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FPD 500FLAT PANEL DISPLAY SYSTEM

FOR THE DC-10

Operator’s Manual

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WARNING

Information subject to the export control laws. This document, which includesany attachments and exhibits hereto, contains information subject toInternational Traffic in Arms Regulation (ITAR) or Export AdministrationRegulation (EAR) of 1979, which may not be exported, released or disclosedto foreign nationals inside or outside the U.S. without first obtaining an exportlicense. Violators of ITAR or EAR may be subject to a penalty of 10 yearsimprisonment and a fine of $1,000,000 under 22 U.S.C. 2778 or Section2410 of the Export Administration Act of 1979. Include this notice with anyreproduced portion of this document.

COPYRIGHT NOTICE

©1997 AlliedSignal, Inc.

Reproduction of this publication or any portion thereof by any means withoutthe express written permission of AlliedSignal Commercial Avionics Systemsis prohibited. For further information contact the Manager, TechnicalPublications; AlliedSignal Commercial Avionics Systems; 400 North RogersRoad; Olathe, Kansas 66062. Telephone: (913) 782-0400.

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FPD 500 FLAT PANEL DISPLAY SYSTEM

1. INTRODUCTION

This Pilot’s Guide is for theAlliedSignal Commercial AvionicsSystems (CAS) Flat Panel ActiveMatrix LCD version of the 5ATIAttitude Director Indicator (ADI)and Horizontal Situation Indicator

(HSI) retrofitted into various air-craft types (e.g. DC-10, B727,etc.).

Throughout this document, theterms “ADI” and “HSI” are used toidentify the two primary functionsof the indicator even though theindicator itself is more correctlyidentified as an EADI/EHSI(Electronic ADI or HSI).

The intended use of the ADI/HSIFPI is to display the aircraft's pri-mary attitude (ADI) and to display

course, heading, glideslope, etc.(HSI). The indicator replaceselectromechanical ADI and HSIindicators with Active Matrix LCDtechnology. A single indicator(herein referred to as the"ADI/HSI") can provide the capa-bility to function as either anAttitude Direction Indicator (ADI)or a Horizontal Situation Indicator(HSI) depending on configurationstrap settings.

Reversionary mode capability is also provided so that du

operation, in the event of a failed ADI or HSI, the other capability to assume the function of both in the “IntegReversionary mode data is hard wired into each ADI much as possible. Reversionary mode is discussed in later in this document.

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Figure 1-1Typical EADI Di

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Figure 1-2Typical EHSI Di

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1.1 SYSTEM DESCRIPTION

The indicator is designed for high reliability through the use of and optimized mechanical packaging. The display is a flatactive matrix LCD with backlighting provided by a cold cathodrescent lamp.

A Graphics Processor (GP) module produces flight instrumenbology on the LCD display. The Interface Processor (IP) a

modules consists of a 32 bit microprocessor, ARINC 429 incapability, and analog/discrete interface capability. These mprocess all of the control inputs from the indicator's front beztrols, external ARINC 429 input data, external discrete data (insuperflags), synchro and analog data, and provides the interthe GP module. The Low Voltage Power Supply (LVPS) providnecessary power to all of the system’s components, while thVoltage Power Supply (HVPS) provides power for the cold clamp. Dimming circuitry is provided to control the lamp's brighThe heaters (LCD and lamp) are activated when the unit is noproper operational temperature due to cold ambient conditions

1.2 INTERNAL MONITORING

The EADI and EHSI FPDs monitor the safety and integrity of ttem operation and isolate and annunciate failures as neceAdditional monitors provide fault isolation capability to isolate fthe SRU level. Loss of power to the indicator results in a comblank indicator. Failures that result in display of misleading intion also results in a completely blank indicator. Failure condue to input data failures, indicator failure, or indicator interfaures result in annunciating the appropriate failure message indicator. All ADI and HSI failure warning flags are annunciablack text in a red box. All caution flags are annunciated as blain a yellow box.

Each 5ATI flat panel display contains an Interface Processor (a Graphics Processor (GP). The IP contains built-in-test fu

that monitor the display’s “health” on a continuous basis. Dfailures result in either annunciation to the flight crew that a failure exists or flagging the appropriate display data. Detectures are also logged in non-volatile memory for retrieval later.

Introduction

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The Graphics Processor communicates with the IP via aface and dual port memory. The GP executes its own Bdent of the IP to determine its own health status. The Gas an independent monitor of the IP and the IP independtors the GP. If the GP detects an IP failure, it shall indepeplay to the flight crew a fail status message “DU FAIL”.

Integrity of displayed data is verified using two separatFirst, random pixels in unused portions of the LCD are dGraphics Engine and the pixel location and color are wraround and compared with the bit map of the display. Mresult in displaying “DU FAIL”. Second, the IP selects a pdisplay for monitoring by instructing the GP to return a smof pixels. In the case where pitch data is monitored the hcaptured and the pixel data reconstituted by the IP to vecorrect pitch attitude was displayed. This monitoring provto-end wrap around verification of displayed critical data.

1.3 ADI/HSI FUNCTION MONITORING

Critical input data consisting of the synchro inputs of pitcheading are monitored for the following conditions and a f

displayed if any of these conditions exists:1. Invalid display data or displaying misleading d

2. Synchro input data outside “reasonable” windo

3. External data valid signal indicates "invalid".

All other input data with an associated valid signal is notthe data valid signal indicates “invalid”. Data in thincludes: Course deviation, glideslope deviation, localizeradio altitude, speed command, rate of turn, and INS/DME

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Introduction


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EADI/EHS

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2. EADI/EHSI OPERATING CONTROLS

2.1 CONTROLS

The controls consist of aBRT/DIM rocker switch, a TESTbutton, four function buttons (“N”NORM, “M” MODE, “R” RANGE,

“I” INTEGRATE), and an ambientlight sensor.

