(c)
Move the right STAB TRIM lever forward until you get continuity in the switch, S538, and identify this position as point "F" on the tape.
(d)
Move the right STAB TRIM lever aft until you get continuity in the switch, S538, and identify this position as point "A" on the tape.
(e)
Find the point half way between points "A" and "F", and identify this middle-point as "M" on the tape.
(f)
If point "M" is greater than 0.1 inch (2.5 mm) away from point "N", adjust the body cables for the stabilizer trim (Ref 27-41-00/501).
NOTE: Use point "M" +/- 0.05 inch (1.27 mm) as an alternative
____ to the adjustment limit position-decal for the cable adjustment.
(g)
If point "M" is not greater than 0.1 inch (2.5 mm) away from point "N", no adjustment will be necessary.
F.
Put the Airplane Back to Its Usual Condition
S 864-017
(1)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:
(a)
11C6, CSEU 1L AC
or FLT CONT ELEC 1L AC
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STAB TRIM LEVERS ON THE ú
27-41-15
CONTROL STAND ú ú 02 Page 405 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(b) (c) (d) (e) (f) (g) (h) (i) (j) 11C7, CSEU 1L DC or FLT CONT ELEC 1L DC11C8, CSEU 2L AC or FLT CONT ELEC 2L AC11C9, CSEU 2L DC or FLT CONT ELEC 2L DC11C12, STAB TRIM SHUTOFF LEFT11C13, STAB TRIM SHUTOFF RIGHT11G17, CSEU 1R AC or FLT CONT ELEC 1R AC11G18, CSEU 1R DC or FLT CONT ELEC 1R DC11G27, CSEU 2R AC or FLT CONT ELEC 2R AC11G28, CSEU 2R DC or FLT CONT ELEC 2R DC
(2) S 444-018Do the activation procedure for the spoilers if you did the deactivation procedure (Ref 27-61-00).
(3) S 864-019Put the LEFT and CENTER STAB TRIM SHUTOFF valve switches on the control stand panel, P10, to the NORM position.
(4) S 414-020Install the access panel on the right side of the control stand.
(5) S 864-021Remove electrical power if it is not necessary (Ref 24-22-00).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STAB TRIM LEVERS ON THE ú
27-41-15
CONTROL STAND ú ú 02 Page 406 ú Jan 20/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
HORIZONTAL STABILIZER ALIGNMENT TABS - REMOVAL/INSTALLATION
___________________________________________________________
1. General
_______
A. This section contains the procedure to install alignment tabs for the stabilizer neutral position, and the manual control upper and lower limit positions.
TASK 27-41-17-424-001
2. Install the Stabilizer Alignment Tabs
_____________________________________
A. References
(1)
AMM 20-10-15/401, Stencil Markings
(2)
AMM 27-41-00/501, Horizontal Stabilizer Trim Control System
B.
Access
(1)
Location Zones 211/212 Area Aft of Pressure Bulkhead to BS 1725 332 Horizontal Stabilizer Leading Edge (Left)
C.
Install the Alignment Tabs
S 214-002
(1)
Find the alignment tab on the stabilizer leading edge. It is on the center of the inboard leading edge of the left stabilizer (Fig. 401).
S 424-009
(2)
If an alignment tab is not installed on the stabilizer, install an alignment tab by stencil (AMM 20-10-15/401).
S 864-004
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES
_______ BEFORE THE STABILIZER IS MOVED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(3) Move the stabilizer such that Dimension B on the stabilizer ballscrew actuator is correct for installation of the alignment tabs (Fig. 401 and 402).
NOTE: For the procedures to move the stabilizer and to measure
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 飞行操纵 FLIGHT CONTROLS 4(84)
