Proposed Rule2024-27664
Airworthiness Directives; General Electric Company Engines.
Primary source
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Published
November 26, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt 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 proposed 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 proposed AD would require replacement of the stage 1 turbine forward cooling plate and the stage 2 turbine aft cooling plate. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 228 (Tuesday, November 26, 2024)</title>
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[Federal Register Volume 89, Number 228 (Tuesday, November 26, 2024)]
[Proposed Rules]
[Pages 93228-93230]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-27664]
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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]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Engines.
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt 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 proposed 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 proposed AD
would require replacement of the stage 1 turbine forward cooling plate
and the stage 2 turbine aft cooling plate. The FAA is proposing this AD
to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 10,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
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#5c2f29323b31337238723f34331c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="87f4f2e9e0eae8a9e3a9e4efe8c7e1e6e6a9e0e8f1">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2024-2540;
Project Identifier AD-2024-00343-E'' at the beginning of your comments.
The most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. The FAA will consider all comments received by the closing date
and may revise this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Sungmo Cho, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
[[Page 93229]]
Background
In 2004, the manufacturer notified the FAA of the identification of
an analytic life shortfall on affected stage 1 turbine forward cooling
plates and stage 2 turbine aft cooling plates installed on certain GE
CT7 Model engines. As a result, GE published updated service material
to remove affected parts at reduced cyclic limits. Based on the results
of a 2019 fleet survey, the manufacturer determined that certain fleets
still have affected cooling plates installed and in service which are
above the recommended removal limits. Specifically, the affected fleet
includes 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. This condition, if not
addressed, could result in the cooling plates failing and lead to
uncontained engine failure and damage to the airplane.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require replacement of the stage 1 turbine
forward cooling plate having part number (P/N) 6064T08P01 and the stage
2 turbine aft cooling plate having P/N 6064T07P05 or P/N 6068T36P01.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 228 engines installed on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
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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.
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The above costs presume that the installed engine would require
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
would need replacement, thus reducing the cost of the proposed 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.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
General Electric Company: Docket No. FAA-2024-2540; Project
Identifier AD-2024-00343-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 10, 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.
[[Page 93230]]
(g) Required Actions
(1) Within the compliance times specified in paragraphs
(g)(1)(i) through (iii) 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 paragraph (g)(1) of this AD:
(i) 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.
(ii) 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.
(iii) 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.
Table 1 to Paragraph (g)(1): Cooling Plate Replacement P/Ns
----------------------------------------------------------------------------------------------------------------
Engine group Part name Affected P/N Replacement P/N
----------------------------------------------------------------------------------------------------------------
1.................................... Stage 1 turbine forward 6064T08P01 6064T08P04
cooling plate.
1.................................... Stage 2 turbine aft cooling 6064T07P05 6064T07P07
plate.
1.................................... Stage 2 turbine aft cooling 6068T36P01 6068T36P04
plate.
2.................................... Stage 1 turbine forward 6064T08P01 6064T08P03 or
cooling plate. 6064T08P04
2.................................... Stage 2 turbine aft cooling 6064T07P05 6064T07P07
plate.
2.................................... Stage 2 turbine aft cooling 6068T36P01 6068T36P04
plate.
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(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#9fded2d0dcdff9fefeb1f8f0e9"><span class="__cf_email__" data-cfemail="dd9c90929e9dbbbcbcf3bab2ab">[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#1d6e68737a70723379337e75725d7b7c7c337a726b"><span class="__cf_email__" data-cfemail="9feceaf1f8f2f0b1fbb1fcf7f0dff9fefeb1f8f0e9">[email protected]</span></a>.
(k) Material Incorporated by Reference
None.
Issued on November 20, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-27664 Filed 11-25-24; 8:45 am]
BILLING CODE 4910-13-P
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