2.1.1 DISPLAY INTENSITY

Press the rocker switch on the BRT end to increase inten

and on the DIM end to decrease intensity. The switch fution is the same for both ADI and HSI.

2.1.2 TEST BUTTON

Pressing and holding the TEST button activates Self Tand displays the test modes. The function is the same both ADI and HSI. Self Test is inhibited during ILS mode.

2.1.3 FUNCTION BUTTONS

2.1.3.1 “N” NORM Button

Pressing this button always reverts the display to Norm

mode (ADI or HSI).

2.1.3.2 “M” MODE Button

This button is non-functional in ADI mode. In HSI moeach press cycles the display between NORMAL, ARC, WWX+MAP , and MAP . Italicized modes are not currenactive.

DIM

TEST

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Figure 2-1FPI Bezel

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EADI/EHSI Operation


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2.1.3.3 “R” RANGE Button

This button is non-functional in ADI mode. In HSI mode,pressing this button changes ranges in MAP mode.

2.1.3.4 “I” INTEGRATE Button

Pressing this button activates the “Integrate” display mode.Exit this mode by pressing the NORM button.

2.1.4 AMBIENT LIGHT SENSOR

Not operational.

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3. EADI/EHSI DISPLAYS

3.1 EADI DISPLAYS

3.1.1 PITCH ATTITUDE

A moving white simulated horizonline rotates angularly with the roll

of the aircraft and moves up anddown with pitch of the aircraft.Blue sky above the horizon andblack ground below the horizonalign with the horizon line as it fol-lows the aircraft's pitch and roll.Pitch scale reference marksextend above and below the hori-zon line indicating 2.5° incre-ments within ±30° of the horizonline and 20°increments from 40°to 80°from the horizon line.

Red excessive pitch chevrons are provided between 4pitch up (on the sky background) and between 30° andown (on the ground background).

When the aircraft pitch attitude is such that the horizon lidisplay, a small portion (eyebrow) of sky or ground will recate the direction of minimum pitch correction to return to

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Figure 3.1-Normal Attitude D

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Figure 3.1-2 Excessive Pitch Up Display

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Figure 3.1Excessive Pitch Do

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EADI/EHSI Displays


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3.1.2 ROLL ATTITUDE

A white stationary roll scale withan orange zero degree index pro-vides the reference for the bankangle pointer. The white skypointer moves in relation to theroll scale to indicate degrees ofaircraft right or left bank. Thefixed scale is marked at 10, 20,30, 45, 60, and 90 degrees, with the 30, 60 and 90 degree being thicker and longer to allow easier recognition. The 90°also serve as the center position on the speed command and lope scales.

3.1.3 SYMBOLIC AIRCRAFT

Located in the center of the display is thefixed yellow aircraft symbol with a black dotat the center. The pitch and roll attitudes ofthe aircraft are displayed by the relationship of the fixed symbocraft and the movable horizon. The symbolic aircraft is flown tothe command cues of the flight director.

3.1.4 SPLIT CUE FLIGHT DIRECTOR

The split cue flight director is representedby vertical and horizontal magenta bars inthe center of the EADI display about thefixed aircraft symbol. The command barsappear to move in front of the yellow air-craft symbol but behind the black dot. Thehorizontal bar provides pitch commandsand the vertical bar provides roll com-mands. The bars are independently drivenand can indicate pitch only, roll only, orcombined pitch and roll commands. The flight director commansatisfied by flying the center black dot of the symbolic aircraftintersection of the flight director command bars. The selectionsame flight director computer by both Captain and First Ofannunciated by an “FD” (black text in a yellow circle). The anntor and the command bars are removed from the display whflight director mode is not active.

The decrab symbol is presented as a white “V” above the syaircraft. The decrab symbol slides left or right along the wingssymbolic aircraft to indicate the rudder command.

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Figure 3.1-4

Roll Attitude

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Figure 3.1-5Symbolic Airc

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Figure 3.1-6Flight Directo

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3.1.5 RATE OF TURN

A white stationary rate of turn scale pro-vides the reference for the rate of turnpointer. A standard rate turn (3degrees/second) is indicated by the pointeraligning directly under the left or rightindex.

3.1.6 SPEED COMMAND

A stationary white vertical scale located on theleft side of the EADI is the reference for thefast-slow pointer (orange circle). The speedcommand circle indicates deviation from theselected speed. Full scale deflection indicates10 knots above or below the target airspeed.

3.1.7 GLIDESLOPE INDICATOR

A white stationary dotted vertical scale locatedon the right side of the indicator is the refer-ence for the glideslope deviation pointer (whitetriangle). The glideslope pointer indicates thecenter of the glideslope with respect to theactual aircraft position.

3.1.8 RISING RUNWAY

A green runway symbol representing theairport runway moves laterally in relation toa white expanded localizer deviation scale.

The lateral deviation indicates the aircraftposition with respect to the localizer center-line. The runway symbol rises linearly toindicate radio altitude below 200 feet. Therunway begins to rise at 200 feet andtouches the bottom of the aircraft symbol atzero feet of radio altitude.

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3.1.9 DECISION HEIGHT (DH) ANNUNCIATION

A yellow circle with “DH” in black isdisplayed when the set decision heightis reached. The annunciator does notflash.

3.1.10 FLIGHT DIRECTOR (FD)

ANNUNCIATIONA yellow circle with “FD” in black is dis-played when the same Flight Directoris selected by both Captain and FirstOfficer. The annunciator does notflash.

3.1.11 ADI FAILURE ANNUNCIATIONS

External sensor systems failures are annunciated in black texta red box. Up to six different failures are displayed:

GYRO Attitude system failures. The bank angle pointer, pitch horizon line and black ground are removed from the di

FD Flight Director system failures. The command bar causthe invalid condition will be displayed as folows: PitchCommand Bar - Full Down, Roll Comand Bar - Full RigDecrab Symbol - Full Left

GS Loss of Glideslope Valid during ILS Approach mode. Tglideslope scale and pointer are removed from the disp

R/T Rate of Turn invalid. The rate of turn scale and pointerremoved from the display.

