FPD 500 FLAT PANEL DISPLAY SYSTEM FOR THE B-727 Operator’s Manual a
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a Table of Contents 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 . . . . . . . . . . . . . . . . . .
Table of Contents a 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.
a Introduction 1. INTRODUCTION 20 GS DH F 20 10 N 10 M 10 10 20 R S 20 TEST I Figure 1-1 EADI Approach Display BRT INS1 1324 000 N 33 GS 0 3 30 DIM INS2 TRU 1234 M 12 24 9 27 6 21 The intended use of the ADI/HSI Flat Panel Indicator (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 Introduction 1.1 SYSTEM DESCRIPTION The indicator is designed for high reliability through the use of Application Specific Integrated Circuits (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.
a Introduction 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.
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a 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. BRT N DIM M R TEST I 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. BRT 2.1.
EADI/EHSI Operation a 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. R 2.1.3.4 “I” INTEGRATE Button Pressing this button activates the “Integrate” display mode. Exit this mode by pressing the NORM button. I 2.1.4 AMBIENT LIGHT SENSOR Not operational. 2-2 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev.
a 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.
a EADI/EHSI Displays 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, 30, 45 and 60 degrees, with the 30 and 60 degree marks being longer to allow easier recognition. GS 20 20 10 DH F 10 Figure 3.1-4 Roll Attitude 3.1.
a EADI/EHSI Displays 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. Figure 3.1-7 Rate of Turn Indicator HF 3.1.6 SPEED COMMAND N M A stationary white vertical scale located on the left side of the EADI is the reference for the fast-slow pointer (orange circle).
a EADI/EHSI Displays 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. This annunciator is not displayed in some installations. 20 DH F N Figure 3.1-11 Decision Height Annunciator 3.1.10 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.
a EADI/EHSI Displays BRT DIM GYRO FD G S N S P D M R RWY TEST I R/T Figure 3.1-13 ADI Sensor Failure Annunciation BRT HDG PIT MON DIM GS ROL GS LOC ALT 20 20 10 DH F N 10 M 10 20 TEST 10 R S 20 2 I Figure 3.1-14 ADI Cross-side Flag Monitor Annunciation Rev.
EADI/EHSI Displays a 3.1.11 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.
a EADI/EHSI Displays Command Bars The rotation indicates the roll correction which the aircraft must make to maintain a selected heading or course, and the placement on the pitch ladder 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. Bank Scale and Pointer Airplane bank angle is indicated by the position of the white pointer on the bank scale.
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a EADI/EHSI Displays BRT BRT 30 20 20 10 10 TEST M R I DIM N 80 M 60 R 40 TEST I FPD 500 FLAT PANEL DISPLAY SYSTEM 20 20 30 30 40 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. 3-9 M R I BRT N DIM Figure 3.1-16 Excessive Pitch ADI Quick Reference Rev.
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a EADI/EHSI Displays 3.2 EHSI DISPLAYS The Mode (M) button cycles the display through Normal, ARC and MAP modes. The MAP modes are not currently implemented. 3.2.1 NORMAL HSI DISPLAY 3.2.1.1 Azimuth Card 12 24 9 27 6 30 A 360 degree rotating white azimuth card indicates aircraft BRT INS2 INS1 heading referenced to a white TRU 1234 1324 000 rectangular box with a triangular N heading index mark (lubber line) DIM 0 3 GS 33 protruding from the bottom.
a EADI/EHSI Displays 3.2.1.3 Selected Heading 13 An orange notched heading bug is manual- 34 000 ly rotated around the azimuth card by an external heading select knob. The heading Figure03.2-3 bug indicates selected heading, and once Selected Heading Bug set, rotates with the azimuth card. 3.2.1.4 Selected Course 3 30 0 12 24 9 27 6 15 18 21 A white selected course pointer is manually rotated around the azimuth card by an external course select knob.
