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CARGO COMPARTMENT DOORS - DESCRIPTION AND OPERATION
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1. General_______
A. Two cargo compartment doors are installed on the lower right side of the fuselage (Fig. 1). Both are plug-type, inward opening doors, hinged at the upper edges and operated manually from either inside or outside the airplane. Except for slight differences in shape, both doors are similar in design and operation.
B. The forward cargo compartment door provides access to the oxygen storage cylinders.
C. Each cargo door is an alclad structure with outer and inner skin and internal webs and stiffeners. The door is hinged from the fuselage structure by two hinge arms on the upper edge. The hinge arms are adjustable by use of serrated plates and shims. The forward and aft cargo doors are equipped with a centering device. Two rollers at the forward and aft door edges locate the door in the closed position by engaging roller stop fittings on the door jambs. A continuous sealing strip around the periphery of the door prevents loss of cabin pressure around the door edges. Pressurization loads on the door are transmitted to the fuselage by twelve adjustable stop fittings attached along the forward, aft, and lower edge of the door. The door bears against corresponding stop pads attached to the fuselage structure surrounding the door. Loads on the upper edge of the door are transmitted to fuselage structure by the two hinge arms. Two access panels in the outer skin provide external access to the door latching mechanism to open the door in the event of failure of the latching mechanism.
D. Each door has a door warning switch.
E. Each door is equipped with a balance mechanism to counterbalance the weight of the door and thus, facilitate door opening. A snubber installed between the hinge arms on each door restrains the free fall of door from the open position if the balance mechanism cable fails. The door is secured in the fully open position by a cam and idler crank located within the counterbalance assembly.
F. On some airplanes there are straps attached to the cargo compartment ceiling. Use these straps as an otional method to hold the cargo door in the open position. Stow the straps prior to flight. Hook the ends of the straps together and pull the straps tight to stow the straps. This will put the straps between the cargo door and the cargo compartment ceiling when the cargo door is open.
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ALL ú ú B04 Page 1 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FLOOR BEAM
SNUBBER
CABLE CLIP
(2 LOCATIONS)
BEARING PLATE (4 LOCATIONS)
DOOR FRAME
HINGE ARM
(2 LOCATIONS) COUNTER BALANCE ASSEMBLY
LANYARD ASSEMBLY
DOOR STOP
(12 LOCATIONS) CARGO COMPARTMENT DOOR
SEE A INSIDE LATCH HANDLE
CARGO COMPARTMENT
(DOOR IN CLOSED POSITION)
CARGO DOOR LATCH MECHANISM
SEE BFWD LOCK-SPRING
ROLLER ARM (2 LOCATIONS)
DOOR FRAME
DOOR STOP
A
DOOR
FRAME ROLLER STOP
LAMINATED ROLLER STOP SERRATED PLATE
SHIM SERRATED TORQUE TUBE LAMINATED SHIM
PLATE BEARING HOUSING
(2 LOCATIONS) TUBE TORQUE
CARGO DOOR LATCH MECHANISM
B
Cargo Compartment Doors Component Location
Figure 1
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ALL ú ú B03 Page 2 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
2. Latch Mechanism (Fig. 1)
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A. The door latch mechanism consists of an internal horizontal torque tube with a latching roller at each end protruding beyond the edge of the door. These latching rollers engage latch fittings attached to the fuselage structure. The torque tube in the door is connected to the operating handle assembly which consists of a short shaft and a handle at each end. The handle on the inboard side of the door projects beyond the inboard skin, but the outboard handle is spring-loaded so that the handle retracts flush with the exterior surface. A recess finger access pan adjacent to the handle provides access to the handle.
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