2020-22-09: Fuselage

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by: 0 a. Removing airworthiness directive (AD) 2001-16-13, Amendment 39-12382 (66 FR 44295, August 23, 2001), and 0 b. Adding the following new AD: \n\n2020-22-09 Airbus SAS: Amendment 39-21305; Docket No. FAA-2020-0970; Project Identifier AD-2020-01359-T. \n\n(a) Effective Date \n\n\n\tThis AD is effective November 25, 2020. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2001-16-13, Amendment 39-12382 (66 FR 44295, August 23, 2001) (''AD 2001-16-13''). \n\n(c) Applicability \n\n\n\tThis AD applies to Airbus SAS Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, certificated in any category, except airplanes on which Airbus Industrie Modification 46636 has been accomplished in production or which have been modified in service as specified in Airbus Service Bulletin A330-53-3090. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 53, Fuselage. \n\n(e) Reason \n\n\n\tThis AD was prompted by a report that during fatigue testing on the fuselage, cracks were detected in the longitudinal buttstrap at stringer 9, at frame 31, and at frame 37.1. The FAA is issuing this AD to address fatigue cracking of the fuselage longitudinal buttstrap, which could result in reduced structural integrity of the fuselage. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Retained Inspection, with New Service Information \n\n\n\tThis paragraph restates the requirements of paragraph (a) of AD 2001-16-13, with new service information. Prior to the accumulation of 15,000 total flight cycles: Perform a roto-test inspection to detectcracks of the fastener holes at frame 31, frame 37.1, and stringer 9, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330- 53-3090, Revision 03, dated December 11, 2002. \n\n(h) Retained Reinforcement, With New Service Information \n\n\n\tThis paragraph restates the requirements of paragraph (b) of AD 2001-16-13, with new service information. If no cracks are detected during the inspection performed in accordance with paragraph (g) of this AD, prior to further flight, reinforce the fuselage structure between frames 31 and 37.1, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002. \n\n(i) Retained Follow-Up Inspection and Repair, With New Service Information and Revised Repair Approval Language \n\n\n\tThis paragraph restates the requirements of paragraph (c) of AD 2001-16-13, with new service information and revised repair approval language. If any crack is detected during the inspection performed in accordance with paragraph (g) of this AD, prior to further flight, perform a high frequency eddy current (HFEC) inspection to determine the crack length, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002. Prior to further flight, repair the crack in accordance with a method approved by the Direction G(eacute)n(eacute)rale de l'Aviation Civile (or its delegated agent) or using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or the European Union Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. \n\n(j) Other FAA AD Provisions \n\n\n\tThe following provisions also apply to this AD: \n\t(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. 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 responsible Flight Standards Office. \n\t(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; orthe European Union Aviation Safety Agency (EASA); or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. \n\t(3) Required for Compliance (RC): Except as required by paragraph (j)(2) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. \n\n(k) Related Information \n\n\n\t(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Frenchairworthiness directive 2001-075(B), dated March 17, 2001, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-0970. \n\t(2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229; email [email protected]. \n\n(l) Material Incorporated by Reference \n\n\n\t(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. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. \n\t(3) The following service information was approved for IBR on November 25, 2020. \n\t(i) Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002. \n\t(ii) (Reserved) \n\n((Page 71532)) \n\n\n\t(4) The following service information was approved for IBR on September 7, 2001 (66 FR 44295, August 23, 2001). \n\t(i) Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001. \n\t(ii) (Reserved) \n\t(5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; internet https://www.airbus.com. \n\t(6) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. \n\t(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, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on October 26, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-24855 Filed 11-9-20; 8:45 am) BILLING CODE 4910-13-P