Rule2026-09662
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
May 14, 2026
Effective
June 18, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320 series airplanes; and Model A321-211, - 212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, - 271N, -271NX, -272N, and -272NX airplanes. This AD was prompted by a review of the cold working process on the assembly line that detected a deviation to the manufacturing process. This AD requires repetitive inspections for the nominal design condition of the fastener holes in the pressure deck membrane to center wing box attachment and, as applicable, an inspection for cracking at the affected area and corrective actions. 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 93 (Thursday, May 14, 2026)</title>
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[Federal Register Volume 91, Number 93 (Thursday, May 14, 2026)]
[Rules and Regulations]
[Pages 27183-27185]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-09662]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 91, No. 93 / Thursday, May 14, 2026 / Rules
and Regulations
[[Page 27183]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-0009; Project Identifier MCAI-2025-00436-T;
Amendment 39-23338; AD 2026-09-16]
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 A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320 series airplanes; and Model A321-211, -
212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -
271N, -271NX, -272N, and -272NX airplanes. This AD was prompted by a
review of the cold working process on the assembly line that detected a
deviation to the manufacturing process. This AD requires repetitive
inspections for the nominal design condition of the fastener holes in
the pressure deck membrane to center wing box attachment and, as
applicable, an inspection for cracking at the affected area and
corrective actions. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 18, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 18,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-0009; 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#4c0d083f0c292d3f2d6229393e233c2d622939"><span class="__cf_email__" data-cfemail="88c9ccfbc8ede9fbe9a6edfdfae7f8e9a6edfd">[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-2026-0009.
FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3520; email: <a href="/cdn-cgi/l/email-protection#2a68434646046b59424c45585e426a4c4b4b044d455c"><span class="__cf_email__" data-cfemail="e1a3888d8dcfa09289878e939589a1878080cf868e97">[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 A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320 series airplanes; and Model A321-211, -212, -213, -231, -
232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N,
and -272NX airplanes. The NPRM was published in the Federal Register on
January 12, 2026 (91 FR 1101). The NPRM was prompted by EASA AD 2025-
0066, dated March 28, 2025 (EASA AD 2025-0066) (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 a review of
the cold working process on the assembly line, a deviation to the
manufacturing process was detected, which could adversely affect the
fatigue life of the pressure deck membrane to center wing box
attachment. This condition, if not addressed, could lead to crack
initiation and propagation, resulting in reduced structural integrity
of the airplane.
In the NPRM, the FAA proposed to require repetitive inspections for
the nominal design condition of the fastener holes in the pressure deck
membrane to center wing box attachment and, as applicable, an
inspection for cracking at the affected area and corrective actions, as
specified in EASA AD 2025-0066. 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-2026-0009.
Discussion of Final Airworthiness Directive
Comments
The FAA received one comment from Delta Air Lines (Delta). The
following presents the comments received on the NPRM and the FAA's
response to each comment.
Request To Add an Exception To Clarify Nominal Diameter of Fasteners
Delta requested that the FAA add an exception to the proposed AD
clarifying the nominal design condition requirement is that the
fasteners installed have a nominal diameter of less than or equal to
4.8 mm (0.189 in.). Delta stated a note in the service information
referenced in EASA AD 2025-0066 specifies that the fasteners installed
have a nominal diameter of 4.8 mm (0.189 in.), but Airbus TechRequest
81741919 clarified the nominal design condition must be less than or
equal to 4.8 mm (0.189 in.).
FAA disagrees that an exception is needed. The FAA notes that
nominal design condition is that fasteners installed have a nominal
diameter as specified in the material referenced in EASA AD 2025-0066.
A nominal diameter of 4.8 mm (0.189 in.) does not mean the diameter
must be exactly of 4.8 mm (0.189 in.). Therefore, the FAA has not
revised this AD in response to this comment.
