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Rule2026-10799

Airworthiness Directives; Airbus SAS Airplanes

Primary source

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Published

May 29, 2026

Effective

July 6, 2026

Issuing agencies

Transportation DepartmentFederal Aviation Administration

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318-111, -112, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -232, -233, -251N, -252N, -253N, -271N, - 272N, and -273N airplanes; and Model A321-211, -212, -213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by the detection of a deviation from the manufacturing process during a review of the cold working process in the assembly line. This AD requires repetitive special detailed inspections (SDIs) and rototest or high frequency eddy current (HFEC) and rototest inspections of the affected fasteners and fastener holes, and applicable on-condition 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 103 (Friday, May 29, 2026)</title>
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[Federal Register Volume 91, Number 103 (Friday, May 29, 2026)]
[Rules and Regulations]
[Pages 31880-31884]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-10799]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-2544; Project Identifier MCAI-2025-00531-T;
Amendment 39-23355; AD 2026-10-15]
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 A318-111, -112, and -122 airplanes; Model
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model
A320-211, -212, -214, -216, -232, -233, -251N, -252N, -253N, -271N, -
272N, and -273N airplanes; and Model A321-211, -212, -213, -231, -232,
-251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and
-272NX airplanes. This AD was prompted by the detection of a deviation
from the manufacturing process during a review of the cold working
process in the assembly line. This AD requires repetitive special
detailed inspections (SDIs) and rototest or high frequency eddy current
(HFEC) and rototest inspections of the affected fasteners and fastener
holes, and applicable on-condition actions. The FAA is issuing this AD
to address the unsafe condition on these products.

DATES: This AD is effective July 6, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 6,
2026.

ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-2544; 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#dc9d98af9cb9bdafbdf2b9a9aeb3acbdf2b9a9">[email&#160;protected]</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-2025-2544.

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#d591b4bbfb87bab1bcbbb495b3b4b4fbb2baa3">[email&#160;protected]</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 A318-111, -112, and -122 airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214,
-215, -216, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N
airplanes; and Model A321-211, -212, -213, -231, -232, -251N, -252N, -
253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX
airplanes. The NPRM was published in the Federal Register on September
15, 2025 (90 FR 44350). The NPRM was prompted by AD 2025-0078, dated
April 9, 2025 (EASA AD 2025-0078) (also referred to as the MCAI),
issued by EASA, which is the Technical Agent for the Member States of
the European

[[Page 31881]]

Union. The MCAI states that a deviation from the manufacturing process
was detected during a review of the cold working process in the
assembly line, which could adversely affect the fatigue life of the
affected areas (forward pressure bulkhead connection to frame (FR) 35
for Airbus A319 and A320 airplanes and FR35.8 for Airbus A321
airplanes, between stringer (STR) 28 and STR 31, both left-hand (LH)
and right-hand (RH) sides; and fuselage skin at FR35 for Airbus A318,
A319 and A320 airplanes and FR35.8 for Airbus A321 airplanes, at STR30,
both LH and RH sides). This condition, if not detected and corrected,
could lead to crack initiation and propagation, possibly resulting in
reduced structural integrity of the airplane.
In the NPRM, the FAA proposed to require repetitive SDIs around the
fastener holes at FR35, STR 28 to STR 31 to check if the fasteners and
fastener holes are in nominal design condition, repetitive rototest or
HFEC and rototest inspections around the fasteners and fastener holes
for cracks, and applicable corrective actions, as specified in EASA AD
2025-0078. 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-2025-2544.

Discussion of Final Airworthiness Directive

Comments

The FAA received comments from three commenters, including American
Airlines (American), the Citizens Rulemaking Alliance, and JetBlue. The
following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Correct a Typographical Error

American requested that the FAA correct a typographical error in
Airbus Service Bulletin A320-53-1520, dated November 18, 2024. American
noted the instructions in that material, for Option 2, Configuration
002, specify to remove 12 fasteners whereas only 9 fasteners are shown
in the corresponding figure. American stated Airbus confirmed via
Repair and Design Approval Form (RDAF) 81664262/004/2025#A that only 9
fasteners are to be removed.
The FAA agrees and has added a new exception to paragraph (h)(4) of
this AD, accordingly.

