Rule2026-11510
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 9, 2026
Effective
July 14, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2022-02- 11, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, 216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2022-02-11 required repetitive rototest inspections of the holes at the door stop fittings for any cracking and repair if necessary. Since the FAA issued AD 2022-02-11, it was determined that additional airplane models must be added to the applicability and the terminating action for repaired affected areas must be clarified. This AD continues to require the actions in AD 2022-02-11 and expands the applicability. 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 110 (Tuesday, June 9, 2026)</title>
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[Federal Register Volume 91, Number 110 (Tuesday, June 9, 2026)]
[Rules and Regulations]
[Pages 34743-34746]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-11510]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-2281; Project Identifier MCAI-2025-00915-T;
Amendment 39-23372; AD 2026-12-02]
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 superseding Airworthiness Directive (AD) 2022-02-
[[Page 34744]]
11, which applied to certain Airbus SAS Model A318 series airplanes;
Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320-211, -212, -214, 216, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
AD 2022-02-11 required repetitive rototest inspections of the holes at
the door stop fittings for any cracking and repair if necessary. Since
the FAA issued AD 2022-02-11, it was determined that additional
airplane models must be added to the applicability and the terminating
action for repaired affected areas must be clarified. This AD continues
to require the actions in AD 2022-02-11 and expands the applicability.
The FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective July 14, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 14,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-2281; 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#b4f5f0c7f4d1d5c7d59ad1c1c6dbc4d59ad1c1"><span class="__cf_email__" data-cfemail="4203063102272331236c2737302d32236c2737">[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-2026-2281.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3225;
email: <a href="/cdn-cgi/l/email-protection#06626768287469626f68674660676728616970"><span class="__cf_email__" data-cfemail="debabfb0f0acb1bab7b0bf9eb8bfbff0b9b1a8">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2022-02-11, Amendment 39-21908 (87 FR 7033,
February 8, 2022) (AD 2022-02-11). AD 2022-02-11 was prompted by EASA
AD 2018-0289R1, dated February 10, 2021 (EASA AD 2018-0289R1), issued
by EASA, which is the Technical Agent for the Member States of the
European Union. AD 2022-02-11 applied to certain Airbus SAS Model A318
series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes. AD 2022-02-11 required repetitive rototest
inspections of the holes at the door stop fittings for any cracking and
repair if necessary. The FAA issued AD 2022-02-11 to address cracking
of the web holes at the door stop fittings, which could affect the
structural integrity of the airplane.
The NPRM was published in the Federal Register on February 25, 2026
(91 FR 9202). The NPRM was prompted by EASA AD 2025-0111, dated May 14,
2025 (EASA AD 2025-0111) (also referred to as the MCAI). The MCAI
states, after issuance of EASA AD 2018-0289R1, Airbus revised the
inspection and modification service bulletins. The inspection service
bulletin now refers to newly developed structural repair manual tasks
as corrective action for certain findings for current engine option
(CEO) airplanes, with no need for specific repair instructions from
Airbus. Further, it was decided, for new engine option (NEO) airplanes,
the applicable airworthiness limitations item tasks should be replaced
with the applicable inspection and modification service bulletins.
In the NPRM, the FAA proposed to continue to require the actions in
AD 2022-02-11, as specified in EASA AD 2025-0111 and to expand the
applicability by adding Airbus SAS Model A319-151N, -153N, -171N, and -
173N airplanes; Model A320-251N, -252N, -253N, -271N, -272N, and -273N
airplanes; and Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -
253NY, -271N, -271NX, -271NY, -272N, and -272NX airplanes. 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-2026-2281.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from an individual who supported the
NPRM without change.
The FAA received an additional comment from American Airlines
(American). The following presents the comment received on the NPRM and
the FAA's response to the comment.
Request To Revise the Applicability
American requested the FAA add an exception to this AD that
specifies airplanes having the modification service bulletin (defined
in EASA AD 2025-0111) embodied after 6,100 flight cycles since airplane
first flight but prior to the effective date of this AD are considered
applicable to this AD, but terminated for the repetitive requirements
of this AD. American is concerned that excluding airplanes, which were
applicable to AD 2022-02-11 but had the modification (terminating
action for the repetitive inspections) accomplished under the authority
of AD 2022-02-11 prior to the effective date of this AD, could
unintentionally be misleading as to the true status (modified) of those
airplanes.
The FAA disagrees with the request. Operators should have records
documenting accomplishment of the modification. Those records will show
that the repetitive inspections required by AD 2022-02-11 were
terminated by the modification, and that this AD does not apply to the
modified airplane. Therefore, no change to this AD is necessary in this
regard.
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 2025-0111 specifies procedures for performing repetitive
[[Page 34745]]
rototest inspections of the door stop fitting holes at positions 1 and
7 at fuselage frame (FR) 16 and FR20 on left- and right-hand sides,
respectively, for any cracking and repair if necessary.
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 1,979 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 on U.S.
Action Labor cost Parts cost Cost per product operators
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Retained actions from AD 2022-02- Up to 33 work-hours $0 Up to $2,805........ Up to $3,823,215.
