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3  BUSHING  ID  0.6270  0.6275  0.6307  0.005  *[2] 
BUSHING  OD  0.6257  0.6265  0.6225  X 
4  BUSHING  ID  0.5000  0.5015  0.5040  0.0050  X 
BOLT  OD  0.4990  0.4995  0.4965  X 
5  BEARING  ID  0.4995  0.5000  0.5040  0.0050  X 
BOLT  OD  0.4990  0.4995  0.4950  X 
6  BUSHING  ID  0.5000  0.5005  0.5040  0.0050  *[3] 
BOLT  OD  0.4990  0.4995  0.4955  X 
7  BUSHING  ID  0.4385  0.4390  0.4415  0.0050  *[4] 
BOLT  OD  0.4365  0.4370  0.4340  X 
8  BUSHING  ID  0.7130  0.7140  0.7160  0.0050  *[5] 
BUSHING  OD  0.7110  0.7115  0.7090  X 
9  BUSHING  ID  0.4385  0.4390  0.4415  0.0050  X 
BOLT  OD  0.4365  0.4370  0.4340  X 
10  BUSHING  ID  0.3125  0.3140  0.3165  0.0050  *[3] 
BOLT  OD  0.3115  0.3120  0.3090  X 

Wing Gear Shock Strut Inboard Door Wear Limits
Figure 601 (Sheet 4)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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  REPLACE PART WORN  REPAIR WORN PART  REPAIR INSTR. 
DIAMETER  WEAR ALLOWED DIM. *[7]  DIAM CLEAR-ANCE MAX 
MIN  MAX 
11  BUSHING  ID  0.5650  0.5660  0.5680  0.0050  *[6] 
BUSHING  OD  0.5630  0.5635  0.5610  X 
12  BUSHING  ID  0.3130  0.3140  0.3165  0.0050  X 
BOLT  OD  0.3115  0.3120  0.3090  X 

*[1] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0003 TO 0.0018 INCH. *[2] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0002 TO 0.0017 INCH. *[3] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0002 TO 0.0020 INCH. *[4] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0015 TO 0.0025 INCH.
LINE REAM TO DESIGN LIMITS. *[5] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0005 TO 0.0020 INCH. *[6] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0015 TO 0.0025 INCH. *[7] LIMITS SHOWN MAY BE EXCEEDED PROVIDED MAXIMUM CLEARANCE IS NOT EXCEEDED.
Wing Gear Shock Strut Inboard Door Wear Limits
Figure 601 (Sheet 5)

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 ALL  ú ú 01 Page 606 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 WING LANDING GEAR SHOCK STRUT OUTBOARD DOOR - REMOVAL/INSTALLATION
__________________________________________________________________
 1. General
_______
 A. This procedure contains two tasks:
 (1)  
The removal of the outboard door of the shock strut on the wing landing gear.

 (2)  
The installation of the outboard door of the shock strut on the wing landing gear.

 TASK 32-12-07-004-001
 2. Wing Landing Gear Shock Strut Outboard Door Removal (Fig. 401)
___________________________________________________
 A. References
 (1)  
09-11-00/201, Towing

 (2)  
32-00-30/201, Landing Gear Door Locks

 (3)  
32-12-06/401, Wing Gear Shock Strut Inboard Door

 (4)  
IPC 32-12-05 Fig. 1, 32-12-06, 32-12-07

 B.
Access

 (1)  
Location Zone
 734 Wing Landing Gear Door, LH
 744 Wing Landing Gear Door, RH

 C.
Prepare for the Procedure

 S 494-014
　
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