2024-05-02: Fuselage

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2024-05-02 Airbus SAS: Amendment 39-22692; Docket No. FAA-2023-1897; Project Identifier MCAI-2023-00921-T. (a) Effective Date This airworthiness directive (AD) is effective May 8, 2024. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A320-214, A320-216, A320-251N, A320-271N, and A321-253NX airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2023-0179, dated October 11, 2023 (EASA AD 2023-0179). (d) Subject Air Transport Association (ATA) of America Code: 53, Fuselage. (e) Unsafe Condition This AD was prompted by a quality review of the forward cargo door frame-to-fuselage skin panel assembly identified several drillings as deviating from manufacturing requirements, creating oversized fastener holes. The FAA is issuing this AD to address oversized fastener holes and cracking. The unsafe condition, if not detected and corrected, could result in reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2023-0179. (h) Exceptions to EASA AD 2023-0179 (1) Where EASA AD 2023-0179 refers to its effective date, this AD requires using the effective date of this AD. (2) Where paragraph (4) of EASA AD 2023-0179 specifies "If, during any SDI as required by paragraph (3) of this AD, any crack is detected, before next flight, contact Airbus for approved repair instructions and, within the compliance time identified therein, accomplish those instructions accordingly," this AD requires replacing those words with "If, during any SDI as required by paragraph (3) of this AD, any cracking is found, before next flight, repair the cracking using a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature." (3) Where paragraph (8) of EASA AD 2023-0179 specifies the repair be done in accordance with "approved Airbus repair instructions," for this AD the repair must have been done using a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (4) Where paragraph (6) of EASA AD 2023-0179 specifies to "oversize that fastener hole and install a new oversize fastener and new rivet," this AD requires replacing those words with "before next flight, oversize that fastener hole and install a new oversize fastener and new rivet." (5) This AD does not adopt the "Remarks" section of EASA AD 2023-0179. (i) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using EASA AD 2023-0153, dated July 26, 2023. (j) No Reporting Requirement Although the service information referenced in EASA AD 2023-0179 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (k) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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 manager of the International Validation Branch, mail it to the address in paragraph (l) of this AD or email to: [email protected]. If mailing information, also submit information by email. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (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, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (j) and (k)(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. (l) Additional Information For more information about this AD, contact Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 206-231-3667; email: [email protected]. (m) 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. (i) European Union Aviation Safety Agency (EASA) AD 2023-0179, dated October 11, 2023. (ii) [Reserved] (3) For EASA AD 2023-0179, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email [email protected]; website easa.europa.eu. You may find this EASA AD on the EASA website ad.easa.europa.eu. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected] . Issued on February 29, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-06996 Filed 4-2-24; 8:45 am]BILLING CODE 4910-13-P