2014-23-08: 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 Airworthiness Directive (AD) 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), and adding the following new AD: 2014-23-08 Airbus: Amendment 39-18024. Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-180-AD. (a) Effective Date This AD becomes effective December 31, 2014. (b) Affected ADs This AD replaces AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012). (c) Applicability This AD applies to Airbus Model A330-201, -202, -203, -223, - 223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers. [[Page 70461]] (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of a cracked nose landing gear (NLG) main fitting and sliding tube during NLG overhaul. We are issuing this AD to detect and correct cracks, defects, or damage of the main fitting or sliding tube, which could result in consequent NLG collapse. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Detailed Inspection and Corrective Actions This paragraph restates the requirements of paragraph (g) of AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with revised service information. For Model A330-201, -202, -203, -223, - 243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311,-312, and -313 airplanes; if fitted with the NLG identified in table 1 to paragraph (g) of this AD: Within 900 flight hours after April 30, 2012 (the effective date of AD 2012-06-19), do a detailed inspection of the NLG main fitting and sliding tube for any cracks, defects, and damage of the paint or surface protection, including paint removal and cracking of the surface treatment. Before further flight after doing the detailed inspection of the NLG, remove the labels, paint, surface protection coatings, and cadmium from the NLG main fitting; do a detailed inspection for any damage to the surface that will impair the magnetic particle inspection (MPI); and, if any defects are found, before further flight, remove any defects by polishing. Do all actions specified in this paragraph in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD. (1) For Model A330 airplanes: Airbus Mandatory Service Bulletin A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014. (2) For Model A340 airplanes: Airbus Mandatory Service Bulletin A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013. Table 1 to Paragraph (g) of This AD--Applicable NLG and Serial Numbers ------------------------------------------------------------------------ Part No. Serial No. ------------------------------------------------------------------------ D23285200.................................................. B2 D23285101-7................................................ B58 D23285101-10............................................... B75 D23581100-1................................................ B124 D23581100-1................................................ B159 D23581100-7................................................ B386 D23581100-7................................................ B398 D23581100-7................................................ B400 D23581100-7................................................ B403 ------------------------------------------------------------------------ (h) Retained Magnetic Particle Inspection This paragraph restates the requirements of paragraph (h) of AD 2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with revised service information. Before further flight after doing the actions required in paragraph (g) of this AD: Do an MPI for cracking of the NLG main fitting and sliding tube, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD. (1) If no crack is detected during the MPI required by the introductory text of paragraph (h) of this AD: Before further flight, flap peen the inspected area where the paint and cadmium has been removed, and replace the protective coatings, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD. (2) If any crack is detected during the MPI required by the introductory text of paragraph (h) of this AD: Before further flight, replace the damaged part with a new or serviceable part, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(1) or (g)(2) of this AD. (i) New Identification of Part and Serial Numbers Within 1,000 flight hours after the effective date of this AD, identify the part number and serial number of the NLG main fitting and NLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix01, dated July 5, 2013; as applicable. A review of airplane maintenance records is acceptable in lieu of this identification if the part number and the serial number of the NLG main fitting and NLG sliding tube can be conclusively determined from that review. (j) New Magnetic Particle Inspection If, during the identification required by paragraph (i) of this AD, it is determined any NLG main fitting or NLG sliding tube is installed and the fitting or tube has a part number and serial number listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable: Within 1,000 flight hours after the effective date of this AD, do an MPI for cracks of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. Accomplishing the MPI required by this paragraph terminates the inspections required by paragraphs (g) and (h) of this AD. (1) If any crack is detected during the MPI required by the introductory text of paragraph (j) of this AD: Before further flight, replace any cracked part (NLG main fitting and NLG sliding tube) with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (2) If no crack is detected during the MPI required by the introductory text of paragraph (j) of this AD: Before further flight, do a flap peening to introduce compressive residual stress and corrosion protection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (k) New Detailed Inspection Within 900 flight hours after doing the flap peening required by paragraph (j)(2) of this AD, do a detailed inspection for damage to paint, damage to the sealant around the labels, damage to the cadmium or base metal, and for cracking of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. Repeat the inspection thereafter at intervals not to exceed 900 flight hours. (1) If any damage to the paint, damage to the sealant around the labels, or damage to the cadmium or base metal, is detected during any detailed inspection required bythe introductory text of paragraph (k) of this AD; Before further flight, do an MPI for cracking of the affected parts, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (2) If any cracking is detected during any inspection required by the introductory text of paragraph (k) or paragraph (k)(1) of this AD: Before further flight, replace any cracked part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (l) Terminating Action Replacement of a part as required by paragraph (j)(1) or (k)(2) of this AD is terminating action for therepetitive detailed [[Page 70462]] inspections required by paragraph (k) of this AD for that part, provided that the part number and serial number of the replacement part is not listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (m) Parts Installation Limitation As of the effective date of this AD, installation of an NLG main fitting or NLG sliding tube having a part number and serial number listed in Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable; is allowed, provided that the NLG main fitting and NLG sliding tube have not accumulated more than 900 flight hours since the most recent inspection accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013; as applicable. (n) Credit for Previous Actions This paragraph provides credit for inspections required by paragraphs (j) and (k) of this AD and the flap peening required by paragraph (j)(2) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (n)(1), (n)(2), or (n)(3) of this AD. (1) Airbus Service Bulletin A330-32-3233, dated October 22, 2009. (2) Airbus Service Bulletin A330-32-3233, Revision 01, dated July 5, 2013. This document is not incorporated by reference in this AD. (3) Airbus Service Bulletin A340-32-4275, dated October 22, 2009. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance(AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date ofthis AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013- 0179, dated August 7, 2013, for related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0425-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD. (q) Material Incorporated by Reference (1) The Director of theFederal 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 this AD specifies otherwise. (3) The following service information was approved for IBR on December 31, 2014. (i) Airbus Service Bulletin A330-32-3233, Revision 02, including Appendix 01, dated January 27, 2014. (ii) Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 5, 2013. (4) The following service information was approved for IBR on April 30, 2012, (77 FR 22188, April 13, 2012). (i) Airbus Service Bulletin A330-32-3233, dated October 22, 2009. (ii) Airbus Service Bulletin A340-32-4275, dated October 22, 2009. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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.