COLORO (PRI) - -51(24)------------------- 125J2E)-909 -- SHIELDGND

SPARE -52-----NCSECX DEFLSHIELDGND -53-----NCVIDEO(PRI)

[+

J

-54(24)----------------17-125J2B-87VIDEO(PRI) - -55 (24)------------------ - 125J2B-88

-- SHIELD GNDSECY DEFLSHEILDGND -56-----NCSPARE -57-----NCRASTER/STROKE(PRI) -

[$

-58 (24)-----------------O- 125J2B-97RASTER/STROKE (PRI) + -59 (24)----------------!- 125J2[I-98

FLYBACK (PRI)

FLYBACK (PRI) r A :::l::;:::::::::::::::::i:i!;:c-- SHIELDGND

LEFTPHOTOSENSOROUT -

[

-62-----NCLEFTPHOTOSENSOROUT + -63-----NCRIGHTPHOTOSENSOROUT + -64-----NCRIGHTPHOTOSENSOROUT - -65-----NCCOLOR3 (SEC) +

[

-66-----NCCOLOR3 (SEC) -67-----NCCOLOR2 (SEC) ; -68-----NCCOLOR2 (SEC) -69-----NCCOLOR1 (SEC) ; -70-----NCCOLOR1 (SEC) - 127J1-71-----NC


Page 598.130May 25/90

Use or dw.closure of mformahon on NW page is sub!ect to the reslnctlons on the lltle page of this dJcument

Honeywell WWR’”c’CITATION V

ED-600 (MFD) (cent)


COLOR O (SEC) +<

127J1-72 -----NCCOLOR O (SEC) - -73 -----NCVIDEO (SEC)

{+ -74 -----NC

VIDEO (SEC) -75 -----NCRASTER/STROKE (SE;) +

<-76 -----NC

RASTER/STROKE (SEC) - -77 -----NCFLYBACK (SEC) +

{-78 -----NC

FLYBACK (SEC) - 127J1-79 -----NC


Table 501 (cent)

22-14-00Page 598-131

Mar 15/89Use or disclosure of mformallon on this page IS sub!ecf to the restnchons on the title pag, of this document

Honeywell !!NJRANC’CITATION V

..

EADI

28 VDC BUSA

‘~:: } ‘“-””’’’””(”w)

EHSI

)

‘~:: }’D-’’”’’”’(”w)

EFIS

{ B

‘~~:::} “’’’’’”’(’”w)

( ) 1A 115J1-5 DC-81 1 (’w)

MFD SYM ‘EN

4) 7.5A-. 125J2A-1

) 125J2A-2

{

4

)

D

I

MG-605/805 (115W)

125J2B-1

125J2B-2

126J1-1 Mc-800 (5W)

MFD DISPLAY

‘~ :::} ED-’c’0’800(’5w)

AD-16219

28 V dc BUSFigureA-1


22-14-00F’aqe 598.132

‘Mar 15/89Use or disclosure of information on this page IS sub\ect to the restrictions on the title page of thm Iocument

Honeywell WMRANC’CITATION V

5 VDC A

DIMMINGT 115J1-3 DC-811 (5W)

b 3J1-26 ED-800 (1 .2W)

AD-16220

Edge LightingFigure A-2


Table 501 (cent)

22-14-00Page 598.133

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Honeywell W!K!””c’CITATION V

PILOT’S SIDE EFIS

COPILOT’S SIDE HSI 2

AD-1 6221 -RI

AC Power RequirementsFigure A-3


Table 501 (cent)22-14-00

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Honeywell !WVHANCECITATION V

r.,—————- 3J 1

I PRl 21

L ——— ——

r Y 1-——-. —————— — MG-6051805I-M 2J 1 125J1B

I

7PRI 21

1-

1———— — - I

I II I

r ——— —— — I ISG-6051805 65J2B 125J1A

I SG PWR ,0I

DN

L. I——— —— —

I1- ——. —— -J

LEFT SGBACKUP

r——— —— —

MC-800 126J1

I 35

1-AD-16222

——— —— -

Reversionary Select Discrete Switching3 Tube EFISFigure A-4


Table 501 (cent)

22-14-00Paqe 598.135

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Honeywell M?K?’”c’CITATION V

PILOTS SIDE

AOA ERROR

{

}+ ~:;:::;, ‘PDDEV (H)

}]- ~ :E’, ‘p” “V(L)

PILOT’SDISPLAY

AOA VALID 65J1A-75

}

SPD DEV VLD125J2B-25 J

AD-16223

AOA/Speed CommandFigure A-5


Table 501 (cent)

22-14-00Page 598,136

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Honeywell M!JEANCECITATIONV

RKVDC---b=’=S5..2A I

PRIMARY CIUTPUT(HI

Pi ‘;’ 1’ ‘ t, ‘~

w

II ==OUTPUT

COMMON (C)N

7J1B

AUX OUTPUT (H) x 18

E

~lLOT’S FD

uOUTPUT TEST E 1

RAD ALT

IQ - lNPuT

II~ f, RA VALID IN

,. .,. 11 RA VALID Y> , ,

1:

., izw==?

Ill ~< 25-P RA TEST IN 1

I NC~215

d

C RA TEST OUT125J2B

NC~5:! C RA “ALID IN I

NC+l”’ a}H CoPILOT’SRA13 ALT

NC+ 18 L INPLJT

AD-16224

Radio Altimeter InterfaceFigure A-6


Table 501 (cent)22-14-00

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Honeywell WJEFCECITATIONn/V

—.—. —,=lB%0 SYU80L GENERATOR

T

II

1

rlmym-m— — — -SG SACKUP

I7J1A

I

AP ENG 46

L—————JSGBACKUP

——-— — -——— -1

paimpri~l- – –

mJm ~mLm COMPUTER

●2SV AP ENG ICONTROLLER

I

llJ1 115.0 44

I

PITCH WHEELINPUT

I

I I

———— — A

AmOPILOT+ ENGAGE -28V

.,~=.y,r – – 1

II I l-” 1.1 .

I-IdL-————a

———— —E6JIB PILOT’SSYMBOLGENERATOR W3A

46 VSMODE GND so

47 IAE MOOE GND 79

———— — d I

‘w

1

33 L Ax

39 H CM”

JIII

1——-— —

,J,e PILOT FZ-EOO 7J1B I

t b 76 VS MODE GND 3s= HOLD I(b77IASMODE GND 37 ~ ERROR

L I-———— .—————A——.——~,%LOTMB-ZDS1t I!2sw.M===.=== 1

x IASMOOE GNDI

1h z VS MODE GNOI I

——-— — A l~!AI

70 MS MOOE GN:

Ea VS MOOE GNC I

———— - JG1-

AirDataCommandB1ockDiagramFigureA-7


22-14-00Paqe 598.138‘May25/90Use or disclosure of mformatlon on this page IS subject to the restrictions on the title page of this {! ~cument

Honeywell M!UN’”c’CITATION V

~~::1,wow 125J2A-34

Weight On WheelsSwitchFigure A-8

WI-650

SG-605/805

MG-605f805

AD-16226-RI‘


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22-14-00Page 598.139

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Honeywell M!KWANCECITATION V

r———

PILOl%SSYMBOLGENERATOR

II “AIuIIIIII

127 fl 1270 127 fl 127 fl

—— ————65J2A 125J2A MFDSYMBOL

{ ‘

H 24

“ }

GENERATOR

‘{

17 1+DATA

c 25DATA

18 c

{ }}

.,A,H 26

CLOCK19 H

c 27CLOCK

20 c

I 65J2E 125J2B

I

{ 7“

H 24 17 H

I

{

DATA

“ }

DATA

c 25 18 c,“6

I{ -

‘ }}

“’B’H 26

CLOCK

19 H

c 27CLOCK

L

4 ~ 20 c

——. —— ——.. —

*

127 (l 127’0 127 n 127 f)

ASCB Bus ConfigurationFigure A-9

—1

III

I1IIIIIII

—J

AD-16227


Table 501 (cent)22-14-00

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Honeywell M!MFANcECITATIONn/V

APP SEL,8J1-f

~’l!—7J1 B-53,7J1A-59

-f,

INC

DME

DME

NC I

I

I

-f

I

I

VALID,65J2B-88 I 16J1-33

GROUNDRANGE

AD-20072

VNAV DisableFigure A-10


22-14-00Page 598.141‘May25/90

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Honeywell W!NFANcECITATION ii/V

III I I II I II II

I I I IIII

I I LRN B _ NcI LRN A _NcI 1°

“J2B-8~12w’B-’~ ‘5J2B-8~ AD-21X175

EFIS Display Select Discrete OutputsFigure A-n


22-14-00Page598.142

May 25/90Use or dwclosure of Information on thts page IS subject to the restrictions on the title page of !h!s ~ocument.

smw

-llnA. A.

6JI

<

10J1B

ENG INTLK ‘< 28 ;w~:”:_Q-FE-LrlC6J !

PILOl”S C-14D IDIR GYRO NO. 1

=}

DG2 II I

r —.. 1 RMI IvALID I

I I I

I6J 1 I

I

HDG 2 STATOR X ~ I 10J1A II

I 48 HEADING X II HOG 2 STATOR Y ~ I

I 4 I 47 HEAOING Y

I I

IHDG 2 STATOR Z z

I

4I I

L d

48 HEADING Z

——.

~? I

COPILOT% C-14DDIR GYRO NO. 2

r ——— 1 ~}RMI 2

1&l r

I H’=’G2sTAToRxI ~ H

111I I

! ‘DG2sTAT0Ry.I+=m ___l

10.JIB

40 HOG RATE DISABLE

PILOTS HOG REV

IIF I ———— -

I I

Honeywell WJFANCECITATIONn/V

APPENDIX B

FMZ-800 FLIGHT MANAGEMENT SYSTEM INSTALLATION

Use or disclosure of Information


onthispagek sub!ecttotherestrictions

22-14-00Page598.142.2

May25/90onthe!Jtlepageofthis[ocumenl.

Honeywell !NNJNANCECITATION V

APPENDIX B

FMZ-800 Flight Management System Interconnect

B1. SCOPE

This Appendix defines the installationrequirements for the HoneywellFMZ-800 Flight ManagementSystem.Thisinterconnectinformationisstand-alone.TheFMZ-800interfaceswiththeEDZ-605/805systemviatheASCBdatabus.

B2. ELECTRICALINSTALLATION

TheelectricalinstallationrequirementsfortheFMZ-800FlightFlanagementSystemaredefinedin paragraph 4 in themainbodyof thisTable.

Thefollowingprogrammingpinschangesarerequiredon the EFISSG andtheMFD SG. Theseprogrammi-ngpinsallowtheSG andMG to communicatewiththeFMZ-800viatheASCB.

