Rule2026-02098
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
February 2, 2026
Effective
March 9, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 91 Issue 21 (Monday, February 2, 2026)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="http://regulations.gov">regulations.gov</a> 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 <a href="/cdn-cgi/l/email-protection#93d2d7e0d3f6f2e0f2bdf6e6e1fce3f2bdf6e6"><span class="__cf_email__" data-cfemail="9bdadfe8dbfefae8fab5feeee9f4ebfab5feee">[email protected]</span></a>.
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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#f59e9c9bdb8680909bdb969d949bb5939494db929a83"><span class="__cf_email__" data-cfemail="cba0a2a5e5b8beaea5e5a8a3aaa58badaaaae5aca4bd">[email protected]</span></a>.
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 <a href="http://regulations.gov">regulations.gov</a> 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
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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:
<a href="/cdn-cgi/l/email-protection#5e1f13111d1e383f3f70393128"><span class="__cf_email__" data-cfemail="682925272b280e0909460f071e">[email protected]</span></a>. 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: <a href="/cdn-cgi/l/email-protection#274c4e49095452424909444f46496741464609404851"><span class="__cf_email__" data-cfemail="2e454740005d5b4b40004d464f406e484f4f00494158">[email protected]</span></a>.
(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 <a href="/cdn-cgi/l/email-protection#99d8ddead9fcf8eaf8b7fcecebf6e9f8b7fcec"><span class="__cf_email__" data-cfemail="e8a9ac9ba88d899b89c68d9d9a879889c68d9d">[email protected]</span></a>. 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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#1472663a7d7a67647177607d7b7a547a7566753a737b62"><span class="__cf_email__" data-cfemail="88eefaa6e1e6fbf8edebfce1e7e6c8e6e9fae9a6efe7fe">[email protected]</span></a>.
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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