RWY Loss of LOC Valid or Radio Altitude Valid during ILSApproach mode. The localizer scale and runway symbremoved from the display.

SPD Loss of Speed Command Valid. The speed comand sc

and circle are removed from the display.

Dual installations perform cross-side monitoring and displayside failures in a yellow box in the lower right corner of the Aplay. For the failure to be displayed, 1) the cross-side sensormust have been displayed on the cross-side display for at leaseconds, or 2) the cross-side HSI has failed. A black numbcates the station where the failure occurred. A red “X” annuncithe yellow box indicates that the cross-side status has no

EADI/EHSI Displays


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20 DH GS

Figure 3.1-11Decision Height Annu

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Figure 3.1-12 Flight Director Annun

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Figure 3.1-13 ADI Sensor Failure Annunciation

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Figure 3.1-14 ADI Cross-side Monotor Annunciation

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received for at least two seconds. All ADI failure flags flash forsix seconds upon initial display, then become steady indication

3.1.12 COMPARATOR MONITOR ANNUNCIATIONS

These annunciations are only presented when configure“HDG” annunciation indicates a difference exists betweCaptain and First Officer headings. Likewise, “PIT” and “RO

cate a difference between the pitch or roll respectively on eacraft side. The “GS”, “LOC” and “ALT” annunciations are not tional at this time. The “MON” annunciation indicates a monitorcondition exists such that comparison of cross-side informatinot be performed.

NOTE: The comparator monitor annunciations will appear self-test if they are configured for display. They will not appearare not configured.

3.1.13 ADI QUICK REFERENCE

The following foldout pages provide a quick guide to the ADI di

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Airplane Symbol andHorizon BarAirplane attitude is indicatedby the position of the fixedaircraft symbol with respectto the movable horizon bar.

Runway and Runway Extension IndicatorIndicates lateral displacement of the aircraft from thview only when a localizer is tuned. On backcoursethe runway indicator gives reverse indications. The ruwill rise vertically to indicate radio altitude from 200 feeteach mark on the rising runway represents 100 feet

Command BarsThe vertical bar indicates the roll correctiomake to maintain a selected heading or cbar indicates the pitch correction the aircraaltitude, pitch, or to track the glideslope. Bflight director mode is commanded by a

Speed Command Circleand ScaleCircle moves up or downthe scale to indicatedeviation from selectedairspeed.

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Sky

Flight Director (FD)AnnunciationIndicates when same flightdirector computer is drivingcommand bars on bothCaptain and FO sides.

Figure 3.1-15 Normal ADI Quick Reference

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AEADI/EHSI Displays



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Figure 3.1-16 Excessive Pitch ADI Quick Reference

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AEADI/EHSI Displays



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3.2 EHSI DISPLAYS

The EHSI is capable of displaying five different presentahorizontal situation. The Mode (M) button cycles the dispNormal, ARC, Wx, Wx + MAP, and MAP modes. The Wxnot currently implemented.

3.2.1 NORMAL HSI DISPLAY

3.2.1.1 Azimuth Card

A 360 degree rotating whiteazimuth card indicates aircraftheading referenced to a whiterectangular box with a triangularheading index mark (lubber line)protruding from the bottom. Theheading index box is shown atthe top center of the azimuthcard, and contains digital headingin integer degrees (0 thru 359).The heading is shown with

respect to True or Magneticnorth, and a blue “TRU” abovethe heading index box indicatesthe current reference. A fixedwhite symbolic aircraft in the cen-ter of the azimuth card indicatesthe aircraft’s relationship to the horizontal situation dazimuth card is divided into five degree increments, degree divisions being longer to help with identification oheading. Fixed 45 degree markers (white triangles) arearound the outside of the azimuth card.

3.2.1.2 Navigation Source Annunciation

The navigation system selected by theflight crew is annunciated in white in thelower left corner of the display. Three navi-gation sources are possible: ILS, VOR, orNAV. Up to three of each system can beannunciated (e.g. NAV1, NAV2, NAV3).

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Figure 3.2-Normal HSI Dis

IL

FigureNavigatio

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3.2.1.3 Selected Heading

An orange notched heading bug is manual-ly rotated around the azimuth card by anexternal heading select knob. The headingbug indicates selected heading, and onceset, rotates with the azimuth card.

3.2.1.4 Selected Course A white selected course pointer is manual-ly rotated around the azimuth card by anexternal course select knob. The pointerindicates the desired navigation course,and once set, rotates with the azimuthcard. When the primary navigation sourceis an INS (NAV annunciated) desired trackfrom the INS is used to position the coursepointer.

3.2.1.5 Course Deviation Display

The course deviation scale (five whitedots) provides a reference for the coursedeviation bar. The course deviation bar isthe center bar of the selected coursepointer. The course deviation bar indicatesthe centerline of the selected navigationcourse or localizer course in relation to thesymbolic aircraft. The course deviationscale and pointer rotate with the azimuthcard when set.

3.2.1.6 Bearing Pointer(s)

Not currently implemented.

Figure 3.2-3Selected Headin

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Figure 3.2-4Selected Course P

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Figure 3.2-5Course Deviation D

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3.2.1.7 Distance Display

Two white alphanumeric distance displays provide the nautical miles from the aircraft to the selected DME or VOtion in the standard navigation mode(DME), or distance to a waypoint in theINS mode. The distance source is annun-ciated above its respective distancevalue. If distance data is invalid, the dis-tance value is replaced by dashes. Whendistance data is missing, the entire dis-ance display is removed. DME distanceis shown as XXX.X from 0.0 thru 399.9NM. INS/LNAV distance is shown asXXX.X from 0.0 thru 999.9 and as XXXXfor 1000 NM and above.

3.2.1.8 To/From Display

An orange arrowhead near the center ofthe azimuth card pointing towards thehead of the course pointer represents the“TO” indication, pointing towards the tailof the course pointer represents the“FROM” indication. The arrowhead pointstoward the navigation station or waypoint,indicating whether the current selectedcourse is TO or FROM the navigationstation or waypoint.

3.2.1.9 Glideslope Display

A white stationary dotted vertical scale locatedon the right side of the indicator is the refer-ence for the glideslope deviation pointer (whitetriangle). The glideslope pointer indicates thecenter of the glideslope with respect to theactual aircraft position.

3.2.1.10 Drift Angle Display


3.2.1.11 Ground Speed Display


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Figure Invalid Distan

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3.2.2 ARC HSI DISPLAY

The ARC format provides for dis-play of weather radar data (notcurrently supported) and providesincreased resolution of the dis-played navigation data due to theenlarged scale.

3.2.2.1 Azimuth Card

The azimuth card functions thesame as in normal HSI mode,except only 45 degrees on eitherside of the current heading is visi-ble.

3.2.2.2 Navigation Source Annunciation

Same as Normal mode.

3.2.2.3 Selected Heading

Same as Normal mode, except that whenthe heading bug moves off the visiblescale, a small orange heading bug symbolis displayed above the right or left edge ofthe azimuth scale to indicate its actual loca-tion.

3.2.2.4 Selected Course

Same as Normal mode, except the lowerportion of the pointer is out of view andwhen the pointer moves off the visiblescale, a small white selected course arrowsymbol is displayed above the right or left

edge of the azimuth scale to indicate itsactual location.

3.2.2.5 Course Deviation Display


3.2.2.6 Bearing Pointer(s)


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Figure 3.2-11ARC HSI Display

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Figure 3.2-1Selected Headin

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Figure 3.2-13Selected Course P

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3.2.2.7 Distance Display


3.2.2.8 To/From Display


3.2.2.9 Glideslope Display Same as Normal mode.

3.2.2.10 Drift Angle Display


3.2.2.11 Ground Speed Display


3.2.3 MAP HSI DISPLAY

The MAP format provides for increased resolution of th

navigation data due to the enlarged scale. It also provinformation. The MAP mode display is the same as ARCnoted in the following paragraphs.

3.2.3.1 Range Rings

The azimuth card forms the outerrange ring. The inner range ringrepresents half the distance to theouter range ring. The half-rangedistance is annunciated at thebottom right end of the inner ring.The full map range is annunciat-ed in the lower left corner of the

display, directly under the modeannunciation. Currently, the rangeis annunciated as dashes only.

3.2.3.2 MAP Waypoints


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Figure 3.2-1MAP Displa

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3.2.4 WX DISPLAY


3.2.5 WX + MAP DISPLAY


3.2.6 HSI FAILURE ANNUNCIATIONSExternal sensor systems failures are annunciated in black texta red box. Up to three different failures are displayed:

HDG Loss of Compass or Heading Valid. The digital headremoved from the display, but the compass card remon the display. See Special Considerations section.

NAV Loss of Course Deviation Valid. The deviation bar anor VOR scale are removed from the display. The to/from arror ILS also removed from the display if the navigation sourc

NAV or VOR.

GS Loss of Glideslope Valid during ILS Approach modeglideslope scale and pointer are removed from the d

An additional annunciation of“ALERT” is provided when anINS waypoint is approached.A red “X” annunciation in theyellow cross-side failure boxindicates that the cross-sidestatus has not been receivedfor at least two seconds. AllHSI failure flags flash for fourto six seconds upon initial dis-play, then become steadyindications.

NOTE: The only cross-side

failure annunciated by a normal HSI (Integrate mode not active) is the red “X” indicating the loss of cross-side information. With Integrate mode active, an HSI will display thecross-side failure information provided by an ADI.

3.2.7 HSI QUICK REFERENCE

The following foldout pages provide a quick guide to the HSI di

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NAV 1

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Figure 3.2-15 HSI Sensor Failure Annuncia

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Airplane SymbolIndicates aircraft relationshipto the horizontal display.

Navigation SourceIndicates the navigationsource selected to drive the

HSI course deviation.Possible annunciations are"NAV", "VOR" or "ILS".

Digital Heading Readoutand Lubber MarkIndicates digital value of magnetic ortrue heading from the selected navigationsystem. Lubber mark indicates headingof aircraft on compass card.

Distance ReadoutIndicates distance in nauticalmiles from the selected DMEor waypoint according tonavigation system 1.

Heading BugIndicates selected headingon the compass card. Thebug is set via an externalheading select knob. Onceset, the bug rotates with the

compass card to providecontinuous indication of theselected heading.

Figure 3.2-16 Normal HSI Quick Reference

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ARC


Navigation SourceIndicates the navigationsource selected to drive theHSI course deviation.



Heading BugIndicates selected headingon the compass card. Thebug is set via an externalheading select knob. Onceset, the bug rotates with the

compass card to providecontinuous indication of theselected heading.

HSI Display ModeIndicates ARC or MAPdisplay.

Figure 3.2-17 ARC HSI Quick Reference

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ARC

Selected Course Arrow

Indicates selected course onthe compass card. The arrowis set via an external courseselect knob. Once set, thearrow rotates with thecompass card to providecontinuous indication of theselected course.

Course Pointer LocatorIndicates to which side thecourse pointer is closest.

Figure 3.2-18 Off-Scale ARC HSI Quick Reference

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MAP

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Navigation SourceIndicates the navigasource selected to drHSI course deviation



Heading BugIndicates selected headingon the compass card. Thebug is set via an externalheading select knob. Onceset, the bug rotates with thecompass card to provide

continuous indication of theselected heading.

HSI Display ModeIndicates ARC or MAPdisplay.

Full-Range AnnunciatorIndicates the full map rangeselected. The azimuth scalerepresents the full rangering. Currently indicatesdashes only.

