(a)  
Make sure that the stabilizer does not move.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-41-10
 ALL  ú ú 02.1 Page 414 ú Sep 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 S 864-044
 (6) Release the control wheel switches and then release the BRAKE BYPASS
 valve button.
 S 864-045
 (7) Use the control wheel switches to move the stabilizer through its
 full travel range.
 (a) Make sure the stabilizer moves smoothly and freely through its
 full travel.
 (b) Make sure that the anti-rotation cables stay loose through the
 full stabilizer travel.
 (c) Make sure there are no leaks or damage in the hydraulic line
 connections.
 S 714-052
 (8) AIRPLANES WITH STAB TRIM LEVERS ON THE CONTROL STAND;
 do the Manual Operation and Mechanical Travel Limits Test
 ú  (AMM 27-41-00/501).
 S 714-053
 (9) AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND;
 do the Alternate-Electric Operation and Travel Limits Test
 ú  (AMM 27-41-00/501).
 H.  Put the Airplane Back to Its Usual Condition
 S 414-047
 (1) Close the access door for the forward stabilizer compartment, 311AL
 ú  (AMM 06-42-00/201).
 ú
 ú  S 864-048
 ú  (2) Remove the power from the hydraulic systems (AMM 29-11-00/201).
 ú
 ú  S 864-049
 ú  (3) Remove electrical power, if it is not necessary (AMM 24-22-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-41-10
 ALL  ú ú 02.1 Page 415 ú Sep 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

1.

2.

ú ú ú
ú ú ú
ú
757 MAINTENANCE MANUAL
 STABILIZER TRIM DRIVE HYDRAULIC MOTOR - REMOVAL/INSTALLATION
____________________________________________________________
General
_______
 A.  This procedure contains steps to remove and install the hydraulic motor on the stabilizer ballscrew actuator.
 TASK 27-41-11-024-001Remove the Hydraulic Motor
__________________________
 A.  References
(1)  
AMM 06-42-00/201, Empennage Access Doors and Panels

(2)  
AMM 24-22-00/201, Electrical Power - Control

(3)  
AMM 29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems

 B.  
Access

 (1)  
Location Zones
 211/212 Control Cabin
 311/312 Area Aft of Pressure Bulkhead to BS 1787.45

 (2)  
Access Panel
 311AL Forward Stabilizer Compartment

 C.  
Prepare for the Removal

S 864-002
(1)  
Supply electrical power (AMM 24-22-00/201).

 S 864-003

 (2)  
Remove the pressure from the right and center hydraulic systems andreservoirs (AMM 29-11-00/201).

 S 864-004

 (3)  
Put the RIGHT and CENTER STAB TRIM SHUTOFF valve switches on the control stand panel, P10, to the CUTOUT position.

 S 864-005

 (4)  
Open these circuit breakers on the overhead panel, P11, and attach DO-NOT-CLOSE tags:

 (a)  
11B19, STAB TRIM ALT (IF INSTALLED)

 (b)  
11C12, STAB TRIM SHUTOFF LEFT

 (c)  
11C13, STAB TRIM SHUTOFF RIGHT

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-41-11
 ALL  ú ú 02.1 Page 401 ú Sep 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 4(73)