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BEARING (RACE)
ID 13
X
BEARING (BALL)
OD 13
X 6
0.005 11 BEARING (BALL)
ID1.2495
1.2500
13 13
X 12 BOLT 10
OD 1.2475
1.2490
1.2470
X
BEARING (RACE)
ID 13
X
BEARING (BALL)
OD 13
X 6
0.005 12 BEARING (BALL)
ID 1.2495
1.2500
13 13
X
BOLT 9 OD 1.2480
1.2490
1.2470
X
BUSHING
ID 1.0000
1.0010
1.0030
X 7
14
0.005 BOLT
OD 0.9980
0.9990
0.9970
X
11
BUSHING
ID 1.2500
1.2510
1.2530
X 7
0.005 12
BOLT OD 1.2475
1.2490
1.2465
X
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 32-32-11
Wear Limits for the Main Gear Actuator Assembly
Figure 601 (Sheet 3)

ALL  ú ú 01 Page 604 ú Jul 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

 

 

(CONTINUED)
DELETED REFER TO OVERHAUL MANUAL FOR REPAIR INSTRUCTIONS REFER TO OVERHAUL MANUAL FOR REPLACEMENT INSTRUCTIONS DELETED BUSHING 10-60516-224 NOTE:THE PREFERRED REPLACEMENT FOR THIS BUSHING IS THE 10-60516-278
BUSHING FOR ALL 65-46112 SUPPORT LINK ASSEMBLIES.
BUSHING 10-60516-278
DISTANCE BETWEEN INNER FLANGE FACES OF 69-41621 BUSHINGS
DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN SUPPORT LINK ASSEMBLY
BOLT 69-42199
NOTE:____ THIS BOLT HAS BEEN SUPERSEDED BY BACB30LJ20CD43. REFER TO
SB 737-32A1224 FOR FURTHER INFORMATION.
BOLT BACB30LJ20CD
737-400 AIRPLANES
737-300/-500 AIRPLANES
THE TOTAL DIAMETRAL CLEARANCE BETWEEN THE BEARING RACE, BEARING BALL, AND BOLT MUST NOT
BE GREATER THAN THE SPECIFIED MAX. DIA CLEARANCE.
FOR -300 AIRPLANES ONLY:
NOTE: FOR MODIFICATION TO INSTALL 1.25 DIA BOLT, SEE SB 737-32-1198.

Wear Limits for the Main Gear Actuator Assembly
Figure 601 (Sheet 4)

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 32-32-11
 ALL  ú ú 01 Page 605 ú Jul 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
C98440
A
737-300/400/500MAINTENANCE MANUAL
 MAIN GEAR UPLOCK MECHANISM - REMOVAL/INSTALLATION
_________________________________________________
 1.  General
_______
 A.  This procedure has these tasks:
 (1)  
A removal of the uplock assembly for the main landing gear

 (2)  
An installation of the uplock assembly for the main landing gear.

 (3)  
A removal of the uplock crank for the main landing gear

 (4)  
An installation of the uplock crank for the main landing gear.

 (5)  
A removal of the uplock hook for the main landing gear

 (6)  
An installation of the uplock hook for the main landing gear.

 (7)  
A removal of the uplock link assembly for the main landing gear

 (8)  
An installation of the uplock link assembly for the main landing gear.

 B.  
The uplock hook, uplock link, and the uplock crank are referred to as the "uplock assembly" in this procedure.

 C.  
Consumable Materials

 (1)  
Compound - Corrosion Inhibiting, BMS 3-27, Mastinox 6856K

 (2)  
D00633 Grease - BMS 3-33

 (3)  
D00013 Grease - MIL-PRF-23827

 D.  
References

 (1)  
AMM 32-00-01/201, Ground Lock Assemblies

 (2)  
AMM 29-15-00/201, Hydraulic Systems A, B, and Standby

 (3)  
AMM 07-11-11/201, Jack Airplane

 (4)  
AMM 32-61-21/401, Main Gear Uplock Sensor

 (5)  
AMM 32-61-21/501, Main Gear Uplock Sensor

 (6)  
AMM 32-32-00/501, Main Landing Gear Extension and Retraction

 TASK 32-32-31-004-001
 2.  Main Landing Gear Uplock Assembly Removal (Fig.401)
_________________________________________
 A.  General
 (1)  
　
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