document no. ams-737-345-27256 aircraft manual …

Document No. AMS-737-345-27256

AIRCRAFT MANUAL

SUPPLEMENT To comply with EASA Regulation CS-25.1529 and CS-25 Appendix H and FAA Regulation CDR 14 25.1529 and to support the continued airworthiness of:

B737-300/400/500 – MSN 27256 Document No: AMS-737-345-27256

Intro Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.

®


Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.

®

HIGHLIGHTS Issue 2 Wiring Diagram Manual 22-11-75 – Added Aircraft Maintenance Manual 22-11-01 – Added Issue 3 Aircraft Maintenance Manual 31-24-01 – Replaced Issue 4 Aircraft Maintenance Manual 23-71-00 - Changed Issue 5

Wiring Diagram Manual 25-00-18 – Added Illustrated Parts Catalogue 25-31-11-99Z – Added



®

RECORD OF REVISION

Issue DIN No. Date Issue DIN No. Date Initial DIN-2364 APR 01/11

2 DIN-2760 JAN 01/12 3 DIN-3364 NOV 01/12 4 DIN-3606 APR 01/13 5 DIN-3950 OCT 01/13

The Aircraft Manual Supplement (AMS) is to be used in conjunction with the related aircraft’s manuals. The information contained within this manual relates to various alterations/changes/modifications that have been carried out on the associated aircraft. A list of effective alterations/changes/modifications can be found in the Introduction pages to this manual. These alterations/changes/modifications are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related convention. This manual complies with EASA Regulations CS-25.1529 and CS-25 Appendix H, which in turn mirror the FAA regulation CDR 14 25.1529. DINs are Document Issue Notes and are administration documents used to issue this manual to the customer and are used for record purposes only.

RRA-00 Page 1



®

INTRODUCTION

1. General A. This publication was prepared by Aerospace Design and Engineering Consultants (AeroDEC®) Ltd and is in accordance with

Air Transport Association of America Specification No. 100, Specification for Manufacturers Technical Data. The data contained within is related to certain changes/modifications/alterations that are in addition to the associated airplane’s type design.

NOTE: THIS MANUAL IS PREPARED SPECIFICALLY TO COVER THE AIRPLANE LISTED IN THE "INTRODUCTION"

SECTION, FOR THE OWNER/OPERATOR NAMED ON THE TITLE PAGE.

THIS MANUAL IS NOT SUITABLE FOR USE, INCLUDING WITHOUT LIMITATION, GENERAL INSTRUCTIONS OR TRAINING, FOR ANY AIRPLANES NOT LISTED HEREIN.

B. The convention for the use of this publication is in the same convention (ATA 100) as the associated manufacturers AMM,

WDM, and IPC. Therefore, this publication is a SUPPLEMENT to the associated AMM, WDM, and IPC, and instructions on how to use this manual are equivalent to the instructions on how to use the manufacturers AMM, WDM and IPC.

C. This Manual Supplement has been raised to give historic design information pertaining to the following related aircraft

manuals: WDM – Wiring Diagram Manual IPC – Illustrated Parts Catalogue AMM – Aircraft Maintenance Manual

D. For information on the approval of the technical content of this document, please refer to the Change/Mod/Alteration listing E. Aircraft Effectivity Information:

MODEL/ TYPE

CUST EFFECT CODE

CUST EFFECT CODE

(IPC ONLY)

VARIABLE ENGR

NUMBER

ENGINE SET

NUMBER

BASIC ENGR

NUMBER

MFG SERIAL

NUMBER REGISTRY NUMBER

CUSTASSIGNED AIRPLANE

IDENT

B737-45D 404 PV284 PA696 P8005 27256

INTRO-00 Page 1 OCT 01/13



®

LIST OF EFFECTIVE PAGES

Description Page No. Date Description Page No. Date

Front Page 31-24-24-99Z 1 APR 01/11 Highlights Chapter 33 Front Page Record of Revision and Approval 1 33-11-00-05Z 0 APR 01/11 Introduction 1 OCT 01/13 33-11-00-05Z 1 APR 01/11 Introduction 2 OCT 01/13 Chapter 34 Front Page List of Effective Pages 1 OCT 01/13 34-28-31-02Z 0 APR 01/11 List of Effective Pages 2 OCT 01/13 34-28-31-02Z 1 APR 01/11 Report/Feedback Sheet 34-62-21-04Z 0 APR 01/11 WDM Front Page 34-62-21-04Z 1 APR 01/11 WDM Contents 1 Chapter 35 Front Page WDM Contents 2 35-12-00-02Z 0 APR 01/11 Chapter 22 Front Page 35-12-00-02Z 1 APR 01/11 22-11-75 1 JAN 01/12 35-12-00-02Z 2 APR 01/11 Chapter 23 Front Page 35-12-00-20Z 0 APR 01/11 23-22-01 1 APR 01/11 35-12-00-20Z 1 APR 01/11 23-71-01 1 Sht 1 APR 01/11 AMM Front Page 23-71-01 1 Sht 2 APR 01/11 AMM Contents 1 Chapter 25 Front Page AMM Contents 2 25-00-18 115/116 OCT 01/13 Chapter 22 Front Page Chapter 31 Front Page 22-11-01 501 JAN 01/12 31-31-01 1 APR 01/11 22-11-01 502 JAN 01/12 Chapter 33 Front Page Chapter 23 Front Page 33-17-01 1 APR 01/11 23-71-00 501 APR 01/13 Chapter 34 Front Page 23-71-00 502 APR 01/13 34-22-11 1 APR 01/11 23-71-00 503 APR 01/13 34-22-21 1 APR 01/11 23-71-00 504 APR 01/13 34-49-04 1 APR 01/11 23-71-00 505 APR 01/13 34-53-12 1 APR 01/11 23-71-00 506 APR 01/13 34-53-22 1 APR 01/11 23-71-00 507 APR 01/13 34-61-11 1 APR 01/11 Chapter 25 Front Page IPC Front Page 25-11-11 201 APR 01/11 IPC Contents 1 25-11-11 202 APR 01/11 IPC Contents 2 25-11-11 203 APR 01/11 Chapter 23 Front Page 25-11-11 204 APR 01/11 23-71-13-01Z 0 APR 01/11 25-11-11 205 APR 01/11 23-71-13-01Z 1 APR 01/11 25-11-11 206 APR 01/11 Chapter 25 Front Page 25-11-11 207 APR 01/11 25-11-11-18Z 0 APR 01/11 25-11-11 208 APR 01/11 25-11-11-18Z 1 APR 01/11 25-11-11 209 APR 01/11 25-11-11-66Z 0 APR 01/11 25-11-11 210 APR 01/11 25-11-11-66Z 1 APR 01/11 25-11-11 211 APR 01/11 25-11-21-22Z 0 APR 01/11 25-11-11 212 APR 01/11 25-11-21-22Z 1 APR 01/11 Chapter 31 Front Page 25-31-11-99Z 0 OCT 01/13 31-24-01 1 APR 01/11 25-31-11-99Z 1 OCT 01/13 31-24-01 2 APR 01/11 Chapter 31 Front Page 31-24-01 3 APR 01/11 31-24-11-01Z 0 APR 01/11 31-24-01 4 APR 01/11 31-24-11-01Z 1 APR 01/11 31-24-01 5 APR 01/11 31-24-22-01Z 0 APR 01/11 31-24-01 6 APR 01/11 31-24-22-01Z 1 APR 01/11 31-24-01 7 APR 01/11 31-24-24-99Z 0 APR 01/11 31-24-01 8 APR 01/11

LEF-00 Page 1 OCT 01/13



®

LIST OF EFFECTIVE PAGES

Description Page No. Date Description Page No. Date

31-24-01 9 APR 01/11 34-49-03 502 APR 01/11 31-24-01 10 APR 01/11 34-62-01 501 APR 01/11 31-24-01 11 APR 01/11 34-62-01 502 APR 01/11 31-24-01 12 APR 01/11 34-62-01 503 APR 01/11 31-24-01 13 APR 01/11 31-24-01 14 APR 01/11 31-24-01 15 APR 01/11 31-24-01 16 APR 01/11 31-24-01 17 APR 01/11 31-24-01 18 APR 01/11 31-24-01 501 APR 01/11 31-24-01 502 APR 01/11 31-24-01 503 APR 01/11 31-24-01 504 APR 01/11 31-24-01 505 APR 01/11 31-24-01 506 APR 01/11 31-24-01 507 APR 01/11 31-24-01 508 APR 01/11 31-24-01 509 APR 01/11 31-24-01 510 APR 01/11 31-24-01 511 NOV 01/12 31-24-01 512 APR 01/11 31-24-01 513 APR 01/11 31-24-01 514 APR 01/11 31-24-01 515 APR 01/11 31-24-01 516 APR 01/11 31-24-01 517 APR 01/11 31-24-01 518 APR 01/11 31-24-01 519 APR 01/11 31-24-01 520 APR 01/11 31-24-01 521 APR 01/11 31-24-01 522 APR 01/11 31-24-01 523 APR 01/11 31-24-01 524 APR 01/11 31-24-01 525 APR 01/11 31-24-01 526 APR 01/11 31-24-01 527 APR 01/11 31-24-01 528 APR 01/11 31-24-01 529 APR 01/11 31-24-01 530 APR 01/11 31-24-01 531 APR 01/11 31-24-01 532 APR 01/11 31-24-01 533 APR 01/11 31-24-22 601 APR 01/11 31-24-22 602 APR 01/11 31-24-24 201 APR 01/11 31-24-24 202 APR 01/11 Chapter 34 Front Page 34-22-00 501 APR 01/11 34-22-00 502 APR 01/11 34-49-03 501 APR 01/11

LEF-00 Page 2 OCT 01/13



®

REPORT/FEEDBACK SHEET

This Report/Feedback Sheet is provided for the purpose of communicating to Aerospace Design and Engineering Consultants (AeroDEC) Ltd. any errors or suggested improvements arising fro this Aircraft Manual Supplement

AMS Section: Applicants Name:ATA Ref(s): Applicants Signature: Date:(Please provide details below):

FEEDBACK ONLY (Please provide details below):

WIRING

DIAGRAM

MANUAL

Contents

WDM-CONTENTS Page 1


®

Chapter 11 PLACARD & MARKINGS

Chapter 21 AIR CONDITIONING

Chapter 22 AUTO FLIGHT

22-11-75 – DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS

Chapter 23 COMMUNICATIONS

23-22-01 – SELCAL

23-71-01 – COCKPIT VOICE RECORDER

Chapter 24 ELECTRICAL POWER

Chapter 25 EQUIPMENT/FURNISHINGS

25-00-18 – SELL COMPONENT MAINTENANCE MANUAL P/N 1003C11A00000

Chapter 26 FIRE PROTECTION

Chapter 27 FLIGHT CONTROLS

Chapter 28 FUEL

Chapter 29 HYDRAULIC POWER

Chapter 30 ICE AND RAIN PROTECTION

Chapter 31 INDICATING/RECORDING SYSTEMS

31-31-01 – DFDRS INTERCONNECT GROUP 1

Chapter 32 LANDING GEAR

Chapter 33 LIGHTS

33-17-01 – MAP, FLIGHT KIT, AND READING LIGHTS

Chapter 34 NAVIGATION

34-22-11 – EFIS POWER/PROGRAM PIN - LEFT

34-22-21 – EFIS POWER/PROGRAM PIN - RIGHT

34-49-04 – GROUND PROXIMITY WARNING

34-53-12 – ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING

34-53-22 – ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING

34-61-11 – FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS

Chapter 35 OXYGEN

Chapter 36 PNEUMATIC

Chapter 38 WATER/WASTE

WDM-CONTENTS Page 2


®

Chapter 49 AIRBORNE AUXILIARY POWER

Chapter 52 DOORS

Chapter 53 FUSELAGE

Chapter 54 NACELLES / PYLONS

Chapter 55 STABILIZERS

Chapter 56 WINDOWS

Chapter 57 WINGS

Chapter 71 POWER PLANT

Chapter 73 ENGINE FUEL AND CONTROL

Chapter 74 IGNITION

Chapter 75 AIR

Chapter 77 ENGINE INDICATING

Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

CHAPTER

AUTO FLIGHT

B737-300/400/500 WIRING DIAGRAM MANUAL

PV284

DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS

22-11-75 INCORPORATES: 22-11-75 AERODEC MOD 1093

Page 1 Page 1

JAN 01/12 JAN 01/12 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

M924FLIGHT CONTROL COMPUTER "A"

W011

W011−737−20

D1671A

2

18

19

22 STD OPT ILS DEVN WARN

25

BIT 1

26

D1795A

D1795B

44

61

STD OPT ALT ALERT

CONFIG PINS

G/S SUPERFLAG

2

D1671B

28

30

32

35

44

62

27

29

33

42

57

BIT 2

STD OPT AIRSPEED WARNSTD OPT CWS WARN

STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO

STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL

STD OPT ODD PARITYSTD OPT EFIS

STD OPT DUAL CHANNELAUTO F/D TOGA

LOC BEFORE G/S

6

7

LVOR/LOC DEVN

R

10

11

BDATA BUS IRU−R−3

A

12

34

53

FRN IRS XFR−A

DME BITE TESTAFDS WARN

43

67

51

R/A FLAG

NAV SELF TESTILS TEST INHIBIT

D1791A

DNG/S DEVN

UP

LORADIO ALTITUDE

HI

1

1

6

7

58

BDATA BUS IRU−L−3

A

9

D1791B

8 BDATA BUS FMC−1

A

26

D1793A

25 BDATA BUS DAA−L−2

A

54 DME HOLD

D1793B

67 26V AC IN LNAV REF

2

6

LOLNAV STRG CMD

HI

30

34

35

36

39

42

51

52

LVOR/LOC DEVN

R

VOR/LOC SUPERFLAG

1ADI BAR GRADIENT

2

AUTO/MANUAL TUNE

ADATA BUS ANCDU−2

B

FWD LOC ANTENNA SELECT

LOCAL IRS XFR

D4317P

1

J

3

5

7

9

11

13

15

17

2

4

6

8

12

14

16

XA1

XA5

E1−3 SHELF

W069

34−31−05

34−33−11

34−31−08

34−26−13

34−31−04

34−26−23

34−33−11

34−31−09

34−61−02

34−61−05

34−31−04

34−26−12

34−31−08

34−26−12

34−31−08

34−31−02

NOT USED

NOT USED

NOT USED

NOT USED

GDX22−DC

GDX22−DC

P7 GLARESHIELD PANEL

M198DFCS MODE CONTROL PANEL

27

D1815

26

29

34−31−11

49

31

50

30

51

27

D299

34−31−11

26

29

30

31

49

50

51

15

1433−11−31

D301

6LCD TEST 33−18−05

RESOLVER

GND

5V ACLIGHTING

731−20

738−20

725−20

729−20

727−20

730−20

753−20

726−20

735−20

733−20

796−20

736−20

732−20

734−20

728−20

W011−013−20

W011−003−20

3110

NOTES:UNLESS OTHERWISE SPECIFIED, ALL REFERENCE DESIGNATIONS ARE PREFIXED 3343−.UNLESS OTHERWISE SPECIFIED, ALL WAYCODES ARE W9.PIN LOCATIONS SUFFIXED BY (−) DENOTES LOWER CASE LETTERS.THE FOLLOWING ENGINEERING DRAWINGS WERE USED: 83340200/T/2, 83340204/A/2, 82430054/G/4 AND AL344−1264.INDICATES PROTECTIVE TUBING.

