Rule2026-00330
Airworthiness Directives; International Aero Engines LLC 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
January 12, 2026
Effective
February 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines, LLC (IAE LLC) Model PW1122G-JM, PW1124G-JM, PW1124G1-JM, PW1127G-JM, PW1127G1-JM, PW1127G1A-JM, PW1127G1B-JM, PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G- JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines. This AD was prompted by multiple reports of fan blade fracture events, three of which resulted in an engine under cowl fire or pool fire. This AD requires removal of one loop cushion clamp from the hydraulic fuel pressure fuel oil cooler fuel tube assembly (CP09 tube assembly), replacement of the thermal management system (TMS) clevis mounts with redesigned TMS clevis mounts, and reinstallation of the loop cushion clamp, as applicable. 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 7 (Monday, January 12, 2026)</title>
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[Federal Register Volume 91, Number 7 (Monday, January 12, 2026)]
[Rules and Regulations]
[Pages 1078-1082]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-00330]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0480; Project Identifier AD-2024-00546-E;
Amendment 39-23226; AD 2025-26-04]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines LLC Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
International Aero Engines, LLC (IAE LLC) Model PW1122G-JM, PW1124G-JM,
PW1124G1-JM, PW1127G-JM, PW1127G1-JM, PW1127G1A-JM, PW1127G1B-JM,
PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-
JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM
engines. This AD was prompted by multiple reports of fan blade fracture
events, three of which resulted in an engine under cowl fire or pool
fire. This AD requires removal of one loop cushion clamp from the
hydraulic fuel pressure fuel oil cooler fuel tube assembly (CP09 tube
assembly), replacement of the thermal management system (TMS) clevis
mounts with redesigned TMS clevis mounts, and reinstallation of the
loop cushion clamp, as applicable. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective February 17, 2026.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 17,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0480; 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, 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 Pratt & Whitney (PW) material identified in this AD,
contact IAE LLC, 400 Main Street, East Hartford, CT 06118; phone: (860)
565-0140; email: <a href="/cdn-cgi/l/email-protection#761e131a064442360601580302155815191b"><span class="__cf_email__" data-cfemail="f8909d9488caccb8888fd68d8c9bd69b9795">[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. It is also available at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2025-0480.
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#036062716c6f2d6d64767a666d436562622d646c75"><span class="__cf_email__" data-cfemail="bad9dbc8d5d694d4ddcfc3dfd4fadcdbdb94ddd5cc">[email protected]</span></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 all International Aero
Engines, LLC (IAE LLC) Model PW1122G-JM, PW1124G-JM, PW1124G1-JM,
PW1127G-JM, PW1127G1-JM, PW1127G1A-JM, PW1127G1B-JM, PW1127GA-JM,
PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-
JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines. The
NPRM was published in the Federal Register on March 28, 2025 (90 FR
14057). The NPRM wasF prompted by multiple reports of fan blade
fracture events due to bird strikes. Three of these events resulted in
an engine under cowl fire or pool fire. In the NPRM, the FAA proposed
to require removal of one loop cushion clamp from the CP09 tube
assembly and replacement of the TMS clevis mounts with redesigned TMS
clevis mounts.
The FAA is issuing this AD to prevent a fuel leak resulting from a
fan blade fracture. The unsafe condition, if not addressed, could
result in an uncontrolled engine fire and damage to the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from nine commenters. The commenters were
[[Page 1079]]
the Airline Pilots Association, International (ALPA); All Nippon
Airways (ANA); Delta Air Lines (Delta); Lufthansa Technik AG
(Lufthansa); PW; ProTech Aero Services Limited (ProTech); United
Airlines (United); and an individual. The following presents the
comments received on the NPRM and the FAA's response to each comment.
Support for the NPRM
ALPA, United, and the individual expressed support for the NPRM.
Request To Define ``Next Engine Shop Visit''
In the NPRM, the FAA proposed that paragraph (g) would require
certain parts to be replaced ``at the next engine shop visit.''
Lufthansa, Delta, and ANA requested that the FAA refine this term.
