This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

7636 

Vol. 89, No. 24 

Monday, February 5, 2024 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0041; Project 

Identifier AD–2024–00032–E] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines, AG 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 International Aero Engines, AG 

(IAE AG) Model V2500 engines. This 

proposed AD was prompted by an 

analysis of an event involving an 

International Aero Engines, LLC (IAE 

LLC) Model PW1127GA–JM engine, 

which experienced a high-pressure 

compressor (HPC) 7th-stage integrally 

bladed rotor (IBR–7) separation that 

resulted in an aborted takeoff. This 

proposed AD would require performing 

an angled ultrasonic inspection (AUSI) 

of certain high-pressure turbine (HPT) 

1st-stage hubs and HPT 2nd-stage hubs 

for cracks and replacing if necessary. 

This proposed AD would also require 

accelerated replacement of certain HPT 

1st-stage hubs and HPT 2nd-stage hubs. 

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 March 6, 2024. 

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–2024–0041; 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. 

Material Incorporated by Reference: 

• For Pratt & Whitney (PW) and IAE 

AG service information identified in 

this NPRM, contact International Aero 

Engines, AG, 400 Main Street, East 

Hartford, CT 06118; phone: (860) 565– 

0140; email: help24@pw.utc.com; 

website: connect.prattwhitney.com. 

• You may view this service 

information 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. 

FOR FURTHER INFORMATION CONTACT: 

Carol Nguyen, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238– 

7655; email: carol.nguyen@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 ADDRESSES. Include ‘‘Docket No. 

FAA–2024–0041; Project Identifier AD– 

2024–00032–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 amend this proposal 

because of those comments. 

The FAA has been informed that PW 

has done some outreach with affected 

operators regarding the proposed 

corrective actions for this unsafe 

condition. As a result, affected operators 

are already aware of the proposed 

corrective actions and, in some cases, 

have already begun planning for 

replacement of the affected parts. 

Therefore, the FAA has determined that 

a 30-day comment period is appropriate 

given the particular circumstances 

related to the proposed correction of 

this unsafe condition. 

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 Carol Nguyen, 

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. 

Background 

On December 24, 2022, an Airbus 

Model A320neo airplane, powered by 

IAE LLC Model PW1127GA–JM engines, 

experienced a failure of the HPC IBR– 

7 that resulted in an engine shutdown 

and aborted take-off. Following this 

event, the manufacturer conducted a 

records review of production and fieldreturned parts and re-evaluated their 

engineering analysis methodology. The 

new analysis found that the failure of 

the HPC IBR–7 was caused by a nickel 

powdered metal anomaly, similar in 

nature to an anomaly previously 

observed on March 18, 2020, when an 


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Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules 7637 

Airbus Model A321–231 airplane, 

powered by IAE AG Model V2533–A5 

engines, experienced an uncontained 

HPT 1st-stage hub failure that resulted 

in high-energy debris penetrating the 

engine cowling. The analysis also 

concluded that there is an increased risk 

of failure for a subpopulation of HPT 

1st-stage hubs and HPT 2nd-stage hubs 

that were manufactured from the same 

production campaign (a batch of nickel 

powdered metal) as the HPT 1st-stage 

hub that failed on March 18, 2020; these 

parts have a higher likelihood of 

containing the nickel powdered metal 

anomaly and are susceptible to failure 

much earlier than previously 

determined. As a result, the FAA is 

proposing an accelerated AUSI for 

certain HPT 1st-stage hubs and HPT 

2nd-stage hubs and, depending on the 

results of the inspections, replacing the 

HPT 1st-stage hubs or HPT 2nd-stage 

hubs. This proposed AD would also 

require accelerated replacement of 

certain HPT 1st-stage hubs and HPT 

2nd-stage hubs. Certain IAE AG Model 

V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, V2531–E5, and 

V2533–A5 engines are among the 

products affected by this condition, 

which, if not addressed, could result in 

hub failure, release of high-energy 

debris, damage to the engine, damage to 

the airplane, and possible loss of 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. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed IAE AG NonModification Service Bulletin (NMSB) 

