(a) Sandpaper, No. 240 grit
(3)
Repair: (Stainless Steel)
(a) Sand damaged area, using No. 240 grit sandpaper.
S. Repair Method No. 17
(1)
General
(a) This method is used to repair slight surface abrasions in anodized aluminum parts.
(2)
Equipment and Materials
(a)
Alodine - 1000 Class B
(b)
burnishing Tool
(3)
Repair: (Anodized Aluminum)
(a)
Remove all burrs and rough edges with burnishing tool.
(b)
Apply alodine 1000 Class B, Method 2, in accordance with BAC 5719, Process Specification for alodizing to damaged area with cotton swab.
559
Aug 15/76 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 25-00-11 Page 227
T. Repair method No. 18
(1)
General
(a) This method is used to repair damaged, decorative paper base laminate faces on interior honeycomb sandwich panels. this repair shall not be used on defects greater than .” in the maximum dimension. The minimum spacing between repairs shall be 1 inch.
(2)
Equipment and Materials
(a)
Fiber Resin - No. 5-418S or 5-419S
(b)
Fiber Resin Hardener - No. 5-40A
(c)
Epocast 4B
(d)
Hardener #951
(e)
Epoxy enamel (BMS 10-11, Type 2 Clear Gloss)
(3)
Repair: (Honeycomb Sandwich Panels)
(a) Repair Procedure 1) Area adjacent to damage shall be adequately protected during rework to prevent further damage to decorative panels.
2) Damaged area shall be removed from honeycomb sandwich panel by cutting a hold slightly larger than damage, but not exceeding . inch in diameter. Do not drill through skin on opposite side of panel.
3) Hole shall be filled with a slight excess of epoxy resin (listed below) to compensate for shrinkage during cure.
EPOXY RESIN PARTS BY WT. Fiber Resin No. 5-418S or 5-419S 100 Fiber Resin Hardener No. 5-40A 12-13 Color match or tint resin using color matching kit from Fiberlay, Inc., or equivalent. Optional Resin to be used in nonperforated panels only.
PARTS BY WT. Epocast 4B 100 *Hardener 951 5-7 Work life at 80 ±10°F is 20-30 minutes, and cure at 80 ±10°F is 18 to 24 hours. *Amount of catalyst can be varied within these limits to suit the using Shop.
559
25-00-11 Page 228 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/76
4) After curing, potting compound shall be finished smooth and flush with face of panel by sanding or machining.
5) Spray repaired area with an epoxy enamel (BMS 10-11 Type 2 Clear Gloss) tinted to match panel.
6) This repair has been approved for use on D10-60199-308 decorative formica (BAC color No. 588). First repairs on other decorative paper base laminates shall be submitted to the Materials Technology Unit and Passenger Accomodations for approval of color match and color fastness.
U. Repair Method No. 19
(1) General
(a) This method is used to repair cuts and scratches and other surface damage in decorative paper-base laminates (Formica) and in Tedlar-Conolite laminates.
NOTE: Color match with this repair is very difficult, and an unsatisfactory gloss and color match may result. Resin used in repair is skydrol-resistant when fully cured.
(2)
Equipment and Materials
(a)
Sandpaper ( 400 to 600 grit )
(b)
Fiber Resin No. 5-418S or 5-419S
(c)
Fiber Resin Hardener No. 5-40A
(d)
Color Matching Kit (Fiberlay Inc.)
(e)
Polishing Wheel, cotton
(f)
Buffing Compound (Learock S-30)
(g)
Mylar Tape
(h)
Plexiglass
(3)
Repair: (Epoxy Paste)
(a) Repair Procedure
1) Area surrounding damage shall be protected during rework to prevent additional damage to decorative panel. Mask a piece of plexiglas with two inch wide Mylar tape. Place masked plexiglas over damaged area, and with a knife cut out a section of tape slightly larger than damaged area. Remove Mylar tape from plexiglas and place tape over damaged area so that cutout is centered over damaged area.
2) Remove all burrs or protruding material from damaged area so that all edges
are flush with the surface.
3) Clean the damaged area with aliphatic naptha per Method 7.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 EQUIPMENT/FURNISHINGS(20)
