2025-16-11: Flight Controls; Landing Gear; Oxygen; Pneumatic

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2025-16-11 Airbus SAS: Amendment 39-23109; Docket No. FAA-2025-1731; Project Identifier MCAI-2025-00491-T. (a) Effective Date This airworthiness directive (AD) is effective September 2, 2025. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A321-271NY airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls; 32, Landing Gear; 35, Oxygen; 36, Pneumatic. (e) Unsafe Condition This AD was prompted by the determination that affected parts addressed by other ADs could also be installed in service on this airplane model. The FAA is issuing this AD to address the unsafe conditions identified in paragraphs (e)(1) through (5) of this AD. (1) Overheat detection system (OHDS) sensing elements that do not properly detect thermal bleed leak events. This unsafe condition, if not addressed, could result in an air leak remaining undetected by the OHDS at an affected position and not being isolated during flight, possibly resulting in localized areas of the main landing gear bay and keel beam being exposed to high temperatures and consequent reduced structural integrity of the airplane. (2) Missing heat treatment of the actuation pin of the SafeLav gaseous oxygen container, which could cause its jamming, with consequent failure of oxygen flow activation. This unsafe condition, if not addressed, could result in lack of supplemental oxygen supply in case of decompression in the cabin/lavatory, possibly resulting in injury to lavatory occupants. (3) Poor reactivity of the start powder used inside the affected oxygen generators. This unsafe condition, if not addressed, could lead to a reduction of the available oxygen capacity of the airplane and could result in injury to airplane occupants. (4) Improper installation of the trimmable horizontal stabilizer actuator (THSA) ball screw jack, which can compromise the failsafe design of the THSA. This unsafe condition, if not addressed, could result in uncontrolled movement of the horizontal stabilizer as a result of a single failure of the THSA and consequent loss of control of the airplane. (5) Erroneous accumulated life information in the THSA release certificate, which could lead to operation of the THSA beyond the certificated life limit. This unsafe condition, if not addressed, could result in failure of the THSA and consequent reduced controllability 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, European Union Aviation Safety Agency (EASA) AD 2025-0075R1, dated July 21, 2025 (EASA AD 2025-0075R1). (h) Exceptions to EASA AD 2025-0075R1 (1) Where EASA AD 2025-0075R1 refers to its effective date, this AD requires using the effective date of this AD. (2) This AD does not adopt the "Remarks" section of EASA AD 2025-0075R1. (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, 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. (j) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3225; email: [email protected]. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) 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 2025-0075R1, dated July 21, 2025. (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 August 5, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025-15687 Filed 8-15-25; 8:45 am]BILLING CODE 4910-13-P