BendixKing FPI 3501B User Manual
FPD 500
FLAT PANEL DISPLAY SYSTEM
FOR THE DC-10
Operator’s Manual
A
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COPYRIGHT NOTICE
©1997 AlliedSignal, Inc.
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.
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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
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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
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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.
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Introduction
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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.
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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.
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Introduction
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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.
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2.1.3.3 “R” RANGE Button
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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,
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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.
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Excessive Pitch Down Display
Figure 3.1-3
3-1
EADI/EHSI Displays
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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.
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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.
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Figure 3.1-10
Rising Runway
3-3
EADI/EHSI Displays
N
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FD
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
A
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
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FPD 500 FLAT PANEL DISPLAY SYSTEM
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Jan/97
A
N
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BRT
S
P
D
GYRO
FD
RWY
R/T
G
S
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10
2020
10
55
55
1010
2020
F
S
FD DH
GS
2
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.
A
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FPD 500 FLAT PANEL DISPLAY SYSTEM
Rev. 0
Jan/97
A
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.
N
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BRT
10
2020
10
55
55
1010
2020
F
S
FD DH
GS
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
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FPD 500 FLAT PANEL DISPLAY SYSTEM
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40
80
60
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60
80
80
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FD
55
1010
2020
3030
40
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FD
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2020
3030
40
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
A
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FPD 500 FLAT PANEL DISPLAY SYSTEM
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