Rule2026-01152
Airworthiness Directives; CFM International, S.A. 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 22, 2026
Effective
February 26, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1A23, LEAP-1A24, LEAP- 1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A engines. This AD was prompted by a report of multiple aborted takeoffs and air turn-backs (ATBs) caused by high-pressure compressor (HPC) stall, which was induced by high levels of non-synchronous vibration (NSV). Additional manufacturer investigation revealed that wear on the No. 3 bearing spring finger housing can lead to high levels of NSV. This AD requires initial and repetitive calculations of the levels of NSV, inspection of the stage 2 high-pressure turbine (HPT) nozzle assembly honeycomb and HPT stator stationary seal honeycomb and, depending on the results of the calculations and inspections, replacement of certain parts. This AD also requires replacement of certain No. 3 bearing spring finger housings at the next shop visit. 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 14 (Thursday, January 22, 2026)</title>
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[Federal Register Volume 91, Number 14 (Thursday, January 22, 2026)]
[Rules and Regulations]
[Pages 2684-2687]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-01152]
[[Page 2684]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-1115; Project Identifier AD-2024-00797-E;
Amendment 39-23240; AD 2026-02-04]
RIN 2120-AA64
Airworthiness Directives; CFM International, S.A. 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
certain CFM International, S.A. (CFM) Model LEAP-1A23, LEAP-1A24, LEAP-
1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ,
LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A engines.
This AD was prompted by a report of multiple aborted takeoffs and air
turn-backs (ATBs) caused by high-pressure compressor (HPC) stall, which
was induced by high levels of non-synchronous vibration (NSV).
Additional manufacturer investigation revealed that wear on the No. 3
bearing spring finger housing can lead to high levels of NSV. This AD
requires initial and repetitive calculations of the levels of NSV,
inspection of the stage 2 high-pressure turbine (HPT) nozzle assembly
honeycomb and HPT stator stationary seal honeycomb and, depending on
the results of the calculations and inspections, replacement of certain
parts. This AD also requires replacement of certain No. 3 bearing
spring finger housings at the next shop visit. The FAA is issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective February 26, 2026.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 26,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-1115; 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 CFM material identified in this AD, contact CFM, GE
Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH
45215; phone: (877) 432-3272; email: <a href="/cdn-cgi/l/email-protection#3756415e56435e585919515b525243444247475845437750521954585a"><span class="__cf_email__" data-cfemail="7f1e09161e0b1610115119131a1a0b0c0a0f0f100d0b3f181a511c1012">[email protected]</span></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-2025-1115.
FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7743; email: <a href="/cdn-cgi/l/email-protection#a1ccc4c9c5c88fcdc0cccfd8c8e1c7c0c08fc6ced7"><span class="__cf_email__" data-cfemail="94f9f1fcf0fdbaf8f5f9faedfdd4f2f5f5baf3fbe2">[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 certain CFM Model LEAP-
1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1,
LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2,
and LEAP-1A35A engines. The NPRM was published in the Federal Register
on June 25, 2025 (90 FR 26947). The NPRM was prompted by a notification
from the engine manufacturer of three aborted takeoffs and two ATBs
caused by HPC stall on CFM Model LEAP-1A engines. Additional
manufacturer investigation revealed that wear on the No. 3 bearing
spring finger housing can lead to high levels of NSV, which could
induce HPC stall. As a result of its investigation, the manufacturer
published service material that specifies procedures for addressing
this situation. The FAA previously published AD 2024-07-06, Amendment
39-22727 (89 FR 33211, April 29, 2024), to address this condition for
parts from one specific supplier whose parts have shown increased
susceptibility to premature wear. Since the publication of that AD, the
manufacturer has identified another supplier whose parts are also
susceptible to the same type of premature wear.
In the NPRM, the FAA proposed to require initial and repetitive
calculations of the levels of NSV, inspection of the stage 2 HPT nozzle
assembly honeycomb and HPT stator stationary seal honeycomb and,
depending on the results of the calculations and inspections,
replacement of certain parts. This AD also requires replacement of
certain No. 3 bearing spring finger housings at the next shop visit.
The FAA is issuing this AD to address the unsafe condition on these
products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from four commenters. The commenters were
the Air Line Pilots Association, International (ALPA), American
Airlines (AAL), CFM, and the Foundation for Aviation Safety. ALPA
supported the NPRM without change. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Request To Allow Automated Alerts for NSV Calculations
AAL requested that the FAA allow for the use of automated CFM-
provided alerts for NSV calculations as an alternative to the
instructions in paragraph (g)(1) of the proposed AD. AAL noted that
automated Customer Notification Reports for exceedance of NSV
thresholds are already in use to provide continuous evaluation of NSV
data and reduce the risk of errors created in manual inspection or
calculation of NSV data.
