AIR CONDITIONING ACCESS DOORS - DESCRIPTION AND OPERATION
1. General
A. The air conditioning access doors provide access to the two air conditioning packs which are installed one on each side of the fuselage keel beam (Fig. 1). The doors form a part of the unpressurized fairing on the lower surface of the fuselage near the wing root extending from the intersection of the wing front spar plane and fairing contour to the intersection of the wing rear spar plane and fairing contour.
B. The doors are similar in construction and the five hinges on each door are arranged so that the doors hinge down from their inboard edge from the keel beam lower chord structure. Each door is of epoxy reinforced glass fabric laminate faced honeycomb core construction. The skins, doublers, gap covers and inserts are of epoxy reinforced fiberglass fabric. On some airplanes, graphite/kevlar skins are installed. The inner surface of each door is covered with aluminum foil and the outer surface is coated with flame sprayed aluminum.
2. Latching Mechanism
A. There are ten heavy duty flush latches installed normal to the door contour on each door. Six of the latches are located near the outboard edge of each door, three near the forward edge and one near the aft edge. The latches secure the doors in closed position, with the latch mechanism permitting quick access to the equipment enclosed by the doors. A trigger is provided on each latch which can be operated by moderate thumb pressure to release the latch bolt from the closed position. The fail-safe design of the latch is such that the failure of the trigger return mechanism will not cause the bolt to open. The exposed surface of each flush latch in closed position is similar in color to the adjacent flame sprayed aluminum fiberglass structure. The other surfaces of the latch that are visible from the outside when the latch is in open position are, in contrast, a bright red fluorescent color to provide rapid visual inspection of the latch position. For information on adjustment/test of these latches, refer to Chapter 12, Hartwell Type Latches.
3. Operation
A. Each door is opened by unlatching and manually restraining the door as it hinges down from its closed position. The free end of the brace tube is then unlatched from its stowed position on the brace catch, on the inner surface of the door panel, and used to secure the door in open position. When closing the door the brace tube is returned to its stowed position on the catch and the door is then closed and latched.
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Oct 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-48-11 Page 1
Air Conditioning Access Door 500
52-48-11 Figure 1 Nov 15/67
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AIR CONDITIONING ACCESS DOORS - APPROVED REPAIRS
1. General
A. Aluminum foil delamination or blisters on the inner surface of the air conditioning bay access doors will affect the ADF system due to the proximity of the ADF loop. Any removal of the aluminum foil from the door, either in part or as a whole, will also affect the ADF system. The following procedure describes the repair of delaminated or blistered areas in the foil.
2. Equipment and Materials
A. Sharp instrument for cutting aluminum foil
B. Smooth edges plastic spatula, or other suitable instrument, to smooth aluminum foil
3. Repair Air Conditioning Access Doors
A. Visually establish the area over which the foil has delaminated from the door inner skin.
B. Using a sharp instrument, cut 0.10 (+0.15/-0.05) inch long slits in the foil with a 3.0 x 3.0 inch (approximately) matrix pattern to cover the entire delaminated area. (See figure 801.)
CAUTION: EXTREME CARE IS NECESSARY TO PREVENT CUTTING OF THE GLASSCLOTH SKIN IMMEDIATELY UNDER THE FOIL. USE A SIDE SLITTING ACTION RATHER THAN A DIRECT CUT ONTO THE DOOR.
C. Starting from the edge of the delaminated area, press the foil back onto the door. Work evenly around the delaminated area, finishing in the center. Due to stretching of the foil, large delaminated areas will have an excess of foil material, causing wrinkles to form during the process of pressing the foil back onto the door inner skin.
D. Use a smooth edged plastic spatula, or other similar instrument, to smooth out or reduce as much as possible the wrinkles formed in the foil.
CAUTION: ANY REMOVAL OF ALUMINUM FOIL FROM THE DOOR, EITHER IN PART OR AS A WHOLE, WILL AFFECT THE ADF SYSTEM.
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Aug 15/68 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-48-11 Page 801
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