Airworthiness Directives; General Electric Company Engines., 93228-93230 [2024-27664]
Download as PDF
<![CDATA[
93228
Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Proposed Rules
Accomplishment Instructions of the
applicable SB,’’ this AD requires replacing
that text with ‘‘Following inspection, if any
bolts are determined to be in an
unserviceable condition, before further flight,
replace the affected bolts in accordance with
the applicable SB.’’
Issued on November 20, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–27659 Filed 11–25–24; 8:45 am]
BILLING CODE 4910–13–P
(i) No Reporting Requirement
Although the service information
referenced in Transport Canada AD CF–
2023–60 specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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 (k) of this AD and email to:
AMOC@faa.gov.
(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.
(k) Additional Information
For more information about this AD,
contact Barbara Caufield, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–7146;
email: barbara.caufield@faa.gov.
lotter on DSK11XQN23PROD with PROPOSALS1
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) 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) Transport Canada AD CF–2023–60,
dated August 14, 2023.
(ii) [Reserved]
(3) For Transport Canada material
identified in this AD, contact Transport
Canada, Transport Canada National Aircraft
Certification, 159 Cleopatra Drive, Nepean,
Ontario K1A 0N5, Canada; phone: (888) 663–
3639; email: TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca;
website: tc.canada.ca/en/aviation.
(4) 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.
(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 fr.inspection@nara.gov.
VerDate Sep<11>2014
17:36 Nov 25, 2024
Jkt 265001
Comments Invited
14 CFR Part 39
(j) Alternative Methods of Compliance
(AMOCs)
[Docket No. FAA–2024–2540; Project
Identifier AD–2024–00343–E]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Engines.
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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.
SUMMARY:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: (202) 493–2251.
• 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.
• 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 regulations.gov under Docket
No. FAA–2024–2540; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
ADDRESSES:
PO 00000
Frm 00006
Fmt 4702
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: sungmo.d.cho@faa.gov.
SUPPLEMENTARY INFORMATION:
Sfmt 4702
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
regulations.gov, 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.
E:\FR\FM\26NOP1.SGM
26NOP1
Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Proposed Rules
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,
93229
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.
Proposed AD Requirements in This
NPRM
FAA’s Determination
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:
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.
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
ESTIMATED COSTS
Action
Labor cost
Replace stage 1 turbine forward cooling
plate and stage 2 turbine aft cooling
plate.
8 work-hours × $85 per hour = $680 ..........
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.
lotter on DSK11XQN23PROD with PROPOSALS1
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
VerDate Sep<11>2014
17:36 Nov 25, 2024
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
Jkt 265001
§ 39.13
[Amended]
Frm 00007
Fmt 4702
$88,360
$89,040
Cost on U.S.
operators
$20,301,120
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
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
PO 00000
Cost per
product
Parts cost
Sfmt 4702
Comply with this AD within the
compliance times specified, unless already
done.
E:\FR\FM\26NOP1.SGM
26NOP1
93230
Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Proposed Rules
(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
1
1
1
2
............................
............................
............................
............................
2 ............................
2 ............................
Part name
Stage
Stage
Stage
Stage
1
2
2
1
turbine
turbine
turbine
turbine
forward cooling plate ............................................................
aft cooling plate ....................................................................
aft cooling plate ....................................................................
forward cooling plate ............................................................
6064T08P01
6064T07P05
6068T36P01
6064T08P01
Stage 2 turbine aft cooling plate ....................................................................
Stage 2 turbine aft cooling plate ....................................................................
6064T07P05
6068T36P01
(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:
AMOC@faa.gov.
(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.
lotter on DSK11XQN23PROD with PROPOSALS1
(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: sungmo.d.cho@faa.gov.
(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
VerDate Sep<11>2014
Affected P/N
17:36 Nov 25, 2024
Jkt 265001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–2538; Project
Identifier MCAI–2023–01211–E]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2022–24–06, which applies to certain
Rolls-Royce Deutschland Ltd & Co KG
(RRD) Model BR700–710A1–10, BR700–
710A2–20, and BR700–710C4–11
engines. AD 2022–24–06 requires initial
and repetitive visual inspections of
certain low-pressure compressor (LPC)
rotor (fan) disks and replacement of any
LPC rotor (fan) disk with cracks
detected. AD 2022–24–06 also allows
for modification of the engine in
accordance with RRD service
information as a terminating action to
these inspections. Since the FAA issued
AD 2022–24–06, the manufacturer
published updated service information
and revised the engine maintenance
manual (EMM) to provide instructions
for an improved ultrasonic inspection
method, which prompted this AD. This
proposed AD would require initial and
repetitive visual inspections of certain
LPC rotor (fan) disks and replacement of
any LPC rotor (fan) disk with cracks
detected and would allow modification
of the engine as a terminating action to
the inspections, as specified in a
SUMMARY:
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
Replacement P/N
6064T08P04
6064T07P07
6068T36P04
6064T08P03 or
6064T08P04
6064T07P07
6068T36P04
European Union Aviation Safety Agency
(EASA) AD, which is proposed for
incorporation by reference. The FAA is
proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments
on this NPRM 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:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: (202) 493–2251.
• 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.
• 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 regulations.gov under Docket
No. FAA–2024–2538; 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, the mandatory
continuing airworthiness information
(MCAI) any comments received, and
other information. The street address for
Docket Operations is listed above.
Material Incorporated by Reference:
• For EASA material identified in this
proposed AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; phone: +49 221 8999 000;
email: ADs@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
E:\FR\FM\26NOP1.SGM
26NOP1
]]>Agencies
[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 [www.gpo.gov]
[FR Doc No: 2024-27664]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
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.
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 regulations.gov 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: [email protected].
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
regulations.gov, 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
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
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 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.
----------------------------------------------------------------------------------------------------------------
(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: [email protected].
(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: [email protected].
(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