The FAA disagrees with the commenter's request to add automated CFM
provided alerts as an additional method of compliance in the final rule
because automated CNRs are dependent on continuous data transmission
from the aircraft to CFM. If data transmission is interrupted, CNRs
cannot be generated, potentially leaving unsafe conditions undetected.
CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, dated September 24,
2025, specifies that operators verify every 50 cycles that at least 100
cycles of post-flight data exist within each 125-cycle period to ensure
the monitoring system is functioning, as specified in paragraph
5.A.(1). This AD requires this action. However, if any operator prefers
to address the unsafe condition by means other than those specified in
the referenced service information, they may request approval for an
AMOC in accordance with paragraph (k) of this AD and, if approved, may
use it instead of the procedures specified in the service information
and the final rule. The FAA did not change this AD as a result of this
comment.
[[Page 2685]]
Request To Refer to New Service Material
CFM requested that the FAA revise the ``Material Incorporated by
Reference under 1 CFR part 51'' paragraph and paragraphs (c), (g), (h),
(i), and (l) of the proposed AD to refer to CFM SB LEAP-1A-72-00-0562-
01A-930A-D, Issue 002-00, dated September 24, 2025, rather than CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 001-00, dated April 30, 2025. CFM
also requested that the FAA revise the ``Material Incorporated by
Reference under 1 CFR part 51'' paragraph of the proposed AD to the
following: ``The FAA also reviewed CFM SB LEAP-1A-72-00-0562-01A-930A-
D, Issue 002-00, dated September 24, 2025. This service material
identifies the affected No. 3 bearing spring finger housings and
specifies procedures for monitoring NSV during engine operation,
replacing the affected No. 3 bearing spring finger housing, inspecting
the stage 2 HPT nozzle assembly honeycomb, and inspecting the HPT
stator stationary seal honeycomb.'' CFM noted that CFM SB LEAP-1A-72-
00-0562-01A-930A-D, Issue 002-00, dated September 24, 2025, specifies
to inspect the stage 2 HPT nozzle assembly and HPT stator stationary
seal, but does not state to replace them, and includes the updated
method for accessing CFM diagnostics.
The FAA agrees with the content in the requested language and has
revised this final rule in all areas to refer to CFM SB LEAP-1A-72-00-
0562-01A-930A-D, Issue 002-00, dated September 24, 2025, rather than
CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 001-00, dated April 30,
2025. These changes will not increase the economic burden on any
operator.
Request To Specify Replacement Threshold
CFM requested that the FAA update the language in the ``Summary''
paragraph of the proposed AD to the following: ``This AD also requires
replacement of certain No. 3 bearing spring finger housings at next
shop visit.'' CFM also requested that the FAA update the language in
the ``Proposed AD Requirements in this NPRM'' paragraph of the proposed
AD to the following: ``This proposed AD would also require replacement
of the No. 3 bearing spring finger housing at next shop visit,
regardless of calculated level of NSV.''
The FAA agrees with the content in the requested language and has
revised the ``Summary'' paragraph of this AD as requested. However, the
``Proposed AD Requirements in this NPRM'' paragraph is not included in
the final rule, therefore the FAA did not change that paragraph as a
result of this comment.
Request for Root Cause of Unsafe Condition
The Foundation for Aviation Safety requested that the FAA provide
the root cause of the unsafe condition, clarify the reason that it was
not addressed during engine certification, and explain what
certification steps have been put in place to prevent this for new
engines being built.
The FAA refers the commentor to the ``Background'' paragraph of
this AD for additional information. The FAA notes that the premature
wear was not anticipated during initial certification and is limited to
specific suppliers, and improvements to the production controls have
been implemented to prevent future occurrences. The FAA did not change
this AD as a result of this comment.
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 CFM Service Bulletin (SB) LEAP-1A-72-00-0536-01A-
930A-D, Issue 001-00, dated July 22, 2024. This service material
specifies procedures for replacing the No. 3 bearing spring finger
housings, inspecting the stage 2 HPT nozzle assembly honeycomb, and
inspecting the HPT stator stationary seal honeycomb.
