(2)
Fuel tanks empty.
(3)
Airplane shall be substantially complete with all major components installed, except that interior items such as seats, galleys, lavatories, etc., may be missing. Electronic "Black Boxes" may also be missing.
(4)
All tools, equipment, and personnel must be removed from airplane. Tools and equipment may be placed directly over main gear if removal is not convenient.
(5)
All airplane parts of significant weight (30 pounds) that are on airplane but not installed would be placed in the approximate position they will occupy when installed.
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E. Remove cargo door personnel safety barrier, if installed.
6. Install Main Cargo Door
A. Check hinge loops and pins for wear per Fig. 402.
B. Position door so that hinge pin holes are in alignment.
C. Lightly lubricate forward and aft hinge pins.
CAUTION: DO NOT LUBRICANT CENTER EIGHT HINGE PINS. HINGE PINS ARE DRY LUBRICATED. REMOVE AS LITTLE DRY LUBRICANT AS POSSIBLE WHEN INSTALLING PINS.
D. With a hammer or pneumatic hammer carefully install hinge pins. Assemble removed hinge sections as necessary.
E. Position forward and aft hinge fairing plates and install bolts.
F. Install diaphragm seal at door hinge (Ref 52-09-111, Removal/Installation).
G. Lower cargo door with the overhead crane until door fits in door opening. If new door is being installed, trim door as necessary to fit into door opening. Final trim will be per step M.
H. Remove door sling or lifting fixture and replace countersunk screws.
I. Connect wiring bundle from door to terminal strop in ceiling at station 460.
J. Connect both flexible hydraulic lines to door.
K. Connect the flexible oxygen line to door.
L. Position outboard link on door, install the bolt and washers and firmly tighten nut. Back off nut until cotter pin can be installed.
M. If not previously installed, install latch actuator (Ref 52-32-21, Removal/Installation).
N. Adjust and test main cargo door assembly (Ref 52-32-0, Adjustment/Test).
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O. Trim door to final dimensions. Gap between door outside skin and fuselage outside skin at forward lower and aft sides should be 0.18 to 0.25 inch.
P. Test main cargo door system (Ref 52-32-0, Adjustment/Test).
Q. Install cargo door ceiling panels (Ref 52-32-81, Removal/Installation).
R. Install hatracks, passenger service units and cove assembly (Ref Chapter 25,
Equipment/Furnishings).
7. Restore Airplane to Normal
A. Install cargo door ceiling panels (Ref 52-32-81).
B. If a new door was installed, install the following components on the cargo door as required:
(1)
New bulb seal
(2)
Insulation and heating blankets
(3)
Dado panels
(4)
Window panels
(5)
Cove assembly
(6)
Hatracks and passenger service units
C. Close the following circuit breakers on load control center P18:
(1)
COVE LTS - LEFT
(2)
CEIL LTS - L FWD
(3)
READING LT - LEFT
(4)
NO SMOKING
(5)
PASS SIGN CONTROL
(6)
FASTEN SEAT BELT
(7)
PASS AND CREW CALL
D. Close the PASSENGER ADDRESS circuit breaker on load control center P6.
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MAIN CARGO DOOR ASSEMBLY - ADJUSTMENT/TEST
1. Main Cargo Door Assembly Adjustment
A. General
(1) The following procedures cover adjustment of door centering, lock mechanism and latch mechanism. Additional adjustments other than those given in this procedure may be required. For adjustment of switches, refer to the appropriate subject adjustment/test procedure. The latch actuator should be installed prior to completing the latch mechanism adjustments.
B. Equipment and Materials
(1) Overcenter Measurement Locating Tool, Main Cargo Door Latch - F80187-6
C. Prepare for Adjustment
(1)
Remove window panels and dado panels from door (Ref 52-32-81 R/I).
(2) 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 舱门 DOORS(87)
