500 Main Gear Trunnion Assembly Wear Limits
Feb 20/91 Figure 601 (Sheet 1) 32-11-11
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Main Gear Trunnion Link Assembly Wear Limits 500
32-11-11 Figure 601 (Sheet 2) Aug 01/74
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 BUSHING ID 1.500 1.501 1.502 0.005 X
BOLT OD 1.498 1.499 1.497 X *[1]
2 BUSHING ID 1.500 1.501 1.502 0.005 X
BOLT OD 1.498 1.499 1.497 X *[1]
3 BUSHING ID 2.625 2.627 2.628 0.006 X
PIN OD 2.623 2.624 2.621 X *[1]
4 BUSHING ID 2.625 2.627 2.628 0.006 X
PIN OD 2.623 2.624 2.621 X *[1]
5 BUSHING ID 2.625 2.627 2.628 0.006 X
PIN OD 2.623 2.624 2.621 X *[1]
6 BEARING ID 3.250 3.251 3.254 0.005 X
LINK OD 3.2385 3.2495 3.2405 X *[2]
7 LINK ID 0.4540 0.4545 0.456 X *[1]
DOWEL OD 0.455 0.456 X
8 PIN ID 1.250 1.251 1.252 0.005 X *[1]
SHAFT OD 1.248 1.249 1.247 X *[2]
9 BUSHING ID 1.0000 1.0010 1.003 0.005 X *[3]
BOLT OD 0.9985 0.9990 0.997 X
500 Main Gear Trunnion Link Assembly Wear Limits
Oct 20/85 Figure 601 (Sheet 3) 32-11-11
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MAIN GEAR SHOCK STRUT - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Ground Lock Assemblies (Ref 32-00-01)
B. Main Gear Oleo Lock Assembly - F80234
C. Adapter Wrench Main Gear Trunnion Pin Nut - F80020-5
D. Bullet Shaped Thread Protector - F80115-1 or F80115-10
E. Bullet Shaped Thread Protector - F80115-2 or F80115-11
F. Main Landing Gear Sling - ME65-73761 or polyester web sling 12 feet long, 3 inches wide, 2000 pound minimum rated capacity, eye and eye configuration. CWEE1-63, 12 feet long. Cambridge Wire Cloth Co., Cambridge, Maryland (Fig. 402)
G. Main Gear Buildup Stand - FME65-73761
H. Mobile crane
I. Lead hammer
J. Wheel chocks
K. Container - suitable for hydraulic fluid, in which to drain brake lines
L. Grease - MIL-G-21164 or MIL-G-23827 optional to BMS 3-33 (Ref 20-30-21)
M. Corrosion preventative compound MIL-C-11796, Class 3 (Ref 20-30-21)
2. Prepare to Remove Main Gear Shock Strut
A. Check that ground lock assemblies (Ref 32-00-01) are installed in all gear.
B. Depressurize hydraulic systems A and B.
C. Operate brakes eight times to depressurize brake accumulator.
D. Open all landing gear circuit breakers on panel P6.
Sep 01/02 32-11-21 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Remove hydraulic access panel 8401 on left or 8501 on right from underside of wing.
F. Remove main gear shock strut doors. Refer to 32-13-11.
G. Deflate and compress shock strut by removing dust cap from charging valve and loosening release valve one or two turns. (See figure 401.)
WARNING: DO NOT LOOSEN VALVE BODY UNLESS SHOCK STRUT IS COMPLETELY DEFLATED. AIR PRESSURE CAN BLOW VALVE BODY OUT, CAUSING INJURY TO PERSONNEL. CHECK THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF AIRPLANE AS IT DESCENDS.
I. Install main gear oleo lock assembly to keep shock strut compressed. (See figure 401.)
J. Place a container under shock strut, remove check valve and drain oil from strut. When strut is empty, install check valve.
NOTE: Arrow on check valve points up when check valve is installed.
K. Jack airplane until tires are making just sufficient contact to prevent wheels rotating. Jacking height will be about 4 inches. Refer to Chapter 7, Airplane Jacking.
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