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A
737-300/400/500MAINTENANCE MANUAL
 MAIN LANDING GEAR TORSION LINKS - INSPECTION/CHECK
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 1.  General
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 A.  This procedure only has illustration and a wear limits table which shows the data for wear limits. There are no procedures for the access, the removal, or the installation of the parts. Refer to the Main Landing Gear Torsion Links - Removal/Installation for procedures to do these tasks.
 TASK 32-11-51-206-001
 2.  Wear Limits for the Torsion Links of the Main Landing Gear (Fig. 601)
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 A.  Wear Limits for the Torsion Links
 S 226-002
 (1)  Refer to Fig. 601 for the inspection points and the wear limits table.
SHOCK STRUT ASSEMBLY
LOWER DRAG STRUT
B
UPPER TORSION
A  LINK
B
C
A
INBD FWD
C
LOWER TORSION LINK
Main Landing Gear Torsion Links Wear Limits
Figure 601 (Sheet 1)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

B-B
THRUST WASHER

UPPER TORSION LINK
DAMPER HOUSING
C-C
Main Landing Gear Torsion Links Wear Limits
Figure 601 (Sheet 2)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NO. INDEX  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  WORN PART REPLACE  PART WORN REPAIR  INSTR REPAIR
DIAMETER  DIM. WEAR MAX  CLEAR-ANCE PER MITTED 
MIN  MAX 
1  BUSHING ID  1.7510  1.7520  1.7535  0.0050  X 
PIN  OD  1.7495  1.7500  1.7485  X  1 
2 BUSHING  2  6.377  6.378  6.382  0.0160  X  6 
BUSHING  3  6.374  6.376  6.371  X  6 
3  BUSHING  ID  1.7510  1.7520  1.7535  0.0050  X 
PIN  OD  1.7495  1.7500  1.7485  X  1 
4  BUSHING  4  6.377  6.378  6.382  0.0160  X 6 
BUSHING  5  6.375  6.376  6.371  X  6 
5  BUSHING  ID  1.7505  1.7515  1.7535  0.0050  X 
PIN OD  1.7495  1.750  1.7485  X  1 
6 BUSHING  ID  1.7505  1.7515  1.7535  0.0050  X 
PIN  OD  1.7495  1.750  1.7485  X  1 
7  BUSHING  ID  1.7505  1.7520  1.7535  0.0050  X 
PIN OD  1.7495  1.750  1.7485  X  1 
8  BUSHING  5  3.625  3.627  3.632  0.0080  X 
BUSHING  7  3.623  3.624  3.619 X 
9 WASHER/WASHER  8  ---- --2.700 MIN  9 
 
 

 

REFER TO OVERHAUL MANUAL FOR REPAIR INFORMATION. DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN LOWER TORSION LINK ASSEMBLY DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN SHOCK STRUT INNER CYLINDER ASSEMBLY DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN UPPER TORSION LINK ASSEMBLY DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN SHOCK STRUT OUTER CYLINDER ASSEMBLY FOR IN-SERVICE REPAIR, INSTALL SPECIAL SHIM PER (AMM 32-11-51/801, FIG. 801) APPROVED REPAIRS.
PREFERRED OVERHAUL REWORK IS TO RESTORE PART TO DESIGN LIMITS USING NEW BUSHINGS. DISTANCE BETWEEN FLANGE FACES OF BUSHINGS IN LOWER DRAG STRUT ASSEMBLY MINIMUM DISTANCE BETWEEN THE THRUST WASHER FACES AS SHOWN IN
FIGURE 601, VIEW C-C.
NOTE:  THIS MEASUREMENT MUST BE TAKEN AFTER YOU ADJUST THE SHIMMY DAMPER AND THE APEX NUT IS TIGHTENED TO THE SPECIFIED TORQUE (AMM 32-11-81/501).
REPLACE THE TWO THRUST WASHERS AND THE LOWER TORSION LINK APEX BUSHINGS, IF THE
DIMENSION IS LESS THAN THE MINIMUM.
Main Landing Gear Torsion Links Wear Limits Figure 601 (Sheet 3)
　
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