Proq Pin Function

62 LRNA InterfaceIDo Identifiesthe63 LRNA InterfaceID1 FMSInterface64 LRNA InterfaceID2

IDo ID1 ID2——

Open Gnd Grid LeftSystemASCB


Table 501 (cent)22-14-00

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I Function

ISPARE+28VDC POWERpOWERRETURNLIGHTINGCOMMONSPARE

I28VANN POMER HCHASSISGfiD28VANN POWER C5V LIGHTING

I28VLIGHTINGSPARENAVDATABUSOUT

( :

I (NAVCTRLBUSoUT :

INAVDATABUSIN ( :

INAVCTRLBU!jIN

( :NAVCLKBUSIN

( :

I (PERF DATA BUS OUT :

I (PERFCTRLBUSOUT ;

IPERF DATA BUS IN :(

i

PERF CTRL BUSIN(.[

pERFCLKBUS IN(

CDUVALID:

ISPARES

IR PHOTOSENSOROUTL PHOTOSENSOROUTPAREIM CONTROLo(JTPARE

PILOT’SCONTROLDISPLAYUNIT

CD”800

Connector PinConnects TO

(22)-------------.------(24) FIG.B-3---------------.----(22) cHASSISGND--..-----------------(22) DC GND--------------------

TO PILOT’S5V

------NC DIMMINGCONTROL

I(24)----f2’--------------(24)---!G!----(24) .=i--------..-~ ----,

------- --

(24j-------Ju!y----lj::1{24)----O--------.-----~24)---io!------------:24) n.$----------- ---------

py -ci”--------2tij---.-7 ------- ------z4j---LYLY-----.-----N&-----NC .-----NC-----NC

121JIA-5512131A-56121JlB-7121J1B-8121JIA-65121J1A-66121J1B-32121JIB-33121JIB-35121J1B-36

------NC:: ------NC

------NC3 ------NC-9 ------NC-h ------NC-~ (24)--------------------

{12IJ1B-1oo

1-m ------NC

------NC~;

------NC12031$


Table 501 (cent)

22-14-00Fage598.144

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Honeywell MUR’”c’CITATION V

Function

.AMP TEST

;PARESlRIGHT/DIMDISCRETE\NNINTENSITYCONTROL

~PARES

‘ESTENABLE!ESERVED;PARES

PILOT’SCONTROLDISFFL~T’~NIT(cent)


120J1-s(24)--------------------TO AIRCRAFTLAMPTEST(GNDFORTEST)

-t-u-V (24)--------------------FIG.B-3-w (22)--------------------TO PILOT’SDAY/

NIGHTSWITCH

~;

:L-BB-cc-DD-EE ------NC-FF-GG

120J1-HH


22-14-00Page 598.145

‘Mar 15/89Use or disclosure of Information on this page is subject to the restrictions on the title pag( of thm document,

Honeywell WiKPANcECITATIONn/V

PILOT’SNAVIGATIONCOMPUTER

NZ-61O


\IRCRAFTBATTERY28 V DC 121J1A-1-------NCJNITOVERHEAT -2

(-28 V DC POWER ~ -3 (20)-------------------- FIG.B-3

-4 (20)--------------------DCGND;HASSISGND -5 (22)--------------------CHASSISGND;IGNALGND -6 (22)--------------------SIGGNDIATTERYRETURN -7

t

-------NCiSCBDATA“A”

(H -8 ---------

)--------------

------!ulFIG.B-5

c -9 --------------!ESERVED -lo!ESERVED -11iSCBCLOCK“A”

{H -12 n

J )------- ------ ------- --

c -13 II FIG.B-5--- - - - - - - - -- -- ------ --

!ESERVED -14;PARE -15ILS DATA BUS

(H -16------NC

ARINC429) c -17------NClMEDATABUS

{H -18------NC

ARINC429) -19------NClMEDATABUS

{i

i-20(24)-----C-----------164J1A-54

PROLINEII) c -21(24)-----1UL----------164J1A-165V STBYMONITOR -22,TSDATABUS

{H -23

(ARINC429) C -245V MONITOR -25TS DATABUS

(H

I-26 (24)-----j~T----------141J1-14

(ARINC429) C -27 (24)-----U---------- 141J1:15

(IATA LOADER DATA BUS IN H

t

-28 (24)------------O----- 123J1-Tc

t

-29 (24)----------~1 ---- 123J1-S‘OR/LOCDATABUS

{H -30 (24)------f- ---------- 164J1B-102

(PROLINE II) c -31 (24)-----1UL----------164J1A-S4‘OR/LOC DATA BUS

(H -32------NC

(ARINC429) c -33------NC5V MONITOR -34CARS DATA BUS IN

(H -35------NC

(ARINC429) C 121J1A-36------NC


22-14-00

I

I

Page 598:146May25/90UseordlsdosureofinformationonthispageIS subjecttotherestrictionsOnihetjtlepageofthisl~~cument.

Honeywell M!UR’”c’CITATION V

PILOT’SNAVIGATIONN;OW;TER (cent)


I-15VMONITOR i21JlA-37

i-38(24)---T--------------FRoM#l

1

}-39(24)--& ------------FUELFLowsENsoR-40(24)----------=------- 144JI-E-41(24)---------JU!------ 144J1-F-42------NC

FUEL FLOW IN #1{Hc

GENERAL BUSOUT#3(PROLINEII)

DATA LOADER COMMONVOR/LOCDATABUS IN(ARINC429) (“c

GENERALBUSOUT#2{H

(ARINC429) cLTS#1 BUSSPEEDHI/LOLTS#2 BUSSPEEDHI/LOLTS#3 BUSSPEEDHI/LOGENERALBUSOUT#1

[H

(ARINC429)

DATALOADERDATA

SPARECDUDATABUSIN

SPAREPERFDATABUSIN

FUELFLOWIN#2

q

{BUSOUT ~

(Hc

{Hc

{Hc

PERFDATABUSOUT{Hc

TESTCLKHICDUDATABUSOUT

(Hc

IESTCLK LO

-43------NC-44------NC-45------NC-46------NC-47(24)-------------------SIGGND-48------NC-49------NC

1

-50(24)-----i=i----------141J1-27

-51”(24)-----!U! ---------- 141J1-28

t-52(24)------f-----------123J1-H-53(24)-----LGL----------IZ3J1-G-54

t-55(24)------=-----------120J1-M-56(24)-----!G’-,----------120J1-N-57-58------NC-59------NC

1-60(24)-----G-----------FROM#2

}-61(24)-----!O~----------FUELFLowsENsoR-62------NC-63------NC ,-64

i-65(24)------O-----------l~oJ1-s-66(24)-----1-J---------- -l;~OJ1-T

121J1A-67


22-14-00Paqe 598.147

‘Mar 15/89Use or disclosure of mformatlon on this page IS subject to the restrictions on the [Itle pag[ of thm document

Honeywell !%$J?ANC’CITATIONV

Function

RESERVED 1RESERVEDSPARERESERVEDRESERVEDSPARECDUCTRLBUSIN

{Hc

TAGSYNC OUT

PILOT’SNAVIGATIONN$OW;TER (cent)

FLIGHTTESTPORTC

{

RCV(RS-232) RET

XMTFLIGHT TEST PORT A

{

RCV(RS-232) RET

XMTCDUSYNCFLIGHTTESTPORTB

{

RCV(RS-232) RET

XMTDATALOADERCLKOUT

{H

CROSSDMEDATABUS{i

(ARINC429) cCROSSDMEDATABUS

(PROLINEII)ASCBDATA“B”

{Hc

RESERVED

{ASCBCLOCK “B” ;

RESERVED

{CDUCTRLBUSOUT ;

TAGSYNC INCDUCLK BUSOUT ~

{MAG/TRUSEL OUTONSIDEAUTOTUNECONTROLREMOTETUNINGCONTROL 1

ConnectorPin

21J1B-1 ------NC-2 ------NC

:: ------NC-5 ------NC ,-6

i‘7 (24)---~mI--------------8 (24)----U--------------9 ------NC

1

-10(24)--1~j------------’11(24)--l-z--------------12(24)---= II------------’13(24)--------Tab--------14(24)------------------~~~(24)--------LL!------

-,;;::l::~::l

’17(24)--Ter-18(24)--i-i

-20(24)-..---.---G---------21(24)--------1.1--------22------NC-23------NC

t-24(24)--1~j--------------25(24)----------

1}

--------26------------------------27------------!-!--------28-29-30-31-32-33-34-35-36-37-38

21J1B-39

n“1 >.-----.-----------------.-!=! ------

[

t(24)--~=i-------------~::~::iy--------------

i(24)--------jet -------~::~+ii-__G- -------

}

(24)-------------------(24)-------------------

Connects To

120J1-P120JI”R

FIG.B-6

FIG.B-6

123JI-K123JI-J

C164J1A-54C164J1A-16FIG.B-$

FIG.B-5

120J1-U120J1-V

120J1-W120JI-X

TO AUTOTUNECIRCUIT


Page 598.148Mar 15/89

Use or disclosure of mformatlon on this page m sub~ecf to the restncttons on the title page of th!s d ]Cument.

Honeywell MIWPANCECITATION V

.,

PILOT’SNAVIGATIONN:O~fiTER(cent)


LATERAL WAYPOINT ALERT 121J1B-40 ------NCVERTICAL WAYPOINT ALERT -41 ------NCDEAD RECKONING -42 ------NC

DFFSET ALERT -43 ------NC

APPROACH SENSITIVITY -44 ------NC

INDEPENDENT OP -45 ------NC

CDU MESSAGE -46 ------NCDEGRADED ACCURACY -47------NCCDUSYNC -48------NCNAVCOMPUTERVALID -49------NCSPARE -50SPARE -51ADCVMO -52VERTICALTRACKAURALALERT -53 ------NCOFFSIDEAUTOTUNINGCONTROL -54

{FUEL FLOW IN #3 H -55 (24)------------------- SIGGND

c -56(24)-------------------SIGGNDLTS#3 DATA BUS H

{-57------NC

(ARINC429) c -58------NCLTS #1 CONFIGURATION

(101 -59------NCID2 -60(24)-------------------SIGGND

LTS #2 CONFIGURATION(ID1 -61------NC102 -62------NC

{

101 -63------NCLTS #3 CONFIGURATIONS

ID2 -64------NC5DICENTER -65------NCCROSSFILLENABLE -66------NCVERSIONB ASCB -67

{

ID1 -68------NCFUELFLOWID ID2 -69------NC

1113 -70(24)-------------------SIGGNDOPERATIONALMODEIDO -71(24)-------------------SIGGNDJEIGHTON WHEELS -72(24)-------------------IO WOW SWITCH

(GND FORWOW)PERFCOMPUTERINSTALLED -73------NC

{

IDO -74------NCLTS #I TYPE ID1 -75(24)-------------------SIGGND

ID2 -76 ------NC

{

IDO -77------NCLTS#2 TYPE ID1 -78------NC

102 121J1B-79------NC


22-14-00Page 598.149

‘Mar 15/89Use or chsclosure of Information on this page is sub}ect to the restrictions on the title pag$: of this document.

FunctionConnector Pin

121J1B-80sIG GND

REsERVED

[l-l

-al(24)----------::::::::::;:J;N1;

FUELFLOWIN #4-82(24)--------::---------

DATALOADERCONNECTEDiL}

-..

-83 (24)--------

[

IDO)

-84(24)-------::::::::::::~~;LE

RADIOTYPECODEID1 -85 (24)-------

1D2~:!!:?!;:~;-------”-------

MAINTENANCETESTSEL -88------NC

ILS/MLssEL

\

-89------NCIDO -90------NCID1LTs#3 l~pE -91------NCID2 -92------NC

OPERATIONALMODE ID1INITIATEDTRANSMIT

-93------NC

INITIATEDRECEIVE

-94-.----NC

[

-95 (24)--------:::::::::::1TABLEB-2

RADIOTYPECODE

m3ID4 % ~:~~=---

ASCBDUAL/SINGLE

sIGGNI}-98 (24)-------------------

SDI#~ -99------NC ---- 120J1-~

SD1 #2~~~~ (24)--------------

CDUVALID------NC

MAG/TRUESELECTENGLISH/METRICID

-102 ---- sIGGNE’

OVERSPEEDPROTECTION

~;:~(24)--------------

W-422 OFFSIDEVORCONNECTED

----- SIGGNC’

CROSSVOR/DMEMANUALTUNE

-1o5(24)-----------------FIG.B-4

VOR/DMEMANUALTUNE121J1B-106(24)-------------

HOCIeWell !:~~~~cE 4

PILOT’s

NAVIGATIONCOMPUTER~cont~NZ-61Oconne(:ts To

I

4

I Interconnect InformationTable 501 ~cont)

2279;?$0 May 2iv90

~e~trlctlOnSon the thle Pa9e of ‘his o ‘umen~

~5e O, disclosure of mformatlonon this page w sub(ect to the

Honeywell W’W’NCECITATION V

Function

SPARE

(+28 V DC POWER ~

{LOADER INSTALLED ~

SPARE

{

cDATA BUS IN

H

{

cCLK BUS IN

i-i

SPARES

{

cDATA BUS OUT

H

SPARES

CHASSIS GNDSPARE

PILOT’SDATA LOADER

DL-800

Connector Pin

123J1-A-B (22)---------------------c ~f:~:ii-----------------

:; (24)------7--------------F

!-G (24)---l~; -------------

-H (24)--&1- -------------

I-J (24)---1~1 -------------

-K (24)--& -------------

-L-M-N-P

ConnectsTo

DC GNDFIG. B-3

121J1B-83

121J1A-53,

121J1A-52,

121J1B-21,

121J1B-20,

-R

!-S (24)---I=; ------------- 121J1A-29,

I I*-T (24)---U- ------------- 121J1A-28,

-u

‘[

-v-w-x-Y-z

1-a-b (22)---------123JI-c h


Table501 (cent)22-14-00

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Use or disclosure of mformatlon on this page IS sublect to the restrictions on the title pag! of this document,

