S 864-067

 (10)
 Set the CAL/RUN switch in the CAL CHK position.

 (a)  Make sure in phase volts are 9.990 to 10.010.
 S 864-068
 (11)
 Set the CAL/RUN switch in the RUN position.

 S 034-045

 (12)
 Disconnect the electrical connector from the Autopilot Pitch Control Servo.

 S 484-046

 (13)
 Connect the -5 cable assembly to the Autopilot Pitch Control Servo and Phase Synchronous Voltmeter.

 F. Adjust the Autopilot Pitch Control Servo
 S 824-047
 (1)  
Adjust the Autopilot Servo control rod (7) until the Phase Synchronous voltmeter shows +3.72 |.03 with the control rod (7) connected to the servo.

 S 434-048

 (2)  
Use the bolt (4), the washers (5), and the nut (6) to connect the servo control rod assembly (7).

 S 434-049

 (3)  
Tighten the control rod (7) jamnut.

 S 864-050

 (4)  
Disconnect the Phase Synchronous Voltmeter

 (a)  
Set the ON/OFF switch in the OFF position.

 (b)  
Disconnect the -5 cable assembly from the Autopilot Pitch Control Servo.

 (c)  
Disconnect the voltmeter from the power source.

 S 434-051
 (5)  
Connect the airplane electrical connector to the autopilot pitch control servo.

 (6)  
Remove the rig pin E/ST 7.

 (7)
Do the "Test the Autopilot Pitch Control Servo Installation" steps.

 S 084-052
 S 734-053
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-12-01
 ALL  ú ú 01 Page 412 ú Mar 20/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 TASK 22-12-01-734-054
 7.  Test the Autopilot Pitch Control Servo Installation___________________________________________________
 A. References
 (1)  
06-42-00/201, Empennage (Major Zone 300) Access Doors and Panels

 (2)  
22-00-02/201, Autoflight BITE

 (3)  
29-11-00/201, Pressurize/Depressurize Main Hydraulic System

 B. Access
 (1)  
Location Zone 313 Stabilizer Center Section Compartment (Left)

 (2)  
Access Panel
 313AL Control Bay Access Door

 C. Prepare to Test
 S 864-078
 (1)  Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:
 (a)  
11E17, FLT CONT COMPUTER POWER LEFT

 (b)  
11E18, FLT CONT COMPUTER SERVO LEFT

 (c)  
11E20, FLIGHT CONT CMPTR PWR CENTER

 (d)  
11E21, FLIGHT CONT CMPTR SERVO CENTER

 (e)  
11E35, FLT CONT CMPTR PWR RIGHT

 (f)  
11E36, FLT CONT CMPTR SERVO RIGHT

 (g)  
11H17, FLT CONT SHUTOFF TAIL LEFT

 (h)  
11H18, FLT CONT SHUTOFF TAIL CENTER

 (i)  
11H28, FLT CONT SHUTOFF TAIL RIGHT

 S 864-079
 (2)  On the P61 panel, remove the DO-NOT-OPERATE tags and set the L, C and R FLT CONTROL SHUTOFF switches on panel P61 in the ON position.
 S 864-080
 WARNING:_______STAY OFF ALL OF THE CONTROL SURFACES. THE CONTROL SURFACES USE HYDRAULIC POWER AND MAY MOVE WHEN ANY CONTROLS ARE MOVED OR WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (3)  
Supply hydraulic pressure (Ref 29-11-00).

 (4)  
Manually operate the elevator system three times.

 (5)
Make sure these circuit breakers on the P11 panel are closed:

 S 864-081
 S 864-082
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-12-01
 ALL  ú ú 07 Page 413 ú Mar 20/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 1(144)