52-41-00
ALL ú ú B01 Page 8 ú Mar 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
B. A hole in the top guide plate allows engagement of a latch pin manually released by a stowing release lever.
6. Lower Hinge Assembly____________________
A. The lower hinge arm (Fig. 1) is splined at one end to receive the torque tube which rotates in the lower hinge support. The other end of hinge arm is connected to the hinge link. The hinge link is also splined to receive a torque tube. Two stop plates are mounted at the lower hinge position at the forward frame of the door opening. A radius link attaches between the stop plates and is fork-shaped to receive the hinge link. The radius link has a stop pin to engage the stop plates. The snubber has spherical-type end bearings and is connected to the radius link and the attach fitting on the hinge support.
7. Door Lining and Insulation__________________________
A. The galley door panels are decorative linings made of vinyl-aluminum or tedlar-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 (Ref Chapter 56, Door-Mounted Windows).
8. Operation_________
A. The door is opened from the airplane interior by rotating the inside handle clockwise. 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 comes on (Ref 52-71-00). The latch rods also operate the control rods attached to the upper and lower gates, causing the gates to fold inward. Further rotation of the handle to full travel of 180 degrees allows the cam plate to transmit angular movement 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. 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 causing 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 degrees counterclockwise during final movement of the door to the open latched position. This is due to the change in relative position of the hinge arms, guide arm, and snubber, passing beyond 180 degrees 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.
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