(2)  
Push, then pull, then center control column. Note increase in pressure required to move control column and check that elevator moves down, then up and returns to center with control column. Observe that autopilot does not disengage.

(3)  
Disengage autopilot and check that control column/wheel moves easily with less pressure required than with autopilot engaged.

C.  Restore Airplane to Normal Configuration
(1)  
Disengage autopilot engage switch.

(2)  
Determine whether there is any further need for electrical power on the airplane; if not, remove external power.

5C8
Jun 20/85 22-11-241 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

A/P AILERON ACTUATOR - 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.  The actuators are installed in the left main wheel well adjacent to the aileron power control units (Ref Chapter 27, Aileron and Aileron Trim Control System).
2.  Equipment and Materials
A.  Fire Resistant Hydraulic Fluid - BMS 3-11
3.  Remove Actuator (Fig. 401)
A.  Depressurize hydraulic systems A and B (Ref Chapter 27, Aileron and Aileron Trim Control System - Maintenance Practices).
WARNING:  PRESSURIZING HYDRAULIC SYSTEMS WILL SUPPLY POWER TO RUDDER, AILERON, ELEVATOR, SPOILER AND SPEED BRAKE SYSTEMS. CARE SHOULD BE TAKEN TO ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.
B.  Open all autopilot circuit breakers on P6 and P18 load control centers and attach DO-NOT-CLOSE tags.
C.  Open tire burst protection screens in left main wheel well (Ref Chapter 27, Tire Burst Screen Doors - Maintenance Practices).
D.  Disconnect hydraulic lines at actuator ports and plug hydraulic lines.
E.  Remove electrical connector from actuator.
F.  Remove the clamp-bolt, washer, and nut that attach the lever assembly to the actuator. Remove the nut and washer that attach the output shaft of the actuator to the lever assembly.
G.  Look through the inspection hole for wear in the shear rivets. Hold the lever assembly and try to turn it at the shear rivet area. Make sure that there is no movement or distortion in the shear rivets.
H.  If there is wear in the shear rivets, then remove the lever assembly.
(1)  
Remove the bolt, washer, and nut that attach the lever assembly to the rod assembly.

(2)  
If it is necessary to remove the lever assembly for the hydraulic system ‘A’ autopilot actuator, remove the bolt, washer, and nut that attach the lever assembly to the second rod assembly.

I.  Remove actuator mounting bolts, washers and nuts, then remove actuator.
J.  Remove reducer and union from actuator ports and save. Install plugs in ports.
4.  Install Actuator
A.  Install reducer and union in actuator ports using new O-rings lightly lubricated with hydraulic fluid.
NOTE: Reducer is installed in pressure port on actuator.

May 01/00 22-11-251 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

H19342
A/P Aileron Actuator Installation  580 
22-11-251  Figure 401  Jun 20/84 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

B.  Check that new unit is filled with hydraulic fluid, cap reducer and unions.
C.  Hold actuator in position and install mounting bolts and washers.
NOTE: Ensure that chamfered (countersunk) side of washer is against head of the bolt.
D.  Place the lever assembly on the actuator and carefully align the splines.
NOTE: The position of a tooth not on the spline provides the access.
E.  If you removed the lever assembly from the rod assembly, then install the bolt, washer, and nut that attach the lever assembly to the rod assembly.
F.  For the lever assembly to the hydraulic system ‘A’ autopilot actuator, install the bolt, washer, and nut that attach the lever assembly to the second rod assembly.
G.  Install the clamp-bolt, washer and nut to attach the lever assembly to the actuator, then install the washer and nut on the output shaft of the actuator.  Tighten the nut on the output shaft, and then tighten the clamp-bolt.
H.  Remove caps and plugs and connect hydraulic lines to actuator.
I.  Connect electrical connector to actuator.
J.  Provide electrical power.
K.  Provide systems A and B hydraulic pressure and check for hydraulic leaks.
WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
　
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(23)