Airworthiness Directives; CFM International, S.A. Engines

[Federal Register Volume 90, Number 237 (Friday, December 12, 2025)]
[Rules and Regulations]
[Pages 57675-57678]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-22684]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-3434; Project Identifier AD-2025-00473-E; 
Amendment 39-23175; AD 2025-21-03]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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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 reports of two in-flight shutdowns and 
subsequent investigation by the manufacturer that revealed cracks in 
the high-pressure turbine (HPT) rotor stage 1 blades. This AD requires 
initial and repetitive borescope inspections (BSIs) of the HPT rotor 
stage 1 blades. Depending on the results of the BSIs, this AD requires 
either additional BSIs at reduced intervals or replacement of the HPT 
rotor stage 1 blades. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective December 29, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 29, 
2025.
    The FAA must receive comments on this AD by January 26, 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 regulations.gov. 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 regulations.gov under 
Docket No. FAA-2025-3434; 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 street address for Docket Operations is listed above.
    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: [email protected].
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section,

[[Page 57676]]

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: Mehdi Lamnyi, Aviation Safety 
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 
(781) 238-7743; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments using a method listed under 
the ADDRESSES section. Include ``Docket No. FAA-2025-3434; Project 
Identifier AD-2025-00473-E'' at the beginning of your comments. The 
most helpful comments reference a specific portion of the final rule, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend this final rule 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 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Mehdi 
Lamnyi, 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 was notified of reports of two in-flight shutdowns on 
airplanes powered by CFM LEAP-1A engines operating extensively in the 
Middle East and North Africa (MENA) region. A subsequent investigation 
by the manufacturer revealed that the engine failures were due to 
cracks in the HPT rotor stage 1 blades. After investigation, the 
manufacturer determined that engines operating in the MENA region are 
susceptible to accelerated HPT rotor stage 1 blade deterioration and 
airfoil distress at earlier cycle times due to the build-up of dust. As 
result, the FAA issued AD 2022-17-12, Amendment 39-22150 (87 FR 53651, 
September 1, 2022) (AD 2022-17-12) to address that unsafe condition in 
the MENA region. Further analysis revealed that these same engines are 
susceptible to similar accelerated deterioration and airfoil distress 
when operating in the South Asia region. This condition, if not 
addressed, could result in failure of the engine, in-flight shutdown, 
loss of thrust control, and consequent loss of control of the airplane.
    The FAA is issuing this AD to address the unsafe condition on these 
products.

FAA's Determination

    The FAA is issuing this AD because the agency determined the unsafe 
condition described previously is likely to exist or develop in other 
products of the same type design.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed CFM Service Bulletin (SB) LEAP-1A-72-00-0485-01A-
930A-D, Issue 003-00, dated July 30, 2025, which specifies procedures 
for performing repetitive BSIs of the HPT rotor stage 1 blades on LEAP-
1A engines operating in the South Asia region, and depending on the 
inspection results, recording and reporting any unserviceable findings, 
inspecting the sister engine's HPT rotor stage 1 blades, or removing an 
unserviceable HPT rotor stage 1 blades from service.
    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.

AD Requirements

    This AD requires initial and repetitive BSIs of the HPT rotor stage 
1 blades and, depending on the results of the inspections, additional 
BSIs at reduced intervals or replacement of the HPT rotor stage 1 
blades. This AD also requires a BSI of the HPT rotor stage 1 blades 
installed on the sister engine of the same airplane if certain criteria 
are met.
    This AD will require similar inspections, compliance times, and 
corrective actions as AD 2022-17-12 except for the initial inspection 
threshold which is specific to operations within the South Asia region.

