Rule2025-21476
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
November 28, 2025
Effective
January 2, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2016-14- 03, which applied to all Airbus SAS Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. AD 2016-14-03 required reinforcing the forward pressure bulkhead at a certain stringer on both the left-hand and right-hand sides and doing related investigative and corrective actions if necessary. Since the FAA issued AD 2016-14-03, new crack findings have prompted the need for repetitive inspections of the area. This AD continues to require the actions in AD 2016-14-03, adds repetitive inspections of structure at a certain frame and applicable corrective actions, provides a terminating action for the repetitive inspections, and revises the applicability by removing airplanes and adding certain airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 227 (Friday, November 28, 2025)</title>
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[Federal Register Volume 90, Number 227 (Friday, November 28, 2025)]
[Rules and Regulations]
[Pages 54559-54563]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-21476]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0479; Project Identifier MCAI-2024-00436-T;
Amendment 39-23172; AD 2025-20-19]
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) 2016-14-
03, which applied to all Airbus SAS Model A319-111, -112, -113, -114, -
115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231,
-232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. AD 2016-14-03 required reinforcing the
forward pressure bulkhead at a certain stringer on both the left-hand
and right-hand sides and doing related investigative and corrective
actions if necessary. Since the FAA issued AD 2016-14-03, new crack
findings have prompted the need for repetitive inspections of the area.
This AD continues to require the actions in AD 2016-14-03, adds
repetitive inspections of structure at a certain frame and applicable
corrective actions, provides a terminating action for the repetitive
inspections, and revises the applicability by removing airplanes and
adding certain airplane models. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective January 2, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 2,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0479; 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#b1f0f5c2f1d4d0c2d09fd4c4c3dec1d09fd4c4"><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.
<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-2025-0479.
FOR FURTHER INFORMATION CONTACT: Nicholas Benson, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3647; email: <a href="/cdn-cgi/l/email-protection#4b2522282324272a38652365292e253824250b2d2a2a652c243d"><span class="__cf_email__" data-cfemail="a1cfc8c2c9cecdc0d28fc98fc3c4cfd2cecfe1c7c0c08fc6ced7">[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 2016-14-03, Amendment 39-18584 (81 FR
44496, July 8, 2016) (AD 2016-14-03). AD 2016-14-03 applied to all
Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes;
[[Page 54560]]
Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD
2016-14-03 required reinforcing the forward pressure bulkhead at a
certain stringer on both the left-hand and right-hand sides and doing
related investigative and corrective actions if necessary. The FAA
issued AD 2016-14-03 to prevent fatigue cracking of the forward
pressure bulkhead, which could result in reduced structural integrity
of the airplane.
The NPRM was published in the Federal Register on March 27, 2025
(90 FR 13848). The NPRM was prompted by AD 2024-0147R1, dated August 7,
2024 (EASA AD 2024-0147R1) (also referred to as ``the MCAI''), issued
by EASA, which is the Technical Agent for the Member States of the
European Union. The MCAI states that after EASA AD 2014-0209 was
issued, several findings of cracks were reported in service during
application of Airworthiness Limitation Item (ALI) tasks 532166 and
533186. As a result of these findings, Airbus has developed different
thresholds and inspection requirements compared to those specified in
ALI tasks 532166 and 533186 and requires those inspections until a
modification is done.
In the NPRM, the FAA proposed to continue to require the actions in
AD 2016-14-03. The FAA also proposed to add repetitive inspections of
structure at a certain frame and applicable corrective actions, provide
a terminating action for the repetitive inspections, and revise the
applicability by removing airplanes and adding certain airplane models,
as specified in EASA AD 2024-0147R1. The FAA is issuing this AD to
address the unsafe condition on these airplane products.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0479.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from United Airlines who supported the
NPRM without change.
The FAA received additional comments from American Airlines
(American), Delta Air Lines (Delta), and ProTech Aero Services Limited
(ProTech). The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Confirm Use of Later Revisions Is Allowed
ProTech requested the FAA confirm that the proposed AD would allow
the use of later-approved revisions of the material specified in EASA
AD 2024-0147R1, as acceptable for compliance with the AD requirements.
