[Federal Register Volume 91, Number 103 (Friday, May 29, 2026)]
[Rules and Regulations]
[Pages 31889-31893]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-10800]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-4645; Project Identifier MCAI-2026-00451-T;
Amendment 39-23365; AD 2026-11-04]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 31890]]
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus SAS Model A319 series airplanes; Model A320 series airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -
252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX
airplanes. This AD was prompted by aeroelastic stability assessments
that indicate that reduced stability margins may exist due to
accumulation of additional mass from rudder repainting or repairs. This
AD requires airframe vibration troubleshooting after an airframe
vibration event, reporting results, and applicable on-condition
actions. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective June 15, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 15,
2026.
The FAA must receive comments on this AD by July 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:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: 202-493-2251.
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.
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 regulations.gov under
Docket No. FAA-2026-4645; 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:
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 [email protected].
You may find this material on the EASA website at ad.easa.europa.eu.
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 regulations.gov under
Docket No. FAA-2026-4645.
FOR FURTHER INFORMATION CONTACT: Frank Carreras, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3539; email: [email protected].
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-2026-4645; Project
Identifier MCAI-2026-00451-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
regulations.gov, 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 Frank
Carreras, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 206-231-3539; email: [email protected].
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 2026-0083, dated April 22, 2026
(EASA AD 2026-0083) (also referred to as the MCAI), to correct an
unsafe condition for all Airbus SAS Model A319 series airplanes; Model
A320 series airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -
253NX, -271NX, and -272NX airplanes. Model A320-215 airplanes are not
certificated by the FAA and are not included on the U.S. type
certificate data sheet; this AD therefore does not include those
airplanes in the applicability. The MCAI states that aeroelastic
stability assessments indicate that reduced stability margins may exist
due to accumulation of additional mass from rudder repainting or
repairs. This condition, if not addressed, could, in combination with a
rudder actuator disconnection, result in potential risk of flutter,
possibly leading to reduced control 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 regulations.gov under
Docket No. FAA-2026-4645.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2026-0083 specifies procedures for accomplishing airframe
vibration troubleshooting after an airframe vibration event, reporting
results, and applicable on-condition actions. On-condition actions
include the following:
Operational test of the rudder servo controls with
individual hydraulic system.
Contacting Airbus for further instructions and doing the
instructions.
Contacting Airbus to define the source of the vibration.
Rudder servo control and hinge bearings freeplay check.
Rudder weight assessment.
Rudder weighing.
Rudder replacement.
Maintenance record check.
Rudder paint thickness measurement.
Paint removal and restoration.
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.
[[Page 31891]]
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
2026-0083 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 2026-0083 is incorporated by reference in this AD. This AD
requires compliance with EASA AD 2026-0083 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 2026-0083 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
2026-0083. Material required by EASA AD 2026-0083 for compliance will
be available at regulations.gov under Docket No. FAA-2026-4645 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 recent aeroelastic stability assessments conducted on the
Airbus SAS Model A319 series airplanes; Model A320 series airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -
252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX
airplanes, indicate that reduced stability margins may exist due to
accumulation of additional mass from rudder repainting or repairs done
during in-service operation. This condition, if not addressed, could,
in combination with a rudder actuator disconnection, result in
potential risk of flutter, possibly leading to reduced control 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 1,996 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 per Cost on U.S.
Labor cost Parts cost product operators
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5 work-hours x $85 per hour = $0 $425 $848,300
$425.........................
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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
------------------------------------------------------------------------
Up to 132 work-hours x $85 per $0*............... Up to $11,220
hour = $11,220.
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*The FAA has received no definitive data on which to base the cost
estimates for the on-condition parts specified in this AD.
The FAA has received no definitive data on which to base the cost
estimates for the on-condition further instructions specified in this
AD.
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
[[Page 31892]]
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.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2026-11-04 Airbus SAS: Amendment 39-23365; Docket No. FAA-2026-4645;
Project Identifier MCAI-2026-00451-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 15, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model A319-111, -112, -113, -
114, -115, -131, -132, -133, -151N, -153N, -171N, and -173N
airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -
251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model
A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -252N, -
253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by aeroelastic stability assessments that
indicate that reduced stability margins may exist due to
accumulation of additional mass from rudder repainting or repairs.
This condition, if not addressed, could, in combination with a
rudder actuator disconnection, result in potential risk of flutter,
possibly leading to reduced control 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, European Union Aviation Safety Agency (EASA) AD
2026-0083, dated April 22, 2026 (EASA AD 2026-0083).
(h) Exceptions to EASA AD 2026-0083
(1) Where EASA AD 2026-0083 refers to its effective date, this
AD requires using the effective date of this AD.
(2) This AD does not adopt the ``Remarks'' section of EASA AD
2026-0083.
(3) The service information specified in EASA AD 2026-0083
specifies to report results to Airbus within a certain compliance
time. For this AD, report results at the applicable time specified
in paragraph (h)(3)(i) or (ii) of this AD.
(i) If the actions required by paragraph (g) of this AD were
done on or after the effective date of this AD: Submit the report
within 30 days after the inspection.
(ii) If the actions required by paragraph (g) of this AD were
done before the effective date of this AD: Submit the report within
30 days after the effective date of this AD.
(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:
[email protected]. 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
2026-0083 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 Frank Carreras,
Aviation Safety
[[Page 31893]]
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone:
206-231-3539; email: [email protected].
(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 2026-0083,
dated April 22, 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 [email protected]. 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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on May 21, 2026.
Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-10800 Filed 5-27-26; 4:15 pm]
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