Honeywell W!!JEPAN’ECITATION V

Function

BITE LODATA FROM CDULO

(LOOPA HI

LO

DATA FROM CDU HI

{LOOP B ‘1

LO

PWR SHIELDPWR COM TO ACUBITE HI

SPARESPARELOOP A SHIELDPRIMARY DATA ~A

OUTPUT (ONSIDE) [B

LOOP B SHIELDSPARE+12 VDCTO ACU-12 VDC TO ACUBITE SHIELD

SPARERESERVEDSECONDARY DATA

{A

OUTPUT (OFFSIDE)SECONDARY DATA

(:

INPUT (OFFSIDE) BPRIMARY DATA

(A

INPUT (ONSIDE) B

(DESTINATION BIT ~

OUTER SHIELDDATA TO CDU

(LOHI

SPAREFSK DATA (+)E FIELD ANT

PILOT’SOMEGA SENSOR

OZ-800

Connector Pin

t

141J1-1 (24)----------~j ------------NC

t:: (24)---=-- ----- -------4 (24)---!V1------- ------

-------- ------------NC

$ 1~j (24)---O-- ----- -------7 (24)--~U1-- ----- ------

--------- -------8 (24)---A

I-9 (20)-------------------10 (24)-~-J---JY1-------

----------11------NC-12------NC-13(24)-----------------

1

-14(24)--------~~i------

-15(24)--------i~~------

-16-17-18-19-20

-21-22-23-24-25-26-27-28-29-30

11W::-i-- -----------

Vm]--r-r- ----------------- --- --------

(24)--------- --------

------NC------NC------NC------lie------NC------NC 1t(24)------------ ------(24)---------!-L ------

z(24)---------- --------------NC

-31 (24)--------------------32 ------NC-33 ------NC-34 ------NC-35 ------NC

141J1-36 ------NC

Connects To—. —

142J1-3

142J1-9142J1-10141J1-13

142J1-12142J1-13141J1-16

142J1-6142J1-I141J1-20

LOOP A SHIELD121J1A-26

121J1A-27

LOOP B SHIELD

142J1-7142J1-5BITE SHIELD

121J1A-50121J1A-51141J1-53

OUTER SHIELD


Table 501 (cent) 22-14-00Page 598,152

Mar 15/89Use or disclosure of mformatlon on this page IS subject to the restrictions on the title page of Ihls tiocument.

Hone~e[l ::Fg:ANCECITATION n/V

PILOT’SOMEGA SENSOR (cent)

OZ-800


SPARE 141J1-37 ------NC

SPARE -38 ------NC

4DG VALID -39 ------NC

SECONDARY (OFFSIDE) ON/OFF -40(24)-------------------141J1-53

iDGREF[

_41------NC;? -42------NC

~SKDATA(-) -43------NCSHIELDCOMMON

-G-44 (24)------------------- A

{

Y -45 ------NCiDGSYNCHROINPUT Z -46------NC

x -47------NC?ANGE/HYPERBOLIC -48------NC~RIMARY(ONSIDE)ON/OFF -49(24)-------------------141J1-53rOP/BOTTOMANT MT -50------NCILEO -51(24)-------------------TOWOW SWITCHILEO(REVERSELOGIC) -52------NC?RoGRAMcoMMoN -53(24)-------------------141J1-40,DC GND

[141J1-49,141J1-29

ICCOMMON

[

-54(20)-------------------DC GND-55 (20)-------------------

28 vDc IN1

-56 (20)------------------- FIG.B-3141J1-57(20)-------------------


Page598,153May25/90

Use or disclosure of Information on thm page IS subject to the restncttons on the t!tle page of this document.

Honeywell !!N!E?ANC’CITATION V

Function

IITEHI;PAREIITE-LOIITESHIELD12 VDC‘WRCOMMON.12VDC‘WRSHIELD

{HI

.00PA LO

[

SHIELDHI

.00PB

t ~lIELDLJTERSHIELD

PILOT’SOMEGA ANTENNA

AT-801

Connector Pin I

142Jl:;(24)------------NC

-3 (24)-------4 (24)-------5 (20)-------6 (20)-------7 (20)-------8 (24j-------9 (24)-------10(24)------11(24)------12(24)------13(24)------14(24)-----

‘l-------------K -------H-Y

IH------------!?-+&-------- ------Y ~j‘i----.-------Il.------------’Y’~;n

t------------

II------ ------;’f’i)142J1-15(24j--------------i

Connect-

141J1-10

141J1-1

141J1-19141J1-9141J1-18

141J1-3141J1-4

141J1-6141J1-7


.154Mar 15/89

Use or disclosure of Information on this page IS subject to the restrictions on the Mle page of this d ~cumenl

Honeywell ~iWfEfANcECITATION V

PILOT’S SIDE J

AD-17194

28 VDCPowerFigureB-3


Table 501 (cent)

22-14-00Paae 598.155

“Mar 15/89Use or disclosure of Information on this page IS subject to the restrictions on the title pag~, of this document

Honeywell WWF~ANcECITATION n/V

PILOT’S AUTO/MANUAL SWITCH

AUTO

I ~ 121J1B-106

*

MANUAL

AD-1 71 95-RI

FMSAuto-Tune SwitchesFigure B-4


22-14-00Paqe598.156‘Play25/90

Use or disclosure of reformation on this page IS subject to the restncttons on the tnle page of this d ]cument,

Honeywell H!K?””c’CITATION V

TO SYSTEM ASCB

PILOT’S FMS ~~121J1A

{

DATA

“A”

{

H 12

CLOCKc 13 4)

“—- ‘\ F ‘--- ‘Y r --- ‘b< --- ,><. -—. ,) L ,--- ,/ L ,--- .J

- +121J1B

( ;;

H 26 i }

{

DATAc 27 4)

“B”

{ .;;

H 29 41

CLOCK

c 30 t)

~ ‘“ ‘~&

““

TO SYSTEM ASCBAD-17196

ASCBConfigurationFigure B-5


Table 501 (cent)

22-14-00Page598.157

Mar 15/89Useordisclosureofinformationon this page IS subjecf to the restrictions on the title pagf of Ih!s documenl.

Honeywell M!KWANCECITATION V

~

PILOl% NZ-610

RCV

PORT C RET

XMT

{

RCV

PORT A RET

XMT

i

{

RCV

PORT B RET

XMT

—.—

1121J1B /\

10 1 III

11 ,II I

12\/

I II f--l,I fx13

~1

J1-2 IRET!! DBMA-25S

14 ‘1-7 (TRW)I II II I

15\/ L/

J1-3

I I

I f\17 1“

II18 t

II I19 I

LSWITCH..— — ———— J

AD-17197

NZ-61O Flight Test InterfaceFigure B-6


Table 501 (cent)

22-14-00Paqe 598.158

‘Mar 15/89Use or disclosure Of information on this page IS subject 10 the restrictions on the title page of this :!ocument.

Honeywell WMFANCECITATION n/V

TableB-2RadioTypeCode

PinJIB-84,85,86, 95,96

RadioTv~e Pin Number84 85 86 95 96

HoneywellPrimusII (Normal) 11000

HoneywellPrimusII (Offside) 11001

CollinsProlineII (Normal) o 0000

CollinsProlineII (Offside) 00001

0 = Ground

1 = Open


Page 598.159‘May 25/90

Use or disclosure of Information on this page IS subject to the restrictions on the We pag! of this document.

Honeywell WJFANCECITATION Ii/l/

APPENDIXC

DADCAZ-81OAND VN-800Interconnect

Use or dwclosure of


22-14-00Page598.160

May25/90on this page IS subject to the restrictions on the htle page of th!s d(,cument.

Honeywell ~f~Jf~ANcECITATIONn/V

Function

28 V DC HI28 V DC HI28 V DC RETURN28 V DC RETURNSIGNALGROUNDSIGNALGROUNDDC GROUNDDC GROUNDCHASSISGROUNDCHASSIS GROUNDASCB DATA “A”

[

H

cALTITUDE REPORTING COMMON

ALTITUDE REPORTING B2

!LTITUDE REPORTING B4

ALTITUDEREPORTINGCl4LTITUDEREPORTINGC24LTITUDEREPORTINGAl4LTITUDEREPORTINGA2NLTITUDEREPORTINGA4ILTITUDEREPORTINGB1lLTITUDEREPORTINGC4lLTITUDEREPORTINGD4\SCBCLOCK “A”

[

H

c

IARO-CORRECTED\LTITUDE NO. 1

PILOT’SDIGITALAIR DATA COMPUTER

AZ-81O

Connector Pin $onnects To

9J1A:;:;:j-------------------

I

FIG.C-1--------------------3 (20)--------------------4 (Do)-------------------DC GND-5 (20) -------------------” SIG GM)

:; ALI- DESIRED-8 ----- ---- ----- ---- ---- - PROGRAM PINS-9 (22)------------------- CHASSIS GND-10 (22)------------------ CHASSIS GNII-11--------NC-12--------NC-13 (24)------------------ 14:jJ1-69,C143Jl-6g-14 (24)------------------ 143J1-85,C143J1-85-15 (24)------------------ 143J1-1oo,C143J1-1OO

-16 (24)------------------ 143,J1-1,C143J1-1-17 (24)------------------ 143,11-26,c143J1-26-18 (24)------------------ 14~J1-9~,c143Jl-9fj-19(24)------------------143J1-99,c143J1-99-20(24)------------------143J1-97,C143J1-97-21 (24)------------------143,11-86,c.14~JI-86-22 (24)------------------143J1-84,c143Jl-Fj4-23 (24)------------------143,]1-13,C]43J1-13-24--------NC-25--------NC

1FINESINE -26(24)--6

I

------------18J1UFINECOS -27(24)--q-t------------18J1-VFINECOMMON -28 (24)--v ------------18J1-WCOARSE DC -29 (24)---1~

1

----- ----- -- 18J1-TCOARSE REF(+15) -30 (24)---I-F ------------18J1R

,COARSE COMMON -31 (24)--4~ ------------18J1-P

?6V AC 400Hz PWR[

H1

-32(24)---fi------------FIG.c-2C 9J1A-33(24)---U------------AC GND


22-14-00Page598.161‘May25/90Use or disclosure of mformatton on this page IS sub!ect to the re$tnctlons on the t!tle page Of this document.

Honeywell iH!MR!ANcECITATIONn/V

PILOT’SDIGITAL AIR D~A8~~MPUTER (cent)


ALTITUDE VALID #1 9J1A-34 (24)------------------ ;&l-:,;OJIB-44

BARO POTEXCITATION(-10V)

i

-35 (24)----fi-----------18Ji-Z-BARO POT WIPER -36 (24)----J-1----------- 18J1-YBARO POTCOMMON li-37 (24)----U-----------18J1-XBARODISABLE -38SSECDISABLE -39

[

SIGNAL -40 (24)------------------7J1B-44COM -41--------NC

ALTITUDERATE#1 +REF(+12) -42--------NC-REF(-12) -43--------NC

INDICATEDAIRSPEED#1 -44--------NCMACHNUMBER#1 -45--------NCMAXIMUMOPERATINGSPEED(VMO) -46--------NCMACH/AIRSPEEDREF (+12) -47--------NCMACH/AIRSPEEDCOMMON -48--------NCAIRSPEEDVALID#l -49--------NCBAROCORRECTEDCOARSEREF(+15V)-50--------NChLT#2 [COARSEDC -51 (24)------------------1OJ1A-21AIRDATASELFTEST -52 (24)------------------FIG.C-5PILOTHOLDOUTPUT- HI -53 (24)------------------7J1B-36PILOTHOLDOUTPUT- LO -54 (24)------------------7J1B-37,65J2A-80,(SIGGND) 12533A-65

PILOTALTITUDEHOLDENGAGE -55 (24)------------------7J1B-81PILOTALTITUDERATEHOLII -56 (24)------------------7J1B-82ENGAGE

PILOTAIRSPEEDHOLDENGAGE -57 (24)------------------7J1B-84PILOTMACHHOLDENGAGE -58--------NCPILOTSLEWENGAGE -59 (24)------------------115J1-57,FIG.C-6PILOTSLEWCONTROLINPUT -60 (24)------------------FIG.C-6<,115J1-58PILOT HOLD REFERENCE -61 (24)------------------ FIG.C-6,65J2A-79,

{

125J3A-64-62

SPARES -63-64

DVERSPEEDWARNINGGND -65 (24)------------------FIG.C-4-66

{

SIGNAL -67--------NCTAS#1 DC REF (+20) -68--------NC

GND -69--------NCTAT/SATDC SIGNAL -70--------NCTAT/SATSELECT 9J1A-71--------NC


Paqe 598:162‘May25/90

Use or disclosure of reformation on thm page IS subject to the restrictions on, the Mle page of thm iocument

Honeywell ~iv~p’”c’CITATION n/V

PILOT’SDIGITALAIRDATACOMPUTER(cent)

AZ-81O

Function Connector Pin $onnects To

TEMPERATUREPROBE- HI 9J1A-72(24)-----~ri----.----

}

500OHMTEMPERATURE PROBE - LOW -73 (24)------- --------- TEMPERATURE P~OBETEMPERATURE PROBE - RET -74 (24)-----YSPARE -75INDICATEDAIRSPEED#3ALT SWITCH

-76(24)------------------1oJ1A-39,7JIA-43-77--------NC

PRESSUREALTITUDEOUT #1 -78 (24)------------------ 7JIA-44

-79

-80

-81

-82

-83-84

[

-85BARO- FINESINE -86--------NCCORRECTED SPARE -87ALTITUDE#2 FINECOMMON -88--------NC

FINE COS -89--- -----NCSPARE -90ALT #2 COARSE COMMON -91--------NC

-92ALERTER SELECT -93--- -----NC

AIRSPEED SWITCH #1 -94AIRSPEED SWITCH #2 -95

-96-97-98

)UAL/SINGLE ASCB -99-- ------NCLEFT/RIGHT PROG

[

-1ooIDO -101(24)-----------------

-102(24)-----------------~IRCRAFT :;;

1

-103(24)-----------------TABLEID ID3 -104(24)-----------------C-1

ID4 -105(24)-----------------ID5 9J1A-106(24)-----------------


22-14-00Paqe598.163‘May25/90UseordisclosureOf mformatlon on this page IS subject to the restrictions on the title page of this document.

