Rule2026-09171
Airworthiness Directives; Airbus SAS Airplanes
Primary source
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Published
May 8, 2026
Effective
May 26, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-153N airplanes; Model A320-251N, -252N, and -271N airplanes; and Model A321-251NX, -252NX, -271NX and -272NX airplanes. This AD was prompted by an Airbus supplier identifying a quality issue in production, which could result in potential deviations from the specified thickness of various fuselage panels. This AD requires, for certain airplanes, doing a "local thickness mapping," doing applicable additional instructions, a general visual inspection (GVI) of certain forward fuselage panels, a full panel thickness measurement, and applicable corrective actions. This AD also requires, for all airplanes, a dispatch restriction from using certain master minimum equipment list (MMEL) items, a prohibition to use certain structural repair manual (SRM) tasks. 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 89 (Friday, May 8, 2026)</title>
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[Federal Register Volume 91, Number 89 (Friday, May 8, 2026)]
[Rules and Regulations]
[Pages 25098-25101]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-09171]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-3871; Project Identifier MCAI-2026-00247-T;
Amendment 39-23327; AD 2026-09-06]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus SAS Model A319-153N airplanes; Model A320-251N, -252N,
and -271N airplanes; and Model A321-251NX, -252NX, -271NX and -272NX
airplanes. This AD was prompted by an Airbus supplier identifying a
quality issue in production, which could result in potential deviations
from the specified thickness of various fuselage panels. This AD
requires, for certain airplanes, doing a ``local thickness mapping,''
doing applicable additional instructions, a general visual inspection
(GVI) of certain forward fuselage panels, a full panel thickness
measurement, and applicable corrective actions. This AD also requires,
for all airplanes, a dispatch restriction from using certain master
minimum equipment list (MMEL) items, a prohibition to use certain
structural repair manual (SRM) tasks. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective May 26, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 26,
2026.
The FAA must receive comments on this AD by June 22, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
[[Page 25099]]
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-3871; 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
street address for Docket Operations is listed above.
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#9bdadfe8dbfefae8fab5feeee9f4ebfab5feee"><span class="__cf_email__" data-cfemail="1a5b5e695a7f7b697b347f6f68756a7b347f6f">[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-2026-3871.
FOR FURTHER INFORMATION CONTACT: Taylor Stanley, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 407-
852-7677; email: <a href="/cdn-cgi/l/email-protection#84d0e5fde8ebf6aad7f0e5eae8e1fdc4e2e5e5aae3ebf2"><span class="__cf_email__" data-cfemail="eabe8b93868598c4b99e8b84868f93aa8c8b8bc48d859c">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments using a method listed under
the ADDRESSES section. Include ``Docket No. FAA-2026-3871; Project
Identifier MCAI-2026-00247-T'' at the beginning of your comments. The
most helpful comments reference a specific portion of the final rule,
explain the reason for any recommended change, and include supporting
data. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this final rule.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this AD contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this AD, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this AD. Submissions containing CBI should be sent to Taylor
Stanley, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 407-852-7677; email: <a href="/cdn-cgi/l/email-protection#9bcffae2f7f4e9b5c8effaf5f7fee2dbfdfafab5fcf4ed"><span class="__cf_email__" data-cfemail="9cc8fde5f0f3eeb2cfe8fdf2f0f9e5dcfafdfdb2fbf3ea">[email protected]</span></a>.
Any commentary that the FAA receives which is not specifically
designated as CBI will be placed in the public docket for this
rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2026-0055R1, dated April 14, 2026
(EASA AD 2026-0055R1) (also referred to as the MCAI), to correct an
unsafe condition for certain Airbus SAS Model A319-153N airplanes;
Model A320-251N, -252N, and -271N airplanes; and Model A321-251NX, -
252NX, -271NX and -272NX airplanes. The MCAI states that an Airbus
supplier identified a quality issue in production, resulting in
potential deviations from the specified thickness of various fuselage
panels delivered to Airbus. The potential for certain forward fuselage
panels to have deviations from the specified thickness, in combination
with certain repairs, can affect the structural integrity of the
airplane.
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-2026-3871.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2026-0055R1 specifies procedures for doing a ``local
thickness mapping'' if the maintenance history verification determines
a ``CAT C/temporary repair'' was done, contacting Airbus to report the
repair status and any finding of that mapping and for additional
instructions, and doing applicable additional instructions. EASA AD
2026-0055R1 also specifies procedures, for certain airplanes, for a GVI
of certain forward fuselage section S12 panels for cracking and other
damage (including panel failure or irregularity), a full panel
thickness measurement, and applicable corrective actions (i.e.,
contacting the manufacturer for repair instructions and doing the
repair). EASA AD 2026-0055R1 also specifies, for all airplanes, a
dispatch restriction from using certain MMEL items, and a prohibition
to use certain SRM tasks.
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.
