Airworthiness Directive · Amendment 39-22146 · Air
Airbus SAS Airplanes
This AD applies to all Airbus SAS Model airplanes, certificated in any category, as identified in paragraphs (c)(1) though (3) of this AD.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
The FAA is superseding Airworthiness Directive (AD) 2020-22- 03, which applied to all Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes. AD 2020-22-03 required revising the existing airplane flight manual (AFM) to incorporate procedures to be applied if an engine bleed over-temperature occurs when the associated engine bleed valve is jammed open, and provided for the optional embodiment of updated flight warning computer (FWC) software, which terminated the AFM revision. This AD was prompted by the development of new maintenance actions and software related to over-temperature failure conditions. This AD continues to require the actions specified in AD 2020-22-03, requires accomplishing the new maintenance tasks and corrective actions, and mandates embodiment of the updated FWC software for certain airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected FWC software. 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 2021-0281, dated December 17, 2021 (EASA AD 2021-0281).
(1) Where EASA AD 2021-0281 refers to October 1, 2020 (the effective date of EASA AD 2020-0205), this AD requires using November 5, 2020 (the effective date of AD 2020-22-03).
(2) Where EASA AD 2021-0281 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2021-0281 specifies to “inform all flight crews, and, thereafter, operate the aeroplane accordingly,” this AD does not require those actions as those actions are already required by existing FAA operating regulations.
(4) Where paragraphs (6) and (7) of EASA AD 2021-0281 specifies actions if “any discrepancies are detected,” for this AD discrepancies include failures related to an over-temperature situation, hidden failures in equipment for a “not isolated over-temperature” failure condition, cracking on the exchanger outlet temperature sensor, or dual drift in the exchanger outlet temperature sensor.
(5) Where paragraph (11) of EASA AD 2021-0281 specifies that an airplane with certain modifications is compliant with “the requirements of paragraph (2) of EASA AD 2020-0077,” for this AD use “for the corresponding requirements of paragraph (2) of EASA AD 2020-0077 that are required by paragraph (g) of AD 2020-17-16, Amendment 39-21221 (85 FR 54900, September 3, 2020).”
(6) The “Remarks” section of EASA AD 2021-0281 does not apply to this AD.
Although the service information referenced in EASA AD 2021-0281 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, 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/manager of the certification office, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
(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 (j)(2) of this AD, if any service information referenced in EASA AD 2021-0281 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 Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229; email: vladimir.ulyanov@faa.gov.
