2026-12-11: Fuselage

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: 2026-12-11 Airbus SAS: Amendment 39-23381; Docket No. FAA-2026-3485; Project Identifier MCAI-2025-00437-T. (a) Effective Date This airworthiness directive (AD) is effective August 3, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025-0067, dated March 28, 2025 (EASA AD 2025-0067). (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a review of the cold working process on the assembly line that detected a deviation to the manufacturing process. The FAA is issuing this AD to address a deviation to the manufacturing process, which could adversely affect the fatigue life of the center fuselage frame (FR) foot joint connections at FR37 to FR41 inclusive, between stringer (STR) STR21 to STR23. The unsafe condition, if not addressed, could lead to crack initiation and propagation, resulting in 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2025-0067. (h) Exceptions to EASA AD 2025-0067 (1) Where paragraph (2) of EASA AD 2025-0067 specifies "any discrepancy is detected, as defined in the SB", this AD requires replacing that text with "any fastener hole is not in nominal design condition, as defined in the SB". (2) Where paragraph (3) of EASA AD 2025-0067 specifies "no discrepancy is detected", this AD requires replacing that text with "fastener holes are in nominal design condition, as defined in the SB". (3) Where paragraph (4) of EASA AD 2025-0067 specifies a "High Frequency Eddy Current (HFEC) inspection around the fastener holes at an affected area is an acceptable method", this AD requires replacing that text with "High Frequency Eddy Current (HFEC) inspection around the fastener holes at an affected area, in accordance with the instructions of the SB, is an acceptable method". (4) Where paragraph (5) of EASA AD 2025-0067 specifies "any crack is detected, as defined in the SB, before next flight, contact Airbus for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly.", this AD requires replacing that text with "any crack is detected, the crack 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." (5) Where paragraph (7) of EASA AD 2025-0067 specifies "no discrepancy", this AD requires replacing that text with "no cracking". (6) This AD does not adopt the "Remarks" section of EASA AD 2025-0067. (i) No Reporting Requirement Although the material referenced in EASA AD 2025-0067 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) 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 (k) of this AD and email to: AMOC@faa.gov . 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 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)(3), (h)(4), and (j)(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. (k) Additional Information For more information about this AD, contact Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3647; email: nicholas.h.benson@faa.gov. (l) 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 2025-0067, dated March 28, 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 ADs@easa.europa.eu; website easa.europa.eu. 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 fr.inspection@nara.gov. Issued on June 10, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026-13062 Filed 6-26-26; 8:45 am]BILLING CODE 4910-13-P