Airworthiness directives › 2014-22-01
AD 2014-22-01 Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes
Makes named: pilatus. Models named: PC-12, PC-12/45, PC-12/47, PC-12/47E. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
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.
Required actions
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 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. (i) 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. (ii) AMOCs approved for AD 2012-26-16, Amendment 39-17311 (77 FR 11572, February 19, 2013) are not approved as AMOCs for this AD. (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.
Unsafe condition
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 a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). The limitations were revised to include repetitive inspections of the inboard flap drive arms for crack(s). These actions are required to ensure the continued operational safety of the affected airplanes.
Affected ADs
This AD supersedes AD 2012-26-16, Amendment 39-17311 (78 FR 11572, February 19, 2013).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1