(2)
Cure 8 hours at 70°F or higher before exposure to rain or outdoor temperatures below 75°
F.
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10. In Process Correction
A. Surfaces with Minor Damage (Not to Bare Metal)
(1)
Sand smooth with 280 grit or finer wet or dry abrasive paper.
(2)
Remove sanding dust with a clean cheesecloth saturated with solvent, Series 86 (Ref AMM/SOPM 20-30-86); wipe dry with clean cheesecloth.
(3)
Reprime if necessary masking surrounding areas. Feather the edges of the dry primer with Scotchbrite pads to make a smooth finish.
(4)
Remove masking and repaint enamel. Spray overlap to make a continuous unblemished surface.
B. Areas with Extensive Damage (Bare Metal Exposed)
(1)
Strip paint film from the damaged area per 51-2-21, Paint Stripping (use Turco 5351 only) or sand to a smooth surface taking care not to sand to bare metal. Feather the edges of the adjacent area with 280 grit or finer abrasive paper wet with water.
CAUTION: DO NOT ALLOW PAINT STRIPPER TO CONTACT FIBERGLASS OR SEAMS OF ADHESIVE BONDED PARTS.
(2)
Remove sanding dust with clean cheesecloth saturated with solvent, Series 86 (Ref AMM/SOPM 20-30-86). Wipe dry with clean cheesecloth.
(3)
Reapply appropriate primer systems and topcoats as required. Feather all edges to make a continuous smooth finish.
C. Areas with Defective Paint Films (Sags, Runs, Drips or Orange Peel)
(1)
Sand area to the degree necessary to correct defects using 280 or finer wet or dry abrasive paper. Feather the edges into surrounding area.
(2)
Wipe sanding residue from area with cheesecloth dampened with solvent, Series 86 (Ref AMM/SOPM 20-30-86).
(3)
Touch up with appropriate enamel.
11. Paint Exterior Decorative Finishes
A. Do not paint pressure relief valve or outflow valve. Paint may prevent pressure relief valve or outflow valve from proper operation. No paint should be applied for a one-inch wide circular band around or on the pressure relief valve doors or outflow valve.
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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 protection from, and proper drainage of, certain fluids. Examples of this are the areas below the toilets, galley, access doors, and battery stowage.
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.
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F85349 F85444 G44572F85451 F85502 F85811
Body Sealing Index and Requirements 500
51-31-0 Figure 1 (Sheet 1) Apr 01/97
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
515 Body Sealing Index and Requirements
Apr 01/97 Figure 1 (Sheet 2) 51-31-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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