BendixKing FPI 3501B User Manual

FPD 500

FLAT PANEL DISPLAY SYSTEM

FOR THE DC-10

Operator’s Manual

WARNING

Information subject to the export control laws. This document, which includes any attachments and exhibits hereto, contains information subject to International Traffic in Arms Regulation (ITAR) or Export Administration Regulation (EAR) of 1979, which may not be exported, released or disclosed to foreign nationals inside or outside the U.S. without first obtaining an export license. Violators of ITAR or EAR may be subject to a penalty of 10 years imprisonment and a fine of $1,000,000 under 22 U.S.C. 2778 or Section 2410 of the Export Administration Act of 1979. Include this notice with any reproduced portion of this document.

Reproduction of this publication or any portion thereof by any means without the express written permission of AlliedSignal Commercial Avionics Systems is prohibited. For further information contact the Manager, Technical Publications; AlliedSignal Commercial Avionics Systems; 400 North Rogers Road; Olathe, Kansas 66062. Telephone: (913) 782-0400.

1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-1

1.1 System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-2

1.2 Internal Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1-2

1.3 ADI/HSI Function Monitoring . . . . . . . . . . . . . . . . . . . . . . . .1-3

2. EADI/EHSI Operating Controls . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1 Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.1 Display Intensity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.2 TEST Button . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.3 Function Buttons . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.3.1 “N” NORM Button . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.3.2 “M” MODE Button . . . . . . . . . . . . . . . . . . . . . . . . . .2-1