Honeywell WJ?’NCECITATION V

Function

TORQUE LOGICOUTPUT 1TORQUE LOGICOUTPUT 2TORQUE LOGICOUTPUT 3TORQUELOGICVALIDIORQUE LOGIC INPUT 1TORQUE LOGIC INPUT 2TORQUE LOGIC TEST

i

IIGITAL RANGEDATA ~

IIGITALRANGECLK ~~t?

IIGITALRANGE SYNC -HI

PILOT’SDIGITALAIRD~~A8~~MPUTER(cent)


9J1B-1

::-4-5-6-7

::-lo-11-12

{

\SCB“B” BUS DATA H -13-------NCc -14-------NC

\scB“B”WJS cLOCK

{“:

;PARES

10mV/ARINC561*PROGPIN)IGITALRANGESYNCLO

{\RiNC429OUTPUT#1 H

c

;PARES

LLTITUDEVALID#2

-15-------NC-16-------NC-17-i8-19-20

. -21-22-23-24-25-26 -------NC-27 -------NC-28-29-30-31-32-33

9J1B-34 (24)------------------ 7J1A-42


Table 501 (cent)

22-14-00.-Page 598.164

Mar 15/89Use or disclosure of Information on thm page is subject to the restrictions on the title page of thts I iocument.

Honeywell WW!””c’CtTATIONn/V

PILOT’SDIGITAL AIR DATA COMPUTER (cent)

AZ-81O


VERTICAL PATH ERROR - HI 9J1B-35(24)------------------7JIB-15,65J2B-39,125J3A-75

VERTICALPATHERROR- COM -36(24)------------------7J1B-14,65J2B-38,125J3A-74

VERTICALPATHERRORVALID -37(24)------------------~;;:Ai76,125J2B-26

IASHOLDSELECT(OUTPUT) -38(24)------------------7JlB~57TO/FROMNULLDISCRETE -39(24)------------------7JIB-39

{

SIGNAL -40ALTITUDERATE COMMON -41OUTPUT#2 +REF(+12) -42

-REF(-12) -43IASOUTPUT#2 -44MACHNUMBEROUTPUT#2 -45SPARE -46AUXMACH/AIRSPEEOREF (+12)#2 -47MACH/AIRSPEEDCOMMON #2 -48

AIRSPEED VALID OUTPUT #Z -49 (24)------------------ 7JIA-52

ASEL SEL INPUT -5o(24)------------------~JJ-~

[H -51(24)------------------65J2B-11

i$~!f$~HOLDOUTPUTL-HI-52(24)------------------65J2B-12-53

COPILOTHOLOOUTPUT- LO -54COPILOTALTITUDEHOLDENGAGE -55COPILOTALTITUDERATEHOLDENG -56COPILOTAIRSPEEDHOLDENGAGE -57COPILOTMACHHOLDENGAGE -58COPILOTSLEWENGAGE -59COPILOTSLEWCONTROLINPUT -60COPILOTHOLDENGAGEREFERENCE -61ASELSEL OUTPUT -62 (24) ------------------ 7JIB-60

DC RANGE[

H -63(24)------------------7JIA-32,65J2B-102L -64(24)------------------7J1A-33,65J2B-101

SLANT/GROUND’RANGEINPUT -65 (24)------------------125J1B-31RANGEVALID ;;?(24)------------------FIG.C-7

{

SIGNALTAS #2 AC REF (11.8 VAC) -68

COM 9J1B-69

Interconnect InformationTable501(cent) 22-14-00

Page598.165May 25/90

Use or disclosure of mformatlon on lhts page IS sub!ecf to the restnctrons on the title page of th!s document.

PILOT’S

DIGITALAIRD~~8~~MpUTER(cont)

Function

lINC429OUTPUT#2 [Hc

ConnectorPin Connects TO

?ESELECTALTITUDEERR6RSIGRESELECTALTITUDEERRORCOMRESELECTALTITUDEERRORDISC59WZjlCHEDALTITUDEALERTLIGHTWITCHEDALTITUDEALERTHORN

!9J1B-70(24)-Tin--------------~~~:$;~~~3~;~~-71(24)-~--------------.72(24)------------------7J1B-51 A

RESELECTALTITUDECRANKLOGICRESELECTALTITUDEVALIDRESSUREALTOUT#2

(DDONO.1

IISPLAYDATA

IJAYPOINT 1 NO.1~AYPOINT 2 NO.IJAYPOINT SELNO.1IASHOLDMODESELVNAVARMVNAV CAPTURETEST INTERLOCK

TEST INTERLOCK

VNAV MODE SELECTVNAV MODE F/B

DISPLAY SELECT

VNAV[H

ISLEWCONTROL C

IDD1 No.1

\

DD2 NO. 1DD3 NO. 1DD4.NO.1DD5 NO.1DD6NO.1DD7NO.1

INPUT

-73-74(24)------------------7J1B-24-75(24)-------------------76(24)------------------~~~RTC~~RN,

.

