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lower surface, between N1 and N2 ribs, forward of the spar. Order Kit OPT10 918800. CAUTION DEPENDING ON THE LOCATION OF THE REPAIR AREA, THE SKIN THICKNESSES CAN BE DIFFERENT. REFER TO CHAPTER 51-30-01 TO DETERMINE THE THICKNESSES OF THE SHEETS TO BE USED. A. Tools and consumable materials - AU4G1 2024 sheets, thickness 0.039 or 0.047 and 0.063 in (1 or 1.2 mm and 1.6 mm) (for shim and stiffener) - Abrasive cloth (TB 05-916C) - Activator (TB 05-925) - Filler Alu (TB 05-911) or Adhesive (TB 08-909) + Hardener (TB 08-930) + 12% Aluminium powder (TB 05-915) - Alodine (TB 13-002) - Wash-primer (TB 16-920) - Primer (TB 16-901) - Finish paint (per aircraft range) - Sealant (TB 09-001A) - Sealant (TB 09-002A) - Sealant (TB 09-013A) - Waterproof compound (TB 05-027) - Drills, dia. 0.13 in (3.3 mm) (No. 30), 0.15 in (3.7 mm) (No. 26), 0.16 in (4.1 mm) (No. 20) and 0.19 in (4.9 mm) (No. 10) - 100° micrometric countersink, with pilots dia. 1/8 in (3.2 mm), 0.157 in (4 mm) and 0.189 in (4.8 mm) ABAA Validity : S / N 1 - 9999 57_00_00 (CA) Page sEp80046 - Clamping pins, dia. 1/8 in (3.2 mm), 0.142 in (3.6 mm), 0.157 in (4 mm) and 0.189 in (4.8 mm) - Rivets - refer to Table 801 - Cleaning agent (TB 11-002) - Pneumatic vacuum cleaner - Clean lintfree cloths B. Repair of the spar 1) Once the area to be repaired has been opened, treat the corrosion - refer to 20-00-04. CAUTION : PREPARATION AND APPLICATION OF FILLER ALU (TB 05-911) MUST IMPERATIVELY BE CARRIED OUT BY QUALIFIED PERSONNEL. 2) Prepare Filler Alu (TB 05-911). 3) Using a spatula, apply Filler Alu (13) to the area to be repaired. 4) After complete curing, rework the area with abrasive cloth (TB 05-916C). 5) Fabricate a shim (2) or (8) of the same thickness as the skin and with dimensions smaller than the opening made by 0.039 in (1 mm). 6) Hold the shim centered in its housing and counterdrill the spar holes from inside the wing. 7) Fabricate a stiffener (3) or (9), 0.047 in (1.2 mm) thick. Determine the dimensions according to the indications below : a) The stiffener must imperatively be secured to the spar with six existing rivets on both sides of shim (2) or (8) - refer to Figures 803 and 804. NOTA : Should the repair area be too close to existing stiffener (1), fabricate a stiffener (11) or (15) including the shape of existing stiffener (1). In such a case, stiffener (11) or (15) shall be 0.063 in (1.6 mm) thick - refer to Figures 805 and 806. b) The stiffener must imperatively be secured to the skin with three rivets on both sides of shim (2) or (8), forward and aft of the spar. c) As a general rule, the pitch of the stiffener / skin attaching rivets must be 1.181 in (30 mm) in staggered rows, and the edge distance 0.394 in (10 mm). 中国通航网 www.ga.cn 通航翻译 www.aviation.cn 本文链接地址：TB20 MAINTENANCE MANUAL 57 机翼 TB20飞机维护手册(19) |
