AD 2015-01-03 Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

Makes named: pilatus. Models named: PC-7. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Pilatus Aircraft Ltd. Model PC-7 airplanes, manufacturer serial numbers (MSN) 101 through MSN 618, certificated in any category.

Unless already done, within the next 12 months after March 2, 2015 (the effective date of this AD), perform a one-time conductivity test of items 6 through 9 and 11 through 13 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, to check the material of the parts—determine whether they are made of aluminum alloy AA2124-T851 or aluminum alloy AA2024-T351. Do not install any item unless it has been inspected following the applicable paragraph of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014. (1) For airplanes with any parts made of aluminum alloy AA2124-T851: Within 12 months after March 2, 2015 (the effective date of this AD), make an entry in the airplane logbook as required by paragraph 3.D.(3) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014. The only other actions of this AD that apply to airplanes with all parts made of aluminum alloy AA2124-T851 are the actions in paragraphs (f)(3), (f)(4), and (f)(5) of this AD. (2) For airplanes with any parts made of aluminum alloy AA2024-T351: Within 12 months after March 2, 2015 (the effective date of this AD), do the actions in paragraphs (f)(2)(i) through (f)(2)(iii) as applicable, including all subparagraphs: (i) For items 7 through 9 and 11 through 13 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after March 2, 2015 (the effective date of this AD), do a one-time inspection for cracks. If any cracks are found as a result of the inspection, before further flight, you must contact Pilatus Aircraft Ltd. to obtain FAA-approved repair instructions approved specifically for compliance with this AD and incorporate those instructions. Use the contact information found in paragraph (h) of this AD. (ii) For item 6 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after March 2, 2015 (the effective date of this AD), replace with a part made of aluminum alloy AA2124-T851. (iii) For Items 1, 2, 4, 5, and 10 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after March 2, 2015 (the effective date of this AD), do the following actions in paragraphs (f)(2)(iii)(A) and (f)(2)(iii)(B), as applicable. (A) For items 1, 2, 4, and 10 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, do a one-time inspection for cracks. If any cracks are found, before further flight, you must contact Pilatus Aircraft Ltd. to obtain FAA-approved repair instructions approved specifically for compliance with this AD and incorporate those instructions. Use the contact information found in paragraph (i)(3) of this AD. (B) For item 5 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, replace with a part made of aluminum alloy AA2124-T851. (3) For all airplanes: For item 3 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, within 12 months after March 2, 2015 (the effective date of this AD), replace elevator center control-rods withP/N 116.35.07.271 (item 3 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014), because the inspection for cracks on this type of control-rods is difficult. If elevator center control-rods P/N 116.35.07.345 (Item 3 as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014), are installed, these type of control rods will be inspected. (4) For all airplanes: As of 12 months after March 2, 2015 (the effective date of this AD), do not install the parts listed in items 1 and 2, 4, and 7 through 13 of paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, that are made of aluminum alloy AA2024-T351 unless they have been inspected and found free of cracks. (5) For all airplanes: As of 12 months after March 2, 2015 (the effective date of this AD), do not install the parts listed in items 3, 5, and 6 of paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014, that are made of aluminum alloy AA2024-T351.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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; email: doug.rudolph@faa.gov. 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, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as possible cracking from stress corrosion on various parts of the airplane structure made of aluminum alloy AA2024-T351. We are issuing this AD to detect and correct stress corrosion cracks that may occur on various parts of the airplane structure initially made of aluminum alloy AA2024-T351, which is susceptible to stress corrosion cracking (SCC). Such a condition, if left uncorrected, could lead to failure of critical parts on the airplane structure and weaken the structural integrity of the airplane.

None.