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24-00 4) Visually inspect all cable connections in the L.H. wing. 500
Replace cables if damaged. Inspect cables for routing, clamp security, lugs and cleanliness.
27-10 5) Visually inspect the visible portions of L.H. aileron rods. 500
27-50 6) Visually inspect (do not remove) the L.H. flap control rods. 500
27-50 7) Remove and clean the L.H. flap control bellcrancks. 500 1000 hrs
Perform a detail examination. Lubricate. Install.
27-50 8) Visually inspect (do not remove) the flap control linkage for security of attach fittings, play, evidence of wear, interference and corrosion - refer to 27-50-01 201. 000 1000 hrs
28-10 9) Perform an operational test of the L.H. fuel tank cap and check the seal condition - refer to 28-10-00 301. 500
28-10 10) Visually inspect the L.H. fuel tank air vent pipes for condition, security and obstruction. 500
30-10 11) Visually inspect the porous leading edges (if installed) on the L.H. wing. 500 NOTE 1
57-10 12) Visually inspect all the wing splices, check for cracks and evidence of corrosion on the splices ; make sure the nuts have not rotated, in case of doubt, torque the nuts - refer to 20-00-01 201. 000
57-00 13) Visually inspect the wing structure for corrosion - refer to 57-00-00 201. 000 2000 hrs or
5 years
NOTE : For salty or highly humid operating
atmospheres, the inspection shall be
performed every 2000 hours or 3 years. NOTE
NOTE 1 : If a 100-hr. inspection has been carried out during the last 3 months, do not perform this operation unless this annual inspection replaces a 100-hr. inspection. For US registered aircraft, perform all operations.
ADAA
Validity : S / N 1 - 9999 05 20 06Page 215
(EA) JUN 01
ATA ANNUAL INSPECTION (AI)
L.H. WING INSPECTION (AREA 500) AREA OTHER
INSPECTION PERFORMED
BY
57-00 14) Thoroughly examine the spar flanges/skin junction from root to N4 rib for corrosion - refer to 57-00-00 201.
NOTE : If PR is applied between (upper and lower surface) skin and spar for repair, do the inspection at 10000 hrs or 10 years. 000
4 years 4000 hrs or
8 years,
then
2000 hrs or
NOTE
57-10 15) Check the pins of the L.H. wing-to-fuselage front, main and rear attachments ; make sure the nuts have not rotated, in case of doubt, torque the nuts - refer
to 20-00-01 201. 500
57-20 16) Visually inspect the L.H. main-landing-gear attachment area for loose rivets, distortion, cracks and evidence of corrosion. 500 NOTE 1
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