(11)
Check upper and lower hinge arm cover installation. If necessary, use laminated shims to fair covers with fuselage external contour.

(12)
Check seal installation (Ref 52-09-141, Diaphragm-Mechanical Seals).

501 
Sep 01/02  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-41-0 Page 506B 

501  Galley Door Contour Adjustment 
Feb 20/91  Figure 502  52-41-0 
Page 507 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

NOTE: Shortening control rod will increase handle retraction force.
543 
52-41-0 Page 508  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Sep 01/02 

D.  Restore Airplane to Normal
(1)  
Remove 60-pound weight from door.

(2)  
Install forward mechanism access panel (l, Fig. 501) on door with screws.

(3)  
Install door lining and insulation panels (Ref 52-41-31, Removal/Installation).

(4)  
Test door as described in par. 3.

3.  Galley Door Adjustment for Soft Unlatching
A.  Prepare for Adjustment
(1)  
Remove door lining and insulation panels (Ref 52-41-31, Removal/Installation).

(2)  
Remove screws attaching forward mechanism access panel (l, Fig. 501) to door structure and remove panel.

(3)  
Attach 60-pound weight to inside door frame at approximate midpoint at lower half of door. (This weight is a substitute for escape slide pack removed with lining.)

B.  Adjust Galley Door to correct for Soft Unlatching
NOTE:  Adjust door when airplane is on wheels. Do not make door adjustments when airplane is jacked.
(1)  
Disconnect upper and lower control rods (Fig. 501) from latch rods at crank (33).

(2)  
Rotate latch rod (30) until rig pin can be inserted through index holes in door roller cam crank (28) and into support fitting (29), and adjust control rod (31 or 32, detail C) length to allow bolt insertion through rod end and crank. Install bolt. Repeat for the other latch rod. Remove rig pins.

(3)  
After completion of adjustments, check that latch rollers engage latch roller cam fittings with no interference.

(4)  
Check that latch roller clearance is 0.04-0.28 inch (Detail G) and adjust if necessary.

500 
May 15/80  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-41-0 Page 509 

C.  Restore Airplane to Normal
(1)  
Remove 60-pound weight from door.

(2)  
Install forward mechanism access panel (1, Fig. 501) on door with screws.

(3)  
Install door lining and insulation panels (Ref 52-41-31, Removal/Installation).

(4)  
Test door as described in par. 4.

4.  Galley Service Door Test
A.  Equipment and Materials
(1)  Door Interior Handle Torque Wrench Adapter – F80171-1, or equivalent
B.  Test Galley Service Door
NOTE:  Airplane must be on its wheels to test door (no jack support).
(1)  
Check that snubber operates correctly to retard or snub rapid motion of door toward stowed and cocked position. No snubbing action should be felt when door is moved slowly from the cocked to stowed position or back to the cocked position. The snubber is designed to resist accelerated movement only and if the snubber performs otherwise, it should be replaced.

(2)  
With interior trim installed, check torque applied on handle when door is opened and closed.

NOTE:  Use interior handle torque wrench adapter ST2580-257 or equivalent to facilitate checking of handle torque.
(a)  
Check that door moves through full cycle of operation smoothly with no binding spots.

(b)  
Check that door opening torque applied to operate handle during the first 90 degrees of handle rotation does not exceed 360 pound-inches. Check that torque required for remaining portion of the opening cycle does not exceed 600 pound-inches.

(c)  
Close door and check that torque applied to handle during closing cycle does not exceed 600 pound-inches.

(d)  
If requirements are not obtained, remove door lining and insulation panels and perform step (3). Refer to 52-41-31, Galley Service Door Lining and Insulation.

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(3)  
With interior trim removed, check torque applied on handle when door is opened and closed when requirements in step (2) are not met.
　
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