Interim Action

    The FAA considers this AD to be an interim action. The unsafe 
condition is still under investigation by the manufacturer and, 
depending on the results of that investigation, the FAA may consider 
further rulemaking action.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 
551 et seq.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause,'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    The FAA justifies waiving notice and comment prior to adoption of 
this rule because no domestic operators are affected by this AD. It is 
unlikely that the FAA will receive any adverse comments or useful 
information about this AD from any U.S. operator.
    Accordingly, notice and opportunity for prior public comment are 
unnecessary, pursuant to 5 U.S.C. 553(b). In addition, for the 
foregoing reason(s), the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

[[Page 57677]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                       Cost per    Cost on U.S.
                  Action                            Labor cost           Parts cost    product       operators
----------------------------------------------------------------------------------------------------------------
BSI of the HPT rotor stage 1 blades......  4 work-hours x $85 per hour           $0         $340              $0
                                            = $340.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary further 
corrective actions and replacements that would be required based on the 
results of the inspection. The agency has no way of determining the 
number of engines that might need these additional inspections or 
replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                    Action                                 Labor cost              Parts cost   Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement of the HPT rotor stage 1 blades...  150 work-hours x $85.00 per hour     $988,200         $1,000,950
                                                 = $12,750.
BSI of the HPT rotor stage 1 blades (on the     4 work-hours x $85 per hour =               0                340
 sister engine).                                 $340.
----------------------------------------------------------------------------------------------------------------

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, and
    (2) Will not affect intrastate aviation in Alaska.

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:

2025-21-03 CFM International, S.A.: Amendment 39-23175; Docket No. 
FAA-2025-3434; Project Identifier AD-2025-00473-E.

(a) Effective Date

    This airworthiness directive (AD) is effective December 29, 
2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International, S.A. Model (CFM) 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 high-pressure 
turbine (HPT) rotor stage 1 blade, having part number (P/N) 
2747M92P01, P/N 2553M91G03, P/N 2553M91G05, P/N 2553M91G06, P/N 
2553M91G07, or P/N 2553M91G08 and that has accumulated more than 
1,100 South Asia takeoffs.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
section.

(e) Unsafe Condition

    This AD was prompted by reports of two in-flight shutdowns due 
to cracks in the HPT rotor stage 1 blades. The FAA is issuing this 
AD to prevent failure of the HPT rotor stage 1 blades. The unsafe 
condition, if not addressed, could result in failure of the engine, 
in-flight shutdown, loss of thrust control, and consequent loss of 
control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

(1) Group 1 Engines: Borescope Inspection (BSI) of HPT Rotor Stage 
1 Blades

    For Group 1 engines with an affected HPT rotor stage 1 blade 
installed:
    (i) Within 100 flight cycles (FCs) after accumulating 1,100 
South Asia takeoffs on the HPT rotor stage 1 blade, before the HPT 
rotor stage 1 blade accumulates 2,500 cycles since new (CSN), or 
within 100 FCs after the effective date of this AD, whichever occurs 
later, perform an initial BSI of the HPT rotor stage 1 blades in 
accordance with the Accomplishment Instructions, paragraph 
5.E.(1)(c), of CFM Service Bulletin LEAP-1A-72-00-0485-01A-930A-D, 
Issue 003-00, dated July 30, 2025 (CFM SB LEAP-1A-72-00-0485-01A-
930A-D, Issue 003-00).
    (ii) Thereafter, at intervals not to exceed 150 FCs since the 
last BSI, perform a repetitive BSI of the HPT rotor stage 1 blades 
in accordance with the Accomplishment Instructions, paragraph 
5.E.(1)(c), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00.

(2) Group 2 Engines: BSI of HPT Rotor Stage 1 Blades

    For Group 2 engines with an affected HPT rotor stage 1 blade 
installed:
    (i) Within 100 FCs after accumulating 1,100 South Asia takeoffs 
on the HPT rotor stage 1 blade, before the HPT rotor stage 1 blade 
accumulates 5,100 CSN, or within 100 FCs after the effective date of 
this AD, whichever occurs later, perform an initial BSI of the HPT 
rotor stage 1 blades in accordance with the Accomplishment 
Instructions, paragraph 5.E.(1)(c), of CFM SB LEAP-1A-72-00-0485-
01A-930A-D, Issue 003-00.
    (ii) Thereafter, at intervals not to exceed 300 FCs since the 
last BSI, perform a

[[Page 57678]]

repetitive BSI of the HPT rotor stage 1 blades in accordance with 
the Accomplishment Instructions, paragraph 5.E.(1)(c), of CFM SB 
LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00.