a EADI/EHSI Displays 3.2.1.7 Distance Display Two white alphanumeric distance displays provide the distance in nautical miles from the aircraft to the selected DME or VORTAC station in the standard navigation mode (DME), or distance to a waypoint in the INS1 INS2 TRU 1324 INS mode. The distance source is annun- 1234 000 Figure 3.2-6 ciated above its respective distance Distance Display value. If distance data is invalid, the distance value is replaced by dashes.
a EADI/EHSI Displays 3.2.2 ARC HSI DISPLAY The ARC format provides increased resolution of the displayed navigation data due to the enlarged scale. BRT DIM INS2 TRU 1324 000 N GS 0 33 3 M 6 30 3.2.2.1 Azimuth Card The azimuth card functions the same as in normal HSI mode, except only 45 degrees on either side of the current heading is visible. INS1 1234 R TEST I ARC RAD1 Figure 3.2-11 ARC HSI Display 3.2.2.
a EADI/EHSI Displays 3.2.2.7 Distance Display Same as Normal mode. 3.2.2.8 To/From Display Same as Normal mode. 3.2.2.9 Glideslope Display Same as Normal mode. 3.2.2.10 Drift Angle Display Not currently implemented. 3.2.2.11 Ground Speed Display Not currently implemented. 3.2.3 MAP HSI DISPLAY The MAP format provides for increased resolution of the displayed navigation data due to the enlarged scale. It also provides for display of weather radar and map waypoints (not currently implemented).
a EADI/EHSI Displays 3.2.4 WX DISPLAY Not currently implemented. 3.2.5 WX + MAP DISPLAY Not currently implemented. 3.2.6 HSI FAILURE ANNUNCIATIONS External sensor systems failures are annunciated in black text inside a red box. Up to three different failures are displayed: HDG Loss of Compass or Heading Valid. The digital heading is removed from the display, but the compass card remains on the display. See Special Considerations section. RAD or INS Loss of Course Deviation Valid.
a EADI/EHSI Displays Digital Heading Readout and Lubber Mark Indicates digital value of magnetic or true heading from the selected navigation system. Lubber mark indicates heading of aircraft on compass card. BRT INS1 1234 N GS 33 0 3 27 24 12 18 21 TEST Airplane Symbol Indicates aircraft relationship to the horizontal display. FPD 500 FLAT PANEL DISPLAY SYSTEM M R I RAD 1 Navigation Source Indicates the navigation source selected to drive the HSI course deviation.
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a EADI/EHSI Displays Mag/True Annunciator Indicates which aircraft heading data is shown: magnetic (blank) or true (TRU). Digital Heading Readout and Lubber Mark Indicates digital value of magnetic or true heading from the selected navigation system. Lubber mark indicates heading of aircraft on compass card. Heading Bug Indicates selected heading on the compass card. The bug is set via an external heading select knob.
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a EADI/EHSI Displays BRT Course Pointer Locator Indicates to which side the course pointer is closest. INS1 1234 DIM 1324 000 N GS 0 33 M R TEST I ARC RAD 1 Figure 3.2-18 Off-Scale ARC HSI Quick Reference FPD 500 FLAT PANEL DISPLAY SYSTEM 3-21 Heading Bug Locator Indicates to which side the heading bug is closest. 3 6 30 Selected Course Arrow Indicates selected course on the compass card. The arrow is set via an external course select knob.
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a EADI/EHSI Displays Digital Heading Readout and Lubber Mark Indicates digital value of magnetic or true heading from the selected navigation system. Lubber mark indicates heading of aircraft on compass card. Heading Bug Indicates selected heading on the compass card. The bug is set via an external heading select knob. Once set, the bug rotates with the compass card to provide continuous indication of the selected heading. Compass Card Indicates aircraft magnetic or true heading under lubber mark.
a EADI/EHSI Displays 3.3 INTEGRATE MODE BRT DIM 20 GS 20 10 DH F N 10 M 10 20 10 0 3 R 20 30 33 S TRU 6 I INS 1 27 TEST 9 The EADI and the EHSI both can provide the Integrated display as a reversionary mode, and the integrated display is identical on either an ADI or HSI.
a EADI/EHSI Displays Command Bars The rotation indicates the roll correction which the aircraft must make to maintain a selected heading or course, and the placement on the pitch ladder 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.
