(b)
Remove the remaining particles with a clean cloth, BMS15-5 that is moist with solvent, Series 85 (AMM 20-30-85/201 or SOPM 20-30-85).
(c)
Dry the surface with a clean cloth, BMS15-5.
(d)
Apply the applicable primer and topcoats again, if necessary, as follows: 1) B51-21-99-307-001, Decorative Exterior Paint System
Application.
(e)
Feather the edges to get a smooth continuous finish.
S 377-026-B00
(2) Repair areas with large damage (bare metal) as follows:
CAUTION: DO NOT LET PAINT STRIPPER TOUCH FIBERGLASS OR SEAMS OF
_______ ADHESIVE BONDED PARTS. THE PAINT STRIPPER CAN CAUSE DAMAGE TO FIBERGLASS OR SEAMS OF ADHESIVE BONDED PARTS.
(a)
Rub the surface smooth with abrasive, A-A-1048, or do this task: 1) B51-21-11-107-006, Paint Stripping.
(b)
Feather the edges of the adjacent area with a 240 grit (minimum) abrasive, A-A-1048 paper that is moist with water.
(c)
Remove the remaining particles with a clean cloth, BMS15-5 that is moist with solvent, Series 85 (AMM 20-30-85/201 or SOPM 20-30-85).
(d)
Dry the surface with a clean cloth, BMS15-5.
(e)
Apply the applicable primer and topcoats as follows:
1) B51-21-99-307-001, Decorative Exterior Paint System Application.
(f)
Feather the edges to get a smooth continuous finish.
S 377-025-B00
(3) Repair areas with defective paint layers as follows:
(a)
Rub the surface with a 240 grit (minimum) wet or dry abrasive, A-A-1048 paper to remove defects.
(b)
Feather the edges into the adjacent areas.
(c)
Remove the remaining particles with a clean cloth, BMS15-5 that is moist with solvent, Series 85 (AMM 20-30-85/201 or SOPM 20-30-85).
(d)
Dry the surface with a clean cloth, BMS15-5.
(e)
Apply the applicable topcoats the manufacturer's specifications and Table 701.
(f)
Feather the edges to get a smooth continuous finish.
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51-21-99
ALL ú ú B02 Page 703 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
SEALS AND SEALING - DESCRIPTION AND OPERATION
_____________________________________________
1. General
_______
A. Certain portions of the airplane structure are sealed to prevent the passage of gases or liquids through the many small gaps which normally exist at joints in fabricated structures (Fig. 1 and 2). Sealing is accomplished by the application of sealing compounds to the crevices, edges and joints through which a fluid might pass. The specification of the sealant used depends upon such factors as its required resistance to the effects of certain fluids and temperatures. In addition to sealing requirements contained in this section, installation drawings for specific items may require more extensive sealing.
B. Most of the structural sealing on the airplane contributes to the formation of three large separate chambers: the pressurized zone of the fuselage and the integral fuel tank of each wing.
C. Several other local areas of structure are sealed to provide corrosion protection from, and proper drainage of, certain fluids. Examples of this are the areas below the passenger floor where all structures contacting the skin is faying surfaced sealed.
CAUTION: TO PREVENT STRUCTURAL CORROSION, CARE MUST BE TAKEN TO ENSURE
_______ STRUCTURE DRAIN HOLES AND DRAIN PATHS ARE NOT INADVERTENTLY COVERED OR FILLED WITH SEALING COMPOUND DURING SEALING OPERATIONS.
D. In the area of the engines, sealant is used to prevent possible
penetration of flammable or hot gases into the wing.
E. Sealing compounds are used to obtain aerodynamic smoothness on exterior surfaces of the fuselage, wing and empennage. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 结构 STRUCTURES(56)
