Forward Galley Service Door Lower Gate Hinge Inspection 500
52-41-0 Figure 602 May 01/98
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
F. Carefully separate the hinge and clean the hinge surfaces.
G. Lightly push against the hinge and do a close visual inspection of the hinge for cracks. Use an inspection mirror and light as needed. A crack will appear as a thin line. Be careful not to mistake the edge of the shim for a crack. Free movement of the hinge could be the result of a large crack or loose hinge screws. Tighten any loose hinge screws as needed.
NOTE: If a crack is found, stop the inspection and replace hinge per Service Bulletin 737-52A1124.
H. Put the Airplane Back in Its Usual Condition
(1)
Install hinge pin. If the old hinge pin was damaged, use a new pin.
(2)
Install spring pins. If necessary, drill new holes 0.094 to 0.097 inch diameter.
(3)
Replace sealant removed in step C.
4. Galley Service Doors Hinge Inspection (Fig. 603)
A. Measure the clearance at the top and bottom of the doors. Refer to 52-41-00/501 for clearance limits.
B. Visually inspect clearance around hinge arm covers and hinge links. Make sure hinge arm covers and hinge links do not contact the outer skin of the fuselage or the outer skin of the door throughout the opening and closing cycle.
C. Visually inspect clearance between upper hinge link and guide plate. Make sure the upper hinge link does not contact the guide plate throughout the opening and closing cycle.
500
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-41-0 Page 605
Galley Service Doors Hinge Inspection 500
52-41-0 Figure 603 May 01/98
Page 606
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
GALLEY SERVICE DOOR - APPROVED REPAIRS
1. General
A. In some cases, due to tolerances and mismatching of hinge arms, door hinge arm locking bolts are not properly engaging with their respective grooves in the torque tube hinge link pins. This results in the door slipping down on the hinges making it difficult to position the door in the opening during closing. It has been necessary in some cases to raise the door into position before closing.
B. The hinge arms may be modified to provide positive engagement of the hinge arm to the hinge link pins by drilling the 0.250-inch diameter locking bolt holes in the hinge arms oversize, adding flanged spacers in the bolt holes and reinstalling the locking bolts through the spacers. The larger diameter of the locking bolt spacer combination ensures positive contact with the grooves in the hinge link pins. Hinge arms with part numbers 65-73978-7 and -8 are redesigned to bring the hinge bolt holes closer to the locking grooves and this procedure does not apply to these parts.
NOTE: This repair procedure applies to the aft entry door also.
C. Repair of galley service door fuselage mounted door stops may be accomplished as a basic repair (Ref par. 4).
2. Equipment and Materials
A. Alodine 1200 - MIL-C-5541 (Ref 20-30-41)
B. Chemical and Solvent Resistant Finish - BMS 10-11, type I (Ref 20-30-41)
C. Spacers, Flanged - BACS18C8-8 (4 required)
D. Sealant - BMS 5-79 or 5-95 (Ref 20-30-41)
3. Repair Galley Service Door Hinge Arms (Fig. 801)
A. Position door in stowed open position.
B. Remove two locking bolts from upper hinge arm.
C. Align grooves in hinge pin with holes in hinge arm.
D. Ream existing 0.250/0.254-inch diameter locking bolt holes in hinge arm to 0.257/0.261-inch diameter 0.50 inch deep to accommodate spacers. Pretreat holes (Method II) and apply Alodine per 51-21-21 and 51-21-41, Cleaning and Painting. Apply primer per 51-21-171, Cleaning and Painting.
E. Insert BACS18C8-8 flanged spacer through hinge arm at each bolt hole. Allow spacers to bottom out against hinge arm face on far side of slot (detail A). Add thin washers if required to eliminate any gap between spacer flanges and hinge arm. A maximum of five washers per spacer is allowed.
F. Install locking bolts.
G. Repeat above steps on lower hinge arm.
500
Feb 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-41-0 Page 801
4. Repair Stop Fitting Cracked Along Parting Line from End Into Stop Fitting Bearing Plate Hole (Fig. 802)
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