Airworthiness Directive · Amendment 39-22258 · Flight controls
Airbus SAS Airplanes
This AD applies to all Airbus SAS Model A350-941 and -1041 airplanes, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2020-18- 04, which applied to Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-18-04 required a one-time health check of the slat power control unit (PCU) torque sensing unit (TSU) for discrepancies, and corrective actions if necessary; a detailed inspection of the left-hand (LH) and right-hand (RH) slat transmission systems for discrepancies, and corrective actions if necessary; and LH and RH track 12 slat gear rotary actuator (SGRA) water drainage and vent plug cleaning (which includes an inspection for moisture). This AD was prompted by a determination that requiring modification of the PCU by replacing each affected slat PCU with a serviceable PCU (one having a different part number) is necessary. This AD continues to require the actions required by AD 2020-18-04, and also requires modification (replacement of each affected slat PCU with a slat PCU having a different part number), and revising the limitations on the installation of affected parts; 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, European Union Aviation Safety Agency (EASA) AD 2021-0275, dated December 10, 2021 (EASA AD 2021-0275).
(1) Where EASA AD 2021-0275 refers to March 11, 2021 (the effective date of EASA AD 2021-0053, dated February 25, 2021), this AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2021-0275 specifies compliance times for accomplishment of certain actions, replace the text “but not exceeding the compliance time for the repeat health check as determined in accordance with the instructions of AOT [Alert Operators Transmission] A27P015-20, or AOT A27P016-20,” with “but within the applicable compliance time specified in paragraph 4.2.3.1 of AOT A27P015-20; or 4.2.2.2.2 or 4.2.2.3.2 of AOT A27P016-20; as applicable.”
(3) Where paragraph (4) of EASA AD 2021-0275 specifies “Appendix 5 of the AOT,” use “the Appendix labeled TSU Condition Check Flowchart of the AOT.”
(4) Where note 2 of EASA AD 2021-0275 states that the certificate of release accompanying a replacement part “will clarify,” use “may be used to clarify.”
(5) The “Remarks” section of EASA AD 2021-0275 does not apply to this AD.
(6) Where EASA AD 2021-0275 refers to its effective date, this AD requires using the effective date of this AD.
(7) Where paragraph (7) of EASA AD 2021-0275 states that the modification specified in paragraph (6) of EASA AD 2021-0275 is terminating action for paragraph (4) of EASA AD 2021-0275, this AD considers accomplishing the modification specified in paragraph (6) of EASA AD 2021-0275 to also be terminating action for the initial health check specified in paragraph (2) of EASA AD 2021-0275.
Although the service information referenced in EASA AD 2021-0275 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, 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. 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, 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 2021-0275 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 Dat Le, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; 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