V2500–ENG–72–0720, dated November 

20, 2023; and PW Special Instruction 

NO. 189F–23, dated November 20, 2023 

which only applies to the IAE AG 

V2531–E5 Model engine. This service 

information specifies procedures for 

performing an AUSI for cracks on 

affected HPT 1st-stage hubs and HPT 

2nd-stage hubs. This service 

information also specifies the list of 

affected HPT 1st-stage hubs and HPT 

2nd-stage hubs, identified by part 

number and serial number, installed on 

certain IAE AG engines. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in ADDRESSES. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

performing an AUSI of certain HPT 1ststage hubs and HPT 2nd-stage hubs and, 

depending on the results of the 

inspections, replacing the HPT 1st-stage 

hubs or HPT 2nd-stage hubs. This 

proposed AD would also require 

accelerated replacement of certain HPT 

1st-stage hubs and HPT 2nd-stage hubs. 

Interim Action 

The FAA considers this proposed AD 

to be an interim action. The unsafe 

condition is still under investigation by 

the manufacturer and, depending on the 

results of that investigation, the FAA 

may consider further rulemaking action. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 116 

engines installed on airplanes of U.S. 

registry. The FAA estimates that 40 

engines would need an AUSI of the HPT 

1st-stage hub; 40 engines would need an 

AUSI of the HPT 2nd-stage hub; 67 

engines would need replacement of the 

HPT 1st-stage hub; and 49 engines 

would need replacement of the HPT 

2nd-stage hub. 

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 

AUSI of HPT 1st-stage hub ............................ 5 work-hours × $85 per hour = $425 ............. $0 $425 $17,000 

AUSI of HPT 2nd-stage hub ........................... 5 work-hours × $85 per hour = $425 ............. 0 425 17,000 

Replace HPT 1st-stage hub ........................... 100 work-hours × $85 per hour = $8,500 ...... 460,000 468,500 31,389,500 

Replace HPT 2nd-stage hub .......................... 100 work-hours × $85 per hour = $8,500 ...... 360,000 368,500 18,056,500 

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. 

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: 


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7638 Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules 

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: 

International Aero Engines, AG: Docket No. 

FAA–2024–0041; Project Identifier AD– 

2024–00032–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 6, 

2024. 

(b) Affected ADs 

This AD is related to AD 2022–02–09, 

Amendment 39–21906 (87 FR 7029, February 

8, 2022) (AD 2022–02–09). 

(c) Applicability 

This AD applies to International Aero 

Engines, AG (IAE AG) Model V2522–A5, 

V2524–A5, V2525–D5, V2527–A5, V2527E– 

A5, V2527M–A5, V2528–D5, V2530–A5, 

V2531–E5, and V2533–A5 engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

an event involving an International Aero 

Engines, LLC Model PW1127GA–JM engine, 

which experienced failure of a high-pressure 

compressor 7th-stage integrally bladed rotor 

that resulted in an engine shutdown and 

aborted takeoff. The FAA is issuing this AD 

to prevent failure of the high-pressure turbine 

(HPT) 1st-stage hub and HPT 2nd-stage hub. 

The unsafe condition, if not addressed, could 

result in uncontained hub failure, release of 

high-energy debris, damage to the engine, 

damage to the airplane, and loss of the 

airplane 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For engines with an installed part, part 

number (P/N), and serial number (S/N) listed 

in Table 1 to paragraph (g)(1) of this AD, with 

no angled ultrasonic inspection (AUSI) 

performed or the AUSI inspected part was 

installed on or after November 1, 2023, at the 

next engine shop visit after the effective date 

of this AD before exceeding the applicable 

cycle limit specified in Table 1 to paragraph 

(g)(1) of this AD, perform an AUSI of the 

affected parts for cracks in accordance with 

the applicable service information listed in 

Table 1 to paragraph (g)(1) of this AD. 

TABLE 1 TO PARAGRAPH (g)(1)—AUSI COMPLIANCE TIMES

Part Table S/N is listed in 

Previously 

operated in 

high-thrust 

model engine 

Cycle limit from the 

effective date 

of this AD 

Applicable service information 

HPT 1st-stage hub P/N 

2A5001.

