Proposed Rule2026-19094
Airworthiness Directives; Pratt & Whitney Engines
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
September 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for all Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G- 3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1919G-RC, PW1921G, PW1921G-RC, PW1922G, PW1923G, and PW1923G-A engines with a certain high-pressure compressor (HPC) module installed. This proposed AD was prompted by six reports of clashing found on either the HPC 2nd stage rotor or 3rd stage rotor caused by contact with the corresponding HPC variable stator vanes (VSV). This proposed AD would require initial and repetitive borescope inspections (BSIs) of the HPC 1st stage, 2nd stage, and 3rd stage rotor rear rim surfaces for evidence of wear, scratching, or contact with the corresponding HPC VSV inner locating ring and, depending on the results, removal from service and replacement. This proposed AD would also require replacement of the HPC VSV bushing set as terminating action to the initial and repetitive BSIs of the HPC 1st stage, 2nd stage, and 3rd stage rotor rear rim surfaces. 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 179 (Thursday, September 17, 2026)</title>
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[Federal Register Volume 91, Number 179 (Thursday, September 17, 2026)]
[Proposed Rules]
[Pages 58823-58826]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-19094]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 91, No. 179 / Thursday, September 17, 2026 /
Proposed Rules
[[Page 58823]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-8816; Project Identifier AD-2026-00605-E]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-
3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1919G-RC,
PW1921G, PW1921G-RC, PW1922G, PW1923G, and PW1923G-A engines with a
certain high-pressure compressor (HPC) module installed. This proposed
AD was prompted by six reports of clashing found on either the HPC 2nd
stage rotor or 3rd stage rotor caused by contact with the corresponding
HPC variable stator vanes (VSV). This proposed AD would require initial
and repetitive borescope inspections (BSIs) of the HPC 1st stage, 2nd
stage, and 3rd stage rotor rear rim surfaces for evidence of wear,
scratching, or contact with the corresponding HPC VSV inner locating
ring and, depending on the results, removal from service and
replacement. This proposed AD would also require replacement of the HPC
VSV bushing set as terminating action to the initial and repetitive
BSIs of the HPC 1st stage, 2nd stage, and 3rd stage rotor rear rim
surfaces. 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 October 19,
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-2026-8816; 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, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For PW material identified in this AD, contact PW, 400
Main Street, East Hartford, CT 06118; phone: (860) 565-0140; email:
<a href="/cdn-cgi/l/email-protection#d7bfb2bba7e5e397a7a5b6a3a3a0bfbea3b9b2aef9b4b8ba"><span class="__cf_email__" data-cfemail="422a272e327076023230233636352a2b362c273b6c212d2f">[email protected]</span></a>; website: <a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
<bullet> You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call (817) 222-5110.
FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7655; email: <a href="/cdn-cgi/l/email-protection#690a081b060547070e1c100c07290f0808470e061f"><span class="__cf_email__" data-cfemail="355654475a591b5b52404c505b755354541b525a43">[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-2026-8816;
Project Identifier AD-2026-00605-E'' 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 revise 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 Carol
Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198. 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 received six reports from the manufacturer of shop finds of
clashing on either the HPC 2nd stage rotor or HPC 3rd stage rotor
caused by wear on the HPC VSV bushing set. A manufacturer investigation
revealed that the wear on the HPC VSV bushing set allowed the vane to
rock forward, which caused the HPC variable vane inner locating ring to
contact the HPC rotor rear rim. This contact can lead to failure of the
HPC 1st stage, 2nd stage, and 3rd stage rotors. This condition, if not
addressed, could result in uncontained part release, damage to the
engine, damage to the airplane, and loss of control of the airplane.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition
[[Page 58824]]
described previously is likely to exist or develop on other products of
the same type design.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed PW Alert Service Bulletin (ASB) PW1000G-A-72-00-
0200-00B-930A-D, Issue No: 001, dated July 13, 2026; and PW ASB
PW1000G-A-72-00-0248-00A-930A-D, Issue No: 001, dated July 13, 2026.
This material specifies procedures for performing initial and
repetitive BSIs of the HPC 1st stage, 2nd stage, and 3rd stage rotor
rear rim surfaces for signs of wear, scratching, or contact with the
HPC VSV inner locating ring. This material also specifies the serial
numbers for affected HPC modules. 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.
Proposed AD Requirements in This NPRM
This proposed AD would require performing initial and repetitive
BSIs of the HPC 1st stage, 2nd stage, and 3rd stage rotor rear rim
surfaces for evidence of wear, scratching, or contact with the
corresponding HPC VSV inner locating ring and, depending on the
results, removal from service and replacement. This proposed AD would
also require replacement of the HPC VSV bushing set as terminating
action to the initial and repetitive BSIs of the HPC 1st stage, 2nd
stage, and 3rd stage rotor rear rim surfaces.
Interim Action
The FAA considers that this proposed AD would be an interim action.
