S 434-022

 (6)  
Push the support bracket into the head of the apex pin as shown on Fig. 401 (View B-B).

 S 434-023

 (7)
Attach the support bracket to the collar with the bracket bolts.

 F.
Put the Airplane Back to Its Usual Condition

 S 434-024
 (1)  
Connect the support bracket(s) for the electrical lines and the hydraulic lines to the upper torsion link.

 S 644-025

 (2)  
Lubricate the links at the grease fittings.

 S 414-026

 (3)  
Install the wheels and tires on the main landing gear
 (AMM 32-45-01/401).

 S 864-031

 (4)  
Remove the DO-NOT-OPERATE tag and put the control lever for the landing gear to the DN position.

 (5)  
Lower the airplane and remove the jacks (AMM 07-11-01/201).

 S 584-027
 

 32-11-16
 ALL  ú ú 03 Page 406 ú Dec 20/96
 
A

757 MAINTENANCE MANUAL
 S 414-035
 (6) Install the strut door (AMM 32-12-04/401).
 

 32-11-16
 ALL  ú ú 02 Page 407 ú Dec 20/96
 
A

757 MAINTENANCE MANUAL
 MAIN 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 Main Gear Torsion Links - Removal/Installation for procedures to do these tasks.
 TASK 32-11-16-206-002
 2.  Wear Limits for the Torsion Links of the Main Landing Gear (Fig. 601)__________________________________________________________
 A.  Wear Limits for the Torsion Links
 S 226-001
 (1)  Refer to Fig. 601 for the inspection points and the wear limits table.
 

 32-11-16
 ALL  ú ú 01 Page 601 ú Jun 20/90
 
A
757
MAINTENANCE MANUAL

B B UPPER LINK TORSION STRUT DRAG  C  A A  DRAG STRUT 3. SIDEPLAY SHOCK STRUT CYLINDER OUTER LINK TORSION UPPER INNER CYLINDER OUTER CYLINDER SHOCK STRUT SHOCK STRUT  PIN PIN 2. SIDEPLAY 1. BUSHING/ 1. BUSHING/ 
C  PIN 
LOWER LINK TORSION  FWD  A-A 
APEX PIN  LOWER LINK TORSION 
4. BUSHING/PIN 
SPACER 
LINK TORSION UPPER 
4. BUSHING/PIN 
COLLAR 

B-B

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

 32-11-16
 ALL  ú ú 01 Page 602 ú Jun 20/90
 
A

757
MAINTENANCE MANUAL

C-C

THE PART IS REPAIRABLE; REFER TO THE COMPONENT MAINTENANCE MANUAL FOR THE REPAIR INSTRUCTIONS. DISTANCE ACROSS BUSHING FLANGES DISTANCE BETWEEN BUSHING FLANGES THE PART IS REPAIRABLE; REFER TO THE COMPONENT MAINTENANCE MANUAL FOR SPECIAL SHIM AND REPAIR
INSTRUCTIONS.
Main Landing Gear Torsion Links Wear Limits
Figure 601 (Sheet 2)

 32-11-16
 ALL  ú ú 01 Page 603 ú Jun 20/94
 
A

757 MAINTENANCE MANUAL
 MAIN GEAR TRUCK ASSEMBLY - REMOVAL/INSTALLATION
_______________________________________________
 1.  General_______
 A.  This procedure contains two tasks. The first task removes the truck assembly for the main landing gear. The second task installs the truck assembly for the main landing gear.
 TASK 32-11-17-004-001
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 1(111)