S 094-087

 (19)
 Remove the DO-NOT-OPERATE tags from the control columns.

 S 864-044

 (20)
 Release the control columns and put them back to the center position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-05
 ALL  ú ú 01 Page 421 ú May 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757 MAINTENANCE MANUAL
 S 864-093
 (21)
 Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:

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

 (b)
11C12, STAB TRIM SHUTOFF RIGHT

 (c)
11C13, STAB TRIM SHUTOFF LEFT

 (d)
11H11 or 11C05, STAB TRIM CONT L

 (e)
11H17, FLT CONT SHUTOFF TAIL LEFT

 (f)
11H18, FLT CONT SHUTOFF TAIL CTR

 (g)
11H20, STAB TRIM CONT R

 (h)
11H28, FLT CONT SHUTOFF TAIL RIGHT

 (i)
11J10, PCU MON SENSOR

 (j)
11J11, PCU MON MOD

 S 864-094
 (22)
 Move the RIGHT and LEFT STAB TRIM SHUTOFF valve switches on the control stand panel, P10, to the NORM position.

 S 864-095

 (23)
 Put the L, R, and C FLT CONTROL SHUTOFF switches on the right side panel, P61, to the ON position.

 S 824-048

 (24)
 Adjust the power control actuator (AMM 27-31-00/501).

 S 724-049

 (25)
 Do a test on the elevator travel limits (AMM 27-31-00/501).

 S 724-096

 (26)
 Do a test on the Elevator PCU Monitor System (AMM 27-31-00/501).

 F.
Put the Airplane Back to Its Usual Condition

 (1)
Install the trailing edge beam and the seal panel.

 S 424-017
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-31-05
 ALL  ú ú 02 Page 422 ú May 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
 S 414-097
 (2)  
Install the PCA access panels, 335DB or 345DB, as necessary (AMM 06-42-00/201).

 S 864-019

 (3)  
Remove electrical power (AMM 24-22-00/201).

 TASK 27-31-05-024-099
 6.  Remove the Elevator Idler Link______________________________
 A. Equipment
 (1)  
Lock Assemblies from the Elevator PCA Lockout Equipment, B27009-12:

 (a)  
Lock Assembly, PCA, B27009-2

 NOTE:____The PCA lock assembly is installed on the PCA. It contains a shear-out device that can help prevent any damage caused by accidental operation during maintenance.

 (b)  
Lock Assembly, PCA Input Linkage, B27009-3

 NOTE: The input linkage lock assembly holds the linkage in
____ the elevator at the up position during maintenance. It is installed on the center PCA linkage.
 B. References
 (1)  
AMM 06-42-00/201, Empennage Access Doors and Panels

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

 (3)  
AMM 27-02-00/601, Flight Controls Surfaces

 (4)  
AMM 27-31-05/601, Elevator Power Control Actuator

 (5)  
AMM 27-61-00/201, Spoiler/Speedbrake Control System

 (6)  
AMM 29-11-00/201, Main (Left, Right and Center) Hydraulic Systems

 C.
Access

 (1)  
Location Zones 211/212 Control Cabin 335/345 Horizontal Stabilizer, Rear Spar to Trailing Edge

 (2)  
Access Panels 335DB/345DB Left/Right Elevator, PCU's and Control Linkage

 D.
Prepare for the Removal

 S 844-100
 (1)  
Prepare for removal with the instructions given in the "Prepare for Removal" paragraph.

 E.
Idler Link Removal (Fig. 401)

 S 024-101
 (1)  
Do these two steps only if you remove the right outboard PCA idler link:

 (a)  
Remove the screws (one on each end) that connect the pressure sensor conduit to the stabilizer rear spar (Fig. 403).
　
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 3(83)