-77(24)------------------~~;~~g;6-78(24)-------------------79 ‘-80(24)-------------------81(24)-------------------82(24)-----------.-------83(24)-------------------84(24)-------------------85(24)-------------------86(24)-------------------87(24)-------------------i38(24)-------------------89(24)-------------------90(24)-------------------91(24)-------------------92(24)-------------------93(24)-------------------94---------NC-95---------NC-96(24)-------------------97(24)-------------------98

~~~O~oN~.~ -99,24)-------------------100(24)-----------------

DOS1NO:l qol (24)-----------------

DDS2NO.1 -102(24)----------------

1-~03(24)-Q -------------

[24)-~ -------------

ISPARESWITCHEDALTITUDEALERT 9J1B-106-------NC

1

LIGHT

-104-105

16J1-1516J1-1916J1-1416J1-1816J1-1116J1-1216J1-616J1-3716JI-1016J1-516J1-238J1-W7JIB-737J1B-74

8J1-R7J1B-61

7J1B-22MUSTBE GROUNDED,WHENAZ-81ODADCIS INSTALLED. A&


paae598.166

16J1-2116J1-3616J1-3316J1-3416J1-1616.31-17

“May 25/90

Use or disclosure of mformatlonon thm page IS subject to the restnct!ons on

the title page of th!s d]cument.

Function

5 VDC TEST POINT

.28 VOC)IMMING CONTROL

;PAREJAYPOINT 2

)ISPLAY DATA - DD6t12VDC TEST POINT

HI

ICGND~15VDC TESTPOINTdAYPOINT 1IISPLAY DATA - DD4IISPLAY DATA - DD5SPARE91SPLAY DATA - DD2DI$PLAY DATA - DDOSLEW CONTROL HISLEW CONTROL LODISPLAY DATA - DD3DISPLAY DATA - DD1LAMP TESTDISPLAY SELECT COMSPAREWAYPOINT/PROFILESELECT

SPARES

DIMMINGCONTROLLO

CHASSIS GND

ISPARES

PILOT’SVNAVCONTROL/DISPLAY

VN-800

connector Pin

16J1-1-------NC-2 (22)--------------------3 (24)-------------------

-27(24)-----------4-5 (24)--------------------6 (24)--------------------7-------NC-8 (22)--------------------9-------NC-10(24)-------------------11 (24)--------------------12(24)-------------------13-14(24)-------------------15(24)-------------------16(24)-------------------17(24)-------------------18(24)-------------------19(24)-------------------20(24)-------------------21(24)------------------

~;onnects To

FIG.C-150F;FIG.C-3

9JIB-899JIB-86

DC PWR GND

9JIB-889J1B-849J1B-85

9J1B-829J1B-809JIB-1039J:1B-1049JIB-839J1B-81FIG.C-59J1B-99

-22-23(24)------------------9J1B-90

J-24-25~ 26127 (24):i-iiij:--------% 50KFIG. c-3

---------

-28(22)------------------cHAssls‘ND

I-29-30

I5 VACLODISPLAYSELECT- DS1DISPLAYSELECT- DS25 VACHI

DISPLAYSELECT- DSO

J

-36(24)------------------;;::::;ODISPLAYDATA- DD7 16J1-37(24)------------------

\ 31:32 (22)---~0r

j

-----------

-33(24)-----------------

-34(24)------------------35(22)---J~-----------

AC PWRGND9J16-1019J18-102O-5VACLIGHTINGCONTROL


Page598.167May 25/90

useOrdisclosure of mformallon on this page IS subjeti to the reStrlCtlOnson the Mle page of this document.

Honeywell iirJfFANcECITATION n/V

DADC

28 VDC PowerRequirementsFigureC-1

26 VAC PowerRequirementsFigure C-2

O-5 VDCDIMMING 16J1-3 VN-80C)(2.5W)

AD-1 7198-171

EdgeLightingFigureC-3


22-14-00Page598.168‘May25/90

Use or disclosure of reformation on this page IS subject to the restrictions on the title page of thm ~ocument.

Honeywell M!WPANCECITATION V

ALTITUDE ALERT HORN

PILOTS +28VDC +

9JIB-76

OVERSPEED HORN

Use or dmclosure of


Page598.169Mar 15/89

Information on this page IS subject to the restncttons on the title pag~ of this document.

Honeywell PM!JRANCECITATION V

AIRCRAFT LAMP TEST SWITCH

+–07~ 16J1-20 VN-800

TEST

DADC TEST

c io 9J1A-52 AZ-810

TEST

AD-17200

Miscellaneous SwitchesFigure C-5

Use or disclosure of mformatlon


on this page IS subject to the restrictions

22-14-00Page 598.170

Mar 15/89on the Otle page of this jocument.

Honepe[[ &iJ..PANcECITATION n/V

‘A=P~T 1cl-—---” “--JU.tm

1%PITCHwHEEL

-— —.

V-ol,25J, B MF~VM~OL~N~T~ 1

r-——. 90 t~

PILOT SYMBOL I---- -------

&l 125J2B SG 9ACKuPI

I GENERAIUR

~ILTn-500———— T I

I

SG SIGNAL 94 ,4 L~7J1A 65J28

AP ENG 46 65J2A ;

L—.. ——

SG BACKUP $2

‘X

.—— — —

———— . IOJ I IS AUTOPILOTCOMPUTER 1.— —-— —q L————I P,LOTOC-811 1%’1

-–––– l_..q ,1, .2YAPEN.

llJ1 175J1 44 28 H\

u 42

I

I : . }

PITCH wHEELINPUT

t45 29 .0

I

v — ‘u

d L

lDJIA ———I

fl~AUTOPILOT

.46 - ENGAGE -28v ———

~JIA PILOT AZ-S1O

ALIC SLEW-

58 60

SLEW ENGAGE [GNDI

GND457 59

L ———— —

!!:~~--L.—.——-

65JIS PILOTS SYMBOLGENERATOR 65J~A

46 vs MOOE GNO 80 54 31ADcCMD

47 IAS MODE GNO 79 61 i

———— —

———— —

7J , ~ PILOT FZ-SOO 7J1B

76 VS MODE GND 36 = $40L0

77 IAS MOOE GND 37~ ,:RROR

———— — ——

L-$—————

PILOT MS-205 1x IAS MOOE GNU I

R z VS MODE GNDI

———— - A w“———

,2W3A MFD SYMBOL GEI

m

65

II x 4S MOOE GND

I s MOOE GNO

——.

AirDataCommandBlockDiagramwithMFDFigureC-6 (Sheet1 of 2)

YERA

l—

II

iI—A

—1IIIIIIIII,

—1TOR

I

I

I

I

,— Jm.mw


Page 598.171May25/90

Use or disclosure of Information on this page IS subject to the restrictions on the title page of this document.

Honeywell Uil!jJfPANcECITATIONn/V

1(

Air DataCommandBlockI)iagramWithoutMFDFigureC-6 (Sheet2)


22-14-00Page598.172‘Play25/90

Use or disclosure of mformatlon on this page IS subject to the restr!ctlons on the title page of this : ocument

Honeywell WUEP””c’CITATIONn/V

APP SEL, 8J1-f

NC ~;7J1B-53,7J1A-89

I

I

DME

{

65J2B-88VALID 7J1A-34 ‘~9JIB-66

II I

I I

{

IDME 65J2B-94 + 28V

ITTN 7J1A-50 Id

III

GROUND{

65J2B-79RANGE

~ + 28Vh

AD-1 7927-RI

VNAV Disable

Figure C-7


22-14-00Paqe 598.173‘May25/90

Use or disclosure of Information on this page IS subject to the restncttons on the title pag$? of this document.

Honeywell K2YEPANCECITATION n/V

TableC-1DADCAircraftIDs

CIT IICorm.Pin Ident ~ ~

9J1A-101 IDO 1 09J1A-102 ID1 o 09J1A-103 ID2 o 19J1A-104 ID3 o 19J1A-105 ID4 1 09J1A-106 ID5 o 0

0 = Jumper to 9J1A-8 (DC Ground)1 = No connection

1 1 00 1 10 I (!1 00 : 00 0 0


22-14-00Page 598.174“May25/90use or disclosure of information on this page IS subject to the restrictions on the Mle page of this \ocument.

Honeywell fl&VJErANcECITATION n/V

APPENDIXD

LSZ-850LIGHTNINGDETECTIONSYSTEMINSTALLATION


22-14-00Page598.175

May25/90Useordisclosureof Information on this page IS subject to the restnct!ons on the t!tle page of this document.

Honeywell K!M?ANCECITATION n/V

LIGHTNING PROCESSOR

LP-850


HREF IN (+)HREF IN (-)

145J1A-1------NC-2 ------NC

{

-3-4-5

SPARES

VREF IN (+)VREF IN (-)

-6 ------NC-7 ------NC

RED VIDOUT (+)RED VIDOUT (-)

-8 ------NC-9 ------NC

GRN VIDOUT (+)GRN VIDOUT (-)GRN VID OUT (S)

-lo------NC-11------NC-12 ------NC

BLU VIDOUT (S)BLU VIO OUT (+)BLU VIDOUT (-)

-13 ------NC-14 ------NC-15 ------NC

VID SEL OUT (+)VIDSELOUT (-)

-16 ------NC-17 ------NC

JC RTN -18------NC

dX STBY -19------NC

RNGIDO(+)?NGID1(+)RNG ID2 (+)?NG ID3 (+)

-20 ------NC-21 ------NC-22 ------NC-23 ------NC

+S OUT (+) -24 ------NC

;REF OUT (+)iREF OUT (-)iREF OUT (S)

-25 ------NC-26 ------NC-27 ------NC

IREF OUT (+)IR-EFOUT (-)

-28 --.---NC

145J1A-29 ------NC


Page598.176‘May 25/90

Use or disclosure of Information on thm page IS subject to the restrictions on the title page of this d >cument.

Honeywell MMF’”c’CITATION n/V

Function

RED VID IN (+)REDVID IN (-)

DC RTN

GRN VID IN (+)GRN VID IN (-)

BLU VID IN (+)BLU VID IN (-)

VID SEL IN (+)IID SEL IN (-)

SEL CL

;EL NAV

{SOUT (-)

IS OUT (+)

rST MODE 1rST MODE 2[ST MODE RTN

IS OUT (-)

;SCOM GND:s1:s2:s3:s4:s5;S6:s7:S8:s9:s10:s11:s12

LIGHTNING PROCESSOR

LP-850 (cent)


145J1A-30------NC-31------NC

-32------NC

-33------NC-34------NC

-35------NC-36------NC

-37------NC-38------NC

-39------NC

-40 ------NC

-41 ------NC

-42 __----Nc

-43------NC-44------NC-45------NC

-46------NC

-47------NC-48------NC-49------NC-50------NC-51------NC-52------NC-53------NC-54------NC-55 (24)------------------14SJ1A-64-56 ------NC-57------NC-58------NC

145J1A-59------NC


22-14-00Page 598.177

‘May 25/90Use or dwclosure of mformatlon on this page is subject to the restrictions on the t!tle page of this document.

Honeywell M!MW’”c’CITATION n/V

Function

CS13CS14CS15CS16CS COMGND

RS 232 INRS 232OUTRS 232 COM

LIGHTNINGPROCESSOR

LP-850(cent)


145J1A-60------NC-61------NC-62------NC-63------NC-64 (24)------------------145JIA-L5

-65 ------NC-66 ------NC-67 ------NC


Paae598.178‘May25/90

Use or disclosure of information on this page is subject to the restrictions on the t!tle page of this ~\ocument

Honeywell MMENANCECITATION n/V

LIGHTNING PROCESSOR

LP-850

Function Connector Pin ~onnects To

DG VALID 145J1B-1 (22)------------------- 6J1-h

wow -2 (24)------------------- FIG. D-3

28 V DC -3 (20)------------------- FIG. D-4PWR GND -4 (20)-------------------DC GNOCHASSIS GND -5 (20)-------------------CHASSISGND

HN (+)I

-6 (24)----~---~- ----- 147J1-11HN (-) -7 (24)----+!----!--’----14m-12

OUTERSHIELDT

.*-8 -------41II

TASREF (LO)

HW (+)

HW (-)HW (S)

-12V DC

E (+)E (-)E (S)

HN (S)

+12V DC12 V DC RTN

SHIELD

TST LOOP (S)

TST LOOP(+)TST LOOP (-)

-9 ------NCII., I

-13 (24)----!-~--------1~~-147J1-15

{ ‘- -,!-14(24)----~-1----~---- 147J1-3-15(24)----~1----1-

Y ‘--- 147J1-4-16 (24)----:j----:

-17--------:j-.d

}-18 (24)----l~--------l---14i’Jl-8

4-19(24)----~j---------- 14i’Jl-9-20(24)----To--------

!I-21 (24)----T-l---4~-22 (24)----~----r- ----- 147J1-5

-23 (24)----d---~- ----- 147J1-6

XMIT INHB -24 ------NC

INHB RTN -25------NC

429DATAIN 1 (H) -26----”-NC429DATA IN I (L) 145JIB-27------NC


Page598.179May25/90

Wseor disclosure of Information on thm page IS sub)ect to the restrictions on the title page of this document.

Honeywell WK?’”c’CITATIONn/V

Function

429 DATA IN 2 (H),429DATAIN 2 (L)I

LIGHTNINGPROCESSOR

LP-850(cent)


145J1B-28(24)------------ --- 9J1B-26l?~-29(.24)---------------- 9J1B-279 ---- SHIELDGND

LX VALIDFLGLX VALIDRTN

TAS (+)

TAS (-)TAS REF (HI)

IAS (+)IAS (-)IASREF (HI)

AP AS (+)APAS (-)

ADC HP (+)ADC HP (-)

SHIELD

429DATAOUT4 (H)429DATAOUT4 (L)SHIELD

IASREF (LO)

429DATAOUT 1 (H):;;EfiTAOUT 1 (L)

429DATAOUT 2 (H)429DATAOUT2 (L)SHIELD

429DATAOUT3 (H)429 DATAOUT3 (L)

-30 ------NC-31------NC

-32------NC-33------NC-34------NC

-35------NC-36------NC-37------NC

-38------NC-39------NC

-40------NC-41------NC

-42-------------

-43------NC-44------NC-45

-46------NC

!

/

-47(24)--P;------------65J2B-62-48 (24)---------------65J2B-6?-49(24)--Y

-50------NC-51------NC-52

I-53(24)--------To------- 125J3A-96

145J1B-54(24)--------~- ------ 125J3A-97


22-14-00Page598.180

May 25/90Use or disclosure of mformatlon on this page IS sub!ect to the restrictions on the title page of th!s jocument.

Honeywell liKNRANcECITATION n/V

Function

4DG (Y)iDG (Z)-IDG(X)

$YNCtiRO(H)jYNCHRO(L)

SPARE

:P RTN

iDGOFF

.X-CT

-x-s

-x

>wRoN

SPARE

LIGHTNINGPROCESSOR

LP-850(cent)

ConnectorPin

$145J1B-55(24)-----------1-----56(24)-----------7;----57(24)----------------

-----

1-58(24)----------+ ----59(24)----------------

v-----

-60

-61(24)------------------

-62------NC

-63(24)------------------

-64 (24)------------------

-65(24)------------------

-66(24)------------------

145J1B-67

Connects To

