(2)
Cut out crack with a 0.06 inch wide slot into the stop pin hole.
(3)
Enlarge stop fitting hole to provide a 0.002 to 0.012-inch diameter clearance with bearing plate.
(4)
Pretreat surfaces (Method II) and apply Alodine per 51-20-2 and 51-20-21, Cleaning and Painting. Apply primer per 51-20-151, Cleaning and Painting.
(5)
Bond bearing plate back in using BMS 5-79 or 5-95 sealant.
500
52-41-0 Page 802 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jan 20/82
500 Galley Service Door Hinge Arm Modification
Sep 20/81 Figure 801 52-41-0
Page 803
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Galley Service Door Approved Repair 500
52-41-0 Figure 802 Jan 20/82
Page 804
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
GALLEY SERVICE DOOR HINGE ARMS - REMOVAL/INSTALLATION
1. General
A. The procedures described and illustrated in this section are for the aft galley service door and are typical for the forward galley service door.
2. Equipment and Materials
A. Grease - MIL-G-23827
3. Remove Galley Service Door Hinge Arms
A. Remove door from airplane as described in 52-41-0 R/I - Galley Service Door.
B. Remove nut (12, Detail A, Fig. 401), washer (11) and cam plate (10) and allow outside handle shaft (7) and outside handle (6) to drop clear.
C. Unscrew and remove hinge arm cover from outside surface of each hinge arm (18, Details B and C).
D. Remove forward mechanism access panel (2) to obtain access to door torque tube (5) and handle mechanism housing (4).
E. Remove bolts from torque tube (3, Fig. 402), connecting sleeves (2) and hinge link pins (1). Slide the connecting sleeves away from the hinges far enough to expose joints between the torque tube and the hinge link pins.
F. Remove the four bolts (21) that hold the outside handle to the handle housing.
G. Remove twelve housing attachment bolts (8, Detail A, Fig. 401) securing handle mechanism housing (4) to door structure.
H. Disconnect upper and lower gate control rods at their connection to each gate.
I. Disconnect upper and lower control rods (1) and (3) through the access holes in the handle mechanism housing from the latching crank (9). Move the control rods clear of the handle mechanism.
J. Remove hinge link bolts (15, Details B and C) and hinge link pin bolts (19) from hinge arms (18).
NOTE: The hinge link pin bolts can be reached from the outside of the door after the hinge covers are removed.
K. Slide the hinge link pins out of engagement with the hinge arms and remove the hinge arms
500
Jun 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-41-11 Page 401
Galley Service Door Hinge Arm Installation 500
52-41-11 Figure 401 (Sheet 1) Nov 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
543 Aft Service Door Hinge Arm Installation
Jun 20/91 Figure 401 (Sheet 2) 52-41-11
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Galley Service Door Hinge Arm Installation 501
52-41-11 Figure 401 (Sheet 3) May 01/98
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Door Hinge Arm and Torque Tube Assembly
May 01/98 Figure 402 52-41-11
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
L. Remove the handle mechanism housing complete with torque tube crank (14) and the torque tube from the door. This step is necessary if the distortion that necessitated the replacement of a hinge arm may also have resulted (to a less noticeable extent) in the distortion of the torque tube. Even a slight bend in the torque tube, or in one hinge arm, will put the several bearings of the mechanism out of alignment, thus necessitating heavy torque on the operating handle.
4. Install Galley Service Door Hinge Arms
A. Check that O-rings (4, Fig. 402) are in good condition and are seated properly in the grooves of hinge link pin (1). Grease the bearing surfaces of the hinge link pins.
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