Airworthiness Directive · Amendment 39-21858 · Wings
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2025-13-10. Comply with the one in force.
This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1) through (3) of this AD and certificated in any category.
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is adopting a new airworthiness directive (AD) for 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. This AD was prompted by the determination that fatigue cracking may occur at the wing manhole access panel attachment holes at certain wing skin panels on airplanes with Sharklets or its structural reinforcements installed. This AD requires repetitive inspections for cracking of the area, and corrective action if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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 2021-0256, dated November 16, 2021 (EASA AD 2021-0256).
(1) Where EASA AD 2021-0256 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (1) of EASA AD 2021-0256 requires “a DET [detailed visual inspection] of the affected areas,” this AD requires a detailed visual inspection to detect discrepancies (cracking) of the affected areas.
(3) Where paragraph (2) of EASA AD 2021-0256 specifies to “contact Airbus for approved instructions and... accomplish [the specified] instructions accordingly” if discrepancies are detected, for this AD if any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, 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.
(4) Paragraph (3) of EASA AD 2021-0256 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(4)(i) or (ii) of this AD.
(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.
(5) The “Remarks” section of EASA AD 2021-0256 does not apply to this AD.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-AVS-AIR-730-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, Large Aircraft Section, 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 paragraph (i)(2) of this AD, if any service information referenced in EASA AD 2021-0256 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.
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.