18 W011−800−20

739−20

37 SPD/ALT INTERVENTION

XB1

Z3

XC2

Z4

XD5

Z9

GD701−DC

GD701−DC

GD701−DC

T1015STA 314.5WL 182.5LBL 19.2

M923FLIGHT CONTROL COMPUTER "B"

W069−737−20

D1655A

2

18

19

22STD OPT ILS DEVN WARN

25

BIT 1

26

D1661A

D1661B

44

61

STD OPT ALT ALERT

CONFIG PINS

G/S SUPERFLAG

2

D1655B

28

30

32

35

44

62

27

29

33

42

57

BIT 2

STD OPT AIRSPEED WARNSTD OPT CWS WARN

STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO

STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL

STD OPT ODD PARITYSTD OPT EFIS

STD OPT DUAL CHANNELAUTO F/D TOGA

LOC BEFORE G/S

6

7

LVOR/LOC DEVN

R

10

11

BDATA BUS IRU−L−3

A

12

34

FRN IRS XFR−A

AFDS WARN

43

67

51

R/A FLAG

NAV SELF TESTILS TEST INHIBIT

D1657A

DNG/S DEVN

UP

LORADIO ALTITUDE

HI

1

1

6

7

58

BDATA BUS IRU−R−3

A

9

D1657B

8BDATA BUS FMC−1

A

26

D1659A

25BDATA BUS DAA−R−2

A

54DME HOLD

D1659B

6726V AC IN LNAV REF

2

6

LOLNAV STRG CMD

HI

30

34

35

36

39

42

51

52

LVOR/LOC DEVN

R

VOR/LOC SUPERFLAG

1ADI BAR GRADIENT

2

AUTO/MANUAL TUNE

ADATA BUS ANCDU−2

B

FWD LOC ANTENNA SELECT

LOCAL IRS XFR

D4117P

32

J

34

36

38

40

42

44

46

48

33

34

37

39

43

45

47

34−31−05

34−33−21

34−31−08

34−26−23

34−31−04

34−26−13

34−33−21

34−31−09

34−61−02

34−61−06

34−31−04

34−26−12

34−31−08

34−26−12

34−31−08

NOT USED

NOT USED

NOT USED

NOT USED

GDX6−DC

GDX6−DC

731−20

738−20

725−20

729−20

727−20

730−20

753−20

726−20

735−20

733−20

796−20

736−20

732−20

734−20

728−20

W069−011−20

W069−009−20

31 41

49W069−800−20

739−20

37SPD/ALT INTERVENTION

34−55−41 53DME BITE TEST 34−55−51

W373−032−22

033−22

034−22

035−22

036−22

037−22

038−22

039−22

040−22

041−22

042−22

043−22

044−22

045−22

046−22

047−22

W373−049−22

048−22

W737−071−22

072−22

073−22

074−22

075−22

076−22

077−22

078−22

079−22

080−22

081−22

082−22

083−22

084−22

085−22

086−22

W737−088−22

087−22

062−20

W737−061−20

W737−063−20

XA1

XA5

XB1

Z3

XC2

Z4

XD5

Z9

GD701−DC

GD701−DC

GD701−DC

T1017STA 314.5WL 182.5LBL 19.2

062−20

W373−061−20

W373−063−20

CHAPTER

COMMUNICATIONS


PV284

SELCAL 23-22-01 INCORPORATES: 23-22-01 AERODEC MOD 0935

Page 1 Page 1

APR 01/11 APR 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

23-27-12

23-25-15

H12

4

4

4

HF-1 ANN LT

HF-1 ANN LT

HF-1 ANN LT

ANN LT CH 4

034-24

133-24

27

27

48

135-24

C7052-24

026-24

014-24

138-24

17

SM27

037-24 12 8305-24

017-24

23-27-11

1

4

56

7891011

12136

P D8963J

P D4287J

12

23-27-11

23-27-11

22-11011-85-42

8051-228050-22

8059-228056-22

8069-22

ELEX PWR-128V DC

FLT GND CALL

13C58 SELCAL

006-22

W089

J D4047P

STA 254DISC.

P18-2 ELECTRONI C LOAD CIRCUIT BREAKER PANEL

P18 LOAD CONTRO L CENTE R - LEFT

OVHD PANEL

CABIN ATTVHF-3 ACARS

LAMP TEST CONT

VHF-2 ANN LT

VHF-1 ANN LTVHF-3 ANN LT

671315

31

2

D141

STA 267DISC.

4

P D4212J

STA 254DISC.

23

P D4033J

W036562-24

STA 200 WL 209.30 RBL 9.06AURAL WRN UNIT MDL

P5

P8-53PANELOBS AUDIO SEL

68

D940

6

D4157J P

31-26-01W246-031-22

W329-011-24

CHIMESHI LO

M315

33-18-04

6

D131

6713152

13

D135

P8-6SEL PANELCAPT AUDIO

P8-7SEL PANELF/O AUDIO

P8

VHF-2 ANN LT

VHF-1 ANN LT

VHF-3 ANN LT

LAMP TEST CONT

FLT GND ANTCABIN ATT

VHF-3 ACARS

FLT GND CALLCABIN ATT

VHF-3 ACARSLAMP TEST CONTVHF-2 ANN LT

VHF-1 ANN LTVHF-3 ANN LT

2

3

1

PD4153J

19

SM26

618

SM24

17

1625

D4155J P

D4331J P

23-42-01

008-24

23-42-01

33-18-04

23-42-01

33-18-04

15137

SM25

P

P

D4285J

D4461J

ANN LT CH 1

ANN LT CH 3

D2555B

SM144 HI

LOCHASSIS GND

2

34

D2555C

28V DC2

D4151J P

W00722-250822-5508

GDX10-DC

D4703J P

17

16

25

A13

B13

A13B13

A13B13

D201B

D539B

D199B

SM30

SM31

SM136

SM138

23-27-1223-27-1223-27-1223-27-12

23-27-12

23-12-1123-12-31

M411 VHF COMM-3 XCVR


HI

LO

HILO

OUTPUTAUDIOSELCAL

OUTPUTAUDIOSELCAL


HILOOUTPUT

AUDIOSELCAL

R454WRN RELAYSELCAL AURAL

W175-

W327-

20

016-24W327-

W015

109-24

150-24054-24

055-24

W323-024-24

023-24

025-24W323-

W319- 031-24

032-24033-24W319-

072-24

071-24

073-24

136-24

076-24137-24

E2-1 ELECTRONI C SHELF

42

25

40

41

49

50

065-24

19383951

23-11-11

131-24

132-24

229-24R

230-24B

127-24

128-24

281-24R282-24B203-24R204-24B040-24

W189- 050-24

051-24

233-24R

234-24B

053-24

054-24

GD173-S201-24R202-24B231-24R232-24B

CIRCUI T INT OUT

W189-

RSV

227-24R

W191- 034-24

6153

A2

X1X2

A1

D2775

D2775

089-22

090-22088-22

SM29 097-22

23-12-21 SM137

228-24B

017-24042-24

297-24R298-24B

W191- 024-22

022-22

GD167-S

026-24032-24

034-24

201-24R202-24B219-24R220-24B

2

3

1J12

D2501A

K12

D2501AM1353

ELEX UNITREMOTE

107-24

4

56789

B4

B1A7

A3B3B8C8A2

A8

GND RESET CH 2ANN LT CH 2

CIRCUI T INT ININD LT INPUTHILOHI

8066-22

8065-22

8215-24R8216-24B8213-24R8214-24B

D4705J P

GDX10-DCA4

CH 4

8064-228054-22

LOGND RESET CH 5

CH 2

CH 5

E1-2 ELECTRONI C SHELF

M25 SELCAL DECODER

8057-24

8070-24

IHR42-7128

LO

GND RESET CH 1

GND RESET CH 3

HILOHILOGND RESET CH 4

D6

B7

A5

B5

A1

C1

B2C2A6B6D1

CH 3

CH 1

8218-24B

8072-24

8058-24

8207-24R8208-24B8203-24R8204-24B8073-24

1

2

3

4

5

6

7891011

GD173-S

GD167-S

GD173-S

ELECTRONI C PNLNOTES:

1

1 CAP AND STOW


PV284

COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0869

Page 1 Page 1 Sheet 1 Sheet 1


AG

M S

ER

VIC

ES

DR

AW

ING

: A

GM

10-

B7

3W-0

137


PV284

COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0869

Page 1 Page 1 Sheet 2 Sheet 2


AG

M S

ER

VIC

ES

DR

AW

ING

: A

GM

10-

B7

3W-0

137

CHAPTER

EQUIPMENT/

FURNISHINGS


PV281

SELL COMPONENT MAINTENANCE MANUAL

P/N 1003C11A00000

25-00-18 INCORPORATES: 25-00-18 AERODEC MOD 1021 Page 115/116 Page 115/116

OCT 01/13 OCT 01/13

Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

Note: This Drawing relates to Pages 115/116 of Sell CMM 25-00-18 for P/No. 1003C11A00000

D

11H001A10 A

C

B

AAC POWER SUPPLY A115/200 VAC, 400 HZ

D101P.1

NOTE: FOR TERMINAL LUGS REFER TO FIGURE 102

FIGURE 108 − UNIT G1 −

1

3

AC NEUTRAL

CASE GROUND

B

C

AC NEUTRAL

2

1

3

D102P.2

BRT

PWR

DIM

C102

2A1

2B1

2C115 A

BOILER

A

B

C

F

G

D

E

D104P

1

2

4

5

3

D105P.4

L101

WORK LIGHTBRUCEBR9172−563

BOILERINVENTUM (DR40)

C103

211 A

WORK LIGHT

1

SHUTOFF

VALVE

3GD01

GD02

GD03

WATER TAPGD06

33

GD05

GD04

GD0911H027A6C 3

S101

2

1

3

5

4

6

BRT

DIM

OFF

S102

2

1

3

5

4

6

BRT

DIM

OFF

1

1

2

3

M101

BALLASTBRUCE03344−107

4

5

6

7

3

1

TB03TB04

GALLEYAREA LIGHTS

1

2

TB01TB02

1 1

3

GD12 SP01

SP02

3

1

WIRE SPEC:

BMS 13+31 AWG

BMS 13+58 AWG

P101

11H002A10 B

11H003A10 C

11H004A10 N

11H005A4 N

11H006A4 N

11H012A10 C

11H011A10 B

11H010A10 A

11H005A22

11H006A22

11H007A22

11H034A16A

11H035A16B

11H036A16C

11H046A16N

11H038A16N

11H039A10N 16

1611H040A10N

11H024A4N

A1

1

6

2

3

4

511H024A20N

11H023A20N

11H021A20C

11H044A20

11H041A20

11H042A20

11H043A20

11H045A20N

11H022A20C

11H016A20C

11H017A20N

11H010A22

11H019A22

11H013A10 C

11H031A16N

11H037A16N

11H023A20N

11H046A16N

11H038A16N

11H017A20N

11H046A16N

11H005A4N

11H0245A20N

11H027A4N

11H046A4N

11H026A4N

11H028A4N

C9001

A2A14 A

HOT JUG11H9004A10A 11H9001A20A 1

2

3

D9001J

HOT JUGJF003001DRIESSEN

1 11H9002A18NGD10 GD11

GD14

GD13

GD15

WTR FLTR

DRIP PAN

3 11H025A4N

11H014A4N

11H020A4N

11H015A4N

11H047A4N

11H048A4N

GD08 SINK

GD07 WORK PLATE

11H9003A18N

CHAPTER

INDICATING/ RECORDING

SYSTEM


PV284

DFDRS INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 0952

Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

454

P18−2

4

8

13

2.5C109 FLT REC AC

12115V AC

ELEX PWR−1 24−58−11

053−22

2.5

C468

1228V DC

BATT. BUS24−58−11

W089−110−22

2.5

C544 POS SENSORS

1226V AC XFR

NO.224−58−11

127−22

W029

D4100PJ

D4397PJ

D4395PJ

8

W089−199−22FLT REC DC

ELECTRONIC LOAD CIRCUIT BREAKER PANEL

P18 LOAD CONTROL CENTRE − LEFT

STA 254DISC.

W105−008−22

W109−013−22

W047−032−22

W047−033−22

7

W047

1

D8945JP

STA 178DISC.

2

SM4 516−22

517−22

515−2210

11518−22

W419−001−22

008−22

005−22

20519−22 020−24

23058−22 023−24

22035−22 022−24

9252−24B 220−22B

4T230

18

11

251−24R 219−22R

15520−24 007−242

12 015−24NOT USED

8

32254−24B

253−24R 31

34

33

35

14 014−24NOT USED

228−24B

227−24R

225−24R

226−24B

4 213−24R

214−24B5

3

6

D483

034−22

19

20

23

22

P5−19 FLIGHT RCRDR AND MACH AIRSPEED PNL

P5 OVERHEAD PANEL

5

3

2

1

FLT RCDRTEST SWITCH

L1 FLIGHT RECORDER LIGHT

1

4

3

2

33−18−04

33−18−04

33−18−16

030−22

W419−003−24

M9009 MICRO QARD1637

1

2

11

3

5

4

9

8

10

6 W419−9001−20

W419−010−20 GD128−DC

A

A

PD8987J

1

2

3

4

5

7

8

9

6

17

18

19

20

PD5955J

3

PD4101J

3 501−22

502−24

503−24

504−24

505−24

W017

522−24

519−24

508−24

633−24R

633−24B

619−24R

620−24B

SM536 014−22

013−22

31−31−31

SM503

SM504

31−31−35

518−24

512−24 1

D2295C

7

H

C

115V AC

M675 DIGITAL FLIGHT DATA

513−20GDX22−AC

16 16

J9

D2295A

K9

A

B

DFDR PLAY OUT

10

182−22GDX21−S

A11

D2295A

A9

B9

A

B

BITE OUT

DIGITAL INPUT

609−24R

610−24B

SM534

SM535

SM533

625−24R

626−24B

J11

K11

A

B

PLAYBACK IN

611−24R

612−24B

183−22 GDX21−S

B11MAINT FLAG

J15DIGITAL GND

K15ANALOGUE GND

515−24

516−22

517−22 GDX23−DC

D2295E

J15

D2295D

K15

DIGITAL GND

CHASSIS GND

H1

510−22

511−22GDX23−DC

H2

A

BACARS DATA IN

H3

H4

A

B

ACARS DATA OUT

23−27−12

ACQUISITION UNIT

21

22

24

26

27

25

28

29

SM545 509−24

R263 FDAUD1805

X2

X1

A2

A3

STATUS RLY

514−24

520−22GDX23−DC

507−24 SM539

31−31−03

A1

506−24

D1805062−24 SM517

31−31−52

31−31−55

23

W419−021−22

019−22

209−24R

210−24B

215−22R

216−22B

017−20

E2−2 ELECTRONIC SHELF

21

D8987JP D183AM96 DIGITAL FLIGHT

STATUS

22 MAINT FLAG

GD815−S

9

10

A

B

PLAYBACK

7

8

A

B

DIGITAL INPUT

011−22 23 28V DC

029−22 1 115V AC H

002−20 2 115V AC L

6 CHASSIS GNDW419−006−20

GD391−AC

GD393−DC

28

D8997JP

27

E3−2 ELECTRONIC SHELF

M528 ENG ACC UNIT

D1458A

41

28

ENG NO. 1

D1458B

41

28

ENG NO. 2

8361−24

8362−24

8359−24

8360−24 SM160

SM162

8327−24

8328−24

8363−24

8364−24

27

D8909JP

28

24

D5212JP

5

W409−027−24

W409−028−24

W2016−017−24

W2016−054−24

32

33

D2596

GND

A3

A2

A1

AIR

E11 LDG GEAR LOGIC SHELF

R277 GND SENSINGRELAY

DATA RECORDER

31−31−51

31−31−0331−31−03

CHAPTER

LIGHTS

B737-300/400/500 AIRCRAFT WIRING MANUAL

PV284

MAP, FLIGHT KIT AND READING LIGHTS 33-17-01 INCORPORATES: 33-17-01 AERODEC MOD 0968

Page 1 Page 1


6

6

GD596-AC 114-20W234-

GD316-AC 100-20W238-

32

1

32

1

D2492

A-E

5

SP722

807-24

D4036JP

20

PD4238J

7

004-24

004-22

SM4

SM3

GD100J-AC

W5007

002-24

E-A

3

D798

35

D796

4

CONTROL CABIN LIGHTING, FUEL SYSTEM AND MISCELLANEOUSP6-3

036-24

G-G

OBSERVERS READING LIGHT

WHT

XFR BUS-128V AC

W044

3 W238-24-53-312 1

804-24

W234-

W234-

D4060P

STA 259DISC.

