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2022-26-01 GE AVIATION CZECH S.R.O (TYPE CERTIFICATE PREVIOUSLY HELD BY WALTER ENGINES A.S., WALTER A.S., AND MOTORLET A.S.): Amendment 39-22279; Docket No. FAA-2022-1239; Project Identifier MCAI-2022-00301-E.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective January 26, 2023.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11,
    M601E-11A, M601E-11AS, M601E-11S, M601F,  H75-100, H75-200,  H80, H80-
    100, H80-200, H85-100, and H85-200  model turboprop engines  installed
    on single-engine airplanes, with an installed combustion chamber outer
    liner having part numbers (P/Ns) M601-229.3, M601-229.3A, M601-229.3B,
    M601-229.31A, or M601-229.31B.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 7240,  Turbine Engine Com-
    bustion Section.

(e) UNSAFE CONDITION

    This AD was prompted by reports of cracks in dilution tube weld  areas
    of the combustion chamber outer liner.  The FAA is issuing this AD  to
    prevent  failure of  the combustion  chamber outer  liner. The  unsafe
    condition, if not  addressed, could result  in uncontained release  of
    the combustion chamber outer liner, loss of engine power, 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) At the next 300-hour (Type 3) engine inspection,  or  within 25 flight
    hours (FHs)  after  the  effective date of this AD,  whichever  occurs
    later,  and thereafter  at intervals not to exceed 300 FHs,  perform a
    borescope inspection (BSI) of the dilution tube weld areas of the com-
    bustion chamber outer liner in accordance  with the Accomplishment In-
    structions, paragraph 2.1 of GEAC Alert Service Bulletin (ASB) ASB-H75
    -72-40-00-0056 [01],  ASB-M601E-72-40-00-0113 [01],  ASB-H80-72-40-00-
    0099 [01], ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-00-0064 [01],
    ASB-M601Z-72-40-00-0063 [01],  and  ASB-H85-72-40-00-0045 [01] (single
    document; formatted as service bulletin identifier [revision number]),
    dated February 16, 2022 (the ASB).

(2) If a crack is detected  during any BSI required by paragraph (g)(1) of
    this  AD,  before  further flight,  perform the  applicable corrective
    actions in accordance with the Accomplishment Instructions,  paragraph
    2.1, Table 1 of the ASB.

(h) TERMINATING ACTION

    Replacing the affected combustion chamber  outer liner  with a combus-
    tion chamber outer liner that does not have  P/N M601-229.3, M601-229.
    3A, M601-229.3B, M601-229.31A,  or M601-229.31B,  constitutes a termi-
    nating action for the repetitive inspections required by paragraph (g)
    (1) of this AD.

(i) CONDITIONAL PART INSTALLATION

(1) After the effective date of this AD,  it is permissible  to install an
    engine, having an affected  combustion chamber outer liner  installed,
    on a single-engine airplane, provided that prior to operation, the BSI
    required by paragraph (g)(1) of this AD is performed and, depending on
    the  findings,  the  applicable corrective  actions  are  performed as
    required by paragraph (g)(2) of this AD.

(2) After the effective date of this AD,  it is permissible  to install an
    affected combustion chamber  outer  liner  on the engine  of a single-
    engine airplane, provided that it is a part eligible for installation,
    as defined in paragraph (j) of this AD, and provided that prior to op-
    eration,  the BSI required by paragraph (g)(1) of this AD is performed
    and, depending on the findings,  the applicable corrective actions are
    performed as required by paragraph (g)(2) of this AD.

(j) DEFINITIONS

    For the purpose of this AD,  a "part eligible for installation"  is an
    affected combustion chamber outer liner,  which was not previously in-
    stalled on an engine,  or  an  affected combustion chamber outer liner
    that, before installation, has passed an inspection (no defects found)
    in accordance with the Accomplishment Instructions, paragraphs 2.2 and
    2.3 of the ASB, or a combustion chamber outer liner that does not have
    P/Ns M601-229.3, M601-229.3A, M601-229.3B, M601-229.31A,  or M601-229.
    31B.

(k) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

    The  Manager,  ECO  Branch,  FAA,  has the authority  to approve AMOCs
    for this AD, if requested  using the procedures found in  Sec.  39.19.
    In accordance with  Sec.  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
    (l)(2) of this AD or  email to: ANE-AD-AMOC@faa.gov. 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) Refer  to  European Union Aviation Safety Agency  (EASA) AD 2022-0034,
    dated March 4, 2022,  for  related  information.  This EASA AD  may be
    found in the AD docket  at regulations.gov  under Docket No. FAA-2022-
    1239.