Figure 3.2-19 MAP HSI Quick Reference

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3.3 INTEGRATE MODE

The EADI and the EHSI both canprovide the Integrated display asa reversionary mode, and theintegrated display is identical oneither an ADI or HSI. The ADIand HSI display functions are thesame as they would be on an ADIor HSI alone, except that the rateof turn display and the rising run-way are not displayed, and theto/from pointer is duplicated onboth sides of the symbolic air-craft. Off scale symbols (headingbug and course pointer) are dis-played as in the ARC HSI mode.

On a display configured as anADI, a pitch value of more than 23 degrees up or down will rthe display reverting to the ADI presentation. The display wautomatically return to Integrate mode when pitch value is reduless than 23 degrees. The Integrate mode must be manually

lected. On a display configured as an HSI, pitch value docause the display to revert to HSI mode.

3.3.1 INTEGRATE MODE FAILURE ANNUNCIATIONS

External failures are annumci-ated in the same way as onthe ADI and HSI, except“RWY” and “R/T”, becausethe rising runway and the rateof turn indicator are notshown on the integrate dis-play.

3.3.2 INTEGRATE MODEQUICK REFERENCE

The following foldout pagesprovide a quick guide to theIntegrate Mode displays.

EADI/EHSI Displays


A

DIM

TEST

BRT

10

2020

10

55

55

1010

2020

F

S

FD DH

0 3 3

3 0

2 7 9

6

3 TRU

NAV 1

Figure 3.3-1Integrate Display

DIM

TEST

BRT

0 3 3

3 0

2 7 9

6

3

S

P

D

GYRO

FD

HDG

NAV2

ALERT

MON


ALT

Figure 3.3-2 Integrate Mode Failure Annunc

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A


EADI/EH

Rev. 0

Jan/97

DIM

TEST

BRT

F

S

F

Airplane Symbol andHorizon BarAirplane attitude is indicated

by the position of the fixedaircraft symbol with respectto the movable horizon bar.

Command BarsThe vertical bar indicates the roll correctiomake to maintain a selected heading or cbar indicates the pitch correction the aircra

altitude, pitch, or to track the glideslope. Bflight director mode is commanded by a

Speed Command Circleand ScaleCircle moves up or downthe scale to indicatedeviation from selectedairspeed.

SkyA small amount of sky willalways be shown if at thetop of the ADI, even if thepitch exceeds viewablelimits of the sky.

GroundA small amounthe ADI, even The eyebrow othe bottom.

Flight Director (FD)AnnunciationIndicates when same flight

director computer is drivingcommand bars on bothCaptain and FO sides.

IN

12

Figure 3.3-3 Integrate Mode ADI Quick Reference

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AEADI/EHSI Displays



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A


EADI/EH

Rev. 0

Jan/97

DIM

TEST

BRT

F

S

FD

NA

Course Deviation Indicates the centenavigation course aircraft symbol.

Navigation SourceIndicates the navigation

source selected to drive theHSI course deviation whichis also displayed on the ADIin Integrate Mode.

Lubber MarkIndicates heading of aircrafton compass card.

Heading BugIndicates selected headingon the compass card. Thebug is set via an externalheading select knob. Onceset, the bug rotates with thecompass card to providecontinuous indication of theselected heading. Whendriven out of view, a smallheading bug is displayedover the right or left end ofthe azimuth card to showthe location.

Distance ReadoutIndicates distance in nauticalmiles from the selected DMEor waypoint according to

navigation system 1.

INS1

123

ALERT

Alert AnnunciatorIndicates that an INSwaypoint is beingapproached.

Figure 3.3-4 Integrate Mode HSI Quick Reference

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AEADI/EHSI Displays



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4. SPECIAL CONSIDERATIONS

4.1 NAVIGATION SOURCE COMBINATIONS

During approach mode (a valid ILS frequency selectedEADI will display a glideslope scale with pointer and a risWhen displayed, the glideslope pointer position is alwaysby the on-side glideslope receiver. The lateral position of

is always determined by the on-side localizer and the vtion of the runway is always determined by the on-side rter. Cross-side and other sensors are never used, therefno need to identify these sensor sources. During enrouvalid ILS frequency is not selected) the glideslope scale symbol are removed from the EADI display.

The navigation sources used to position the course devithe EHSI are identified since three sources are possannunciated as “NAV”, VOR is annunciated as “VOR” andannunciated as “ILS”. The glideslope scale with poindetermined by the glideslope receiver is also displayecourse deviation bar is driven by the localizer receiver annunciated as the navigation source. The glideslope

pointer are removed from display on the EHSI when tsensor is “VOR” or “NAV”.

When Integrate mode is selected on an EADI, the navigaused to position the course deviation bar on the integratedmatch that selected for use on the associated EHSI. Thtion sources are identified with the same annunciations EHSI.

Some aircraft installations allow independent selection osensors for the EADI and EHSI. This can result in unexpenations of sensors between the two displays and also EADI display with the Integrate mode selected. For expresence of a glideslope scale and pointer on an EADI mode does not insure that the course deviation bar on thplay is driven by the localizer. The actual navigation sourdeviation may be NAV, VOR or ILS as selected for thecorrect navigation source is annunciated in all cases aused to avoid confusion. All the possible combinations athe following figures.

