2014-22-01: Time Limits

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Amendment 39-17311 (78 FR 11572, February 19, 2013), and adding the following new AD: 2014-22-01 PILATUS AIRCRAFT LTD.: Amendment 39-18005; Docket No. FAA-2014-0594; Directorate Identifier 2014-CE-022-AD. (a) Effective Date This airworthiness directive (AD) becomes effective December 18, 2014. (b) Affected ADs This AD supersedes AD 2012-26-16, Amendment 39-17311 (78 FR 11572, February 19, 2013). (c) Applicability 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. (d) Subject Air Transport Association of America (ATA) Code 5: Time Limits. (e) Reason 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. (f) Actions and 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 ANDMISCELLANEOUS--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. (g) Other FAA AD Provisions 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, [[Page 67346]] 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 DistrictOffice (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. (h) Special Flight Permit Special flight permits are prohibited. (i) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2014-0170, dated July 17, 2014, for related information. The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2014-0594-0003. (j) Material Incorporated by Reference (1) The Director of the FederalRegister approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) 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. (ii) 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. Note to paragraph (j)(2) of this AD: 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; 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, were issued as complete updates to the AMM Airworthiness Limitations sections. (3) For Pilatus Aircraft LTD. service information identified in this AD, contact PILATUS AIRCRAFT LTD., Customer Service Manager, CH-6371 STANS, Switzerland; telephone: +41 (0) 41 619 33 33; fax: +41 (0) 41 619 73 11; Internet: http://www.pilatus-aircraft.com or email: aircraft.com">SupportPC12@pilatus-aircraft.com. (4) You may view this service information at FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.