Rule2026-11215
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
June 4, 2026
Effective
July 9, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a determination that double overcoating sealant was not applied during production on certain fasteners in the center wing box (CWB) and belly faring junction for both left-hand (LH) and right-hand (RH) sides, and certain fasteners are also susceptible to rotation. This AD requires replacing each affected part and applying additional head nut cap protection. 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 107 (Thursday, June 4, 2026)</title>
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[Federal Register Volume 91, Number 107 (Thursday, June 4, 2026)]
[Rules and Regulations]
[Pages 33593-33595]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-11215]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-2280; Project Identifier MCAI-2025-01562-T;
Amendment 39-23369; AD 2026-11-08]
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
certain Airbus SAS Model A350-941 airplanes.
[[Page 33594]]
This AD was prompted by a determination that double overcoating sealant
was not applied during production on certain fasteners in the center
wing box (CWB) and belly faring junction for both left-hand (LH) and
right-hand (RH) sides, and certain fasteners are also susceptible to
rotation. This AD requires replacing each affected part and applying
additional head nut cap protection. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective July 9, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 9,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-2280; 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#4f0e0b3c0f2a2e3c2e612a3a3d203f2e612a3a"><span class="__cf_email__" data-cfemail="3c7d784f7c595d4f5d1259494e534c5d125949">[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-2026-2280.
FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: (206)
231-3553; email: <a href="/cdn-cgi/l/email-protection#87d3e6ece6efeef4e6a9cce8e5e6fee6f4efeec7e1e6e6a9e0e8f1"><span class="__cf_email__" data-cfemail="f7a3969c969f9e8496d9bc9895968e96849f9eb7919696d9909881">[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 certain Airbus SAS
Model A350-941 airplanes. The NPRM was published in the Federal
Register on February 25, 2026 (91 FR 9199). The NPRM was prompted by
EASA AD 2025-0210, dated September 24, 2025 (EASA AD 2025-0210) (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 that
during production some fasteners located at the junction between the
CWB lower panel and the belly fairing fittings on both LH and RH sides
may have been installed without double overcoating sealant; in
addition, some fasteners EN6115 code B have been installed, which are
susceptible to rotation. This condition, if not corrected, could lead
to loss of fastener clamping and crack of nut sealant cover, possibly
resulting, in the case of a lightning strike, in a risk of a fuel tank
explosion and consequent loss of the airplane.
In the NPRM, the FAA proposed to require replacing each affected
part and applying additional head nut cap protection, as specified in
EASA AD 2025-0210. 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-2026-2280.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from the Airline Pilots Association,
International (ALPA) who supported the NPRM without change.
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
EASA AD 2025-0210 specifies procedures for replacing fasteners
installed at Frame (FR) 46 and FR 49 on the LH and RH sides of the CWB
and for applying additional head nut cap protection (e.g., applying
sealant and corrosion inhibiting fastener head protection). 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 5 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Labor cost Parts cost product operators
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64 work-hours x $85 per hour = $5,440........................ $480 $5,920 $29,600
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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
[[Page 33595]]
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 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:
2026-11-08 Airbus SAS: Amendment 39-23369; Docket No. FAA-2026-
2280; Project Identifier MCAI-2025-01562-T.
(a) Effective Date
This airworthiness directive (AD) is effective July 9, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A350-941 airplanes,
certificated in any category, as identified in European Union
Aviation Safety Agency (EASA) AD 2025-0210, dated September 24, 2025
(EASA AD 2025-0210).
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a determination that double overcoating
sealant was not applied during production on certain fasteners in
the center wing box and belly faring junction for both left-hand and
right-hand sides, and certain fasteners are susceptible to rotation.
The FAA is issuing this AD to address incorrect fastener
installation. This unsafe condition, if not addressed, could result
in loss of fastener clamping and crack of nut sealant cover,
possibly resulting, in the case of a lightning strike, in a risk of
a fuel tank explosion and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2025-0210.
(h) Exceptions to EASA AD 2025-0210
(1) Where EASA AD 2025-0210 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where the definition of ``Affected part'' in EASA AD 2025-
0210 specifies ``as specified in the SB'', this AD requires
replacing that text with ``as specified in Airbus Service Bulletin
A350-57-P094, dated June 17, 2025''.
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0210.
(i) 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 (j) of this AD and email to:
<a href="/cdn-cgi/l/email-protection#53121e1c10133532327d343c25"><span class="__cf_email__" data-cfemail="0e4f43414d4e686f6f20696178">[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 (i)(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.
(j) Additional Information
For more information about this AD, contact Tak Kobayashi,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: (206) 231-3553; email: <a href="/cdn-cgi/l/email-protection" class="__cf_email__" data-cfemail="a1d5c0cac0c9c8d2c08fcacec3c0d8c0d2c9c8e1c7c0c08fc6ced7">[email protected]</a>.
(k) 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 2025-0210,
dated September 24, 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#c68782b586a3a7b5a7e8a3b3b4a9b6a7e8a3b3"><span class="__cf_email__" data-cfemail="4a0b0e390a2f2b392b642f3f38253a2b642f3f">[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#91f7e3bff8ffe2e1f4f2e5f8feffd1fff0e3f0bff6fee7"><span class="__cf_email__" data-cfemail="e68094c88f8895968385928f8988a688879487c8818990">[email protected]</span></a>.
Issued on May 22, 2026.
Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-11215 Filed 6-3-26; 8:45 am]
BILLING CODE 4910-13-P
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