Airworthiness Directive · Amendment 39-22561 · Engine fuel and control
Airbus SAS Airplanes
This AD applies to all Airbus SAS Model A330-841 and -941 airplanes, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2022-18- 12, which applied to all Airbus SAS Model A330-841 and -941 airplanes. AD 2022-18-12 required installing serviceable engine electronic control (EEC) software or EEC units having the serviceable software, limiting certain parts installation configurations, and prior or concurrent modification of EEC software. This AD was prompted by a determination that engine crystal icing protection could be (temporarily) lost if an erroneous total pressure value is provided by the airplane system, which is addressed through EEC software. This AD continues to require certain actions in AD 2022-18-12 and requires adding new limitations for intermixing of certain EEC software standards and a new operational limitation for engines with certain EEC software installed, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of certain engines under certain conditions. 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 2022-0253, dated December 19, 2022 (EASA AD 2022-0253).
(1) Where EASA AD 2022-0253 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2022-0253 refers to “10 September 2021,” this AD requires using October 20, 2022 (the effective date of AD 2022-18-12).
(3) Where EASA AD 2022-0253 refers to “10 September 2023,” this AD requires using October 20, 2024 (24 months after October 20, 2022, the effective date of AD 2022-18-12).
(4) This AD does not adopt the “Remarks” section of EASA AD 2022-0253.
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 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 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 Tim Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-231-3667; email timothy.p.dowling@faa.gov.
