6. Install Lift Actuator Assembly (Fig. 401)
A.  Position actuator links (15) between support fittings (14) mounted on cabin ceiling and install bolts (12), washers, and nuts.
NOTE: Before installing actuator attaching bolts, coat shanks with film of grease.
Two additional laminated washers (13) are installed between both sides of aft actuator link (15) and aft support fitting. Peel off laminations as required to maintain a gap  of .01 inch maximum.
B.  Tighten nuts until washers are snug against bolt shoulders and then back off only as required to install cotter pins.
C.  Remove temporary support between actuator and bracket (6).
D.  Attach outboard ends of thrust rods (9) to strut fittings (3) with bolts, nuts, and washers (18).
E.  Tighten nuts until washers are snug against bolt shoulders and then back off only as required to install cotter pins.
F.  Rotate bellcrank (1) upward and connect actuator rod end to bellcrank (1) with spacers attaching bolt, washer and nut (21). Install bolt attaching bellcrank (1) to link (2).
G.  Tighten nut on support pin (11) 1500 to 2000 pound-inches. Tighten further (up to 10 degrees maximum) only as required to install cotter pin. Do not back off nut to install cotter pin. 
H.  Tighten B-nuts connecting coiled tubes (17) to bulkhead tee-fittings (4) and tighten fitting jamnuts.
I.  Position thrust rod support clamps (7) and tube support bracket (8) on thrust rods and tighten clamp bolts.
535 
52-32-31 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/84 

J.  Connect all hydraulic lines to tee-fittings (4) and tighten B-nuts.
K.  Ensure all attaching nuts, bolts, for proper torque, safety wire or cotter pin as applicable and ensure all hydraulic fittings are tightened.
L.  Bleed main cargo door hydraulic system and ensure actuator is free from leaks and binding of linkage. Refer to 52-32-0, Main Cargo Door System.
M.  Install new felt absorber pad and retainer spring (20).
N.  Install aft curved ceiling panels on cargo door and cabin ceiling. Refer to 52-32-81 and  Chapter 25, Ceiling Lining.
527 
Nov 15/72  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-32-31 Page 405 

MAIN CARGO DOOR LIFT ACTUATOR LINKAGE - REMOVAL/INSTALLATION
1. General
A.  Components of the lift actuator linkage consist of a link assembly, bellcrank assembly, a door actuator fitting, two strut fittings and attaching bolts, nuts and washers. (See figure 401.)
B.  Extreme care should be exercised to avoid contaminating cabin lining with grease. Should any grease spill on the airplane, decontaminate. Refer to Chapter 12, Cleaning and Washing.
2.  Equipment and Materials
A.  Grease, MIL-G-23827
B.  Grease gun equipped with MS24203 nozzle or equivalent
3.  Prepare for Removal
A.  Close and lock main cargo door.
B.  Open main cargo door control circuit breaker on load control center P6.
C.  Remove aft curved ceiling panels from cargo door and cabin ceiling. Refer to 52-32-81 and Chapter 25, Ceiling Lining.
4.  Remove Lift Actuator Linkage
A.  Remove actuator rod attaching bolt, nut and washer (13, figure 401.)
B.  Remove the two nuts, bolts and washers (7) attaching bellcrank assembly (1) to ceiling bellcrank fittings.
C.  Remove bolt, nut and washer (2) connecting bellcrank assembly to link assembly (3).
D.  Remove bellcrank.
E.  Remove cotter pin from nut on link attaching bolt (4) and remove bolt, nut and washer connecting link assembly (3) to door actuator fitting (5).
F.  Remove link assembly.
511 
May 15/68  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-32-41 Page 401 

Lift Actuator Linkage Installation  511 
52-32-41  Figure 401  May 15/68 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5. Install Lift Actuator Linkage

A.  If used parts are being installed, check for allowable wear (Ref 52-32-41).
B.  With cargo door in closed position, lift actuator 11, Fig. 401) must be in retracted position.  (Fig. 401 shows actuator in extended – door open position - for clarity.)
C.  Install link assembly (3, Fig. 401) on cargo door actuator fitting (5) with attaching bolt, nut and washer (4).
D.  Torque nut until washer is snug against bolt shoulder and back off only as required to install cotter pin.
E.  Position bellcrank (1) in the ceiling bellcrank fittings and install bolts, nuts and washers (7).
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 艙門 DOORS(94)