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 - Unpublished Work - See title page for details.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 - Unpublished Work - See title page for details.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 - Unpublished Work - See title page for details.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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