(2)
Install panel attach nuts (and screws where applicable) along top and bottom edge of the panel.
(3)
Tighten panel fastener studs (18), one-quarter turn, along forward and aft edges of the panel.
(4)
Attach panel to lining retainer (6, detail A) with four screws (8).
B. Install assist handle (detail B).
(1)
Attach beveled outer collars (13), assist handle nuts (14), and inner collars (15) to door structure with bolts (16).
(2)
Engage threads on assist handle (5) with threads in the assist handle nuts (14) and install assist handle by rotating nuts using the AN8514-4 wrench.
C. Install galley service door inside handle (detail A).
(1)
On airplanes with round handles, install door inside handle (3) with shim(s) (7), insert support (9), washers (10), and three bolts (12).
NOTE: On airplanes with shim (7) made up of laminations, remove laminations as necessary to allow a clearance of 0.10 inch between outer edge of door inside handle and door lining. Alter bolt grip length or add washer under bolt head as required to allow for shimming variations.
(2)
On airplanes with rectangular handle,
install handle, two bolts, washers and lockwire.
(3)
Lockwire bolts.
(4)
Install insert (11) in center of door inside handle.
D. Install escape slide assembly (4) on door [Ref Chapter 25, Escape Slide Assembly (Door-Mounted)].
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Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-41-31 Page 405
GALLEY SERVICE DOOR STRUCTURE TORQUE TUBE - REMOVAL/INSTALLATION
1. General
A. The following procedure is for the forward galley service door but is also applicable for the aft galley service door.
2. Equipment and Materials
A. Grease - MIL-G-21164 (Ref 20-60-2)
3. Remove Galley Service Door Structure Torque Tube (Fig. 401)
A. Remove door from airplane, as described in 52-41-0, Removal/Installation.
B. Remove access panel on outside of body between the upper and lower door hinge cutouts to obtain access to structure torque tube.
C. Remove bolts securing sleeves to torque tube and upper and lower hinge link pin. Slide the sleeves clear of hinge link pins.
D. Raise and lower torque tube to remove sleeves.
E. Remove torque tube by withdrawing outboard through upper or lower hole in structure.
4. Install Galley Service Door Structure Torque Tube (Fig. 401)
NOTE: Hinge link pins, sleeves, and torque tube spares are supplied as a matched assembly or as individual undrilled parts. Undrilled hinge link pins and torque tubes or a combination of undrilled hinge link pins/sleeves or torque tube/sleeves may be installed and drilled during installation.
A. Apply a thin coat of grease to mating surfaces of hinge link pins, sleeves and torque tube.
B. Install hinge link pins in upper and lower hinge link.
NOTE: A master spline is incorporated in the splines of the link pins and the upper and lower hinge links. If matched structure torque tube assembly is installed the hinge links will be properly aligned when all components are assembled.
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Feb 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-41-41 Page 401
C. Position torque tube in structure by inserting through upper or lower hole in structure.
D. Raise and lower torque tube and install sleeves.
E. Insert bolts through sleeves, install washers and nuts, and tighten bolts.
F. If required, drill hinge link pin and/or torque tube to match fastener holes in sleeve.
(1)
Clamp upper and lower hinge links so that they are flush with airplane external skin.
(2)
Drill two 0.234-inch diameter holes through sleeve and torque tube and/or sleeve and hinge link pin. Ream holes to a finished size of 0.2500 +0.0005 inch.
(3)
Insert bolts through sleeve, install washers and nuts, and tighten bolts.
NOTE: Final alignment of torque tube upper and lower hinge links is made by adjusting snubber during door installation.
G. Check that sleeve fasteners clear structure when torque tube assembly is rotated. If necessary, trim any fastener threads to provide clearance.
H. Install access panel removed to obtain access to torque tube.
I. Install door as described in 52-41-0, Removal/Installation.
500
52-41-41 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/79
500 Door Structure Torque Tube Installation
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