W238-

C308

KIT LIGHTSFLIGHTMAP AND

073-24 SM91 533-24

844-24

2 13C309

STA 219, WL 224, RBL 36FIRST OFFICER S FLIGHT KIT LIGHT

XFR BUS-228V AC

24-53-41

BLK RW

L12READING LIGHTFIRST OBSERVERS

P6 LOAD CONTROL CENTER - RIGHT

DISC.

19

DISC.572ATS462ATS

W036W98-24 W234-014-24

W97-24

P5 OVERHEAD PANEL

SP188

SP186

GD610-AC=G =P

W

L9MAP LIGHTFIRST OFFICERS

-632W287PS 806PS004-205

D798

P23-1

GD190-ACG=P= R

W

L11

W238-

J

P21-1

SP606=P =G

W

L8MAP LIGHTCAPTAINS

G=P=GD1444-AC

D2458

G-A

L10STA 219, WL 224, LBL 36CAPTAIN S FLIGHT KIT LIGHT

RW

W234-C-P W234-C-G

W238-G-B

A-D-632W -632W

GD600-AC

070-24

W234-

STA 254, WL 265SECOND OBSERVERS READING LIGHT

G-P

4

F/O MAP LT DIMMER

W238-003-20

MAP LIGHT MODULE

D796

2

P10 FIRST OBSERVERS PANEL

W234-

011-22

CAPT MAP LT DIMMER

MAP LIGHT MODULE

010-20

(R505)

(R504)

E-D

W234-015-24

G=P=GD604-AC

RW

W234-B-P W234-B-G

L13

CHAPTER

NAVIGATION


PV284

EFIS POWER/PROGRAM PIN - LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 0864

Page 1 Page 1



PV284

EFIS POWER/PROGRAM PIN - RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 0864

Page 1 Page 1



PV284

GROUND PROXIMTY WARNING 34-49-04 INCORPORATES: 34-49-04 AERODEC MOD 0862

Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

329

C8ALTITUDE CALLOUT ENABLE

B15TERRAIN DISPLAY TYPE

D1153B

A3PPCOM (PROGRAMME PIN COMMON)

W021−501−24

W021−507−22

W9021−050−22

W021−518−24

GDX10−DC

SM1153

B10PPCNF2

A10PPCNF1

D1153A

W9021−047−22

W9021−048−22

W9021−076−22C10PPCNF3

W021−517−24

AIRCRAFT TYPE SELECT

D6PPCNF17 (PROGRAMME PIN PARITY)

B5PPCNF12 (WINDSHEAR CONTROL) W9021−069−22

C4PPCNF11 (AUDIO DECLUTTER / VOLUME)

W9021−054−22

W9021−053−22

W9021−049−22

W9021−052−22

SM505

34−49−03

D4PPCNF4

B4PPCNF5

A8PPCNF6

ALTITUDE CALLOUT MENU

D1153B

C2PPCNF9 (2 ILS / 2 LRRA / 3 LRRA)

B5PPCNF13 (TCF / TAD / SIM REPO)

D15GLIDESLOPE CANCEL OUTPUT

W9021−051−22 SP9009

C12DISCRETE OUTPUT 4 (WINDSHEAR CAUTION)

B12DISCRETE OUTPUT 6 (AUDIO ON)

D1153A

C2PPCNF14 (BANK ANGLE)

W9021−058−22

W9021−077−22 SM9025

W9021−061−22

W9021−060−22

W9021−059−22 SM9026

M652 ENHANCED GROUND PROXIMITY COMPUTER

E2−4 SHELF

34−49−03

W021−704−24

34−45−02

W021−8199−24 SM1151

W021−543−24

W021−506−24

34−49−03

A5PPCNF8 (AUDIO MENU) W9021−079−22 SM506

D14PPCNF7 (OPTIONAL GPS) W9021−055−22

B7DISCRETE OUTPUT 3 (PULL−UP WARNING) W021−511−2234−49−03

34−45−02


PV284

ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

403

E3

D149B

875−24MODE S ADDRESS BIT COMMON

D3 874−24BIT 24

C3 873−24BIT 23

B3 872−24BIT 22

A3 871−24BIT 21

K2 870−24BIT 20

J2 869−24BIT 19

H2 868−24BIT 18

G2 867−24BIT 17

F2 866−24BIT 16

E2 865−24BIT 15

D2 864−24BIT 14

C2 863−24BIT 13

B2 862−24BIT 12

A2 861−24BIT 11

K1 860−24BIT 10

J1 859−24BIT 9

H1 858−24BIT 8

G1 857−24BIT 7

F1 856−24BIT 6

E1 855−24BIT 5

D1 854−24BIT 4

C1 853−24BIT 3

B1 852−24BIT 2

A1 851−24BIT 1

J5 850−24ANT BITE PROGRAM

MODE S ADDRESS

C5

D149A

877−24MAX TAS PROGRAMME

D5 876−24PROGRAMME COMMON

SM800

W017

M1469D2681

25

24

23

22

21

20

19

18

17

16

15

14

13

12

11

10

9

8

7

6

5

4

3

2

1

E2−2

1.

SHORTING RECEPTACLE

ELECTRONIC SHELF

M163 ATC−1 TRANSPONDER (MP)

(TP)

A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3

MODE S CODE

ADDRESS BIT

REGISTRY OCTAL

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24

AIRPLANE

D149B AND D2681

1.

OO−TNP 21150720PV284 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 1 0 0 00

1.NOTES:

FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D149B AND D2681


PV284

ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

403

E3

D155B

875−24MODE S ADDRESS BIT COMMON

D3 874−24BIT 24

C3 873−24BIT 23

B3 872−24BIT 22

A3 871−24BIT 21

K2 870−24BIT 20

J2 869−24BIT 19

H2 868−24BIT 18

G2 867−24BIT 17

F2 866−24BIT 16

E2 865−24BIT 15

D2 864−24BIT 14

C2 863−24BIT 13

B2 862−24BIT 12

A2 861−24BIT 11

K1 860−24BIT 10

J1 859−24BIT 9

H1 858−24BIT 8

G1 857−24BIT 7

F1 856−24BIT 6

E1 855−24BIT 5

D1 854−24BIT 4

C1 853−24BIT 3

B1 852−24BIT 2

A1 851−24BIT 1

J5 850−24ANT BITE PROGRAM

MODE S ADDRESS

C5

D155A

877−24MAX TAS PROGRAMME

D5 876−24PROGRAMME COMMON

SM800

W087

M1470D2683

25

24

23

22

21

20

19

18

17

16

15

14

13

12

11

10

9

8

7

6

5

4

3

2

1

E2−4

1.

SHORTING RECEPTACLE

ELECTRONIC SHELF

M381 ATC−2 TRANSPONDER (MP)

(TP)

A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3

MODE S CODE

ADDRESS BIT

REGISTRY OCTAL

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24

AIRPLANE

D155B AND D2683

1.

OO−TNP 21150720PV284 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 1 0 0 00

1.NOTES:

FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D155B AND D2683


PV284

FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS


Page 1 Page 1


A

ER

OD

EC

DR

AW

ING

: A

L34

6-12

90

F11

E11

C11

D11

G11

H11

CAA FLT RULES

AIR FRAME / ENG CODE

C13

D10

F10

F12

F14

F15

G10

B13

H12

J10

K15

H10

C10

D2179BM1175 FMC NO.1

DEGGREES F DEFAULT

VOR INHIBIT

TAKEOFF SPEED

ASPIRATED TAT PROBE

PERFORMANCE OPTION

FLT NUMBER ENTRY

KILOGRAM OPTION

TAKEOFF PROFILE

RUNWAY POSITION UPDATE

NON AGILITY DME TYPE

NAV AID SUPPRESSION ON EFIS

SELECTED COURSE INHIBIT ON EFIS

8022−22

8021−22

8025−22

8026−22

8023−22

8024−22

8010−22

8002−22

8011−22

8012−22

8013−22

8014−22

8015−22

8016−22

8017−22

8018−22

8019−22

8007−22

8008−22

2

1

5

6

3

4

9

10

11

12

13

14

15

16

17

18

19

7

8

D6739P

E1−2 ELECTRONICS SHELF

J

W737−002−22

001−22

025−22

026−22

023−22

024−22

049−22

050−22

051−22

052−22

053−22

054−22

055−22

056−22

057−22

058−22

059−22

047−22

XB1

XA1

XC1

XC2

XB2

XA2

XA6

XB6

Z11

Z12

XA8

XC8

XD5

T1013STA 314.5LBL 19.2WL 182.5

W737−003−22WK

028−22WO GD127−S

W737−027−22WV

GD127−SW737−065−22

GD127−SW737−066−22

B10FAA / CAA QRH SPEEDS 8320−22 20 W737−020−22

048−22

XD8

W007

ILLUSTRATED

PARTS

CATALOGUE

Contents

IPC-CONTENTS Page 1


®





23-71-13-01Z – MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY)



25-11-11-18Z – SEAT INSTL – SECOND OBSERVER

25-11-11-66Z – ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)

25-11-21-22Z – PANEL INSTL – LINING STA 261 TO STA 269

25-31-11-99Z – HOT CUP INSTL – GALLEY 1



Chapter 28 FUEL




31-24-11-01Z – FLIGHT RECORDER INSTL – AFT REMOVAL

31-24-22-01Z – EQUIP INSTL – ELECT. RACKS (DIGITAL FLIGHT DATA ACQUISITION UNIT ONLY)

31-24-24-99Z – EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY)


Chapter 33 LIGHTS

33-11-00-05Z – LIGHT INSTL – CONT CAB CREW


34-28-31-02Z – EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY)

34-62-21-04Z – EQUIPMENT AND SOFTWARE INSTL – ELECT. RACKS (FMCS ONLY)

IPC-CONTENTS Page 2


®

Chapter 35 OXYGEN

35-12-00-02Z – OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY)

35-12-00-20Z – OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)




Chapter 52 DOORS

Chapter 53 FUSELAGE



Chapter 56 WINDOWS

Chapter 57 WINGS



Chapter 74 IGNITION

Chapter 75 AIR


Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

CHAPTER

COMMUNICATIONS

B737-300/400/500 ILLUSTRATED PARTS CATALOGUE

23-71-13-01Z 23-71-13 MOD 0869 Fig 1Z APR 01/11 Page 0

Page produced by Aerospace Design and Engineering Consultants (AeroDEC) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY) Figure 1Z




FIG ITEM PART NUMBER NOMENCLATURE EFF

CODE UNITS PER

ASSY 1234567

1Z --1 AGM10-B73E-0137 CVR SWITCH INSTALLATION 404404 RF

10 233A3211-1 • MODULE – COCKPIT VOICE RECORDER 1--20 TDH8127-3003 • RELAY 1--30 BACR13CF2AB • RELAY 1

-- ITEMS NOT ILLUSTRATED

CHAPTER

EQUIPMENT/

FURNISHINGS




SEAT INSTL – SECOND OBSERVER FIGURE 18Z





CODE UNITS PER

ASSY 1234567

18Z --1 AGMIS10-B73E-0145 SECOND OBSERVER STATION INSTALLATION 404404 RF

10 11-007-1 • SEAT ASSY 1--20 65-76688-3 • FILLER 1--30 69-43995-1 • LOOP STRAP 1--40 69-44684-1 • SHIM 1--50 65-46836-2 • VELCRO 1





ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 66Z





CODE UNITS PER

ASSY 1234567

66Z --1 AGMIS10-B73E-0145 SECOND OBSERVERS STATION INSTL 404404 RF

10 69-44447-2 • ASHTRAY ASSY 120 69-43944-1 • BRACKET ASSY 130 69-44458-3 • SUPPORT ASSY 140 BACS40R05C05F • SHIM - LAMINATED 250 26S55-5AB • STUD 2





PANEL INSTL – LINING STA 261 TO STA 269 FIGURE 22Z





CODE UNITS PER

ASSY 1234567

22Z --1 AGMIS10-B73E-0145 SECOND OBSERVER STATION INSTALLATION 404404 RF

10 69-45405-20 • PANEL – LINING 120 69-45405-21 • PANEL – LINING 1

ATTACHING PARTS --30 SFSW10F8DL26GY • SCREW 14

- - - - - - - - - * - - - - - - - - - -



25-31-11-99Z 25-31-11 MOD-1021 Fig 99Z OCT 01/13 Page 0


HOT CUP INSTL – GALLEY 1 Figure 99Z


25-31-11-99Z 25-31-11 MOD-1021 Fig 99Z OCT 01/13 Page 1



CODE UNITS PER

ASSY 1234567

99Z --1 MEO-1021-001 INTRODUCTION OF DRIESSEN COMBO ASSY ON GALLEY G1A 404404 RF --1 AL253-1576 INSTALLATION OF DREISSEN COMBO ASSY (AERODEC DRAWING) 404404 RF

10 JF003001 • COMBO ASSY – HOT CUP 1

SEE DRIESSEN CMM 25-26-33 50 34-00318 • BRACKET ASSY 160 AL253-0247-001 • BRACKET CONNECTOR 170 9-028-13 • SCREW 2

--80 NAS1836-3-22 • INSERT 490 NAS514P1032-6 • SCREW 2100 NAS1149D0332J • WASHER 4110 NAS603-6 • SCREW 4

--120 NAS1149D0363J • WASHER 8140 NAS43DD1-10FC • SPACER 4160 NAS514P632-12 • SCREW 4170 NAS1149D0616J • WASHER 4180 MS35649-262 • NUT 4190 AC16707 • CONNECTOR 1210 AL113-0248-001 • PLACARD – USER INSTRUCTIONS 1220 AN935-6 • WASHER 4