6J1-b6J1-Z6J1-aSHIELDGND

6J1-X6J1-YSHIELDGND

146J1-L

146J1-K

146J1-H

146J1-J

146J1-E


Page 598.181May 25/90

Use or dmclosure of Information on thm page IS subject to the restrictions on the ttle page of thm document.

Function

!8 V LIGHTING

i V LIGHTING

.IGHTING COMMON

;PARE

>WRON

ARE

ARE

,-s

LIGHTNINGSENSOR CONTROLLER

LU-850

Connector Pinconnects To——

146J1-A ------NC

-B (24)-------------------FIG”‘-5

-C (24)-------------------‘lGHTINGGND

-0

-E (24)-------------------145J1B-65

-F

-G

-H (24)------------------- 145J1B-64

-J (24)-------------------145J1B-65

;-CT

J RTN

IARE

IG OFF

PARES

-K (24)------------------- 145J1B-63

-L (24)------------------- 145J1B-61

-M

-N ------NC

[

-P-R-s-T-u

146J1-V

Hone~ell MYJRA*CECITATION1l/V

I

-1Interconnect Information

Table 501 (cent) 22-14-00Paue598,182

“Mav 25/90Use or disclosure of Information on thm page IS subJect to

the restrtcttons on the Mle page of thts I: xumefit. “

Honeywell MII!IRANC’CfTATIONn/V

Function

HW (+)

SPARE

E (+)E (-)

TSTLOOP(+)TSTLOOP(-)

CHASSISGND

+12V DC12 V RTN

SPARE

iN (+)

+N (-)

SPARE

iw (-)

-12VDC

;PARES

LIGHTNING ANTENNA

AT-850/855

ConnectorPin

147J1-1(24)-----fi----

7

-----

-2:1

II

1-3 (24)----q-P------~l----4 (24)----7-1-------- ---

‘l------a-------

-5 (24)-------6 (24)--------------~ --

-----7 ------NCI I

[1.

N~::;U]-----rL--r - ----------+-r - ---- -

-lo 1!Ii 1$

~1-11 (24)----TT---- - - ----12 (24)----rT---- - - ---

Ii ‘ -----13

1!-Jf----;- -----

’14 ‘24)- I [ . ------15(24)----Lj--~-~.------

yY --------

[

-16-17-18

f-19-20

I -21147J1-22

L ---- ----- ---

.!~onnectsTo

145J1B-10

145J1B-14145J1B-15145J1B-16145J1B-22145J1B-23145J1B-21

145J1B-18145J1B-19

145JiB-6145J1B-7145J1B-17

145J1B-11145J1B-12145J1B-13145J1B-20145J1B-8


22-14-00Page 598.183

May25/90Useordisclosureof !nformatlon on this page IS subject to the restrictions on the title pagt~ of thm document,

Function

ERIALCONTROL(HI)ERIALCONTROL(Lo)

PARE

8V DC INPUT8 V DC GNDHASSISGND8 V LIGHTINGV LIGHTINGIGHTINGCOMMONaNNUNCIATORDIMMINGiPARE:ONTROLBUS SHIELDiPARE

‘SB1~EMOTE ON

‘SBZ)FFINIFFOUT

. .

WEATHERRADARCONTROLLER

MC-650

Connector Pin Connects TO1

61J1-A-B

-c

-D-E-F-G-H-J-K-L-M-N-P-R-s-T

61J1-U

(24)-------------$

+9- - 59J1-s(24)-------------+-L-- 59J1-d

‘JI

I(22)--------------------28 V DC POWER

(22)J

------------------ DC POWERGND

~::n::~-----------,----CHASSIS‘ND

(24)--------------!---- ~l[H;;N:O~;[(24)-----.---------.--(24) 4-------------- ---- DAY/NIGtlTLOGIC

I

(24) 1--.-----------

[;:;------------------- wow sWITCH

------------------- 59J1-U

:--:--NC------NC------NC

J


page 598.184May25/90

Use or disclosure of mtormatlon on this page IS subject to the restrictions on the title page of this 0 Jcument

Honeywell Mll!!PANcECITATION n/V

WEATHERRADARCONTROLLER

WC-650

Function Connector Pin Jonnects To

CP RTN 61J2-M------NC

PWRON -E (24)-------------------145J1B-66

LX-S -H (24)-------------------145J1B-64

LX -J (24)-------------------145JIB-65

LX-CT -K (24) ------------------- 14!5J1B-63

CP RTN 61J2-L(24)-----------------Z-145J1B-61


22-14-00Page 598.185

May25/90Use or disclosure of Information on this page IS sub!ecf to the restrictions on the title page of this document.

Honeywell tifl!ll~r’”c’CITATION n/V

H: 145J1B-2

AD-20079 @

Weight On WheelsFigure D-3

PILOT’S Q

28 V DC 145J1 B-3 (28 W)

oAD-20079 2

DC PWl? Requirements

Figure D-4

5 V DC DIMMING 146J1-B(35 VA)

AD-20079@

Panel LightingFigure D-5


Page598.186May 25/90UseordisclosureOfmfofmatlononthispage!ssubjecttotherestrictionsonIhetitlepageofthisdt)cument,

APPENDIX E

CITATION 11 INSTALLATIONWIRING

Table 501 (cent) 22-14-00Page598.187

May 25/90Use or disclosure of mformal!on on this page IS sub!ect to the restrictions on the title page of this document.

Honeywell WWAN’ECITATIONn/V

APPENDIX E

CITATION II INSTALLATIONWIRING

ThisappendixdefinestheCitationII installation wiring. TheCitationIIAvionicsinstallationis identicalto theCitationV installation(referto themainbody), except the following:

● The RollRateMonitor(57J1),RZ-220,isnotusedin theCitation11avionicsinstallation.

c The SP-200(-941)autopilotis used in the Citation II installation.The

interconnect information for SP-200 (-941) is provided in thisappendix.


Paqe598.188‘May25/90

Use or disclosure of information on this page IS subject to the restr!ctlons on the Ilfle page of this d ]cument

Honeywell HYEPANC’CITATION 11~

AUTOPILOTCOMPUTERSP-200


+15 VDC 1OJ1A-1 (24)------------------+5 VDC -2 ------NC

+28 V A/P ENG ● TCS SEL -3 (20)------------------

SERVO PWR GND -4 (18)------------------

+28 VDC FROM A/P DIS ENGSW -5 (20)------------------SPARE -6-15VDC -7 (24)------------------CHASSIS GND -8 --------

d .9

ROLLHROLLCROLLHOLDANNGNDPITCHCOUPLEANNGNDAP OFF LIGHTGNDAP OFFHORNGNDPITCHHPITCHCROLLCOUPLEANNGNDROLLA/P PATHCOMMAND(ROLLLEFT= -)

V/LRADIODEVIATIONG/SDISPLACEMENTCMDADCALT INPUTG/S INTCMDAIRDATACOMMAND(+)SPAREAIRDATACOMMAND(-)TURNKNOBCOMMANDW(+ROLLLEFT)

TURNKNOBCOMMANDCT

t-9 (24)---------~--------10(24)-------~--------11------NC-12------NC-13(24)------------------14(24)--------

i

---------15(24)------13---------16 (24)------V---------17------NC-18(24)-----------------

-19------NC

1

.20(24)--,7-------------21(24)--1-[------------------------22(24)--G

[

-23 (24)---------,?------24-25(24)---------L!------26(24)---------------

-27(24)---------------

llJI-C, FIG.E-8,FIG.E-9

llJ1-C, 12J1-F,13J1-F, FIG. E-512!J1-C, 13J1-C14J1-C, SERVOPWRGNDFIG.E-5

llJ1-A

lJ1-u,7J1A-14lJI-s,7J1A-15

FIG.E-5FIG.E-5lJI-CC,7J1B-27lJi-AA,7J1B-28

7J:.A-28

7J;.B-429J1-52,16J1-377JIB-437JIB-33

7J1B-34llJ1-B

11.11-D*51K-

PITCHWHEEL+ CLIMB

J

-28(24)~1-------- FIL.E-4PITCHWHEEL+ DIVE -29(24)~- -------------1m Q OUTPUTGAINCONTROL -30------NCAPE 1OJ1A-31------NC


22-14-00Page598:189

May25/90UseordisclosureofIntormatlononthispage IS subject 10 the restrictions on the title pagf of this document.

Honeywell WMR!ANCECITATION n/V

. .

AUTOPILOT COMPUTER (cent)SP-200

Function Connector Pin ConnertsTo.-

ANEROIDSWITCHINPUT 10JIA1;;[;U]-----------------FIG. E-8PITCH WHEEL LOGICINHIBIT -----------------7J1B-49,65J2B-96SPARE -34VOR 0SS OUTPUT (+5 V 0SS) -35 ------NC

ROLL SPARE #8 -36 ------NC

SPARE -37

SPARE -38

AIRSPEED INPUT -39 (24)----------------- 7J1A-43, 9J1-64-40 -- ----NC

[COURSE ERROR :

-41 -- ----NC

-42 - -----NC

PITCH COUPLE SEL GND -43 ------NC

SPARE -44

ROLL INTEGRAL DISABLE -45 ------NC

{

x

1}

-46 (24)---n-----------HEADING Y -47(24)---j~-----------FIG.E-6

-48 (24)---J~----------A/PTEST (;15V) -49 (24)-----------------llJ1-Y

[

-50 (24)-----------------FIG.E-6-51 (24)-----------------1OJ1B-36

AUTOPILOTVALIDINTLK -52------NC-53------NC-54------NC

+28V PULSETRIMUP -55 (22) ----------------- FIG.E-5INTERLOCK -56------NCSPARE -57+28V PULSE TRIM DOWN -58 (22)----------------- FIG. E-5HDG ERROR -59------NCYAWRATE -60------NCPITCHDISPLACEMENT -61------NCPITCHRATE -62------NCLIFTCOMP -63 ------NCROLL DISPLACEMENT -64 ------NCROLL RATE -65 ------NCROLL IN1 -66 - -----NCROLL COORDINATION 1OJ1A-67 ------NC


Page 598.190May 25/90

Use or disclosure of reformation on this page IS subject to the restrictions on the title page of this d}cument

Honeywell KMFANCECITATION Ii/V

AUTOPILOT$N4JJ\TER(cent)


SIGNAL GND 1OJ1B-1 (20)-----------------SPARE-2+28V INPUTPOWER -3 (18)-----------------115VAC, 400HZ (H) -4 (22)---=-----------AC POWERGND -5 (22)---rl--+-.-------

SPARE26 VACOUTPUTDC POWERGNDSPARESPARE+28VDCA/P ENG

+28 VDC Y/DENG+28VDC FROMDISENGAGESW (Y/D)

28 VDC PULSETRIMDRIVE+28VDCTK OUTOF DETENTTTLGNDHDGHOLDANN “ GNDTORQUEWARNING28 VDC TCS SELECT

APP ARM GNDAPPCAPGND

II-6

1-7 (22)---:-- ----------8 (20)------------------9-lo-11 (22) -----------------12 (22) -----------------13 (22)----------------

-14 (22)-----------------15 (24)-----------------16------NC-17------NC-18 (24)-----------------19 (24)-----------------20------NC-21 (24)----------------

AIL SYNCHROEXCC -22 (22)----------------HDGGND -23------NCV/lGND -24------NCREVCRS GND -25------NCSBYGND -26------NCSOFTRIDEMODEGND -27 (24)----------------ENGINTLKTODG VALIDRELAY -28 (24)----------------

AILSYNCHROEXC H -29 (22)----------------+28V A/P ENGSELECTSYNCHRO -30 (24)----------------RUDDERSYNCHROEXC C -31 (24)----------------RUDDERSYNCHRO EXC H -32 (24)----------------+28 V A/P ENGINTERLOCK -33 (24)----------------

FLAPINPUTNO.2 -34------NC+28VDC Y/DENGSELECT 1OJ1B-35(24)----------------

ConnectsTo

SIGNALGND

FIG.E-1FIG.E-2AC POWERGND,13J1-E

13J1-D,6J1-X,C6J1-XDC POWERGND

65J1A-94,FIG.E-414J1-FFIG. E-5

FIG. E-5FIG. E-5

FIG.E-10FIG.E-5,65J1A-90

7JIB-70,65J1B-50,8J1-h12J1-E

llJ1-Z6J1-h,C6J1-h,FIG.E-612J1-DFIG.E-714J1-E14J1-DlJI-P,llJ1-P,FIG.E-7

llJ1-R


22-14-00Page 598.191

May25/90Use or disclosure of information on thts page IS subject to the restrictions on the Mle pag,, of thw document.

Honeywell R!IUE”ANCEGITATIONn/V

AUTOPILOTCOMPUTER(cent)SP-200


ENG INTERLOCK 10JIB::; [;:] ----------------- 1OJ1A-51LATERALMODELOGIC -----------------7J1A-77ALTHOLDMODEGND -38(24)-----------------7J1B-64+28V ALT VALIDOUTPUT -39------NCIASHOLDMODEGND -40 (24)----------------- 7J1B-65

V/S MODE GND -41(24)-----------------7J1B-63ALTHOW SYNCGND -42------NCIAS ● SYNCGND -43------NCADC VALID 4: (24) ----------------- 9J1-12v/s ● SYNCGND ------NC

GEAR + FLAPS DOWN -46 (24)----------------- FIG.E-9RESERVEDSPARE -47HEADINGRATEDISABLE -48(24)-h--------------FIG.E-6ELEV TACH (+) ’49 (24)-Fi

1------------- 13J1-N

ELEV TACH (-) -50 (24)-L~ -fi-

#

--------- 13J1-LELEV SERVO POSITION(H) -51(24)-----FT---------13J1-PELEVSERVOPOSITION(C) -52(24)-----I-OF ------- 13J1-RELEVSERVOAMPLOUTPUT(+)

1

-53(20)-------,-,------- 13J1-A,llJ1-WSPARE -54ELEV SERVO AMPL OUTPUT (-) -55 (20)-------l& ------- 13J1-B, llJ1-XAILERON TACH (+)

t-56 (24)---------I? ---- 12J1-L

AILERON TACH (-) -57 (24)---------1Y - -- 12J1-NAILERON SERVO AMPL OUTPUT (+) -58 (20)------------- -- 12J1-BAILERON SERVO POSITION (X)

ji-59 (24)-? -~~-~~~~~ -- 12J1-P

AILERON SERVO AMPL OUTPUT (-) -60 (20)-[~ -- 12J1-AAILERON SERVO POSITION (Y) ~:; [;:]-J --------: --- 12J1-RRUDDERSERVOAMPL (+) -----------------14J1-ARUDDERSERVOPOSITION(H) -63(24)-----------------14J1-PRUDDERSERVOAMPL(-) -64(20)-----------------14J1-BRUDDERSERVOPOSITION(C) -65(24)-----------------14J1-RRUDDERTACH(+) -66(24)-----------------14J1-LRUDDERTACH(-) 1OJ1B-67(24)-----------------14J1-N

Interconnect InformationTable501(cent) 22=14-00

Paae598.192“May25/90

Use or disclosure of Information on this page is subJect to the restrictions on the Iltle page of this document.

Honeywell MWW!ANCECITATION n/V

Function

TURN KNOB CWTURNKNOB WTURNKNOB CCW

TURNKNOB CT

28V ANN POWER (NIGH:)TURNKNOBOUT

{OF DETENTSWITCH NO

NC

O-28V EDGE LIGHTINGLIGHTING GNDA/P ENG INPUT +28VYD ENG

LOWBANKLIMITA/PENGSELECT

YD ENGSELECTSPARESPARE

PITCHWHEEL +PITCHWHEEL [ELEVSERVOAMPL- +

[ELEVSERVOAMPL -