This AD does allow the use of later-approved revisions of the
material referenced in EASA AD 2024-0147R1 as acceptable for compliance
with the required actions. This AD adopts the ``Ref. Publications''
section of EASA AD 2024-0147R1, which includes the current version of
the referenced material as well as later approved revisions.
Request To Provide Credit for Actions Accomplished per a Certain
Service Bulletin
Delta requested the FAA confirm that accomplishment of Airbus
Service Bulletin A320-53-1372, dated May 15, 2018, instead of Airbus
Service Bulletin A320-53-1268, Revision 03, dated May 7, 2015, suffices
for taking credit for paragraph (4) of EASA AD 2024-0147R1. If the FAA
agrees, then Delta requested the FAA add a new exception to paragraph
(h) of the proposed AD to specify, where paragraph (4) of EASA AD 2024-
0147R1 states ``in accordance with the instructions of Airbus Service
Bulletin A320-53-1268,'' this AD considers Airbus Service Bulletin
A320-53-1372 as acceptable for compliance. Delta requested the new
exception because paragraph (4) of the EASA AD 2024-0147R1 does not
mention Airbus Service Bulletin A320-53-1372, and the FAA's NPRM does
not address Delta's concern. Delta stated it received an acceptable
method of compliance (AMOC) to FAA AD 2016-14-03 (via AMOC Letter No.
AIR-676-18-307, dated July 20, 2018) that allowed use of Airbus Service
Bulletin A320-53-1372 instead of Airbus Service Bulletin A320-53-1268
and would like to take credit for previous compliance actions for its
applicable airplanes.
The FAA partially agrees. The FAA agrees that, for certain airplane
serial numbers, the modification specified in paragraph (3) of EASA AD
2024-0147R1 may be accomplished using the original issue of Airbus
Service Bulletin A320-53-1372, dated May 15, 2018, or later approved
revisions, but disagrees that an exception is needed to provide credit
for accomplishing the modification using the original issue of that
service bulletin before the effective date of this AD. EASA AD 2024-
0147R1 defines ``the applicable modification SB'' as Airbus Service
Bulletin A320-53-1268, Revision 01, or Airbus Service Bulletin A320-53-
1372, as applicable to the manufacturer serial number. Since no
revision number is cited for Airbus Service Bulletin A320-53-1372 in
the definition, this means operators may use any revision of the
service bulletin specified in the ``Ref. Publications'' paragraph of
the EASA AD, as applicable, to accomplish the modification. However,
paragraph (4) of EASA AD 2024-0147R1 is necessary to provide credit for
any modification done before the effective date of this AD using the
original issue of Airbus Service Bulletin A320-53-1268, dated January
8, 2013, because the definition only cites Revision 01 of that service
bulletin. The FAA has not changed the AD in this regard.
The FAA clarifies that AMOCs approved previously for AD 2016-14-03
are approved as AMOCs for the corresponding provisions of EASA AD 2024-
0147R1 that are required by paragraph (g) of this AD. The FAA has
revised paragraph (i) of this AD accordingly.
Request To Correct Part Numbers
American requested the FAA revise the proposed AD to allow use of
the correct part numbers as an AMOC to certain part numbers specified
in Figure A-GBAAG--Sheet 02 of Airbus Service Bulletin A320-53-1383,
dated March 5, 2019. American stated that, while incorporating changes
found in Airbus Service Bulletin Information Transmission (SBIT) 19-
0038, Revision 03, dated February 10, 2025, it found an error in the
figure, and Airbus confirmed that certain part numbers in the tables
and instructions for COMPD07 of subtasks 531383-420-202-001 and 531383-
420-204-001 should be corrected.
The FAA agrees there is an error in Airbus Service Bulletin A320-
53-1383, dated March 5, 2019, but no change to this AD is necessary.
The FAA reviewed the service bulletin and determined that Figure A-
GBAAG Sheet 02 is not required for compliance. Subtasks 531383-420-202-
001 and 531383-420-204-001 provide procedures to wet install fasteners
in accordance with Structural Repair Manual (SRM) 51-42-00, but they
only reference the figure and an airplane maintenance manual (AMM) task
for additional information. Since the service bulletin does not specify
that the fastener installation must be done in accordance with the
figure, operators are not required to use the part numbers identified
in the figure. Operators may instead use the correct part numbers
identified in Airbus Message 81581889/005, Discrepancy in Figure A-
GBAAG Sheet 02, dated April 24, 2025, to comply with the requirements
of this AD. Further, Airbus's response to American
[[Page 54561]]
indicated the part numbers would be corrected in a later revision of
the service bulletin, which may be used for compliance according to the
``Ref. Publications'' section of EASA AD 2024-0147R1. The FAA has not
changed the AD in this regard.
