2026-09-06: 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: 2026-09-06 Airbus SAS: Amendment 39-23327; Docket No. FAA-2026-3871; Project Identifier MCAI-2026-00247-T. (a) Effective Date This airworthiness directive (AD) is effective May 26, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A319-153N airplanes; Model A320-251N, -252N, and -271N airplanes; and Model A321-251NX, -252NX, -271NX and -272NX airplanes; certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2026-0055R1, dated April 14, 2026 (EASA AD 2026-0055R1). (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an Airbus supplier identifying a quality issue in production, which could result in potential deviations from the specified thickness of various fuselage panels delivered to Airbus. The FAA is issuing this AD to address the potential for certain forward fuselage panels to have deviations from the specified thickness, which, in combination with certain repairs, can 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 2026-0055R1. (h) Exceptions to EASA AD 2026-0055R1 (1) Where EASA AD 2026-0055R1 refers to March 20, 2026 (the effective date of EASA AD 2026-0055, dated March 13, 2026), this AD requires using the effective date of this AD. (2) Where paragraph (1) of EASA AD 2026-0055R1 specifies to "accomplish the 'local thickness mapping' ", for this AD replace that text with "accomplish the 'local thickness mapping', as applicable". (3) Where paragraph (4) of EASA AD 2026-0055R1 specifies "if any crack is identified on an affected panel, before next flight, contact Airbus for approved instructions and within the compliance time identified therein, accomplish those instructions accordingly", this AD requires replacing that text with "if any cracking or other damage is detected, the cracking and other 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". (4) Where the service information referenced in EASA AD 2026-0055R1 specifies to send an inspection report to Airbus if the measured thicknesses are within the drawing tolerances, or if the airplane can be released permanently with the panel condition acceptable as-is following the Airbus assessment, for this AD, send the report at the applicable time specified in paragraph (h)(4)(i) or (ii) of this AD. (i) If the finding was made on or after the effective date of this AD: Submit the report within 14 days after the finding. (ii) If the finding was made before the effective date of this AD: Submit the report within 14 days after the effective date of this AD. (5) This AD does not adopt the "Remarks" section of EASA AD 2026-0055R1. (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. (3) Required for Compliance (RC): Except as required by paragraph (i)(2) of this AD, if any material referenced in EASA AD 2026-0055R1 that 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 Taylor Stanley, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 407-852-7677; 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 2026-0055R1, dated April 14, 2026. (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 April 24, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026-09171 Filed 5-6-26; 4:15 pm]BILLING CODE 4910-13-P