AD 71-17-04 R1

71-17-04 R1 SIAI-MARCHETTI: Amendment 39-1266 as amended by Amendment 39-4516. Applies to Models S.205-18/F, S.205-18/R, S.205-20/F, S.205-20/R, S.205-22/R, S.208, and S.208A airplanes (all serial numbers) certificated in any category.

COMPLIANCE: Required as indicated unless already accomplished.

To prevent failure of the main landing gear, accomplish the following:

(a) Before further flight, unless already accomplished within the last 50 hours time- in-service, and thereafter at intervals not to exceed 100 hours time-in-service from the last check, visually check, using a magnifying glass of at least 5 power, the main landing gear wheel axle-to- strut-tube fittings for cracks in accordance with "INSTRUCTIONS" paragraph (a), SIAI- Marchetti Service Bulletin No. 205B27A, dated October 7, 1977. If cracks are found, comply with paragraph (c) or (d) as appropriate. The checks required by this paragraph may be performed by the pilot, who must make the prescribed maintenance record entry indicating compliance with paragraph (a) of this AD.

(b) Within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished within the last 450 hours time-in-service and thereafter at intervals not to exceed 500 hours time-in-service from last inspection, inspect the main gear wheel axle-to- strut-tube fittings for cracks, using a dye penetrant method, in accordance with "INSTRUCTIONS" paragraph (b), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977. If cracks are found, comply with paragraph (c) or (d) as appropriate.

(c) If cracks which do not extend to the lateral external surface of a fitting are found during a check required by paragraph (a) or during an inspection required by paragraph (b), within the next 50 hours time-in-service, and thereafter at intervals not to exceed 50 hours time- in-service from the last inspection, inspect the main landing gear wheel axle-to-strut tube fittings for cracks, using a dye penetrant method in accordance with "INSTRUCTIONS" paragraph (b), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977.

(d) If cracks are found on the lateral external area of a fitting during a check required by paragraph (a), or during an inspection required by paragraph (b) or (c), before further flight replace the cracked part with a new part of the same part number, in accordance with "INSTRUCTIONS" paragraph (d.1), SIAI-Marchetti Service Bulletin No. 205B27A, dated October 7, 1977, or FAA approved equivalent, and continue to check in accordance with paragraph (a) and continue to inspect in accordance with paragraph (b).

(e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.

Amendment 39-1266 became effective upon publication in the Federal Register to all persons except those persons to whom it was made immediately effective upon receipt of the airmail letter dated July 16, 1971, which contained this amendment.

This Amendment 39-4516 becomes effective December 27, 1982.