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2021-23-51 GENERAL ELECTRIC COMPANY:
Project Identifier AD-2021-01192-E

(a) EFFECTIVE DATE

    This emergency AD is effective upon receipt.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to General Electric Company (GE)  CF34-8C1,  CF34-8C5,
    CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2,  CF34-8E2A1,
    CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6 and CF34-8E6A1 model turbo-
    fan engines installed on an airplane  that  has  accumulated more than
    250 parked days outdoors in the last 24 months within 10 miles (16 km)
    from a saltwater coastline.

Note 1 to paragraph (c):A "parked day" is 24 consecutive hours with no en-
gine operation.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 7230,  Turbine Engine Com-
    pression Section.

(e) UNSAFE CONDITION

    This AD was prompted by an in-flight shutdown  of an engine and subse-
    quent  investigation  by  the  manufacturer  that  revealed  a  broken
    variable  geometry  (VG)  actuator rod  end  caused  by corrosion  and
    seizure of the rod end bearing.  The FAA is issuing this AD  to detect
    corrosion and seizure of the rod end bearing. The unsafe condition, if
    not addressed, could result in failure of one or more engines, loss of
    engine thrust control, and reduced control of the airplane.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) On one engine installed on an airplane,  before accumulating 30 flight
    hours (FHs) or within 5 calendar days,  whichever  occurs  first after
    the effective date of this AD,  perform  an  inspection  of the master
    compressor VG actuator, significant item number (SIN) 30401, and slave
    compressor VG actuator, SIN 30402,  in accordance with the Accomplish-
    ment Instructions, paragraphs 3.A.(1) and (2),  of  GE CF34-8C Service
    Bulletin (SB) 75-0028 R00 (GE CF34-8C SB 75-0028) or GE CF34-8E SB 75-
    0023 R00  (GE CF34-8E SB 75-0023),  both  dated  November 2, 2021,  as
    applicable to the engine model.

(2) On the other engine  installed  on the airplane,  not inspected as re-
    quired by paragraph (g)(1) of this AD, before accumulating 350 FHs  or
    within 60 calendar  days, whichever occurs  first after the  effective
    date of  this AD,  perform an  inspection of  the master compressor VG
    actuator, SIN 30401, and slave  compressor VG actuator, SIN 30402,  in
    accordance with  the Accomplishment  Instructions, paragraphs  3.A.(1)
    and  (2),  of GE  CF34-8C  SB 75-0028  or  GE CF34-8E  SB  75-0023, as
    applicable to the engine model.

(3) For engines not in service, before further flight,  perform an inspec-
    tion of the master compressor VG actuator, SIN 30401,  and  slave com-
    pressor VG actuator, SIN 30402,  in accordance with the Accomplishment
    Instructions, paragraphs 3.A.(1) and (2),  of GE CF34-8C SB 75-0028 or
    GE CF34-8E SB 75-0023, as applicable to the engine model.

(4) If the master compressor VG actuator, SIN 30401, or the slave compres-
    sor VG actuator, SIN 30402,  does not pass any inspection  required by
    paragraphs (g)(1) through (3) of this AD,  before further flight,  re-
    move the part and replace with a part eligible for installation.

(h) REPORTING REQUIREMENTS

    Within 10 days after performing the inspections required by paragraphs
    (g)(1) through (3) of this AD,  in accordance  with paragraphs 3.A.(1)
    and (2), of GE CF34-8C SB 75-0028 or GE CF34-8E SB 75-0023,  send your
    inspection report form, pictures, or report findings to GE at aviation
    .fleetsupport@ae.ge.com.

(i) SPECIAL FLIGHT PERMIT

    Special flight permits are prohibited.

(j) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, ECO 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  certification
    office, send it to the attention of the person identified in paragraph
    (k)(1) of this AD. Information may be emailed to: ANE-ADAMOC@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.

(k) RELATED INFORMATION

(1) For further information  about this AD,  contact:  Scott M. Stevenson,
    Aviation Safety Engineer, ECO Branch, FAA,  1200 District Avenue, Bur-
    lington, MA 01803;  phone: (781) 238-7132; fax: (781) 238-7199; email:
    scott.m.stevenson@faa.gov.

(2) For service information identified in this AD,  contact: General Elec-
    tric Company, 1 Neumann Way, Cincinnati, OH 45215;  phone:  (513) 552-
    3272; email: aviation.fleetsupport@ae.ge.com; website: www.ge.com. You
    may view this referenced service information 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 (781) 238-7759.

Issued on November 4, 2021. Lance T Gant, Director, Compliance & Airworth-
iness Division, Aircraft Certification Service.
PREAMBLE 

DATE: November 4, 2021
AD #: 2021-23-51

Emergency Airworthiness Directive (AD) 2021-23-51 is sent to owners and operators of General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines.

Background

This emergency AD was prompted by an in-flight shutdown of an engine and subsequent investigation by the manufacturer that revealed a broken compressor variable geometry (VG) actuator rod end caused by corrosion and seizure of the rod end bearing. This condition, if not addressed, could result in failure of one or more engines, loss of engine thrust control, and reduced control of the airplane.

Relevant Service Information

The FAA reviewed GE CF34-8C Service Bulletin (SB) 75-0028 R00 and GE CF34-8E SB 75-0023 R00, both dated November 2, 2021. These SBs specify procedures for performing a onetime inspection of the master compressor VG actuator and slave compressor VG actuator, differentiated by engine model, to identify possible rod end corrosion or seizure.

FAA’s Determination


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

AD Requirements

This AD requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. This AD may also require reporting the results of the inspection to GE.

Interim Action

The FAA considers this AD to be an interim action. The FAA anticipates that further AD action will follow.

Paperwork Reduction Act


A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to take approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.

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.

Presentation of the Actual AD


The FAA is issuing this AD under 49 U.S.C. Section 44701 according to the authority delegated to me by the Administrator.