11 (1,363 CEO airplanes). x $85 per hour =
$2,805.
Repetitive inspections (616 NEO Up to 34 work-hours 0 Up to $2,890........ Up to $1,780,240.
airplanes). x $85 per hour =
$2,890.
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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 this on-condition action:
Estimated Costs of On-Condition Actions
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Labor cost Parts cost Cost per product
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51 work-hours x $85 per hour = $350 $4,685
$4,335.......................
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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,
(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:
0
a. Removing Airworthiness Directive (AD) 2022-02-11, Amendment 39-21908
(87 FR 7033, February 8, 2022); and
0
b. Adding the following new AD:
2026-12-02 Airbus SAS: Amendment 39-23372; Docket No. FAA-2026-2281;
Project Identifier MCAI-2025-00915-T.
(a) Effective Date
This airworthiness directive (AD) is effective July 14, 2026.
(b) Affected ADs
This AD replaces AD 2022-02-11, Amendment 39-21908 (87 FR 7033,
February 8, 2022) (AD 2022-02-11).
(c) Applicability
This AD applies to Airbus SAS airplanes identified in paragraphs
(c)(1) through (4) of this AD, certificated in any category, as
identified in European Union Aviation Safety Agency (EASA) AD 2025-
0111, dated May 14, 2025 (EASA AD 2025-0111).
(1) Model A318-111, -112, -121, and -122 airplanes.
[[Page 34746]]
(2) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -
151N, -153N, -171N, and -173N airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -
252N, -253N, -271N, -272N, and -273N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -
251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -
271NY, -272N, and -272NX airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report that cracks were detected on
frame (FR) 16 and FR20 web holes and passenger door intercostal
fitting holes at the door stop fitting locations, and a
determination that a certain compliance time must be clarified. This
AD was also prompted by a determination that additional airplane
models must be added to the applicability and the terminating action
for repaired affected areas must be clarified. The FAA is issuing
this AD to address cracking of the web holes at the door stop
fittings. The unsafe condition, if not addressed, could 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 2025-0111.
(h) Exceptions to EASA AD 2025-0111
(1) Where EASA AD 2025-0111 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where table 1 of EASA AD 2025-0111 specifies a compliance
time of ``Before exceeding 30[,]000 FC since aeroplane first
flight,'' this AD requires, for the inspection at frame 16 only,
using a compliance time of ``Before exceeding 30,000 flight cycles
since airplane's first flight, or within 30 days after March 15,
2022 (the effective date of AD 2022-02-11), whichever occurs
later.''
(3) Where table 1 of EASA AD 2025-0111 refers to a compliance
time ``after 31 May 2017 [reference date for the compliance time
included in ALS Part 2 rev. 6]'', this AD requires using a
compliance time after ``May 31, 2018 (the effective date of task
531103-01-1 in ``ALS Part 2 rev. 6'').''
(4) Where paragraph (3) of EASA AD 2025-0111 specifies
``repaired in accordance with Airbus approved repair instructions,
accomplish the next due inspection of each repaired affected area in
accordance with, and within the compliance time as specified in,
Airbus approved repair instructions, as applicable'', this AD
requires replacing that text with ``repaired 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),
provided the DOA approval includes the DOA-authorized signature:
Accomplish the next due inspection of each repaired area in
accordance with, and within the compliance time specified in, the
applicable approved repair instructions''.
(5) Where paragraph (4) of EASA AD 2025-0111 specifies ``cracks
are detected'', this AD requires replacing that text with ``any
crack is detected''.
(6) Where the applicable inspection service bulletin referenced
in EASA AD 2025-0111 specifies to report findings and completion of
all inspections, as applicable, this AD requires reporting only if
the cracked intercostal(s) have been replaced using repair
instruction R53113118, R53113626, or R53113627, as applicable.
Report results at the applicable time specified in paragraph (6)(i)
or (ii) of this AD. If operators have reported findings as part of
obtaining any corrective actions approved by Airbus SAS's EASA DOA,
operators are not required to report those findings as specified in
this paragraph.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(7) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0111.
(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#fbbab6b4b8bb9d9a9ad59c948d"><span class="__cf_email__" data-cfemail="17565a58545771767639707861">[email protected]</span></a>.
(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
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 Dan Rodina, Aviation
Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198;
phone: 206-231-3225; email: <a href="/cdn-cgi/l/email-protection#ff9b9e91d18d909b96919ebf999e9ed1989089"><span class="__cf_email__" data-cfemail="85e1e4ebabf7eae1ecebe4c5e3e4e4abe2eaf3">[email protected]</span></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 2025-0111,
dated May 14, 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#88c9ccfbc8ede9fbe9a6edfdfae7f8e9a6edfd"><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#ed8b9fc384839e9d888e99848283ad838c9f8cc38a829b"><span class="__cf_email__" data-cfemail="3157431f585f4241545245585e5f715f5043501f565e47">[email protected]</span></a>.
Issued on June 4, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-11510 Filed 6-8-26; 8:45 am]
BILLING CODE 4910-13-P
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