Fpd 500 A Operator’s Manual Flat Panel Display System

Transcript

FPD 500 FLAT PANEL DISPLAY SYSTEM FOR THE DC-10 Operator’s Manual A 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. 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. 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .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 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM i 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 3.2.3.1 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 ii FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A Introduction 1. INTRODUCTION BRT DIM F FD 20 10 N 5 5 M 10 20 R 20 TEST I Figure 1-1 Typical EADI Display BRT INS1 INS2 TRU 1234 1324 000 N DIM 0 3 30 33 GS M 12 24 9 27 6 21 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. 5 18 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). GS 10 5 10 S DH 20 R 15 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.). TEST I ILS 1 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 A 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 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. 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. 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 A Introduction This page intentionally left blank. 1-4 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 2.1.2 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 DIM TEST 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 N This button is non-functional in ADI mode. In HSI mode, each press cycles the display between NORMAL, ARC, WX, WX+MAP, and MAP. Italicized modes are not currently active. M Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 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. 0 Jan/97 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. 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. BRT DIM F FD 20 10 GS N 10 5 5 5 5 10 S DH 20 M 10 20 R 20 TEST I Figure 3.1-1 Normal Attitude Display 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). BRT BRT DIM FD N DIM FD 5 30 30 20 10 5 TEST 20 30 20 10 10 20 M R N 5 10 40 M 30 40 R 5 I Figure 3.1-2 Excessive Pitch Up Display TEST I Figure 3.1-3 Excessive Pitch Down Display 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 3-1 EADI/EHSI Displays A 3.1.2 ROLL ATTITUDE A white stationary roll scale with FD 20 DH 20 GS an orange zero degree index pro- F vides the reference for the bank 10 10 angle pointer. The white sky 5 5 pointer moves in relation to the roll scale to indicate degrees of Figure 3.1-4 aircraft right or left bank. The Roll Attitude fixed scale is marked at 10, 20, 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 5 5 Located in the center of the display is the 10 10 Figure 3.1-5 fixed yellow aircraft symbol with a black dot Symbolic Aircraft at the center. The pitch and roll attitudes of 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 10 10 by vertical and horizontal magenta bars in 5 5 the center of the EADI display about the fixed aircraft symbol. The command bars appear to move in front of the yellow air5 5 craft symbol but behind the black dot. The 10 10 horizontal bar provides pitch commands and the vertical bar provides roll comFigure 3.1-6 mands. The bars are independently driven Flight Director and can indicate pitch only, roll only, or 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 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 DIM F F 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. S Figure 3.1-8 Speed Command Indicator H 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. N GS M R 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 5 10 20 5 10 20 Figure 3.1-10 Rising Runway FPD 500 FLAT PANEL DISPLAY SYSTEM 3-3 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. 3.1.10 FLIGHT DIRECTOR (FD) ANNUNCIATION 20 DH GS N Figure 3.1-11 Decision Height Annunciator A yellow circle with “FD” in black is displayed when the same Flight Director DIM 20 F is selected by both Captain and First Officer. The annunciator does not Figure 3.1-12 flash. Flight Director Annunciator FD 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 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 A EADI/EHSI Displays BRT DIM GYRO FD S P D N G S M R RWY TEST I R/T Figure 3.1-13 ADI Sensor Failure Annunciation BRT HDG PIT ROL GS MON DIM F FD ALT 20 20 10 10 S TEST LOC 20 DH GS N 10 5 5 5 5 M 10 R 20 2 I Figure 3.1-14 ADI Cross-side Monotor Annunciation Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 3-5 EADI/EHSI Displays A 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 A EADI/EHSI Displays 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. 