Delta stated that there was no definition of ``engine shop visit'' in
the NPRM. Lufthansa requested that the FAA specify the type of shop
visit. Lufthansa stated that during quick-turn shop visits with nose-
down procedure, it is not possible to perform the required
modification. Lufthansa also noted that the modification requirement
could have a significant effect on operations that are intended to
minimize turnaround time, and requested that such types of visits be
excluded from the rule. ANA indicated that the engine manufacturer's
recommended maintenance program defines ``shop visit'' as ``whenever an
engine maintenance opportunity entails separating pairs of major mating
gas path flanges.'' ANA requested clarification on whether this
definition of ``shop visit'' from the engine maintenance program is
applicable.
The FAA agrees to define ``next engine shop visit,'' however, the
FAA does not agree to exclude quick-turn shop visits. To clarify, for
this AD quick-turn shop visits are defined as limited scope and meant
to target specific engine issues. However, regardless of the reason for
induction, the FAA considers those quick-turn shop visits to be
``engine shop visits,'' as defined in paragraph (i) of this final rule.
Operators may request an alternative method of compliance (AMOC) in
accordance with the procedures specified in paragraph (k) of this AD,
provided sufficient data are submitted to substantiate that the AMOC
would provide an acceptable level of safety. The FAA has revised this
final rule by including paragraph (i), which includes the definition of
``engine shop visit.''
Request To Alter Compliance Times
The individual requested that the FAA account for different
compliance schedules in relation to this NPRM. The commenter stated
that the compliance schedule of the required actions could affect
operators with major operational interruptions and higher maintenance
costs if additional down time is necessary to comply with this proposed
AD. Additionally, the commenter encouraged the FAA to work with
stakeholders to improve the AD, such as by exploring other alternative
methods of risk reduction or conducting a cost-benefit analysis.
The FAA disagrees with the request to alter the compliance times of
this AD. In developing an appropriate compliance time for this action,
the FAA considered the recommendations from the manufacturer. These
recommendations included the urgency associated with the unsafe
condition, the availability of required parts, and the practical aspect
of accomplishing the required modification within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. In consideration of these items, the FAA has determined that
the specified compliance times will ensure an acceptable level of
safety. The NPRM gives all stakeholders and the general public the
opportunity to comment on the proposed required actions and compliance
times.
As to the commenter's other suggestion, the FAA worked with
industry stakeholders, including the manufacturer, and affected
operators through the public comment process, to develop this final
rule. However, any operator may request an AMOC in accordance with the
procedures specified in paragraph (k) of this AD, provided sufficient
data are submitted to substantiate that the AMOC would provide an
acceptable level of safety. The FAA has not changed this AD based on
this comment.
Request for Different Compliance Times for Engines That Are Not
Installed
ProTech stated support for the compliance times for engines that
are already installed on airplanes. However, ProTech requested that the
FAA specify a compliance time of ``Within 30 days after the effective
date of this AD, or at the time of installation on an airplane,
whichever comes later . . .'' for engines which are not installed on an
airplane.
The FAA agrees to clarify the compliance time and has revised
paragraph (g)(1) of this AD to account for each subset of engines.
Request To Remove Certain Language
PW requested that the FAA remove ``due to bird strike'' from the
Summary, Background, and the Unsafe Condition sections.
The FAA agrees with the request. Although three of the six fan
blade fracture events were caused by bird strikes, other events can
fracture a fan blade. The FAA has removed all instances of ``due to
bird strike'' in this final rule, except for the description of the
NPRM in the Background section.
Request To Use Updated Service Material
Delta and ANA requested that the FAA update the required actions to
refer to an updated revision of the applicable service material. Delta
stated that the later revision allows operators to reuse certain part-
numbered bolts that are removed, if the bolts pass certain inspection
requirements. Delta stated that this is based on parts availability.
Delta also requested the FAA revise the credit for previous actions
paragraph to include the updated service material.
ANA stated that the instructions in a certain engine manual do not
specify the requirement to discard bolt part number MS9716-08 or to
install new bolts. ANA also stated that if the bolts have passed
certain inspections and procedures and the required torque was applied,
these bolts are not required to be discarded. ANA requested that the
FAA allow certain part-numbered bolts to be reused and not discarded if
they have passed certain inspections and procedures.
The FAA agrees to allow certain part-numbered bolts to be reused if
they have passed certain inspections and procedures. Additionally,
since the NPRM was published, the manufacturer has released multiple
revisions to PW Alert Service Bulletin (ASB) PW1000G-C-72-00-0214-00A-
930A-D. The FAA has revised this AD to reference PW ASB PW1000G-C-72-
00-0214-00A-930A-D, Issue 006 as the appropriate source of material and
has included credit for all previous revisions.
