MAIN CARGO DOOR LIFT ACTUATOR ASSEMBLY - REMOVAL/INSTALLATION
1. General
A. During removal or installation of the link actuator assembly or during lubrication of actuator and linkage components, extreme care must be taken to avoid contamination of the cabin lining with hydraulic fluid or lubricants. A container will be necessary to catch hydraulic fluid from disconnected lines. Should any fluid spill on the airplane, decontaminate (Ref Chapter 12, Cleaning and Washing).
2. Equipment and Materials
A. A suitable container to catch hydraulic fluid
B. Grease - MIL-G-23827 (Ref 20-30-21)
C. Grease gun with MS24203 nozzle
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 (Ref 52-32-81 and Chapter 25, Ceiling Lining).
4. Remove Lift Actuator Assembly (Fig. 401)
NOTE: Assembly consists of lift actuator (19), thrust rods (9), support pin, nut and washer (11), brackets (6 and 8), coiled tubing (17), and support clamps and blocks (7).
A. Remove hydraulic lines to control valve and latch actuator from tee-fittings (4).
B. Cap or plug all open hydraulic ports and lines.
C. Remove bolt attaching bellcrank (1) to link (2) and rotate bellcrank (1) upward to disconnect actuator rod from bellcrank assembly (1) by removing attaching nut, bolt, and spacers (21). Strap (5) will support actuator.
D. Insert wood support between actuator (19) and bracket (6).
E. Disconnect thrust rods (9) from strut fittings (3) by removing attaching nuts and bolts (18).
F. Remove nuts and bolts (12) attaching actuator links (15) to support fittings (14).
511
Feb 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-32-31 Page 401
Lift Actuator Installation 520
52-32-31Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/77
G. Remove actuator assembly.
5. Prepare for Installation
A. Main cargo door must be installed and rigged prior to actuator assembly installation. Refer to 52-32-11, Adjustment/Test.
B. Lock cargo door in closed position.
C. Ensure bellcrank (1) and link (2) are installed. Refer to 52-32-11.
NOTE: Lift actuator assembly is assembled prior to installation and consists o f the actuator (figure 401), thrust rod assemblies (9), two link fittings (15) and attaching support pin (11), washers and nut, brackets (6 and 8) and support clamps and blocks (7). Felt absorber pad is not installed until after cargo door is adjusted and tested.
D. Install thrust rods (9), and links (15) on inboard end of actuator (19) with support pin (11), nut and washers.
E. Tighten nut on support pin (11) to take up slack but leave loose enough for free rotation of links.
F. Clamp bracket assembly (6) loosely to the thrust rods (9) with clamps and blocks (7).
G. Install two tee-fittings (4) in outboard bracket (6). Tighten fitting jamnuts finger-tight.
H. Position bracket (6) along thrust rods and position thrust rods to permit connection of hydraulic coiled tubes (17) to the tee-fittings (4). Finger tighten tubing B-nuts.
I. While maintaining the thrust rod actuator relationship, install the strap (5) around the actuator and fasten to the bracket (6) with nut and bolt.
J. Install a temporary support between the actuator and bracket (6).
K. Install the two tube support brackets (8) loosely with attaching hardware.
Aug 15/68 52-32-31 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 艙門(mén) DOORS(93)
