(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective June 26, 2025.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD  applies  to  General Electric Company (GE) Model CF34-10E2A1,
    CF34-10E5, CF34-10E5A1, CF34-10E6, CF34-10E6A1,  CF34-10E7,  and CF34-
    10E7-B engines  with an installed high-pressure turbine  (HPT) shroud/
    low-pressure turbine (LPT)  nozzle assembly  having part number  (P/N)
    2205M38G01, 2205M38G02, 2205M38G03, 2205M38G04, or 2205M38G05.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD was prompted  by a report of failed retention features  of the
    inner and outer support air ducts  (commonly referred to  as spoolies)
    discovered  during engine disassembly.  The FAA is issuing  this AD to
    prevent failure of the combustion case.  The unsafe condition,  if not
    addressed, could result in the inner surface  of  the  combustion case
    having reduced load carrying capability  for  fan blade out  or  other
    extreme event  with possible engine separation  and  loss  of the air-
    plane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

(1) At the next engine shop visit  after the effective date of this AD, do
    a visual inspection  of  the  combustion case inner shell surface  for
    wear and gouges  in accordance  with paragraphs 3.A.(1) and (2) of the
    Accomplishment Instructions  in  GE CF34-10E Service Bulletin (SB) 72-
    0351 R01, dated July 17, 2019 (GE CF34-10E SB 72-0351 R01).

(i) If any wear or gouges are found during any inspection required by par-
    agraph (g)(1) of this AD, before further flight, repair the combustion
    case in accordance with Table 1 of GE CF34-10E SB 72-0351 R01.

(ii) If any wear  or gouges exceed the maximum repairable limit in accord-
     ance  with  Table 1  of  GE CF34-10E SB 72-0351 R01,  before  further
     flight, remove the combustion case from service.

(2) At the next engine shop visit after the effective date of this AD, re-
    work the affected HPT shroud/LPT nozzle assembly,  in  accordance with
    paragraph 3.B.  of  the  Accomplishment Instructions of GE CF34-10E SB
    72-0351 R01.

(h) DEFINITION

    For the purpose of this AD,  an "engine shop visit" is defined as when
    the HPT shroud/LPT nozzle assembly  or  the  HPT rotor disk is removed
    from the engine.

(i) 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 proce-
    dures 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 (j) of this
    AD and email to: AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector,  or  lacking a principal inspector,  the manager of the local
    flight standards district office/certificate holding district office.

(j) RELATED INFORMATION

    For more information about this AD,  contact Alexei Marqueen, Aviation
    Safety Engineer, FAA,  2200 South 216th Street,  Des Moines, WA 98198;
    phone: (781) 238-7178; email: alexei.t.marqueen@faa.gov.

(k) 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) GE CF34-10E Service Bulletin 72-0351 R01, dated July 17, 2019.

(ii) [Reserved]

(3) For GE material identified in this AD, contact GE, 1 Neumann Way, Cin-
    cinnati, OH 45215; phone: (513) 552-3272; email: aviation.fleetsupport
    @ge.com; website: 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 Admin-
    istration (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 May 8, 2025. Peter A White, Deputy Director, Integrated Certifi-
cate Management Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Alexei Marqueen, Aviation Safety Engineer
FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-7178;
email: alexei.t.marqueen@faa.gov.