A/PTEST+15VDCSOFTRIDEMODEGNDPOWERGNDSPARE+28V DC A/PENG ● TCS SEL

HDGMODEGND

SPARE

LAMPTESTGND

O-5VLIGHTING28VANN POWER(DAY)CHASSISGND

AUTOPILOTCONTROLLERPC-500


llJ1-A (24)------------------ lCIJIA-7

+

-B (24)---=- ----------- lCIJIA-26-C (24)--;-;-------------10J1A-1

1L ~-----------1oJ1A-27-D (24)---=--E (22)------------------FIGE-1-F ~22j------------------FIG E-5-G (22)------------------ llJ1-L, FIG. E-5-H (24j------------------ FIG.E-5

-J ------NC-K ------NC-L (22)------------------lIJ1-G, FIG.E-5-M (22)------------------FIGE-5-N (24)------------------7J1A-93-P (24)------------------lJ1-P, IOJIB-33,

FIG. E-7-R (24) ------------------ 1OJ1B-35-s-T

i]-U (24)----------O----- FIG E-4-V (24)----------U----- “-w (24)--~i-

t------------1OJ1B-53,13J1-A

-x (24)-:u--------------1OJ1B-55,13J1-B

-Y (24)------------------1OJ1A-49-Z (24)------------------1OJ1B-27-a (20)------------------DC POWERGND-b-C (24)------------------1OJ1A-3,12J1-F,

13J1-F-d (24)------------------::;:i7;i8J1-r,

-e

-f (24)------------------7J1A-54,16J1-16,LAMPTESTSWITCH

-g (22)------------------FIG.E-3-h (22)------------------FIG.E-1

llJ1-j(22)-----3


22-14-00Page598:193

May25/90useordisclosure Of lnfOrmatlOn on this page is subject to the restrictionson the Mle pag~ of this document.

Honeywell tijWJ5iANcECITATION n/V

PILOT’S 28 V DC

115 V AC

AP

~Bus— . — —IOJIB-3 AP (1OOW)

NIGHTr— lflJ1-E~

OC Power RequirementsFigure E-1

AP

—! >6

t- llJ1-h !

t ‘;WDAY J

‘AP DISCONNECT

400 HZ— 1A

I 1

AC Power “RequirementsFigure E-2

AD-20227

AP (17 VA)

PILOT’S 5V DC DIMMINGI

llJ1-gAP CONT (3 VA)

AD-20229

Edge LightingFigure E-3

.



22-14-00Page 598.194

May 25/90on Ihm page IS sub!ect to the restrictions on the t!tle page of th)s ltocument.

Honeywell WRANCECITATIONn/V

::::iNMT&....%01 lz-3aD

I

L

1= &_Jq 44 23 wH IPITCH WHEEL I

n“)llll 1 ~4sl I AZI LOI I

——— —— A

1-17’

1111 :%111 Ilr’”m .I

171111 -Cl “

“-yQw%J&iiP’=’v -. ==2=;DC SLEW

y ~:s

a

SLEW ENGAGE ~GND)

1

- 37I

II L-- ——-A II IP ———- —

S5J1B ‘1- SYMBOL G3NERATOR &J~ i4- 4sVS MOOE GND m

4 I47 lAS MODE GND 7s

. ———— — I—-—-—7J1E I1W 7s VS MODE GND 36 I

( 77 1- MOOE GNO alI

. ———.— — ———. — A

. ——-— —~, Ptwl ms-2Qs 1

1I

W&4 MFr=M70LzN~~T~ 1

x IAS MOOE GNO 1

- z VS MOOE GNOI I

———— — a l~lAI

70 IAS MODE GND1

———— — Jm.!-

Air DataCommandBlock DiagramFigure E-4


22-14-00Paqe 598,195‘May 25/90Useordisclosureofmformatlonon th!s page IS subject to the restrictions on the title pag( of this document.

Honeywell WEPANC’CITATIONn/V

Engage/Trim InterlockFigure E-5


22-14-00Page598.196‘May 25/90

Use or disclosure of mformatlon on this page IS subject to the restrictions on the title page of thm d )cument

H

ar+m22

0-o-sm=

(DUlnat+

>.

NN

6J }

<

10J1B

ENG INTLK .—< 28“%*a’’-z~~~~L~~~~

C6J i C6JI

PILOllS C-14Dh<+)

I

DIR GYRO NO. 1I

, i I I.10❑; ““’v” ‘

II I I

—...- ..-.

r--–%v

I .f3G2sTATof4x tL4LlI.

I ‘DG2sTAT0Ry I B ~

II ‘DG2sTAT0RzH--L ——— -J

COPlLO13 C-14D

T::3i’RM’2 -1II - d

–)

II -lI ‘DG2sTAT0RyIBPm4

IHEAOING X

I

IHEADING Y

I

I

I+7’HEADING Z

i= 1n I I

10J1B

I

+

46 tlDG RATE OISABLE

I II

~ - ——— JI

J( F

JUNCTION

+-l+

Box

IPILOT’S HDG REV

~

L1

II

AD 17928.R2

Honeywell MiW&NANcECITATIONn/V

. .

(AP CONT) llJ1

+28 V DCL—> PENG SEL

710J1B lJ1+28 V DCENG INTLK-> 33; ~ p <_/o—;:>—:&:’~ ;?

LATCH VG VALID

AD-20Z30-R1

Autopilot Engage Select and VG Valid SwitchingFigure E-7


22-14-00Page 598.198

May 25/90UseordisclosureofmformatlononthispageIS subjecttotherestrictionsonthetitlepageofIhls:ocumenl

Honeywell WK!ANC’CITATIONn/V

FEET ALT AD-783-R3

Aneroid Switch WiringFigure E-8

-+::<1FLAPS DN

+15VOC-> 1AD.-?~

Flap Transition SwitchFigure E-9

WARN

AD-785

Torque Warn Annunciator

Figure E-10


22-14-00Page 598.199/598~2~0

May 25/90Use or disclosure of Information on this page IS sub!ect to the restnct!ons on the t!tle pagr of this document,

Honeywell !#i~!f~ANc’CITATION V

-.

SECTION 7

SYSTEM SCHEMATICS

Information normally contained in overall system schematics has been incorporated

in the mode flow diagrams (Section 3) and the interconnects (Section 6);

therefore, this section has been omitted.

22-14-00Page 601/602

Mar 15/89Use or disclosure of mformatlon on thw Page IS sub!ect to the restncttons on the Mle pag~> of th~s document.

Honeywell WM?ANcECITATION V

SECTION 8REMOVAL/REINSTALLATIONAND ADJUSTMENT

1. General

2

3

This section provides instructions for removing and reinstalling, and

adjusting each unit of the Integrated Flight Control System that has been

previously installed in the system. Should any INSTALLATION CRITICAL cases

arise with the reinstallation of any unit, be sure to comply 100 percent with

the instructions.

CAUTION: TO PREVENT COMPONENT DAMAGE, TURN AIRCRAFT POWER OFF WHEN REMOVING

OR INSTALLING COMPONENTS.

~: No adjustment is required unless states otherwise.

After reinstallation of any unit, check unit operation in accordance with

applicable GROUND CHECK procedure.

Equipment and Materials

No special equipment or materials other than those commonly used in shop are

required for reinstalling and adjusting the System.

Procedure for All Indicators and Electronic Dis~lavs (Exce~t WI-650 Weather

Radar Indicator

A. Remove Indicators or Displays.

(1) Loosen screws on panel at each corner of unit.

NOTE : If new shelf-type clamp is used,only the top two screws need

to be loosened.

(2) S1 ide unit out of panel and disconnect cable connector(s).

B. Reinstall Indicators or Displays.

(1) Mate unit connector(s) with cable connector(s) and slide unit into

panel .

(2) Tighten screws on panel at each corner of unit.

c. ADI Inclinometer Level Adjustment

(1) Loosen two screws on cover.

(2) Adjust inclinometer or lever

level and tighten screws.on right side until inclinometer is

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Honeywell lNi&WANcECITATIONn/V

4. Procedure for Selectors and Controllers

A. MS-205Mode Selector, PC-500 Autopilot Controller, RI-106S Instrument

I

Remote Controller, DC-811 Display Controller, MC-800 MFD Controller,AV-850A Audio Control Unit, CD-800 Control Display Unit, and WC-650Weather Radar Controller

(1) Remove unit.

(a) Loosen unit screw fasteners.

(b) Slide unit out of panel and disconnect cable connector.

(2) Reinstall unit.

(a) ~:::lunit connector with cable connector and slide unit into.

(b) Tighten unit screw fasteners.

I B. VN-212 VNAV Computer/Controller,VN-800 VNAV Control/Display, and LU-850Lightning Sensor Controller

(1) Remove unit.

(a) Loosen screws on panel at each corner of unit.

(b) Slide unit out of panel and disconnect cable connector.

(2) Reinstall Unit.

(a) ~;;glunit connector with cable connector and slide unit into.

(b) Tighten screws on panel at each corner of unit.

5. Procedure for Sensors and Gyros

A. AG-222 Accelerometer and RG-204 Rate Gyro

NOTE: Before removing accelerometer, note direction of arrow to ensureunit is reinstalled properly.

(1) Remove Accelerometer or Rate Gyro.

(a) Disconnect cable connector from unit.

(b) Remove hardware securing unit to airframe.

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Honeywell !iNK?’””CITATION V

5. A. (2) Reinstal1 Accelerometer or Rate Gyro.

(a) Secure unit to airframe with applicable hardware. Ensure thatarrow on accelerometer is pointed in proper direction.

(b) Mate unit connector with cable connector.

B. VG-14A Vertical Gyro and C-14D Directional Gyro.

CAUTION: A GYRO MAY BE DAMAGED BY MOVING IT AFTER ELECTRICAL POWER ISREMOVED BUT BEFORE THE GYRO ROTOR STOPS. THE GYRO ROTOR WON’TCOME TO A STOP FOR APPROXIMATELY 15 MINUTES AFTER ELECTRICALPOWER IS REMOVED. WHEN REMOVING OR INSTALLING A GYRO FROM ORTO ITS MOUNT, DO SO GENTLY WITH NO QUICK MOTION. THE GYROSHOULD NOT BE TWISTED IN ITS ISOLATOR SHOCK MOUNTS. ANYEXCESSIVE TWISTING WILL CAUSE THE GYRO TO REMAIN OFFSET FROMITS NEUTRAL POSITIONFORA SHORTPERIODOF TIME.

(1) Remove Gyro.

(a) Disconnect cable connector from gyro.

(b) Remove hardware securing gyro to airframe.

(2) Reinstall Gyro.

(a) Secure gyro to airframe with applicable hardware.

(b) Mate gyro connector with cable connector.

(c) For VG-14A Gyros Only, any adjustment necessary to the ROLL andPITCH gradients will be determined by performing the applicableGROUND CHECK procedure.

c. FX-220 Flux Valve

~: Whenever a flux valve is removed and replaced, a compass swingmust be performed to maintain desired heading accuracy.

(1) Remove flux valve.

(a) Gain access to flux valve by removing wing access panel.

(b) Remove cover from flux valve and disconnect six wires from fluxvalve terminals.

(c) Remove three screws securing flux valve to mounting bracket.

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Honeywell WVF’”c’CITATION V

5. c. (2) Reinstall flux valve. “

(a) Install flux valve in mounting bracket and secure with three6-40X3/8-inch, round head, nonmagnetic machine screws,Honeywell Part No. 319011.

NOTE: Do not use magnetic type screws to mount the flux valve.

(b) Connect applicable wires to flux valve terminals and instal 1

cover on flux valve.

(c) Perform compass swing calibration procedures.

(3) Compass Swing Calibration

(a) Energize the Compass System and allow several minutes for thegyro to reach operating speed and for the system to slave tothe magnetic heading.

~: The aircraft should be in its normal flight position with theelectrical system and radio equipment operating.

(b) Position the aircraft on a compass rose and turn it to each ofthe four cardinal headings.

(c) Allowing sufficient time for the heading indicator to settlerecord the differences in readings between the headingindicator and the compass rose at each cardinal heading as p’or minus, depending on whether the dial readings are greaterless than the compass rose readings.

usor

NOTE : Instead of the compass rose, a magnetic sighting compass may

be used. To take a reading, the compass is located at a

considerable distance fore and aft of the aircraft and is

moved back and forth from the line of sight coinciding withthe plane. When a sight is taken facing aft, 180 degreesmust be added or subtracted from the sighting compassreading. When facing fore, the compass reads directly.

(d) Add the errors algebraically and divide by four. The result is

the index error.

(e) Loosen the screws holding the flux valve flange to its mountingsurface and rotate the flange of the unit to cancel out theindex error. If the error is positive, the flange should berotated in the counterclockwise direction (giving a minusreading on the flange) as observed from above the unit.

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5. c. (3) (f)

(9)

(h)

(i)

If the error is negati~e, rotate the flange in the clockwise

direction (giving a plus reading on the flange). The amount of

rotation should equal the index error.

Tighten the mounting screws and recheck the readings at the