2.1.3.4 “I” INTEGRATE Button . . . . . . . . . . . . . . . . . . . . . .2-2

2.1.4 Ambient LIght Sensor . . . . . . . . . . . . . . . . . . . . . . . . . .2-2

3. EADI/EHSI Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-1

3.1 EADI Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-1

3.1.1 Pitch Attitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-1

3.1.2 Roll Attitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-2

3.1.3 Symbolic Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-2

3.1.4 Split Cue Flight Director . . . . . . . . . . . . . . . . . . . . . . . .3-2

3.1.5 Rate of Turn . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3

3.1.6 Speed Command . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3

3.1.7 Glideslope Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3

3.1.8 Rising runway . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-3

3.1.9 Decision Height (DH) Annunciation . . . . . . . . . . . . . . .3-4

3.1.10 Flight Director (FD) Annunciation . . . . . . . . . . . . . . . .3-4

3.1.11 ADI Failure Annunciations . . . . . . . . . . . . . . . . . . . . .3-4

3.1.12 Comparator Monitor Annunciations . . . . . . . . . . . . . .3-6

3.2 EHSI Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-11

3.2.1 Normal HSI Display . . . . . . . . . . . . . . . . . . . . . . . . . . .3-11

3.2.1.1 Azimuth Card . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-11

3.2.1.2 Navigation Source Annunciation . . . . . . . . . . . . .3-11

3.2.1.3 Selected Heading . . . . . . . . . . . . . . . . . . . . . . . . .3-12

3.2.1.4 Selected Course . . . . . . . . . . . . . . . . . . . . . . . . . .3-12

3.2.1.5 Course Deviation Display . . . . . . . . . . . . . . . . . . .3-12

3.2.1.6 Bearing Pointer(s) . . . . . . . . . . . . . . . . . . . . . . . . .3-12

3.2.1.7 Distance Display . . . . . . . . . . . . . . . . . . . . . . . . . .3-13

3.2.1.8 To/From Display . . . . . . . . . . . . . . . . . . . . . . . . . .3-13

3.2.1.9 Glideslope Display . . . . . . . . . . . . . . . . . . . . . . . .3-13

3.2.1.10 Drift Angle Display . . . . . . . . . . . . . . . . . . . . . . .3-13

3.2.1.11 Ground Speed Display . . . . . . . . . . . . . . . . . . . .3-13

3.2.2 ARC HSI Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-14

3.2.2.1 Azimuth Card . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-14

3.2.2.2 Navigation Source Annunciation . . . . . . . . . . . . .3-14

3.2.2.3 Selected Heading . . . . . . . . . . . . . . . . . . . . . . . . .3-14

3.2.2.4 Selected Course . . . . . . . . . . . . . . . . . . . . . . . . . .3-14

3.2.2.5 Course Deviation Display . . . . . . . . . . . . . . . . . . .3-14

3.2.2.6 Bearing Pointer(s) . . . . . . . . . . . . . . . . . . . . . . . . .3-14

Table of Contents

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

Table of Contents

3.2.2.7 Distance Display . . . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.2.8 To/From Display . . . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.2.9 Glideslope Display . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.2.10 Drift Angle Display . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.2.11 Ground Speed Display . . . . . . . . . . . . . . . . . . . .3-15

3.2.3 MAP HSI Display . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.3.1 Range Rings . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.3.2 MAP Waypoints . . . . . . . . . . . . . . . . . . . . . . . . . .3-15

3.2.4 Wx Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-16

3.2.5 Wx + MAP Display . . . . . . . . . . . . . . . . . . . . . . . . . . .3-16

3.2.6 HSI Failure Annunciations . . . . . . . . . . . . . . . . . . . . .3-16

3.3 Integrate Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3-24

3.3.1 Integrate Mode Failure Annunciations . . . . . . . . . . . .3-24

4. Special Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-1

4.1 Navigation Source Combinations . . . . . . . . . . . . . . . . . . . .4-1

4.2 Heading Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4-5

4.3 Selected Course Failure . . . . . . . . . . . . . . . . . . . . . . . . . . .4-6

4.4 Selected Heading Failure . . . . . . . . . . . . . . . . . . . . . . . . . .4-6

5. Operating Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-1

5.1 Start Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-1

5.2 Self Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-1

5.2.1 ADI Self Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-2

5.2.2 HSI Self Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-4

5.2.3 Integrate Mode Self Test . . . . . . . . . . . . . . . . . . . . . . . .5-6

5.3 Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-8

5.4 Emergency Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . .5-8

6. Maintenance MODE Displays . . . . . . . . . . . . . . . . . . . . . . . . . .6-1

6.1 Maintenance Page 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-2

6.2 Maintenance Page 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-2

6.3 Maintenance Page 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-3

6.4 Maintenance Page 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-3

6.5 Maintenance Page 5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-4

6.6 Maintenance Page 6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-4

6.7 Maintenance Page 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-5

6.8 Maintenance Page 8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-5

6.9 Maintenance Page 9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-6

6.10 Maintenance Page 10 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-6

6.11 Maintenance Page 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-7

6.12 Maintenance Page 12 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-8

6.13 Maintenance Page 13 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-8

6.14 Maintenance Page 14 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-9

6.15 Maintenance Page 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-9

6.16 Maintenance Page 16 . . . . . . . . . . . . . . . . . . . . . . . . . . .6-10

6.17 Maintenance Page 17 . . . . . . . . . . . . . . . . . . . . . . . . . . .6-10

6.18 Maintenance Page 18 . . . . . . . . . . . . . . . . . . . . . . . . . . .6-11

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

TEST

BRT

2020

1010

2020

FD DH

DIM

TEST

BRT

000

TRU

ILS 1

INS1

1234

INS2

1324

1. INTRODUCTION

This Pilot’s Guide is for the AlliedSignal Commercial Avionics Systems (CAS) Flat Panel Active Matrix LCD version of the 5ATI Attitude Director Indicator (ADI) and Horizontal Situation Indicator (HSI) retrofitted into various aircraft types (e.g. DC-10, B727, etc.).

Throughout this document, the terms “ADI” and “HSI” are used to identify the two primary functions of the indicator even though the indicator itself is more correctly identified as an EADI/EHSI (Electronic ADI or HSI).