(2) For more information about this AD, contact Barbara Caufield, Aviation
    Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA
    01803; phone: (781) 238-7146; email: barbara.caufield@faa.gov.

(m) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the service information  listed in this paragraph under 5
    U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) GE Aviation Czech s.r.o. (GEAC)  Alert Service Bulletin (ASB) ASB-H75-
    72-40-00-0056 [01],  ASB-M601E-72-40-00-0113  [01],  ASB-H80-72-40-00-
    0099 [01], ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-00-0064 [01],
    ASB-M601Z-72-40-00-0063 [01],  and  ASB-H85-72-40-00-0045 [01] (single
    document; formatted as service bulletin identifier [revision number]),
    dated February 16, 2022.

(ii) [Reserved]

(3) For GEAC service information identified in this AD,  contact  GE Avia-
    tion Czech s.r.o., Beranovych 65,  199 02 Praha 9, Letnany,  Czech Re-
    public; phone: +420 222 538 111.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section, Operational Safety Branch, 1200 District Avenue, Burling
    -ton, MA 01803.  For information  on the availability of this material
    at the FAA, call (817) 222-5110.

(5) You may view  this service information  that is incorporated by refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material  at NARA,  email: fr.
    inspection@nara.gov,  or go to: www.archives.gov/federal-register/cfr/
    ibr-locations.html.

Issued on December 7, 2022.  Christina Underwood, Acting Director, Compli-
ance & Airworthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT:  Barbara Caufield,  Aviation Safety Engi-
neer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;  phone:
(781) 238-7146; email: barbara.caufield@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1239; Project Identifier MCAI-2022-00301-E;
Amendment 39-22279; AD 2022-26-01]
RIN 2120-AA64

Airworthiness Directives; GE Aviation Czech s.r.o. (Type
Certificate Previously Held by WALTER Engines a.s., Walter a.s., and
MOTORLET a.s.) Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A,
M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200,
H85-100, and H85-200 model turboprop engines. This AD was prompted by
reports of cracks in dilution tube weld areas of the combustion chamber
outer liner. This AD requires initial and repetitive borescope
inspections (BSIs) of the dilution tube weld areas of the combustion
chamber outer liner and, depending on the results of the inspections,
replacement of the combustion chamber outer liner with a part eligible
for installation. The FAA is issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective January 26, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 26,
2023.

ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1239; 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 GEAC service information identified in this final
rule, contact GE Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02
Praha 9, Let[ncaron]any, Czech Republic; phone: +420 222 538 111.
You may view this 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 (817) 222-5110. It is
also available at regulations.gov under Docket No. FAA-2022-1239.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7146; email: barbara.caufield@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 GEAC M601D-11,
M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200,
H80, H80-100, H80-200, H85-100, and H85 200 model turboprop engines.
The NPRM published in the Federal Register on September 27, 2022 (87 FR
58466). The NPRM was prompted by AD 2022-0034, dated March 4, 2022,
issued by the European Union Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Union
(referred to after this as ``the MCAI''). The MCAI states that
occurrences of cracks in dilution tube weld areas of the combustion
chamber outer liner have been reported. These cracks can lead to crack
propagation, possibly resulting in part separation, loss of engine
power, and reduced control of the aircraft.
In the NPRM, the FAA proposed to require initial and repetitive
BSIs of the dilution tube weld areas of the combustion chamber outer
liner and, depending on the results of the inspections, corrective
action in accordance with the service information. The FAA is issuing
this AD to address the unsafe condition on these products.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2022-1239.

Discussion of Final Airworthiness Directive

Comments

The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI referenced above. The FAA reviewed the relevant data and
determined that air safety requires adopting this 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.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GEAC Alert Service Bulletin (ASB) ASB-H75-72-40-
00-0056 [01], ASB-M601E-72-40-00-0113 [01], ASB-H80-72-40-00-0099 [01],
ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-00-0064 [01], ASB-M601Z-
72-40-00-0063 [01], and ASB-H85-72-40-00-0045 [01], (single document;
formatted as service bulletin identifier [revision number]), dated
February 16, 2022. This service information specifies procedures for
BSIs of the dilution tube weld areas of the combustion chamber outer
liner and replacement of the combustion chamber outer liner.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES.

Costs of Compliance

The FAA estimates that this AD affects 33 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
BSI of combustion chamber outer liner 2.5 work-hours x $85 per hour = $212.50 $0 $212.50 $7,012.50

The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The agency has no way of determining the number of aircraft
that might need these replacements:

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
On-wing replacement of combustion chamber outer liner 64 work-hours x $85 per hour = $5,440
$74,909
$80,349
In-shop replacement of combustion chamber outer liner 56 work-hours x $85 per hour = $4,760
74,909
79,669

The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.

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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: