3 BEARING ID 0.6245 0.6250 0.6440 *[3] OR 0.020 X
BOLT OD 0.6235 0.6240 0.6045 X
4 BUSHING ID 0.6245 0.6260 0.6440 0.020 X *[4]
BOLT OD 0.6235 0.6240 0.6050 X
5 BUSHING ID 0.8750 0.8765 0.8830 0.010 X *[5]
BUSHING OD 0.8720 0.8730 0.8650 X
6 BEARING ID 0.6245 0.6250 0.6440 *[3] OR 0.020 X
BOLT OD 0.6230 0.6240 0.6045 X
7 SLEEVE ID 0.6250 0.6260 0.6275 0.0045 X
BOLT OD 0.6230 0.6240 0.6215 X
8 BUSHING ID 0.8100 0.8110 0.8128 0.0048 X *[6]
SLEEVE OD 0.8080 0.8090 0.8062 X
9 BOLT *[7] 2.240 2.260 2.280 X
BUSHING *[8] *[9] 2.329 2.315 X *[6]
10 SPACER *[10] *[12] 0.822 0.828 0.018 X
BEARING *[11] 0.810 0.812 NA X
Body Gear Shock Strut Inboard Door Wear Limits
Figure 601 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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747-400
MAINTENANCE MANUAL
*[1] OBTAIN BUSHING. BORE HOLE, IF REQUIRED, TO OBTAIN 0.0004 TO 0.0024 INCH INTERFERENCE FIT.
*[2] MINIMUM FLANGE THICKNESS FOR FLANGED BUSHINGS.
*[3] 0.010 INCH BETWEEN BALL AND RACE.
*[4] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0003 TO 0.0022 INCH.
MAXIMUM OVERSIZE BUSHING AND HOLE IN FITTING IS 0.625 INCH, IF REQUIRED.
*[5] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0004 TO 0.0023 INCH.
MAXIMUM OVERSIZE BUSHING AND HOLE IN FITTING IS 0.0625 INCH, IF REQUIRED.
*[6] OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0006 TO 0.0031 INCH.
MAXIMUM OVERSIZE HOLE IN FITTING IS 1.01 INCHES, IF REQUIRED.
*[7] DIMENSION BETWEEN THREAD UNDERCUT AND BOLTHEAD.
*[8] DISTANCE OVER FLANGES OF BUSHINGS.
*[9] NON NET FIT BUSHINGS - 2.325 INCHES. NET FIT BUSHINGS 2.317 INCHES.
*[10] DISTANCE BETWEEN INNER FACES OF SPACERS, PLUS POSSIBLE 1/6 TURN BACK OF NUT.
*[11] WIDTH OF BALL IN ROD END BEARING.
*[12] NON NET FIT BUSHINGS - 0.799 INCH. NET FIT BUSHINGS - 0.791 INCH.
*[13] LIMITS SHOWN MAY BE EXCEEDED PROVIDED MAXIMUM CLEARANCE IS NOT EXCEEDED.
Body Gear Shock Strut Inboard Door Wear Limits
Figure 601 (Sheet 4)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400 MAINTENANCE MANUAL
BODY GEAR SHOCK STRUT OUTBOARD DOOR - REMOVAL/INSTALLATION
__________________________________________________________
1. General
_______
A. This procedure has two tasks:
(1)
The removal of the outboard door of the shock strut for the body landing gear (referred to as the outboard door).
(2)
The installation of the outboard door.
B.
The outboard door is connected to the outer cylinder of the shock strut by a linkage rod. And it is connected to the structure by three hinges.
TASK 32-14-06-004-001
2. Body Gear Shock Strut Outboard Door Removal (Fig. 401)
__________________________________________
A. References
(1)
AMM 09-11-00/201, Towing
(2)
AMM 32-00-30/201, Landing Gear Door Locks
(3) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 起落架 LANDING GEAR 3(93)
