(d)  Test autopilot A aileron actuator. 1) Open AUTOPILOT circuit breakers (P6 and P18). 2) Remove connector D1827 from A aileron autopilot actuator. 3) Install J1 lead to test set and A aileron autopilot actuator connector. 4) Connect power cable of test set to D152 electronic equipment rack service
outlet. Make certain test set POWER switch is OFF.
5)  Establish a basic flow rate with system A flight controls switched ON and isolation valves 1, 2 and 3 closed. Record this flow as base for autopilot A aileron actuator leakage.
NOTE:  Ground interconnect must be open to accomplish this step using ammeter readings vs flow.
6)  Set test set switches:
a) SOLENOID EXCITATION [PISTON and ENGAGE] A - ON (2)
b) CURRENT SELECT switch - A T-VALVE
c) SOLENOIDS selector switch - A NORMAL
d) SOLENOID ON/OFF switch - ON
e) ACTUATOR SELECT switch - A only
f) POWER switch - ON

CAUTION:  PERSONNEL AND EQUIPMENT MUST BE CLEARED FROM SURFACE MOVEMENT AREA PRIOR TO APPLYING POWER TO PREVENT EQUIPMENT DAMAGE OR PERSONNEL INJURY.
7) Adjust A ONLY ACTUATOR SELECT POSITION CONTROL until ailerons are neutral. Allow flow to stabilize and take reading. 8) Difference between flow rate step (d)5) and (d)7) is leakage for autopilot A
aileron actuator. Maximum permissible 2000 cc/min. 9) Place POWER switch on test set - OFF. 10) Place SOLENOID EXCITATION [PISTON/ENGAGE] switches (2) - OFF.
501 
29-00 Page 618B  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/84 

11) Remove J1 cable from autopilot A aileron actuator.
12) Install connector D1827 to autopilot A aileron actuator.
13) Close AUTOPILOT circuit breakers (P6 and P18).

(e) Test autopilot B elevator actuator. 1) Open AUTOPILOT circuit breakers (P6 and P18). 2) Remove connector D1687 from B elevator autopilot actuator. 3) Install J2 lead to test set and B elevator autopilot actuator connector. 4) Connect power cable of test set to D152 electronic equipment rack service outlet. Make certain test set POWER switch is OFF. 5) Establish a basic flow rate with system B flight controls switched ON and isolation valves 4 and 5 closed and isolation valve 6 open. Record this flow as base for autopilot B elevator actuator leakage.  Note left elevator position.
6)  Set test set switches:
a) SOLENOID EXCITATION [PISTON and ENGAGE] B - ON (2)
b) CURRENT SELECT switch - B T-VALVE
c) SOLENOIDS selector switch - B NORMAL
d) SOLENOID ON/OFF switch - ON
e) ACTUATOR SELECT switch - B only
f) POWER switch - ON

CAUTION:  PERSONNEL AND EQUIPMENT MUST BE CLEARED FROM SURFACE MOVEMENT AREA PRIOR TO APPLYING POWER TO PREVENT EQUIPMENT DAMAGE OR PERSONNEL INJURY.
7)  Adjust B ONLY ACTUATOR SELECT POSITION CONTROL until left elevator is within 1/2 inch of position noted in step (e)5). Allow flow to stabilize and take reading.
8)  Difference between flow rate step (e)5) and (e)7) is leakage for autopilot B elevator actuator. Maximum permissible 2000 cc/min.
501 
Oct 20/84  29-00 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Page 618C 

9) Place POWER switch on test set - OFF.
10) Place SOLENOID EXCITATION [PISTON/ENGAGE] switches (2) - OFF.
11) Remove J2 cable from autopilot B elevator actuator.
12) Install connector D1687 to autopilot B elevator actuator.
13) Close AUTOPILOT circuit breakers (P6 and P18).

(f) Test autopilot A elevator actuator. 1) Open AUTOPILOT circuit breakers (P6 and P18). 2) Remove connector D1681 from A elevator autopilot actuator. 3) Install J2 lead to test set and A elevator autopilot actuator connector. 4) Connect power cable of test set to D152 electronic equipment rack service outlet. Make certain test set POWER switch is OFF. 5) Establish a basic flow rate with system B flight controls switched ON and isolation valves 1 and 2 closed and isolation valve 3 open.  Record this flow as base for autopilot A elevator actuator leakage.  Note right elevator position.
6)  Set test set switches:
a) SOLENOID EXCITATION [PISTON and ENGAGE] A - ON (2)
b) CURRENT SELECT switch - A T-VALVE
c) SOLENOIDS selector switch - A NORMAL
d) SOLENOID ON/OFF switch - ON
e) ACTUATOR SELECT switch - A only
f) POWER switch - ON

CAUTION:  PERSONNEL AND EQUIPMENT MUST BE CLEARED FROM SURFACE MOVEMENT AREA PRIOR TO APPLYING POWER TO PREVENT EQUIPMENT DAMAGE OR PERSONNEL INJURY.
7)  Adjust A ONLY ACTUATOR SELECT POSITION CONTROL until right elevator is within 1/2 inch of position noted in (f)5). Allow flow to stabilize and take reading.
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 液壓 HYDRAULIC POWER(16)