Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 91, Number 21 (Monday, February 2, 2026)]
[Rules and Regulations]
[Pages 4445-4447]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-02098]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-1120; Project Identifier MCAI-2025-00019-T; 
Amendment 39-23250; AD 2026-03-01]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: 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.

DATES: This AD is effective March 9, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 9, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2025-1120; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
    <bullet> For European Union Aviation Safety Agency (EASA) material 
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 
Cologne, Germany; telephone +49 221 8999 000; email [email protected]. 
You may find this material on the EASA website at ad.easa.europa.eu.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available at regulations.gov under 
Docket No. FAA-2025-1120.

FOR FURTHER INFORMATION CONTACT: Kin Suen Chan, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 847-
294-7496; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus SAS Model 
A350-941 and -1041 airplanes. The NPRM was published in the Federal 
Register on June 27, 2025 (90 FR 27485). The NPRM was prompted by AD 
2025-0008, dated January 9, 2025 (EASA AD 2025-0008) (also referred to 
as the MCAI), issued by EASA, which is the Technical Agent for the 
Member States of the European Union. The MCAI states occurrences of 
ECAM messages requiring FCRM replacement have been reported, and 
further investigation identified an issue linked to solder structural 
fatigue. This condition, if not corrected, could lead to failure of a 
flight control actuator, possibly resulting in reduced control of the 
airplane.
    In the NPRM, the FAA proposed to require replacement of affected 
parts before exceeding the life limit and limit the installation of 
affected parts under certain conditions, as specified in EASA AD 2025-
0008. The FAA is issuing this AD to address the unsafe condition on 
these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2025-1120.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from Air Line Pilots Association, 
International (ALPA) who supported the NPRM without change.
    The FAA received additional comments from Delta Air Lines (Delta) 
and the Foundation for Aviation Safety. The following presents the 
comments received on the NPRM and the FAA's response to each comment.

Request To Replace Parts Using Standard Maintenance Procedures

    Delta requested the FAA confirm that the proposed AD would only 
require replacing each affected part with a serviceable part within the 
compliance time specified in table 1 of EASA AD 2025-0008 and testing 
the installed serviceable part in accordance with paragraph 3.E. of 
Airbus Service Bulletin A350-27-P066, dated November 12, 2024. Delta 
stated that if this is correct, then using standard maintenance manuals 
instead of the Airbus service bulletin would provide an acceptable 
level of safety. Delta noted the service bulletin also specifies 
collecting FCRM part and serial numbers but reporting of that 
information is not mandatory according to paragraph (i) of the proposed 
AD. Delta concluded that allowing operators to use standard maintenance 
manuals and maintenance records to replace affected parts will provide 
more flexibility to address the safety condition.
    The FAA confirms this AD requires replacing each affected part with 
a serviceable part within the applicable compliance time specified in 
table 1 of EASA AD 2025-0008, except as provided by paragraph (h)(1) of 
this AD. This AD also requires testing each installed serviceable part 
in accordance with paragraph 3.E. of the Airbus service bulletin and 
limits the installation of affected parts under certain conditions. The 
FAA notes the replacement and testing procedures in paragraphs 3.C. and 
3.E. of the Airbus service bulletin refer to the applicable A350 
maintenance procedures. If an operator would like to use other 
maintenance procedures not referenced in the Airbus service bulletin, 
the FAA will consider requests for alternative methods of compliance 
(AMOCs) under the provisions of paragraph (j)(1) of this AD. The FAA 
has not changed this AD in regard to this comment.

Request To Clarify Condition for Replacement

    Delta requested the FAA add an exception to paragraph (h) of the 
proposed AD to clarify the condition in paragraph 3.C(1)(a)1c of Airbus 
Service Bulletin A350-27-P066, dated November 12, 2024, for when the 
replacement of the FCRMs must be done. Delta stated it is not clear 
whether that paragraph requires replacement when any FCRM reaches the 
threshold,

[[Page 4446]]

or all 22 FCRMs reach it. Delta noted paragraph (1) of EASA AD 2025-
0008 and paragraph (h)(3) of the proposed AD imply each FCRM must be 
replaced prior to reaching the threshold, and replacement of the other 
FCRMs may be postponed until closer to their thresholds.
    The FAA agrees that this AD requires replacement of each affected 
FCRM before it reaches the life limit required by this AD, and that all 
22 FCRMs may not need to be replaced at the same time. Additionally, 
the FAA notes that the requirements of the AD take precedence over any 
instructions specified in the referenced Airbus service bulletin. 
Operators must comply with the requirements of this AD and use the 
relevant procedures in the Airbus service bulletin to replace an 
affected FCRM and test the installed serviceable FCRM. The FAA has 
determined no change to this AD is necessary in this regard.