The FAA also reviewed CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue
002-00, dated September 24, 2025. This service material identifies the
affected No. 3 bearing spring finger housings and specifies procedures
for monitoring NSV during engine operation, inspecting the stage 2 HPT
nozzle assembly honeycomb, and inspecting the HPT stator stationary
seal honeycomb.
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 three 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
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Calculate NSV data....................... 1 work-hour x $85 per hour $0 $85 $255
= $85.
Inspect stage 2 HPT nozzle assembly 4 work-hours x $85 per hour 0 340 1,020
honeycomb and HPT stator stationary seal = $340.
honeycomb.
Replace No. 3 bearing spring finger 17 work-hours x $85 per 64,590 66,035 198,105
housing. hour = $1,445.
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The FAA estimates the following costs to do any necessary
replacements and inspections that would be required based on the
results of the proposed calculation. The agency has no way of
determining the number of engines that might need these replacements
and inspections:
[[Page 2686]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
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Replace stage 2 HPT nozzle assembly honeycomb. 8 work-hours x $85 per hour = $58,536 $59,216
$680.
Replace HPT stator stationary seal............ 8 work-hours x $85 per hour = 6,855 7,535
$680.
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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:
2026-02-04 CFM International, S.A.: Amendment 39-23240; Docket No.
FAA-2025-1115; Project Identifier AD-2024-00797-E.
(a) Effective Date
This airworthiness directive (AD) is effective February 26,
2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to CFM International, S.A. (CFM) Model LEAP-
1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1,
LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-
1A33B2, and LEAP-1A35A engines with an installed No. 3 bearing
spring finger housing having part number (P/N) 2629M62G01 and a
serial number identified in Table 1 of CFM Service Bulletin (SB)
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, dated September 24,
2025 (CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00).
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by a report of multiple aborted takeoffs
and air turn-backs caused by high-pressure compressor (HPC) stall,
which was induced by high levels of non-synchronous vibration (NSV),
and an additional manufacturer investigation that revealed wear on
the No. 3 bearing spring finger housing. The FAA is issuing this AD
to prevent HPC stall. The unsafe condition, if not addressed, could
result in engine power loss at a critical phase of flight such as
takeoff or climb, loss of engine thrust control, reduced
controllability of the airplane, and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Within 50 flight cycles (FCs) after the effective date of
this AD and thereafter at intervals not to exceed 50 FCs, calculate
the NSV data in accordance with the Accomplishment Instructions,
paragraphs 5.A.(1) and 5.A.(3), or 5.B.(1) and 5.B.(3) of CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00.
(2) If, during any calculation required by paragraph (g)(1) of
this AD, the NSV data exceeds the limits specified in the
Accomplishment Instructions paragraph 5.A.(4)(a)1, 5.A.(4)(a)2, or
5.B.(4)(a)1 of CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00,
discontinue the calculations required by paragraph (g)(1) of this AD
and within 25 FCs or 5 FCs, as applicable to the threshold exceeded,
of the flight when these limits are exceeded:
(i) Remove from service the No. 3 bearing spring finger housing
having P/N 2629M62G01 and a serial number identified in Table 1 of
CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, and replace with
a part eligible for installation.
(ii) Inspect the stage 2 high-pressure turbine (HPT) nozzle
assembly honeycomb for rubs in accordance with the Accomplishment
Instructions, paragraphs 5.A.(4)(a)4b or 5.B.(4)(a)3b of CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00.
(iii) Inspect the HPT stator stationary seal honeycomb for rubs
in accordance with the Accomplishment Instructions, paragraphs
5.A.(4)(a)4b or 5.B.(4)(a)3b of CFM SB LEAP-1A-72-00-0562-01A-930A-
D, Issue 002-00.
(3) If, during the inspection required by paragraph (g)(2)(ii)
of this AD, the stage 2 HPT nozzle assembly honeycomb fails to meet
the serviceability criteria referenced in the Accomplishment
Instructions, paragraphs 5.A.(4)(a)4b or 5.B.(4)(a)3b of CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, before further flight,
replace the stage 2 HPT nozzle assembly honeycomb.
(4) If, during the inspection required by paragraph (g)(2)(iii)
of this AD, the HPT stator stationary seal honeycomb fails to meet
the serviceability criteria referenced in the Accomplishment
Instructions, paragraphs 5.A.(4)(a)4b or 5.B.(4)(a)3b of CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, before further flight,
replace the HPT stator stationary seal.