Request To Revise Fastener Removal Procedure

JetBlue requested that the FAA allow removal of the fasteners and
inspection of all affected fasteners holes at the same time with any
applicable repair to follow, instead of removal of one fastener at a
time followed by inspection and repair of one fastener hole at a time,
as specified in paragraph C(4)(b) of Airbus Service Bulletin A320-53-
1519, dated November 18, 2024, and Airbus Service Bulletin A320-53-1520
dated November 18, 2024. JetBlue stated that Airbus confirmed via Tech
Request 8159376 that 100% of the fasteners can be removed from the
affected holes prior to performing non-destructive tests and corrective
actions, if needed. JetBlue also stated this approach is intended to
prevent work stoppages and improve efficiency during the inspection
process.
The FAA agrees and has added a new exception to paragraph (h)(5) of
this AD, accordingly.

Request To Justify Forgoing Notice and Comment or Issue an NPRM

The Citizens Rulemaking Alliance requested that the FAA either
provide its justification for finding good cause to bypass notice and
comment procedures, or convert this action to an NPRM to extend the
comment period and delay compliance enforcement. The commenter also
requested that the FAA add to the AD docket the chronology of the
underlying events and the quantitative risk assessment that justifies
use of the good cause exemption.
The FAA notes the comment was submitted in response to an NPRM for
which the FAA provided a 45-day comment period. This final rule is
effective 35 days after its publication in the Federal Register.
Therefore, no change to this AD is necessary.

Request To Make Incorporation by Reference (IBR) Materials Reasonably
Available

The Citizens Rulemaking Alliance requested that the FAA make IBR
material available and free to the public during the comment period.
The commenter asserted that this AD incorporates by reference
manufacturer service information.
The FAA notes that this AD incorporates by reference EASA AD 2025-
0078, not the manufacturer service information referenced in that EASA
AD. The FAA posted EASA AD 2025-0078 to the AD docket when the NPRM was
published in the Federal Register. The material referenced in EASA AD
2025-0078 may only be posted before the final rule's publication if it
is already publicly available or if there is written consent from the
owner of that material. Additionally, the FAA provided notice in the
NPRM that the material referenced in EASA AD 2025-0078 will be
available in the AD docket after this AD is published. Therefore, the
FAA did not change this AD as a result of this comment.

Request To Comply With the Paperwork Reduction Act (PRA)

The Citizens Rulemaking Alliance requested that the FAA revise the
AD to comply with the PRA if reporting is required or remove any
reporting provisions until PRA requirements are satisfied. If reporting
is not required, the commenter requested the FAA clarify that in the
AD.
The FAA notes paragraph (i) of this AD specifies that reporting is
not required. If an AD were to require reporting, the preamble of the
AD would include a paragraph titled ``Paperwork Reduction Act'' that
would provide the applicable OMB control number, required PRA
statements, and the estimated time to collect the required information
(burden). Any costs associated with the reporting requirement would be
included in the Costs of Compliance section in the preamble of the AD.
Therefore, the FAA did not change this AD as a result of this comment.

Request To Consider Impact on Small Entities

The Citizens Rulemaking Alliance requested that the FAA either
provide the factual basis for its Regulatory Flexibility Act (RFA)
certification that the AD will not have a significant economic impact
on a substantial number of small entities, including the number of
small entities operating affected airplanes, or prepare an initial
regulatory flexibility analysis that identifies alternatives to
minimize impact if the cost analysis shows the impact on small entities
is not de minimis.
The FAA provides the following clarification. The RFA of 1980 (5
U.S.C. 601-612), as amended by the Small Business Regulatory
Enforcement Fairness Act of 1996 (Pub. L. 104-121) and the Small
Business Jobs Act of 2010 (Pub. L. 111-240), requires Federal agencies
to consider the effects of the regulatory action on small business and
other small entities and to minimize any significant economic impact.
The term ``small entities'' comprises small businesses and not-for-
profit organizations that are independently owned and operated and are
not dominant in their fields, and governmental jurisdictions with
populations of less than 50,000.
This AD will affect 23 domestic entities, of which 8 are small
entities.