Request To Clarify Inspection Requirement for FCRMs With Different 
Conditions

    Delta requested the FAA add exceptions to paragraph (h) of the 
proposed AD to clarify that the procedures in paragraphs 3.C(1)(a)2, 4, 
and 5 of Airbus Service Bulletin A350-27-P066, dated November 12, 2024, 
apply if any of the 22 FCRMs meet the conditions of those paragraphs. 
Delta stated it is not clear whether the procedures in those paragraphs 
should be accomplished if all or any of the 22 FCRMs meet the 
conditions of those paragraphs. Delta also stated that access to the 
FCRMs and replacement should be based on each affected part and not the 
condition of all 22 FCRMs.
    The FAA agrees with Delta's interpretation of paragraphs 
3.C(1)(a)2, 4, and 5 in the Airbus service bulletin, but has determined 
that no change to this AD is necessary in this regard. The FAA notes 
that this AD does not require the inspection procedures in the Airbus 
service bulletin. Instead, this AD requires replacement of each 
affected FCRM, as defined in EASA AD 2025-0008, before it reaches the 
life limit required by this AD. To comply with the requirements of this 
AD, operators must use the relevant procedures in the Airbus service 
bulletin to replace an affected FCRM and test the installed serviceable 
FCRM.

Request To Identify Root Cause and Prevention of Component Failure

    The Foundation for Aviation Safety asked what the root cause of the 
component failure is and what is being done to prevent this from 
happening in the future.
    As noted in EASA AD 2025-0008, investigation of the reported FCRM 
failures identified an issue linked to solder structural fatigue in the 
affected FCRMs. Safety analysis conducted by Airbus demonstrated that 
the FCRM failure rate increases with part utilization (i.e., the number 
of accumulated in-service flight cycles and/or flight hours), and that 
the FCRMs must be replaced before reaching 9,000 flight cycles (FC) or 
50,000 flight hours (FH), whichever occurs first. To prevent failure of 
an affected FCRM from occurring in the future, the FAA is requiring 
operators to replace each affected FCRM before it exceeds the life 
limit of 9,000 FC or 50,000 FH, whichever occurs first. The FAA also 
requires testing of any serviceable part installed on an airplane prior 
to returning the airplane to service.

Conclusion

    These products have been approved by the civil aviation authority 
of another country and are approved for operation in the United States. 
Pursuant to the FAA's bilateral agreement with this State of Design 
Authority, that authority has notified the FAA of the unsafe condition 
described in the MCAI referenced above. The FAA reviewed the relevant 
data, considered any comments received, and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these products. Except for 
minor editorial changes, this AD is adopted as proposed in the NPRM. 
None of the changes will increase the economic burden on any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2025-0008, which specifies procedures for 
replacing affected FCRMs with serviceable FCRMs and testing the 
serviceable FCRMs. EASA AD 2025-0008 also limits the installation of 
affected parts under certain conditions. This material is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 35 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
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                                                          Cost per
              Labor cost                 Parts cost        product               Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85.....         $28,000         $28,085  $982,975 (per FCRM).
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities

[[Page 4447]]

under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2026-03-01 Airbus SAS: Amendment 39-23250; Docket No. FAA-2025-1120; 
Project Identifier MCAI-2025-00019-T.

(a) Effective Date

    This airworthiness directive (AD) is effective March 9, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A350-941 and -1041 
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Unsafe Condition

    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. The 
FAA is issuing this AD to address potential failure of a flight 
control actuator. The unsafe condition, if not addressed, could 
result in reduced control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Requirements

    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).

(h) Exceptions to 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.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0008 specifies 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

(j) Additional AD Provisions

    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: 
[email protected]. 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.

(k) Additional Information

    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: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless this AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2025-0008, 
dated January 9, 2025.
    (ii) [Reserved]
    (3) For EASA material identified in this AD, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]. You may find this material on 
the EASA website at ad.easa.europa.eu.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., 
Des Moines, WA. For information on the availability of this material 
at the FAA, call 206-231-3195.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on January 27, 2026.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2026-02098 Filed 1-30-26; 8:45 am]
BILLING CODE 4910-13-P

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