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NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant inspection - refer to 20-00-14. - tightening of the two nuts securing the rod to the rear fitting and the half-fittings, - tightening of the bolts securing the half-fittings to the fuselage, Rear fitting secured with blind rivets - loose rivets, Rear fitting secured with bolts and nuts - tightening of the bolts, S / N 735 - 1999 with option 0633 S / N 2000 - 9999 - installation of the fittings with sealant (TB 09-916). 7) Inspect the main landing gear bearings for : - evidence of impacts, cracks and corrosion, NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant inspection - refer to 20-00-14. - tightening of the attachment bolts. 8) Inspect the hinged strut bearing for : - evidence of impacts, cracks and corrosion, NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant inspection - refer to 20-00-14. - tightening of the attachment nuts on the spar, - tightening of the nuts on the spar flange, S / N 735 - 1999 with option 0633 S / N 2000 - 9999 - presence of sealant (TB 09-916) between the bearing and the spar. 9) Inspect the landing gear box for : - distortions, impacts, cracks and evidence of corrosion on N1, N2 and N3 ribs, - loose rivets, - tightening of the nuts securing N3 rib to the spar, - presence of the grommets and protection edgings in the clearing holes and on sharp edges, at wiring and brake hose passages, - security and correct routing of the wiring and the brake hose with clamps and tie-wraps, AAAA Validity : S / N 1 - 9999 57-00-00Page 604 (EA) JUN 02 - distortions, impacts, cracks, evidence of corrosion and loose rivets on the supports of the flaps control bellcrank, - evidence of impacts, corrosion and loose rivets of the spar flanges on upper and lower surface skins, S / N 1607, 1615 - 1626, 1628 - 9999 I - presence of a coat of sealant (TB 09-013A) or (TB 09-918) over the area, S / N 1 - 9999 - tightening of the upper and lower surface screws on the spar, on wing root side. 10) Inspect flap and aileron arm assemblies for : - distortions, impacts, cracks and evidence of corrosion, NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant inspection - refer to 20-00-14. Attachment with rivets - loose rivets, Attachment with bolts - tightening of the nuts, S / N 735 - 1999 with option 0633 S / N 2000 - 9999 - presence of sealant (TB 09-916) between the arm assembly and the rib. 11) Carefully inspect each box for : NOTE : Depending on accessibility, each box must be inspected either with a swivel mirror and a flashlight or with a borescope. 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(12) |