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. Sky Decision Height (DH) Annunciation Indicates when decision height is reached. BRT Flight Director (FD) Annunciation Indicates when same flight director computer is driving command bars on both Captain and FO sides. DIM FD 20 20 10 Speed Command Circle and Scale Circle moves up or down the scale to indicate deviation from selected airspeed. Airplane Symbol and Horizon Bar Airplane attitude is indicated by the position of the fixed aircraft symbol with respect to the movable horizon bar. F 5 5 5 5 20 TEST M 10 R 20 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. 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°. Figure 3.1-15 Normal ADI Quick Reference FPD 500 FLAT PANEL DISPLAY SYSTEM N I 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. Rev. 0 Jan/97 GS 10 10 S DH Decrab Symbol Indicates rudder command required to align aircraft with the runway. The decrab symbol is only displayed on an autopilot coupled approach. 3-7 Rate of Turn Indicator Needle indicates turn rate and direction. Outer marks indicate three degrees per second. Ground A EADI/EHSI Displays This page intentionally left blank. 3-8 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A EADI/EHSI Displays BRT 40 30 30 20 20 10 10 5 M R 5 TEST I N 80 M 60 R 40 TEST I FPD 500 FLAT PANEL DISPLAY SYSTEM FD 5 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 N 5 10 10 20 20 30 30 40 M R I BRT N DIM Figure 3.1-16 Excessive Pitch ADI Quick Reference Rev. 0 Jan/97 DIM TEST 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 BRT DIM 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. M R 80 N 80 FD 60 DIM BRT TEST I A EADI/EHSI Displays This page intentionally left blank. 3-10 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A EADI/EHSI Displays 3.2 EHSI DISPLAYS The EHSI is capable of displaying five different presentations of the horizontal situation. The Mode (M) button cycles the display through Normal, ARC, Wx, Wx + MAP, and MAP modes. The Wx 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. The M heading index box is shown at the top center of the azimuth card, and contains digital heading R in integer degrees (0 thru 359). The heading is shown with TEST I respect to True or Magnetic ILS 1 north, and a blue “TRU” above the heading index box indicates Figure 3.2-1 the current reference. A fixed Normal HSI Display white symbolic aircraft in the center of the azimuth card indicates the aircraft’s relationship to the horizontal situation display. The azimuth card is divided into five degree increments, with the 10 degree divisions being longer to help with identification of the current heading. Fixed 45 degree markers (white triangles) are positioned around the outside of the azimuth card. 15 18 21 3.2.1.2 Navigation Source Annunciation The navigation system selected by the flight crew is annunciated in white in the lower left corner of the display. Three navigation sources are possible: ILS, VOR, or NAV. Up to three of each system can be annunciated (e.g. NAV1, NAV2, NAV3). Rev. 0 Jan/97 TEST ILS 1 Figure 3.2-2 Navigation Source Annunciation FPD 500 FLAT PANEL DISPLAY SYSTEM 3-11 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 33 0 3 12 24 9 27 6 30 A white selected course pointer is manually rotated around the azimuth card by an external course select knob. The pointer indicates the desired navigation course, and once set, rotates with the azimuth card. When the primary navigation source is an INS (NAV annunciated) desired track from the INS is used to position the course Figure 3.2-4 pointer. Selected Course Pointer 15 18 21 3.2.1.5 Course Deviation Display 30 27 9 12 24 6 The course deviation scale (five white dots) provides a reference for the course deviation bar. The course deviation bar is the center bar of the selected course pointer. The course deviation bar indicates the centerline of the selected navigation Figure 3.2-5 course or localizer course in relation to the symbolic aircraft. The course deviation Course Deviation Display scale and pointer rotate with the azimuth card when set. 3.2.1.6 Bearing Pointer(s) Not currently implemented. 3-12 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. When distance data is missing, the entire disINS1 INS2 TRU ance display is removed. DME distance ------000 is shown as XXX.X from 0.0 thru 399.9 Figure 3.2-7 NM. INS/LNAV distance is shown as Invalid Distance Display XXX.X from 0.0 thru 999.9 and as XXXX for 1000 NM and above. 