[[Page 31882]]

The table below displays the industries of the small entities, their
average annual revenue, and the AD's estimated cost burden relative to
average annual revenue.

Number of Small Entities Affected by Industry and Cost Significance \1\
----------------------------------------------------------------------------------------------------------------
Affected Cost per AD/
NAICS code Description small Average annual Number of annual
entities revenue aircraft revenue (%)
----------------------------------------------------------------------------------------------------------------
336412.......................... Aircraft Engine and 1 $5,200,000 5 0.52
Engine Parts
Manufacturing.
336413.......................... Other Aircraft Part and 1 3,960,000 1 0.14
Auxiliary Equipment
Manufacturing.
336413.......................... Other Aircraft Part and 1 215,930 1 2.48
Auxiliary Equipment
Manufacturing.
336413.......................... Other Aircraft Part and 1 520,000 1 1.03
Auxiliary Equipment
Manufacturing.
481211.......................... Nonscheduled Chartered 1 246,350,000 22 0.05
Passenger Air
Transportation.
532411.......................... Commercial Air, Rail, 1 1,020,000 1 0.53
and Water
Transportation
Equipment Rental and
Leasing.
532411.......................... Commercial Air, Rail, 1 1,070,000 2 1.00
and Water
Transportation
Equipment Rental and
Leasing.
532411.......................... Commercial Air, Rail, 1 218,330 2 4.91
and Water
Transportation
Equipment Rental and
Leasing.
----------------------------------------------------------------------------------------------------------------
\1\ Source: SBA (2023). NAICS (North American Industrial Classification System). Dun & Bradstreet. D&B Hoovers.
Retrieved April 12, 2024. <a href="https://app.hoovers.dnb.com/">https://app.hoovers.dnb.com/</a>.

While the FAA has determined that this AD affects a substantial
number of small entities, the compliance cost of the AD relative to
small entities' annual revenue is minimal. The estimated cost per
affected airplane is $5,355 (63 work-hours x $85 per work-hour). Based
on the number of airplanes per small entity, the total cost burden is
less than 3 percent of average annual revenue for all but one small
entity. Therefore, as provided in section 605(b), the FAA certifies
this AD will not result in a significant economic impact on a
substantial number of small entities. The FAA did not change this AD as
a result of this comment.

Request To Provide Additional Cost Information

The Citizens Rulemaking Alliance requested that the FAA add to the
AD docket the cost per small entity, including downtime and
recordkeeping.
The FAA recognizes that, in doing the actions required by an AD,
operators might incur indirect costs (such as loss of revenue due to
airplane downtime, recordkeeping to document AD compliance, etc.) in
addition to the direct costs. The cost analysis in an AD typically
describes only the direct costs of the specific actions required by an
AD, which does not include indirect costs, since the FAA lacks data on
those costs and they may vary significantly among operators. However,
the FAA considered the impact that this AD will have on affected
operators and determined this AD will not trigger any downtime costs
because the requirements of this AD can be performed during regularly
scheduled maintenance.
In the Costs of Compliance section of the proposed AD, the FAA
disclosed the estimated cost per airplane on the U.S. registry. Since
the FAA has assessed and disclosed the total known costs of the AD
requirements in the Costs of Compliance section of the proposed AD, and
the commenter did not provide additional cost data for the FAA to
consider in its cost analysis, it is not necessary to provide
additional information in the AD docket. The FAA did not change this AD
as a result of 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 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, and any other changes described previously,
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 2025-0078 specifies procedures for repetitive SDIs around
the fastener holes at FR35, STR 28 to STR 31 to check if the fasteners
and fastener holes are in nominal design condition, repetitive rototest
or HFEC and rototest inspections around the fasteners and fastener
holes for cracks, and applicable corrective actions. Corrective actions
include repair.
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 1,474 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 63 work-hours x $85 per hour = $0 Up to $5,355.............. Up to $7,893,270.
$5,355.
----------------------------------------------------------------------------------------------------------------

