Rule2025-03383
Airworthiness Directives; General Electric Company Engines
Primary source
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Published
March 4, 2025
Effective
April 8, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CT7-5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, CT7-9C3, CT7-9D, and CT7-9D2 engines. This AD was prompted by the manufacturer's determination that certain GE Model CT7 fleets have affected cooling plates installed that do not meet lifing guidelines. This AD requires replacement of the stage 1 turbine forward cooling plate and the stage 2 turbine aft cooling plate. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 41 (Tuesday, March 4, 2025)</title>
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[Federal Register Volume 90, Number 41 (Tuesday, March 4, 2025)]
[Rules and Regulations]
[Pages 11120-11122]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-03383]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2540; Project Identifier AD-2024-00343-E;
Amendment 39-22974; AD 2025-05-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain General Electric Company (GE) Model CT7-5A2, CT7-5A3, CT7-7A,
CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, CT7-9C3, CT7-9D, and CT7-9D2
engines. This AD was prompted by the manufacturer's determination that
certain GE Model CT7 fleets have affected cooling plates installed that
do not meet lifing guidelines. This AD requires replacement of the
stage 1 turbine forward cooling plate and the stage 2 turbine aft
cooling plate. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 8, 2025.
ADDRESSES: AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a>
under Docket No. FAA-2024-2540; 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.
FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-
7241; email: <a href="/cdn-cgi/l/email-protection#97e4e2f9f0faf8b9f3b9f4fff8d7f1f6f6b9f0f8e1"><span class="__cf_email__" data-cfemail="0c7f79626b61632268226f64634c6a6d6d226b637a">[email protected]</span></a>.
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 GE Model CT7-
5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, CT7-
9C3, CT7-9D, and CT7-9D2 engines. The NPRM published in the Federal
Register on November 26, 2024 (89 FR 93228). The NPRM was prompted by
the manufacturer's determination that certain GE Model CT7 fleets have
affected cooling plates installed that do not meet lifing guidelines.
In the NPRM, the FAA proposed to require replacement of the stage 1
turbine forward cooling plate and the stage 2 turbine aft cooling
plate. The FAA is issuing this AD to address the unsafe condition on
these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received one comment from the Airline Pilots Association,
International. The commenter 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.
Costs of Compliance
The FAA estimates that this AD affects 228 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
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Replace stage 1 turbine forward 8 work-hours x $85 per $88,360 $89,040 $20,301,120
cooling plate and stage 2 turbine hour = $680.
aft cooling plate.
----------------------------------------------------------------------------------------------------------------
The above costs presume that the installed engine requires
replacement of both the stage 1 turbine forward cooling plate and stage
2 turbine aft cooling plate. It is possible that only one of these
needs replacement, thus reducing the cost of this AD.
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.
[[Page 11121]]
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:
2025-05-02 General Electric Company: Amendment 39-22974; Docket No.
FAA-2024-2540; Project Identifier AD-2024-00343-E.
(a) Effective Date
This airworthiness directive (AD) is effective April 8, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) Model CT7-5A2,
CT7-5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, CT7-9C3,
CT7-9D, and CT7-9D2 engines with an installed stage 1 turbine
forward cooling plate having part number (P/N) 6064T08P01; or with
an installed stage 2 turbine aft cooling plate having P/N 6064T07P05
or P/N 6068T36P01.
(d) Subject
Joint Aircraft System Component (JASC) Code 7200, Engine
(Turbine/Turboprop).
(e) Unsafe Condition
This AD was prompted by the manufacturer's determination that
certain GE Model CT7 fleets have affected cooling plates installed
that do not meet lifing guidelines. The FAA is issuing this AD to
prevent the failure of the stage 1 turbine forward cooling plate and
stage 2 turbine aft cooling plate. The unsafe condition, if not
addressed, could result in uncontained engine failure and damage to
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within the compliance times specified in paragraphs (g)(1)
through (3) of this AD, replace the affected stage 1 turbine forward
cooling plate or stage 2 turbine aft cooling plate, as applicable,
with a replacement P/N eligible for installation, in accordance with
table 1 to the introductory text of paragraph (g) of this AD:
Table 1 to the Introductory Text of Paragraph (g)--Cooling Plate Replacement P/Ns
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Engine group Part name Affected P/N Replacement P/N
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1............................... Stage 1 turbine 6064T08P01...................... 6064T08P04.
forward cooling
plate.
1............................... Stage 2 turbine aft 6064T07P05...................... 6064T07P07.
cooling plate.
1............................... Stage 2 turbine aft 6068T36P01...................... 6068T36P04.
cooling plate.
2............................... Stage 1 turbine 6064T08P01...................... 6064T08P03 or
forward cooling 6064T08P04.
plate.
2............................... Stage 2 turbine aft 6064T07P05...................... 6064T07P07.
cooling plate.
2............................... Stage 2 turbine aft 6068T36P01...................... 6068T36P04.
cooling plate.
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(1) For Group 1 engines with an affected part installed, replace
the affected part at the next exposure of the gas generator stator
assembly that occurs after the effective date of this AD.
(2) For Group 2 engines with an affected part installed having
7,000 part cycles since new (PCSN) or less as of the effective date
of this AD, replace the affected part at the next exposure of the
gas generator stator assembly or within 2,000 flight cycles (FCs)
but before reaching 7,500 PCSN, whichever occurs first after the
effective date of this AD.
(3) For Group 2 engines with an affected part installed having
more than 7,000 PCSN as of the effective date of this AD, replace
the affected part at the next exposure of the gas generator stator
assembly or within 500 FCs, whichever occurs first after the
effective date of this AD.
(h) Definitions
For the purpose of this AD:
(1) ``Group 1 engines'' are GE Model CT7-5A2, CT7-5A3, CT7-9B,
CT7-9B1, CT7-9B2, CT7-9D, and CT7-9D2 engines.
(2) ``Group 2 engines'' are GE Model CT7-7A, CT7-7A1, CT7-9C,
and CT7-9C3 engines.
(3) ``Exposure of the gas generator stator assembly'' is when
the gas generator rotor and stator assembly are separated from the
combustor module.
(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 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-520 Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (j) of this AD and email to: <a href="/cdn-cgi/l/email-protection#26676b69656640474708414950"><span class="__cf_email__" data-cfemail="a1e0eceee2e1c7c0c08fc6ced7">[email protected]</span></a>.
(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.
(j) Additional Information
For more information about this AD, contact Sungmo Cho, Aviation
Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198;
phone: (781) 238-7241; email: <a href="/cdn-cgi/l/email-protection#ea999f848d8785c48ec4898285aa8c8b8bc48d859c"><span class="__cf_email__" data-cfemail="186b6d767f7577367c367b7077587e7979367f776e">[email protected]</span></a>.
(k) Material Incorporated by Reference
None.
[[Page 11122]]
Issued on February 25, 2025.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-03383 Filed 3-3-25; 8:45 am]
BILLING CODE 4910-13-P
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