Special Con

Rev. 0

Jan/97

A

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Special Considerations


A

DIM

TEST

BRT

N

M

R

I

DIM

TEST

BRT

DIM

TEST

BRT

N

M

R

I

DIM

TEST

BRT

10

2020

10

55

55

1010

2020

F

S

0 3 3

3 0

2 7 9

6

3 TRU

NAV 1

INS1

1234I

13

10

2020

10

55

55

1010

2020

F

S

0 3 3

3 0

2 7 9

6

3 TRU

NAV 1

INS1

1234INS2

1324

ADI ENROUTE ADI APPROAC

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000 TRU

NAV 1

INS1

1234I

1

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000 TRU

NAV 1

INS1

1234INS2

1324

Figure 4.1-1HSI on NAV (INS)

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Special Con

Rev. 0

Jan/97

A

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N

M

R

I

DIM

TEST

BRT

DIM

TEST

BRT

N

M

R

I

DIM

TEST

BRT

10

20

10

55

55

1010

20

F

S

0 3 3

3 0

2 7

3

VOR 1

INS1

1234

10

2020

10

55

55

1010

2020

F

S

0 3 3

3 0

2 7 9

6

3

VOR 1

INS1

1234INS2

1324

ADI ENROUTE ADI APPRO

0 3 3

3 0

2 7

2 4

2 1 5

3

1 8

000

VOR 1

INS1

1234

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000

VOR 1

INS1

1234INS2

1324

Figure 4.1-2 HSI on VOR

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A

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TEST

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N

M

R

I

DIM

TEST

BRT

DIM

TEST

BRT

N

M

R

I

DIM

TEST

BRT

10

2020

10

55

55

1010

2020

F

S

0 3 3

3 0

2 7 9

6

3

ILS 1

INS1

1234I

13

10

2020

10

55

55

1010

2020

F

S

0 3 3

3 0

2 7 9

6

3

ILS 1

INS1

1234INS2

1324

ADI ENROUTE ADI APPROAC

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000

ILS 1

INS1

1234I

1

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000

ILS 1

INS1

1234INS2

1324

I L S

I L S

GS

Figure 4.1-3 HSI on ILS

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4.2 HEADING FAILURE

Invalid heading is indicated by replacing the digital headwith a red “HDG” flag. The compass card will continueplayed and will rotate in response to the heading signal the EHSI. If the heading signal is not received by the EHSpass card will freeze at the last valid value for heading anflag will be in view.

When the “HDG” flag is displayed, the positions of the seling bug and selected course arrow should not be trusbecause heading is used to generate the selected hselected course signals received by the EHSI, and thheading at that location (outside the EHSI) is unknown.

Special Con

Rev. 0

Jan/97

A

Figure 4.2-1Heading Failure Flag

DIM

TEST

BRT

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

G

ILS 1

INS1

1234INS2

1324

HDG

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4.3 SELECTED COURSE FAILURE

If selected course is not received by the EHSI, the selected arrow head and tail are removed from the display and the deviation scale is fixed in a horizontal position (selected defaults to aircraft heading). The to/from arrow will continue to played if the to/from signal is still received from the selected ntion source. The to/from arrow and course deviation may be in

since the selected course used by the navigation source (if unknown.

4.4 SELECTED HEADING FAILURE

If selected heading is not received by the EHSI, the selected hbug is removed from the display.



A

Figure 4.3-1Selected Course Failure Flag

DIM

TEST

BRT

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000

VOR 1

INS1

1234INS2

1324

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5. OPERATING INSTRUCTIONS

Consult Aircraft Flight Manual Supplement for specific and limitations in operation.

5.1 START UP

When power is initially applied to

the EADI/EHSI system, variousflags may be annunciated on thedisplays, representing systemsnot yet operational. If all flags donot clear, then recheck theannunciated system.

Adjust brightness control on theEADI and EHSI to desired bright-ness.

5.2 SELF TEST

Performing the Self Test is notrequired at any time. If a failure was to occur or existwould be annunciated. This test is intended to familiarize with the various flagging methodology used and a quicproper color presentation.

Self Test is inhibited during ILS mode if both glideslope aare valid.

Operating

Rev. 0

Jan/97

A

DIM

TEST

BRT

Figure 5.1-Bezel

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5.2.1 ADI SELF TEST

Press and hold the TEST button on the ADI to initiate the threees of self test. Release of the button will cause the previous disreturn, unless BIT test is in progress, in which case the test wiplete, then the display will return.

Phase 1 - A static display that imitates the electromechanical sfor five seconds.

• No failure flags displayed

• Attitude - 10°pitch up, 20°right roll

• Flight Director - Full scale (16.7°) pitch up, full scale (16.7°) rig

• Rudder Command - Full scale right

• Glideslope - Centered

• Speed Command - Centered

• Rate of Turn - Centered

• Rising Runway - Centered laterally, 100 feet radio altitude

Phase 2 - All failure and warning flags flashing for five seconds

• Ground - Decluttered

• Pitch Scale - Decluttered

• Roll Sky Pointer - Decluttered

• SPD, GYRO, GS, R/T, RWY flags

• FD light - On steady

• DH light - On steady

• CM annunciations - Appear only if configured

• All flags except FD and DH flashing

Phase 3 - Steady flags displayed while internal BIT test perform

Same as Phase 2 except flags remain on steady

Operating Instructions


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Operating

Rev. 0

Jan/97

N

M

R

I

DIM

TEST

BRT

1 0

2 0

2 0

1 0 5

5

3 0

3 0

5

5 1 0

1 0

F

S

GS

TEST

MON

Figure 4.1-2 ADI Self Test Phase 1

N

M

R

I

DIM

TEST

BRT

TEST

FD DH

2

MON


ALT

S

P

D

GYRO

FD

RWY

R/ T

G

S

Figure 4.1-3 ADI Self Test Phase 2 & 3

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5.2.2 HSI SELF TEST

Press and hold the TEST button on the HSI to initiate the threees of self test. Release of the button will cause the previous disreturn, unless BIT test is in progress, in which case the test wiplete, then the display will return.


