27-31-15
ALL ú ú 01 Page 404 ú Dec 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
S 864-005
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN
_______ HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
(4)
Pressurize the right hydraulic system (Ref 29-11-00).
S 864-006
(5)
Move the horizontal stabilizer until Dimension B on the stabilizer actuator ballscrew is 15.89 | 0.01 inches
(403.6 +/- 0.25 mm) (Fig. 401).
S 864-007
(6)
Remove the pressure from the right hydraulic system (Ref 29-11-00).
S 214-008
(7)
Make sure the pressure is removed from the left and center hydraulic systems (Ref 29-11-00).
S 864-009
(8)
Put the L, R, and C FLT CONTROL SHUTOFF switches on the right side panel, P61, to the OFF position.
S 864-010
(9)
Put the RIGHT and CENTER STAB TRIM SHUTOFF valve switches on the control stand panel, P10, to the CUTOUT position.
S 864-011
(10)
Open these circuit breakers on the overhead panel, P11, and attach DO-NOT-CLOSE tags:
(a)
11B19, STAB TRIM CONT ALT (IF INSTALLED)
(b)
11C12, STAB TRIM SHUTOFF LEFT
(c)
11C13, STAB TRIM SHUTOFF RIGHT
(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
E.
Remove the Aft Quadrants (Fig. 402)
(1)
Install rig pin E/ST6 in the base of the captain's control column.
S 494-012
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-31-15
ALL ú ú 01 Page 405 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
S 494-013
(2) Install the rig pins E/ST8 and E/ST9 in the left and right
elevator's middle PCAs.
S 494-014
(3) Attach tags to identify the captain's and the first officer's
elevator control cables.
S 034-015
(4) Disconnect the captain's and the first officer's elevator control
cables.
NOTE:____ All three turnbuckles must loosened to make allowances for
the cable tension regulator.
S 034-016
(5) Disconnect the left and right output control rods from the output arms on the aft quadrant.
NOTE: Do not change the adjustment of the output control rods.
____
S 034-017
(6)
Remove the asymmetry limiter actuator (Ref 27-31-03).
S 034-018
(7)
Use the spring removal tool to remove the decentering springs on the elevator feel unit.
NOTE:____There are 4 springs. The force of the installed spring is 100 pounds (445 newtons).
S 034-019
(8)
Disconnect the two control rods for the elevator feel unit from the torque tube levers on the aft quadrant.
S 034-020
(9)
Disconnect the three servo control rods for the autopilot pitch control from the torque tube levers on the aft quadrant.
S 034-021
(10)
Remove the two cam springs from the override mechanism on the aft quadrant.
S 034-022
(11)
Remove the three fasteners that hold the first officer's aft quadrant and torque tube to the captain's aft quadrant and torque tube.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 3(107)
