757 MAINTENANCE MANUAL
2) Install the cotter pin through the nut (9).
F. Put the Airplane Back to Its Usual Condition
S 644-019
(1)
Lubricate the brake rods at the grease fittings (AMM 12-21-14/301).
S 844-020
(2)
Remove the DO-NOT-OPERATE tag from the control lever for the landing gear.
S 844-021
(3)
Move the control lever for the landing gear to the DN position.
32-11-19
ALL ú ú 01 Page 406 ú Sep 20/97
A
757 MAINTENANCE MANUAL
MAIN GEAR BRAKE ROD - 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 Brake Rod -Removal/Installation for the procedures to do these tasks.
TASK 32-11-19-206-002
2. Wear Limits for the Brake Rod of the Main Landing Gear (Fig. 601)______________________________________________________
A. Wear Limits for the Brake rod
S 226-001
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
32-11-19
ALL ú ú 01 Page 601 ú Jun 20/90
A
757
MAINTENANCE MANUAL
SHOCK STRUT INNER CYLINDER
BRAKE RODSBRAKE RODS
PIN BRAKE RODBRAKE ROD
SHOCK STRUT
TRUCK
1. BUSHING/ 1. BUSHING/
A B PIN PIN
A-A
A B
BRAKE ROD
(4 LOCATIONS)
BRAKE
PIN
2. BUSHING/PIN 2. BUSHING/PIN
B-B
Main Landing Gear Brake Rod Wear Limits
Figure 601 (Sheet 1)
32-11-19
ALL ú ú 01 Page 602 ú Jun 20/90
A
757
MAINTENANCE MANUAL
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE PART WORN REPAIR WORN PART REPAIR INSTR
DIAMETER MITTED PER-WEAR DIM. DIAM CLEAR-ANCE MAX
MIN MAX
1 BUSHING ID 1.6250 1.6260 1.6295 0.0055 X
PIN OD 1.6230 1.6240 1.6205 X 1
2 BUSHING ID 1.1870 1.1880 1.1912 0.0052 X
PIN OD 1.1850 1.1860 1.1828 X 1
THE PART IS REPAIRABLE; REFER TO THE COMPONENT
MAINTENANCE MANUAL FOR THE REPAIR INSTRUCTIONS.
Main Landing Gear Brake Rod Wear Limits
Figure 601 (Sheet 2)
32-11-19
ALL ú ú 01 Page 603 ú Jun 20/90
A
757 MAINTENANCE MANUAL
MAIN GEAR DOWNLOCK SPRINGS - REMOVAL/INSTALLATION
_________________________________________________
1. General_______
A. This procedure contains two tasks. The first task removes the downlock springs on the main landing gear. The second task installs the downlock springs on the main landing gear.
TASK 32-11-22-004-015
2. Remove the Downlock Springs for the Main Landing Gear (Fig. 401)_____________________________________________________
A. Equipment
(1)
Downlock Spring Extender, MLG and NLG - B32002-1
B.
References
(1)
AMM 32-00-20/201, Landing Gear Downlocks
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：757 AMM 飞机维护手册 起落架 CHAPTER 32 - LANDING GEAR 1(120)