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a EADI/EHSI Displays Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 2. Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 1. INS1 DIM 1324 20 GS 20 10 F N 10 10 20 33 10 0 3 20 Course Deviation Indicator and Scale Indicates the centerline of the selected navigation course in relation to the aircraft symbol. Figure 3.
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a Special Considerations 4. SPECIAL CONSIDERATIONS 4.1 NAVIGATION SOURCE COMBINATIONS During approach mode (a valid ILS frequency selected), a normal EADI will display a glideslope scale with pointer and a rising runway. When displayed, the glideslope pointer position is always determined by the on-side glideslope receiver. The lateral position of the runway is always determined by the on-side localizer and the vertical position of the runway is always determined by the on-side radio altimeter.
a Special Considerations ADI ENROUTE BRT INS1 INS2 1234 1324 20 DIM 20 10 F N 10 M 10 33 10 0 R 3 S 20 6 30 20 I INS 1 BRT 9 27 TEST INS2 INS1 1234 1324 000 N DIM 0 3 M 12 24 9 27 6 30 33 R 15 18 21 TEST I INS 1 Figure 4.1-1 HSI on NAV (INS) 4-2 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev.
a Special Considerations ADI APPROACH ADI ENROUTE BRT INS1 BRT INS2 1234 20 DIM 20 10 F INS1 INS2 1234 1324 N DIM 1324 20 GS 20 10 10 F 10 M M 10 S 20 0 3 30 33 24 12 R 15 21 18 21 I M 9 12 24 N GS 27 M 9 27 DIM 1324 000 6 6 TEST 27 27 3 30 0 9 N 33 INS2 INS1 1234 1324 000 DIM I 9 BRT INS2 S 20 TEST RAD 1 INS1 1234 R 3 6 I BRT 10 0 33 30 20 TEST RAD 1 10 R 3 6 30 0 TEST 18 33 R 15 10 20 N I RAD 1 RAD 1 Figu
a Special Considerations 4.2 HEADING FAILURE Invalid heading is indicated by replacing the digital heading readout with a red “HDG” flag. The compass card will continue to be displayed and will rotate in response to the heading signal received by the EHSI. If the heading signal is not received by the EHSI, the compass card will freeze at the last valid value for heading and the “HDG” flag will be in view.
a Special Considerations 4.3 SELECTED COURSE FAILURE If selected course is not received by the EHSI, the selected course arrow head and tail are removed from the display and the course deviation scale is fixed in a horizontal position (selected course defaults to aircraft heading). The to/from arrow will continue to be displayed if the to/from signal is still received from the selected navigation source.
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a Operating Instructions 5. OPERATING INSTRUCTIONS Consult Aircraft Flight Manual Supplement for specific procedures and limitations in operation. 5.1 START UP When power is initially applied to the EADI/EHSI system, various flags may be annunciated on the displays, representing systems not yet operational. If all flags do not clear, then recheck the annunciated system. Adjust brightness control on the EADI and EHSI to desired brightness. 5.2 SELF TEST BRT N DIM M R TEST I Figure 5.
Operating Instructions a 5.2.1 ADI SELF TEST Press and hold the TEST button on the ADI to initiate the three phases of self test. Release of the button will cause the previous display to return, unless BIT test is in progress, in which case the test will complete, then the display will return. Phase 1 - A static display that imitates the electromechanical self test for five seconds.
a Operating Instructions BRT MON 30 DIM GS F 20 30 TEST 20 N M 10 10 R 10 S 10 TEST I Figure 4.1-2 ADI Self Test Phase 1 BRT HDG PIT ROL GS MON DIM ALT GYRO FD G S LOC DH N S P D TEST M R TEST RWY R/T 2 I Figure 4.1-3 ADI Self Test Phase 2 & 3 Rev.