The intended use of the ADI/HSI FPI is to display the aircraft's primary attitude (ADI) and to display course, heading, glideslope, etc. (HSI). The indicator replaces electromechanical ADI and HSI indicators with Active Matrix LCD technology. A single indicator (herein referred to as the "ADI/HSI") can provide the capability to function as either an Attitude Direction Indicator (ADI) or a Horizontal Situation Indicator (HSI) depending on configuration strap settings.

Introduction

Figure 1-1

Typical EADI Display

Figure 1-2

Typical EHSI Display

Reversionary mode capability is also provided so that during normal operation, in the event of a failed ADI or HSI, the other FPI has the capability to assume the function of both in the “Integrate” mode. Reversionary mode data is hard wired into each ADI and HSI as much as possible. Reversionary mode is discussed in more detail later in this document.

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

1-1

Introduction

1.1 SYSTEM DESCRIPTION

The indicator is designed for high reliability through the use of ASICs and optimized mechanical packaging. The display is a flat panel active matrix LCD with backlighting provided by a cold cathode fluorescent lamp.

A Graphics Processor (GP) module produces flight instrument symbology on the LCD display. The Interface Processor (IP) and I/O modules consists of a 32 bit microprocessor, ARINC 429 interface capability, and analog/discrete interface capability. These modules process all of the control inputs from the indicator's front bezel/controls, external ARINC 429 input data, external discrete data (includes superflags), synchro and analog data, and provides the interface to the GP module. The Low Voltage Power Supply (LVPS) provides the necessary power to all of the system’s components, while the High Voltage Power Supply (HVPS) provides power for the cold cathode lamp. Dimming circuitry is provided to control the lamp's brightness. The heaters (LCD and lamp) are activated when the unit is not at the proper operational temperature due to cold ambient conditions.

1.2 INTERNAL MONITORING

The EADI and EHSI FPDs monitor the safety and integrity of the system operation and isolate and annunciate failures as necessary. Additional monitors provide fault isolation capability to isolate faults to the SRU level. Loss of power to the indicator results in a completely blank indicator. Failures that result in display of misleading information also results in a completely blank indicator. Failure conditions due to input data failures, indicator failure, or indicator interface failures result in annunciating the appropriate failure message on the indicator. All ADI and HSI failure warning flags are annunciated as black text in a red box. All caution flags are annunciated as black text in a yellow box.

Each 5ATI flat panel display contains an Interface Processor (IP) and a Graphics Processor (GP). The IP contains built-in-test functions that monitor the display’s “health” on a continuous basis. Detected failures result in either annunciation to the flight crew that a display failure exists or flagging the appropriate display data. Detected failures are also logged in non-volatile memory for retrieval later.

1-2

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

The Graphics Processor communicates with the IP via a host interface and dual port memory. The GP executes its own BIT independent of the IP to determine its own health status. The GP also acts as an independent monitor of the IP and the IP independently monitors the GP. If the GP detects an IP failure, it shall independently display to the flight crew a fail status message “DU FAIL”.

Integrity of displayed data is verified using two separate functions. First, random pixels in unused portions of the LCD are driven by the Graphics Engine and the pixel location and color are wrapped back around and compared with the bit map of the display. Miscompares result in displaying “DU FAIL”. Second, the IP selects a portion of the display for monitoring by instructing the GP to return a small window of pixels. In the case where pitch data is monitored the horizon line is captured and the pixel data reconstituted by the IP to verify that the correct pitch attitude was displayed. This monitoring provides an endto-end wrap around verification of displayed critical data.

Introduction

1.3 ADI/HSI FUNCTION MONITORING

Critical input data consisting of the synchro inputs of pitch, roll, and heading are monitored for the following conditions and a failure flag is displayed if any of these conditions exists:

1. Invalid display data or displaying misleading data.

2. Synchro input data outside “reasonable” window.

3. External data valid signal indicates "invalid".

All other input data with an associated valid signal is not used when the data valid signal indicates “invalid”. Data in this category includes: Course deviation, glideslope deviation, localizer deviation, radio altitude, speed command, rate of turn, and INS/DME distance.

