Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 8889 

website easa.europa.eu. You may find this 

EASA AD on the EASA website at 

ad.easa.europa.eu. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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 fr.inspection@

nara.gov. 

Issued on December 19, 2024. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02133 Filed 2–3–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2325; Project 

Identifier AD–2024–00412–E; Amendment 

39–22927; AD 2025–01–03] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

CFM International, S.A. (CFM) Model 

LEAP–1A and LEAP–1C engines. This 

AD was prompted by an investigation of 

an in-flight shut down event that 

revealed the aft arm of the high-pressure 

turbine (HPT) rotor interstage seal had 

failed. This AD requires removal from 

service and replacement of the HPT 

rotor interstage seal for LEAP–1A 

engines. Since the HPT rotor interstage 

seal part number is interchangeable 

between LEAP–1A and LEAP–1C 

engines, this AD also prohibits 

installation of these affected parts onto 

any LEAP–1A or LEAP–1C engine. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 11, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 11, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2325; 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: 

• 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: aviation.fleetsupport@

ge.com. 

• 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– 

2024–2325. 

FOR FURTHER INFORMATION CONTACT: 

Mehdi Lamnyi, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, 

Des Moines, WA 98198; phone: (781) 

238–7743; email: mehdi.lamnyi@

faa.gov. 

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–1A 

and LEAP–1C engines. The NPRM 

published in the Federal Register on 

October 2, 2024 (89 FR 80155). The 

NPRM was prompted by a report of an 

in-flight shutdown caused by turbine 

blades that had broken and metal that 

entered the exhaust. A manufacturer 

investigation later revealed that the aft 

arm of the HPT rotor interstage seal had 

failed due to a non-conforming surface 

condition in the fillet area coupled with 

higher-than-expected operating stress 

due to friction. In the NPRM, the FAA 

proposed to require removal from 

service and replacement of the HPT 

rotor interstage seal. Since the HPT rotor 

interstage seal part number is 

interchangeable between LEAP–1A and 

LEAP–1C engines, the NPRM also 

proposed to prohibit installation of 

these affected parts onto any LEAP–1A 

or LEAP–1C engine. 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 

Airline Pilots Association International 

(ALPA), StandardAero, an individual 

commenter, and an anonymous 

commenter. All commenters supported 

the NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, this AD is adopted as proposed 

in the NPRM. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed the following CFM 

material: 

• CFM Service Bulletin (SB) LEAP– 

1A–72–00–0525–01A–930A–D, Issue 

002–00, dated June 28, 2024, which 

provides the serial numbers (S/Ns) of 

the affected HPT rotor interstage seals 

for LEAP–1A engines. 

• CFM SB LEAP–1C–72–00–0124– 

01A–930A–D, Issue 001–00, dated 

September 5, 2024, which provides the 

S/Ns of the affected HPT rotor interstage 

seals that are excluded from installation 

onto LEAP–1C engines. 

This material also includes 

instructions for removal and installation 

of the HPT rotor interstage seal. 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 56 engines installed on airplanes 

of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 


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8890 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace HPT rotor interstage seal ................. 12 work-hours × $85 per hour = $1,020 ........ $195,000 $196,020 $10,977,120 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2025–01–03 CFM International, S.A.: 

Amendment 39–22927; Docket No. 

FAA–2024–2325; Project Identifier AD– 

2024–00412–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 11, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following CFM 

International, S.A. (CFM) engines: 

(1) 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. 

(2) Model LEAP–1C28, LEAP–1C30, and 

LEAP–1C30B1 engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an investigation 

of an in-flight shut down event that revealed 

the aft arm of the high-pressure turbine (HPT) 

rotor interstage seal had failed. The FAA is 

issuing this AD to prevent failure of the HPT 

rotor interstage seal. The unsafe condition, if 

not addressed, could result in failure of one 

or more engines, loss of thrust control, and 

loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For LEAP–1A engines having an HPT 

rotor interstage seal installed with a part 

number (P/N) and serial number (S/N) listed 

in Table 1 of CFM Service Bulletin (SB) 

LEAP–1A–72–00–0525–01A–930A–D, Issue 

002–00, dated June 28, 2024 (CFM SB LEAP– 

1A–72–00–0525–01A–930A–D Issue 002–00), 

at the next engine shop visit or before 

exceeding the applicable cyclic threshold in 

table 1 to paragraph (g)(1) of this AD, 

whichever occurs first after the effective date 

of this AD, remove the affected HPT rotor 

interstage seal from service and replace with 

a part eligible for installation. 

TABLE 1 TO PARAGRAPH (g)(1)—REMOVAL THRESHOLDS FOR EACH ENGINE MODEL

Engine model Removal cyclic threshold 

LEAP–1A23, LEAP–1A24, LEAP–1A24E1, LEAP–1A26, LEAP– 

1A26E1, LEAP–1A29, LEAP–1A30, LEAP–1A32, LEAP–1A33, 

LEAP–1A33B2, and LEAP–1A35A.