3.2.1.8 To/From Display 7 30 3 G 24 2 Figure 3.2-8 “TO” Display 12 15 18 21 3.2.1.9 Glideslope Display Figure 3.2-9 “FROM” Display GS 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. 3.2.1.10 Drift Angle Display 0 6 An orange arrowhead near the center of the azimuth card pointing towards the head of the course pointer represents the “TO” indication, pointing towards the tail of the course pointer represents the “FROM” indication. The arrowhead points toward the navigation station or waypoint, indicating whether the current selected course is TO or FROM the navigation station or waypoint. 33 M R Figure 3.2-10 Glideslope Indicator Not currently implemented. 3.2.1.11 Ground Speed Display Not currently implemented. Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 3-13 A EADI/EHSI Displays 3.2.2 ARC HSI DISPLAY BRT INS1 INS2 TRU 1234 1324 000 N DIM GS 0 33 3 30 M 6 The ARC format provides for display of weather radar data (not currently supported) and provides increased resolution of the displayed navigation data due to the enlarged scale. R 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. TEST I ARC ILS 1 Figure 3.2-11 ARC HSI Display 3.2.2.2 Navigation Source Annunciation Same as Normal mode. 3.2.2.3 Selected Heading Same as Normal mode, except that when GS 0 the heading bug moves off the visible 3 33 scale, a small orange heading bug symbol is displayed above the right or left edge of Figure 3.2-12 the azimuth scale to indicate its actual loca- Selected Heading Bug tion. 3.2.2.4 Selected Course 3 30 Same as Normal mode, except the lower portion of the pointer is out of view and when the pointer moves off the visible scale, a small white selected course arrow symbol is displayed above the right or left edge of the azimuth scale to indicate its actual location. 0 33 Figure 3.2-13 Selected Course Pointer 3.2.2.5 Course Deviation Display Same as Normal mode. 3.2.2.6 Bearing Pointer(s) Not currently implemented. 3-14 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 range information. The MAP mode display is the same as ARC except as noted in the following paragraphs. 3.2.3.2 MAP Waypoints INS1 INS2 TRU 1234 1324 000 N DIM GS 0 33 3 M 6 The azimuth card forms the outer range ring. The inner range ring represents half the distance to the outer range ring. The half-range distance is annunciated at the bottom right end of the inner ring. The full map range is annunciated in the lower left corner of the display, directly under the mode annunciation. Currently, the range is annunciated as dashes only. BRT 30 3.2.3.1 Range Rings R -TEST MAP - - - ILS 1 I Figure 3.2-14 MAP Display Not currently implemented. Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 3-15 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. NAV or VOR or ILS Loss of Course Deviation Valid. The deviation bar and scale are removed from the display. The to/from arrow is also removed from the display if the navigation source is NAV or VOR. Loss of Glideslope Valid during ILS Approach mode. The glideslope scale and pointer are removed from the display. BRT HDG N DIM 0 27 12 24 NAV 18 21 TEST M 9 A L E R T G S 3 30 33 6 An additional annunciation of “ALERT” is provided when an INS waypoint is approached. A red “X” annunciation in the yellow cross-side failure box indicates that the cross-side status has not been received for at least two seconds. All HSI failure flags flash for four to six seconds upon initial display, then become steady indications. R 15 GS I NAV 1 NOTE: The only cross-side failure annunciated by a normal HSI (Integrate mode not Figure 3.2-15 active) is the red “X” indicatHSI Sensor Failure Annunciation ing the loss of cross-side information. With Integrate mode active, an HSI will display the same cross-side failure information provided by an ADI. 3.2.7 HSI QUICK REFERENCE The following foldout pages provide a quick guide to the HSI displays. 3-16 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 INS2 TRU 1234 1324 000 N DIM 3 30 33 0 24 12 18 21 I ILS 1 Course Deviation Indicator and Scale Indicates the centerline of the selected navigation course in relation to the aircraft symbol. Figure 3.2-16 Normal HSI Quick Reference FPD 500 FLAT PANEL DISPLAY SYSTEM R 15 TEST Navigation Source Indicates the navigation source selected to drive the HSI course deviation. Possible annunciations are "NAV", "VOR" or "ILS". Rev. 0 Jan/97 M 9 Airplane Symbol Indicates aircraft relationship to the horizontal display. GS 6 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. Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 2. 27 Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 1. Mag/True Annunciator Indicates which aircraft heading data is shown: magnetic (blank) or true (TRU). 3-17 Selected Course Arrow Indicates selected course on the compass card. The arrow is set via an external course select knob. Once set, the arrow rotates with the compass card to provide continuous indication of the selected course. To/From Pointer Indicates if selected course is to or from the selected VOR Station. Not displayed with ILS active. 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. A EADI/EHSI Displays This page intentionally left blank. 3-18 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. Once set, the bug rotates with the compass card to provide continuous indication of the selected heading. Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 2. BRT INS1 INS2 TRU 1234 1324 000 N DIM GS 0 33 3 M 6 30 Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 1. Compass Card Indicates aircraft magnetic or true heading under lubber mark. R Airplane Symbol Indicates aircraft relationship to the horizontal display. TEST HSI Display Mode Indicates ARC or MAP display. Navigation Source Indicates the navigation source selected to drive the HSI course deviation. I ARC ILS 1 FPD 500 FLAT PANEL DISPLAY SYSTEM 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. To/From Pointer Indicates if selected course is to or from the selected VOR Station or waypoint. Not displayed with ILS active. Course Deviation Indicator and Scale Indicates the centerline of the selected navigation course in relation to the aircraft symbol. Figure 3.2-17 ARC HSI Quick Reference Rev. 0 Jan/97 Selected Course Arrow Indicates selected course on the compass card. The arrow is set via an external course select knob. Once set, the arrow rotates with the compass card to provide continuous indication of the selected course. 3-19 A EADI/EHSI Displays This page intentionally left blank. 3-20 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A EADI/EHSI Displays BRT Course Pointer Locator Indicates to which side the course pointer is closest. INS1 1234 1324 000 N DIM GS 0 33 M R TEST I ARC ILS 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. Once set, the arrow rotates with the compass card to provide continuous indication of the selected course. Rev. 0 Jan/97 INS2 TRU 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. A EADI/EHSI Displays This page intentionally left blank. 3-22 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 2. BRT INS1 INS2 TRU 1234 1324 000 N DIM GS 0 33 3 M 6 30 Distance Readout Indicates distance in nautical miles from the selected DME or waypoint according to navigation system 1. Mag/True Annunciator Indicates which aircraft heading data is shown: magnetic (blank) or true (TRU). R Airplane Symbol Indicates aircraft relationship to the horizontal display. -TEST HSI Display Mode Indicates ARC or MAP display. Full-Range Annunciator Indicates the full map range selected. The azimuth scale represents the full range ring. Currently indicates dashes only. I MAP - - - ILS 1 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. To/From Pointer Indicates if selected course is to or from the selected VOR Station or waypoint. Not displayed with ILS active. Navigation Source Indicates the navigation source selected to drive the HSI course deviation. Course Deviation Indicator and Scale Indicates the centerline of the selected navigation course in relation to the aircraft symbol. Figure 3.2-19 MAP HSI Quick Reference Rev. 0 Jan/97 Selected Course Arrow Indicates selected course on the compass card. The arrow is set via an external course select knob. Once set, the arrow rotates with the compass card to provide continuous indication of the selected course. FPD 500 FLAT PANEL DISPLAY SYSTEM 3-23 Half-Range Ring and Annunciator Indicates half of the full map range selected. Currently indicates dashes only. A EADI/EHSI Displays 3.3 INTEGRATE MODE BRT DIM F FD 20 20 10 20 GS N 10 5 5 5 5 10 S DH 10 0 3 R 20 30 33 M TRU 6 I NAV 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. The ADI and HSI display functions are the same as they would be on an ADI or HSI alone, except that the rate of turn display and the rising runway are not displayed, and the to/from