Main Cargo Door Mechanism Component Location 511
52-32-0 Figure 1 (Sheet 1) May 15/68
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
511 Main Cargo Door Mechanism Component Location
Aug 15/72 Figure 1 (Sheet 2) 52-32-0
Page 3
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
panels along the lower outside edge of the door provide access for emergency unlocking and unlatching of the door in the event of a malfunction of the normal or manual systems. Eight latch mechanism viewing windows are on the lower outside edge of the door below the access panels. The hydraulically operated lift actuator is installed above the ceiling panels adjacent to the main cargo door at station 486. Seven windows with associated interior panels are installed on the door. A main cargo door locked switch is in the lower aft section of the cargo door. The cargo door locked switch interrupts power to the main cargo door control panel switches whenever the cargo door is locked. A main cargo door position switch is installed in the fuselage doorsill at station 427. The cargo door position switch is part of the door warning circuits, floodlight circuits and control valve sequencing circuits. Two canopy position (limit) switches and operating cams are installed with the lift actuator at station 486. The main cargo door control panel is installed in the passenger compartment on the left side of station 304 bulkhead. A control valve, shutoff valve, handpump, relief valve, two flow limiters and three check valves are installed in the hydraulic lines on the left wheel well aft bulkhead.
C. The main cargo door is manually unlocked by pulling on the external locking handle; the cargo door is then hydraulically unlatched and opened. Hydraulic system pressure for operation of the main cargo door actuators is controlled from the cargo door control panel. The panel contains two cargo door position switches, an amber warning light and cargo area lighting switches. One switch controls raising the cargo door to the canopy position and closing the door from canopy position. The second switch controls raising the door from the canopy position to the full open position and back to the canopy position. Electrical power for the system is from 28-volt dc bus No. 2 circuit breakers on load control center P6. Manual operation of the door is accomplished with the hydraulic handpump and manual positioning of the hydraulic control valve.
D. The main cargo door unlocked light on the main cargo door control panel and the main cargo door warning light will be on if the door is open. If the door is closed and the handle is unlocked, the main cargo door unlocked light and the main cargo door warning light will be on. In addition, if the handle is unlocked, the lights at latch viewing windows No. 2 and 7 will be off. If either lockpin is not engaged at latch No. 3 or 6, the lockpin switch will extinguish the light at viewing window No. 2 or 7 respectively, and the main cargo door warning light will be on (Fig. 2 and 6).
2. Door Assembly
A. The door is an aluminum structure consisting of the upper and lower door beams, doorframes and stringers. The structure is covered with a full outer skin and on the inside upper portion, with an inner skin. Seven window assemblies are installed below the horizontal centerline of the door. Ten piano-type hinge sections are bolted to the upper door beam. The components of the latch mechanism are attached to the lower beam and frames. A locking handle assembly is installed at the forward end of the door at about the horizontal centerline of the door. The locking mechanism is installed throughout the lower portion of the door below the windows. The latch actuator is installed below the windows in the center of the door. Eight clear plastic viewing panels are installed in the outer skin at the bottom of the door. Eight removable access panels are also installed in the outside skin of the door just above the viewing panels. A door centering cam is installed at the junction of the lower beam and the end doorframe at the fore and aft doorframes. Hydraulic lines, electrical wiring, gasper air and oxygen are connected at the aft end of the door through cutouts in the ceiling lining support beam.
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52-32-0 Page 4 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/79
B. The door structure on the inside of the airplane is normally covered with the door lining consisting of a formed decorative window panel, a carpet riser panel, overhead stowage compartments, and passenger service units. Between the windows and the door lower edge are three insulation and heating panels. One panel starts at the forward edge of the door to the latch actuator; the second panel starts at the aft edge of the latch actuator to the aft end of the door. The third panel runs full length of the door and covers the area above the latch actuator cutout to about halfway up the edge of the window panels. The heating panels are installed with quick disconnects. A bulb seal runs around the periphery of the door. A diaphragm seal runs full length of the door and is connected to the upper door beam and the fuselage beam just below the hinge sections.
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