A/P AILERON ACTUATOR - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on
GJ B-2509 and B-2510
1. A/P Aileron Actuator Adjustment
A. General
(1) The aileron rigging must be fully adjusted and operable before the actuator can be adjusted (Ref 27-11-00, Adjustment/Test). The tire burst protection screens must be folded out of the way (Ref Chapter 27, Tire Burst Screen Doors - Maintenance Practices).
B. Equipment and Materials
(1)
VTVM - Hewlett Packard, Model 410C (2 required)
(2)
Test Set - Autopilot Elevator/Rudder/Aileron Control Unit - P/N F80217-125
C. Prepare to Adjust
(1)
Provide electrical and hydraulic power.
(2)
Position hydraulic systems A and B switches on P5 panel to OFF and open FLT CONT SYS circuit breaker on P6 load control center.
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.
(3)
Open autopilot circuit breakers on P6 and P18 load control centers.
(4)
Set ailerons and aileron trim to 0.
(5)
Connect power cable between test set and D152 electronic equipment rack service outlet.
(6)
Disconnect D1827 (A system) and D1691 (B system) connectors from autopilot actuators; connect cables J-1 to actuator A and J-2 to actuator B, then to test set.
(7)
Connect VTVM to LVDT FEEDBACK J10A and J11A on test set (A system).
(8)
Set switches on test set as follows (A system):
(a)
LVDT FEEDBACK switches A ON, B ON.
(b)
LVDT EXCITATION switches A ON, B ON.
(c)
NSS EXCITATION switches A OFF, B OFF.
(d)
NSS FEEDBACK switches A OFF, B OFF.
(e)
SOLENOID EXCITATION (PISTON and ENGAGE) switches A ON, B ON.
(f)
CURRENT SELECT switch to A T-VALVE.
(g)
SOLENOIDS ON/OFF (CENTER SWITCH) - ON.
(h)
A & B SOLENOIDS switches to A NORM, B NORM.
(i)
ACTUATOR SELECT switch to A and B COMMON.
(j)
POWER switch to ON.
NOTE: Lights A and B should be ON. NSS lights should be OFF.
D. Adjust Actuator (Fig. 501)
(1) Remove bolts from one end of rod assembly between the 2 actuators and rod assembly between actuator A and PCU input lever.
Feb 20/93 22-11-251 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2)
Position hydraulic system A and B switches to ON and close FLT CONT SYS circuit breaker.
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)
Operate A position control knob on test set until meter is at lowest reading. Check that voltage between J10A and J11A is less than 0.080 volts and lock position control in place. Check that there is no free play at autopilot output levers. Inspect shear rivet area of output lever and check for no movement in this area. If movement is detected remove lever assembly and replace shear rivets, ref OHM 27-09-05.
(4)
Hold rod assembly thru rod end and lever. Adjust as necessary and check that rod end bearing threads are visible thru inspection holes in rod assembly.
(5)
Tighten jamnut on rod ends. Check that bolt still slips smoothly thru rod end and actuator lever and install bolt, washer and nut.
(6)
Jiggle pilot's control wheel in neutral and ensure system is centered. Check that index mark at inboard end of right aileron is aligned.
(7)
Hold rod assembly to actuator A and check that bolt can be slipped smoothly thru rod end and lever. Adjust as necessary and check that rod end bearing threads are visible thru inspection holes in rod assembly.
(8)
(Deleted)
(9)
Tighten jamnut on rod ends. Check that bolt still slips smoothly thru rod end and actuator lever and install bolt, washer and nut. Check that installation of bolts does not cause any motion of ailerons as observed at right aileron index mark.
中國航空網 m.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(24)
