2026-12-02: 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: a. Removing Airworthiness Directive (AD) 2022-02-11, Amendment 39-21908 (87 FR 7033, February 8, 2022); and b. Adding the following new AD: 2026-12-02 Airbus SAS: Amendment 39-23372; Docket No. FAA-2026-2281; Project Identifier MCAI-2025-00915-T. (a) Effective Date This airworthiness directive (AD) is effective July 14, 2026. (b) Affected ADs This AD replaces AD 2022-02-11, Amendment 39-21908 (87 FR 7033, February 8, 2022) (AD 2022-02-11). (c) Applicability This AD applies to Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025-0111, dated May 14, 2025 (EASA AD 2025-0111). (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N, -171N, and -173N airplanes. (3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -271NY, -272N, and -272NX airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report that cracks were detected on frame (FR) 16 and FR20 web holes and passenger door intercostal fitting holes at the door stop fitting locations, and a determination that a certain compliance time must be clarified. This AD was also prompted by a determination that additional airplane models must be added to the applicability and the terminating action for repaired affected areas must be clarified. The FAA is issuing this AD to address cracking of the web holes at the door stop fittings. The unsafe condition, if not addressed, could affect the 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 2025-0111. (h) Exceptions to EASA AD 2025-0111 (1) Where EASA AD 2025-0111 refers to its effective date, this AD requires using the effective date of this AD. (2) Where table 1 of EASA AD 2025-0111 specifies a compliance time of "Before exceeding 30[,]000 FC since aeroplane first flight," this AD requires, for the inspection at frame 16 only, using a compliance time of "Before exceeding 30,000 flight cycles since airplane's first flight, or within 30 days after March 15, 2022 (the effective date of AD 2022-02-11), whichever occurs later." (3) Where table 1 of EASA AD 2025-0111 refers to a compliance time "after 31 May 2017 [reference date for the compliance time included in ALS Part 2 rev. 6]", this AD requires using a compliance time after "May 31, 2018 (the effective date of task 531103-01-1 in "ALS Part 2 rev. 6")." (4) Where paragraph (3) of EASA AD 2025-0111 specifies "repaired in accordance with Airbus approved repair instructions, accomplish the next due inspection of each repaired affected area in accordance with, and within the compliance time as specified in, Airbus approved repair instructions, as applicable", this AD requires replacing that text with "repaired 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), provided the DOA approval includes the DOA-authorized signature: Accomplish the next due inspection of each repaired area in accordance with, and within the compliance time specified in, the applicable approved repair instructions". (5) Where paragraph (4) of EASA AD 2025-0111 specifies "cracks are detected", this AD requires replacing that text with "any crack is detected". (6) Where the applicable inspection service bulletin referenced in EASA AD 2025-0111 specifies to report findings and completion of all inspections, as applicable, this AD requires reporting only if the cracked intercostal(s) have been replaced using repair instruction R53113118, R53113626, or R53113627, as applicable. Report results at the applicable time specified in paragraph (6)(i) or (ii) of this AD. If operators have reported findings as part of obtaining any corrective actions approved by Airbus SAS's EASA DOA, operators are not required to report those findings as specified in this paragraph. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (7) This AD does not adopt the "Remarks" section of EASA AD 2025-0111. (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: AMOC@faa.gov . (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 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; phone: 206-231-3225; email: dan.rodina@faa.gov. (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 2025-0111, dated May 14, 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. 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 4, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026-11510 Filed 6-8-26; 8:45 am]BILLING CODE 4910-13-P