I. Clean areas on forward and aft hinges (13) of door which the corrosion protection washers (14) will contact when installed.
NOTE: The corrosion protection washers will be installed between the bonding jumper (19) terminal and the door hinge (13).
(1)
Clean painted area by applying lacquer thinner using a clean cloth. Use an uncontaminated portion of cloth for each application, taking care to avoid overrun or spilling of thinner beyond limits of the area to be bonded.
(2)
Spot area by hand application of abrasive material. If practical, use a circular or elliptical motion of the abrasive to provide a uniform smooth finish.
500
May 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-22-11 Page 405
J. Connect bonding jumper (19) to forward and aft hinges (13) on door.
(1)
Install close tolerance bolt (16) in forward and aft door hinges with aluminum alloy flat washer under head of each bolt.
(2)
Slide thin aluminum alloy washer (14) on bolt for corrosion protection.
(3)
Slide bonding jumper (19) terminal on bolt (16).
(4)
Slide aluminum alloy flat washer on bolt.
(5)
Slide lockwasher on bolt.
(6)
Install 450 degree self-locking nut (15) on bolt to attach bonding jumper.
(7)
Apply a coat of epoxy primer to stripped areas that are exposed outside the corrosion preventive washer.
(8)
Apply a finish coat of epoxy enamel to primed areas to match adjacent areas.
K. Connect door operator rod (1) to door center hinge (4).
(1)
Apply thin coat of corrosion preventive compound to short thread, close tolerance, corrosion resistant steel bolt (5).
(2)
Position door operator rod (1) in fork of door center hinge (4) and insert compound coated bolt through hinge and door operator rod end.
NOTE: If rod was previously adjusted, the rod may need unlocking and extending to enable bolt insertion. Adjust and lock per par. L.
(3)
Slide washer on bolt and install castellated shear nut with corrosion resistant cotter pin.
500
32-22-11 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/90
L. Adjust door operator rod.
(1)
Remove lockwire from jamnut and rod end lock (3) on each end of door operator rod (1).
(2)
Loosen jamnut on each rod end of rod (1).
NOTE: Only loosen jamnut so operator rod can be turned for adjustment. Excessive loosening will disengage rod end (3) lock from end of operator rod barrel.
(3)
While applying 70 + 10 pounds down load approximately 1.0 inch aft and 1.0 inch outboard of forward inboard corner or 85 + 10 pounds at forward stop fitting on each door, adjust each door operator rod until forward inboard corner on each door is 0.10 + 0.02 inch below body contour.
(4)
Check for contour mismatch, as obtained in step 3.G.
(5)
Remove weight from door.
(6)
Tighten jamnut on each door operator rod end.
(7)
Lockwire each jamnut and rod end lock (3) on each rod (1) end with NC32 Monel lockwire using double twist method.
M. Check door operation.
(1)
Pressurize Hydraulic System A (Ref 29-11-0 MP).
(2)
Extend and retract gear and check for proper operation of doors. Refer to 32-33-0 for nose gear extension and retraction.
(3)
Extend gear.
(4)
Install ground lock assembly on nose gear (Ref 32-00-01).
(5)
Remove jacks from airplane.
500
Feb 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-22-11 Page 407
LANDING GEAR CONTROL SYSTEM - DESCRIPTION AND OPERATON
1. General
A. The landing gear control system is operated by moving a control lever projecting from the pilots' instrument panel (Fig. 1). A cable system transmits the control lever movement to a selector valve in the left wheel well. When positioned by the control lever the selector valve directs hydraulic pressure to the actuators for gear retraction and extension. The control lever is provided with a lock, to prevent the lever from being moved into UP position when the airplane is supported on the gear. An override trigger in the control lever may be used to bypass the lock for testing or if the lock system should lose electrical power.
2. Landing Gear Selector Valve
A. The landing gear selector valve directs hydraulic pressure to the landing gear up and down lines (Fig. 2). Return fluid from the landing gear system passes back through the selector valve and on to the system A reservoir. The selector valve is bolted to the ceiling of the left main wheel well. Linkage connects the selector valve to the control cable system. When the landing gear control handle is operated, motion from the handle is transferred through the cable system to a shaft passing through the wheel well ceiling. An arm on the end of shaft below the ceiling positions the selector valve through an adjustable link.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 起落架 LANDING GEAR(76)
