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.’’ 

(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. 

(j) Alternative Methods of Compliance 

(AMOCs) 

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. 

(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. 

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 

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: sungmo.d.cho@faa.gov. 

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. 


lotter on DSK11XQN23PROD with PROPOSALS1
Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Proposed Rules 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

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace stage 1 turbine forward cooling 

plate and stage 2 turbine aft cooling 

plate.

8 work-hours × $85 per hour = $680 .......... $88,360 $89,040 $20,301,120 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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. 


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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 Part name Affected P/N Replacement P/N 

1 ............................ Stage 1 turbine forward cooling plate ............................................................ 6064T08P01 6064T08P04 

1 ............................ Stage 2 turbine aft cooling plate .................................................................... 6064T07P05 6064T07P07 

1 ............................ Stage 2 turbine aft cooling plate .................................................................... 6068T36P01 6068T36P04 

2 ............................ Stage 1 turbine forward cooling plate ............................................................ 6064T08P01 6064T08P03 or 

6064T08P04 

2 ............................ Stage 2 turbine aft cooling plate .................................................................... 6064T07P05 6064T07P07 

2 ............................ Stage 2 turbine aft cooling plate .................................................................... 6068T36P01 6068T36P04 

(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. 

(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 

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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: 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 

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 


lotter on DSK11XQN23PROD with PROPOSALS1