11,100 cycles since new (CSN) accumulated on the affected part. 

LEAP–1A26CJ and LEAP–1A29CJ ......................................................... 9,700 CSN accumulated on the affected part.

(2) For LEAP–1A engines having an HPT 

rotor interstage seal installed with a P/N and 

S/N listed in Table 2 of CFM SB LEAP–1A– 

72–00–0525–01A–930A–D Issue 002–00, at 

the next piece part exposure or before 

exceeding the applicable cyclic threshold in 

table 1 to paragraph (g)(1) of this AD, 

whichever occurs first after the effective date 

of this AD, remove the affected HPT rotor 

interstage seal from service and replace with 

a part eligible for installation. 

(h) Installation Prohibition 

(1) After the effective date of this AD, do 

not install an HPT rotor interstage seal 

having a P/N and S/N listed in Table 1 or 

Table 2 of CFM SB LEAP–1A–72–00–0525- 

01A–930A–D Issue 002–00, in any LEAP–1A 

engine. 

(2) After the effective date of this AD, do 

not install an HPT rotor interstage seal 

having a P/N and S/N listed in Table 1 of 

CFM SB LEAP–1C–72–00–0124–01A–930A– 

D, Issue 001–00, dated September 5, 2024, in 

any LEAP–1C engine. 

(i) Definitions 

For the purpose of this AD: 


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Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 8891 

(1) ‘‘LEAP–1A engines’’ are 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, 

LEAP–1A35A engines. 

(2) ‘‘LEAP–1C engines’’ are CFM Model 

LEAP–1C28, LEAP–1C30, and LEAP–1C30B1 

engines. 

(3) A ‘‘part eligible for installation’’ is any 

HPT rotor interstage seal having a P/N and 

S/N that is not listed in Table 1 or Table 2 

of CFM SB LEAP–1A–72–00–0525–01A– 

930A–D Issue 002–00. 

(4) An ‘‘engine shop visit’’ is the induction 

of an engine into the shop for maintenance 

involving the separation of major mating 

engine flanges, except for the separation of 

engine flanges solely for the purposes of 

transportation without subsequent engine 

maintenance. 

(5) A ‘‘piece-part exposure’’ is when the 

HPT rotor interstage seal is separated from 

the HPT rotor assembly. 

(j) 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 (k) of this AD and email to: 

AMOC@faa.gov. 

(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. 

(k) 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: mehdi.lamnyi@faa.gov. 

(l) 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 Service Bulletin LEAP–1A–72–00– 

0525–01A–930A–D, Issue 002–00, dated June 

28, 2024. 

(ii) CFM Service Bulletin LEAP–1C–72– 

00–0124–01A–930A–D, Issue 001–00, dated 

September 5, 2024. 

(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: 

aviation.fleetsupport@ge.com. 

(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 fr.inspection@nara.gov. 

Issued on January 30, 2025. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02204 Filed 2–3–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2141; Project 

Identifier MCAI–2024–00421–T; Amendment 

39–22931; AD 2025–01–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2022–11– 

01, which applied to certain Airbus SAS 

Model A300 series airplanes; Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes; and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). AD 2022–11–01 required a 

detailed inspection (DET) of the main 

landing gear (MLG) support rib 5 lower 

flange, a fluorescent penetrant 

inspection (FPI) around the spot facing 

of certain fastener holes if necessary, 

and applicable corrective actions. This 

AD was prompted by the determination 

that additional airplanes are affected by 

the unsafe condition. This AD continues 

to require the actions in AD 2022–11– 

01 and adds airplanes to the 

applicability, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective March 11, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 11, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2141; 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, the mandatory 

continuing airworthiness information 

(MCAI), 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: 

• For EASA material identified in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email 

ADs@easa.europa.eu; website 

easa.europa.eu. You may find this 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available at regulations.gov 

under Docket No. FAA–2024–2141. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aviation Safety Engineer, FAA, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: 206–231– 

3225; email: Dan.Rodina@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2022–11–01, 

Amendment 39–22051 (87 FR 32292, 

May 31, 2022) (AD 2022–11–01). AD 

2022–11–01 applied to certain Airbus 

SAS Model A300 and A300–600 series 

airplanes. AD 2022–11–01 required a 

one-time DET of the MLG support rib 5 

lower flange, inboard and outboard of 

rib 5, on the right-hand and left-hand 

sides (i.e., affected area); a one-time FPI 

around the spot facing of certain 

fastener holes if necessary; and 

applicable corrective actions. The FAA 

issued AD 2022–11–01 to address 

cracking in the affected area that, if not 

detected and corrected, could affect the 

structural integrity of the airplane. 

The NPRM published in the Federal 

Register on September 16, 2024 (89 FR 

75507). The NPRM was prompted by 

AD 2024–0145, dated July 23, 2024, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union (EASA AD 2024–0145) 

(also referred to as the MCAI). The 

MCAI states certain airplanes were 

excluded from the applicability of 

EASA AD 2021–0190, dated August 17, 

2021 (corresponds to AD 2022–11–01) 


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