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)
Place uplock actuator (17) in position and insert actuator pin (12) through link assembly
(10) and rod end of actuator.
(15)
Install bearing (9), washer and nut to each end of actuator pin (12).
(16)
Tighten actuator pin nuts 4 to 6 pound-feet.
501
32-32-31 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
4. Removal/Installation Uplock Hook
A. Remove Uplock Hook
(1)
Remove lockwire and drive out spring pins (16, Fig. 401) securing uplock springs (14) to upper spring shaft (19).
(2)
Remove lockwire and drive out spring pins (16, Fig. 401) securing uplock springs (14) to lower spring shaft (22) and remove washers.
CAUTION: SPRING TENSION IS APPROXIMATELY 25 POUNDS.
(3)
Tap out shaft (19) from hook to release springs (14). Retain spacers (18) that drop free when shaft comes out.
(4)
Remove bolt (21) securing hook (15) to stop link (20).
(5)
Remove hook to uplock crank attachment bolt (13) and remove hook (15) from airplane.
B. Install Uplock Hook
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 uplock hook (15, Fig. 401) in uplock crank (4) and insert hook attachment bolt (13) from forward side.
(2)
Add washer and nut. Tighten nut to standard torque, and lock with cotter pin (Ref Chapter 20, Standard Torque Values).
(3)
Connect hook (15) to stop link (20). Insert bolt (21) from aft side. Add washer and nut.
(4)
Tighten nut to standard torque and lock with cotter pin (Ref Chapter 20, Standard Torque Values).
(5)
Insert lower spring shaft (22) through link assembly (10), stop link (20), and hook (15).
(6)
Install ends of uplock springs (14) on lower spring shaft (22). Secure with spring pins (16).
(7)
Pass lockwire through spring pins and lock with double-twist method.
501
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-32-31 Page 403
Main Gear Uplock Mechanism Installation 500
32-32-31 Figure 401 (Sheet 1) Aug 15/80
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Main Gear Uplock Mechanism Installation
May 20/82 Figure 401 (Sheet 2) 32-32-31
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Removal/Installation Link Assembly
A. Remove Link Assembly
(1)
Remove lockwire and drive out spring pins (16, Fig. 401) and lower spring shaft (22) to release uplock springs (14) from link assembly (10).
(2)
Disconnect uplock actuator (17) from upper end of link assembly (10). Observe bearings
(9) on ends of actuator pin (12).
(3)
Remove link attachment bolt (11) and remove link assembly from airplane.
B. Install Link Assembly
(1)
Place link assembly (10, Fig. 401) in position on uplock crank (4) with cutouts for stop link facing hook.
(2)
Put the bolt (11) through the stop link with head forward.
NOTE: Butter lubricate threads with MIL-PRF-23827.
(3)
Install washer, nut, and tighten nut to 125 inch-pounds (14.1 newton-meters) over run-on torque.
NOTE: If necessary, back off nut to nearest possible locking position and install cotter pin. A zero torque condition is acceptable. 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(91)
