Airworthiness Directive · Amendment 39-23076 · Wings
Airbus SAS Airplanes
This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1) through (3) of this AD, certificated in any category.
(1) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes.
(2) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes.
(3) Model A321-211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes.
The FAA is superseding Airworthiness Directive (AD) 2021-25- 14, which applied to all Airbus SAS 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. AD 2021-25-14 required repetitive inspections for cracking at the wing manhole access panel attachment holes at certain wing skin panels, and corrective action if necessary. Since the FAA issued AD 2021-25-14, new investigation results determined that additional airplanes are subject to the unsafe condition and certain structural repair manual (SRM) tasks should not be used to accomplish repairs. This AD continues to require the actions in AD 2021-25-14. This AD also changes the applicability to both add and remove airplane models, updates the compliance times, and prohibits the use of certain SRM tasks for repair. The FAA is issuing this AD to address the unsafe condition on these products.
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, European Union Aviation Safety Agency (EASA) AD 2024-0230, dated December 2, 2024 (EASA AD 2024-0230).
(1) Where EASA AD 2024-0230 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2024-0230 refers to February 8, 2024 (the effective date of EASA AD 2024-0027, dated January 25, 2024), this AD requires using the effective date of this AD.
(3) Where paragraph (2) of EASA AD 2024-0230 specifies “any finding is detected as defined in the AOT, 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 cracking is detected, the cracking 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) This AD does not adopt the requirements of paragraph (4) of EASA AD 2024-0230.
(5) This AD does not adopt the “Remarks” section of EASA AD 2024-0230.
Although the material referenced in EASA AD 2024-0230 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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 (i) and (j)(2) of this AD, if any material referenced in EASA AD 2024-0230 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.
For more information about this AD, contact Timothy Dowling, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-222-5102; email: Timothy.P.Dowling@faa.gov.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
