AD 2007-15-09 Airworthiness Directives; Pilatus Aircraft Limited Model PC-6 Series Airplanes

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

This AD applies to Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes; manufacturer serial numbers (MSN) 101 through 951, and MSN 2001 through 2092; that are certificated in any category. These airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.

Unless already done, do the following actions: (1) For MSN 2001 through MSN 2092: Within the next 100 hours time-in-service (TIS) on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 3 months after September 4, 2007 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD. (2) For MSN 101 through MSN 951 do the following actions, as applicable: (i) If the upper wing strut fitting has less than 3,500 hours TIS or has been installed for less than 84 months (7 years): Within the next 1,000 hours TIS on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 24 months after September 4, 2007 (the effective date of this AD) without exceeding 3,600 hours TIS or 87 months (7 years, 3 months), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD, or; (ii) If the upper wing strut fitting has 3,500 or more hours TIS or has been installed for 84 months (7 years) or longer: Within the next 100 hours TIS on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 3 months after September 4, 2007 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD. Note 1: If the TIS of the upper wing strut fittings cannot be positively determined by a review in the airplane maintenance records, then by default the upper wing strut fittings were installed from the date of original Certificate of Airworthiness. (3) Do the following at the times specified in paragraph (f)(1) or (f)(2) of this AD: (i) Perform a visual and non-destructive inspection of the upper wing strut fittings for cracks following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. (ii) Examine for conformity the spherical bearings following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. (4) If during any inspection required by paragraph (f)(3)(i) of this AD cracks are found in the upper wing strut fitting, before further flight replace the wing strut fitting with a new part number (P/N) 111.35.06.185 (left side) or P/N 111.35.06.186 (right side) following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. Replacement of the upper wing strut fitting does not terminate the repetitive inspection specified in paragraph (f)(3) of this AD. (5) If during any inspection required by paragraph (f)(3)(ii) of this AD the spherical bearing is found not in conformity, before further flight replace the bearing with a new P/N 944.61.00.109 following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. Replacement of the spherical bearing does not terminate the repetitive inspection specified in paragraph (f)(3) of this AD. (6) Report to Pilatus Aircraft Ltd. Customer Liason Manager results of the inspection/examination using Table 1 of Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) The FAA AD is requiring repetitive inspections and reporting results to the manufacturer, not just a one-time inspection and report as required in the MCAI. (2) The Service Bulletin specifies “subsequent inspections for cracks will be included in Chapter 5 of the Aircraft Maintenance Manual (AMM).” The only way we (FAA) can mandate these repetitive inspections is through an AD. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, 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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et. seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120 0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No: 2007-0114, dated May 02, 2007; and Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007, for related information. Material Incorporated by Reference (i) You must use Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007, 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; telephone: +41 (0)41 619 6580; fax: +41 (0)41 619 6576; e-mail: fodermatt@pilatus-aircaft.com. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on July 19, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-14428 Filed 7-27-07; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions: (1) For MSN 2001 through MSN 2092: Within the next 100 hours time-in-service (TIS) on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 3 months after September 4, 2007 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD. (2) For MSN 101 through MSN 951 do the following actions, as applicable: (i) If the upper wing strut fitting has less than 3,500 hours TIS or has been installed for less than 84 months (7 years): Within the next 1,000 hours TIS on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 24 months after September 4, 2007 (the effective date of this AD) without exceeding 3,600 hours TIS or 87 months (7 years, 3 months), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD, or; (ii) If the upper wing strut fitting has 3,500 or more hours TIS or has been installed for 84 months (7 years) or longer: Within the next 100 hours TIS on the upper wing strut fitting after September 4, 2007 (the effective date of this AD) or within 3 months after September 4, 2007 (the effective date of this AD), whichever occurs first, and repetitively thereafter at intervals not to exceed 12 months, do the actions specified in paragraph (f)(3) of this AD. Note 1: If the TIS of the upper wing strut fittings cannot be positively determined by a review in the airplane maintenance records, then by default the upper wing strut fittings were installed from the date of original Certificate of Airworthiness. (3) Do the following at the times specified in paragraph (f)(1) or (f)(2) of this AD: (i) Perform a visual and non-destructive inspection of the upper wing strut fittings for cracks following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. (ii) Examine for conformity the spherical bearings following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. (4) If during any inspection required by paragraph (f)(3)(i) of this AD cracks are found in the upper wing strut fitting, before further flight replace the wing strut fitting with a new part number (P/N) 111.35.06.185 (left side) or P/N 111.35.06.186 (right side) following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. Replacement of the upper wing strut fitting does not terminate the repetitive inspection specified in paragraph (f)(3) of this AD. (5) If during any inspection required by paragraph (f)(3)(ii) of this AD the spherical bearing is found not in conformity, before further flight replace the bearing with a new P/N 944.61.00.109 following the Accomplishment Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. Replacement of the spherical bearing does not terminate the repetitive inspection specified in paragraph (f)(3) of this AD. (6) Report to Pilatus Aircraft Ltd. Customer Liason Manager results of the inspection/examination using Table 1 of Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) The FAA AD is requiring repetitive inspections and reporting results to the manufacturer, not just a one-time inspection and report as required in the MCAI. (2) The Service Bulletin specifies “subsequent inspections for cracks will be included in Chapter 5 of the Aircraft Maintenance Manual (AMM).” The only way we (FAA) can mandate these repetitive inspections is through an AD. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, 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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et. seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120 0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No: 2007-0114, dated May 02, 2007; and Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007, for related information. Material Incorporated by Reference (i) You must use Pilatus Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007, 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; telephone: +41 (0)41 619 6580; fax: +41 (0)41 619 6576; e-mail: fodermatt@pilatus-aircaft.com. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or 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/cfr/ibr-locations.html. Issued in Kansas City, Missouri, on July 19, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-14428 Filed 7-27-07; 8:45 am] BILLING CODE 4910-13-P