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 E. Install the lower torsion link.
 S 414-045
 (1)  
Apply grease to, and install, the parts that follow to connect the lower torsion link (5) to the shock strut (View A-A):

 (a)  
Pin (6)

 (b)  
Lockbolt (7)

 (c)  
Washer (8)

 (d)  
Nut (9) 1) Tighten the nut to 150-200 pound-inches.

 NOTE: If necessary, you can loosen the nut to the
____ nearest lock position to install the cotter pin.
 (e)  Cotter Pin
 S 424-047
 (2)
Apply grease to, then install, these parts to connect the upper torsion link (11) to the lower torsion link (5) (View B-B):

 (a)  
Apex Pin (12)

 (b)  
Washer (13, 14, and 16)

 (c)  
Nut (15) 1) Tighten the nut to 200-250 pound-inches.

 (d)  
Cotter Pin

 F.
Put the Airplane Back to Its Usual Condition.

 S 414-051
 (1)  
Install the wheel and the tire on the nose landing gear
 (AMM 32-45-02/401).

 S 584-052

 (2)  
Lower the axle of the nose landing gear and remove the axle jack (AMM 07-11-03/201).

 S 864-065

 (3)  
Remove the DO-NOT-OPERATE tags from the control lever for the landing gear. Put the lever on the DN position.

 (4)  
Lubricate the torsion link at the grease fittings.

 S 644-054
 

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 S 824-119
 (5)  
Do this task "Measure/Adjust the Clearance for the Nose Landing Gear Not Compressed Sensor" (AMM 32-09-08/201), if you did one of the tasks that follow:

 (a)  
You replaced a torsion link bushing(s).

 (b)  
You installed a new upper/lower torsion link.

 (c)  
You installed a new sensor/target.

 (d)  
You moved or damaged the sensor/target bracket.

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 NOSE GEAR TORSION LINKS - INSPECTION/CHECK
__________________________________________
 1.  General_______
 A.  This procedure only has an illustration, and a wear limit table which shows the data for wear limits. There are no procedures for access, removal, or installation of the parts. Refer to the Nose Gear Torsion Links - Removal/Installation for the procedure to do these tasks.
 TASK 32-21-09-206-001
 2.  Wear Limits for the Torsion Links of the Main Landing Gear (Fig. 601)__________________________________________________________
 A.  Wear Limits for the Torsion Links
 S 226-002
 (1)  Refer to Fig. 601 for the inspection points and the wear limits table.
 

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C-C

Nose Landing Gear Torsion Links Wear Limits
Figure 601 (Sheet 1)

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NO. INDEX PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  WORN PART REPLACE  PART WORN REPAIR  INSTR REPAIR 
DIAMETER  PER-MITTED WEAR DIM.  MAX ANCE CLEAR-DIAM 
MIN  MAX 
1  BUSHING  ID  1.5000  1.5010  1.5040  0.0050  X
PIN  OD  1.4980  1.4990  1.4960  X  1 
2  BUSHING  ID 1.5000  1.5010  1.5044  0.0054 X 
PIN  OD  1.4980  1.4990  1.4956  X  1 
3 BUSHING  ID  0.3750  0.3790  0.3812  0.0047 X 
BOLT  OD  0.3735  0.3745  0.3723  X 
4 SHOCK STRUT LOWER LINK/  5.9330  5.9390  5.9770  2 0.0380 3 
5 BUSHING  ID  0.7500  0.7510  0.7537  0.0047 X 
PIN  OD  0.7480  0.7490  0.7463  X 
6 APEX JOINT  1.6140  1.6180  1.6290  2 0.0110 3 
7 BUSHING  ID  1.2500  1.2510  1.2540  0.0050 X 
　
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 2(3)