pointer is duplicated on both sides of the symbolic aircraft. Off scale symbols (heading bug and course pointer) are displayed as in the ARC HSI mode. Figure 3.3-1 Integrate Display On a display configured as an ADI, a pitch value of more than 23 degrees up or down will result in the display reverting to the ADI presentation. The display will not automatically return to Integrate mode when pitch value is reduced to less than 23 degrees. The Integrate mode must be manually reselected. On a display configured as an HSI, pitch value does not cause the display to revert to HSI mode. 3.3.1 INTEGRATE MODE FAILURE ANNUNCIATIONS 3-24 ROL GS ALT GYRO FD S P D N G S M A L E R T 33 30 DIM LOC TEST HDG 0 R 3 NAV 9 The following foldout pages provide a quick guide to the Integrate Mode displays. HDG PIT MON 6 3.3.2 INTEGRATE MODE QUICK REFERENCE BRT 27 External failures are annumciated in the same way as on the ADI and HSI, except “RWY” and “R/T”, because the rising runway and the rate of turn indicator are not shown on the integrate display. 2 I Figure 3.3-2 Integrate Mode Failure Annunciation FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A EADI/EHSI Displays 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. BRT Flight Director (FD) Annunciation Indicates when same flight director computer is driving command bars on both Captain and FO sides. FD 1324 20 20 10 N 5 5 M 10 0 3 R 20 TEST TRU I 9 NAV 1 Ground A small amount of ground will always be shown, if at the top of the ADI, even if the pitch exceeds viewable limits of the ground. The eyebrow of ground will be obscured by the compass card at the bottom. Figure 3.3-3 Integrate Mode ADI Quick Reference Rev. 0 Jan/97 5 33 30 20 GS 10 5 10 S DH 6 Airplane Symbol and Horizon Bar Airplane attitude is indicated by the position of the fixed aircraft symbol with respect to the movable horizon bar. F Decision Height (DH) Annunciation Indicates when decision height is reached. INS2 1234 DIM Speed Command Circle and Scale Circle moves up or down the scale to indicate deviation from selected airspeed. INS1 27 Sky A small amount of sky will always be shown if at the top of the ADI, even if the pitch exceeds viewable limits of the sky. 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. FPD 500 FLAT PANEL DISPLAY SYSTEM 3-25 Decrab Symbol Indicates rudder command required to align aircraft with runway. The decrab symbol is only displayed on an autopilot coupled approach. 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. 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°. A EADI/EHSI Displays This page intentionally left blank. 3-26 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. DIM F FD INS2 1324 20 20 10 5 5 TEST N 10 0 3 30 33 R 20 TRU I Alert Annunciator Indicates that an INS waypoint is being approached. Navigation Source Indicates the navigation source selected to drive the HSI course deviation which is also displayed on the ADI in Integrate Mode. Course Deviation Indicator and Scale Indicates the centerline of the selected navigation course in relation to the aircraft symbol. Figure 3.3-4 Integrate Mode HSI Quick Reference Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 3-27 Mag/True Annunciator Indicates which aircraft heading data is shown: magnetic (blank) or true (TRU). M 9 NAV 1 GS 5 10 20 DH 10 5 A S L E R T Compass Card Indicates aircraft magnetic or true heading under lubber mark. 6 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. When driven out of view, a small heading bug is displayed over the right or left end of the azimuth card to show the location. INS1 1234 27 Lubber Mark Indicates heading of aircraft on compass card. BRT Airplane Symbol Indicates aircraft relationship to the horizontal display. Selected Course Arrow Indicates selected course on the compass card. The arrow is set via an external course select knob. Once set, the arrow rotates with the compass card to provide continuous indication of the selected course. When driven out of view, a small arrow displayed over the right or left end of the azimuth card to show the location. To/From Pointer Indicates if selected course is to or from the selected VOR Station or waypoint. Duplicated on both ends of the course pointer so that at least one will always be visible. A EADI/EHSI Displays This page intentionally left blank. 