2025-07-05: 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: 2025-07-05 Airbus SAS: Amendment 39-23006; Docket No. FAA-2024-2320; Project Identifier MCAI-2024-00268-T. (a) Effective Date This airworthiness directive (AD) is effective May 13, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A350-941 and -1041 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2024-0129, dated July 5, 2024 (EASA AD 2024-0129). (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an updated stress analysis on the forward (FWD) cargo door and its attachment piano hinges that revealed a risk of cracking and crack propagation on piano hinges 2 and 3, originating from opening-closing fatigue cycles of the FWD cargo door. The FAA is issuing this AD to address potential failure of the piano hinges due to cracking. The unsafe condition, if not addressed, could result in damage to the FWD cargo door surrounding structure and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2024-0129. (h) Exceptions to EASA AD 2024-0129 (1) Where EASA AD 2024-0129 refers to "16 May 2024 [the effective date of EASA AD 2024-0098]," this AD requires using the effective date of this AD. (2) Where paragraph (2) of EASA AD 2024-0129 specifies "if, during the DET as required by paragraph (1) of this AD, any crack or damage is detected, before next flight, contact Airbus for approved instructions and, within the compliance time specified therein, accomplish those instructions accordingly," this AD requires replacing that text with "if any crack or damage is detected, the crack or damage must be repaired before further flight using a method approved by the Manager, AIR-520, Continued Operational Safety 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) This AD does not adopt the "Remarks" section of EASA AD 2024-0129. (i) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-520, Continued Operational Safety 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 Continued Operational Safety Branch, mail it to the address identified in paragraph (j) 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. (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, AIR-520, Continued Operational Safety 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) Required for Compliance (RC): Except as required by paragraphs (h)(2) and (i)(2) of this AD, if any material referenced in EASA AD 2024-0129 contains paragraphs that are labeled as RC, the instructions in RC paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended. The instructions in paragraphs, including subparagraphs under those paragraphs, 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC. (j) Additional Information For more information about this AD, contact Nathan Weigand, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3531; email: [email protected] . (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024-0129, dated July 5, 2024. (ii) [Reserved] (3) For EASA material identified in this AD, 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 at ad.easa.europa.eu . (4) You may view this material 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. (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 March 28, 2025. Victor Wicklund, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025-06006 Filed 4-7-25; 8:45 am]BILLING CODE 4910-13-P