Operating Instructions a 5.2.2 HSI SELF TEST Press and hold the TEST button on the HSI to initiate the three phases of self test. Release of the button will cause the previous display to return, unless BIT test is in progress, in which case the test will complete, then the display will return. Phase 1 - A static display that imitates the electromechanical self test for five seconds.
a BRT Operating Instructions BRT INS2 INS1 3999 3999 000 N DIM GS 0 3 6 30 33 INS2 INS1 3999 DIM N GS 0 33 M M 30 6 12 24 9 R R 15 18 21 TEST I TEST I ARC INS 1 INS 1 Figure 4.1-4 Normal HSI Self Test Phase 1 Figure 4.1-5 ARC HSI Self Test Phase 1 BRT BRT HDG HDG N 0 3 6 30 33 33 A L E R T 15 18 21 TEST M INS A L E R T R I 3 6 27 0 TEST 12 24 N G S M 9 INS DIM 30 G S TEST TEST INS 1 Figure 4.
Operating Instructions a 5.2.3 INTEGRATE MODE SELF TEST Press and hold the TEST button on the ADI/HSI to initiate the three phases of self test. Release of the button will cause the previous display to return, unless BIT test is in progress, in which case the test will complete, then the display will return. Phase 1 - A static display that imitates the electromechanical self test for five seconds. • No failure flags displayed • Compass Card - 0° (north) • Source/Distance Display - INSX/3999; or DMEX/399.
a BRT Operating Instructions INS1 INS2 1234 1324 30 DIM GS F 20 30 20 TEST N M 10 10 0 10 R 10 S 3 6 30 33 I 9 INS 1 27 TEST Figure 4.1-10 Integrate Mode Self Test Phase 1 BRT DIM GYRO FD G S DH TEST 3 INS 9 NAV 1 27 TEST A L E R T M R 6 30 33 HDG 0 N S P D 2 I Figure 4.1-11 Integrate Mode Self Test Phase 2 & 3 Rev.
Operating Instructions a 5.3 LIMITATIONS For information on EADI/EHSI system operating limitations, please refer to the approved Flight Manual Supplement for the particular aircraft in question. 5.4 EMERGENCY PROCEDURES For information on EADI/EHSI system emergency procedures, please refer to the approved Flight Manual Supplement for the particular aircraft in question. 5-8 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev.
a Maintenance Mode Displays 6. MAINTENANCE MODE DISPLAYS The maintenance mode provides access to the display’s internal operating parameters and fault status. The maintenance mode may be accessed by pressing the TEST and Integrate (I) buttons simultaneously. Data is displayed on multiple pages. The “Next” page is selected using the Range (R) pushbutton. The last page wraps around to the first page. Pressing the Normal (N) button exits the maintenance mode.
a Maintenance Mode Displays 6.1 MAINTENANCE PAGE 1 The following is the definition of the states for the page: Parameter A/C TYPE A/C SIDE DISPLAY TYPE CM ANNUN FD CMD IN VIEW PITCH CMD ROLL CMD States B-727/DC-10 CAPT/FO ADI/HSI ON/OFF HI/LO 150/120 150/66 BRT FPI-3501B MAINTENANCE PG 01 COPYRIGHT ALLIEDSIGNAL AVIONICS INC.
a Maintenance Mode Displays 6.3 MAINTENANCE PAGE 3 The following is the definition of the states for the page: Parameter LAMP IP, GP,ETC. States REPLACE/ PASS/FAIL PASS/FAIL BRT DIM DU STATUS PG 03 LAMP IP GP POWER SUPPLY DIMMER/LCD I/O #1 I/O #2 BEZEL PASS PASS PASS PASS PASS PASS PASS PASS N M R TEST I Figure 6.3-1 Maintenance Page 3 6.
