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B.  Check that yaw damper self-test switch is positioned to OFF.
C.  Close yaw damper circuit breakers.
4.  Installation Test
A.  Provide electrical power to airplane and energize load control center P6.
B.  Pressurize hydraulic system B then apply hydraulic pressure to control surfaces (Ref 29-12-0).
WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, SPOILER SPEED BRAKE AND RUDDER SYSTEM. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
C.  Check that flight control B switch is on.
D.  Engage yaw damper and check that yaw damper disengage warning light is off.
E.  Position yaw damper engage switch to OFF position. Verify that yaw damper disengaged light illuminates.
F.  Engage yaw damper, check that rudder is centered and remains steady.
G.  Position cockpit yaw damper test switch to left and hold. Observe rudder deflects left and returns to center. Center test switch and observe that rudder deflects right then returns to center. Position test switch to right and hold. Observe rudder deflects right and returns to center. Center test switch and observe that rudder deflects left then returns to center.
NOTE: Do not hold test switch longer than 10 seconds, torquing coil will overheat.
H.  Remove hydraulic and electrical power if no longer required.
May 01/00 22-11-141 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

ACCELEROMETER - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA - N241WA GJ B-2509 and B-2510
1.  General
A.  Two identical 3 axis accelerometers are installed below the J10 box on left outboard forward side of forward cargo compartment. Removal and installation is similar for both units.
2.  Remove Accelerometers
A.  Open autopilot AC circuit breakers on P6 and P18 load control centers.
B.  Remove lower left forward sidewall panel in forward cargo compartment.
C.  Disconnect connector from airplane wiring.
D.  Remove mounting screws and accelerometer.
3.  Install Accelerometer
A.  Hold accelerometer in position and install mounting screws.
B.  Install connector to airplane wiring.
C.  Reinstall cargo compartment sidewall panel.

H88490
512  Accelerometer Installation 
May 20/82  Figure 401  22-11-142 
Page 401 

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

AUTOPILOT PITCH COMPUTER - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SBL thru ZS-SBR SD ST-AFK, ST-AFL WA N7502-N4571M GJ ALL EXCEPT B-2509 and B-2510
1.  General
A.  The autopilot pitch 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. Wait 3 minutes for rate gyro rundown (if applicable).
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 pitch 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.
NOTE:  Do not apply rate gyro test signals for longer than 10 seconds. On airplanes with computers using derived rate circuits, ignore steps using rate gyro switch.
C.  Perform Pitch Control Channel Self-Test:
STEP ACTION  OBSERVATION
(1)  
With self-test switch in OFF position Meter reads in RED range

(2)  
Rotate self-test switch from OFF to Meter moves to right at a constant rate for

position 1  approximately 10 seconds. Rate of movement changes in the YELLOW range

(3)  
Rotate self-test switch from position Self-test meter initially deflects to right stop, 1 to 2 then decreases and settles in YELLOW range

Feb 20/84 22-11-151 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

STEP ACTION
(4)  
Rotate self-test switch from position 2 to 3

(5)  
Rotate self-test switch from position 3 to 4

(6)  
Rotate self-test switch from position 4 to 5

(7)  
Rotate self-test switch to OFF position

(8) 
 Engage autopilot

 OBSERVATION
　
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