Airworthiness Directive · Amendment 39-15138 · Wings
Pilatus Aircraft Limited Model PC-6 Series Airplanes
Superseded. A later AD replaced this one: AD 2007-19-14. Comply with the one in force.
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.
We are adopting a new airworthiness directive (AD) for the products listed above. 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:
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.
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.
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.
