500  Galley Service Door Mechanism 
May 15/67  Figure 1 (Sheet 1)  52-41-0 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aft Service Door Mechanism  543 
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581  Galley Service Door Mechanism 
May 01/98  Figure 1 (Sheet 3)  52-41-0 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Galley Service Door Mechanism  500 
52-41-0  Figure 1 (Sheet 4)  May 15/67 
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5.  Upper Hinge Assembly
A.  The upper hinge arm (9, detail C, figure 1) is splined to receive the torque tube (12) which rotates in the upper hinge support (11). The other end of the hinge arm (9) is bolted to the hinge link (5) which is connected to the guide arm (15) by means of pin (4). The hinge link (5) is splined to receive torque tube (14). Guide arm (15) is connected with rod end bearing (13) and attach fitting (10) to hinge support (11). The other end of guide arm (15) contains a spring-loaded guide arm roller that carries two guide arm roller bushings which operate in tracks in roller guide plates (1). A hole in the top guide plate allows engagement of a latch pin which is manually released by a stowing release lever or a stowing release button (3).
6.  Lower Hinge Assembly
A.  The lower hinge arm (11, detail D, figure 1) is splined at one end to receive torque tube (13) which rotates in the lower hinge support (12). The other end of hinge arm (11) is connected by bolt (8) to hinge link (5) which is splined to receive torque tube (3). The two stop plates (1) are mounted at the lower hinge position at the forward frame of the door opening. A radius link (4) is located between the stop plates (1) and is fork shaped to receive the hinge link (5) and has a stop pin to engage the stop plates (1). The snubber (16), has spherical-type end bearings connected to radius link (4) at one end by snubber attachment bolt (2); the other end is connected by bolt (14) to attach fitting (15) which is bolted to hinge support (12).
7.  Door Lining and Insulation
A.  The galley door panels are decorative linings made of vinyl-aluminum laminate with an insulation blanket cemented to the outboard side of each panel. The galley door has an upper panel and a lower panel. The inboard window is removable without removing the panel. Refer to Door-Mounted Windows in Chapter 56.
8.  Operation
A.  The door is opened from the airplane interior by rotating the inside handle clockwise (figure 2). Initial rotation of the cam plate transmits angular movement to the latching crank assembly. The control rods at each end of the latching crank, turn the latch rods and withdraw the latch rollers from the latches, allowing the door to move inward. As the door moves inward the proximity switch in the door warning circuit is closed and the door warning light is energized. Refer to Section 52-71-0. The latch rods also operate the control rods attached to the upper and lower gates, causing these to fold inward. Further rotation of the handle to its full travel of 180° allows the cam plate to transmit angular movement.
501 
May 01/98  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-41-0 Page 7 

Galley Service Door Operation from Inside Airplane  500 
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to the cocking crank assembly. The cocking crank operates the pushrod connected to the torque tube crank. Movement of the pushrod is resisted by the torque tube, causing the door to rotate on the hinge arms and pivot about the torque tube axis. This motion is due to the change in relative positions of the hinge arm and guide arm at the upper hinge, and the hinge arm and snubber at the lower hinge. Tracking of the door is controlled by the guide arm roller in the roller guide plates as the door rotates to the cocked position (figure 2, step 3). The door is swung through the opening by means of the assist handle. The outward lateral travel of the hinge arm transmits motion through the radius link to the guide arm which in turn causes the door to rotate, in an outward direction, about the pivot axis of the torque tube. The inside handle on the door automatically rotates approximately 45° counterclockwise during final movement of the door to the open latched position (figure 2, step 6). This is due to the change in relative position of the hinge arms, guide arm and snubber, passing beyond 180° from the door cocked position and causing the door to counter-rotate and operate the cocking crank and cam plate in reverse. When the door is approximately parallel with the airplane exterior, the stop pin contacts the stop plate and prevents further movement of the door. The door is latched in the open position by the latch pin engaging the latch pin hole.
　
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