Airworthiness Directive · Amendment 39-23250 · 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 adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of electronic centralized aircraft monitor (ECAM) messages requiring flight control remote module (FCRM) replacement linked to solder structural fatigue. This AD requires replacement of affected parts before exceeding the life limit and limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2025-0008, dated January 9, 2025 (EASA AD 2025-0008).
(1) Where EASA AD 2025-0008 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2025-0008 defines a serviceable part as an “FCRM, eligible for installation in accordance with Airbus instructions, which is not an affected part; or an affected part that has accumulated less than 9 000 flight cycles (FC) and less than 50 000 flight hours (FH) since first installation on any aeroplane (see Note 1 of this AD)”, this AD requires replacing that text with “FCRM, eligible for installation, which is not an affected part; or an affected part that has accumulated less than 9,000 flight cycles (FC) and less than 50,000 flight hours (FH) since first installation on any airplane (see Note 1 of this AD)”.
(3) Where paragraph (1) of EASA AD 2025-0008 specifies to “replace each affected part with a serviceable part, as defined in this AD, in accordance with the instructions of the SB”, this AD requires replacing that text with “replace each affected part with a serviceable part, as defined in this AD, and test in accordance with paragraph 3.E. of the Accomplishment Instructions of the SB”.
(4) Where paragraph (2) of EASA AD 2025-0008 specifies “the affected part is replaced as required by paragraph (1)”, this AD requires replacing that text with “the affected part is replaced with a serviceable part at the applicable time specified in row A of Table 1”.
(5) This AD does not adopt the “Remarks” section of EASA AD 2025-0008.
Although the material referenced in EASA AD 2025-0008 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, 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, send it to the attention of the person identified in paragraph (k) of this AD and email 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 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 material 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 Kin Suen Chan, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 847-294-7496; email: kin.suen.chan@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
