2015-23-05: Fuselage

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 adding the following new airworthiness directive (AD): 2015-23-05 Airbus: Amendment 39-18321. Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-AD. (a) Effective Date This AD becomes effective December 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and - 243F airplanes. [[Page 72572]] (2) Airbus Model A330-301, -302, -303, -321, -322,-323, -341, - 342, and -343 airplanes. (3) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts and which would make the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Strut Types For the purpose of this AD, a Societ[eacute] Anonyme de Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut is a strut on which the diameter of the strut end is less than 43 millimeters. All other struts are Technical Airborne Components Industries (TAC) struts. (h) Repetitive Inspections of TAC Strut Ends At the applicable time specified in paragraph (i) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of all TAC strut ends of the THS support located at frame (FR) 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 42 months or 20,000 flight hours, whichever occurs first. For airplanes on which Airbus Modification 203493 or 203834 has been embodied in production, or Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin A340-53-4199, as applicable, has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by this paragraph. (i) ComplianceTimes for the Actions Required by Paragraphs (h) and (k) of This AD Do the inspections required by paragraphs (h) and (k) of this AD at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) For Model A330 series airplanes having manufacturer serial numbers 012 through 209 inclusive, and Model A340 series airplanes having manufacturer serial numbers 002 through 210 inclusive: Within 6 months after the effective date of this AD. (2) For Model A330 series airplanes having manufacturer serial numbers 211 through 422 inclusive, and Model A340 series airplanes having manufacturer serial numbers 212 through 447 inclusive: Within 24 months after the effective date of this AD. (3) For Model A330 series airplanes having manufacturer serial numbers 423 and subsequent, and Model A340 series airplanes having manufacturer serial numbers 450 through 955 inclusive: Within 36 months after the effective date of this AD or since the first flight of the airplane, whichever occurs later. (j) Corrective Action for TAC Strut Ends and Installation of Reinforcing Clamps (1) If, during any inspection required by paragraph (h) of this AD, no cracks are found: Before further flight, reinstall or install, as applicable, reinforcing clamps on the strut ends, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (2) If, during any inspection required by paragraph (h) of this AD, any crack is found: Before further flight, replace any affected strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (k) Repetitive Inspections of SARMA Strut Ends At the applicable time specified in paragraph (i) of this AD, do an HFEC inspection for cracking of all SARMA strut ends of the THS support located at FR 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 12 months. (l) Corrective Action for SARMA Strut Ends If any crack is found on a strut end during the inspection required by paragraph (k) of this AD: Before further flight, replace any affected SARMA strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (m) No Terminating Action Replacement of THS struts on an airplane does not constitute terminating action for the repetitive inspections required by this AD. (n) No Reporting Although Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; and Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; specify to submit certain information to the manufacturer, this AD does not include that requirement. (o) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (h), (j), and (k) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (n)(1) through (n)(6) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330-53-3206, dated February 7, 2013. (2) Airbus Service Bulletin A330-53-3206, Revision 01, dated June 10, 2013. (3) Airbus Service Bulletin A330-53-3206, Revision 02, dated August 8, 2013. (4) Airbus Service Bulletin A340-53-4208, dated February 7, 2013. (5) Airbus Service Bulletin A340-53-4208, Revision 01, dated June 10, 2013. (6) Airbus Service Bulletin A340-53-4208, Revision 02, dated August 8, 2013. (p) 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: 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0068, dated March 18, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA- 2014-1043-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) 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. [[Page 72573]] (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014. (ii) Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014. (3) 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. (4) 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. (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.