FAA's Determination
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 is issuing this AD
after determining that the unsafe condition described previously is
likely to exist or develop on other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in EASA AD
2026-0055R1 described previously, except for any differences identified
as exceptions in the regulatory text of this AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result,
EASA AD 2026-0055R1 is incorporated by reference in this AD. This AD
requires compliance with EASA AD 2026-0055R1 in its entirety through
that incorporation, except for any differences identified as exceptions
in the regulatory text of this AD. Using common terms that are the same
as the heading of a particular section in EASA AD 2026-0055R1 does not
mean that operators need comply only with that section. For example,
where the AD requirement refers to ``all required actions and
compliance times,'' compliance with this AD requirement is not limited
to the section titled ``Required Action(s) and Compliance Time(s)'' in
EASA AD 2026-0055R1. Material required by EASA AD 2026-0055R1 for
compliance will be available
[[Page 25100]]
at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-3871 after this AD is
published.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because the potential for certain forward fuselage panels to have
deviations from the specified thickness, in combination with certain
repairs, can affect the structural integrity of the airplane.
Additionally, the compliance time in this AD is shorter than the time
necessary for the public to comment and for publication of the final
rule. Accordingly, notice and opportunity for prior public comment are
impracticable and contrary to the public interest pursuant to 5 U.S.C.
553(b).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 24 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
33 work-hours x $85 per hour = $2,720........................ $0 $2,720 $65,280
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
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Up to 8 work-hours x $85 per hour $0 Up to $680.
= $680.
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Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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, and
(2) Will not affect intrastate aviation in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 25101]]
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:
2026-09-06 Airbus SAS: Amendment 39-23327; Docket No. FAA-2026-3871;
Project Identifier MCAI-2026-00247-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 26, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A319-153N airplanes; Model
A320-251N, -252N, and -271N airplanes; and Model A321-251NX, -252NX,
-271NX and -272NX airplanes; certificated in any category, as
identified in European Union Aviation Safety Agency (EASA) AD 2026-
0055R1, dated April 14, 2026 (EASA AD 2026-0055R1).
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an Airbus supplier identifying a quality
issue in production, which could result in potential deviations from
the specified thickness of various fuselage panels delivered to
Airbus. The FAA is issuing this AD to address the potential for
certain forward fuselage panels to have deviations from the
specified thickness, which, in combination with certain repairs, can
affect the structural integrity 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 2026-0055R1.
(h) Exceptions to EASA AD 2026-0055R1
(1) Where EASA AD 2026-0055R1 refers to March 20, 2026 (the
effective date of EASA AD 2026-0055, dated March 13, 2026), this AD
requires using the effective date of this AD.
(2) Where paragraph (1) of EASA AD 2026-0055R1 specifies to
``accomplish the `local thickness mapping' '', for this AD replace
that text with ``accomplish the `local thickness mapping', as
applicable''.
(3) Where paragraph (4) of EASA AD 2026-0055R1 specifies ``if
any crack is identified on an affected panel, before next flight,
contact Airbus for approved instructions and within the compliance
time identified therein, accomplish those instructions
accordingly'', this AD requires replacing that text with ``if any
cracking or other damage is detected, the cracking and other damage
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''.
(4) Where the service information referenced in EASA AD 2026-
0055R1 specifies to send an inspection report to Airbus if the
measured thicknesses are within the drawing tolerances, or if the
airplane can be released permanently with the panel condition
acceptable as-is following the Airbus assessment, for this AD, send
the report at the applicable time specified in paragraph (h)(4)(i)
or (ii) of this AD.
(i) If the finding was made on or after the effective date of
this AD: Submit the report within 14 days after the finding.
(ii) If the finding was made before the effective date of this
AD: Submit the report within 14 days after the effective date of
this AD.
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2026-0055R1.
(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#1b5a5654585b7d7a7a357c746d"><span class="__cf_email__" data-cfemail="de9f93919d9eb8bfbff0b9b1a8">[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 referenced in EASA AD
2026-0055R1 that 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.
(j) Additional Information
For more information about this AD, contact Taylor Stanley,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 407-852-7677; email: <a href="/cdn-cgi/l/email-protection#3d695c4451524f136e495c535158447d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="ecb88d9580839ec2bf988d82808995ac8a8d8dc28b839a">[email protected]</span></a>.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) 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 2026-0055R1,
dated April 14, 2026.
(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#bafbfec9fadfdbc9db94dfcfc8d5cadb94dfcf"><span class="__cf_email__" data-cfemail="2465605764414557450a4151564b54450a4151">[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#c9afbbe7a0a7bab9acaabda0a6a789a7a8bba8e7aea6bf"><span class="__cf_email__" data-cfemail="82e4f0acebecf1f2e7e1f6ebedecc2ece3f0e3ace5edf4">[email protected]</span></a>.
Issued on April 24, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-09171 Filed 5-6-26; 4:15 pm]
BILLING CODE 4910-13-P
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