Airworthiness Directive · Amendment 39-18005 · Time limits
PILATUS AIRCRAFT LTD. Airplanes
Superseded. A later AD replaced this one: AD 2016-26-08. Comply with the one in force.
This AD applies to PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes, all manufacturer serial numbers (MSNs), certificated in any category.
We are superseding Airworthiness Directive (AD) 2012-26-16 for all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/ 47E 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 a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). We are issuing this AD to require actions to address the unsafe condition on these products.
Unless already done, do the actions in paragraphs (f)(1) through (f)(5) of this AD:
(1) Before further flight after December 18, 2014 (the effective date of this AD), insert Data module code 12-A-04-00-00-00A-000A-A, “STRUCTURAL, COMPONENT AND MISCELLANEOUS—AIRWORTHINESS LIMITATIONS,” dated March 13, 2014, of the Pilatus Model type—PC-12, PC-12/45, PC-12/47, Aircraft Maintenance Manual (AMM), Document No. 02049, 12-A-AM-00-00-00-I, revision 28, dated May 31, 2014, for Models PC-12, PC-12/45, PC-12/47, and Data module code 12-B-04-00-00-00A-000A-A, “STRUCTURAL AND COMPONENT LIMITATIONS—AIRWORTHINESS LIMITATIONS,” dated March 13, 2014, of the Pilatus Model type—PC-12/47E MSN-1001-UP, Aircraft Maintenance Manual (AMM), Document No. 02300, 12- B-AM-00-00-00-I, revision 11, dated May 31, 2014, for Model PC-12/47E, into the Limitations section of the FAA-approved maintenance program (e.g., maintenance manual). These limitations section revisions do the following:
(i) Establish an inspection of the inboard flap drive arms,
(ii) Specify replacement of components before or upon reaching the applicable life limit, and
(iii) Specify accomplishment of all applicable maintenance tasks within certain thresholds and intervals.
(2) Only authorized Pilatus Service Centers can do the Supplemental Structural Inspection Document (SSID) as required by the documents in paragraph (f)(1) of this AD because deviations from the type design in critical locations could make the airplane ineligible for this life extension.
(3) If no compliance time is specified in the documents listed in paragraph (f)(1) of this AD when doing any corrective actions where discrepancies are found as required in paragraph (f)(1)(iii) of this AD, do these corrective actions before further flight after doing the applicable maintenance task.
(4) During the accomplishment of the actions required in paragraphs (f)(1)(i), (f)(1)(ii), and (f)(1)(iii) of this AD, if a discrepancy is found that is not identified in the documents listed in paragraph (f)(1) of this AD, before further flight after finding the discrepancy, contact PILATUS AIRCRAFT LTD. at the address specified in paragraph (i) of this AD for a repair scheme and incorporate that repair scheme.
(5) Within the next 3 months after December 18, 2014 (the effective date of this AD) or within the next 150 hours TIS after December 18, 2014 (the effective date of this AD), whichever occurs first, inspect the inboard flap drive arms for cracks and take all necessary corrective actions.
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.