--230 NAS514P1032-18 • SCREW 4--240 AL253-1580-001 • ADAPTER PANEL 1--260 TC342A-X • CLIP 1


CHAPTER


SYSTEM




EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY) FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 MEO-0952-001 INSTALLATION OF A MINI QUICK ACCESS RECORDER 404404 RF

10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1





FLIGHT RECORDER INSTL – AFT REMOVAL FIGURE 1Z





CODE UNITS PER

ASSY 1234567

3Z --1 AGM10-B73E-0035 FDAM/FDR REPLACEMENT 404404 RF

10 980-4700-042 • RECORDER – FLIGHT DATA 1 (ALT PART NOS.: 980-4700-001, 980-4700-003)





EQUIPMENT INSTL – ELECT. RACKS (DIGITAL FLIGHT DATA ACQUISITION UNIT ONLY) FIGURE 1Z





CODE UNITS PER

ASSY 1234567

3Z --1 AGM10-B73E-0035 FDAM/FDR REPLACEMENT 404404 RF

10 967-0212-002 • UNIT – DIGITAL FLIGHT DATA ACQUISITION 1


CHAPTER

LIGHTS




LIGHT INSTL – CONT CAB CREW Figure 5Z





CODE UNITS PER

ASSY 1234567

5Z --1 AGMIS10-B73E-0145 SECOND OBSERVER’S STATION INSTL 404404 RF

10 34265-8 • LIGHT ASSY 120 65-45757-5 • BRACKET 1


CHAPTER

NAVIGATION




EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY) FIGURE 2Z





CODE UNITS PER

ASSY 1234567

3Z --1 AGM10-B73E-0033 IRS 2005 MAGNETIC VARIATION TABLE ACTIVATION 404404 RF

10 S242T101-117 • UNIT – INERTIAL REFERENCE 2 NOTE: EXISTING IRU PART NO. S242T101-107, WILL BECOME S242T101-117 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AD-34-0027 PER BOEING SERVICE LETTER 737-SL-34-177





EQUIPMENT AND SOFTWARE INSTL – ELECT RACKS (FMCS ONLY) FIGURE 4Z





CODE UNITS PER

ASSY 1234567

2Z --1 AGM10-B73E-0036 INSTL OF 4 MCU FLIGHT MANAGEMENT COMPUTER 404404 RF

10 171497-05-01 • COMPUTER – FLIGHT MANAGEMENT (ALT NO: 176200-01-01) 1--20 66-14144-2 • SEAL TRAY 1--30 10-62225-1013 • OPS SOFTWARE (ALT NO: 549849-014) 1--40 443200-001 • MOD KIT – 8MCU TO 4MCU ADAPTER 1


CHAPTER

OXYGEN




OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 2Z (SHEET 1 OF 2)





CODE UNITS PER

ASSY 1234567


10 801307-00 • OXYGEN CYLINDER ASSY 120 69-46296-7 • BRACKET 130 65-53541-364 • TUBE ASSY 140 65-53541-397 • TUBE ASSY 150 65-53541-404 • TUBE ASSY 160 69-45719-1 • TUBE GUARD 1

--70 AN924-5D • TUBE NUT 1--80 NAS1149DN832H • WASHER 2--90 BACC10DK5 • TUBE CLAMP 5--100 BACE21AW0505L • ELBOW 1--110 BACN10GH3-12 • SPACER PLATE 1--120 BACR15BB3D4 • RIVET 2--130 BACT16AZ050505L • TEE 1--140 MS21902D5 • UNION 1--150 MS21908D5 • ELBOW 1--160 NAS1801-3-9 • SCREW 1--170 NAS1801-3-15 • SCREW 1--180 NAS1801-3-17 • SCREW 1--190 NAS1801-3-25 • SCREW 2--200 NAS42DD-6-32 • SPACER 3--210 NAS42DD-6-40 • SPACER 2--220 NAS602-7P • SCREW 2





OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 20Z





CODE UNITS PER

ASSY 1234567


15 69-50982-12 • PANEL ASSY – SUPPORT 160 69-36613-2 • SHELF ASSY – OXY MASK 165 65-63685-5 • ANGLE 270 65-57439-3 • CLIP 275 69-50983-2 • ANGLE ASSY 180 69-50984-AGM1 • ANGLE ASSY 185 69-74512-AGM3 • BRACKET ASSY 193 69-50981-11 • CLOSURE PANEL ASSY 1105 69-45759-142 • FITTING ASSY 1

--110 AN960PD10L • WASHER 7--120 BACN10JC3 • NUT 15--130 BACN10JR3F • NUTPLATE 2--140 BACR15BA3A6 • RIVET 4--150 BACR15BB4D4 • RIVET 2--160 BACR15BB6D6 • RIVET 2--170 BACW10X4 • RETAINING RING 2--180 NAS1801-3-11 • SCREW 2--190 NAS514P1032-6 • SCREW 6--200 NAS514P632-7 • SCREW 4--210 NAS601-5P • SCREW 2--220 NAS601-8P • SCREW 2--230 NAS603-10P • SCREW 2--240 NAS603-6P • SCREW 3--250 NAS603-8P • SCREW 2--260 66-23277-2 • INSULATION PLATE 1--270 66-3044-1 • HEADPHONE HOOK 1--280 MC10-25-104 • OXYGEN MASK 1--290 MXP105 • MASK STOWAGE CUP 1--300 MXP210-00 • SMOKE GOGGLES 1--310 SFSW10F8DL26GY • SCREW 14


AIRCRAFT

MAINTENANCE

MANUAL

Contents

AMM-CONTENTS Page 1


®




22-11-00– DIGITAL FLIGHT CONTROL SYSTEM

PAGE BLOCK 501 – ADJUSTMENT/TEST


23-71-00 – VOICE RECORDER SYSTEM




25-11-11 – FLIGHT COMPARTMENT EQUIPMENT

PAGE BLOCK 201 – MAINTENANCE PRACTICES



Chapter 28 FUEL




31-24-01 – FLIGHT DATA RECORDER SYSTEM

PAGE BLOCK 1 – DESCRIPTION AND OPERATION


31-24-22 – FLIGHT DATA ACQUISITION UNIT

PAGE BLOCK 601 – SERVICING

31-24-24 – QUICK ACCESS RECORDER (MINI)

PAGE BLOCK 201 – MAINTENANCE PRACTICES


Chapter 33 LIGHTS


34-22-00 – ELECTRONIC FLIGHT INSTRUMENT SYSTEM – EFIS DISPLAY MODES TEST


AMM-CONTENTS Page 2


®

34-49-03 – GROUND PROXIMITY WARNING SYSTEM


34-62-01 – FLIGHT MANAGEMENT COMPUTER SYSTEM – PROGRAM PIN VERIFICATION


Chapter 35 OXYGEN




Chapter 52 DOORS

Chapter 53 FUSELAGE



Chapter 56 WINDOWS

Chapter 57 WINGS



Chapter 74 IGNITION

Chapter 75 AIR


Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

CHAPTER

AUTO FLIGHT

B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL

EFFECTIVITY

22-11-01404 Page 501 MOD 1093 JAN 01/12


DIGITAL FLIGHT CONTROL SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry an Option Pin Check of the Digital Flight Control System. The Option Pin Check is part of the System Test.

B. Any other test associated with the Digital Flight Control System in accordance with

22-11-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. System Test – DFCS – Option Pin Check Only

A. Location Zones

Zone Area

101 Control Cabin - Left 102 Control Cabin - Right

B. Prepare for the System Test

SUBTASK 22-11-01-845-129

(1) Do the preparation for the DFCS BITE test in this task: "Operational Test - Digital Flight Control System".

C. Option Pin Check

SUBTASK 22-11-01-745-020

(1) Do the Option Pin Check:

(a) Open the AFCS B FCC DC circuit breaker on P6-2 Circuit Breaker Panel.

(b) [If POST SB 737-34-1593] Set the FMC transfer switch to NORMAL position.

(c) Push the INIT/REF key on the CDU keyboard to show the POS INIT page or PERF INIT page.

(d) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page.

(e) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page.

(f) Push the LSK adjacent to <DFCS to show the DFCS BITE TEST LINE MAINT

1/2 page.

(g) [If POST SB 737-34-1593] Ignore the message "MOVE FMC TRANSFER SWITCH TO BOTH ON L" shows on the CDU and keep the position of the FMC transfer switch in the NORMAL position.

(h) Stop for approximately 15 seconds.

(i) Push the LSK adjacent to <PUSH IF NO RESPONSE.

(j) Push the LSK adjacent to <CONTINUE.


EFFECTIVITY

22-11-01404 Page 502 MOD 1093 JAN 01/12


(k) Push the NEXT PAGE key on the CDU to show the DFCS BITE TEST OVERNIGHT MAINT 2/2 page.

(l) Push the LSK adjacent to <SENSOR VALUES to show the Sensor Values Test

Index page.

(m) Push the LSK adjacent to <OPTIONS (SOP) to show the first page of the standard options.

(n) Push the LSK adjacent to <CONTINUE to show the second page of the

standard options.

(o) For AERODEC MOD-1093, Make sure that the following options on Table 502 are displayed or not displayed on the CDU display.

Table 502

SOP – A/S WARNING NOT DISPLAYED

SOP – CWS WARN NOT DISPLAYED

SOP – WINGS LVL NOT DISPLAYED

SOP – CWS OV/RD NOT DISPLAYED

SOP – PARITY OPEN DISPLAYED

(p) Close the AFCS B FCC DC circuit breaker on the P6-2 Circuit Breaker

Panel.

(q) Open the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.

(2) Do the steps in the Option Pin Check again for the channel B.

(3) Close the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.

(4) Push the INIT/REF key on the CDU keyboard to get out of the BITE.

D. If required, continue testing in accordance with 22-11-01 Page Block 501 of the

appropriate AMM, or Put the Airplane Back to Its Initial Condition in accordance with 22-11-01 Page Block 501.

CHAPTER

COMMUNICATIONS


EFFECTIVITY

23-71-00AIRCRAFT WITH CVR SWITCH Page 501 MOD 0869 APR 01/13

Page produced by Aerospace Design and Engineering Consultants (AeroDECTM) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.


EFFECTIVITY




EFFECTIVITY



H. AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Voice Recorder AUTO/ON Switch Test

(1) TEST WITHOUT ENGINES RUNNING

NOTE: Additional relays are added to tum the CVR "on" when either engine is running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.

(a) Close all applicable circuit breakers to the CVR system.

(b) At the P5 overhead panel, at the cockpit voice recorder (CVR) control panel,

connect a 600 ohm headset to the CVR monitor jack.

(c) Make sure the CVR AUTO/ON switch is in the AUTO position.

(d) Make sure ambient cockpit audio is not heard over the headset. The CVR is OFF.

(e) On the CVR P5 control panel; AIRPLANES WITH VOICE RECORDER CONTROL PANEL

WITH METER; Make sure that the voice recorder control panel meter needle does not move while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light does not come on while you push the TEST switch.

(f) Make sure the CVR AUTO/ON switch is in the ON position.

(g) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(h) On the P5 control panel and make sure that; AIRPLANES WITH VOICE RECORDER

CONTROL PANEL WITH METER; Make sure that the voice recorder control panel meter needle moves and stays in the green area while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light comes on while you push the TEST switch.

(i) At the P18-2 panel, open circuit breaker (C9500) VOICE RECORDER RELAY.

(j) Make sure the CVR Auto/On switch automatically switches to the AUTO position.

(k) Make sure you cannot hear flight deck conversation in the headset. The CVR

is OFF.

(l) Close circuit breaker (C9500) VOICE RECORDER RELAY.


EFFECTIVITY



(2) TEST WITH ENGINES RUNNING

NOTE: Additional relays are added to tum the CVR "on" when either engine is

running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.

(a) Make sure the CVR AUTO/ON switch is in the AUTO position.

(b) Start No. 1 Engine Per AMM 71-00-00/201, ensure the No. 1 Eng N2 Gauge is

>46.33%.

(c) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(d) Shut down No.1 Eng Per AMM 71-00-00/201.

(e) Wait six minutes.

NOTE: The CVR switch circuit relay R9500 will tum the CVR off after five minutes.

(f) Make sure you cannot hear flight deck conversation in the headset. The CVR

is OFF.

(g) Start No. 2 Engine Per AMM 71-00-00/201, ensure the No. 2 Eng N2 Gauge is >46.33%.

(h) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(i) Shut down No.2 Eng Per AMM 71-00-00/201.

(j) Wait six minutes.

NOTE: The CVR switch circuit relay R9500 will turn the CVR off after five

minutes.

(k) Make sure you cannot hear flight deck conversation in the headset. The CVR is OFF.

I. Put the Airplane Back to the Usual Condition S 085-015 (1) Remove the headphone from the control panel.

S 865-036

(2) AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Set the voice recorder AUTO/ON switch to the AUTO position. S 865-016 (3) Remove electrical power if it is not necessary (AMM 24-22-00/201)

CHAPTER

EQUIPMENT/

FURNISHINGS


EFFECTIVITY

25-11-11AIRPLANES WITH SECOND OBSERVER’S SEAT Page 201 MOD 0968 APR 01/11



EFFECTIVITY



CHAPTER


SYSTEM


EFFECTIVITY

31-24-01AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU AND HONEYWELL FDR Page 1 MOD 0876 APR 01/11


E2-3


EFFECTIVITY



(E2-3)


EFFECTIVITY




EFFECTIVITY



FLIGHT DATA RECORDER SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry of a System Test of the Flight Data Recorder System. The System Test refer to other task which do tests of the inputs to the Flight Data Recorder System.

B. Any other test associated with the Flight Data Recorder System in accordance with

31-24-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. System Test – Flight Data Recorder System

A. General (1) The system test has procedures to do tests of the inputs to the flight data

recorder system. Tests can be accomplished out of sequence, and tests can also be accomplished independently.

(2) These tasks use the word SUBFRAME 0 to make a selection of a parameter which is on all four subframes. Some portable testers do not have a switch position for subframe 0. On these test sets, make a selection of subframes 1 thru 4 when the task uses subframe 0.

B. Location Zones

Zone Area 101 Control Cabin - Left 102 Control Cabin - Right

C. Prepare for Test

(1) References

Reference Title

24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)

(2) Tools/Equipment

Reference Description

981-6301-002 Data Signal Display Unit (DSDU) – Honeywell (A31007-32 Adapter Cable of -30 kit (without FDEP)) (A31007-35 Adapter Cable of -49 kit (with FDEP)) 2222786 Portable Tester - Teledyne (A31007-2 Adapter Cable of -1 kit) 2229738-X Portable Tester - Teledyne (A31007-60 Adapter Cable of -59 kit)

964-0446-001 Handheld Download Unit (HHDLU) - Honeywell

(704-2554-001 Adapter Cable)


EFFECTIVITY



(3) Location Zones

Zone Area


(4) Preparation Procedure

(a) Supply electrical power (AMM 24-22-00) (b) Make sure the engines are off, the airplane is in ground mode, and the

following circuit breakers on the P18 panel are open: FLT REC AC (C109) FLT REC DC (C468)

(c) Do this step only if using tester 1 through 3 listed above. Remove the

shorting plug from the system test plug on the P18 panel and connect the tester using the appropriate adapter cable.