3-28 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. Cross-side and other sensors are never used, therefore there is no need to identify these sensor sources. During enroute mode (a valid ILS frequency is not selected) the glideslope scale and runway symbol are removed from the EADI display. The navigation sources used to position the course deviation bar on the EHSI are identified since three sources are possible. INS is annunciated as “NAV”, VOR is annunciated as “VOR” and localizer is annunciated as “ILS”. The glideslope scale with pointer position determined by the glideslope receiver is also displayed when the course deviation bar is driven by the localizer receiver and “ILS” is annunciated as the navigation source. The glideslope scale and pointer are removed from display on the EHSI when the selected sensor is “VOR” or “NAV”. When Integrate mode is selected on an EADI, the navigation source used to position the course deviation bar on the integrated display will match that selected for use on the associated EHSI. These navigation sources are identified with the same annunciations used on the EHSI. Some aircraft installations allow independent selection of navigation sensors for the EADI and EHSI. This can result in unexpected combinations of sensors between the two displays and also on a single EADI display with the Integrate mode selected. For example, the presence of a glideslope scale and pointer on an EADI in Integrate mode does not insure that the course deviation bar on the same display is driven by the localizer. The actual navigation source of lateral deviation may be NAV, VOR or ILS as selected for the EHSI. The correct navigation source is annunciated in all cases and must be used to avoid confusion. All the possible combinations are shown in the following figures. Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 4-1 A Special Considerations ADI ENROUTE INS1 1324 20 10 5 5 5 10 10 0 3 S TRU 27 10 0 3 TRU INS2 TRU 1324 000 N DIM 0 3 30 33 12 12 R 15 21 TEST 18 21 NAV 1 M 9 27 M I R 20 27 INS1 9 27 M 6 6 30 3 24 33 1234 N TEST 5 9 BRT INS2 1324 000 0 5 I NAV 1 TRU 33 5 TEST 9 INS1 1234 N 6 I DIM 20 GS 10 5 10 R 20 6 BRT 20 M TEST NAV 1 20 F 30 33 30 20 DIM 10 5 10 S N 20 INS2 1324 24 F INS1 1234 18 DIM BRT INS2 1234 R 15 BRT ADI APPROACH I NAV 1 Figure 4.1-1 HSI on NAV (INS) 4-2 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A Special Considerations ADI ENROUTE INS1 1324 20 10 5 5 5 10 10 0 3 S 10 0 3 INS2 INS1 1324 000 N 0 3 30 33 12 12 R 15 21 TEST 18 21 VOR 1 M 9 27 M I R 20 I DIM 9 27 M 6 6 30 3 24 33 1234 N TEST 5 27 27 000 0 5 9 9 1324 N 6 6 BRT INS2 33 5 TEST VOR 1 INS1 1234 DIM 20 GS 10 5 10 R 20 I BRT 20 M TEST VOR 1 20 F 30 33 30 20 DIM 10 5 10 S N 20 INS2 1324 24 F INS1 1234 18 DIM BRT INS2 1234 R 15 BRT ADI APPROACH I VOR 1 Figure 4.1-2 HSI on VOR Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 4-3 A Special Considerations ADI ENROUTE INS1 1324 20 10 5 5 5 10 3 S 1324 27 INS2 1324 N 33 0 3 12 12 R 15 21 TEST 18 21 ILS 1 GS M 9 27 M I R 20 000 DIM 9 ILS G S 3 6 30 3 6 27 10 0 INS1 1234 N 24 33 M 30 000 TEST 5 9 BRT INS2 0 5 I ILS 1 INS1 33 5 TEST 9 27 I N 6 ILS 1234 DIM 20 GS 10 5 10 R 20 6 BRT 20 M 10 0 TEST ILS 1 20 F 30 33 30 20 DIM 10 5 10 S N 20 INS2 1324 24 F INS1 1234 18 DIM BRT INS2 1234 R 15 BRT ADI APPROACH I ILS 1 Figure 4.1-3 HSI on ILS 4-4 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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. When the “HDG” flag is displayed, the positions of the selected heading bug and selected course arrow should not be trusted. This is because heading is used to generate the selected heading and selected course signals received by the EHSI, and the validity of heading at that location (outside the EHSI) is unknown. BRT INS2 INS1 1234 1324 HDG N DIM 3 GS M 12 24 9 27 6 30 33 0 R 15 18 21 TEST I ILS 1 Figure 4.2-1 Heading Failure Flag Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 4-5 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. The to/from arrow and course deviation may be incorrect since the selected course used by the navigation source (if any) is unknown. BRT INS2 INS1 1234 1324 000 N DIM 3 M 12 24 9 27 6 30 33 0 R 15 18 21 TEST I VOR 1 Figure 4.3-1 Selected Course Failure Flag 4.4 SELECTED HEADING FAILURE If selected heading is not received by the EHSI, the selected heading bug is removed from the display. 4-6 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 5.1-1 Bezel Performing the Self Test is not required at any time. If a failure was to occur or exist, the failure would be annunciated. This test is intended to familiarize the operator with the various flagging methodology used and a quick check for proper color presentation. Self Test is inhibited during ILS mode if both glideslope and localizer are valid. Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 5-1 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. • No failure flags displayed • Attitude - 10° pitch up, 20° right roll • Flight Director - Full scale (16.7°) pitch up, full scale (16.7°) right roll • 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 performed. Same as Phase 2 except flags remain on steady 5-2 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A Operating Instructions BRT MON 30 DIM F GS 20 30 TEST 20 M 10 10 N 5 5 5 5 S R 10 10 TEST I Figure 4.1-2 ADI Self Test Phase 1 BRT HDG PIT ROL GS MON DIM FD S P D LOC ALT GYRO FD DH N G S TEST M R TEST RWY R/T 2 I Figure 4.1-3 ADI Self Test Phase 2 & 3 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 5-3 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. • No failure flags displayed • Compass Card - 0° (north), digital heading “000” • Source/Distance Display - INSX/3999; or DMEX/399.9 if available, if 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 displayed Phase 2 - All failure and warning flags flashing for five seconds. • Source/Distance Display - Decluttered • Selected Course - Decluttered • Lateral Deviation - Decluttered • TO/FROM - Decluttered • Heading Bug - Decluttered • Digital Heading/Lubber Mark - Decluttered Phase 3 - Steady flags displayed while internal BIT test performed. Same as Phase 2 except flags remain on steady 5-4 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A BRT Operating Instructions BRT INS2 INS1 3999 3999 000 N DIM 0 3 GS 6 30 33 INS2 INS1 3999 N DIM GS 0 33 M 3 M TEST 30 6 12 24 9 27 TEST R R 15 18 21 TEST I TEST I ARC NAV 1 NAV 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 6 TEST 12 24 33 M 18 21 I M NAV A L E R T R 15 TEST 3 G S 6 NAV N 0 9 27 TEST A L E R T G S 3 30 33 DIM 30 DIM TEST R I ARC NAV 1 NAV 1 Figure 4.1-7 Normal HSI Self Test Phase 2 & 3 Rev. 0 Jan/97 3999 000 FPD 500 FLAT PANEL DISPLAY SYSTEM Figure 4.1-8 ARC HSI Self Test Phase 2 & 3 5-5 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/399.9 if available, if 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 displayed • Attitude - 10° pitch up, 20° right roll • Flight Director - Full scale (16.7°) pitch up, full scale (16.7°) right roll • Rudder Command - Full scale right • Glideslope & Speed Command - Centered Phase 2 - All failure and warning flags flashing for five seconds. • 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 Phase 3 - Steady flags displayed while internal BIT test performed. Same as Phase 2 except flags remain on steady 5-6 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A BRT Operating Instructions INS1 INS2 1234 1324 30 DIM F GS 20 30 TEST 20 M 10 10 5 5 5 S 50 10 3 R 10 6 30 33 N I 9 NAV 1 27 TEST Figure 4.1-10 Integrate Mode Self Test Phase 1 BRT GYRO FD FD S P D DH A L E R T M 33 27 R 3 NAV 9 NAV 1 HDG 0 6 TEST N G S TEST 30 DIM 2 I Figure 4.1-11 Integrate Mode Self Test Phase 2 & 3 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 5-7 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. 0 Jan/97 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. The maintenance mode is inhibited during the ILS mode if glideslope and localizer are both valid. NOTE: The maintenance pages are intended to aid troubleshooting on the ground. They are not intended for use in flight. The first maintenance page contains the current software version and mod level, unit serial number, and part number, as well as the AlliedSignal copyright information. Page 2 begins the unit operating parameters. The following maintenance pages shall be displayed: • FPI-3501B MAINTENANCE PG 01 • DU OPERATING PARAMS PG 02 • DU STATUS PG 03 • DU BEZEL STATUS PG 04 • DU INTERFACE STATUS PG 05 • DU INTERFACE STATUS PG 06 • DU INTERFACE STATUS PG 07 • DU INTERFACE STATUS PG 08 • DU INTERFACE STATUS PG 09 • DU INTERFACE STATUS PG 10 • DU CALIBRATION DATA PG 11 • WHITE FLAT FIELD TEST PATTERN PG 12 • RED FLAT FIELD TEST PATTERN PG 13 • GREEN FLAT FIELD TEST PATTERN PG 14 • BLUE FLAT FIELD TEST PATTERN PG 15 • BLACK FLAT FIELD TEST PATTERN PG 16 • GRAY SHADES FOR WHITE, RED, GREEN, BLUE PG 17 • WATCHDOG TIMER TEST PG 18 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-1 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. 