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AC 43.13-1B 9/8/98 4-59. REPAIRING CRACKED MEM BERS. Acceptable methods of repairing vari ous types of cracks in structural elements are shown in figures 4-21 through 4-24. The fol lowing general procedures apply in repairing such defects. a. Drill small holes 3/32 inch (or 1/8 inch) at the extreme ends of the cracks to minimize the possibility of their spreading further. b. Add reinforcement to carry the stresses across the damaged portion and to stiffen the joints. (See figures 4-14 through 4-17.) The condition causing cracks to de velop at a particular point is stress concentra tion at that point in conjunction with repetition of stress, such as produced by vibration of the structure. The stress concentration may be due to the design or to defects such as nicks, scratches, tool marks, and initial stresses or cracks from forming or heat-treating opera tions. It should be noted, that an increase in sheet thickness alone is usually beneficial but does not necessarily remedy the conditions leading to cracking. 4-60. STEEL AND ALUMINUM FIT TINGS. a. Steel Fittings. Inspect for the follow ing defects. (1) Fittings are to be free from scratches, vise and nibbler marks, and sharp bends or edges. A careful examination of the fitting with a medium power (at least 10 power) magnifying glass is acceptable as an inspection. (2) When repairing aircraft after an ac cident or in the course of a major overhaul, in spect all highly-stressed main fittings, as set forth in the manufacturer’s instruction manual. (3) tings. (4) Replace torn, kinked, or cracked fit Page 4-40 Par 4-59 Elongated or worn bolt holes in fit tings, which were designed without bushings, are not to be reamed oversize. Replace such fittings, unless the method of repair is ap proved by the FAA. Do not fill holes with welding rod. Acceptable methods of repairing elongated or worn bolt holes in landing gear, stabilizer, interplane, or cabane-strut ends are shown in figure 4-25. b. Aluminum and Aluminum Alloy Fit tings. (1) Replace damaged fittings with new parts that have the same material specifica tions. (2) Repairs may be made in accordance with data furnished by the aircraft manufac turer, or data substantiating the method of re pair may be submitted to the FAA for ap proval. 4-61. CASTINGS. Damaged castings are to be replaced and not repaired unless the method of repair is specifically approved by the air craft manufacturer or substantiating data for the repair has been reviewed by the FAA for approval. 4-62. SELECTIVE PLATING IN AIR CRAFT MAINTENANCE. Selective plating is a method of depositing metal from an elec trolyte to the selected area. The electrolyte is held in an absorbent material attached to an in ert anode. Plating contact is made by brushing or swabbing the part (cathode) with the elec trolyte-bearing anode. a. Selective Plating Uses. This process can be utilized for any of the following rea sons.PDF Image | AFS-640
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