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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 and/or 0.047 in (1 and/or 1.2 mm) (for shim and stiffener) - Alodine (TB 13-002) - Primer (TB 16-901) - Finish paint (per aircraft range) - Sealant (TB 09-001A) - Sealant (TB 09-002A) - Waterproof compound (TB 05-027) - Drill, dia. 0.13 in (3.3 mm) (No. 30) - 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm) - Clamping pins, dia. 1/8 in (3.2 mm) - Rivets, P / N 5595 7 32 001 - Cleaning agent (TB 11-002) - Pneumatic vacuum cleaner - Clean linffree cloths B. Procedure 1) Fabricate a shim (17), dia. 0.75 in (19 mm), and a stiffener (16), dia. 2.05 in (52 mm), of the same thickness as the skin. 2) Mark then, using a drill, dia. 0.13 in (3.3 mm) (No. 30), drill the holes in stiffener (16) - refer to Figure 806, Section BB. NOTE : Depending on the position of stiffener (16) with respect to the existing rivets, adapt stiffener drilling with a minimum pitch of 0.787 in (20 mm). 3) If the axis of the core sample was a rivet, drill the center of shim (17) and stiffener (16) to diameter 0.13 in (3.3 mm) (No. 30) - refer to Detail D. 4) Position and center stiffener (16) on the core sample area, then turn it correctly to obtain a regular pitch between the existing rivets and the holes in the stiffener. 5) Counterdrill the skin and the spar to diameter 0.13 in (3.3 mm) (No. 30). Secure with pins as you progress. 6) Remove stiffener (16). Deburr the holes and vacuum-clean the chips. 7) Using a 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm), countersink the holes in stiffener (16). ABAA Validity : S / N 1 - 9999 57-00-00Page 805 (CA) JUN 02 8) Apply a protection to stiffener (16) and shim (17) - refer to Table 801. 9) Using a cloth moistened with cleaning agent (TB 11-002), clean the spar and the skin around the aperture. 10) Protect the edge of the skin with Alodine (TB 13-002). 11) Smear shim (17) and stiffener (16) with a coat of sealant (TB 09-001A) and position them. 12) Cut the rivets to length (refer to Table 801) and install them wet with sealant (TB 09-001A). 13) Apply a bead of sealant (TB 09-002A) to the periphery of stiffener (16). 14) Smear the rivet shanks with sealant (TB 09-001A). 15) Perform paint touch-ups on the rivet heads and the sealant bead. 16) Protect the spar flanges / skins junctions with waterproof compound (TB 05-027). 3. PRINCIPLE OF CORROSION REPAIR ON THE SPAR, FROM N1 RIB TO N4 RIB (Table 801, Figures 803, 804, 805 and 806) NOTE : If the repair area is located between N1 and N2 ribs, install an additional door on the wing 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(18) |
