54-42-12
 ú ú B01 Page 205 ú Jul 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NO. INDEX  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  WORN PART REPLACE  PART WORN REPAIR  INSTR. REPAIR 
DIAMETER  ALLOWED DIM. WEAR  MAX ANCE CLEAR-DIAM 
MIN  MAX 
1  FITTING  ID  0.8750  0.8757  0.8763  0.0000  3 
BUSHING  OD  0.8763  0.8770  0.8757  X 
2 BUSHING  ID  0.7495  0.7505  0.7522  0.0042  X 
BOLT  OD  0.7480  0.7490  0.7463  X 2 
3 CROSSBEAM  ID  0.8750  0.8757  0.8763  0.0000  3 
BUSHING  OD  0.8763  0.8770  0.8757  X 
4  BUSHING  ID  0.7495  0.7505  0.7522  0.0042  X 
BOLT OD  0.7480  0.7490  0.7463  X  2 
5 CROSSBEAM  ID  1.4375  1.4380  --- 0.0020  ---
BEARING  OD  1.4370  1.4375  --- X 
6 BEARING RACE  ID  1.1880  1.1885  1.1915 AXIAL 0.0080 4  X 
BEARING BALL  OD  1.1865  1.1870  --- X 
7  BEARING BALL  ID  0.7495  0.7500  0.7517 4 X 
BOLT  OD  0.7480  0.7490  0.7463  X  2 

Forward Engine Mount Wear Limits
Figure 202 (Sheet 4)

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH VIBRATION ISOLATORS ú

 54-42-12
 ú ú B01 Page 206 ú Jul 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
WING
UPPER LINK

BRACKET (4 LOCATIONS)
NOTE: RIGHT SIDE INSTALLATION

A
IS SHOWN. LEFT SIDE IS
THE SAME BUT OPPOSITE.

Forward Vibration Isolator Removal/Installation Figure 203 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH VIBRATION ISOLATORS ú

 54-42-12
 ú ú B01 Page 207 ú Nov 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

B

Forward Vibration Isolator Removal/Installation
Figure 203 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH VIBRATION ISOLATORS ú

 54-42-12
 ú ú B01 Page 208 ú Nov 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 022-004-B00
 (3)  
Remove the bolts, washers and the nuts that attach the crossbeam assembly to the strut.

 S 022-005-B00

 (4)  
Remove the crossbeam assembly.

 S 022-006-B00

 (5)  
If it is necessary, remove the cross pin, the bracket, and the nut from the right end of the crossbeam.

 E. Remove the Vibration Isolator
 S 022-007-B00
 (1)  Do these steps to remove the applicable vibration isolator from the crossbeam (Fig. 203):
 (a)  
At the forward outboard location on the isolator, remove the bolt, washers, and the bond jumper assembly.

 (b)  
At the other three locations, remove the bolts and the washers.

 (c)  
Remove the isolators.

 TASK 54-42-12-402-013-B00
 3.  Forward Engine Mount Installation_________________________________
 A. General
 (1)  This procedure contains two topics:
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 NACELLES/PYLONS(46)