Airworthiness Directive · Amendment 39-22692 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A320-214, A320-216, A320-251N, A320-271N, and A321-253NX airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2023-0179, dated October 11, 2023 (EASA AD 2023-0179).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, A320-216, A320-251N, A320-271N, and A321-253NX airplanes. This AD was prompted by a quality review of the forward cargo door frame-to-fuselage skin panel assembly identified several fastener holes that deviated from the manufacturing requirements. This AD requires a geometrical check of the diameter of certain fastener holes for deviations, and if any deviation is found, repetitive special detailed inspections of the affected area for discrepancies and, depending on findings, accomplishment of applicable corrective actions, 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2023-0179.
(1) Where EASA AD 2023-0179 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (4) of EASA AD 2023-0179 specifies “If, during any SDI as required by paragraph (3) of this AD, any crack is detected, before next flight, contact Airbus for approved repair instructions and, within the compliance time identified therein, accomplish those instructions accordingly,” this AD requires replacing those words with “If, during any SDI as required by paragraph (3) of this AD, any cracking is found, before next flight, repair the cracking 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) Where paragraph (8) of EASA AD 2023-0179 specifies the repair be done in accordance with “approved Airbus repair instructions,” for this AD the repair must have been done 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.
(4) Where paragraph (6) of EASA AD 2023-0179 specifies to “oversize that fastener hole and install a new oversize fastener and new rivet,” this AD requires replacing those words with “before next flight, oversize that fastener hole and install a new oversize fastener and new rivet.”
(5) This AD does not adopt the “Remarks” section of EASA AD 2023-0179.
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.