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
[[Page 27184]]
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 2025-0066 specifies procedures for repetitive special
detailed inspections (SDI) for any discrepancy of the fastener holes
(i.e., fastener holes that are not in nominal design condition) in the
pressure deck membrane to the center wing box attachment, under
titanium angle connection and corner brackets at frame 36, at stringer
30, both left hand and right hand sides. EASA AD 2025-0066 also
specifies procedures for a rototest inspection for any discrepancy
(i.e., cracking) at the affected area and corrective actions, as
applicable. Corrective actions include contacting Airbus for approved
repair instructions and accomplishing those instructions. EASA AD 2025-
0066 also specifies procedures for repairing fastener holes, which
would terminate the repetitive inspections.
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 477 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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Labor cost Parts cost Cost per product Cost on U.S. operators
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Up to 76 work-hours x $85 per hour = Up to $183............. Up to $6,643........... Up to $3,168,711
$6,460.
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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 *
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
1 work-hour x $85 per hour = $85 (rototest $0 $85
inspection)................................
------------------------------------------------------------------------
*The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this AD.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected operators.
The FAA has received no definitive data on which to base the cost
estimates for the optional actions specified in this AD.
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 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:
2026-09-16 Airbus SAS: Amendment 39-23338; Docket No. FAA-2026-0009;
Project Identifier MCAI-2025-00436-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 18, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model airplanes specified in
paragraphs (c)(1) through (3) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2025-0066, dated March 28, 2025 (EASA AD 2025-0066).
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
[[Page 27185]]
(2) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -
252N, -253N, -271N, -272N, and -273N airplanes.
(3) Model A321-211, -212, -213, -231, -232, -251N, -251NX, -
252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a review of the cold working process on
the assembly line that detected a deviation to the manufacturing
process. The FAA is issuing this AD to address a deviation to the
manufacturing process, which could adversely affect the fatigue life
of the pressure deck membrane to center wing box attachment. This
condition, if not addressed, could lead to crack initiation and
propagation, resulting in reduced 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 paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, EASA AD 2025-0066.
(h) Exceptions to EASA AD 2025-0066
(1) Where paragraph (2) of EASA AD 2025-0066 specifies ``any
discrepancy, as defined in the SB'', this AD requires replacing that
text with ``any fastener hole is not in nominal design condition, as
defined in the SB''.
(2) Where paragraph (3) of EASA AD 2025-0066 specifies ``no
discrepancy is detected'', this AD requires replacing that text with
``fastener holes are in nominal design condition, as defined in the
SB''.
(3) Where paragraph (4) of EASA AD 2025-0066 specifies if ``any
discrepancy is detected, as defined in the SB, before next flight,
contact Airbus for approved repair instructions and, within the
compliance time specified therein, accomplish those instructions
accordingly'', this AD requires replacing that text with ``any
cracking is detected, repair the cracking 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 paragraph (6) of EASA AD 2025-0066 specifies ``no
discrepancy'', this AD requires replacing that text with ``no
cracking''.
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0066.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2025-0066 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#12535f5d51527473733c757d64"><span class="__cf_email__" data-cfemail="febfb3b1bdbe989f9fd0999188">[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 DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (h), (i), and (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 Bill Ashforth,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3520; email: <a href="/cdn-cgi/l/email-protection#692b00050547281a010f061b1d01290f0808470e061f"><span class="__cf_email__" data-cfemail="9fddf6f3f3b1deecf7f9f0edebf7dff9fefeb1f8f0e9">[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 2025-0066,
dated March 28, 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#6223261122070311034c0717100d12034c0717"><span class="__cf_email__" data-cfemail="6524211625000416044b0010170a15044b0010">[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#2c4a5e0245425f5c494f584543426c424d5e4d024b435a"><span class="__cf_email__" data-cfemail="fb9d89d59295888b9e988f929495bb959a899ad59c948d">[email protected]</span></a>.
Issued on April 30, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-09662 Filed 5-13-26; 8:45 am]
BILLING CODE 4910-13-P
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