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

1-3

Introduction

This page intentionally left blank.

1-4

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

TEST

BRT

DIM

BRT

TEST

EADI/EHSI Operation

2. EADI/EHSI OPERATING CONTROLS

2.1 CONTROLS

The controls consist of a BRT/DIM rocker switch, a TEST button, four function buttons (“N” NORM, “M” MODE, “R” RANGE, “I” INTEGRATE), and an ambient light sensor.

Figure 2-1 FPI Bezel

2.1.1 DISPLAY INTENSITY

Press the rocker switch on the BRT end to increase intensity and on the DIM end to decrease intensity. The switch function is the same for both ADI and HSI.

2.1.2 TEST BUTTON

Pressing and holding the TEST button activates Self Test and displays the test modes. The function is the same for 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 Normal mode (ADI or HSI).

2.1.3.2 “M” MODE Button

This button is non-functional in ADI mode. In HSI mode, each press cycles the display between NORMAL, ARC,

WX+MAP

, and

MAP

. Italicized modes are not currently

WX,

active.

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

2-1

EADI/EHSI Operation

2.1.3.3 “R” RANGE Button

This button is non-functional in ADI 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.

In HSI mode,

2-2

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

TEST

BRT

2020

1010

2020

FD DH

DIM

TEST

BRT

1010

2020

3030

DIM

TEST

BRT

1010

2020

3030

EADI/EHSI Displays

3. EADI/EHSI DISPLAYS

3.1 EADI DISPLAYS

3.1.1 PITCH ATTITUDE

A moving white simulated horizon line rotates angularly with the roll of the aircraft and moves up and down with pitch of the aircraft. Blue sky above the horizon and black ground below the horizon align with the horizon line as it follows the aircraft's pitch and roll. Pitch scale reference marks extend above and below the horizon line indicating 2.5° increments within ±30° of the horizon line and 20° increments from 40° to 80° from the horizon line.

Red excessive pitch chevrons are provided between 40° and 90° pitch up (on the sky background) and between 30° and 90° pitch down (on the ground background).

Figure 3.1-1

Normal Attitude Display

Figure 3.1-2

When the aircraft pitch attitude is such that the horizon line is off the display, a small portion (eyebrow) of sky or ground will remain to indicate the direction of minimum pitch correction to return to level flight.

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

Excessive Pitch Up Display

Excessive Pitch Down Display

Figure 3.1-3

3-1

EADI/EHSI Displays

2020

FD DH

1010

3.1.2 ROLL ATTITUDE

A white stationary roll scale with an orange zero degree index provides the reference for the bank angle pointer. The white sky pointer moves in relation to the roll scale to indicate degrees of aircraft right or left bank. The fixed scale is marked at 10, 20,

Figure 3.1-4 Roll Attitude

30, 45, 60, and 90 degrees, with the 30, 60 and 90 degree marks being thicker and longer to allow easier recognition. The 90° marks also serve as the center position on the speed command and glideslope scales.

3.1.3 SYMBOLIC AIRCRAFT

Located in the center of the display is the fixed yellow aircraft symbol with a black dot at the center. The pitch and roll attitudes of

Figure 3.1-5

Symbolic Aircraft

the aircraft are displayed by the relationship of the fixed symbolic aircraft and the movable horizon. The symbolic aircraft is flown to satisfy the command cues of the flight director.

3.1.4 SPLIT CUE FLIGHT DIRECTOR

The split cue flight director is represented by vertical and horizontal magenta bars in the center of the EADI display about the fixed aircraft symbol. The command bars appear to move in front of the yellow aircraft symbol but behind the black dot. The horizontal bar provides pitch commands and the vertical bar provides roll commands. The bars are independently driven and can indicate pitch only, roll only, or

Figure 3.1-6

Flight Director

combined pitch and roll commands. The flight director commands are satisfied by flying the center black dot of the symbolic aircraft to the intersection of the flight director command bars. The selection of the same flight director computer by both Captain and First Officer is annunciated by an “FD” (black text in a yellow circle). The annunciator and the command bars are removed from the display when the flight director mode is not active.

