(5)  
Re-center heading bug and then rotate 45 degrees to the right.

(6)  
Observe that the control wheel rotates clockwise and stops at same angle as in step (4).

(7)  
Observe that the difference between the two control wheel reading is no greater than 4 degrees.

(8)  
Remove electrical and hydraulic power from airplane if no longer required.

5C8
Jun 20/85 22-11-131 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

AILERON FORCE LIMITER - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on
SD ST-AIB and on
WA N235WA-N241WA
GJ B-2509 and B-2510
1.  General (Fig. 401)
A.  The aileron force limiter is located at the bottom of the captain's control column on the aileron drum shaft assembly.
2.  Remove Aileron Force Limiter
A.  Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
B.  Open autopilot and aileron force limiter circuit breakers on P6 and P18 load control centers.
C.  Disconnect force limiter electrical connectors.
D.  Support force limiter; remove mounting bolts, washers and nuts, and remove force limiter.
3.  Install Aileron Force Limiter
A.  Support force limiter and mate spline with shaft assembly and align three holes in force limiter fitting with holes in shaft assembly bracket.
NOTE: Ensure that arrow on force limiter points towards nose of airplane.
B.  Install bolt, washer and nut in aft hole of limiter and bracket and two bolts, washers and nuts in forward holes (bolt shafts point down). Tighten bolts.
C.  Connect electrical connectors to force limiter.
D.  Test force limiter (Ref Aileron Force Limiter - Adjustment/Test).
E.  Close access doors.
May 15/81 22-11-132 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

H19338
Aileron Force Limiter Installation  580 
22-11-132Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/80 

AILERON FORCE LIMITER - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on SD St-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1.  Aileron Force Limiter Test
A.  General
(1)  This test ensures that the aileron force limiter operates properly and assumes that the rest of the autopilot system is operating normally.
B.  Prepare to Test
(1)  
Provide electrical and hydraulic power.

(2)  
Check that hydraulic system A and B switches on P5 panel are positioned to ON and that FLT CONT SYS circuit breaker on P6 load control center is closed.

WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.

(3)  
Ensure that all autopilot circuit breakers are closed on P6 and P18 load control centers.

(4)  
Ensure flaps are up.

C.  Test Aileron Force Limiter
(1)  
Place autopilot A engage switch to CMD, set bank limit to 30 degrees and select HDG SEL mode.

(2)  
Rotate HDG SEL knob on MCP to obtain heading select increase of 45 degrees. Observe control wheel rotates CW and stops between 15 and 19 degrees.

(3)  
Lower flaps 10 units. Observe that the control wheel rotates CW and stops between 23 and 27 degrees. Raise flaps.

(4)  
Reduce heading select signal to zero and disengage autopilot.

(5)  
Repeat steps (1) thru (4) for counterclockwise direction. Observe that the difference between the two control wheel reading is no greater than 4 degrees.

(6)  
Repeat steps (1) thru (5) using autopilot engage switch B.

(7)  
Remove electrical and hydraulic power if no longer required.

Jan 20/82 22-11-132 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

YAW DAMPER COUPLER - REMOVAL/INSTALLATION
EFFECTIVITY
All except aircraft with Yaw Damper Coupler P/N 4084042
1. General
NOTE: For aircraft with coupler P/N 4084042 installed (incorporating SB 27A1206), see 22-12-01.
A.  The yaw damper coupler is retained in the electronic rack by cam-action levers which hook over forks on the shelf.
2.  Remove Coupler
A.  Open yaw damper AC and DC circuit breakers on P6 panel. Wait 3 minutes for rate gyro rundown (if required).
B.  Release coupler by pressing triggers then pull ejection levers to release unit.
C.  Remove coupler.
3.  Install Coupler
A.  Place coupler in rack and simultaneously push ejection levers up until levers are latched per 20-10-111, Electrical/Electronic Black Box - Maintenance Practices.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 2(18)