NOTE: Only testers 1 through 3 listed above can be connected to this

system test plug.

(d) When tester 1 (Honeywell DSDU) is used, set the switches to the following positions:

Switch Position

POWER ON WORD As given in test SUBFRAME As given in test INPUT ARINC INPUT DATA DATA PARAMETER SYNC B OCTAL DISPLAY 12 BIT

(e) When tester 2 or 3 (TELEDYNE) is used, set the switches to the following

positions:

Switch Position

DATA 12 bit for 12 bit signals 10 bit for 10 bit signals or discretes

READOUT ACFT UPDATE AUTO SUBFRAME As given in test WORD As given in test

(f) Do this step if using tester 4 listed above (Honeywell HHDLU).

1) Attach the HHDLU interface cable to the test connector at the front side of the Solid State Flight Data Recorder (SSFDR).

NOTE: To get access to the SSFDR, open the aft lowered ceiling panel

No. 2 (AMM 25-21-71/401). The HHDLU is used on the Honeywell SSFDR only.


EFFECTIVITY



2) Once power is applied to the flight recorder, press and release the power button next to the input connector on the HHDLU. The HHDLU display will be inactive for approximately 30 seconds while the unit initializes. The Main Menu will then be displayed.

Note: The following steps can be performed with or without a memory

cartridge installed in the HHDLU.

3) On the HHDLU, press and release the DSDU key. The DSDU menu will be displayed. After initial synchronization, WORD 1 in base octal will be displayed on all three display lines. Press and release WRD 1. The word configuration menu will be displayed.

NOTE: In the following tests, the top line of the HHDLU display will

contain WRDI data, unless otherwise stated the test results refer to the top line of the display only. Data displayed in the lower lines can be ignored (WRDZ and WRD3).

4) The following steps will be necessary in subsequent procedures in order

to select a particular Subframe, Word and Numerical Base.

5) To cancel a modified character, press and release the EXIT key instead of the SEL key.

6) To carry out SUBFRAME SELECT, do the following procedure:

a) Press and release the SF key. The SUBFRAME SELECT menu will be displayed.

b) Press and release the left or right arrow keys until desired subframe number is displayed. The display scrolls down or up through subframes 1, 2, 3, 4 and ALL.

c) Press and release the SEL key. The HHDLU will accept the subframe selected and the word configuration menu will be displayed.

d) Press and release the WORD, BASE or EXIT key, as required. The WORD SELECT, BASE SELECT or DSDU menu will be displayed.

7) To carry out WORD SELECT, do the following procedure:

a) Press and release the WORD key. The WORD SELECT menu will be displayed.

b) Press and release the left or right arrow keys until the desired word is displayed. The HHDLU display scrolls down or up through the available words.

c) Press and release the SEL key. The HHDLU accept the word selected and the word configuration menu is displayed.

d) Press and release either the BASE or EXIT key, as required. The BASE SELECT or DSDU menu will be displayed.

8) To carry out BASE SELECTION, do the following procedure:

a) Press and release the BASE key. The BASE SELECT menu will be displayed.

b) Press and release either the BIN, OCT, DEC or HEX key to select binary, octal, decimal or hexadecimal base, as required. Asterisks (*) indicate current base selected. The word configuration menu will be displayed.

c) Press and release the EXIT key. The DSDU menu will be displayed.


EFFECTIVITY



(g) Several of the parameters to be tested are recorded in superframe format. This is a format that is used to store parameter data that changes infrequently. A superframe counter, recorder in WORD 64, SUBFRAME 1, BITS 1-4 is used for timing purposes to store and subsequently recover the parameter data. When using the HHDLU to display superframe data, use the second line of the HHDLU display (WRD 2) to display the superframe counter. When the counter value (binary value plus 1) matches the expected superframe cycle the next update of parameter data is valid.

(h) Put the Test - Normal Switch on the Flight Recorder Test Module to the

Test Position.

D. Procedure

(1) Supply electrical power (PAGEBLOCK 24-22-00/201).

(2) Make sure the engines are off.

(3) Sync Word Test

(a) On the tester, set the SUBFRAME to 1 and the WORD to 1. Make sure the tester display shows 1107.

(b) Repeat for each SUBFRAME and verify the correct values as shown below:

Subframe 2 - 2670 Subframe 3 - 5107 Subframe 4 - 6670

(4) Relative Time (Frame Count) Test

(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 64. Verify displayed

values increases by 1 count at 4-second intervals.

(5) Clock Signal (GMT) Test

(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 17.

(b) Set the captain's clock to 13 hours and 42 minutes.

(c) Set the GMT knob on the clock to the run position.

(d) Immediately make sure the tester display is 3324 or 3325.

(e) Set the clock to its usual condition.

(6) DADC Bus Signal Test

(a) References Reference Description AMM 34-12-01/501 Air Data System


EFFECTIVITY



(b) In this test it is necessary to put the DADC into the TEST mode. You can use one of three methods depending on the type of DADC installed on the airplane.

1) Airplanes with a test select switch on the DADC; Put the Test select

switch to the function position and push and hold the Test button.

2) Airplanes with a Test - History switch on the DADC; Put the Test - History switch to the Test position.

3) Airplanes with a Self-Test switch on the DADC; Put the Self- Test switch

to the Test position.

(c) Make sure the Air Data Computer System is serviceable (AMM 34-12-01/501)

(d) On the Tester, Set the SUBFRAME to 0 and the WORD to 33.

(e) Put the DADC No. 1 into Test Mode.

(f) Make sure the tester display is 4663 to 4775.

(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 8.

(h) Make sure the tester display is 6560 to 7027.

(7) EFIS Bus Signals Test

(a) References Reference Description

AMM 34-22-00/501 EFIS AMM 34-28-01/201 Inertial Reference System

(b) Make sure the EFIS system is serviceable (AMM 34-22-00/501)

(c) Make sure the IRS system is serviceable (AMM 34-28-01/201)

(d) Make sure the SYS DSPL switch on the IRS display is in the L position

(e) Make sure the EFIS transfer switch is in the NORM position.

(f) Make sure the IRS transfer switch is in the NORM position.


(h) On the IRS display unit, push and hold the DSPL SEL switch in the test

position for more than 10 seconds.

(i) Make sure the tester display is 0224 to 0303.

(j) Put the SYS DSPL switch on the IRS display in the R position.

(k) Put the EFIS transfer switch to the BOTH-ON 2 (or BOTH-ON-R) position


EFFECTIVITY



(l) On the IRS display unit, push and hold the DSPL SEL switch in the test position for more than 10 seconds.

(m) Make sure the tester display is 0224 to 0303.

(n) Put the EFIS transfer switch to its usual position.

(8) Accelerometer Signals Test

(a) Special Tools and Equipment


# Inclinometer

(b) References Reference Description

AMM 31-24-81/401 Flight Recorder System Accelerometer

(c) Loosen the accelerometer but do not disconnect the electrical connector, AMM 31-24-81/401

(d) Use the inclinometer to put the accelerometer in to the positions shown in

the table below.

(e) Set the tester to the applicable words and subframe and make sure the display agrees with the values shown in the table below.

(f) Carefully install the accelerometer to its usual position (AMM 31-24-81/401)

WORD SUBFRAME ACCEL POSITION TESTER DISPLAY

VERTICAL ACCEL 02, 10, 18, 26, 34, 42, 50, 58 0

NORMAL 3520 – 3636 INVERTED 1746 – 2064

LATERAL ACCEL

11, 27, 43, 59 0 NORMAL 4024 – 4217

LEFT FACE UP 0150 – 0337 LONGITUDINAL ACCEL

9, 25, 41, 57 0 NORMAL 4024 – 4217

FORWARD FACE UP 7704 – 7777

(9) ATC Event (Radio Keying) signals Test

(a) References Reference Description

AMM 23-11-01/501 HF Communication System AMM 23-11-00/501 VHF Communication System

WARNING: MAKE SURE THAT PERSONNEL STAY A MINIMUM OF 6 FEET AWAY FROM

THE VERTICAL STABILIZER WHEN THE HF SYSTEM TRANSMITS. RF ENERGY FROM THE HF COMMUNICATION ANTENNA CAN CAUSE INJURY TO PERSONNEL.


EFFECTIVITY



(b) Make sure the HF Communication system is serviceable (AMM 23-11-01/501)

(c) Make sure the VHF Communication system is serviceable (AMM 23- 11-00/501)

(d) Tune all transceivers to approved frequencies.

(e) On the captain's audio selector panel, push the VHF-1 switch.

(f) On the Tester, Set the SUBFRAME to 0 and the WORD to 07.

(g) Make sure bit 3 is a 1 (or light is on).

(h) Push the captain's PTT button and make sure bit 3 goes to a 0 (or light goes off)

(i) On the captain's audio selector panel, push the VHF-2 switch.

(j) On the Tester, Set the SUBFRAME to 0 and the WORD to 08.

(k) Make sure bit 3 is a 1 (or light is on).

(l) Push the captain's PTT button and make sure bit 3 goes to a 0 (or light

goes off).

(m) On the captain's audio selector panel, pus the HF-1 switch.

(n) On the Tester, Set the SUBFRAME to 0 and the WORD to 04.

(o) Make sure bit 2 is a 1 (or light is on).

(p) Push the captain's PTT button and make sure bit 2 goes to a 0 (or light goes off).

(q) Use the first officer's audio selector panel and first officer's PTT button

and repeat test.

(10) EIS Bus signals Test (a) References


AMM 31-42-00/501 EIS System

NOTE: If the input signal of the actual N1 is 10% RPM or more on one of the two engines the BITE test will not function.

(b) On the Tester, Set the SUBFRAME to 0 and the WORD to 04.

(c) Push and hold the primary EIS BITE button.

(d) Let the display become stable and make sure it shows N1 of 106%.

(e) Make sure the tester display is 6374 to 6603.

(f) Release the primary EIS BITE button.


EFFECTIVITY




(h) Push and hold the BITE button on the primary EIS.

(i) Let the display become stable and make sure it shows N1 of 106%.

(j) Make sure the tester display is 6374 to 6603.

(k) Release the primary EIS BITE button.

(l) On the Tester, Set the SUBFRAME to 1, WORD to 49, and SUPERFRAME CYCLE to 3.

(m) Push and hold the BITE button on the secondary EIS.

(n) Let the display become stable and make sure the left oil pressure shows 13

psi.

(o) Make sure the tester display is 0013 to 0017.

(p) Release the secondary EIS BITE button.

(q) On the Tester, Set the SUBFRAME to 1, WORD to 49, and SUPERFRAME Cycle to 2.

(r) Push and hold the BITE button on the secondary EIS.

(s) Let the display become stable and make sure the right oil pressure shows

13 psi.

(t) Make sure the tester display is 0013 to 0017.

(u) Release the secondary EIS BITE button.

(11) FCC Bus Signals Test (a) References


AMM 22-11-01/501 Digital Flight Control System AMM 27-51-00/201 Trailing Edge Flaps

(b) Make sure the Autopilot system is serviceable (AMM 22-11-01/501).

(c) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 16.

CAUTION: WHEN YOU CHANGE DIRECTIONS WITH THE ELECTRICAL FLAP DRIVE KEEP

THE SWITCH IN THE SAME POSITION FOR 30 SECONDS. YOU CAN CAUSE DAMAGE TO THE ELECTRICAL FLAP DRIVE IF YOU DO NOT KEEP THE SWITCH IN THE SAME POSITION FOR 30 SECONDS

(d) Use the electrical flap drive to put the trailing edge flaps in the 2°

position (AMM 27-51-00/201)

NOTE: The position refers to the middle of the white band.


EFFECTIVITY



(e) Make sure the tester display is 0000 to 0557.

(f) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 16.

(g) Use the electrical flap drive to put the trailing edge flaps in the 25° position.


(12) Control Column Position Signal Test

(a) References


AMM 29-00-00/201 Hydraulic Power

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATOR S, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(b) Supply hydraulic power A and B (AMM 29-00-00/201).

(c) Make sure the control column is in the neutral position and install a rig

pin in the captain's control column.

(d) On the Tester, set the SUBFRAME to 0 and the WORD to 13 and 45 (in turn).

(e) Make sure the tester display is 7640 to 0137 (nominal 0000).

(f) Remove the rig pin from the captain's control column and move the column to the full forward position (against the stop).

NOTE: Do not use too much force on the control column or you may not

see correct values.

(g) Make sure the tester display is 6420 to 6716.

(h) Move the column to the full aft position (against the stop).


(j) Move the control column to the usual position.

(k) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201

(13) Control Wheel Position Signal Test



11MIT5-74110-51 Universal Protractor (or equivalent)


EFFECTIVITY



(b) References


AMM 27-11-00/201 Aileron and Aileron Trim Control

(c) Install the protractor to the control wheel.

(d) Make sure the control wheel is in the neutral position and install a rig pin in the captain's control wheel.

(e) On the Tester, Set the SUBFRAME to 0 and the WORD to 21 and 53 (in turn).

(f) Make sure the tester display is 7745 to 0033 (nominal 0000).

(g) Remove the rig pin and turn the control wheel counter clockwise to 50°.


(i) Turn the control wheel clockwise to 50°.


(k) Move the control wheel to the usual position.

(l) Remove the protractor from the control wheel.

(14) Rudder Pedal Position signal Test

(a) References


AMM 27-21-00/501 Rudder and Rudder Trim Control System.

(b) Use the rudder pedal crank to move the captain's rudder pedal to the zero position and install a rig pin in the captain's rudder pedal.

(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 29 and 61 (in turn).

(d) Make sure the tester display is 7557 to 0221 (nominal 0000).

(e) Remove the rig pin and push the captain's right rudder pedal forward to the

stop.


(g) Push the captain's left rudder pedal forward to the stop.


(i) Move the rudder pedals to the usual position.


EFFECTIVITY

31-24-01AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU AND HONEYWELL FDR Page 511 MOD 0876 NOV 01/12


(15) Elevator Position Signal Test (a) References


AMM 29-00-00/201 Hydraulic Power AMM 27-31-00/201 Elevator and Tab Control AMM 27-31-00/501 Elevator and Tab Control AMM 31-24-51/401 Elevator Position Transmitter

WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL

SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(b) Make sure the elevator system is serviceable (AMM 27-31-00/201).

(c) Set the ''B'' dimension on the stabiliser jackscrew to 41.57 ± 0.05 inches.

AMM 27-31-00/501.

(d) Open the STAB TRIM circuit breaker on the P6 panel.

(e) Make sure the mach trim actuator is in the null position.

(f) Supply hydraulic power A and B (AMM 29-00-00/201).

(g) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table:

(h) Set the elevators to the positions shown in the following table and make

sure the values agree with the tester display.

