66-29-03 SIAI-MARCHETTI: Amdt. 39-313 Part 39 Federal Register November 23, 1966. Applies to Model S.205 Airplanes, Serial Numbers 101 through 222, 224, 228, 229, 231 through 233.
Compliance required as indicated.
To detect cracks on the rear spar web at areas adjacent to the aileron outboard hinge bracket bolts, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 90 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the rear spar web for cracks in accordance with Siai Service Bulletin No. 205B4, dated September 14, 1966. If cracks are detected during this inspection, comply with (b) of this AD before further flight.
(b) Modify the rear spar by incorporating a reinforcement as set forth in paragraph (b) of Siai Service Bulletin No. 205B4, dated September 14, 1966, or an FAA-approved equivalent.
(c) The repetitive inspections required by (a) of this AD may be discontinued after the rear spar is reinforced in accordance with (b) of this AD.
This directive effective November 23, 1966.