• No failure flags displayed

• Compass Card - 0°(north), digital heading “000”

• Source/Distance Display - INSX/3999; or DMEX/399.9 if avaiif not available, then blank

• Glideslope - Centered

• Selected Course - 90°

• Lateral Deviation - Centered

• TO/FROM - Both displayed

• Heading Bug - 180°

If ARC or MAP mode:

•Off Scale Symbols - Both heading bug and course pointer disp


• Source/Distance Display - Decluttered

• Selected Course - Decluttered

• Lateral Deviation - Decluttered

• TO/FROM - Decluttered

• Heading Bug - Decluttered

• Digital Heading/Lubber Mark - Decluttered





A

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A


Operating

Rev. 0

Jan/97

N

M

R

I

DIM

TEST

BRT

0

3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

000

GS

NAV 1

INS1

3999INS2

3999

TEST

Figure 4.1-4 Normal HSI Self Test Phase 1

N

M

R

I

DIM

TEST

BRT

0 3 3

3 0

2 7

2 4

2 1 1 5

1 2

9

6

3

1 8

NAV 1

HDG

G

S

NAVALERT

TEST

Figure 4.1-7 Normal HSI Self Test Phase 2 & 3

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5.2.3 INTEGRATE MODE SELF TEST

Press and hold the TEST button on the ADI/HSI to initiate thphases of self test. Release of the button will cause the previoplay to return, unless BIT test is in progress, in which case twill complete, then the display will return.


• No failure flags displayed• Compass Card - 0°(north)

• Source/Distance Display - INSX/3999; or DMEX/399.9 if avaiif not available, then blank

• Glideslope & Later al Deviation - Centered

• Selected Course - 90°

• TO/FROM - Both displayed

• Heading Bug - 180°(out of view)

• Off Scale Symbols - Both heading bug and course pointer dis

• Attitude - 10°pitch up, 20°right roll

• Flight Director - Full scale (16.7°) pitch up, full scale (16.7°) rig

• Rudder Command - Full scale right

• Glideslope & Speed Command - Centered


• Source/Distance Display - Decluttered

• Selected Course & Lateral Deviation - Decluttered

• TO/FROM - Decluttered

• Heading Bug - Decluttered

• Lubber Mark - Decluttered

• Ground - Decluttered

• Pitch Scale - Decluttered

• Roll Sky Pointer - Decluttered

• SPD, GYRO, GS, R/T, RWY flags

• FD light - On steady

• DH light - On steady

• CM annunciations - Appear only if configured

• All flags except FD and DH flashing





A

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A


Operating

Rev. 0

Jan/97

N

M

R

I

DIM

TEST

BRT

1 0

2 0

2 0

1 0 5

5

3 0

3 0

5

5 1 0

1 0

F

S

GS

TEST

0 3 3

3 0

2 7 9

6

3

NAV 1

INS1

1234INS2

1324

Figure 4.1-10 Integrate Mode Self Test Phase 1

N

M

R

I

DIM

TEST

BRT

TEST

0 3 3

3 0

2 7 9

6

3

FD DH

NAV 1

S

P

D

GYRO

FD

HDG

NAV

G

S

2

ALERT

Figure 4.1-11Integrate Mode Self Test Phase 2 & 3

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5.3 LIMITATIONS

For information on EADI/EHSI system operating limitations, refer to the approved Flight Manual Supplement for the particucraft in question.

5.4 EMERGENCY PROCEDURES

For information on EADI/EHSI system emergency proceplease refer to the approved Flight Manual Supplement for theular aircraft in question.



A

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Maintenance Mo

Rev. 0

Jan/97

A

6. MAINTENANCE MODE DISPLAYS

The maintenance mode provides access to the displaoperating parameters and fault status. The maintenancebe accessed by pressing the TEST and Integrate (I) buttneously. Data is displayed on multiple pages. The “Neselected using the Range (R) pushbutton. The last paround to the first page. Pressing the Normal (N) butto

maintenance mode. The maintenance mode is inhibitedILS mode if glideslope and localizer are both valid.

NOTE: The maintenance pages are intended to aid trouon the ground. They are not intended for use in flight.

The first maintenance page contains the current softwaremod level, unit serial number, and part number, as AlliedSignal copyright information. Page 2 begins the unparameters. The following maintenance pages shall be di

• FPI-3501B MAINTENANCE

• DU OPERATING PARAMS

• DU STATUS

• DU BEZEL STATUS

• DU INTERFACE STATUS






• DU CALIBRATION DATA

• WHITE FLAT FIELD TEST PATTERN• RED FLAT FIELD TEST PATTERN

• GREEN FLAT FIELD TEST PATTERN

• BLUE FLAT FIELD TEST PATTERN

• BLACK FLAT FIELD TEST PATTERN

• GRAY SHADES FOR WHITE, RED, GREEN, BLUE

• WATCHDOG TIMER TEST

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Maintenance Mode Displays


A

6.1 MAINTENANCE PAGE 1

The following is the definition ofthe states for the page:

Parameter States

A/C TYPE B-727/DC-10

A/C SIDE CAPT/FO

DISPLAY TYPE ADI/HSICM ANNUN ON/OFF

FD CMD IN VIEW HI/LO

PITCH CMD 150/120

ROLL CMD 150/66



Parameter States

LAMP HEATER ON/OFF

LCD HEATER ON/OFF

A red flashing “FREEZE” annun-ciation indicates that the statusannunciations are static with noupdate, frozen by pressing theMode (M) button.

DIM

TEST

BRT

DU OPERATING PARAMS PG

INTERNAL TEMPERATURE 38

EXTERNAL LIGHT LEVEL

DISPLAY BRIGHTNESS 25.46

BURST CONTROL OUTPUT 23.50

DIM/HV OUTPUT 0.00

LAMP HEATERLCD HEATER

TOTAL POWER CYCLES

TOTAL TIME 64 H

POWER CYCLE TIME 0 HRS 11 M

Figure 5.2-1Maintenance Page 2

TEST FREEZE

Figure 6.2-2 Frozen Maintenance Pag

DIM

TEST

BRT

FPI-3501B MAINTENANCE PG

COPYRIGHT

ALLIEDSIGNAL AVIONICS INC. 1995

SW RELEASE 01/2H ID 1230960925

BOOT RELEASE 01/02

S/N 0021

P/N 066-50017-0101

INSTALL/CONFIGURATION OPTIONS

A/C TYPE DC-10 A/C SIDE CAPT

DISPLAY TYPE HSI

CM ANNUNCIATIONS OFF

FD CMD IN VIEW HI

PITCH CMD 150

ROLL CMD 150


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Parameter States

LAMP REPLACE/

PASS/FAIL

IP, GP,ETC. PASS/FAIL



Parameter States

PUSHBUTTON 0/1

NOTE: Remember, if you are testing the buttons, that pressing the R button will advance to the next page, and pressing the N

button will exit the maintenance mode.

