Airworthiness Directive · Amendment 39-22986 · Pneumatic
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2025-05-14 R1. Comply with the one in force.
This AD applies to all Airbus SAS Model A350-941 and A350-1041 airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by a report indicating that the thrust reverser and pylon thermal blankets were found damaged due to air leaking from the pre-cooler exchanger (PCE). This AD requires repetitively testing the PCE for air leaks and reporting the results, and, depending on findings, inspecting the thermal blankets for damage and replacing the PCE, 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 2024-0058R2, dated October 4, 2024 (EASA AD 2024-0058R2).
(1) Where EASA AD 2024-0058R2 refers to March 11, 2024 [the effective date of the original issue of this [EASA] AD], this AD requires using the effective date of this AD.
(2) Where paragraph (4) of EASA AD 2024-0058R2 specifies if “any discrepancy, as defined in the AOT, is identified, before next flight, contact Airbus for approved repair instructions and accomplish those instructions accordingly,” this AD requires replacing that text with “any discrepancy is detected, the discrepancy must be repaired before further flight using a method approved by the Manager, AIR-520, Continued Operational Safety 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) Paragraph (6) of EASA AD 2024-0058R2 specifies to report air leak test results to Airbus within a certain compliance time. For this AD, report test results at the applicable times specified in paragraphs (h)(3)(i) and (ii) of this AD.
(i) Report test results, except smart aircraft condition monitoring system recorder (SAR017) data, at the applicable time specified in paragraph (h)(3)(i)(A) or (B) of this AD.
(A) If the test was done on or after the effective date of this AD: Submit the report within 30 days after the test.
(B) If the test was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(ii) Report SAR017 data at the applicable time specified in paragraph (h)(3)(ii)(A) or (B) of this AD.
(A) If the test was done on or after the effective date of this AD: Submit the SAR017 data within 6 months after the completion of each air leak test and applicable corrective actions required by this AD.
(B) If the test was done before the effective date of this AD: Submit the SAR017 data within 6 months after the effective date of this AD.
(4) This AD does not adopt the “Remarks” section of EASA AD 2024-0058R2.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-520, Continued Operational Safety 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 Continued Operational Safety Branch, mail it to the address identified in paragraph (j) of this AD. Information may be emailed to: 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, AIR-520, Continued Operational Safety 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 material referenced in EASA AD 2024-0058R2 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 Dan Rodina, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3225; email: dan.rodina@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
