[Federal Register Volume 90, Number 177 (Tuesday, September 16, 2025)]
[Rules and Regulations]
[Pages 44489-44491]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-17852]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 90, No. 177 / Tuesday, September 16, 2025 /
Rules and Regulations
[[Page 44489]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0627; Project Identifier MCAI-2024-00608-E;
Amendment 39-23135; AD 2025-18-08]
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.) Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2024-06-02
for all GE Aviation Czech s.r.o. (GEAC) Model M601D-11, M601E-11,
M601E-11A, M601E-11AS, M601E-11S, and M601F engines. AD 2024-06-02
required a one-time detailed visual inspection (DVI) of the compressor
case pad welds for any crack, and replacement of the compressor case if
necessary. Since the FAA issued AD 2024-06-02, the manufacturer
determined that the compliance time for the DVI can be extended, and
repetitive inspections of the centrifugal compressor case must be
accomplished. This AD requires performing repetitive DVIs of the
compressor case pad welds for any crack, replacing the compressor case
if necessary, and sending certain inspection results to the
manufacturer. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 21, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 21,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0627; 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 European Union Aviation Safety Agency (EASA) material
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +49 221 8999 000; email: [email protected];
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, 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-2025-0627.
FOR FURTHER INFORMATION CONTACT: Robert Charbonneau, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (781) 238-7132; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2024-06-02, Amendment 39-22707 (89 FR
21196, March 27, 2024) (AD 2024-06-02). AD 2024-06-02 applied to all
GEAC Model M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, and
M601F engines. AD 2024-06-02 required a one-time DVI of the compressor
case pad welds for any crack and replacement of the compressor case if
necessary. The FAA issued AD 2024-06-02 to prevent failure of the
centrifugal compressor case.
The NPRM was published in the Federal Register on April 23, 2025
(90 FR 17022). The NPRM was prompted by EASA AD 2024-0194, dated
October 15, 2024 (EASA AD 2024-0194) (also referred to as the MCAI)
issued by EASA, which is Technical Agent for the Member States of the
European Union. The MCAI states that since that AD was issued, it has
been confirmed that the compliance time for the DVI can be extended,
and that repetitive DVIs of the affected part must be accomplished.
In the NPRM, the FAA proposed to require performing repetitive DVIs
of the compressor case pad welds for any crack, replacing the
compressor case if necessary, and sending certain inspection results to
the manufacturer.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-0627.
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 civil 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, that authority 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, to
include allowing the use of a part eligible for installation, this AD
is adopted as proposed in the NPRM. None of the changes will increase
the economic burden on any operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2024-0194, which specifies procedures for
performing repetitive DVIs of the compressor case pad welds for any
crack, replacement of the compressor case if necessary, and sending
certain inspection results to the manufacturer.
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.
[[Page 44490]]
Differences Between This AD and the MCAI
GEAC Model M601D, M601D-1, M601D-2, M601D-11NZ, M601E, M601E-21,
M601FS, and M601Z engines do not have an FAA type certificate,
therefore this AD does not include those engines in the applicability.
Costs of Compliance
The FAA estimates that this AD affects 45 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect centrifugal compressor case...... 1 work-hour x $85 per hour $0 $85 $3,825
= $85.
Report inspection results................ 1 work-hour x $85 per hour 0 85 3,825
= $85.
----------------------------------------------------------------------------------------------------------------
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 engines
that might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace centrifugal compressor case........... 10 work-hours x $85 per hour = $5,000 $5,850
$850.
----------------------------------------------------------------------------------------------------------------
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.
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 be
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.
Regulatory Findings
The FAA has determined that 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:
0
a. Removing Airworthiness Directive 2024-06-02, Amendment 39-22707 (89
FR 21196, March 27, 2024); and
0
b. Adding the following new airworthiness directive:
2025-18-08 GE Aviation Czech s.r.o. (Type Certificate Previously
Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.):
Amendment 39-23135; Docket No. FAA-2025-0627; Project Identifier
MCAI-2024-00608-E.
(a) Effective Date
This airworthiness directive (AD) is effective October 21, 2025.
(b) Affected ADs
This AD replaces AD 2024-06-02, Amendment 39-22707 (89 FR 21196,
March 27, 2024) (AD 2024-06-02).
[[Page 44491]]
(c) Applicability
This AD applies to GE Aviation Czech s.r.o. (GEAC) (type
certificate previously held by WALTER Engines a.s. Walter a.s., and
MOTORLET a.s.) Model M601D-11, M601E-11, M601E-11A, M601E-11AS,
M601E-11S, and M601F engines.
(d) Subject
Joint Aircraft System Component (JASC) Codes 7120, Engine Mount
Section; 7230, Turbine Engine Compressor Section.
(e) Unsafe Condition
This AD was prompted by a report of a crack on the centrifugal
compressor case mount pad weld area caused by a non-conforming weld
(lack of welding penetration). The FAA is issuing this AD to prevent
failure of the centrifugal compressor case. The unsafe condition, if
not addressed, could result in crack propagation, possibly resulting
in engine separation and reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified in paragraph (h) of this AD, perform all
required actions within the compliance times specified in, and in
accordance with, European Union Aviation Safety Agency (EASA) AD
2024-0194, dated October 15, 2024 (EASA AD 2024-0194).
(h) Exceptions to EASA AD 2024-0194
(1) Where EASA AD 2024-0194 requires compliance from its
effective date, this AD requires using the effective date of this
AD.
(2) Where EASA AD 2024-0194 defines serviceable part as
``Centrifugal compressor case, eligible for installation in
accordance with GEAC instructions, which is not an affected part'',
this AD requires replacing that text with ``centrifugal compressor
case, eligible for installation, which is not an affected part''.
(3) Where EASA AD 2024-0194 specifies ``Replacing the affected
part of an engine with a centrifugal compressor case, eligible for
installation in accordance with GEAC instructions, which is not an
affected part'', this AD requires replacing that text with
``Replacing the affected part of an engine with a centrifugal
compressor case, eligible for installation, which is not an affected
part''.
(4) Where EASA AD 2024-0194 specifies to contact the
manufacturer for approved instructions if any crack is detected on
an affected part, this AD requires replacement of the compressor
case.
(5) This AD does not adopt the ``Remarks'' paragraph of EASA AD
2024-0194.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, AIR-730 International Validation 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 AIR-730 International Validation
Branch, send it to the attention of the person identified in
paragraph (j) of this AD and email to: [email protected].
(j) Additional Information
For more information about this AD, contact Robert Charbonneau,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (781) 238-7132; email:
[email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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) European Union Aviation Safety Agency (EASA) AD 2024-0194,
dated October 15, 2024.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: [email protected]; website: easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu.
(4) You may view this material at FAA, 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 September 3, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-17852 Filed 9-15-25; 8:45 am]
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