(5) At the next shop visit after the effective date of this AD,
perform the following:
(i) Replace the No. 3 bearing spring finger housing having P/N
2629M62G01 and a serial number identified in Table 1 of CFM SB LEAP-
1A-72-00-0562-01A-930A-D, Issue 002-00, with a part eligible for
installation in accordance with paragraph 5.A.(1) of CFM SB LEAP-1A-
72-00-0536-01A-930A-D, Issue 001-00, dated July 22, 2024 (CFM SB
LEAP-1A-72-00-0536-01A-930A-D, Issue 001-00); and,
[[Page 2687]]
(ii) Inspect the stage 2 HPT nozzle assembly honeycomb and the
HPT stator stationary seal honeycomb for rubs and disposition in
accordance with paragraph 5.B.(4) and 5.B.(5) of CFM SB LEAP-1A-72-
00-0536-01A-930A-D, Issue 001-00.
(h) Terminating Action
Replacement of the No. 3 bearing spring finger housing having P/
N 2629M62G01 and a serial number identified in Table 1 of CFM SB
LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00 with a part eligible for
installation, as specified in paragraph (g)(2)(i) and (g)(5) of this
AD, constitutes terminating action for the calculations required by
paragraph (g)(1) of this AD.
(i) Definitions
(1) For the purpose of this AD, a ``part eligible for
installation'' is a No. 3 bearing spring finger housing that does
not have P/N 2629M62G01 and a serial number identified in Table 1 of
CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00.
(2) For the purpose of this AD, a ``shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges, except that the
separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance does not
constitute an engine shop visit.
(j) Credit for Previous Actions
You may take credit for the actions required by paragraphs
(g)(1) through (4) and (h) of this AD if you performed these actions
before the effective date of this AD using CFM SB LEAP-1A-72-00-
0562-01A-930A-D, Issue 001-00, dated April 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, AIR-520 Continued Operational
Safety Branch, send it to the attention of the person identified in
paragraph (l) of this AD and email to: <a href="/cdn-cgi/l/email-protection#d99894969a99bfb8b8f7beb6af"><span class="__cf_email__" data-cfemail="d6979b999596b0b7b7f8b1b9a0">[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.
(3) For service material that contains steps that are labeled as
Required for Compliance (RC), the following provisions apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, that are required by
paragraph (g) of this AD must be done to comply with this AD. An
AMOC is required for any deviations to RC steps required by
paragraph (g) of this AD, including substeps and identified figures.
(ii) Steps not labeled 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 RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(l) Additional Information
(1) For more information about this AD, contact Mehdi Lamnyi,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7743; email: <a href="/cdn-cgi/l/email-protection#1a777f727e7334767b777463735a7c7b7b347d756c"><span class="__cf_email__" data-cfemail="b7dad2dfd3de99dbd6dad9cedef7d1d6d699d0d8c1">[email protected]</span></a>.
(2) For CFM material, which is not incorporated by reference in
this AD, contact CFM, GE Aviation Fleet Support, 1 Neumann Way, M/D
Room 285, Cincinnati, OH 45215; phone: (877) 432-3272; email:
<a href="/cdn-cgi/l/email-protection#80e1f6e9e1f4e9efeeaee6ece5e5f4f3f5f0f0eff2f4c0e7e5aee3efed"><span class="__cf_email__" data-cfemail="6706110e06130e080949010b020213141217170815132700024904080a">[email protected]</span></a>.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) CFM International, S.A. (CFM) Service Bulletin (SB) LEAP-1A-
72-00-0536-01A-930A-D, Issue 001-00, dated July 22, 2024.
(ii) CFM SB LEAP-1A-72-00-0562-01A-930A-D, Issue 002-00, dated
September 24, 2025.
(3) For CFM material identified in this AD, contact CFM, GE
Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH
45215; phone: (877) 432-3272; email: <a href="/cdn-cgi/l/email-protection#0b6a7d626a7f626465256d676e6e7f787e7b7b64797f4b6c6e25686466"><span class="__cf_email__" data-cfemail="a6c7d0cfc7d2cfc9c888c0cac3c3d2d5d3d6d6c9d4d2e6c1c388c5c9cb">[email protected]</span></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#3d5b4f1354534e4d585e495452537d535c4f5c135a524b"><span class="__cf_email__" data-cfemail="2147530f484f5251444255484e4f614f4053400f464e57">[email protected]</span></a>.
Issued on January 13, 2026.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2026-01152 Filed 1-21-26; 8:45 am]
BILLING CODE 4910-13-P
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</html>Indexed from Federal Register on January 22, 2026.
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