63-05-03 SNOW: Amdt. 541 Part 507 Federal Register March 2, 1963. Applies to Model S-2 Aircraft Serial Numbers 1003 Through 1162.
Compliance required as indicated.
(a) Within 10 hours' time in service after the effective date of this AD, inspect the wing main spar upper and lower spar web flange for cracks in the vicinity of the wing-fuselage attach points (approximately wing Station 19), using at least a 10-power glass.
(b) If cracks are found, repair prior to further flight in accordance with Snow Service Letter No. 23 or FAA Engineering and Manufacturing Branch approved equivalent.
(c) If no cracks are found, repeat the inspection specified in (a) at intervals not to exceed 25 hours' time in service from the previous inspection.
(d) The repetitive inspection required by (c) may be discontinued when the modification set forth in Snow Service Letter No. 23 or an FAA Engineering and Manufacturing Branch approved equivalent is incorporated.
This directive effective March 8, 1963.