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 2)  The maximum deviation allowed between IRU input values and the median IRU value follows: a) Roll attitude - 5 degrees b) Body axis roll rate - 2.5 degrees/second c) Body axis yaw rate - 2.5 degrees/second d) Body axis lateral acceleration - 0.1 g's e) Ground speed - 60 knots
 (c) Fault Annunciation 1) The input data fault logic is a continuous input monitoring system. The input data is determined invalid if an IRU watchdog, parity, or SSM bus fault is set. If any IRU input or comparison fault is detected, a corresponding fault message is sent to the CMC. Fault latching is inhibited on ground or if the air/ground discrete is invalid. The monitors can be reset by the power-up reset, IRU auto-reset, or the maintenance reset.
 2)  IRU data is declared unacceptable if: a) Two out of three IRUs have comparison faults b) An input fault and a comparison fault are detected. c) All IRUs have input faults
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747-400
MAINTENANCE MANUAL

 3)  When IRU data is declared unacceptable, the yaw damper channel goes INOP and is auto-disengaged. An IRU autoreset is generated with the airplane in air. If sensor data within monitor threshold is detected for 10 seconds continuously, the IRU fault latch is reset, provided there have been no more than four resets since the airplane was on the ground.
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747-400 FAULT ISOLATION/MAINT MANUAL
YAW DAMPER SYSTEM
COMPONENT  SHT 102 FIG.  QTY  ACCESS/AREA  REFERENCE 
M7955 ACCELEROMETER - AFT L MODAL SUPPRESSION,  2  1  FLOOR PNL, STA 2260 BULK CARGO COMPT BELOW MAIN DECK  22-21-03
 M7956 ACCELEROMETER - AFT R MODAL SUPPRESSION, 2  1  FLOOR PNL, STA 2260 BULK CARGO COMPT BELOW MAIN DECK 22-21-03 
M7953 ACCELEROMETER - FWD L MODAL SUPPRESSION, 2  1  320, ABOVE NOSE GEAR WHEEL WELL BELOW MAIN DECK FLOOR PNL, STA  22-21-03 
HYDRAULIC INTERFACE MODULE CIRCUIT, M7603 M7954 ACCELEROMETER - FWD R MODAL SUPPRESSION,CARD - (FIM 29-10-00/101)  2  1  320, ABOVE NOSE GEAR WHEEL WELL BELOW MAIN DECK FLOOR PNL, STA 22-21-03 
CIRCUIT BREAKER - 1  FLT COMPT, P7 
FCE 2L DC, C10264 1  7C11  * 
FCE 1L DC, C8783  1  7C13  * 
FCE 1R DC, C8785 1  7C15  * 
FCE 2R DC, C10266 1  7C17  * 
LWR YAW DAMPER, C8781 1  7C18  * 
UPR YAW DAMPER, C8780 UPPER RUDDER CONTROL, M8004 LOWER RUDDER CONTROL, M8005 R CENTRAL MAINTENANCE, M7374 L CENTRAL MAINTENANCE, M7373 R AIR DATA, B164 L AIR DATA, B163 FCE PWR SUPPLY 1R, M7360 FCE PWR SUPPLY 2L, M7359 FCE PWR SUPPLY 1L, M7358 C AIR DATA, B166 COMPUTER - (FIM 34-12-00/101) COMPUTER - (FIM 45-10-00/101) MODULE - (FIM 27-09-00/101) MODULE - (FIM 27-21-00/101) 1  7C09  * 
MODULE - LOWER YAW DAMPER, M7363 1 1  117AL, MAIN EQUIP CTR, E2-2  22-21-02 
MODULE - UPPER YAW DAMPER, M7362  1  1  117AL, MAIN EQUIP CTR, E1-2  22-21-02 
PANEL - PASSENGER OXYGEN AND YAW DAMPER, M7315  1  1  FLT COMPT, P5  22-21-01 

* SEE THE WDM EQUIPMENT LIST
Yaw Damper System - Component Index
Figure 101 (Sheet 1)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A04542
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747-400 FAULT ISOLATION/MAINT MANUAL
COMPONENT  FIG. 102 SHT  QTY  ACCESS/AREA  REFERENCE 
ALTERNATE AIR/GND, R777 UNITS - (31-61-00/101) SWITCHES - (29-11-00/101) PRIMARY AIR/GND, R330 PRIMARY AIR/GND, R627 DEMAND 2 PRESSURE, S343 DEMAND 3 PRESSURE, S344 EDP 2 PRESSURE, S6 EDP 3 PRESSURE, S7 C EFIS/EICAS INTERFACE, M7352 L EFIS/EICAS INTERFACE, M7353 R EFIS/EICAS INTERFACE, M7351 RELAYS - (31-01-39/101) RELAYS - (31-01-36/101) ALTERNATE AIR/GND, R770 UNITS - (34-21-00/101) C INERTIAL REFERENCE, B7163 L INERTIAL REFERENCE, B7161 R INERTIAL REFERENCE, B7162 GROUND SAFETY RELAY, R988 GROUND SAFETY RELAY, R7073 PROXIMITY SWITCH ELECTRONICS, M7838 UNIT - (32-09-00/101) 
　
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