The manufacturer is currently developing additional mitigations that
will address the unsafe condition identified in this AD. Once this is
developed, approved, and available, the FAA might consider additional
rulemaking.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 215 engines installed on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
BSIs of HPC 1st stage, 2nd stage, and 3rd 3 work-hours x $85 per hour $0 $255 $54,825
stage rotor. = $255.
Replacement of HPC VSV bushing set....... 1 work-hour x $85 per hour 20,300 20,385 4,382,775
= $85.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The agency has no way of determining the number of
engines that might need these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of HPC 1st stage rotor.......... 30 work-hours x $85 per hour = $313,500 $316,050
$2,550.
Replacement of HPC 2nd stage rotor.......... 30 work-hours x $85 per hour = 299,000 301,550
$2,550.
Replacement of HPC 3rd stage rotor.......... 30 work-hours x $85 per hour = 256,400 258,950
$2,550.
----------------------------------------------------------------------------------------------------------------
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 adding the following new airworthiness
directive:
Pratt & Whitney: Docket No. FAA-2026-8816; Project Identifier AD-
2026-00605-E.
[[Page 58825]]
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 19, 2026.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all Pratt & Whitney (PW) Model PW1519G,
PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-
3, PW1919G, PW1919G-RC, PW1921G, PW1921G-RC, PW1922G, PW1923G, and
PW1923G-A engines that have a high-pressure compressor (HPC) module
installed with a serial number listed in Table 1 of PW Alert Service
Bulletin (ASB) PW1000G-A-72-00-0200-00B-930A-D, Issue No: 001, dated
July 13, 2026 (PW1000G-A-72-00-0200-00B-930A-D, Issue No: 001); or
Table 1 of PW1000G-A-72-00-0248-00A-930A-D, Issue No: 001, dated
July 13, 2026 (PW ASB PW1000G-A-72-00-0248-00A-930A-D, Issue No:
001).
(2) This AD does not apply to engines that have incorporated PW
Service Bulletin PW1000G-A-72-00-0224-00A-930A-D or PW Service
Bulletin PW1000G-A-72-00-0170-00B-930A-D, as applicable.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by six reports of clashing found on either
the HPC 2nd stage rotor or 3rd stage rotor caused by contact with
the HPC variable stator vanes (VSV). The FAA is issuing this AD to
prevent failure of the HPC 1st stage, 2nd stage, and 3rd stage
rotors. The unsafe condition, if not addressed, could result in
uncontained part release, damage to the engine, damage to the
airplane, and loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purpose of this AD:
(1) Model ``PW1500G'' engines are PW Model PW1519G, PW1521G,
PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G, and PW1525G-3
engines.
(2) Model ``PW1900G'' engines are PW Model PW1919G, PW1919G-RC,
PW1921G, PW1921G-RC, PW1922G, PW1923G, and PW1923G-A engines.
(3) An ``HPC front case split flange separation'' is when the
HPC front case horizontal flange is separated.
(4) An ``HPC VSV bushing set'' is comprised of sleeve bearings
having part numbers (P/Ns) 30G1934, 30G1935, and 30G1936; and thrust
washer bearings having P/Ns 30G1938, 30G1939, and 30G1940.
(5) ``Parts eligible for installation'' are comprised of sleeve
bearings having P/Ns 30G6496, 30G6497, and 30G6498; and thrust
washer bearings having P/Ns 30G6499, 30G6500, and 30G6503; or later
approved P/Ns.
Note 1 to paragraph (g)(5): An HPC case with P/N 30G6509 has
installed sleeve bearings with P/Ns 30G6496, 30G6497, and 30G6498.
(6) An ``HPC 1st stage, 2nd stage, or 3rd stage rotor eligible
for installation'' is any HPC 1st stage, 2nd stage, or 3rd stage
rotor that was not removed from service in accordance with the
requirements of this AD.
(h) Required Actions
(1) Before accumulating 8,000 flight hours (FH) or within 1,000
FH after the effective date of this AD, whichever occurs later,
perform an initial borescope inspection (BSI) of the HPC 1st stage,
2nd stage, and 3rd stage rotor rear rim surfaces for evidence of
circumferential wear, scratching, or damage that shows previous
contact with the corresponding HPC VSV inner locating ring in
accordance with the applicable ASB listed in table 1 to paragraph
(h)(1) of this AD, as applicable to engine model.
Table 1 to Paragraph (h)(1)--Applicable ASBs
[Use this table 1 to determine the applicable ASB to perform the actions required by paragraphs (h)(1) and (2)
of this AD.]
----------------------------------------------------------------------------------------------------------------
Applicable service bulletin Applicable service bulletin
Part Engine model for engines installed on for engines not installed
aircraft on aircraft
----------------------------------------------------------------------------------------------------------------
HPC 1st stage rotor............ PW1500G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph B., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph A., step (5), of
A-72-00-0248-00A-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0248-00A-930A-D, Issue No:
001.
HPC 1st stage rotor............ PW1900G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph B., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph A., step (5), of
A-72-00-0200-00B-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0200-00B-930A-D, Issue No:
001.