a Maintenance Mode Displays 6.5 MAINTENANCE PAGE 5 The following is the definition of the states for the page: BRT DU INTERFACE STATUS Parameter 429 TX/RX 561/568 RX SYNCHRO States ACTIVE/ INACTIVE ACTIVE/ INACTIVE ANGLE DATA VALUE DIM 429 TX 429 RX 1 429 RX 2 561/568 RX 1 561/568 RX 2 SYNCHRO INPUT 1 SYNCHRO INPUT 2 SYNCHRO INPUT 3 SYNCHRO INPUT 4 SYNCHRO INPUT 5 PG 05 INACTIVE INACTIVE INACTIVE INACTIVE INACTIVE 000 180 180 360 000 TEST N M R I Figure 6.5-1 Maintenance Page 5 6.
a Maintenance Mode Displays 6.
a Maintenance Mode Displays 6.9 MAINTENANCE PAGE 9 The following is the definition of the states for the page: BRT DU INTERFACE STATUS Parameter ANALOG DATA States Value DIM ANALOG CHANNEL 0 ANALOG CHANNEL 1 ANALOG CHANNEL 2 ANALOG CHANNEL 3 ANALOG CHANNEL 4 ANALOG CHANNEL 5 ANALOG CHANNEL 6 ANALOG CHANNEL 7 ANALOG CHANNEL 8 ANALOG CHANNEL 9 ANALOG CHANNEL 10 ANALOG CHANNEL 11 PG 09 -.026 V -.003 V -1.137 V -1.138 V -.001 V -.017 V .010 V -.000 V .000 V -1.977 V 1.276 V 1.
a Maintenance Mode Displays 6.11 MAINTENANCE PAGE 11 The following is the definition of the states for the page: BRT DU CALIBRATION DATA Parameter ANALOG DATA States Value DIM PG 11 NON VOLATILE DATA N LIS CALIBRATION VALUE = 42277 VCOM = 3824 CALIBRATION T0P = 3839 T4P = T0N = 4 T4N = T1P = 2032 T5P = POINT T1N = 2096 T5N = T2P = 1680 T6P = T2N = 2448 T6N = T3P = 1472 T7P = T3N = 2704 T7N = M 1312 2912 1168 3136 1008 3376 0 4080 TEST R I Figure 6.
a Maintenance Mode Displays 6.12 MAINTENANCE PAGE 12 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. BRT N DIM M R TEST I Figure 6.12-1 Maintenance Page 12 6.13 MAINTENANCE PAGE 13 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. BRT N DIM M R TEST I Figure 6.13-1 Maintenance Page 13 6-8 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev.
a Maintenance Mode Displays 6.14 MAINTENANCE PAGE 14 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. BRT N DIM M R TEST I Figure 6.14-1 Maintenance Page 14 6.15 MAINTENANCE PAGE 15 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. BRT N DIM M R TEST I Figure 6.15-1 Maintenance Page 15 Rev.
a Maintenance Mode Displays 6.16 MAINTENANCE PAGE 16 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. BRT N DIM M R TEST I Figure 6.16-1 Maintenance Page 16 6.17 MAINTENANCE PAGE 17 Pages 12 - 17 are a check of the primary colors (white, red, green, blue, black) on the display. This one checks the gray shades of white, red, green, and blue. BRT N DIM M R TEST I Figure 6.17-1 Maintenance Page 17 6-10 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev.
a Maintenance Mode Displays 6.18 MAINTENANCE PAGE 18 This page contains “Watchdog Timer Test” information. This test is currently disabled and only displays “N/D”. BRT WATCHDOG TIMER STATUS PG 18 N DIM M N/D R TEST I Figure 6.18-1 Maintenance Page 18 Rev.
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