AUTOPILOT ROLL COMPUTER - REMOVAL/INSTALLATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The autopilot roll computer is retained in the electronic rack by cam-action levers which hook over forks on the shelf.
2. Remove Computer
A. Open autopilot circuit breakers on P6 or P18 panel.
B. Release computer by pressing triggers then pull ejection levers to release unit.
C. Remove computer.
3. Install Computer
A. Place computer in rack and simultaneously push ejection levers up until levers are latched per 20-10-111, Electrical/Electronic Black Box - Maintenance Practices.
B. Check that roll computer self-test switch is positioned to OFF.
C. Close autopilot circuit breakers.
4. Installation Test
A. Provide electrical power to airplane buses.
B. Open radio altimeter circuit breakers.
C. Perform Roll Control Channel Self-Test:
STEP ACTION OBSERVATION
(1)
Engage AIL engage switch and select a
VOR frequency
(2)
Disengage AIL engage switch
(3)
Place self-test switch in OFF position Self-test meter reads in RED range
(4)
Rotate self-test switch from OFF to Self-test meter slowly increased to
position 1 YELLOW range, after 10 seconds in YELLOW range, rapidly decreases to zero, then rapidly increases with a reduction in rate of increase in the YELLOW range, then slowly and continuously increases to right stop
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STEP ACTION OBSERVATION
(5) Rotate self-test switch from position 1 to 2 Self-test meter initially deflects to left, then settles in YELLOW range
(6) Rotate self-test switch from position 2 to 3 Self-test meter initially deflects to left, then settles in YELLOW range within 1 minute
(7) Rotate self-test switch from position 3 to 4 Self-test meter initially deflects to zero then increases, momentarily settles in the YELLOW range, then slowly increases toward right stop
(8) Rotate self-test switch from position 4 to 5 Self-test meter initially deflects left, then increases with 2 rate changes; the second rate change should occur in the YELLOW range. Indicator then increases toward right stop
(9) Rotate self-test to OFF
D. Disengage autopilot and restore airplane systems to normal.
E. Remove electrical power if no longer required.
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22-11-161 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/84
.AUTOPILOT ACCESSORY UNIT - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SBL thru ZS-SBR WA N4502W-N4571M GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The autopilot accessory unit is retained in the electronic rack by a cam-action lever which hooks on a shelf mounted fork.
2. Remove Accessory Unit
A. Open autopilot, yaw damper, A/P stabilizer trim and auto throttle (when installed) circuit breakers.
B. Release unit by pressing trigger to release, then pull ejection lever to release unit.
C. Remove accessory unit.
3. Install Accessory Unit
A. Examine mounting tray and connectors for distortion of tray and bent or pushed back connector pins. Repair as required.
B. Place accessory unit in rack and push ejection handle up until lever is latched per 20-10-111, Electrical/Electronic Black Box - M/P.
C. Close circuit breakers opened in step 2.A.
4. Installation Test
A. Provide electrical power to airplane buses.
B. Provide attitude valid and compass valid signals.
C. Engage autopilot (pitch and roll). Operate stab trim switch on aisle stand to CUTOUT position. Check that autopilot or pitch channel disengages and that A/P disengage warning lights flash.
D. Disengage autopilot, if engaged. Restore airplane to normal.
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