Table 1 of IAE AG Non-Modification 

Service Bulletin V2500–ENG–72– 

0720, dated November 20, 2023 

(IAE AG NMSB V2500–ENG–72– 

0720).

Yes ................. 100 flight cycles (FCs) Accomplishment Instructions, paragraph 5., of IAE AG NMSB 

V2500–ENG–72–0720. 

Table 1 of Pratt & Whitney (PW) 

Special Instruction NO. 189F–23, 

dated November 20, 2023 (PW 

SI 189F–23).

Accomplishment Instructions, paragraph 5., of PW SI 189F–23. 

Table 1 of IAE AG NMSB V2500– 

ENG–72–0720.

No .................. 700 FCs ....................... Accomplishment Instructions, paragraph 5., of IAE AG NMSB 

V2500–ENG–72–0720. 

HPT 2nd-stage hub P/N 

2A4802.

Table 2 of IAE AG NMSB V2500– 

ENG–72–0720.

Yes ................. 800 FCs ....................... Accomplishment Instructions, paragraph 6., of IAE AG NMSB 

V2500–ENG–72–0720. 

Table 2 PW SI 189F–23 ................. Accomplishment Instructions, paragraph 6., of PW SI 189F–23. 

Table 2 of IAE AG NMSB V2500– 

ENG–72–0720.

No .................. 1100 FCs ..................... Accomplishment Instructions, paragraph 6., of IAE AG NMSB 

V2500–ENG–72–0720. 

(2) For parts inspected in accordance with 

paragraph (g)(1) of this AD, within 4,000 FCs 

from accomplishment of the AUSI required 

by paragraph (g)(1) of this AD or at the next 

HPT module removal after the AUSI required 

by paragraph (g)(1) of this AD, whichever 

occurs first, remove the part from service and 

replace with a part eligible for installation. 

(3) If any crack is found during the 

inspections required by paragraphs (g)(1) of 

this AD, before further flight, remove the 

affected part from service and replace with a 

part eligible for installation. 

(4) For engines with an AUSI inspected 

part installed prior to November 1, 2023, 

having a P/N and S/N listed in Table 2 to 

paragraph (g)(4) of this AD, at the next HPT 

module removal after the effective date of 

this AD, but before exceeding the applicable 

cycle limit specified in Table 2 to paragraph 

(g)(4) of this AD, remove the affected part 

from service and replace with a part eligible 

for installation. 

TABLE 2 TO PARAGRAPH (g)(4)—PART REPLACEMENT COMPLIANCE TIMES

Part Table S/N is listed in Previously operated in highthrust model engine 

Cycle limit from 

the effective 

date of this AD 

HPT 1st-stage hub P/N 

2A5001.

Table 1 of IAE AG NMSB V2500–ENG–72–0720 .................

Table 1 of PW SI 189F–23. 

Yes ......................................... 1,800 FCs. 

Table 1 of IAE AG NMSB V2500–ENG–72–0720 ................. No .......................................... 2,800 FCs. 

HPT 2nd-stage hub P/N 

2A4802.

Table 2 of IAE AG NMSB V2500–ENG–72–0720 .................

Table 2 of PW SI 189F–23. 

Yes ......................................... 3,400 FCs. 


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Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules 7639 

TABLE 2 TO PARAGRAPH (g)(4)—PART REPLACEMENT COMPLIANCE TIMES—Continued 

Part Table S/N is listed in Previously operated in highthrust model engine 

Cycle limit from 

the effective 

date of this AD 

Table 2 of IAE AG NMSB V2500–ENG–72–0720 ................. No .......................................... 3,800 FCs. 

(5) For engines with an installed part that 

has a P/N and S/N listed in Table 3 to 

paragraph (g)(5) of this AD, at the next HPT 

module removal after the effective date of 

this AD, but before exceeding the applicable 

cycle limit specified in Table 3 to paragraph 

(g)(5) of this AD, remove the affected part 

from service and replace with a part eligible 

for installation. 

