2025-11-08: Landing gear

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: 2025-11-08 Airbus SAS: Amendment 39-23054; Docket No. FAA-2025-0207; Project Identifier MCAI-2024-00455-T. (a) Effective Date This airworthiness directive (AD) is effective July 11, 2025. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A350-941 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Unsafe Condition This AD was prompted by an inspection that found several anodic burns on the main landing gear (MLG) bogie beam axles following a high velocity oxygen-fuel stripping process. The FAA is issuing this AD to address the anodic burns on the MLG bogie beam axles. The unsafe condition, if not addressed, could lead to structural failure of the MLG and consequent collapse, possibly resulting in damage to the airplane and injury to the occupants. (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, European Union Aviation Safety Agency (EASA) AD 2024-0156, dated August 13, 2024 (EASA AD 2024-0156). (h) Exceptions to EASA AD 2024-0156 (1) Where EASA AD 2024-0156 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2024-0156 defines a serviceable part as "Any MLG bogie beam axle, eligible for installation in accordance with Airbus instructions, that is not an affected part", for this AD replace that text with "Any MLG bogie beam axle, eligible for installation, that is not an affected part". (3) Where paragraph (1) of EASA AD 2024-0156 specifies a compliance time for the replacement, for this AD, do the replacement within 24,000 flight hours or 5,700 flight cycles, whichever occurs first since first installation of the affected part on an airplane, or within 12 months after the effective date of this AD, whichever occurs later. (4) Where paragraph (1) of EASA AD 2024-0156 specifies "in accordance with the instructions of the SB", this AD requires replacing that text with "in accordance with the replacement instructions of the SB". (5) This AD does not adopt the "Remarks" section of EASA AD 2024-0156. (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 AIR-520, Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email 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 paragraph (i)(2) of this AD, if any material 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. (j) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3225; 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 2024-0156, dated August 13, 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]. You may find this material 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 May 29, 2025. Lona C. Saccomando, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025-10319 Filed 6-5-25; 8:45 am]BILLING CODE 4910-13-P