(c)  
Remove the flap lever lock from the flap control lever.

 TASK 27-51-00-402-031
 12. Flap Lever Lock Installation____________________________
 A. General
 (1)  
The flap lever lock prevents accidental movement of the flap control lever. With electrical power on, the flaps will operate if you move the flap control lever.

 B.
Special Tools and Equipment

 (1)  
G27024 Flap Lever Lock

 C.
Access

 (1)  
Location Zone
 221, 222 Control Cabin

 D.
Procedure

 S 422-032
 (1)  
Install the flap lever lock (Fig. 202):

 (a)
Set the flap lever lock on the flap control lever.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 01 Page 221 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
 (b) (c) (d)  Let the flap lever lock fall on the detent plate.Tighten the screw on the flap lever lock.Make sure you cannot move the flap control lever. 

FLAP

Flap Lever Lock Installation
Figure 202

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 01 Page 222 ú Jun 10/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST
___________________________________________
 1.  General_______
 A.  There are three tasks in this procedure. There is a system test of the trailing edge (TE) flap control system. There is a system test of the load relief system for the trailing edge flaps. There is also a ground test of the flap control units (FCU's).
 (1)  
The TE flap control system test has these parts:

 (a)  
A test of the flap control lever

 (b)  
A test of the flap control units

 (c)  
A test of the flap load relief system

 (d)  
The installation of the door locks on the body landing gear

 (e)  
A test of the primary hydraulic operation

 (f)  
A test of the primary electric operation

 (g)  
A test of the alternate electric operation

 (h)  
A test of the trailing edge flap no-coast drag brake

 (i)  
The removal of the door locks from the body landing gear.

 (2)  
The system test of the load relief system for the trailing edge flaps has these parts:

 (a)  
An extension of the flaps

 (b)  
The installation of a pitot pressure source

 (c)  
A test of the system at 30 units

 (d)  
A test of the system at 25 units

 (e)  
The retraction of the flaps

 (f)  
The removal of the pitot pressure source.

 TASK 27-51-00-735-001
 2.  System Test - Trailing Edge Flap System_______________________________________
 A.  Standard Tools and Equipment
 (1)  
Spring Scale, 0-10 pound (0-5 kilogram) range

 B.  
References

 (1)  
24-22-00/201, Manual Control

 (2)  
29-11-00/201, Main Hydraulic Supply System

 (3)  
32-00-30/201, Landing Gear Door Locks

 (4)  
36-00-00/201, Pneumatic System

 C.  
Access

 (1)  
Location Zone
 137 Body Landing Gear Well, LH
 138 Body Landing Gear Well, RH
 221 Control Cabin, LH
 222 Control Cabin, RH
 577 Inboard Flap LH
 587 Outboard Flap LH
 677 Inboard Flap RH
 687 Outboard Flap RH

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 01 Page 501 ú Jun 18/00
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 4(59)