2015-23-06: 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 removing Airworthiness Directive (AD) 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and adding the following new AD: 2015-23-06 Airbus: Amendment 39-18322. Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-AD. (a) Effective Date This AD becomes effective December 29, 2015. (b) Affected ADs This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). (c) Applicability This AD applies to Airbus Model A330-201, -202, -203, -223, - 243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-311, -312,and -313 airplanes; certificated in any category; all manufacturer serial numbers on which Airbus Modification 44205 has been embodied in production, except those on which Airbus Modification 52974 or 53223 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by the results of a fatigue and damage tolerance evaluation that concluded existing compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 73095]] (g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 Weight Variant (WV) 027 Airplanes For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the upper shell structure between frame (FR) 80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable. (1) For airplanes that, as of the effective date of this AD, have not been inspected in accordance with Airbus Service Bulletin A330-53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Beforereaching the applicable threshold specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53- 3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable for airplane model, configuration, and utilization, since the airplane's first flight. (ii) Within the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53- 4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization since the airplane's first flight; or within 12 months after the effective date of this AD; whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have been inspected in accordance with Airbus Service Bulletin A330- 53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the applicable interval specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable; to be counted from the last inspection. (ii) Within 12 months after the effective date of this AD without exceeding the intervals defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53- 4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization to be counted from the last inspection. (h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 WV 027 Airplanes If any crack is detected during any HFEC inspection required by the introductory text to paragraph (g) of this AD: Before further flight,repair 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). Accomplishment of a repair for a specific area, as required by this paragraph, is terminating action for the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, as applicable, for that specific repaired area only. The need and definition of subsequent repetitive inspections (if any) for that specific repaired area will be defined in the applicable repair 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). (i) Optional Terminating Action For Airbus Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: Modification, which includes inspections and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340- 53-4165, Revision 02, dated March 29, 2010; as applicable; terminates the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, except where Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010; as applicable; specifies to contact the manufacturer, repair using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (j) Inspection and Modification for Airbus Model A330-200 Airplanes Within the compliance times specified in paragraph (j)(1) or (j)(2) of this AD, whichever occurs later: Do all applicable actions, including an eddy current rotating probe test and an HFEC inspection for cracks, and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. (1) Within the compliance times identified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, as applicable for airplane configuration and utilization since the airplane's first flight. (2) Within 12 months after the effective date of this AD without exceeding the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, since the airplane's first flight. (k) Inspection and Modification for Airbus Model A340-300 Airplanes, Only WV 027 For Model A340-300 airplanes, WV 027 only: Before the accumulation of 14,200 total flight cycles from the airplane's first flight, do all applicable inspections and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. (l) Corrective Action for Airbus Model A330-200 Airplanes; and Model A340-300 Airplanes, only WV 027 If any crack is detected during the inspection required by the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; concurrently with modification required by paragraph the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD. (m) Definition of ``Threshold'' and ``Interval'' (1) For the purposes of this AD, the term ``Threshold,'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the airplane's first flight. (2) For the purposes of this AD, the term ``Interval'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the last inspection, as applicable. (i) Airbus Service Bulletin A330-53-3168, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008. (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340-53-4174, dated September 19, 2007. (v) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008. (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. (n) Credit for Previous Actions (1) For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: This paragraph provides credit for the modification specified inparagraph (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330-53-3159, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated June 15, 2009. (iii) Airbus Service Bulletin A340-53-4165, dated September 19, 2007. (iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated June 17, 2009. (2) For Model A330-200 airplanes: This paragraph provides credit for the inspection [[Page 73096]] and modification required by the introductory text to paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as applicable. (i) Airbus ServiceBulletin A330-53-3160, dated July 9, 2007, which was incorporated by reference in AD 2008-22-20, Amendment 39- 15717 (73 FR 66747, November 12, 2008). (ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated April 28, 2009, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, which is not incorporated by reference in this AD. (3) For Model A340-300 airplanes, WV 027 only: This paragraph provides credit for the inspection and modification required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340-53- 4172, dated July 10, 2007, which is was incorporated by reference in AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). (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 of this 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 EASA; or Airbus's EASA 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) EASA Airworthiness Directive 2014-0012R1, dated January 24, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0490. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) 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 this AD specifies otherwise. (3) The following service information was approved for IBR on December 29, 2015. (i) Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010. (ii) Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010. (v) Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. (4) The following service information was approved for IBR on December 17, 2008 (73 FR 66747, November 12, 2008). (i) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008. (ii) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008. (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.