TABLE 3 TO PARAGRAPH (g)(5)—PART REPLACEMENT COMPLIANCE TIMES

Part Table S/N is listed in Previously operated in highthrust model engine 

Cycle limit from 

the effective 

date of this AD 

HPT 1st-stage hub P/N 

2A5001.

Table 3 of IAE AG NMSB V2500–ENG–72–0720 .................

Table 3 of IAE AG NMSB V2500–ENG–72–0720 .................

Yes .........................................

No ..........................................

1,800 FCs. 

2,800 FCs. 

HPT 2nd-stage hub P/N 

2A4802.

Table 4 of IAE AG NMSB V2500–ENG–72–0720 .................

Table 4 of IAE AG NMSB V2500–ENG–72–0720 .................

Yes .........................................

No ..........................................

3,400 FCs. 

3,800 FCs. 

(h) Definitions 

(1) For the purposes of this AD, a ‘‘part 

eligible for installation’’ is an HPT 1st-stage 

disk or HPT 2nd-stage disk having an S/N 

that is not listed in IAE AG NMSB V2500– 

ENG–72–0720 or PW SI 189F–23. 

(2) For the purposes of this AD, an ‘‘HPT 

module removal’’ is when the HPT rotor and 

stator assembly are removed from the engine. 

(3) For the purposes of this AD, 

‘‘Previously operated in high-thrust model 

engine’’ refers to HPT 1st-stage hubs or HPT 

2nd-stage hubs that have previously operated 

in an IAE AG Model V2527E–A5, V2527M– 

A5, V2528–D5, V2530–A5, V2531–E5, or 

V2533–A5 engine for any duration. 

(4) For the purposes of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, H–P, except for the following 

situations, which do not constitute an engine 

shop visit: 

(i) Separation of engine flanges solely for 

the purposes of transportation without 

subsequent engine maintenance. 

(ii) Engine removal for the purpose of 

performing field maintenance activities at a 

maintenance facility in lieu of performing 

them on-wing. 

(5) For the purposes of this AD, the date 

that an AUSI inspected part was installed is 

the date of the authorized release 

certification for the shop visit at which the 

part was first installed after the AUSI was 

performed. 

(i) Terminating Action to AD 2022–02–09 

Compliance with paragraph (g)(1) of this 

AD satisfies the requirements of AD 2022– 

02–09. 

(j) 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 (k) of this AD. 

(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 Carol Nguyen, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238–7655; 

email: carol.nguyen@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) International Aero Engines AG (IAE AG) 

Non-Modification Service Bulletin V2500– 

ENG–72–0720, dated November 20, 2023. 

(ii) Pratt & Whitney (PW) Special 

Instruction NO. 189F–23, dated November 

20, 2023. 

(3) For PW and IAE AG service information 

identified in this AD, contact International 

Aero Engines, AG, 400 Main Street, East 

Hartford, CT 06118; phone: (860) 565–0140; 

email: help24@pw.utc.com; website: 

connect.prattwhitney.com. 

(4) You may view this service information 

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 January 24, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–02205 Filed 1–31–24; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Office of Justice Programs 

28 CFR Part 94 

[Docket No.: OJP (OVC) 1808] 

RIN 1121–AA89 

Subject: Victims of Crime Act (VOCA) 

Victim Compensation Grant Program 

AGENCY: Office for Victims of Crime, 

Office of Justice Programs, Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Office of Justice Programs 

(‘‘OJP’’), a bureau of the Department of 

Justice, Office for Victims of Crime 

(‘‘OVC’’) proposes adding a subpart to 

its regulations to replace the existing 

Victims of Crime Act (‘‘VOCA’’) Victim 

Compensation Program Guidelines 

(‘‘Guidelines’’), and update and codify 

program requirements for the VOCA 

Victim Compensation Formula Grant 

Program (‘‘Victim Compensation 

Program’’). 

DATES: Comments must be received by 

no later than 11:59 p.m., E.T., on April 

5, 2024. 

ADDRESSES: 

Electronic comments: OVC 

encourages commenters to submit all 

comments electronically through the 


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