Airworthiness Directive · Amendment 39-18064 · Standard practices/structures
PILATUS Aircraft Ltd. Airplanes
This AD applies to Pilatus Aircraft Ltd. Model PC-7 airplanes, manufacturer serial numbers (MSN) 101 through MSN 618, certificated in any category.
We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-7 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 require actions to address the unsafe condition on these products.
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 aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
