68-19-02 SIAI-MARCHETTI: Amendment 39-654. Applies to Model S.205/22R airplanes, Serial Nos. 213, 370, 371, 372, 373, 374, 378, 379, 380, 381, 382, 384, 385, 386, 387, 388, 389, 390, 392, 393, 394, 395, 396, 398, 4-124, 4-125, 4-132, 4-142, 4-143, 4-145, 4-146, 4- 147, 4-148.
Compliance required as indicated, unless already accomplished.
To detect cracks in the lower part of fuselage frame No. 2, at the rudder control bellcrank brackets, and to detect cracks and deformation in the stringers of the fuselage belly skin which are located at the outboard rudder pedal support tube brackets, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD, visually inspect, using a lamp and mirror, the lower portion of fuselage frame No. 2 for cracks and the lower fuselage stringers for cracks and deformation in accordance with Siai Service Bulletin No. 205B20, dated March 22, 1968, or later RAI-approved revision or an FAA-approved equivalent. If no cracks are found, comply with paragraph (d) within the next 100 hours' time in service after the effective date of this AD.
(b) If cracks are found during the inspection required by paragraph (a) none of which exceed 3/16 inches in length, repeat that inspection at intervals not to exceed 20 hours' time in service from the last inspection and comply with paragraph (d) within the next 100 hours' time in service after the effective date of this AD. The repetitive inspection required in this paragraph may be discontinued upon compliance with paragraph (d).
(c) If cracks are found during the inspection required by paragraph (a) which exceed 3/16 inches in length, comply with paragraph (d) before the next flight.
(d) Modify fuselage frame No. 2 and stringers in accordance with Siai Service Bulletin No. 205B20, dated March 22, 1968, or later RAI-approved revision, or an FAA- approved equivalent.
This amendment becomes effective October 11, 1968.