Airworthiness Directives; CFM International, S.A. Engines, 8889-8891 [2025-02204]

Download as PDF Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 lotter on DSK11XQN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 16:07 Feb 03, 2025 Jkt 265001 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 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 8889 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: E:\FR\FM\04FER1.SGM 04FER1 8890 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations ESTIMATED COSTS Action Labor cost Replace HPT rotor interstage seal ................. 12 work-hours × $85 per hour = $1,020 ........ 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 Parts cost (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: $195,000 Cost per product $196,020 Cost on U.S. operators $10,977,120 (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 lotter on DSK11XQN23PROD with RULES1 LEAP–1A23, LEAP–1A24, LEAP–1A24E1, LEAP–1A26, LEAP– 1A26E1, LEAP–1A29, LEAP–1A30, LEAP–1A32, LEAP–1A33, LEAP–1A33B2, and LEAP–1A35A. LEAP–1A26CJ and LEAP–1A29CJ ......................................................... (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 VerDate Sep<11>2014 16:07 Feb 03, 2025 Jkt 265001 11,100 cycles since new (CSN) accumulated on the affected part. 9,700 CSN accumulated on the affected part. 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–72–00–052501A–930A–D Issue 002–00, in any LEAP–1A engine. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 (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: E:\FR\FM\04FER1.SGM 04FER1 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations (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. 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. (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. [Docket No. FAA–2024–2141; Project Identifier MCAI–2024–00421–T; Amendment 39–22931; AD 2025–01–07] lotter on DSK11XQN23PROD with RULES1 (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 VerDate Sep<11>2014 16:07 Feb 03, 2025 Jkt 265001 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 RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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 SUMMARY: PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 8891 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) E:\FR\FM\04FER1.SGM 04FER1

Agencies

[Federal Register Volume 90, Number 22 (Tuesday, February 4, 2025)]
[Rules and Regulations]
[Pages 8889-8891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-02204]


-----------------------------------------------------------------------

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: [email protected].
     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: [email protected].

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:

[[Page 8890]]



                                                 Estimated costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace HPT rotor interstage seal.....  12 work-hours x $85 per         $195,000        $196,020     $10,977,120
                                         hour = $1,020.
----------------------------------------------------------------------------------------------------------------

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:

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- 11,100 cycles since new (CSN)
 1A26, LEAP-1A26E1, LEAP-1A29, LEAP-      accumulated on the affected
 1A30, LEAP-1A32, LEAP-1A33, LEAP-        part.
 1A33B2, and LEAP-1A35A.
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:

[[Page 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: [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.

(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: [email protected].

(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: [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 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
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