2015-17-10: Landing gear

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 39-14945 (72 FR 7576, February 16, 2007), and adding the following new AD: 2015-17-10 SOCATA (type certificate previously held by EADS SOCATA): Amendment 39-18243; Docket No. FAA-2015-2047; Directorate Identifier 2015-CE-013-AD. (a) Effective Date This AD becomes effective September 29, 2015. (b) Affected ADs This AD supersedes AD 2007-04-13, Amendment 39-14945, (72 FR 7576, February 16, 2007) (``AD 2007-04-13''). (c) Applicability This AD applies to SOCATA Model TBM 700 airplanes, serial numbers 1 through 638 and 687, that: (1) are not equipped with a left-hand main landing gear (MLG) body part number (P/N) D68161 or D68161-1 and a right-hand MLG body P/N D68162 or D68162-1; and (2) are certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 32: Landing gear. (e) Reason This AD was prompted from 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 cracks found on the main landing gear cylinders. In addition, the FAA determined that airplanes with MLG with forging body that had not reached 1,750 landings as of March 23, 2007 (the effective date of AD 2007-04-13) were not affected by AD 2007-04-13. This is not the intent and allows airplanes to fly indefinitely with the unsafe condition. This AD increases the scope of the affected airplanes by including those airplanes with MLG with forging body either at or under 1,750 landings as of March 23, 2007, increases the time between the repetitive inspections, and incorporates a modification to terminate the required repetitive inspections. We are issuing this AD to detect and correct cracks in the shock strut cylinder of the MLG, which could cause the MLG to fail. Failure of the shock strut cylinder of the MLG could result in a collapsed MLG during takeoff or landing and possible reduced structural integrity of the airplane. (f) Actions and Compliance for Airplanes Not Previously Affected by AD 2007-04-13 Unless already done, do the actions in paragraphs (f)(1), (f)(2), and (h) of this AD: (1) For MLG with forging body that were either at or under 1,750 landings as of March 23, 2007 (the effective date of (AD 2007-04- 13): Upon or before accumulating 1,750 landings on the MLG with forging body since new or within the next 100 landings after September 29, 2015 (the effective date of this AD), whichever occurs later, inspect the forging body for cracks. Do the inspection following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014. (2) If no cracks are detected during the inspection required in paragraph (f)(1) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed. (g) Actions and Compliance for Airplanes Previously Affected by AD 2007-04-13 Unless already done, do the actions in paragraphs (g)(1), (g)(2), and (h) of this AD, including all subparagraphs: (1) As of March 23, 2007 (the effective date retained from AD 2007-04-13), for MLG with forging body totaling more than 1,750 landings but less than 3,501 landings since new: (i) Inspect the forging body for cracks within 100 landings after March 23, 2007 (the effective date retained from AD 2007-04- 13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014. (ii) If no cracks are detected during the inspection required in paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed. (2) As of March 23, 2007 (the effective date retained from AD 2007-04-13), for MLG with forging body totaling more than 3,500 landings since new: (i) Inspect the forging body for cracks within25 landings after March 23, 2007 (the effective date retained from AD 2007-04-13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014. (ii) If no cracks are detected during the inspection required in paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014, is installed. (h) Actions and Compliance for All Affected Airplanes If any cracks are detected during any inspection required in paragraphs (f)(1) through (g)(2) of this AD, including all subparagraphs: (1) Before further flight, remove the affected landing gear leg and confirm the presence of the crack with dye penetrant inspection or fluorescent penetrant inspection. (2) If the crack is confirmed, before further flight, contact SOCATA at the address in paragraph (l)(5) of this AD to coordinate the FAA-approved landing gear repair/replacement and implement any FAA-approved repair/replacement instructions obtained from SOCATA, or replace the cracked landing gear with a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, dated December 2014. This replacement terminates the repetitive inspections required by this AD. (i) Calculating Unknown Number of Landings for Compliance The compliance times of this AD are presented in landings instead of hours time-in-service (TIS). If the number of landings is unknown, hours TIS may be used by dividing the number of hours TIS by 1.35. (j) 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: Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: albert.mercado@faa.gov. 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. (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 productis airworthy before it is returned to service. [[Page 51459]] (k) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2006-0085R2, dated January 16, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002. (l) 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. (3) The following service information was approved for IBR on September 29, 2015. (i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70- 130, Revision 3, dated December 2014. (ii) Reserved. (4) The following service information was approved for IBR on March 23, 2007 (72 FR 7576, February 16, 2007). (i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70- 130, dated January 2006. (ii) Reserved. (5) For SOCATA service information identified in this AD, contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, telephone: (954) 893-1400; fax: (954) 964-4141; Internet: http://www.socata.com. (6) 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. In addition, you can access this service information on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2047. (7) 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.