2024-04-04: 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) 2018-14-09, Amendment 39-19329 (83 FR 34034, July 19, 2018); and b. Adding the following new AD: 2024-04-04 Airbus SAS: Amendment 39-22683; Docket No. FAA-2023-2144; Project Identifier MCAI-2023-00898-T. (a) Effective Date This airworthiness directive (AD) is effective April 22, 2024. (b) Affected ADs This AD replaces AD 2018-14-09, Amendment 39-19329 (83 FR 34034, July 19, 2018) (AD 2018-14-09). (c) Applicability This AD applies to Airbus SAS Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category, all manufacturer serial numbers, except the airplanes specified in paragraphs (c)(1) through (3) of this AD. (1) Airplanes on which Airbus SAS modification 161255 has been embodied in production. (2) Model A319 series airplanes on which Airbus SAS modifications 28238, 28162, and 28342 have been concurrently embodied in production. (3) Model A318 series airplanes on which Airbus SAS modification 39195 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of early cracking on the four holes of the crossbeam splicing at certain fuselage frames (FR). The FAA is issuing this AD to address cracking at two upper rows of fasteners of the crossbeam splicing at FR16 and FR20, on both the left-hand (LH) and right-hand (RH) sides. The unsafe condition, if not addressed, could result in reduced structural integrity of the airplane due to the failure of structural components. (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 2023-0150, dated July 20, 2023 (EASA AD 2023-0150). (h) Exceptions to EASA AD 2023-0150 (1) Where EASA AD 2023-0150 refers to "28 July 2016 [the effective date of EASA AD 2016-0139]," this AD requires using August 23, 2018 (the effective date of AD 2018-14-09). (2) Where EASA AD 2023-0150 refers to its effective date, this AD requires using the effective date of this AD. (3) Where rows B and C of the "Threshold" column in Table 1 of EASA AD 2023-0150 refer to "54 800 FH," for this AD, replace that text with "54 900 FH." (4) Where paragraph (5) of EASA AD 2023-0150 refers to "valid within the EASA system," for this AD, replace that text with "approved by the FAA, EASA, Airbus SAS's EASA Design Organization Approval (DOA), or an EASA DOA (other than Airbus SAS's EASA DOA)." (5) Where paragraph (5) of EASA AD 2023-0150 specifies "contact that design approval holder (DAH) for assessment and repair instructions, obtain EASA AMOC approval and accomplish those instructions accordingly, as applicable," for this AD, replace that text with "modify the repair using a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature." (6) Where the service information referenced in paragraphs (8) and (9) of EASA AD 2023-0150 refers to actions when an existing hole diameter is "more than or equal to the minimum starting hole diameter," for this AD, replace that text with "more than or equal to the maximum starting hole diameter." (7) This AD does not adopt the "Remarks" section of EASA AD 2023-0150. (i) No Reporting Requirement Although the service information referenced in EASA AD 2023-0150 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, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: [email protected]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (ii) AMOCs approved previously for AD 2018-14-09 are approved as AMOCs for the corresponding provisions of EASA AD 2023-0150 that are required by paragraph (g) of this AD. (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, International Validation 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 paragraphs (i) and (j)(2) of this AD, if any service information 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 Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 817-222-5102; email [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023-0150, dated July 20, 2023. (ii) [Reserved] (3) For EASA AD 2023-0150, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email [email protected]; website easa.europa.eu. You may find this EASA AD on the EASA website at ad.easa.europa.eu. (4) You may view this material that is incorporated by reference 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 March 11, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-05494 Filed 3-15-24; 8:45 am]BILLING CODE 4910-13-P