2016-26-08: 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 39-18005 (79 FR 67343, November 13, 2014) and adding the following new AD: 2016-26-08 PILATUS AIRCRAFT LTD.: Amendment 39-18766; Docket No. FAA-2016-7003; Directorate Identifier 2016-CE-015-AD. (a) Effective Date This airworthiness directive (AD) becomes effective February 9, 2017. (b) Affected ADs This AD replaces AD 2014-22-01, 39-18005 (79 FR 67343, November 13, 2014). (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 main landing gear (MLG) attachment bolts. 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 (6) of this AD: (1) Before further flight after February 9, 2017 (the effective date of this AD), insert the following revisions into the Limitations section of the FAA-approved maintenance program (e.g., maintenance manual). Compliance with an electronic version of the Limitations section is acceptable provided the specifically referenced sections are followed even though there may be differences with the pagination: (i) STRUCTURAL, COMPONENT AND MISCELLANEOUS--AIRWORTHINESS LIMITATIONS, Data module code 12-A-04-00-00-00A-000A-A, dated July 12, 2016, of the Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN- 101-888, Aircraft Maintenance Manual (AMM), Document No. 02049, 12- A-AM-00-00-00-I, revision 32, dated July 18, 2016; and (ii) STRUCTURAL AND COMPONENT LIMITATIONS--AIRWORTHINESS LIMITATIONS, Data module code 12-B-04-00-00-00A-000A-A, dated July 19, 2016, 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 15, dated July 30, 2016. (2) The new limitations section revisions listed in paragraphs (f)(1)(i) and (ii) of this AD specify the following: (i) Establish inspections of the MLG attachment bolts, (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. (3) Only authorized Pilatus Service Centers can do the Supplemental Structural Inspection Document (SSID) as required by [[Page 1175]] the documents in paragraphs (f)(1)(i) and (ii) of this AD because deviations from the type design in critical locations could make the airplane ineligible for this life extension. (4) If no compliance time is specified in the documents listed in paragraphs (f)(1)(i) and (ii) of this AD when doing any corrective actions where discrepancies are found as required in paragraph (f)(2)(iii) of this AD, do these corrective actions before further flight after doing the applicable maintenance task. (5) During the accomplishment of the actions required in paragraph (f)(2) of this AD, including all subparagraphs, if a discrepancyis found that is not identified in the documents listed in paragraphs (f)(1)(i) and (ii) of this AD, before further flight after finding the discrepancy, contact PILATUS AIRCRAFT LTD. at the address specified in paragraph (h) of this AD for a repair scheme and incorporate that repair scheme. (6) Before or upon accumulating 6 years time-in-service (TIS) on the MLG attachment bolts or within the next 3 months TIS after February 9, 2017 (the effective date of this AD), whichever occurs later, inspect the MLG attachment bolts for cracks and corrosion and before further flight 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 ATTN: 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 2014-22-01, 39-18005 (79 FR 67343, November 13, 2014) 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) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2016-0083, dated April 28, 2016, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov/document?D=FAA-2016-7003-0002. (i) Material Incorporated by Reference (1) The Director of the Federal Register 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) STRUCTURAL, COMPONENT AND MISCELLANEOUS--AIRWORTHINESS LIMITATIONS, Data module code 12-A-04-00-00-00A-000A-A, dated July 12, 2016, of the Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN- 101-888, Aircraft Maintenance Manual (AMM), Document No. 02049, 12- A-AM-00-00-00-I, revision 32, dated July 18, 2016. (ii) STRUCTURAL AND COMPONENT LIMITATIONS--AIRWORTHINESS LIMITATIONS, Data module code 12-B-04-00-00-00A-000A-A, dated July 19, 2016, 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 15, dated July 30, 2016. (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, 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. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-7003. (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.