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16 - Leading edge
17 - Wing root
— 10 mm 0.39 in
— 6 mm
0.23 in 200 mm
7.87 in
1 mm - 10 mm
0.39 in
0.039 in
- 30 mm 1.18 in 1,5 mm 0.06 in
15 Ecart detects par
controle visuel
16 Gap detected during
visual inspection
Ca Cs 0 0
0 0
0 Ca
— Profondeur corrosion
Corrosion depth
14572000AAAAYZ4200 — Ecart detects par courant de Foucault
Gap detected by Eddy current
Corrosion inspection (spar / skins interfaces) - Visual examination
Figure 607
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Validity : S / N 1 - 9999 57-00-00Page 614
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WINGS
REPAIR
NOTE : Apply a protection treatment - refer to 20-00-04, to all metal parts which have been bared during repair operations.
1. REPAIR - WRINKLED SKIN, LEADING EDGE BOX, WING ROOT AREA
A. Tools and consumable materials
- A rib P / N TB10 11016100 or a stiffener (2) - see Figure 802 for fabrication details
- A R.H. shim (3) - see Figure 802 for fabrication details
- A L.H. shim (4) - see Figure 802 for fabrication details
- 2 screws Z00.N5122683194 (15)
- 2 screws Z00.N5122683084 (10)
- 2 screws Z00.N5122683087 (13)
- 2 screws Z00.N5122683099 (14)
- 2 washers Z00.N5701039240 (16)
- 6 washers Z00.N5701039160 (11)
- 2 nuts Z00.N5401458239 (17)
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本文链接地址：TB20 MAINTENANCE MANUAL 57 机翼 TB20飞机维护手册(16)
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