Maintenance Mo

Rev. 0

Jan/97

A

DIM

TEST

BRT

DU BEZEL STATUS

BRT PUSHBUTTON

DIM PUSHBUTTON

N PUSHBUTTON

M PUSHBUTTON

R PUSHBUTTON

I PUSHBUTTONTEST PUSHBUTTON

Figure 6.4-Maintenance Pa

DIM

TEST

BRT

DU STATUS

LAMP

IP

GP

POWER SUPPLY

DIMMER/LCD

I/O #1

I/O #2

BEZEL


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Parameter States

429 TX/RX ACTIVE/

INACTIVE

561/568 RX ACTIVE/ INACTIVE

SYNCHRO ANGLE

DATA

VALUE



Parameter States

DISCRETE HI HI/OPEN

DISCRETE LO OPEN/LO



A

DIM

TEST

BRT

DU INTERFACE STATUS PG

DISCRETE HI INPUT 0

DISCRETE LO INPUT 0

DISCRETE HI INPUT 1

DISCRETE LO INPUT 1

DISCRETE HI INPUT 2

DISCRETE LO INPUT 2

DISCRETE HI INPUT 3

DISCRETE LO INPUT 3

DISCRETE HI INPUT 4DISCRETE LO INPUT 4

DISCRETE HI INPUT 5

DISCRETE LO INPUT 5


DIM

TEST

BRT


429 TX INACT

429 RX 1 INACT

429 RX 2 INACT

561/568 RX 1 INACT

561/568 RX 2 INACTSYNCHRO INPUT 1

SYNCHRO INPUT 2SYNCHRO INPUT 3

SYNCHRO INPUT 4

SYNCHRO INPUT 5


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Parameter States

DISCRETE HI HI/OPEN

DISCRETE LO OPEN/LO



Parameter States

DISCRETE OPEN/LO

Maintenance Mo

Rev. 0

Jan/97

A

DIM

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DU INTERFACE STATUS

DISCRETE INPUT 12DISCRETE INPUT 13

DISCRETE INPUT 14

DISCRETE INPUT 15

DISCRETE INPUT 16

DISCRETE INPUT 17

DISCRETE INPUT 18

DISCRETE INPUT 19


DIM

TEST

BRT

DU INTERFACE STATUS

DISCRETE HI INPUT 6

DISCRETE LO INPUT 6DISCRETE HI INPUT 7

DISCRETE LO INPUT 7

DISCRETE HI INPUT 8

DISCRETE LO INPUT 8

DISCRETE HI INPUT 9

DISCRETE LO INPUT 9

DISCRETE HI INPUT 10

DISCRETE LO INPUT 10

DISCRETE HI INPUT 11DISCRETE LO INPUT 11


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Parameter States

ANALOG DATA Value



Parameter States

DISCRETE OUT HI/LO



A

DIM

TEST

BRT


DISCRETE OUTPUT 0

DISCRETE OUTPUT 1

DISCRETE OUTPUT 2

DISCRETE OUTPUT 3DISCRETE OUTPUT 4

DISCRETE OUTPUT 5

DISCRETE OUTPUT 6

DISCRETE OUTPUT 7


DIM

TEST

BRT


ANALOG CHANNEL 0 -.02


ANALOG CHANNEL 2 -1.13

ANALOG CHANNEL 3 -1.13



ANALOG CHANNEL 6 .01


ANALOG CHANNEL 8 .00ANALOG CHANNEL 9 -1.97

ANALOG CHANNEL 10 1.27

ANALOG CHANNEL 11 1.30


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Parameter States

ANALOG DATA Value

The LIS data displayed may beeither current or stored non-volatile data, selected by press-ing the Integrate (I) button. Thecurrent values will alternatebetween frozen and real time bypressing the Mode (M) button.

Maintenance Mo

Rev. 0

Jan/97

A

DIM

TEST

BRT

DU CALIBRATION DATA

TEMPERATURE CORRECTE

INTERNAL TEMPERATURE

CALIBRATED LIS VALUE = 105

VCOM = 3742

T0P = 3839 T

T0N = 4 T

T1P = 1398 T

T1N = 3036 T

T2P = 1229 T

T2N = 3306 T

T3P = 1098 TT3N = 3517 T

FREEZE

CALIBRATION

POINT


Current Dat

DIM

TEST

BRT

DU CALIBRATION DATA

NON VOLATILE DATA

LIS CALIBRATION VALUE = 42

VCOM = 3824

T0P = 3839 T

T0N = 4 T

T1P = 2032 T

T1N = 2096 TT2P = 1680 T

T2N = 2448 T

T3P = 1472 T

T3N = 2704 T

CALIBRATION

POINT


Non-Volatile D

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Pages 12 - 17 are a check of theprimary colors (white, red, green,blue, black) on the display.





A

DIM

TEST

BRT


DIM

TEST

BRT


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Maintenance Mo

Rev. 0

Jan/97

A

DIM

TEST

BRT

Figure 6.14Maintenance Pa

DIM

TEST

BRT


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Pages 12 - 17 are a check of theprimary colors (white, red, green,blue, black) on the display. Thisone checks the gray shades ofwhite, red, green, and blue.



A

DIM

TEST

BRT


DIM

TEST

BRT


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This page contains “WatchdogTimer Test” information. This testis currently disabled and only dis-plays “N/D”.

Maintenance Mo

Rev. 0

Jan/97

A

DIM

TEST

BRT

WATCHDOG TIMER STATUS

N/D


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A


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Printed .2K 8/97 CW

fpd 500 efis

Documents