WORD SUBFRAME POSITION TESTER DISPLAY LEFT ELEVATOR

14 0 At Index Mark 7731 – 0051 10” Above Index 7217 – 7336 10” Below Index 0473 – 0635

RIGHT ELEVATOR 46 0

At Index Mark 7726 – 0046 10” Below Index 7144 – 7304 10” Above Index 0441 – 0560

(i) Remove hydraulic power A and B if it is no longer necessary

(AMM 29-00-00/201


EFFECTIVITY



(16) Aileron Position signal Test

(a) References


AMM 27-11-00/201 Aileron and Aileron Trim Control AMM 31-24-31/401 Aileron Position Transmitter



(b) Supply power to the aileron system (AMM 27-11-00/501)

(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the

following table.

(d) Set the ailerons to the positions shown in the following table and make sure the values agree with the tester display.

WORD SUBFRAME POSITION TESTER DISPLAY

LEFT AILERON

22 0

At Index Mark (point A aligned with point B)

7736 – 0042

4” Above Index 0475 – 0612 4” Below Index 7166 – 7302

RIGHT AILERON

54 0

At Index Mark (point A aligned with point B) 7736 – 0042

4” Above Index 7166 – 7302 4” Below Index 0475 – 0612

(e) Remove power to the aileron system if it is no longer necessary

(AMM 27-11-00/201)

(17) Rudder Position Signal Test (a) References


AMM 27-21-00/201 Rudder and Rudder Trim Control AMM 31-24-41/401 Rudder Position Transmitter



(b) Make sure the rudder control system is serviceable (AMM 27-21-00/201).


EFFECTIVITY



(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.

(d) Set the rudder to the positions shown in the following table and make sure

the values agree with the tester display.

WORD SUBFRAME POSITION TESTER DISPLAY RUDDER

30 & 62 0 At Index Mark 7756 – 0021

16” Left of Index 7274 – 7365 16” Right of Index 0421 – 0511

(e) Remove power to the rudder control system if it is no longer necessary

AMM 27-21-00/201.

(18) Stabilizer Position Signal Test (a) References


AMM 27-41-00/501 Horizontal Stabilizer Trim Control System AMM 29-00-00/201 Hydraulic Power



(b) Supply hydraulic power A and B (AMM 29-00-00/201).


following table.

(d) Set the Horizontal Stabilizer to the positions shown in the following table and make sure the values agree with the tester display.

WORD SUBFRAME POSITION TESTER DISPLAY

STABILIZER

44 0

41.57” Dimension B (3 units trim) 7705 – 0074

27.16” Dimension B (13 units trim) 0440 – 0660

(e) Remove hydraulic power A and B if it is no longer necessary

(AMM 29-00-00/201)

(19) Stabilizer Trim (A/P) Control Signal Test (a) References


AMM 27-41-00/501 Horizontal Stabilizer Trim Control System


EFFECTIVITY




(c) Put the dip engage switch A to the CMD position.

(d) Make sure bit 2 is a 0 (or light is off).

(e) Make sure all the STAB TRIM circuit breakers on the P18 panel are closed.

(f) Pull the control column aft until the stabilizer trim operates (AMM 27-41- 00/501).

(g) Make sure bit 2 changes to a 1 (or light comes on).

(h) Put the control column in the neutral position and make sure bit 2 goes to

0 (or light goes off).

(20) Stabiliser Trim (Manual) switch Signal Test


(b) Make sure the trim switches on the control wheel are in the neutral position.

(c) Make sure bit 1 is a 0 (or light is off).

(d) Set the trim switch on the captain's control wheel to the TRIM NOSE UP

position.

(e) Make sure bit 1 changes to a 1 (or light comes on).

(f) Set the trim switch on the captain's control wheel to the neutral position.

(g) Make sure bit 1 changes to a 0 (or light is off).

(h) Set the trim switch on the captain's control wheel to the TRIM NOSE DN position.

(i) Make sure bit 1 changes to a 1 (or light comes on).

(j) Set the trim switch on the captain's control wheel to the neutral position.

(k) Make sure bit 1 changes to a 0 (or light is off).

(l) Use the first officer's control wheel switches and repeat the test

(21) Alternate Flaps Signals Test


(b) Make sure the alternate 'flaps master arming switch on the P5-3 panel is in

the off position.

(c) Make sure bit 6 is a 0 (or the light is off).

(d) Set the alternate flaps master arming switch to the ARMED position.

(e) Make sure bit 6 changes to a 1 (or the light comes on).


EFFECTIVITY



(22) Leading Edge Flap Position Signal Test (a) References


AMM 27-81-00/201 Leading Edge Flap and Slat

(b) Make sure the flap system is serviceable (AMM 27-81-00/201).

CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.


following table.

(d) Move the flaps to get the conditions shown in the following table and make sure the values agree with the tester display.

FLAP NUMBER WORD SUBFRAME FLAP LIGHT

FLAP LIGHT CONDITION

BIT NUMBER

TESTER DISPLAY

1 23 1 & 3

IN TRANSIT OFF 2

1 (LIGHT ON) IN TRANSIT ON 0 (LIGHT OFF)

35 2 & 4 FULL EXTEND OFF

12 1 (LIGHT ON)

FULL EXTEND ON 0 (LIGHT OFF)

2 23 2 & 4

IN TRANSIT OFF 2



11 1 (LIGHT ON)


3 23 1 & 3

IN TRANSIT OFF 1



10 1 (LIGHT ON)


4 23 2 & 4

IN TRANSIT OFF 1



9 1 (LIGHT ON)


(23) Leading Edge Slat Position Signal Test (a) References


AMM 27-81-00/201 Leading Edge Flap and Slat AMM 29-00-00/201 Hydraulic Power

(b) Make sure the slat system is serviceable (AMM 27-81-00/201).

(c) Supply hydraulic power A and B (AMM 29-00-00/201).

CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED

POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.


EFFECTIVITY



(d) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.

(e) Move the slats to get the conditions shown in the following table and make

sure the values agree with the tester display

FLAP NUMBER

WORD SUBFRAME FLAP LIGHT FLAP LIGHT CONDITION

BIT NUMBER

TESTER DISPLAY

1

35 2 & 4 IN TRANSIT OFF

8 1 (LIGHT ON)

IN TRANSIT ON 0 (LIGHT OFF)

24 1 & 3 MID EXTEND OFF

3 1 (LIGHT ON)

MID EXTEND ON 0 (LIGHT OFF)


2 1 (LIGHT ON)


2


7 1 (LIGHT ON)



3 1 (LIGHT ON)



2 1 (LIGHT ON)


3


6 1 (LIGHT ON)



2 1 (LIGHT ON)



1 1 (LIGHT ON)


4


5 1 (LIGHT ON)



2 1 (LIGHT ON)



4 1 (LIGHT ON)


5


4 1 (LIGHT ON)



1 1 (LIGHT ON)



11 1 (LIGHT ON)


6


3 1 (LIGHT ON)



1 1 (LIGHT ON)



12 1 (LIGHT ON)


(F) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201) .


EFFECTIVITY



(24) Thrust Reverser Position Signal Test

(a) References


AMM 78-31-00/501 Thrust Reverser System AMM 29-00-00/201 Hydraulic Power

CAUTION: PUT A SAFETY OBSERVER NEAR THE THRUST REVERSER WHEN YOU DO

THIS TEST. THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS WHEN IT MOVES.

(b) Pull the safety pins from each thrust reverser isolation valve at the

forward air conditioning bay AMM 78-31-00/201.

(c) Make sure the thrust reverser circuit breakers are closed.

(d) With the two thrust reverser handles fully down, energize the A and B Hydraulic systems AMM 29-00-00/201.

(e) On the Tester, Set the SUBFRAME and WORD to the locations shown in the

following table.

(f) Move the thrust reversers to get the conditions shown in the following table and make sure the values agree with the tester display .

ENGINE NUMBER

WORD SUBFRAME T/R POSITION BIT NUMBER

TESTER DISPLAY

1 56 0

T/R L SLV STOWED 3

1 (LIGHT ON) T/R L SLV NOT STOWED 0 (LIGHT OFF)

56 0 T/R L SLV STOWED

4 1 (LIGHT ON)

T/R L SLV NOT STOWED 0 (LIGHT OFF)

2 39 0

T/R L SLV STOWED 4

1 (LIGHT ON) T/R L SLV NOT STOWED 0 (LIGHT OFF)


3 1 (LIGHT ON)

T/R L SLV NOT STOWED 0 (LIGHT OFF)

1 56 0

T/R L SLV STOWED 1

0 (LIGHT OFF) T/R L SLV NOT STOWED 1 (LIGHT ON)


2 0 (LIGHT OFF)

T/R L SLV NOT STOWED 1 (LIGHT ON)

2 39 0

T/R L SLV STOWED 2

0 (LIGHT OFF) T/R L SLV NOT STOWED 1 (LIGHT ON)


1 0 (LIGHT OFF)

T/R L SLV NOT STOWED 1 (LIGHT ON)

(g) Put the thrust reversers in the locked position.

(h) Return the safety pins to the thrust reverser isolation values.

(i) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201).


EFFECTIVITY



(25) Speed Brake Handle Signal Test (a) References


AMM 27-62-00/501 Speed Brake Control System

(b) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.

(c) Set the speed brake handle to the positions shown in the following table

and make sure the values agree with the tester display.

WORD SUBFRAME POSITION TESTER DISPLAY SPEED BRAKE HANDLE

20 0 DOWN 7751 – 0027 ARMED 7674 – 7751 INFLIGHT 7036 – 7113

(d) Put the speed brake handle in its usual position.

(26) Autothrottle Bus Signals Test

(a) Make sure the engines are off.

(b) Put the No. 1 throttle lever to the full forward position.

(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 07.

(d) Make sure the tester display is 2000 to 2707.

(e) Put the No. 2 throttle lever to the full aft (idle) position.


(g) Make sure the tester display is 7525 to 0253 (nominal 0000).

(h) Put the No. 1 and No. 2 throttle lever's to the usual position.

(27) FMC Bus Signals Test

(a) References


AMM 28-41-02/501 Fuel Quantity Indicating System AMM 34-62-00/501 Flight Management Computer System

(b) Make sure the following systems are serviceable:

1) Flight Management Computer System (AMM 34-62-00/501) 2) DAA No. 1 3) Fuel Quantity Indicator System (AMM 28-41-02/501)


EFFECTIVITY



(c) Use the FMC CDU to get access to the PREF INIT 1/1 page: 1) Push the INIT REF key on the CDU. 2) Make sure the CDU shows the POS INIT page. 3) Push the line-select key 6L (<index). 4) Make sure the CDU shows the INIT REF INDEX 1/1 page. 5) Push the line-select key 3L (<PERF). 6) Make sure the CDU shows the PERF NIT 1/1 page.

(d) Enter the following information into the CDU.

1) Make sure a number shows below the FUEL annunciation (next to line-select key 2L).

2) Use the keys on the FMC CDU to enter a gross weight of 46.8K KG (102,960 lbs).

3) Make sure 46.8K shows on the CDU scratch pad. 4) Push the line-select key 1L. 5) Make sure the CDU shows the gross weight adjacent to the line- select

key 1L. 6) Push the line-select key 6R (TAKEOFF>). 7) Make sure the CDU shows the TAKEOFF REF 1/1 page.

(e) On the Tester, Set the SUBFRAME to 3, WORD to 49, and SUPERFRAME CYCLE

to 15.


NOTE: Value will only be visible when the is cycled on CDU.

(g) On the Tester, Set the SUBFRAME to 0, and the WORD to 63.

(h) Push the line -select key next to the FIXED OUTPUTS prompt on the FMCS BITE page of the CDU.


(28) Autothrottle Disengage Switch Signals Test

(a) On the Tester, Set the SUBFRAME to 0 and WORD to 48.

(b) Make sure bit 1 is a 1 (or light is on).

(c) Push the A/T disengage switch on the thrust lever for engine No. 1

(d) Make sure bit exchanges to a 0 (or light goes off).

(e) Release the A/T disengage switch.

(29) Yaw Damper Engage Signals Test


(b) Engage Yaw Damper switch on P5-3.

(c) Make sure bit 1 is a 1 (or light is on).

(d) Disengage Yaw Damper switch. 1

(e) Make sure bit 1 changes to a 0 (or light goes off).


EFFECTIVITY



(30) Marker Beacon Signals Test


(b) Make sure bit 1 is a 0 (or light is off).

(c) Push the SELF-TEST button on the marker beacon receiver and make sure bit 1 on the tester changes to a 1 (or light comes on) in conjunction with the marker beacon lights on the P1 and P3 panels.

NOTE: The Self-Test button on the marker beacon receiver causes the

marker beacon lights to come on in order (i.e. Outer, Middle, and Airways). All three of these inputs relate to WORD 12, discrete bit 1.

On some marker beacon receivers the Self-Test button does not exist.If this is the case perform the system test IAW MM 34-35-00 and ensure that bit 1 on the tester changes to a 1 (or light comes on) in conjunction with the marker beacon lights.

(31) Master Caution Annunciator Signals Test

(a) Set the IRS Transfer switch to the NORM position.

(b) Close the IRS-1 AC breaker on the P18-2 panel.

(c) Make sure the IRS master caution light is off.

(d) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.

(e) Make sure bit 2 is a 1 (or light is on).

(f) Open the IRS AC circuit breaker.

(g) Make sure the IRS master caution light comes on.

(h) Make sure bit 2 is a 0 (or light is off).

(32) A/P Warning (Captain) Signals Test

(a) Open the following circuit breakers on the P6-2 panel:

1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC


(c) Get the FMC MAINT PAGE on the CDU.

(d) Push the line select key next to the DFCS BITE prompt and make sure the

captains A/P warning light in on.

(e) Make sure bit 4 is a 0 (or light is off).

(f) Push the INIT REF key on the FMC CDU and make sure the captain's A/P warning light is off.


EFFECTIVITY




(h) Close the following circuit breakers on the P6-2 panel: 1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC

(33) A/P Warning (First Officer) Signals Test




(c) Get the FMC MAINT PAGE on the CDU.

(d) Push the line select key next to the DFCS BITE prompt and make sure the

first officer's A/P warning light in on.


(f) Push the INIT REF key on the FMC CDU and make sure the first officer's A/P warning light is off.


(h) Close the following circuit breakers on the P6-2 panel:


(34) Autothrottle Warning Signals Test


(b) Make sure the autothrottle is engaged and the autothrottle warning lights

are off.

(c) Make sure bit 8 is a 1 (or light is on).

(d) Push the A/T disengage switch on the thrust lever for engine No. 1 and make sure the autothrottle warning lights flash.

(e) Make sure bit 8 changes to a 0 (or light go off).

(f) Release the A/T disengage switch


EFFECTIVITY



(35) Fire Warning (Wheel Well) Signals Test

(a) Open the following circuit breakers on the P6-2 panel: 1) FIRE PROTECTION DETECTION APU 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2

(b) Ensure the following circuit breaker on the P6-2 are closed:

1) OVHT WHL WELL WING BODY

(c) On the Tester, set the SUBFRAME to 0 and the WORD to 38.

(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the wheel well light comes on.


(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the wheel well light

goes off.

(g) Make sure bit 12 is a 0 (or light is off).

