(2)
Use the Akro installation instructions to attach the patch over the center of the damage.
4. Repairs for Molded Panels, Shrouds, and Panels with Complex Curves
A. General
(1) The task that follows is a repair for molded panels, shrouds, and panels with complex curves.
B. Equipment and Materials
(1)
Resin - Fiberglass, BMS 8-201, Type II
(2)
Abrasive paper (200 grit or finer)
(3)
Fiberglass Fabric - BMS 9-3, Type H
(4)
Solvent
NOTE: Use one of these:
(a)
Naphtha, Aliphatic - TT-N-95, Type I or II
(b)
Isopropyl Alcohol
500
25-52-100 Page 804 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/93
C. Procedure - Repair Molded Panels, Shrouds, and Panels with Complex Curves
(1)
Get access behind the panel or remove the panel from the airplane (Ref 25-52-111/401, 25-52-121/401, or 25-52-131/401).
(2)
Lightly rub the damaged area with abrasive paper on the two sides of the panel.
(3)
Clean the damaged area with solvent.
(4)
Do the structural repair on the fiberglass side of the panel (Ref SRM 51-40-9).
(5)
Mix 100 parts by weight of Epocast 50-A resin to 15 parts by weight of Epocast No. 946 hardener (BMS 8-201, Type II).
(6)
Do the steps that follow to the front and the back of the panel:
(a)
Apply a layer of the mixed adhesive resin to the side of the damaged panel that shows in the cargo compartment.
(b)
Apply a layer of BMS 9-3, Type H, fiberglass fabric on the layer of adhesive resin.
NOTE: The fiberglass fabric should make a minimum of a 2-inch overlap on the area that is not damaged. For example, the fiberglass fabric dimension that is necessary for a 1.5-inch diameter hole would be 5.5-inch diameter.
(c)
Apply one more layer of the adhesive.
(7)
Allow the adhesive to cure for a minimum of 24 hours at 77 +10°F or a minimum of 1 hour at 150 +10°F.
(8)
Attach permanently with bolts, NAS603-5P or equivalent, washers, AN960JD10L, and nuts, MS21042L3, at a maximum of 2 inches apart and approximately 0.5 inch from the edges of the fiberglass fabric.
(9)
Make sure there is sufficient clearance between the bolts and the adjacent systems behind the panel.
(10)
Grind the ends of the bolts smooth with the nuts to get sufficient clearance.
(11)
Install the panel if you removed it to do the repairs (Ref 25-52-111/401, 25-52-121/401, or 25-52-131/401).
(12)
If sufficient clearance is still not obtained, replace the damaged panel.
5. Silicone Impregnated Liner Repairs
A. General
(1) The task that follows is for the repair of silicone impregnated fabric which is used as the cargo door liners.
B. Equipment and Materials
(1)
Thread, Fiberglass - P/N GTH-18 (Supplier: Lance Industries)
(2)
Material, Biscote Patch - P/N HT101 (Supplier: Bisco Products Inc.)
C. Procedure - Repair the Silicone Impregnated Liner
(1) Use fiberglass thread to stitch the tear together or stitch a patch of biscote material on the damage.
NOTE: There should be approximately seven stitches for each inch and a minimum material overlap of 1 inch.
500
Feb 20/93 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 25-52-100 Page 805
CARGO COMPARTMENT CEILING LINING - REMOVAL/INSTALLATION
1. General
A. The cargo compartment ceiling lining is composed of many small panels. When performing maintenance procedures on the cargo compartment ceiling lining, it may be necessary to remove all the ceiling lining panels or possibly only one of the small panels. When removing only one panel, remove the cap strips only around the periphery of the panel to be removed.
B. Screws securing the lining panels vary in length. Keep sizes separated and mark location to facilitate installation.
C. Velcro tape bonded to the floor beams is used extensively to retain the lining panels.
D. The removal/installation procedures for cargo compartment lining panels are the same for the forward and aft cargo compartments, except as noted in the following procedures.
E. The cargo compartments are limited pressure sealed compartments. Leakage across the interior surface must be held to minimum. Seal all visible open holes, joggles, and irregular metal surfaces where leakage may occur. All rubber seal joints must be butted to ensure minimum air leakage.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 EQUIPMENT/FURNISHINGS(132)