Request To Correct a Typographical Error
Delta requested the FAA revise the exception in paragraph (h)(4) of
the proposed AD by changing ``herein'' to ``therein.'' Delta stated
paragraph (6) of EASA AD 2024-0147R1 uses ``herein'' to specify the
compliance times for repair instructions provided by Airbus based on
inspection findings after accomplishing ALI tasks 532166 and 533186.
Delta believes ``herein'' is a typographical error because the EASA AD
does not mention any compliance times for the ALI tasks inspection
findings. Delta stated that repair instructions and compliance times as
a result of the ALI inspection findings should be specified in the
appropriate Airbus Repair Design Approval Forms (RDAFs).
The FAA does not agree that usage of ``herein'' in EASA AD 2024-
0147R1 and paragraph (h)(4) of this AD is a typographical error.
Paragraph (6) of the EASA AD applies to airplanes that have been
inspected per ALI task 532166 and/or 533186 and repaired using Airbus
approved instructions. The FAA clarifies that, for these airplanes,
paragraph (6) of the EASA AD specifies accomplishing the repetitive
inspections of each repaired hole in accordance with the applicable
Airbus approved instructions within the compliance time ``herein,''
where herein refers to table 1 of the EASA AD for the applicable
inspection compliance times. The FAA has not revised the AD in this
regard.
Request To Calculate Compliance Time Based on Accomplishment of a
Certain Task
Delta requested the FAA add an exception to paragraph (h) of the
proposed AD to allow the compliance time in table 1 of EASA AD 2024-
0147R1 to be calculated based on accomplishment of ALI task 532166-01-1
instead of ALI task 532166-02-1. Delta noted that ALI task 532166-02-1
states the task is an alternative to ALI task 532166-01-1, and that it
accomplishes ALI task 532166-01-1 instead of ALI task 532166-02-1.
Since Airbus has stipulated that the task is alternative, Delta
therefore concluded that the compliance time may also be calculated
using ALI task 532166-01-1 instead of ALI task 532166-02-1.
The FAA does not agree with the request. EASA AD 2024-0147R1 does
not list ALI task 532166-01-1 as an alternate inspection task in Table
1--Initial Inspection. Further, ALI task 532166-02-1 is a special
detailed inspection (rototest), while ALI task 532166-01-1 is a visual
inspection. The FAA has not changed this AD 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, 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
The FAA reviewed EASA AD 2024-0147R1, which specifies procedures
for repetitive inspections for cracking of the airplane structure at
frame (FR) 35 and stringer (STGR) 30 on the left-hand and right-hand
sides for Airbus SAS Model A318, Model A319, and Model A320 airplanes;
and at FR 35.8 and STGR 30 on the left-hand and right-hand sides for
Airbus SAS Model A321 airplanes. EASA AD 2024-0147R1 also specifies
obtaining and following instructions for crack repair. EASA AD 2024-
0147R1 specifies that accomplishment of that inspection on an airplane
terminates ALI tasks 532166 and task 533186 requirements.
EASA AD 2024-0147R1 also specifies procedures for modifying the
forward pressure bulkhead at the frame coupling on the left-hand and
right-hand sides of FR 35 and STGR 30, including applicable related
investigative and corrective actions, for Airbus SAS Model A318, Model
A319, and Model A320 airplanes; and at FR 35.8 and STGR 30 for Airbus
SAS Model A321 airplanes. EASA AD 2024-0147R1 specifies that this
modification constitutes terminating action for the repetitive
inspections for that airplane.
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 1,922 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
The FAA estimates that it would take up to 21 work-hours per
product to comply with the retained actions from AD 2016-14-03. The
average labor rate is $85 per work-hour. Based on these figures, FAA
estimates the cost for U.S. operators is up to $3,430,770, or up to
$1,785 per product.
