(4)
Connect stop link (20) to link assembly by inserting lower spring shaft (22) through links (10), stop link (20), and hook (15).
(5)
Add a washer on each end of lower spring shaft (22).
(6)
Install ends of uplock springs (14) on lower spring shaft (22). Secure uplock springs with spring pins (16).
(7)
Pass lockwire through spring pins and lock with double twist method.
(8)
Connect uplock actuator (17) to link assembly (10).
(a)
Insert actuator pin (12) through link assembly (10).
(b)
Add bearing (9), washer and nut to each end of pin (12).
(c)
Tighten nuts 4 to 6 pound-feet.
504
32-32-31 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 01/02
6. Removal/Installation Uplock Crank
A. General
(1) Uplock hook (15, Fig. 401) and link assembly (10) must be removed before uplock crank
(4) can be removed.
B. Remove Uplock Crank
(1)
Remove crank attachment bolt (23, Fig. 401).
(2)
Remove bolt (2) securing crank retaining collar (3).
(3)
Remove nut from uplock support shaft (5).
(4)
Tap out shaft (5). Retrieve crank retaining collar (3) as shaft comes out.
NOTE: Position, number, and size of shims (6) installed under shaft head and between uplock crank (4) and uplock support fitting (8) should be tagged for use during assembly.
(5)
Remove uplock crank (4) from airplane.
C. Install Uplock Crank
WARNING: USE NITRILE GLOVES FOR SKIN PROTECTION AGAINST BMS 3-27 (MASTINOX 6856K). IF MASTINOX GETS ON YOUR SKIN, IMMEDIATELY REMOVE IT WITH WATER. IF THIS MATERIAL GETS IN YOUR EYES, IMMEDIATELY FLUSH YOUR EYES WITH WATER AND GET MEDICAL AID. THIS MATERIAL CONTAINS VERY POISONOUS AND FLAMMABLE AGENTS WHICH CAN CAUSE INJURIES TO PERSONS.
CAUTION: UNWANTED MASTINOX MUST BE REMOVED FROM SURFACES WHICH WILL BE GREASED. APPLICATION OF MASTINOX TO JOINTS THAT TURN COULD CAUSE FAILURE OF THE LANDING GEAR TO EXTEND OR RETRACT.
NOTE: 1. Parts, which are not lubricated after installation, must be coated with Mastinox 6856K.
2. Parts, which are lubricated after installation, must be lubricated with Aero Shell 07.
(1)
Place crank (4, Fig. 401) in position in reaction link (24).
(2)
Install attachment bolt (23) with head to antirotation lug on reaction link.
(3)
Add washer and nut.
(4)
Turn the nut on the bolt until the self-locking threads are fully engaged but the nut is not seated.
(5)
Measure the torque, and make sure that the torque is 90-800 pound-inches (This is the run-on torque).
(6)
Tighten the nut to the run-on torque plus 250-300 pound-inches.
(7)
Install uplock support shaft (5) through side strut support frame (7).
NOTE: Shim with chamfer to be installed with inside diameter chamfer against fillet radius at base of support shaft head. Position, number, and size of shims should be installed as tagged on disassembly. If new shims are installed assemble three thick (0.06-inch) shims (6) between uplock crank (4) and side strut support frame (7).
(8)
Pass shaft through uplock crank (4), place uplock crank retaining collar (3) on shaft, and insert narrow end of shaft (5) through support fitting (8).
(a) Align collar slot with bellcrank rib and engage rib into slot.
(9)
Install collar bolt (2) through crank retaining collar (3) and shaft (5). Insert bolt from side with counter bore.
(10)
Do a check on the clearance between the shims (6), and the support frame (7) on each side of the support frame (7). Add the clearance that you get on each side of the support frame (7). Add or adjust shims as necessary to achieve this clearance so that centerline of uplock hook (15) lines up with centerline of uplock roller within + 0.10 inch.
NOTE: The total clearance must be between 0.002 - 0.020 inches.
(11)
Add special large diameter washer (1) and nut.
(12)
Tighten nut with hand. If necessary, back off nut to line up nearest castellation with hole in shaft. Lock nut with cotter pin.
(13)
Add washer and nut to collar bolt (2). Tighten nut 30 to 40 pound-inches torque.
(14)
Install uplock sensor and mounting bracket on uplock hook. Adjust as necessary (Ref 32-61-21).
502
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-32-31 Page 407
7. Restore Airplane to Normal Configuration
A. Lubricate gear (Ref Chapter 12, Main Landing Gear Lubrication).
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(92)
