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2. VISUAL INSPECTION All components likely to interfere are removed (cowlings, doors, etc...). The inspection is carried out : - On the damaged area. - On surrounding areas, since a major impact having entailed damage to part of the structure may have consequential effects (transmitted through the structure itself) on adjacent components. - On attachments of main components which will be inspected thoroughly. 3. MEASUREMENTS - TRIANGULATION - LEVELING The purpose of complete measurements is to evidence the structural distorsions which are not detected during visual inspection. Measurement dimensions, triangulation and leveling points - see 51-50-01. For location dimensions and deflection angles, refer to corresponding chapters of this manual. In case the measurements show differences out of tolerances with respect to original sizes, the aircraft should be inspected by manufacturer specialists who will decide the necessity and place of repair (Flying Club, Service-Station, Manufacturer or scrap). WA Validity : All 51-50-00Page 1 (BA) SEP 91 PAGE INTENTIONALLY LEFT BLANK WA Validity : All 51-50-00Page 2 (BA) SEP 91 ALIGNMENT AND SYMMETRY INSPECTION / CHECK 1. ALIGNMENT AND SYMMETRY CHECKS (Figures 601 and 602 and Tables 601 and 602) A. Tools and consumable materials - Steel tape decameter - Plumb line - Adhesive tape - Transit - Graduated sighting ruler B. Location of check points - Point (a) : Punch mark located at 0.08 in or 0.12 in (2 or 3 mm) below metal sheets junction, 0.24 in (6 mm) behind firewall and 4.72 in (120 mm) under RHF, R.H. side. - Point (b) : Punch mark located at 0.08 in or 0.12 in (2 or 3 mm) below metal sheets junction, 0.24 in (6 mm) behind firewall and 4.72 in (120 mm) under RHF, L.H. side. - Point (e) : Punch mark located at about 1.97 in (50 mm) above metal sheets junction, 0.24 in (6 mm) forward of frame C9 and 4.72 in (120 mm) under RHF, L.H. side. - Point (f) : Punch mark located at about 1.97 in (50 mm) above metal sheets junction, 0.24 in (6 mm) forward of frame C9 and 4.72 in (120 mm) under RHF, R.H. side. NOTE : A yellow arrow, located under points a, b, e and f, allows easier location. - Point (g) : Last rivet attaching skin under R.H. wing spar. - Point (h) : Last rivet attaching skin under L.H. wing spar. - Point (j) : Rivet attaching horizontal stabilizer skin and stabilizer tip by the spar, R.H. side. - Point (k) : Rivet attaching horizontal stabilizer skin and stabilizer tip by the spar, L.H. side. - Point (m) : Trailing edge upper angle of rudder. - Point (o) : Rivet located at about 2.36 in (60 mm) from R.H. wing leading edge attaching skin and end rib. - Point (p) : Rivet located at about 2.36 in (60 mm) from L.H. wing leading edge attaching skin and end rib. 中国通航网 www.ga.cn 通航翻译 www.aviation.cn 本文链接地址：TB20 MAINTENANCE MANUAL 51 标准施工/结构 TB20飞机维护手册(20) |