The FAA estimates that it would take up to 11 work-hours per
product to comply with the new proposed actions. The average labor rate
is $85 per work-hour. Based on these figures, FAA estimates the cost
for U.S. operators is up to $1,797,070, or up to $935 per product.
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in the cost estimate.
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
[[Page 54562]]
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) 2016-14-03, Amendment 39-18584
(81 FR 44496, July 8, 2016); and
0
b. Adding the following new AD:
2025-20-19 Airbus SAS: Amendment 39-23172; Docket No. FAA-2025-0479;
Project Identifier MCAI-2024-00436-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 2, 2026.
(b) Affected ADs
This AD replaces AD 2016-14-03, Amendment 39-18584 (81 FR 44496,
July 8, 2016) (AD 2016-14-03).
(c) Applicability
This AD applies to Airbus SAS Model airplanes specified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2024-0147R1, dated August 7, 2024 (EASA AD 2024-0147R1).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by the need to complete certain mandated
programs intended to support the airplane reaching its limit of
validity (LOV) of the engineering data that support the established
structural maintenance program. This AD was also prompted by reports
that during inspections accomplished as specified in certain
Airworthiness Limitation Items (ALIs), cracks were detected on the
fastener holes at frame (FR) 35 or FR 35.8 between stringers (STGRs)
28 and 31. The FAA is issuing this AD to prevent fatigue cracking on
the forward pressure bulkhead. The unsafe condition, if not
addressed, could result in reduced structural integrity of the
fuselage.
(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 2024-0147R1.
(h) Exceptions to EASA AD 2024-0147R1
(1) Where EASA AD 2024-0147R1 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0147R1 specifies ``If,
during any inspection as required by paragraph (1) of this AD,
discrepancies are detected, before next flight, contact Airbus to
obtain approved instructions for corrective action and accomplish
those instructions accordingly'', this AD requires replacing that
text with the following: ``If, during any inspection as required by
paragraph (1) of this AD, any cracking is detected, 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.''
(3) Where EASA AD 2024-0147R1 refers to ``03 October 2014 [the
effective date of EASA AD 2014-0209],'' this AD requires using
August 12, 2016 (the effective date of AD 2016-14-03).
(4) Where paragraph (6) of EASA AD 2024-0147R1 specifies
``repaired using Airbus approved instructions, accomplish the
(repetitive) inspection for each repaired hole in accordance with
the applicable Airbus approved instructions within the compliance
time herein specified'', this AD requires replacing that text with
the following: ``repaired using a method approved by the Manager,
AIR-520, Continued Operational Safety Branch, FAA; or EASA; or
Airbus SAS's EASA DOA, provided the DOA approval includes the DOA-
authorized signature: accomplish the (repetitive) inspection for
each repaired hole in accordance with the applicable approved
instructions within the compliance time herein specified.''
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0147R1.
(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#094844464a496f6868276e667f"><span class="__cf_email__" data-cfemail="fabbb7b5b9ba9c9b9bd49d958c">[email protected]</span></a>.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2016-14-03 are approved as
AMOCs for the corresponding provisions of EASA AD 2024-0147R1 that
are required by paragraph (g) of this AD.
(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 Nicholas Benson,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3647; email: <a href="/cdn-cgi/l/email-protection#e58b8c868d8a898496cb8dcb87808b968a8ba5838484cb828a93"><span class="__cf_email__" data-cfemail="dab4b3b9b2b5b6bba9f4b2f4b8bfb4a9b5b49abcbbbbf4bdb5ac">[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 2024-0147R1,
dated August 7, 2024.
(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#58191c2b183d392b39763d2d2a372839763d2d"><span class="__cf_email__" data-cfemail="7435300734111507155a1101061b04155a1101">[email protected]</span></a>. You may find this material on
the EASA website at ad.easa.europa.eu.
[[Page 54563]]
(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#d6b0a4f8bfb8a5a6b3b5a2bfb9b896b8b7a4b7f8b1b9a0"><span class="__cf_email__" data-cfemail="82e4f0acebecf1f2e7e1f6ebedecc2ece3f0e3ace5edf4">[email protected]</span></a>.
Issued on October 3, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-21476 Filed 11-26-25; 8:45 am]
BILLING CODE 4910-13-P
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</html>Indexed from Federal Register on November 28, 2025.
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