four cardinal headings. Recalculate the index error to make

sure it is zero.

If the index error is not zero, readjust the flux valve flangeuntil this error is cancelled.

Any remaining errors in excess of fl degree which are caused byextraneous magnetic fields should be counteracted byreadjusting the compensator. Refer to paragraph 5.D.(3).

D. CS-412 Dual Remote Compensator

(1) Remove Compensator.

(a) Disconnect cable connector(s) from unit.

(b) Remove hardware securing unit to airframe.

(2) Reinstall Compensator.

(a) Secure unit to airframe with applicable hardware.

(b) Mate unit connector(s) with cable connectors.

(c) Perform compensator adjustment procedures.

(3) Compensator Adjustments.

NOTE : Before making the following adjustments to the dual remotecompensator, perform flux valve index error adjustment.

(a) Remove the compensator cover and adjust the compensationpotentiometers to their center position.

(b) Using a compass rose, place the aircraft on a north heading andallow compass dial to settle.

(c) Compensate for any difference between actual heading and

compass dial indication by loosening locking nut and adjusting

N-S (North-South) potentiometer on compensator. Tighten

locking nut.

(d) Place the aircraft on an east heading and allow compass dial to

settle.

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Honeywell Will!’””CITATION n/V

5.

6.

I

D. (3) (e)

(f)

(9)

(h)

(i)

(j)

Compensate for any difference between actual heading andcomDass dial indication b.vlooseninq lockinq nut and adiiustinqE-W’(East-West) potentiom~ternut.

Place the aircraft on a southsettle.

on coiiipensato;. Tighten lockin~

heading and allow compass dial to

Compensate for half of any difference between actual headingand compass dial indication by loosening locking nut andadjusting N-S potentiometer on compensator. Tighten lockingnut.

Place the aircraft on a west heading and allow compass dial tosettle.

Compensate for half of any difference between actual headingand compass dial indication by loosening locking nut andadjusting E-W potentiometer on compensator. Tighten lockingnut.

The compensator should now be fully adjusted for propercompensation. As a check, swing the aircraft on 30-degreeincrements and note readings on compass dial. All readingsshould be within 1 degree of the actual heading. If errors aregreater than 1 degree, repeat index error adjustment and aboveadjustments for greater accuracy.

NOTE: MC-1 or MC-2 Magnetic Compass Calibrator Set can be usedfor index error and compensator adjustment in lieu ofthe above procedure.

Procedure for SP-200 AutoDilot. FZ-500 Fliaht Director, NZ-61O Navigation andAZ-241/AZ-810 Air Data ComDuters, SG-605/MG-605 Symbol Generators, OZ-800Receiver Processor unit. RNZ-850 NAV Unit, RCZ-850 COM Unit, ML-850 MLSReceiver, and LP-850 Liqhtninq Sensor Processor

A. Remove unit.

(1) For air data computers, disconnect pitot and static lines.

(2) Loosen mounting tray holddown assembly knob.

(3) Slowly pull forward on unit handle to separate unit and trayconnectors and slide unit out of tray.

B. Reinstall unit.

(1) Slide unit into mounting tray.

(2) Carefully apply firm pressure until unit connector is mated withconnector receptacle on mounting tray.

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Honeywell W!JRANCECITATION V

CAUTION: DO NOT FORCE FIT.-” IF MATING IS DIFFICULT,REMOVE THE UNIT AND CHECK FOR CONNECTOR PINSTHAT MAY BE BENT OR OUT OF ALIGNMENT. ALSOCHECK THE ALIGNMENT OF THE RECEPTACLE IN THEMOUNTING TRAY.

6. B. (3) Insert mounting tray holddown assembly knob into hookon front ofunit, and tighten holddown knob.

(4) For air data computers, connect pitot and static l-nes and performpitot/static leak check.

7. Procedure for SM-200 Servo Drive and SB-201 Drum and Bracket Assembly

A. Servo Drive Assembly

(1) Remove Servo Drive Assembly.

(a) Disconnect cable connector from servo drive.

(b) Cut safety wire securing four screws on rear of servo drive,and remove screws.

(c) Slide servo drive out of drum and bracket assembly.

(2) Reinstall Servo Drive Assembly.

(a)

(b)

B. Drum and

Slide servo drive into rear of drum and bracket assembly andsecure with four screws, Honeywell Part No. 4011086. Safetywire all four screws.

Mate servo drive connector with cable connector.

Bracket Assembly

(1) Remove Drum and Bracket Assembly.

(a) Remove servo drive in accordance with paragraph 7.A. (1).

(b) Release bridle cable tension.

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7. B. (1) (c) Cut safety wire on fou~ screws securing retaining plate, andremove screws and retaining plate.

(d) Remove four cable keepers, Honeywell Part No. 2518330.

(e) Cut safety wire and remove two screws securing swagged cableterminals to drum.

(f) Unwrap bridle cables from drum.

(g) :;~;;:m~our bolts securing drum and bracket assembly to

.

(2) Reinstal 1 Drum and Bracket Assembly.

(a) Mount drum and bracket assembly rigidly to airframe with fourl/4-inch diameter bolts of sufficient length, and four suitablelock washers and nuts.

(b) Wrap bridge cables around servo bracket drum. Secure swagged

cable terminals to servo bracket drum with two, 0.138-32-NC-2A

stainless steel drilled screws, Honeywell Part No. 2554911-1.Safety wire screws through adjacent holes in drum with Low MuMonel wire, 0.020 inch diameter and 4 inches long.

m

TO ENSURE CABLE TERMINAL CAPTURE, USE ONLY SCREW, HONEYWELL PART NO.2554911-1. STANDARD FILLISTER HEAD SCREWS MAY NOT PROPERLY RETAINTHE CABLE TERMINAL.

(c) Adjust control system and bridle cables to proper tension.Cable tension will vary with aircraft. Refer to TypeCertificate, Supplementary Type Certificate, or aircraft manualas applicable to determine proper cable tensions.

(d) Install two of four cable keepers, Honeywell Part No. 2518330,on the servo bracket at points of cable tangency to drum. Theother two cable keepers shall be located at 90 degrees from thefirst two.

(e) Install retaining plate, Honeywell Part No. 2518332, on theslotted end of the cable keepers using four, 5/16-inch long,

No. 8-32, drilled fillister head screws. Safety wire thesefour screws with Low Mu Monel wire, 0.032-inch in diameter and4 inches long.

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Honeywell WWANCECITATIONV

INSTALLATION CRITICAL

TO ENSURE THAT THE CABLE CANNOT JAM BETWEEN THE DRUMAND KEEPERS, THE DISTANCE BETWEEN THE KEEPERS AND DRUMSHALL BE MEASURED AFTER THE KEEPERS AND RETAINING PLATEARE INSTALLED. THE DISTANCE BETWEEN THE DRUM ANDKEEPERS SHALL NOT EXCEED 0.040-INCH AND NOT BE LESSTHAN 0.005 INCH. THE 3/32-INCH CABLE DIAMETER SHALL BEVERIFIED. THESE ARE CRITICAL INSTALLATIONREQUIREMENTS.

(f) Reinstall servo drive in accordance with paragraph 7.A. (2).

8. Procedure for RT-300 Radio Altimeter Receiver Transmitter

A. Remove Radio Altimeter Receiver Transmitter.

(1) Disconnect cable and antenna connectors.

(2) Remove mounting hardware on front of unit and loosen mountinghardware on back and remove unit.

B. Reinstall Radio Altimeter Receiver Transmitter.

(1) Slide unit into mounting location and secure with applicablehardware.

(2) Mate unit connectors with applicable antenna and cable connectors.

c. Radio Altimeter Display Zero Ground Adjustment.

~: On the radio Altimeter Receiver Transmitter, the zero adjustpotentiometer is accessible through hole above connector on frontof unit.

Apply power and adjust potentiometer for zero foot display

indication on the ED-600 EADI.

9. Procedure for RZ-220 Roll Rate Monitor

A. Remove Monitor.

(1) Disconnect cable connector from unit.

(2) Remove hardware securing unit to airframe.

B. Reinstall Monitor.

(1) Secure unit to airframe with applicable hardware.

(2) Mate unit connector with cable connector.

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Honeywell WIRANCECITATION V

10. Procedure for WU-650 Antenna and Re~eiver/Transmitter Unit

A. Remove Antenna and Receiver/Transmitter Unit.

(1) Disconnect cable connector from unit.

(2) Remove hardware securing unit to airframe.

B. Reinstall Antenna and Receiver/Transmitter Unit.

(1) Secure unit to airframe with applicable hardware.

(2) Mate unit connector with cable connector.

(3) Perform test and adjustment in accordance with procedures inPRIMUS@ 650 System Description and Installation Manual, Pub. No.A09-3941-01.

11. Procedure for WI-650 Weather Radar Indicator

A. Remove Indicator.

(1) Using a 7/64 allen wrench, turn two screws (access holes are nearlower edge of Indicator front panel) counterclockwise to disengagetwo locking pawls holding Indicator to mounting tray.

(2) Slide Indicator out of instrument panel, andconnector P101 and connector P102, if used.

B. Reinstall Indicator.

(1) Turrt two screws (access holes are near lower

disconnect aircraft

edqe of Indicator. .front panel) counterclockwise so that locking p~wls will travelrearmost.

(2) Connect Indicator to aircraft mating connector P101. If used,connect mating connector P102.

(3) Slide Indicator, connector-end first, into tray, and engage twospring-loaded guide pins at rear.

(4) Turn locking-pawl screws clockwise until pawls engage tray (throughrectangular cutouts).

CAUTION: USE ONLY HAND PRESSURE TO SEAT INDICATOR INTO PANEL. DO NOTUSE THE LOCKING-PAWL SCREWS TO “SCREWJACK” THE INDICATOR INTOPLACE.

(5) Push Indicator into panel with one hand until springs in guide pinsare depressed, hold in place and tighten locking-pawl screws.

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Honeywell WMPANC’CITATION V

12. Procedure for RM-850 Radio Management Unit (RMU)

A. Remove RMU.

(1) Loosen screws on panel at each top corner of unit.

(2) Slide unit out of panel and disconnect aircraft cable connector.

B. Reinstall RMU.

(1) Mate unit connector with aircraft cable connector and slide unitinto panel.

(2) Tighten screws on panel at each top corner of unit.

13. Procedure for CD-850 Clearance Deliverv CDU

A. Remove Clearance Delivery CDU.

(1) Using a3/32 Allen Wrench, loosen unit mounting clamps.

(2) Slide unit out of panel and disconnect aircraft cable connector.

B. Reinstall Clearance Delivery CDU.

(1) Mate unit connector with aircraft cable connector and slide unitinto panel.

(2) Using a3/32 Allen Wrench, tighten unit mounting clamps.

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Honeywell M!’K!’NCECITATIONV

SECTION 9SHIPPING, HANDLING. AND STORAGE

Refer to manual, Honeywell Pub. No. 09-1100-01, for detailed procedures for

preparing all system components for storage or shipment.

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Note 1, Honeywell, 09/11/97 09:48:35 AM +15VDC

Note 2, Honeywell, 09/11/97 09:49:05 AM GND

Page 387

Note 3, Honeywell, 09/11/97 09:42:40 AM ,

Note 4, Honeywell, 09/11/97 09:43:45 AM 10J1B-54

cessna citation ii y v

Documents

thispageis

listof effective

850a audiocontrol

81o air datasystem

microwave

605and optional

altitude selected

line select