S 864-016
(8)
Do this task: "Supply Pneumatic Power" (AMM 36-00-00/201).
S 714-017
(9)
Do a check on the flap linkage adjustment:
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE
_______ AND TE FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN YOU MOVE THE FLAP CONTROL LEVER. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(a)
Move the flap control lever more than the 5 unit detent to extend the LE flaps.
CAUTION:_______MAKE SURE TO ADJUST THE FLAP LINKAGE ACCURATELY. THE POWER DRIVE UNIT WILL NOT OPERATE CORRECTLY IF THE FLAP LINKAGE ADJUSTMENT IS NOT ACCURATE.
(b)
Make sure the flap linkage is in the specified limits (Fig. 402).
NOTE:____Use the dimension X with the rigging bar. As an alternative, you can use dimension Y if the tool is not available.
(c)
Make sure the extend stop clearance is in the specified limits (Fig. 402).
(d)
Move the flap control lever to the full UP detent to retract LE flaps.
(e)
Make sure the flaps retract.
G.
Put the Airplane Back to Its Usual Condition
(1)
Do this task: "Pneumatic Power Removal" (AMM 36-00-00/201).
S 864-019
(2)
Do this task to depressurize hydraulic systems No. 1 and 4:
"Hydraulic System Depressurization" (AMM 29-11-00/201).
(3)
Do this task: "Electrical Power Removal" (AMM 24-22-00/201).
S 864-018
S 864-020
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-81-07
ALL ú ú 02 Page 410 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
VARIABLE CAMBER FLAP ACTUATING LINKAGE - REMOVAL/INSTALLATION
_____________________________________________________________
1. General_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the variable camber flap actuating linkage. The procedure has these parts:
(1)
The removal of the variable camber flap
(2)
The removal of the rotary actuators
(3)
The removal of the drive shaft
(4)
The removal of the actuating linkage
(5)
The installation of the actuating linkage
(6)
The installation of the variable camber flap
(7)
The installation of the drive shaft
(8)
The installation of the rotary actuators.
B.
This procedure gives instructions for the removal and installation of actuating links CD and the torque tube with link ABG attached. You remove and install all other actuating links with the variable camber flaps (AMM 27-81-01/401).
TASK 27-81-08-004-001
2. Variable Camber Flap Actuating Linkage Removal (Fig. 401)______________________________________________
A. Special Tools and Equipment
(1)
MIT65B15171 Variable Camber Flap Hinge Nut Torque Adapter
B.
References
(1)
AMM 27-81-02/401, Variable Camber Flaps
(2)
AMM 27-81-05/401, Drive Shaft
(3)
AMM 27-81-07/401, Variable Camber Flaps Rotary Actuator
(4)
AIPC 27-81-02, Fig. 1
(5)
AIPC 27-81-02, Fig. 5
(6)
AIPC 27-81-02, Fig. 10
(7)
SSM 27-81-01, SSM 27-81-02, SSM 27-81-03, SSM 27-81-04, SSM 27-81-05, SSM 27-81-06
(8)
WDM 27-51-21, WDM 27-51-22, WDM 27-81-11, WDM 27-81-12, WDM 27-81-21, WDM 27-81-22, WDM 27-81-31, WDM 27-81-32, WDM 27-81-41, WDM 27-81-42, WDM 27-81-81, WDM 27-81-82
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 7(139)
