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9/8/98 AC 43.13-1B CHAPTER 3. FIBERGLASS AND PLASTICS SECTION 1. REPAIR OF LIGHT LOAD LAMINATE STRUCTURES 3-1. GENERAL. There is a wide variation in the composition and structural application of laminates, and it is essential that these fac tors be given major consideration when any restoration activities are undertaken. To a similar extent, there also exist many types of laminate structure repairs that may or may not be suitable for a given condition. For this rea son, it is important that the aircraft or compo nent manufacturer’s repair data be reviewed when determining what specific type of repair is permissible and appropriate for the damage at hand. NOTE: Review Material Safety Data Sheets for material to be used. When handling materials, prepreg fabrics, or parts with prepared surfaces, ob- serve shelf life. Latex gloves and ap- proved masks must be worn. a. The materials used in the repair of laminate structures must preserve the strength, weight, aerodynamic characteristics, or electri cal properties of the original part or assembly. Preservation is best accomplished by replacing damaged material with material of identical chemical composition or a substitute approved by the manufacturer. b. To eliminate dangerous stress con- centrations, avoid abrupt changes in cross-sectional areas. When possible, for scarf joints and facings, make small patches round or oval-shaped, and round the corners of large repairs. Smooth and properly contour aerody namic surfaces. c. Test specimens should be prepared during the actual repair. These can then be subjected to a destructive test to establish the quality of the adhesive bond in the repaired part. To make this determination valid, the specimens must be assembled with the same adhesive batch mixture and subjected to curing pressure, temperature, and time identical to those in the actual repair. 3-2. FIBERGLASS LAMINATE RE- PAIRS. The following repairs are applicable to fiberglass laminate used for non-structural fairing, covers, cowlings, honeycomb panel facings, etc. Prior to undertaking the repair, remove any paint by using normal dry sanding methods. Bead blasting may be used but cau tion must be exercised not to abrade the sur faces excessively. NOTE: Chemical paint strippers must not be used. NOTE: These repairs are not to be used on radomes or advanced com- posite components, such as graphite (carbon fiber) or Kevlar. CAUTION: Sanding fiberglass lami- nates gives off a fine dust that may cause skin and/or respiratory irrita- tion unless suitable skin and respira- tion protection is used. Sanding also creates static charges that attract dirt or other contaminants. a. Check for voids and delamination by tap testing. (See chapter 5.) When the surface of a fiberglass laminated structure is scratched, pitted, or eroded; first wash with detergent and water to remove all of the dirt, wax, or oxide film. Then scrub the surface with an accept able cleaner. After the surface is thoroughly cleaned, sand it with 280-grit sandpaper, and again use an acceptable cleanser to remove any sanding residue and moisture. This is Par 3-1 Page 3-1PDF Image | AFS-640
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