(h) Close the following circuit breakers on the P6-2 panel: 1) FIRE PROTECTION DETECTION APU 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2

(36) Fire Warning (APU) Siqnals Test


1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION ENG 1 3. FIRE PROTECTION DETECTION ENG 2

(b) Ensure the following circuit breakers on the P6-2 panel are closed:

1) FIRE PROTECTION DETECTION APU


(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the APU fire light comes on.


(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the APU fire light

goes off.


(h) Close the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2


EFFECTIVITY



(37) Fire Warning (Engine No. 1) Signals Test

(a) Open the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 2


1) FIRE PROTECTION DETECTION ENG 1


(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the ENG #1 light comes on.


(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the ENG #1 fire light

goes off.


(h) Close the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 1

(38) Fire Warning (Engine No. 2) Signals Test


1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 1


1) FIRE PROTECTION DETECTION ENG 2


(d) Put the FAULT/INOP--OVHT/FIRE switch in the OVHT/FIRE position and make sure the ENG #2 light comes on.


(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the ENG #2 are light

goes off.


(h) Close the following circuit breakers on the put panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 2


EFFECTIVITY



(39) Landing Gear Position signals Test

(a) Make sure the airplane is on the ground, all three gears are down and locked and the landing gear doors are open.

(b) Install locks on all landing gear.

(c) Make sure hydraulic power is off.

(d) Make sure the LEFT, RIGHT and NOSE GEAR green lights on the P2 panel are

on.

(e) Make sure the LEFT, RIGHT and NOSE GEAR red lights on the P2 panel are off.

(f) On the Tester, Set the SUBFRAME and WORD to the locations shown in the

following table.

(g) On one gear at a time install a copper shield between the downlock sensor and the actuator of the proximity switch shown in the following table and make sure the values agree with the tester display.

LANDING GEAR

WORD SUBFRAME GEAR LIGHT LIGHT CONDITION

BIT NUMBER

TESTER DISPLAY

LEFT 35 1

GREEN ON 1

0 (LIGHT OFF) GREEN OFF 1 (LIGHT ON)

38 0 RED ON

5 0 (LIGHT OFF)

RED OFF 1 (LIGHT ON)

RIGHT 35 1

GREEN ON 2


38 0 RED ON

10 0 (LIGHT OFF)


NOSE 35 3

GREEN ON 2


38 0 RED ON

9 0 (LIGHT OFF)


(40) Air/Ground Signals Test


(b) Make sure bit 1 is a 0 (or light off).

(c) Push the GND SENSING TEST switch on the landing gear accessory unit on the E11 shelf.

(d) Make sure bit 1 is a 1 (or light goes on).

(e) Release the GND SENSING TEST switch.


(g) Make sure bit 2 is a 0 (or light off).

(h) Push the NOSE SENSING TEST switch on the landing gear accessory.


EFFECTIVITY



(i) Make sure bit 2 is a 1 (or light goes on).

(41) DSWC Bus Signal Test



# Angle-of-Attack vane angle protractor

(b) Put the A and B PITOT STATIC HEAT switches on the pilot's overhead panel to the off position.

NOTE: This removes the heater power from the angle-of-airflow (alpha) vane.

WARNING: DO NOT TOUCH THE ALPHA VANES UNTIL THEY ARE COOL. HOT ALPHA

VANES CAN BURN YOU.

(c) Turn the left vane slowly to make sure it moves freely.

(d) Attach a portable airflow sensor calibrator to the left vane.

(e) Make sure the A SNSR EXC AC circuit breaker on the P18-1 circuit panel is closed.

(f) Use the protractor to put the vane in a 11° a trailing edge up position.

(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 19 and 51 (in turn).

(h) Make sure the tester display is 104X to 112X.

NOTE: X represents any alphanumeric character.

(i) Remove the portable airflow sensor calibrator from the left vane

(42) DAA Bus Signals Test

(a) Set the captain's VHF NAV control panel on the P8 control stand to the MAN

position.

(b) Tune the control panel to 108.25 MHz.


(d) Make sure the tester display is 5XXX.

NOTE: XXX represents any alphanumeric character.

(e) On the Tester, Set the SUBFRAME to 2 and the WORD to 49.

(f) Make sure the tester display is 0404.

(g) Set the First Officer's VHF NAV control panel on the P8 control stand to the MAN position.

(h) Tune the control panel to 109.50 MHz.


EFFECTIVITY



(i) On the Tester, Set the SUBFRAME to 4 and the WORD to 52.

(j) Make sure the tester display is 0XXX.


(k) On the Tester, Set the SUBFRAME to 4 and the WORD to 49.

(l) Make sure the tester display is 0452.

(43) Hydraulic System Low Pressure Signal Test (a) References



CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.

(b) Close the following circuit breakers on the put panel:

1) MASTER DIM SECTION 1 (C00313) 2) MASTER DIM SECTION 5 (C00317) 3) MASTER DIM SECTION 6 (C00318)

(c) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 3.

(d) Make sure the system A-ENG 1 LOW PRESSURE annunciator on the P5 forward

overhead panel is on.


(f) Open the SECTION 6 MASTER DIM circuit breaker.

(g) Disconnect the D2684 connector from the S796 system A engine pump low pressure switch.

(h) Close the SECTION 6 MASTER DIM circuit breaker.

(i) Make sure bit 2 is a 1 (or light goes on).

(j) Make sure the system A-ENG 1 LOW PRESSURE annunciator is off.

(k) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 3.

(l) Make sure the system B-ENG 2 LOW PRESSURE annunciator on the P5 forward

overhead panel is on.

(m) Make sure bit 2 is a 0 (or light is off).

(n) Open the SECTION 5 MASTER DIM circuit breaker.


EFFECTIVITY



(o) Disconnect the D2686 connector from the S797 system B engine pump low pressure switch.

(p) Close the SECTION 5 MASTER DIM circuit breaker.

(q) Make sure bit 2 is a 1 (or light goes on).

(r) Open the SECTION 1, 5, and 6 MASTER DIM circuit breakers.

(s) Make sure the system A-ENG 1 LOW PRESSURE annunciator is off.

(t) Connect the electrical connectors to system A and B engine pump low

censure switches.

(u) Close the SECTION 1, 5, and 6 MASTER DIM circuit breakers.

(v) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 3.

(w) Make sure the system B-ELEC 1 LOW PRESSURE annunciator is on.

(x) Make sure bit 1 is a 0 (or light is off).

WARNING: TO AVOID INJURY TO PERSONNEL, STAY CLEAR OF THE LEADING EDGE SLAT is WHICH CAN MOVE AUTOMATICALLY (UNLESS OTHERWISE INHIBITED) DURING MAINTENANCE WHEN EITHER HYDRAULIC SYSTEM IS PRESSURIZED AND THE TRAILING EDGE FLAPS ARE IN POSITION 1, 2, OR 5 AND THE NOSE OR MAIN LANDING GEAR AIR/GROUND RELAYS SENSE AN AIRBORNE CONDITION.

(y) Set the system B-ELEC 1 switch to the on position.

(z) Make sure the system B electrical pump is on.

(aa) Make sure the system ELEC-1 LOW PRESSURE annunciator is off.

(ab) Make sure bit 1 is a 1 (or light goes on).

(ac) Set the system B-ELEC 1 switch to the off position.

(ad) Make sure the system ELEC-1 LOW PRESSURE annunciator comes On.

(ae) Make sure bit 1 is a 0 (or light is off).

(af) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 3.

(ag) Set the system A-ELEC 2 switch to the on position.

(ah) Make sure the system A electrical pump is on.

(ai) Make sure the system ELEC-2 LOW PRESSURE annunciator is off.

(aj) Make sure bit 1 is a 1 (or light goes on).

(ak)Set the system A-ELEC 2 switch to the off position.

(al)Make sure the system ELEC-2 LOW PRESSURE annunciator comes On.


EFFECTIVITY



(am) Make sure bit 1 is a 0 (or light is off).

(an) Open the following circuit breakers: 1) NORMAL STANDBY HYDRAULIC PUMP (C847) ON P6-11 2) ALTERNATE STANDBY HYDRAULIC PUMP (C848) ON P6-12

(ao) Set the FLT CONTROL A switch on the P5-3 panel to the STBY RUD position.

(ap) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 36.

(aq) Make sure bit 2 is a 0 (or light is off).

(ar) Close the NORMAL and ALTERNATE STANDBY HYDRAULIC PUMP circuit breakers.

(as) Make sure bit 2 is a 1 (or light is on).

(at) Set the FLT CONTROL A switch to the off position.

(au) Remove hydraulic power if it is no longer necessary (AMM 29-00-00/201).

(av) Open the NORMAL and ALTERNATE STANDBY HYDRAULIC PUMP circuit breakers.

(44) IRU Bus Signals Test

(a) References


AMM 34-28-01/50 Inertial Reference System

(b) Open the following circuit breakers on the P18-2 panel: 1) FMCS CMPTR (C1017).

(c) Wait at least 60 seconds before continuing to next step.

(d) Make sure the EFIS transfer switch is in the NORM position.

(e) Make sure the IRS transfer switch is in the NORM position.

(f) Make sure the two IRUS are in NAV mode (AMM 34-28-01/501).

(g) Make sure the SYS DSPL switch is in the L position.

(h) On the Tester, Set the SUBFRAME to 1 and the WORD to 52.

(i) On the IRS display unit, turn and hold the DSPL SEL knob to the TEST

position.


(k) Turn the SYS DSPL switch is in the R position.

(l) On the IRS display unit, turn and hold the DSPL SEL knob to the TEST position.

(m) Make sure the tester display is 2760 to 3237.


EFFECTIVITY



(45) Fuel Cutoff Signals Test

(a) Open the following circuit breaker on the P6-2 panel: 1) ENG 1 R IGN 2) ENG 1 L IGN 3) ENG 2 R IGN 4) ENG 2 L IGN

(b) Make sure pneumatic power is NOT available to the two engines.

(c) Make sure the fire handles are in the NORMAL ignition.

(d) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 56.

(e) Make sure the engine No. 1 start lever is in the CUTOFF position.

(f) Make sure bit 5 is a 1 (or light is on).

(g) Put the engine No. 1 start lever switch in the START position.

(h) Make sure bit 5 is a 0 (or light goes off).

(i) Put the engine No. 1 start lever switch in the CUTOFF position.

(j) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 56.

(k) Make sure the engine No. 2 start lever is in the CUTOFF position.

(l) Make sure bit 5 is a 1 (or light is on).

(m) Put the engine No. 2 start lever switch in the START position.

(n) Make sure bit 5 is a 0 (or light goes off).

(o) Put the engine No. 2 start lever switch in the CUTOFF position.

(p) Close the following circuit breaker on the put panel:

1) ENG 1 R IGN 2) ENG 1 L IGN l 1 3) ENG 2 R IGN 4) ENG 2 L IGN

(46) Stick Shaker Signals Test


(b) Make sure bit 2 is a 0 (or light is off).

(c) Push the STALL WARNING TEST NO.1 button on the stall warning module.

(d) Make sure bit 2 is a 1 (or light goes on).

(e) Release the STALL WARNING TEST NO.1 button.

(f) Make sure bit 2 is a 0 (or light goes off).

(g) Push the STALL WARNING TEST NO. 2 button on the stall warning module.


EFFECTIVITY



(h) Make sure bit 2 is a 1 (or light goes on).

(i) Release the STALL WARNING TEST NO. 2 button.

(47) EFIS Transfer Switch Signals Test

(a) Make sure the EFIS transfer switch on the P5 overhead panel is in the NORMAL position.

(b) On the Tester, Set the SUBFRAME to 1 and WORD to 36.


(d) Set the EFIS transfer switch to the BOTH-ON-2 position.

(e) Make sure bit 2 is a 1 (or light goes on).

(f) Set the EFIS transfer switch to NORMAL.

(48) IRS Transfer Switch Signals Test

(a) Make sure the IRS transfer switch on the P5 overhead panel is in the

NORMAL position.

(b) On the Tester, Set the SUBFRAME to 3 and WORD to 36.


(d) Set the IRS transfer switch to the BOTH-ON-2 (or BOTH-ON-R) position.

(e) Make sure bit 2 is a 1 (or light goes on).

(f) Set the IRS transfer switch to NORMAL.

(49) GPWC Bus Signal Test


(b) Push the ground proximity warn TEST switch.

(c) Make sure bit 1 changes to a 1 (or light comes on) when the PULL-UP light is on.

(d) Make sure bit 1 changes to a 0 (or light goes off) when the PULL-UP light

goes off.

(50) TCAS Bus Signal Test


(b) Make sure the AIR/GND RELAY & LTS circuit breaker is closed.

(c) Make sure bit 12 is a 0 (or light is on.

(d) Momentarily put the Mode S/TCAS mode switch on the TCAS/ATC control panel, in the TEST position.


EFFECTIVITY



(e) Make sure bit 12 changes to a 1 (or light goes on).

(51) Cabin Altitude >10k ft Bus Signal Test

(a) Remove the connector D776 from the cabin pressure switch S128 at STA 192, WL 207, BL 0.


(c) Ground pin A of the electrical connector D776.

(d) Make sure bit 1 is a 0 (or light is off).

(e) Remove the ground on pin A of the electrical connector D776.

(f) Make sure bit 1 changes to a 1 (or light comes on).

(g) Put the connector D776 to its usual condition.

(52) Brake Pressure Signal Test

(a) References


AMM 32-41-00/501 Hydraulic Brake System AMM 29-00-00/201 Hydraulic Power


SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(b) Put chocks around the airplane wheels.

(c) Release the parking brake.

(d) Supply hydraulic power to system B (AMM 29-00-00/201).

(e) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and WORD to 24.

(f) Push the captain's left brake pedal fully against the stop.

(g) Find the PSI value in the table that best agrees with the hydraulic

pressure display and make sure the tester display agrees with the value.

(h) Release the captain's left brake pedal.

(i) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and WORD to 24.

(j) Push the captain's right brake pedal fully against the stop.

(k) Find the PSI value in the table that best agrees with the hydraulic pressure display and make sure the tester display agrees with the value.

(l) Release the captain's right brake pedal.


EFFECTIVITY



(m) Remove hydraulic power to system B.

(n) Pump the brake pedal to fully deplete the accumulator.

(o) Supply hydraulic power to system A.

(p) Push the captain's right brake pedal fully against the stop.

(q) Find the PSI value in the table that best agrees with the hydraulic pressure display and make sure the tester display agrees with the value.

(r) Release the captain's right brake pedal.

(s) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and WORD to 24.

(t) Push the captain's left brake pedal fully against the stop.

(u) Find the PSI value in the table that best agrees with the hydraulic

pressure display and make sure the tester display agrees with the value.

(v) Release the captain's left brake pedal.

BRAKE PRESSURE TEST DISPLAY 2400 55XX – 60XX 2500 57XX – 62XX 2600 60XX – 64XX 2700 62XX – 66XX 2800 64XX – 70XX 2900 66XX – 72XX 3000 70XX – 73XX 3100 72XX – 75XX 3200 73XX – 77XX 3300 75XX – 77XX


(w) Remove hydraulic power if it is no longer necessary (AMM 29-00-00/201).

