AD 2009-24-03 Airworthiness Directives; Vulcanair S.p.A. Models P 68, P 68B, P 68C, P 68C-TC, and P 68 “OBSERVER” Airplanes

Makes named: vulcanair. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Models P 68, P 68B, P 68C, P 68C-TC, and P 68 “OBSERVER” airplanes, serial numbers 001 through 356, that are certificated in any category.

For airplane serial numbers 001 through 328, to address this problem, you must do the following, unless already done:   Actions Compliance Procedures (1) Visually inspect the front and rear wing spars for cracks Initially inspect within the next 100 hours time-in-service (TIS) after May 17, 1985 (the effective date of AD 85-08-04), or upon reaching 2,100 hours total TIS, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 500 hours TIS Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985; or Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 1, dated September 27, 1984. (2) Repair all cracks found and modify the front and rear wing spars Before further flight after any inspection specified in paragraph (e)(1) of this AD where cracks are found. Modification of the front and rear wing spar terminates the repetitive inspection requirements of this AD Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985; or Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 1, dated September 27, 1984. (3) To terminate the repetitive inspection requirements of this AD, you may modify the front and rear wing spar Before further flight after any inspection specified in paragraph (e)(1) of this AD where cracks are not found Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985; or Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 1, dated September 27, 1984. (f) For airplane serial numbers 329 through 356, to address this problem, you must do the following, unless already done:   Actions Compliance Procedures (1) Visually inspect the front and rear wing spars for cracks Initially within the next 100 hours TIS after January 4, 2010 (the effective date of this AD), or upon reaching 2,100 total hours TIS, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 500 hours TIS Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985. (2) Repair all cracks found and modify the front and rear wing spars Before further flight after any inspection specified in paragraph (f)(1) of this AD where cracks are found. Modification of the front and rear wing spar terminates the repetitive inspection requirements of this AD Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985. (3) To terminate the repetitive inspection requirements of this AD, you may modify the front and rear wing spar Before further flight after any inspection specified in paragraph (e)(1) of this AD where cracks are not found Follow Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985. Alternative Methods of Compliance (AMOCs) (g) The Manager, Small Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Sarjapur Nagarajan, Aerospace Engineer, ACE-112, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (h) AMOCs approved for AD 85-08-04 are approved for this AD. Related Information (i) To get copies of the service information referenced in this AD, contact Vulcanair S.p.A, Via G. Pascoli, 7, Casoria (Naples) 80026 Italy; telephone: (+39)081.5918111; fax: (+39)081.5918172; e-mail: customerservice@vulcanair.com; Internet: http://www.vulcanair.com. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http://www.regulations.gov. Material Incorporated by Reference (j) You must use Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 3, dated September 30, 1985; or Partenavia Costruzioni Aeronautiche S.p.A Service Bulletin No. 65 Rev. 1, dated September 27, 1984, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Vulcanair S.p.A, Via G. Pascoli, 7, Casoria (Naples) 80026 Italy; telephone: (+39)081.5918111; fax: (+39)081.5918172; e-mail: customerservice@vulcanair.com; Internet: http://www.vulcanair.com. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329-3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on November 13, 2009. Margaret Kline, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-28074 Filed 11-25-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks in the front and rear wing spars. We are issuing this AD to detect and correct cracks in the front and rear wing spars, which could result in the wing separating from the airplane. This failure could lead to loss of control.