Proposed Rule2026-03793
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 25, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2022-02-11, which applies 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 requires 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 proposed AD would continue to require the actions in AD 2022-02-11 and expand the applicability. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 37 (Wednesday, February 25, 2026)</title>
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[Federal Register Volume 91, Number 37 (Wednesday, February 25, 2026)]
[Proposed Rules]
[Pages 9202-9205]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-03793]
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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]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2022-02-11, which applies 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 requires 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
proposed AD would continue to require the actions in AD 2022-02-11 and
expand the applicability. The FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by April 13,
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.
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 NPRM, 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 proposed AD, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#7031340330151103115e1505021f00115e1505"><span class="__cf_email__" data-cfemail="97d6d3e4d7f2f6e4f6b9f2e2e5f8e7f6b9f2e2">[email protected]</span></a>. You may find this material on the EASA website at
ad.easa.europa.eu. It is also available at <a href="http://regulations.gov">regulations.gov</a> under Docket
No. FAA-2026-2281.
<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.
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#d1b5b0bfffa3beb5b8bfb091b7b0b0ffb6bea7"><span class="__cf_email__" data-cfemail="6a0e0b044418050e03040b2a0c0b0b440d051c">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2026-2281;
Project Identifier MCAI-2025-00915-T'' at the beginning of your
comments. The most helpful comments reference a specific portion of the
proposal, 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 proposal 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 NPRM.
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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to 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#1276737c3c607d767b7c73527473733c757d64"><span class="__cf_email__" data-cfemail="36525758184459525f58577650575718515940">[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
The FAA issued AD 2022-02-11, Amendment 39-21908 (87 FR 7033,
February 8, 2022) (AD 2022-02-11), for certain Airbus SAS Model A318-
111, -112, -121, and -122 airplanes; 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 was prompted by an MCAI
originated by EASA, which is the Technical Agent for the Member States
of the European Union. EASA issued AD 2018-0289R1, dated February 10,
2021 (EASA AD 2018-0289R1), to correct an unsafe condition.
AD 2022-02-11 requires 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.
Actions Since AD 2022-02-11 Was Issued
Since the FAA issued AD 2022-02-11, EASA superseded EASA AD 2018-
0289R1 and issued EASA AD 2025-0111, dated May 14, 2025 (EASA AD 2025-
0111) (also referred to as the MCAI), to correct an unsafe condition
for all Airbus SAS Model A318-111, -112, -121, and -122 airplanes;
Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N,
-171N, and -173N airplanes; Model A320-211, -212, -214, -215, -216, -
231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, -
232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -
271NX, -271NY, -272N, and -272NX airplanes. Model A320-215 airplanes
are not certificated by the FAA and are
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not included on the U.S. type certificate data sheet; this proposed AD
therefore does not include those airplanes in the applicability. 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. EASA
AD 2025-0111 retains the requirements of EASA AD 2018-0289R1, expands
the applicability to the NEO fleet, and provides clarification on the
terminating action for repaired affected areas.
The FAA is proposing 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.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2022-02-11, this proposed AD would retain all of the
requirements of AD 2022-02-11. Those requirements are referenced in
EASA AD 2025-0111, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2025-0111, which specifies procedures for
performing repetitive 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.
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 NPRM
after determining that the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would retain all requirements of AD 2022-02-11.
This proposed AD would require accomplishing the actions specified in
EASA AD 2025-0111 described previously, as incorporated by reference,
except for any differences identified as exceptions in the regulatory
text of this proposed 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, the
FAA proposes to incorporate EASA AD 2025-0111 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2025-0111 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2025-0111 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 2025-
0111. Material required by EASA AD 2025-0111 for compliance will be
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-2281 after the
FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,979 airplanes of U.S. registry. The FAA estimates the
following costs to comply with this proposed 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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Cost per
Labor cost Parts cost product
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51 work-hours x $85 per hour = $4,335. $350 $4,685
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[[Page 9204]]
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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus SAS: Docket No. FAA-2026-2281; Project Identifier MCAI-2025-
00915-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by April 13, 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.
(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
[[Page 9205]]
instruction R53113118, R53113626, or R53113627, as applicable.
Report results at the applicable time specified in paragraph
(6)(7)(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#ecada1a3afac8a8d8dc28b839a"><span class="__cf_email__" data-cfemail="0f4e42404c4f696e6e21686079">[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#a8ccc9c686dac7ccc1c6c9e8cec9c986cfc7de"><span class="__cf_email__" data-cfemail="bcd8ddd292ced3d8d5d2ddfcdadddd92dbd3ca">[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#3071744370555143511e5545425f40511e5545"><span class="__cf_email__" data-cfemail="3e7f7a4d7e5b5f4d5f105b4b4c514e5f105b4b">[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#5036227e393e2320353324393f3e103e3122317e373f26"><span class="__cf_email__" data-cfemail="462034682f2835362325322f2928062827342768212930">[email protected]</span></a>.
Issued on February 23, 2026.
Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-03793 Filed 2-24-26; 8:45 am]
BILLING CODE 4910-13-P
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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.