(a)
Remove the thread protector from the apex pin.
(b)
Apply compound to the threads of the apex pin.
(c)
Install the tang washer and apex nut, hand tight, on the apex pin.
(d)
Tighten the apex nut 840-1080 pound-inches.
(e)
Install the antirotation bolt, washer, nut and cotter pin.
NOTE: If needed, you may loosen the castellated nut to the
____
nearest lock position
(f)
Remove the excess compound.
F.
Put the Airplane Back to Its Usual Condition.
S 414-019
(1)
Install the downlock actuator for the main landing gear
(AMM 32-32-02/401).
S 414-020
(2)
Install the downlock springs for the main landing gear
(AMM 32-11-22/401).
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(3) S 644-021Lubricate the links at the grease fittings.
(4) S 584-022Lower the airplane and remove the jacks (AMM 07-11-01/201).
S 094-031
WARNING: USE THE PROCEDURE IN AMM 32-00-15/201 TO REMOVE THE DOOR LOCKS.
_______ THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(5) Remove the door locks from the landing gear and close the doors (AMM 32-00-15/201).
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MAIN GEAR DOWNLOCK ASSEMBLY - INSPECTION/CHECK
______________________________________________
1. General
_______
A. This procedure only has an illustration and wear limit table which shows the data for the wear limit. There are no procedures for access, removal or installation of the parts. Refer to Main Gear Downlock Assembly -Removal/Installation for procedures to do these tasks.
TASK 32-11-12-206-001
2. Main Gear Downlock Assembly Wear Limits (Fig. 601)
_______________________________________
NOTE: Wear limits for components attached to the Main Gear Downlock can be
____
found in the Maintenance Manual subject for the components.
A. Wear Limits for the Downlock Assembly
S 206-002
(1) Refer to Fig. 601 for the inspection points and the wear limits table.
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LOWER DOWNLOCK
DOWNLOCK ASSEMBLY SEE A BOLT UPPER DOWNLOCK 1. BUSHING/
INBD
BOLT 1. BUSHING/
B B A-A
A
A
DOWNLOCK ASSEMBLY
A
Main Landing Gear Downlock Assembly Wear Limits
Figure 601 (Sheet 1)
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2. BUSHING/PIN SPINDLE
2. BUSHING/PIN
DOWNLOCK SPINDLE C-C
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE PART WORN REPAIR WORN PART REPAIR INSTR
DIAMETER DIM. WEAR MITTED PER- DIAM CLEAR-ANCE MAX
MIN MAX
1 2 3 4 BUSHING ID 1.1875 1.1885 1.1912 0.0042 0.0042 0.0070 0.0070 X
BUSHING BOLT ID OD 0.7085 1.1865 0.7095 1.1870 0.7117 1.1843 X X 1
BUSHING PIN ID OD 1.4385 0.7070 1.4395 0.7075 1.4440 0.7053 X X 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(106)
