27-21-08
 ALL  ú ú 01 Page 601 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

SEE A
A 
AFT QUADRANT A 
2. QUADRANT (CLEVIS/BOLT)  A 
1. QUADRANT/BEARING  3.  QUADRANT/BEARING 

4. BEARING/BOLT
A-A
Rudder Aft Quadrant Wear Limits Figure 601 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-08
 ALL  ú ú 01 Page 602 ú Dec 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

INDEX NO.  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  WORN PART REPLACE  PART WORN REPAIR  INSTR. REPAIR 
DIAMETER  MITTED PER-WEAR DIM.  MAX ANCE CLEAR-DIAM 
MIN  MAX 
1  QUADRANT  ID  0.8738  0.8743  0.8750  0  1 
BEARING  OD  0.8745  0.8750  0.8740  X 
2  QUADRANT (CLEVIS)  ID  0.2500  0.2540  0.2545  0.0060  2 
BOLT  OD  0.2485  0.2495  0.2480  X 
3  QUADRANT  ID  0.8748  0.8753  0.8770  0.0020  1 
BEARING  OD  0.8745  0.8750  0.8730  X 
4  BEARING  ID  0.3745  0.3750  0.3755  0.0020  X 
BOLT  OD  0.3735  0.3745  0.3730  X 

SHRINK FIT BUSHING
PRESS FIT BUSHING

Rudder Aft Quadrant Wear Limits
Figure 601 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-08
 ALL  ú ú 01 Page 603 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 AILERON AND RUDDER TRIM CONTROL MODULE -
______________________________________ MAINTENANCE PRACTICES
_____________________
 1.  General_______
 A.  There are three tasks in this procedure. The first task is the removal of the trim control module for the aileron and the rudder. The second task is the installation of trim control module for the aileron and the rudder. The third task is to clean the rudder trim switch.
 TASK 27-21-09-002-001
 2.  Aileron and Rudder Trim Control Module - Removal (Fig. 201)________________________________________________
 A.  References
 (1)  
AMM 24-22-00/201, Manual Control

 B.  
Access

 (1)  
Location Zones
 221/222 Control Cabin

 C.  
Prepare for the Removal

 S 862-002
 (1)  
Supply electrical power (AMM 24-22-00/201).

 S 862-003

 (2)  
Put the FLT CONTROL HYD POWER - TAIL switches No. 1, 2, 3 and 4 on the overhead panel to the SHUTOFF position and attach DO-NOT-OPERATE tags.

 S 862-004

 (3)  
Open these circuit breakers and attach DO-NOT-CLOSE tags:

 (a)  
P7, Overhead Circuit Breaker Panel
 1) 7D16, RUD TRIM CONT
 2) 7D17, AILERON TRIM

 D.  
Procedure

 S 022-005
 (1)  
Remove the aileron and rudder trim control module:

 (a)  
Turn the four fasteners that connect the trim module to the aft electronic control panel, P8.

 (b)  
Lift the trim module from the P8 panel.

 (c)  
Disconnect the two electrical connectors from the trim module.

 (d)  
Remove the trim module from the P8 panel.

 TASK 27-21-09-402-023
 3.  Aileron and Rudder Trim Control Module - Installation (Fig. 201)
_____________________________________________________
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-21-09
　
中國航空網 www.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 2(102)