S 438-012

 (9)  
Install the splice tube with the primer wet (AMM 51-24-01/701):

 (a)  
Install the bolts and nuts.

 (b)  
Tighten the nuts to 15-20 pound-inches (1.7-2.3 N-m) more than the run-on torque.

 S 228-014
 (10)
 Do a check of the torque tube.

 (a)  
The maximum permitted eccentricity is 0.010 inch (0.25 mm)

 T.I.R. for each foot (0.3 meter) of length.
 S 378-015
 (11)
 Apply alodine to the torque tube.

 S 378-025

 (12)
 Apply two layers of primer to the repaired area.

 S 428-016

 (13)
 Install the torque tube (AMM 27-51-20/401).

 TASK 27-51-20-408-017
 4.  Flap Torque Tube Coupling Installation______________________________________
 A. Standard Tools and Equipment
 (1)  
Rivets - BACR15BB8D10, or equivalent (10 necessary)

 B.
Consumable Materials

 (1)  
C00259 Enamel - Primer, Green, BMS 10-11

 C.
References

 (1)  
AIPC 27-51-60, Fig. 1

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-20
 ALL  ú ú 01 Page 805 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 D. Access
 (1)  Location Zone 135 Wing Landing Gear Wheel Well, LH 136 Wing Landing Gear Wheel Well, RH 572 Landing Gear Support Beam and Rear Spar to Trailing Edge,
 LH 672 Landing Gear Support Beam and Rear Spar to Trailing Edge,
 RH
 581 Rear Spar to Trailing Edge, LH
 681 Rear Spar to Trailing Edge, RH

 E. Install a torque tube coupling
 S 378-018
 (1)  
Apply a layer of primer to the torque tube and the inner surface of the coupling (Fig. 802).

 S 428-019

 (2)  
Before the primer dries, put the coupling in its position on the torque tube (Fig. 802).

 S 358-020

 (3)
Drill No. F 0.257 inch (6.53 mm) holes in the torque tube in the same location as the holes in the coupling (10 locations).

RIVET (10 LOCATIONS) COUPLING

TORQUE TUBE ASSEMBLY
(12.2 mm)
Torque Tube Coupling Installation
Figure 802

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-20
 ALL  ú ú 01 Page 806 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 358-021
 (4) Install the rivets.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-20
 ALL  ú ú 01 Page 807 ú Oct 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 FLAP ANGLE GEARBOXES - 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 a flap angle gearbox. The procedure has these parts:
 (1)
The installation of the landing gear door locks

 (2)
The extension of the flaps

 (3)
The removal of an angle gearbox

 (4)
The installation of the angle gearbox

 (5)
The retraction of the flaps.

 B.  
There are eight angle gearboxes in the flap drive system. This procedure applies to each of them.

 TASK 27-51-21-004-001
 2.  Flap Angle Gearbox Removal (Fig. 401)
__________________________
 A.  References
 (1)
27-51-20/401, Flap Torque Tube

 (2)
29-11-00/201, Main Hydraulic Supply System
　
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(180)