Request To Require Reinstallation of the Loop Cushion Clamp
Delta requested that the FAA revise the required actions to require
reinstallation of the loop cushion clamp after replacement of the TMS
clevis mounts. Delta stated that PW ASB PW1000G-C-72-00-0214-00A-930A-D
contains a step for reinstalling the loop cushion clamp after the TMS
clevis mounts have been replaced, which the FAA did not include in the
NPRM. Delta expressed the expectation that
[[Page 1080]]
since the required steps of the service material include removal of the
loop cushion clamp, that the intention would also be to reinstall.
The FAA agrees. However, since the NPRM was published, PW ASB
PW1000G-C-72-00-0214-00A-930A-D has been updated and the FAA has
revised this AD to refer to the latest revision of the required
material. Additionally, the steps contained in the updated material
have changed, which in turn, caused the steps referenced in this AD to
change. Accordingly, the FAA has revised paragraph (g)(2) of this AD to
require the steps in the latest revision of PW ASB PW1000G-C-72-00-
0214-00A-930A-D, which includes reinstalling the loop cushion clamp
with the redesigned TMS clevis mounts after the TMS clevis mounts are
replaced.
Request To Revise Terminating Action
PW requested that the FAA revise the terminating action paragraph
of the NPRM to specify that the actions specified in paragraph (g)(2)
of the NPRM constitute a terminating action for the entire NPRM. No
further justification was provided.
The FAA disagrees with the request to revise the terminating action
to apply to the entire AD. The FAA notes that the terminating action
paragraph of this AD only applies to the removal of the loop cushion
clamp because once the TMS clevis mounts are replaced, this action is
no longer necessary. The FAA has not changed this AD based on this
request.
Request To Change Interim Action to Final Action
PW requested that the FAA revise the wording of the NPRM to specify
that the required actions are final and that the NPRM is not considered
an interim action. PW stated that the TMS clevis mounts replacement and
subsequent reinstallation of the loop cushion clamp addresses the
unsafe condition.
The FAA agrees that the TMS clevis mounts replacement and
subsequent reinstallation of the loop cushion clamp does address the
unsafe condition. However, since the FAA has not included the interim
action paragraph in this final rule, there is no need for the FAA to
change this final rule based on the request.
Request for Clarification Regarding Removal of the Loop Cushion Clamp
ANA requested that the FAA revise paragraphs (c) or (g)(1) of the
NPRM to include an exemption for engines that have already complied
with ASB PW1000G-C-72-00-0214-00A-930A-D. ANA requested clarification
whether engines that have replaced the TMS clevis mounts are also
required to remove the loop cushion clamp. ANA stated that even though
the terminating action removes the requirement to remove the loop
cushion clamp, there is still possibility for confusion for the
operator, which may accidentally do both actions.
The FAA agrees to clarify. The replacement of the TMS clevis mounts
specified in paragraph (g)(2) of this AD terminates the loop clamp
removal specified in paragraph (g)(1) of this AD. As discussed
previously in this final rule, the FAA has also included reinstallation
of the loop clamp as an additional requirement to paragraph (g)(2) of
this AD and as such, there is no need to include the language suggested
by the commenter. Furthermore, paragraph (f) of this AD states to
accomplish the required actions within the compliance times specified,
``unless already done.'' Therefore, if operators have accomplished the
actions required for compliance with this AD before the effective date
of this AD, no further action is necessary. The FAA has not revised
this AD in this regard.
Conclusion
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 the following material.
<bullet> PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 006,
dated August 19, 2025, which specifies procedures for replacement of
the TMS clevis mounts with redesigned TMS clevis mounts and
reinstallation of the loop cushion clamp.
<bullet> PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 005,
dated September 18, 2024, which specifies procedures for removing one
loop cushion clamp from the CP09 tube assembly.
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 586 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Remove one loop cushion clamp from the 9 work-hours x $85 per hour $0 $765 $448,290
CP09 tube assembly. = $765.
Replace the TMS clevis mounts............ 107 work-hours x $85 per 17,000 26,095 15,291,670
hour = $9,095.
Install one loop cushion clamp on the 9 work-hours x $85 per hour 0 765 448,290
CP09 tube assembly. = $765.
----------------------------------------------------------------------------------------------------------------
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
[[Page 1081]]
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:
2025-26-04 International Aero Engines LLC: Amendment 39-23226;
Docket No. FAA-2025-0480; Project Identifier AD-2024-00546-E.
(a) Effective Date
This airworthiness directive (AD) is effective February 17,
2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to International Aero Engines, LLC Model
PW1122G-JM, PW1124G-JM, PW1124G1-JM, PW1127G-JM, PW1127G1-JM,
PW1127G1A-JM, PW1127G1B-JM, PW1127GA-JM, PW1129G-JM, PW1130G-JM,
PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-JM, PW1428GH-JM,
PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 1400, Miscellaneous
Hardware.
(e) Unsafe Condition
This AD was prompted by multiple reports of fan blade fracture
events, three of which resulted in an engine under cowl fire or pool
fire. The FAA is issuing this AD to prevent a fuel leak resulting
from a fan blade fracture. The unsafe condition, if not addressed,
could result in an uncontrolled engine fire and damage to the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 30 days after the effective date of this AD or upon
installation of an affected engine, whichever occurs later, remove
one loop cushion clamp, part number ST1540-06, from the hydraulic
fuel pressure fuel oil cooler fuel tube assembly (CP09 tube
assembly) in accordance with the Accomplishment Instructions, For
Engines Installed On Aircraft, paragraph C, or For Engines Not
Installed On Aircraft, paragraph A, of Pratt & Whitney (PW) Alert
Service Bulletin (ASB) PW1000G-C-73-00-0053-00A-930A-D, Issue No.
005, dated September 18, 2024.
(2) At the next engine shop visit after the effective date of
this AD, replace the thermal management system (TMS) clevis mount
with redesigned TMS clevis mounts in accordance with paragraphs AI,
AJ, AL through AN, and AZ(6) of the Accomplishment Instructions of
PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 006, dated August
19, 2025.
(h) Terminating Action
The actions specified in paragraph (g)(2) of this AD constitute
terminating action for the requirements of paragraph (g)(1) of this
AD. This terminating action may be accomplished instead of the
actions specified in paragraph (g)(1) of this AD.
(i) Definition
For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraph (g)(1) of this AD, if done before the effective date of
this AD using any of the material specified in paragraph (j)(1)(i)
through (iv) of this AD inclusive.
(i) PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 001, dated
October 25, 2022.
(ii) PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 002,
dated November 07, 2022.
(iii) PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 003,
dated November 21, 2022.
(iv) PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 004,
dated March 15, 2024.
(2) This paragraph provides credit for the actions specified in
paragraph (g)(2) of this AD, if done before the effective date of
this AD using any of the material specified in paragraph (j)(2)(i)
through (v) of this AD inclusive.
(i) PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 001, dated
July 19, 2023.
(ii) PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 002,
dated March 15, 2024.
(iii) PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 003,
dated May 16, 2024.
(iv) PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 004,
dated September 18, 2024.
(v) PW ASB PW1000G-C-72-00-0214-00A-930A-D, Issue No. 005, dated
July 30, 2025.
(k) Alternative Methods of Compliance (AMOCs)
(1) 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 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#95d4d8dad6d5f3f4f4bbf2fae3"><span class="__cf_email__" data-cfemail="91d0dcded2d1f7f0f0bff6fee7">[email protected]</span></a>.
(2) 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#204341524f4c0e4e475559454e604641410e474f56"><span class="__cf_email__" data-cfemail="701311021f1c5e1e170509151e301611115e171f06">[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)(3)
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-C-
72-00-0214-00A-930A-D, Issue No. 006, dated August 19, 2025.
(ii) PW ASB PW1000G-C-73-00-0053-00A-930A-D, Issue No. 005,
dated September 18, 2024.
(3) For PW material identified in this AD, contact International
Aero Engines, LLC, 400 Main Street, East Hartford, CT 06118; phone:
(860) 565-0140; email: <a href="/cdn-cgi/l/email-protection#d7bfb2bba7e5e397a7a0f9a2a3b4f9b4b8ba"><span class="__cf_email__" data-cfemail="056d60697537314575722b7071662b666a68">[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,
[[Page 1082]]
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#fc9a8ed295928f8c999f88959392bc929d8e9dd29b938a"><span class="__cf_email__" data-cfemail="c7a1b5e9aea9b4b7a2a4b3aea8a987a9a6b5a6e9a0a8b1">[email protected]</span></a>.
Issued on December 23, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2026-00330 Filed 1-9-26; 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.