1995 DIM SW RELEASE 01/2H BOOT RELEASE 01/02 S/N 0021 P/N 066-50017-0101 N ID 1230960925 M 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 R TEST I Figure 6.1-1 Maintenance Page 1 6.2 MAINTENANCE PAGE 2 The following is the definition of the states for the page: BRT DU OPERATING PARAMS Parameter LAMP HEATER LCD HEATER States ON/OFF ON/OFF DIM INTERNAL TEMPERATURE EXTERNAL LIGHT LEVEL DISPLAY BRIGHTNESS BURST CONTROL OUTPUT DIM/HV OUTPUT LAMP HEATER LCD HEATER TOTAL POWER CYCLES TOTAL TIME POWER CYCLE TIME PG 02 38 °C 120 25.46 FL 23.50 % 0.00 V OFF OFF 303 64 HRS 0 HRS 11 MINS N M R TEST A red flashing “FREEZE” annunciation indicates that the status annunciations are static with no update, frozen by pressing the Mode (M) button. 6-2 I Figure 5.2-1 Maintenance Page 2 TEST I FREEZE Figure 6.2-2 Frozen Maintenance Page 2 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 6.4 MAINTENANCE PAGE 4 The following is the definition of the states for the page: BRT DU BEZEL STATUS Parameter PUSHBUTTON States 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. DIM BRT DIM N M R I TEST PG 04 PUSHBUTTON PUSHBUTTON PUSHBUTTON PUSHBUTTON PUSHBUTTON PUSHBUTTON PUSHBUTTON 0 0 0 0 0 0 0 N M R TEST I Figure 6.4-1 Maintenance Page 4 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-3 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 6.6 MAINTENANCE PAGE 6 The following is the definition of the states for the page: BRT DU INTERFACE STATUS Parameter DISCRETE HI DISCRETE LO States HI/OPEN OPEN/LO DIM DISCRETE HI INPUT DISCRETE LO INPUT DISCRETE HI INPUT DISCRETE LO INPUT DISCRETE HI INPUT DISCRETE LO INPUT DISCRETE HI INPUT DISCRETE LO INPUT DISCRETE HI INPUT DISCRETE LO INPUT DISCRETE HI INPUT DISCRETE LO INPUT 0 0 1 1 2 2 3 3 4 4 5 5 PG 06 HI LO HI LO HI LO HI LO HI LO HI LO TEST N M R I Figure 6.6-1 Maintenance Page 6 6-4 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 A Maintenance Mode Displays 6.7 MAINTENANCE PAGE 7 The following is the definition of the states for the page: Parameter DISCRETE HI DISCRETE LO States HI/OPEN OPEN/LO BRT DIM DU INTERFACE STATUS PG 07 DISCRETE HI INPUT 6 DISCRETE LO INPUT 6 DISCRETE 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 11 DISCRETE LO INPUT 11 HI OPEN HI LO OPEN OPEN OPEN OPEN OPEN OPEN HI LO TEST N M R I Figure 6.7-1 Maintenance Page 7 6.8 MAINTENANCE PAGE 8 The following is the definition of the states for the page: Parameter DISCRETE States OPEN/LO BRT DIM DU INTERFACE STATUS PG 08 DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE OPEN LO OPEN OPEN LO OPEN LO LO INPUT INPUT INPUT INPUT INPUT INPUT INPUT INPUT 12 13 14 15 16 17 18 19 N M R TEST I Figure 6.8-1 Maintenance Page 8 Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-5 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 1.301 V TEST N M R I Figure 6.9-1 Maintenance Page 9 6.10 MAINTENANCE PAGE 10 The following is the definition of the states for the page: BRT DU INTERFACE STATUS Parameter DISCRETE OUT States HI/LO DIM DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE DISCRETE OUTPUT OUTPUT OUTPUT OUTPUT OUTPUT OUTPUT OUTPUT OUTPUT 0 1 2 3 4 5 6 7 PG 10 LO LO LO LO LO LO LO LO N M R TEST I Figure 6.10-1 Maintenance Page 10 6-6 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 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 6.11-1 Maintenance Page 11 Non-Volatile Data The LIS data displayed may be either current or stored nonvolatile data, selected by pressing the Integrate (I) button. The current values will alternate between frozen and real time by pressing the Mode (M) button. BRT DU CALIBRATION DATA DIM TEST PG 11 TEMPERATURE CORRECTED DATA N INTERNAL TEMPERATURE 46 °C CALIBRATED LIS VALUE = 105743 VCOM = 3742 CALIBRATION T0P = 3839 T4P = T0N = 4 T4N = T1P = 1398 T5P = POINT T1N = 3036 T5N = T2P = 1229 T6P = T2N = 3306 T6N = T3P = 1098 T7P = T3N = 3517 T7N = 1005 3664 883 3826 768 4030 0 4080 M FREEZE R I Figure 6.11-2 Maintenance Page 11 Current Data Rev. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-7 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. 0 Jan/97 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. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-9 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. 0 Jan/97 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. 0 Jan/97 FPD 500 FLAT PANEL DISPLAY SYSTEM 6-11 A Maintenance Mode Displays This page intentionally left blank. 6-12 FPD 500 FLAT PANEL DISPLAY SYSTEM Rev. 0 Jan/97 Printed .2K 8/97 CW AlliedSignal, Inc. Commercial Avionics Systems 400 North Rogers Road Olathe, KS USA 66062-1294 FAX: 913-791-1302 Telephone: 913-782-0400 006-18046-0000 Rev. 0 1/97 A