Airworthiness Directive · Amendment 39-22563 · Nacelles/pylons
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A350-941 and A350-1041 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2023-0026, dated January 30, 2023 (EASA AD 2023-0026).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and A350-1041 airplanes. This AD is prompted by reports that excessively deep spot faces on the front engine mounting bolt holes on the wing pylon were detected on the production line. This AD requires a one-time inspection for clash (interference) of the three front engine mounting bolt holes on both the left and right wing pylons, 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 paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2023-0026.
(1) Where EASA AD 2023-0026 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2023-0026 refers to “discrepancies,” for this AD discrepancies are any clash (interference) between the lockplate support and rib 1 or between the pylon bolt and the engine mount; damage (cracks, scratches, or erosion of the protective coating); and incorrect spot face depth or pylon thickness at the spot face.
(3) Where paragraph (2) of EASA AD 2023-0026 specifies to “contact Airbus for approved instructions for corrective action and accomplish those 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, 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) This AD does not adopt the “Remarks” section of EASA AD 2023-0026.
(5) Where the service information referenced in EASA AD 2023-0026 specifies to report inspection results or findings, this AD requires submitting information only if damage (cracks) or incorrect spot face depth or pylon thickness at the spot face are found during any inspection required by EASA AD 2023-0026. Operators are required to submit certain information as part of obtaining any corrective actions approved by Airbus SAS's EASA DOA.
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 (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, 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.
(3) Required for Compliance (RC): Except as required by paragraph (i)(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.
For more information about this AD, contact Dat Le, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7317; email dat.v.le@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.
Aircraft