[[Page 31883]]

The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs 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:

2026-10-15 Airbus SAS: Amendment 39-23355; Docket No. FAA-2025-2544;
Project Identifier MCAI-2025-00531-T.

(a) Effective Date

This airworthiness directive (AD) is effective July 6, 2026.

(b) Affected ADs

None.

This AD applies to Airbus SAS airplanes specified in paragraphs
(c)(1) through (4), certificated in any category, as identified in
European Union Aviation Safety Agency (EASA) AD 2025-0078, dated
April 9, 2025 (EASA AD 2025-0078).
(1) Model A318-111, -112, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -232, -233, -251N, -252N,
-253N, -271N, -272N, and -273N airplanes.
(4) Model A321-211, -212, -213, -231, -232, -251N, 252N, -253N,
-271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX airplanes.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by the detection of a deviation from the
manufacturing process during a review of the cold working process in
the assembly line. The FAA is issuing this AD to address reduced
fatigue life of the affected areas of the forward pressure bulkhead
connection to, and fuselage skin at, certain frames. The unsafe
condition, if not addressed, could result 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 paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2025-0078.

(h) Exceptions to EASA AD 2025-0078

(1) Where EASA AD 2025-0078 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraphs (2) and (3) of EASA AD 2025-0078 specify
``discrepancy'', this AD requires replacing that text with
``fastener or fastener hole that is not in a nominal design
condition''.
(3) Where paragraph (6) of EASA AD 2025-0078 specifies ``If,
during inspection as required by paragraph (3), (4) or (5) of this
AD, any crack is found, 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 ``If,
during any inspection required by paragraph (3), (4), or (5) of this
AD, any cracking is found, the cracking must be repaired before
further flight using a method approved by the Manager, AIR-520,
Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.''
(4) Where Airbus Service Bulletin A320-53-1520 referenced in
EASA AD 2025-0078 to remove ``12 FASTENERS'', this AD requires
replacing that text with ``9 FASTENERS''.
(5) Where Airbus Service Bulletin A320-53-1519 and Airbus
Service Bulletin A320-53-1520 referenced in EASA AD 2025-0078
contain Notes that specify to ``Remove only one fastener and follow
the Service Bulletin process from the inspection to the installation
and repeat the same process for other fasteners,'' and Cautions that
specify ``Only one fastener to be removed at a time from the
affected holes'' and ``The rototest inspection has to be performed
hole by hole with only one fastener removed at a time from the
affected holes,'' this AD allows all fasteners to be removed from
the affected fastener holes at the same time prior to performing
non-destructive tests and corrective actions.
(6) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0078.

(i) No Reporting Requirement

Although the material referenced EASA AD 2025-0078 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#1e5f53515d5e787f7f30797168">[email&#160;protected]</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)(4) and (5), (i), and (j)(2) of this AD, if any
material contains procedures or tests that are identified as RC,

[[Page 31884]]

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 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#6024010e4e320f04090e01200601014e070f16">[email&#160;protected]</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 2025-0078,
dated April 9, 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#b5f4f1c6f5d0d4c6d49bd0c0c7dac5d49bd0c0">[email&#160;protected]</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#761004581f1805061315021f1918361817041758111900">[email&#160;protected]</a>.

Issued on May 13, 2026.
Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-10799 Filed 5-28-26; 8:45 am]
BILLING CODE 4910-13-P

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