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

3-2

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

1010

2020

3.1.5 RATE OF TURN

A white stationary rate of turn scale provides the reference for the rate of turn pointer. A standard rate turn (3 degrees/second) is indicated by the pointer aligning directly under the left or right index.

3.1.6 SPEED COMMAND

A stationary white vertical scale located on the left side of the EADI is the reference for the fast-slow pointer (orange circle). The speed command circle indicates deviation from the selected speed. Full scale deflection indicates 10 knots above or below the target airspeed.

3.1.7 GLIDESLOPE INDICATOR

A white stationary dotted vertical scale located on the right side of the indicator is the reference for the glideslope deviation pointer (white triangle). The glideslope pointer indicates the center of the glideslope with respect to the actual aircraft position.

EADI/EHSI Displays

Figure 3.1-7

Rate of Turn Indicator

Figure 3.1-8

Speed Command

Indicator

Figure 3.1-9

Glideslope Indicator

3.1.8 RISING RUNWAY

A green runway symbol representing the airport runway moves laterally in relation to a white expanded localizer deviation scale. The lateral deviation indicates the aircraft position with respect to the localizer centerline. The runway symbol rises linearly to indicate radio altitude below 200 feet. The runway begins to rise at 200 feet and touches the bottom of the aircraft symbol at zero feet of radio altitude.

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

Figure 3.1-10

Rising Runway

3-3

EADI/EHSI Displays

DIM

3.1.9 DECISION HEIGHT (DH) ANNUNCIATION

A yellow circle with “DH” in black is displayed when the set decision height is reached. The annunciator does not flash.

3.1.10 FLIGHT DIRECTOR (FD) ANNUNCIATION

A yellow circle with “FD” in black is displayed when the same Flight Director is selected by both Captain and First Officer. The annunciator does not flash.

3.1.11 ADI FAILURE ANNUNCIATIONS

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

GYRO Attitude system failures. The bank angle pointer, pitch scale,

horizon line and black ground are removed from the display.

FD Flight Director system failures. The command bar causing

the invalid condition will be displayed as folows: Pitch Command Bar - Full Down, Roll Comand Bar - Full Right, Decrab Symbol - Full Left

Decision Height Annunciator

Flight Director Annunciator

Figure 3.1-11

Figure 3.1-12

GS Loss of Glideslope Valid during ILS Approach mode. The

glideslope scale and pointer are removed from the display.

R/T Rate of Turn invalid. The rate of turn scale and pointer are

removed from the display.

RWY Loss of LOC Valid or Radio Altitude Valid during ILS

Approach mode. The localizer scale and runway symbol are removed from the display.

SPD Loss of Speed Command Valid. The speed comand scale

and circle are removed from the display.

Dual installations perform cross-side monitoring and display crossside failures in a yellow box in the lower right corner of the ADI display. For the failure to be displayed, 1) the cross-side sensor failure must have been displayed on the cross-side display for at least two seconds, or 2) the cross-side HSI has failed. A black number indicates the station where the failure occurred. A red “X” annunciation in the yellow box indicates that the cross-side status has not been

3-4

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

TEST

BRT

S P D

GYRO

RWY

R/T

G S

DIM

TEST

BRT

2020

1010

2020

FD DH

MON

HDG PIT ROL GS LOC

ALT

EADI/EHSI Displays

Figure 3.1-13

ADI Sensor Failure Annunciation

Figure 3.1-14

ADI Cross-side Monotor Annunciation

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

3-5

EADI/EHSI Displays

received for at least two seconds. All ADI failure flags flash for four to six seconds upon initial display, then become steady indications.

