EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-12-00
ALL ú ú 01 Page 102 ú Dec 20/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 FAULT ISOLATION/MAINT MANUAL
ELECTRICAL ELECTROHYDRAULICCONNECTOR (REF) SERVO VALVE
ELECTROHYDRAULIC SOLENOID VALVE NO. 1
ELECTROHYDRAULIC SOLENOID VALVE NO. 2
LEFT, CENTER, OR RIGHT AUTOPILOT PITCH CONTROL SERVO M271,M272 OR M273
CENTER ELEVATOR NEUTRAL SHIFT GREEN TAPE (REF) B FROM SHT 1
TRANSDUCER, LEFT ELEVATOR
TS5151 NEUTRAL SHIFT
TRANSDUCER, TS5153 CONTROL COLUMNS
SEE D
FORWARD EQUIPMENT CENTER ACCESS DOOR,113AL
FWD
RIGHT ELEVATOR CAPTAIN FIRST
NEUTRAL SHIFT OFFICER
TRANSDUCER, GREEN TAPE (REF) TS5152
FEEL AND CENTERING UNIT ASSEMBLY (REF)
C FROM SHT 1
FLIGHT COMPARTMENT FLOOR (REF)
LEFT ELEVATOR CONTROL FORCE TRANSDUCER, RIGHT ELEVATOR CONTROLTS15 1 FORCE TRANSDUCER,
TS14 1
CONTROL COLUMNS (VIEW IN THE FORWARD DIRECTION)
D
1 AIRPLANES WITH CONTROL WHEEL STEERING
Autopilot/Flight Director Pitch Channel - Component Location Figure 102 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-12-00
ALL ú ú 06 Page 103 ú Dec 20/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
AUTOPILOT PITCH CONTROL SERVO - REMOVAL/INSTALLATION
____________________________________________________
1. General (Fig. 401)_______
A. There are three autopilot pitch servos. They are attached to the torque box aft of the horizontal stabilizer at section 48 of the airplane.
B. This procedure includes tasks to remove, install, adjust, and test the Autopilot Pitch Control Servo. A task is also included to replace the control rod.
C. There are two tasks to adjust the Autopilot Pitch Control Servo:
(1)
Adjustment with the Maintenance Control Display Panel (MCDP)
(2)
Adjustment with the Phase Synchronous Voltmeter Model 101A
TASK 22-12-01-004-065
2. Remove the Autopilot Pitch Control Servo________________________________________
A. References
(1)
06-42-00/201, Empennage (Major Zone 300) Access Doors and Panels
(2)
24-22-00/201, Electrical Power - Control
(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 for Removal
S 864-001
(1)
Supply electrical power (Ref 24-22-00).
S 864-002
(2)
Remove the pressure from the left, center and right hydraulic systems (Ref 29-11-00).
S 864-003
(3)
On right side panel, P61, set the L, C and R FLT CONTROL SHUTOFF switches in the OFF position and attach DO-NOT-OPERATE tags.
(4)
Set the two F/D switches on the MCP in the OFF position.
S 864-005
(5)
Open these circuit breakers on the overhead circuit breaker panel, P11, and attach DO-NOT-CLOSE tags:
(a)
11H17, FLT CONT SHUTOFF LEFT
(b)
11H18, FLT CONT SHUTOFF CENTER
(c)
11H28, FLT CONT SHUTOFF RIGHT
(d)
For the left servo: 1) 11E17, FLT CONT COMPUTER POWER LEFT 2) 11E18, FLT CONT COMPUTER SERVO LEFT
S 864-004
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-12-01
ALL ú ú 01 Page 401 ú Dec 20/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：757 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(139)