(3) BSI Results Disposition for Group 1 and Group 2 Engines

    Based on the results of the BSI required by paragraphs (g)(1) or 
(2) of this AD, as applicable, either re-inspect or replace, as 
applicable, the HPT rotor stage 1 blades set using the criteria, 
compliance times, and procedures as described in the Accomplishment 
Instructions, paragraph 5.E.(1)(e), of CFM SB LEAP-1A-72-00-0485-
01A-930A-D, Issue 003-00.

(4) Conditional Inspection of the Sister Engine for Group 1 and 
Group 2 Engines

    (i) Based on the BSI results disposition required by paragraph 
(g)(3) of this AD, if re-inspection or replacement of the HPT rotor 
stage 1 is required, within 50 FCs based on the criteria, compliance 
times, and procedures described in the Accomplishment Instructions, 
paragraph 5.E.(1)(e), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 
003-00, then perform the actions required in paragraph (g)(4)(ii) of 
this AD.
    (ii) Within 5 FCs after performing the inspection required by 
paragraph (g)(1) or (2) of this AD, as applicable, either inspect or 
replace the HPT rotor stage 1 blades on the sister engine using the 
procedures and compliance times in the Accomplishment Instructions, 
paragraph 5.E.(1)(f), of CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 
003-00. Where CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00, 
specifies to remove the engine, this AD requires replacement of the 
HPT rotor stage 1 blades.

(h) Definitions

    For the purpose of this AD, the following definitions apply:
    (1) Group 1 engines are CFM Model LEAP-1A29, LEAP-1A29CJ, LEAP-
1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A engines.
    (2) Group 2 engines are CFM Model LEAP-1A23, LEAP-1A24, LEAP-
1A24E1, LEAP-1A26, LEAP-1A26CJ, and LEAP-1A26E1 engines.
    (3) A ``South Asia takeoff'' is any takeoff accomplished in the 
South Asia region, which includes the following countries: 
Bangladesh, Bhutan, India, Maldives, Nepal, and Sri Lanka.
    (4) A ``sister engine'' refers to the other engine installed on 
the same airplane.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the initial BSI required 
by paragraphs (g)(1)(i) or (2)(i) of this AD if you performed the 
initial BSI before the effective date of this AD using CFM Service 
Bulletin LEAP-1A-72-00-0485-01A-930A-D, Issue 001-00, dated 
September 27, 2022, or Issue 002-00, dated April 16, 2025.
    (2) The inspections and corrective actions as required by 
paragraphs (g)(1) through (4) of this AD satisfy the requirements of 
paragraphs (g)(1) through (4) of AD 2022-17-12, Amendment 39-22150 
(87 FR 53651, September 1, 2022) (AD 2022-17-12).
    (3) The inspections and corrective actions as required by 
paragraphs (g)(1) through (4) of AD 2022-17-12 satisfy the 
requirements of paragraphs (g)(1) through (4) of this AD.

(j) No Reporting Requirement

    Where CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 003-00, 
requires reporting any unserviceable findings, this AD does not 
require that action.

(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 the AIR-520 Continued 
Operational Safety Branch, send it to the attention of the person 
identified in paragraph (l) of this AD and email to: [email protected].
    (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

    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: [email protected].

(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) CFM Service Bulletin LEAP-1A-72-00-0485-01A-930A-D, Issue 
003-00, dated July 30, 2025.
    (ii) [Reserved]
    (3) For CFM material identified in this AD, contact CFM 
International, S.A., GE Aviation Fleet Support, 1 Neumann Way, M/D 
Room 285, Cincinnati, OH 45215; phone: (877) 432-3272; email: 
[email protected].
    (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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on December 5, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-22684 Filed 12-11-25; 8:45 am]
BILLING CODE 4910-13-P

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