HPC 2nd stage rotor............ PW1500G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph C., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph B., step (5), of
A-72-00-0248-00A-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0248-00A-930A-D, Issue No:
001.
HPC 2nd stage rotor............ PW1900G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph C., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph B., step (5), of
A-72-00-0200-00B-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0200-00B-930A-D, Issue No:
001.
HPC 3rd stage rotor............ PW1500G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph D., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph C., step (5), of
A-72-00-0248-00A-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0248-00A-930A-D, Issue No:
001.
HPC 3rd stage rotor............ PW1900G............. Accomplishment Instructions, Accomplishment
For Engines Installed On Instructions, For Engines
Aircraft, paragraph D., Not Installed On Aircraft,
step (5), of PW ASB PW1000G- paragraph C., step (5), of
A-72-00-0200-00B-930A-D, PW ASB PW1000G-A-72-00-
Issue No: 001. 0200-00B-930A-D, Issue No:
001.
----------------------------------------------------------------------------------------------------------------
(2) Thereafter, at intervals not to exceed 1,000 FH since the
last BSI, perform repetitive BSIs of the HPC 1st stage, 2nd stage,
and 3rd stage rotor rear rim surfaces for circumferential wear,
scratching, or damage that shows previous contact with the
corresponding HPC VSV inner locating ring in accordance with the
applicable ASB listed in table 1 to paragraph (h)(1) of this AD, as
applicable to the engine model.
(3) If, during any BSI required by paragraph (h)(1) or (2) of
this AD, evidence of circumferential wear, scratching, or damage
that shows previous contact with the corresponding HPC VSV inner
locating ring is discovered on the HPC 1st stage, 2nd stage, or 3rd
stage rotor rear rim surface, before further flight, remove each
damaged part from service and replace with an HPC 1st stage, 2nd
stage, or 3rd stage rotor eligible for installation.
(4) At the next HPC front case split flange separation after the
effective date of this AD, replace the HPC VSV bushing set with
parts eligible for installation.
Note 2 to paragraph (h)(4): Guidance for performing the
replacement of the HPC VSV bushing set may be found in PW Service
Bulletin PW1000G-A-72-00-0224-00A-930A-D, Issue No: 003, dated April
25, 2025, for PW Model PW1500G engines; and PW Service Bulletin
PW1000G-A-72-00-0170-00B-930A-D, Issue No: 004, dated July 25, 2025,
for PW Model PW1900G engines.
(i) Terminating Action
Replacing the HPC VSV bushing set in accordance with paragraph
(h)(4) of this AD constitutes terminating action for the initial and
repetitive BSIs of the HPC 1st stage, 2nd stage, and 3rd stage rotor
rear rim surface required by paragraphs (h)(1) and (2) of this AD.
(j) No Reporting Requirement
Although PW1000G-A-72-00-0200-00B-930A-D, Issue No: 001, and PW
ASB PW1000G-A-72-00-0248-00A-930A-D, Issue No: 001, specify to
submit certain
[[Page 58826]]
information to the manufacturer, including capturing photos and
videos, this AD does not require those actions.
(k) 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 local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the AIR-520 Continued Operational Safety
Branch, send it to the attention of the person identified in
paragraph (l)(1) of this AD and email to: <a href="/cdn-cgi/l/email-protection#30717d7f73705651511e575f46"><span class="__cf_email__" data-cfemail="89c8c4c6cac9efe8e8a7eee6ff">[email protected]</span></a>. Before using
any approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(l) Additional Information
(1) For more information about this AD, contact Carol Nguyen,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7655; email: <a href="/cdn-cgi/l/email-protection#7b181a09141755151c0e021e153b1d1a1a551c140d"><span class="__cf_email__" data-cfemail="5c3f3d2e333072323b292539321c3a3d3d723b332a">[email protected]</span></a>.
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (m)(4)
of this AD.
(m) 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 the AD specifies otherwise.
(i) Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW1000G-A-
72-00-0200-00B-930A-D, Issue No: 001, dated July 13, 2026.
(ii) PW ASB PW1000G-A-72-00-0248-00A-930A-D, Issue No: 001,
dated July 13, 2026.
(3) For PW material identified in this AD, contact PW, 400 Main
Street, East Hartford, CT 06118; phone: (860) 565-0140; email:
<a href="/cdn-cgi/l/email-protection#452d2029357771053537243131322d2c312b203c6b262a28"><span class="__cf_email__" data-cfemail="19717c75692b2d59696b786d6d6e71706d777c60377a7674">[email protected]</span></a>; website: <a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call (817) 222-5110.
(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#fd9b8fd394938e8d989e89949293bd939c8f9cd39a928b"><span class="__cf_email__" data-cfemail="e28490cc8b8c91928781968b8d8ca28c839083cc858d94">[email protected]</span></a>.
Issued on September 15, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-19094 Filed 9-16-26; 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.