Airworthiness Directives; CFM International, S.A. Engines

[Federal Register Volume 91, Number 131 (Friday, July 10, 2026)]
[Rules and Regulations]
[Pages 42649-42653]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-13979]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-7214; Project Identifier AD-2026-00225-E; 
Amendment 39-23407; AD 2026-14-06]
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 superseding Airworthiness Directive (AD) 2025-21-
03, which applied to 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. AD 2025-21-03 required initial and repetitive 
borescope inspections (BSIs) of the high-pressure turbine (HPT) rotor 
stage 1 blades. Depending on the results of the BSIs, AD 2025-21-03 
required either additional BSIs at

[[Page 42650]]

reduced intervals or replacement of the HPT rotor stage 1 blades. Since 
the FAA issued AD 2025-21-03, the manufacturer published updated 
service material and determined that engines operating in the South 
Asia region are susceptible to accelerated HPT rotor stage 1 blade 
deterioration and airfoil distress. 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. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective July 27, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 27, 
2026.
    The FAA must receive comments on this AD by August 24, 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-2026-7214; 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, 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 
regulations.gov under Docket No. FAA-2026-7214.

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-2026-7214; Project 
Identifier AD-2026-00225-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 issued AD 2025-21-03, Amendment 39-23175 (90 FR 57675, 
December 12, 2025), (AD 2025-21-03), for 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. AD 2025-21-03 required 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. AD 2025-21-03 also required a BSI of the HPT 
rotor stage 1 blades installed on the sister engine of the same 
airplane if certain criteria are met. AD 2025-21-03 was prompted by 
reports of two in-flight shutdowns and subsequent investigation by the 
manufacturer that revealed cracks in the HPT rotor stage 1 blades. The 
FAA issued AD 2025-21-03 to prevent failure of the HPT rotor stage 1 
blades.

Actions Since AD 2025-21-03 Was Issued

    Since the FAA issued AD 2025-21-03, the manufacturer determined 
that engines operating in the South Asia region are susceptible to 
accelerated HPT rotor stage 1 blade deterioration and airfoil distress 
due to the build-up of dust. As a result, the manufacturer published 
updated service material expanding the list of regions affected by the 
unsafe condition. The FAA also received a comment from Airbus India 
requesting clarification on BSI requirements for the sister engine if a 
non-affected HPT blade is installed, or if the sister engine has an 
engine configuration that is below the applicability threshold listed 
in CFM Service Bulletin (SB) LEAP-1A-72-00-0485-01A-930A-D, Issue 003-
00, dated July 30, 2025. As a result, the FAA has updated the 
regulatory text of this AD to require certain actions be performed in 
accordance with CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-00, 
dated May 19, 2026 (CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-
00), and to clarify that the conditional inspection of the sister 
engine is not required if the sister engine has an affected part 
installed and has already met certain inspection conditions. 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.

[[Page 42651]]

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-
00, 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, inspecting the sister 
engine's HPT rotor stage 1 blades, or removing 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.

Interim Action

    The FAA considers this AD to be an interim action. The manufacturer 
is currently developing a terminating action that will address the 
unsafe condition identified in this AD. Once this terminating action is 
developed and available, the FAA might consider further rulemaking.

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 use this product. 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 operators of engines 
installed on airplanes of U.S. registry with the criteria identified in 
the Applicability section of the AD.
    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
----------------------------------------------------------------------------------------------------------------
BSI of the HPT rotor stage 1 blades...  4 work-hours x $85 per             $0             $340               $0
                                         hour = $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
----------------------------------------------------------------------------------------------------------------
                                                                                                      Cost per
                     Action                                   Labor cost               Parts cost      product
----------------------------------------------------------------------------------------------------------------
Replacement of the HPT rotor stage 1 blades.....  150 work-hours x $85 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 = $340            0           340
 sister engine).
----------------------------------------------------------------------------------------------------------------

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.

[[Page 42652]]

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2025-21-03, Amendment 39-23175 (90 
FR 57675, December 12, 2025); and
0
b. Adding the following new airworthiness directive:

2026-14-06 CFM International, S.A.: Amendment 39-23407; Docket No. 
FAA-2026-7214; Project Identifier AD-2026-00225-E.

(a) Effective Date

    This airworthiness directive (AD) is effective July 27, 2026.

(b) Affected ADs

    This AD replaces AD 2025-21-03, Amendment 39-23175 (90 FR 57675, 
December 12, 2025) (AD 2025-21-03).

(c) Applicability

    This AD applies to CFM International, S.A. 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 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 that has accumulated more than 1,100 South Asia takeoffs, 
and has accumulated 2,500 part cycles since new (PCSN) for Group 1 
engines, or 5,100 PCSN for Group 2 engines.

(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) 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.

(h) 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 PCSN 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 (SB) LEAP-1A-72-00-0485-01A-930A-D, Issue 004-00, dated May 
19, 2026 (CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-00).
    (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 004-00.

(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 PCSN, 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 004-00.
    (ii) Thereafter, at intervals not to exceed 300 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 004-00.

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

    Based on the results of the BSI required by paragraphs (h)(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 004-00.

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

    (i) If the sister engine has accumulated 50 FCs or less since 
the last BSI of the HPT rotor stage 1 blade for Group 1 engines, or 
100 FCs or less since the last BSI of the HPT rotor stage 1 blade 
for Group 2 engines, no further action is required by paragraph 
(h)(4) of this AD.
    (ii) Based on the BSI results disposition required by paragraph 
(h)(3) of this AD, if re-inspection or replacement of the HPT rotor 
stage 1 blades is required, within 50 FCs, then within 5 FCs after 
performing the inspection required by paragraph (h)(1) or (2) of 
this AD, as applicable, either inspect or replace the affected 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 004-00. 
Where CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-00, specifies 
to remove the engine, this AD requires replacement of the HPT rotor 
stage 1 blades.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the initial BSI required 
by paragraphs (h)(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; or Issue 
003-00, dated July 30, 2025.
    (2) The inspections and corrective actions as required by 
paragraphs (h)(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 (h)(1) through (4) of this AD.

(j) No Reporting Requirement

    Where CFM SB LEAP-1A-72-00-0485-01A-930A-D, Issue 004-00, 
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)(1) 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

    (1) For more information about this AD, contact Mehdi Lamnyi, 
Aviation Safety

[[Page 42653]]

Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 
(781) 238-7743; email: [email protected].
    (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) CFM Service Bulletin LEAP-1A-72-00-0485-01A-930A-D, Issue 
004-00, dated May 19, 2026
    (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 July 6, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division, 
Aircraft Certification Service.
[FR Doc. 2026-13979 Filed 7-9-26; 8:45 am]
BILLING CODE 4910-13-P

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