3.1.12 COMPARATOR MONITOR ANNUNCIATIONS

These annunciations are only presented when configured. The “HDG” annunciation indicates a difference exists between the Captain and First Officer headings. Likewise, “PIT” and “ROL” indicate a difference between the pitch or roll respectively on each aircraft side. The “GS”, “LOC” and “ALT” annunciations are not operational at this time. The “MON” annunciation indicates a monitor invalid condition exists such that comparison of cross-side information can not be performed.

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

3.1.13 ADI QUICK REFERENCE

The following foldout pages provide a quick guide to the ADI displays.

3-6

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

Airplane Symbol and Horizon Bar

Airplane attitude is indicated by the position of the fixed aircraft symbol with respect to the movable horizon bar.

Bank Scale and Pointer

Airplane bank angle is indicated by the position of the white pointer on the bank scale. Scale indices represent 0, 10, 20, 30, 45, 60 and 90 degree bank angles.

Rate of Turn Indicator

Needle indicates turn rate and direction. Outer marks indicate three degrees per second.

Glideslope Pointer and Scale

Pointer represents glideslope beam and moves up or down the glideslope deviation scale to indicate vertical displacement of the aircraft from the glideslope center. In view only when localizer is tuned and reliable glideslope is present. The glideslope scale and pointer are removed when backcourse is active.

Runway and Runway Extension Indicator

Indicates lateral displacement of the aircraft from the localizer. In view only when a localizer is tuned. On backcourse aproaches, the runway indicator gives reverse indications. The runway indicator will rise vertically to indicate radio altitude from 200 feet to touchdown, each mark on the rising runway represents 100 feet.

Command Bars

The vertical bar indicates the roll correction which the aircraft must make to maintain a selected heading or course, and the horizontal bar indicates the pitch correction the aircraft must make to maintain altitude, pitch, or to track the glideslope. Bars appear when a valid flight director mode is commanded by an external control panel.

Speed Command Circle and Scale

Circle moves up or down the scale to indicate deviation from selected airspeed.

DIM

TEST

BRT

2020

1010

2020

FD DH

Sky

Ground

Decision Height (DH) Annunciation

Indicates when decision height is reached.

Flight Director (FD) Annunciation

Indicates when same flight director computer is driving command bars on both Captain and FO sides.

Pitch Scale

Indicates amount of pitch up/down. Graduated in 2.5° increments within ±30° of the horizon line and in 20° increments from 40 ° to 80°.

Decrab Symbol

Indicates rudder command required to align aircraft with the runway . The decrab symbol is only displayed on an autopilot coupled approach.

EADI/EHSI Displays

Rev. 0 Jan/97

Figure 3.1-15

Normal ADI Quick Reference

FPD 500 FLAT PANEL DISPLAY SYSTEM

3-7

EADI/EHSI Displays

This page intentionally left blank.

3-8

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

DIM

TEST

BRT

DIM

TEST

BRT

DIM

TEST

BRT

1010

2020

3030

DIM

TEST

BRT

1010

2020

3030

Sky

An eyebrow of sky will always be shown, even if the pitch exceeds viewable limits of the sky. If the pitch changes from what is shown to drive the remaining sky off the display, the eyebrow will remain and the horizon line will drive off the display .

Ground

An eyebrow of ground will always be shown, even if the pitch exceeds viewable limits of the ground. If the pitch changes from what is shown to drive the remaining ground off the display, the eyebrow will remain and the horizon line will drive off the display .

Chevrons

Red Chevrons indicate direction of pitch correction to return to a normal pitch attitude. They first appear 23° Nose Up and 10° Nose Down

EADI/EHSI Displays

Figure 3.1-16

Excessive Pitch ADI Quick Reference

Rev. 0 Jan/97

FPD 500 FLAT PANEL DISPLAY SYSTEM

3-9

EADI/EHSI Displays

This page intentionally left blank.

3-10

FPD 500 FLAT PANEL DISPLAY SYSTEM

Rev. 0

Jan/97

+ 45 hidden pages