Airworthiness Directive · Amendment 39-22738 · Time limits/maintenance checks
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2026-03-07. Comply with the one in force.
This AD applies to Airbus SAS Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, -343, -841, and -941 airplanes, certificated in any category, with an original airworthiness certificate or original export certificate of airworthiness issued on or before October 2, 2023.
The FAA is superseding Airworthiness Directive (AD) 2014-15- 09, AD 2020-15-09, and AD 2022-16-07. AD 2014-15-09 applied to all Airbus SAS Model A330-200 Freighter, A330-200 and -300, and A340-200, - 300, -500, and -600 series airplanes. AD 2020-15-09 applied to all Airbus SAS Model A330-941 airplanes. AD 2014-15-09 and AD 2020-15-09 required repetitive operational tests of the hydraulic locking function on certain spoiler servo-controls (SSCs) and replacement if necessary. AD 2022-16-07 applied to certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2022-16-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by the determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2014-15-09, AD 2020-15-09, and AD 2022-16-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. This AD also removes Model A340-200, -300, -500, and -600 series airplanes from the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2014-15-09, with removed references to Model A340 service information. For Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes: At the latest of the times specified in paragraphs (g)(1) through (3) of this AD, accomplish an operational test of the hydraulic locking function on each SSC (any type), when fitted on the Blue or Yellow hydraulic circuits, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27-3195, Revision 01, dated February 6, 2014. Repeat the operational test thereafter at intervals not to exceed 48 months. Accomplishing the revision of the existing maintenance or inspection program required by paragraph (p) of this AD terminates the requirements of this paragraph.
(1) Within 48 months since first flight of the airplane.
(2) Within 48 months since accomplishing the most recent operational test, as specified in Airbus All Operators Telex (AOT) A330-27A3185; dated January 4, 2012.
(3) Within 24 months after September 5, 2014 (the effective date of AD 2014-15-09).
This paragraph restates the credit provided in paragraph (h) of AD 2014-15-09, with removed references to Model A340 service information. This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before September 5, 2014 (the effective date of AD 2014-15-09) using Airbus Service Bulletin A330-27-3195, dated December 7, 2012.
This paragraph restates the replacement required by paragraph (i) of AD 2014-15-09, with removed references to Model A340 service information. If, during any operational test required by paragraph (g) of this AD, the hydraulic locking function of an SSC fails the test, before further flight, replace the affected SSC with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-27-3195, Revision 01, dated February 6, 2014.
This paragraph restates the no terminating action statement specified in paragraph (j) of AD 2014-15-09, with no changes. Doing the replacement required by paragraph (i) of this AD is not terminating action for the repetitive operational tests required by paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (g) of AD 2020-15-09, with no changes. For Model A330-941 airplanes: Except as specified in paragraph (l) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2020-0054, dated March 11, 2020 (EASA AD 2020-0054). Accomplishing the revision of the existing maintenance or inspection program required by paragraph (p) of this AD terminates the requirements of this paragraph.
This paragraph restates the exceptions specified in paragraph (h) of AD 2020-15-09, with no changes. The “Remarks” section of EASA AD 2020-0054 does not apply to this AD.
This paragraph restates the requirements of paragraph (i) of AD 2022-16-07, with no changes. For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before July 1, 2021: Except as specified in paragraph (n) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2021-0248, dated November 15, 2021 (EASA AD 2021-0248). Accomplishing the revision of the existing maintenance or inspection program required by paragraph (p) of this AD terminates the requirements of this paragraph.
This paragraph restates the exceptions specified in paragraph (j) of AD 2022-16-07, with no changes.
(1) Where EASA AD 2021-0248 refers to its effective date, this AD requires using September 27, 2022 (the effective date of AD 2022-16-07).
(2) The requirements specified in paragraphs (1) and (2) of EASA AD 2021-0248 do not apply to this AD.
(3) Paragraph (3) of EASA AD 2021-0248 specifies revising “the approved AMP [aircraft maintenance program]” within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, within 90 days after September 27, 2022 (the effective date of AD 2022-16-07).
(4) The initial compliance time for doing the tasks specified in paragraph (3) of EASA 2021-0248 is at the applicable “associated thresholds,” as incorporated by the requirements of paragraph (3) of EASA AD 2021-0248, or within 90 days after September 27, 2022 (the effective date of AD 2022-16-07), whichever occurs later.
(5) The provisions specified in paragraphs (4) and (5) of EASA AD 2021-0248 do not apply to this AD.
(6) The “Remarks” section of EASA AD 2021-0248 does not apply to this AD.
This paragraph restates the provisions specified in paragraph (k) of AD 2022-16-07, with a new exception. Except as required by paragraph (p) of this AD, after the existing maintenance or inspection program has been revised as required by paragraph (m) of this AD, no alternative actions (e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2021-0248.
Except as specified in paragraph (q) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2023-0199, dated November 17, 2023 (EASA AD 2023-0199). Accomplishing the revision of the existing maintenance or inspection program required by this paragraph terminates the requirements of paragraphs (g), (k), and (m) of this AD.
(1) This AD does not adopt the requirements specified in paragraphs (1) and (2) of EASA AD 2023-0199.
(2) Paragraph (3) of EASA AD 2023-0199 specifies revising “the AMP,” within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, within 90 days after the effective date of this AD.
(3) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2023-0199 is at the applicable “associated thresholds” as incorporated by the requirements of paragraph (3) of EASA AD 2023-0199, or within 90 days after the effective date of this AD, whichever occurs later.
(4) This AD does not adopt the provisions specified in paragraphs (4) and (5) of EASA AD 2023-0199.
(5) This AD does not adopt the “Remarks” section of EASA AD 2023-0199.
(6) Where the service information referenced in EASA AD 2023-0199 specifies the compliance time for tasks 282400-G0001-1-C and 282400-P0001-1-C as “24 Months from the Effective Date of the EASA Airworthiness Directive that is expected to be issued to mandate this change, without exceeding the current 29 000 FH”, this AD requires using within 24 months after the effective date of this AD, without exceeding the current 29,000 flight hour interval.
After the existing maintenance or inspection program has been revised as required by paragraph (p) of this AD, no alternative actions (e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2023-0199.
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 manager of the International Validation Branch, mail it to the address identified in paragraph (t)(1) 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): For any service information referenced in EASA AD 2020-0054 that contains RC procedures and tests: Except as required by paragraph (s)(2) of this AD, RC 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.
(1) For more information about this AD, contact Vladimir Ulyanov, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-231-3229; email Vladimir.ulyanov@faa.gov.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(8) of this AD.