(53) Main/Attn Brake Select Signals Test (a) References



WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(b) Make sure the parking brake is not set.


EFFECTIVITY



(c) Supply hydraulic power to system B (AMM 29-00-00/201).

(d) Make sure hydraulic power to system A and STANDBY is of.

(e) On the Tester, Set the SUBFRAME to 4 and WORD to 56.

(f) Make sure bit 6 is a 1 (or light is on).

(g) Remove hydraulic power to system B.

(h) Supply hydraulic power to system A.

(i) Pump the captain's brake pedal to remove the pressure from the main brake lines.

(j) Make sure bit 6 is a 0 (or light goes off).

(k) Remove hydraulic power if it is no longer necessary (AMM 29-00- 00/201 .

E. Put the Airplane in its Usual Condition

(1) References


AMM 24-22-00/201 Manual Control

(2) Put the Test - Normal Switch on the Flight Recorder Test Module to the Normal Position.

(3) Put the power switch on the tester to the OFF position (if applicable).

(4) Disconnect the tester from the flight data recording system.

(5) Remove electrical power if it is no longer necessary (AMM 24-22- 00/201 .


EFFECTIVITY

31-24-22AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU Page 601 MOD 0876 APR 01/11


FLIGHT DATA ACQUISITION UNIT - SERVICING

1. General

A. This procedure contains:

1) A DFDAU Database Load Procedure 2. Install Database Into the DFDAU

A. References

Reference Title

20-15-11 P/B 201 ON-AIRPLANE SOFTWARE INSTALLATION – MAINTENANCE PRACTICES 24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)

B. Location Zones

Zone Area


C. DFDAU Database Load Procedure

NOTE: The proper DFDAU database must be loaded prior to performing any ground

tests. The following steps define the procedure for loading of the database if the proper database was not verified above. The data loader indications are based on a Honeywell PDL. Differing indications may be observed with alternate data loaders. The load disks have been created to verify the proper configuration of the Aircraft Type discretes and to confirm the aircraft is in "ground" mode (determined by a logic zero at the DFDAU binary port B37, LTP3H), prior to loading. Confirm the proper configuration of these discretes if difficulty loading is encountered.

1) Open the following Circuit breakers on the P18 panel:

FLT REC AC (C109) FLT REC DC (C468)

2) Connect data loader to the DFDAU using FDAMS DFDAU PDL Interface cable

assembly.

3) On front panel of the FDAMS DFDAU PDL Interface cable assembly, set the toggle switch to DFDAU position and turn the rotary selector switch to the DFDAU MANDATORY EE ENABLE position.

4) Close the following Circuit breakers on the P18 panel:



EFFECTIVITY

31-24-22AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU Page 602 MOD 0876 APR 01/11


5) Insert diskette, part number 998-2512-503 or approved alternate per Honeywell Component Part List, dwg. no. 756-0134-102, into data loader.

a) RDY and PROG light will illuminate during the load process.

b) RDY light will blink at approximately 3 second intervals.

c) Time to load the diskette is approximately 15 minutes, but vary with data

loader type.

d) Remove diskette when the COMP light on data loader illuminates.



7) Turn the rotary selector switch on the FDAMS DFDAU PDL Interface cable to the

DFDAU NON-MANDATORY EE ENABLE position.

8) Close the following Circuit breakers on the P18 panel:


9) Insert diskette, part number 998-2513-503 or approved alternate 503 or

approved alternate per Honeywell Component Part List, dwg. no. 756-0134-102, into data loader.

a) RDY and PROG light will illuminate during the load process.

b) RDY light will blink at approximately 3 second intervals.

c) Time to load the diskette is approximately 8 minutes, but varies with data

loader type.

d) Remove the diskette when COMP light on data loader illuminates.



11) Disconnect the FDAMS DFDAU PDL Interface cable assembly and data loader from

the DFDAU.

12) Repeat Section D (above) to verify the proper database was loaded.


EFFECTIVITY

31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 201 MOD 0952 APR 01/11


QUICK ACCESS RECORDER (MINI) – MAINTENANCE PRACTICES 1. General A. This procedure has this task: 1) The return to service test of the mini Quick Access Recorder (QAR). 2. Return to Service Test A. Test Equipment and Material

Reference Description 802-0208 RSU II Kit or functionally equivalent computer with USB port. 700-0179 miniQAR MKII HS USB I/F Software (included with 805-0005) 605-0177 Portable Test Interface (PTI) Cable 805-0005 miniQAR MKII, HS USB I/F KIT Includes PTI cable (605-0177)

and software (700-0179) B. Test Setup

1) Connect PTI cable P/N 605-0177 to the UUT DB9 connector.

NOTE: Do not Connect the USB connector of the PTI cable P/N 605-0177.

C. Procedures

1) Turn-on the PC or RSU II and allow it to boot.

2) If the RSU Menu is displayed, select File, Exit to Windows (refer to the RSU II Operations Manual, Part Number 900-0208 – included in the RSU II Kit.)

3) On the Windows toolbar, select Start, Programs, Avionica, and MiniQAR Support

Util.

4) Connect the USB connector of the PTI cable P/N 605-0177 to the USB Port of the PC or RSU II.

5) Make sure that the BIT LED of the Unit Under Test is illuminated.

6) Select “Tools”.

7) A “Return to service” prompt appears. Select “Yes”

8) A message “Return To Service In-Progress Please Wait” will be displayed.

9) The “Please Wait” will be replaced by a Results screen. Make sure all results

indicate PASSED.

10) Select “Continue”.

11) Verify that the miniQAR LED is blinking.


EFFECTIVITY

31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 202 MOD 0952 APR 01/11


12) Select “OK”. Make sure the message appears “miniQAR Successfully Erased”

13) Select “OK”. Make sure the message appears “Return to Service Complete. You may now disconnect the miniQAR”

14) Disconnect the USB connector of the PTI cable P/N 605-177 from the USB Port

of the PC or RSU tablet first.

15) Disconnect the DB9 connector of the PTI cable PN 605-0177 from the UUT DB9 connector.

16) End of test. The miniQAR can now be returned to service.

CHAPTER

NAVIGATION


EFFECTIVITY

34-22-00404 (PV284) Page 501 MOD 0864 APR 01/11


ELECTRONIC FLIGHT INSTRUMENT SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry An EFIS Display Modes Test of the EFIS System. The EFIS Display Modes Test is part of the Operation Test of the EFIS System

B. Any other test associated with the EFIS System in accordance with 34-22-00 Page

Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

C. EFIS Display Modes Test

SUBTASK 34-22-00-865-028-001

(1) Make sure the EFI transfer switch is in the NORMAL position.

SUBTASK 34-22-00-865-149-001

WARNING: DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS ADDED OR REMOVED IN AREA 200 FEET OR LESS OF THE ANTENNA. THIS CAN CAUSE AN EXPLOSION.

DO NOT OPERATE THE WEATHER RADAR WHILE THE AIRPLANE IS IN A HANGAR OR OTHER ENCLOSURE. MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET OR LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN CAUSE INJURY TO PERSONS.

(2) On the two EFIS control panels, set the controls as follows:

(a) The RANGE switch to the 80 position.

(b) The map mode display switches to the on position.

(c) The WXR ON switch to the on position.

SUBTASK 34-22-00-745-030-001

(3) Push the INIT/REF key on the FMCS CDU.

SUBTASK 34-22-00-745-031-001 (4) Push the line select key (LSK) 6L (<INDEX) on the FMCS CDU.

SUBTASK 34-22-00-745-032-001

(5) Push the LSK 6R (MAINT>).

(a) Make sure the FMCS CDU display shows the MAINT BITE INDEX 1/1 page.

SUBTASK 34-22-00-745-033-001 (6) Push the LSK 5L (<EFIS).

(a) Make sure the FMCS CDU display shows the EFIS BITE TEST page.

SUBTASK 34-22-00-745-034-001

(7) Push the LSK 3L (<SELF TEST).


EFFECTIVITY

34-22-00404 (PV284) Page 502 MOD 0864 APR 01/11


SUBTASK 34-22-00-755-189-001

(8) AIRPLANES WITH EFIS SYMBOL GENERATOR P/N S242T404-413 AND ON; Make sure the hex code lines on the bottom right of the two EADIs show as follows:

Table 501/34-22-00-993-804-001

7A391B0 87BE000 E080000

Note: Make sure EHSI displays HDG up in the NAV, MAP and PLAN mode.

(Refer to pages 519, 522 and 523 of the applicable AMM)

SUBTASK 34-22-00-865-035-001 (9) On the left and right EFIS control panels, set the mode switches to the

positions as follows:

(a) FULL NAV (b) EXP NAV (c) FULL VOR/ILS

NOTE: To show the VOR mode, a VOR frequency (108.00) must be set on the

VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.

(d) EXP VOR/ILS

NOTE: To show the VOR mode, a VOR frequency (108.00) must be set on the

VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.

(e) MAP (f) CTR MAP (g) PLAN

SUBTASK 34-22-00-755-036-001

(10) For each mode on the left EFIS control panel, make sure the applicable test patterns show on the left display units.

SUBTASK 34-22-00-755-037-001

(11) For each mode on the right EFIS control panel, make sure the applicable test patterns show on the right display units.

SUBTASK 34-22-00-755-038-001

(12) For each mode on the two EFIS control panels, make sure the test patterns are the same on the two EADIs and the two EHSIs.


EFFECTIVITY

34-49-03AIRPLANES WITH ENHANCED GROUND PROMXITY WARNING Page 501 MOD 0862 APR 01/11


GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST 1. General

A. This section carries out an operational test of the Enhanced Ground Proximity Warning System (EGPWS) to support the continuous operation of AeroDEC Modification MOD-0862.

2. Enhanced Ground Proximity Warning System - Operational Test

A. References

Reference Title

24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)

B. Location Zones

Zone Area

101 Control Cabin - Left 102 Control Cabin - Right 205 Electronic Compartment

C. Prepare for the Test

(1) Supply electrical power (Ref PAGEBLOCK 24-22-00/201).

(2) Make sure this circuit breaker is closed:

(a) P18 Circuit Breaker Panel

1) TERRAIN DISPLAY 2) ENHANCED GND PROX

D. Operational Test

(1) Carry out a Level 1 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system:

AURAL WARNING LIGHTS EADI

"Minimums" "1000" "500" "100" "50" "40" "30" "20" "10"


EFFECTIVITY

34-49-03AIRPLANES WITH ENHANCED GROUND PROMXITY WARNING Page 502 MOD 0862 APR 01/11


(2) Carry out a Level 2 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI

“CURRENT FAULTS” “NO FAULTS” “PRESS TO CONTINUE”

(3) Carry out a Level 3 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI

“ALTITUDE CALLOUT MENU 91”

E. Put the Airplane Back to Its Usual Condition

(1) Remove electrical power if it is not necessary (PAGEBLOCK 24-22-00/201).

------------------------- END OF TASK ---------------------------


EFFECTIVITY

34-62-01404 (PV284) Page 501 MOD 0853 APR 01/11


FLIGHT MANAGEMENT COMPUTER SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry a Program Pin Verification of the Flight Management Computer System. The Program Pin Verification is part of the System Test – Analogue Discretes.

B. Any other test associated with the Flight Management Computer System in

accordance with 34-62-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. System Test - FMCS

A. General

(1) The system test fully examines the FMCS. The system test procedure includes the tests shown below: (a) Operational Test (par. 2) (b) Analog Discretes. (c) Performance Code/Performance Factors - Verification/Adjustment

Note: For all other tests, other than the Program Pin Verification (detailed

below), please refer to the associated AMM.

B. References

Reference Title

24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER) 34-28-01 P/B 201 INERTIAL REFERENCE SYSTEM - MAINTENANCE PRACTICES

C. Location Zones

Zone Area


D. Analog Discretes

(1) Do the prepare for test (34-62-01 – associated AMM): "Operational Test -

FMCS" if it is necessary.

(2) Make sure that the CDU display shows the FMCS BITE 1/1 page.

(3) If the CDU does not show the FMCS BITE 1/1 page, do these steps: (a) Push the INIT REF key on the CDU front panel to show the POS INIT or

PERF INIT page. (b) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page. (c) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page. (d) Push the LSK adjacent to <FMCS to show the FMCS BITE 1/1 page.


EFFECTIVITY

34-62-01404 (PV284) Page 502 MOD 0853 APR 01/11


(4) Do the Program Pin Verification: (a) Push the PREV PAGE key on CDU to show the FMCS ANALOG DISC 2/4 page.

(b) Make sure the outputs on the CDU display are the same as the outputs

shown below:

Table 514

ASSUMED TEMP ENABLE

CAA FLT RULES DISABLE

CAA FLT RULES ENABLE

KILOGRAM OPTION DISABLE

MAG/TRUE MAG

OMEGA OFF

ALL AIRCRAFT PRE SB 737-34-1593 SRCE/DEST IDENT LEFT

ALL AIRCRAFT POST SB 737-34-1593 SRCE/DEST IDENT RIGHT

ALL AIRCRAFT ASPIRATED TAT DISABLE

FRQ SCAN DME DISABLE

FRQ SCAN DME ENABLE

°C/°F DEFAULT °C

EFIS INSTALLED ON

ALL AIRCRAFT; AIRPLANES WITH SOFTWARE U7.0 AND ON

NOTE: OMEGA is removed and PERF CODE 1 is added.

ALL AIRCRAFT POST SB 737-34-1593

NOTE: The SOURCE/DEST IDENT line will show RIGHT when you do a test of

the right FMC.

ALL AIRCRAFT

(c) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 3/4 page.

(d) Make sure the outputs on the CDU display are the same as the outputs

shown below: Table 515

VMO/MMO 340/.82

MAINT TEST DISABLE

ALL AIRCRAFT POST SB 737-34-1593 FMC SOURCE SEL *[1] NORMAL

ALL AIRCRAFT

*[1] The FMC SOURCE SEL line will read BOTH-ON-L when the FMC SOURCE SELECT switch is in the BOTH ON L position and BOTH-ON-R in the BOTH ON R position


EFFECTIVITY

34-62-01404 (PV284) Page 503 MOD 0853 APR 01/11


NOTE: AIRPLANES WITH SOFTWARE UPDATE 7.X, 8.X or 10.X; MAINT TEST is removed.

NOTE: AIRPLANES WITH SOFTWARE UPDATE 10.X;

VMO/MMO is removed.

(e) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 4/4 page.

(f) Make sure the outputs on the CDU display are the same as the outputs

shown below:

Table 516

VOR INHIBIT DISABLE

FLIGHT NUMBER DISABLE

TOGA RW POS UPD ENABLE

TAKEOFF PROFILE DISABLE

FAA/CAA QRH SPD DISABLE

FAA/CAA QRH SPD ENABLE

TAKEOFF SPEEDS DISABLE

NAVAID SUPPRESS DISABLE

SEL CRS INHIBIT DISABLE

ACARS INSTALLED OFF

(5) Push the line select key (LSK) adjacent to <INDEX (6L) to show FMCS BITE 1/1 page.

(6) Refer to the associated AMM to continue testing, or put aircraft back to to

its usual condition.

document no. ams-737-345-27256 aircraft manual …

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