6008 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations 

NRC licensing approval or the 

acceptability of licensee commitments 

to these RGs. Although these RGs are 

withdrawn, current licensees may 

continue to use them, and withdrawal 

does not affect any existing licenses or 

agreements. However, these RGs should 

not be used in future requests or 

applications for NRC licensing actions. 

II. Additional Information 

As noted in the Federal Register on 

December 9, 2022 (87 FR 75671), this 

document is being published in the 

‘‘Rules’’ section of the Federal Register 

to comply with publication 

requirements under 1 CFR chapter I. 

III. Submitting Suggestions for 

Improvement of Regulatory Guides 

A member of the public may, at any 

time, submit suggestions to the NRC for 

improvement of existing RGs or for the 

development of new RGs. Suggestions 

can be submitted on the NRC’s public 

website at https://www.nrc.gov/readingrm/doc-collections/reg-guides/ 

contactus.html. Suggestions will be 

considered in future updates and 

enhancements to the ‘‘Regulatory 

Guide’’ series. 

Dated: January 25, 2024. 

For the Nuclear Regulatory Commission. 

Meraj Rahimi, 

Chief, Regulatory Guide and Programs 

Management Branch, Division of Engineering, 

Office of Nuclear Regulatory Research. 

[FR Doc. 2024–01872 Filed 1–30–24; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0034; Project 

Identifier AD–2023–01154–Q; Amendment 

39–22662; AD 2024–01–11] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

helicopters with certain Pacific 

Scientific Company rotary buckle 

assemblies (buckles) installed. This AD 

was prompted by a report of a 

manufacturing defect in the screws used 

inside the buckle. This AD requires 

inspecting the buckle screws and, 

depending on the results, reidentifying 

the buckle, replacing the screws and 

reidentifying the buckle, or replacing 

the buckle. This AD also prohibits 

installing certain buckles. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 15, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 15, 2024. 

The FAA must receive comments on 

this AD by March 18, 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–2024–0034; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

Material Incorporated by Reference: 

• For service information identified 

in this final rule, contact Parker Meggitt 

Services, 1785 Voyager Avenue, Simi 

Valley, CA 93063; phone: 877–666– 

0712; email: TechnicalSupport@

meggitt.com; website: meggitt.com/ 

services_and_support/customer_

experience/update-on-buckle-assemblyservice-bulletins. 

• You may view this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Parkway, Room 6N– 

321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. It is also available at 

regulations.gov under Docket No. FAA– 

2024–0034. 

FOR FURTHER INFORMATION CONTACT: 

David Kim, Aviation Safety Engineer, 

FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712; phone: (562) 627– 

5274; email: david.kim@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2024–0034; 

Project Identifier AD–2023–01154–Q’’ at 

the beginning of your comments. The 

most helpful comments reference a 

specific portion of the final rule, 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 final rule 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 final rule. 

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 AD 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 AD, 

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 AD. Submissions containing CBI 

should be sent to David Kim, Aviation 

Safety Engineer, FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712; 

phone: (562) 627–5274; email: 

david.kim@faa.gov. Any commentary 

that the FAA receives which is not 

specifically designated as CBI will be 

placed in the public docket for this 

rulemaking. 

Background 

The FAA has received a report of a 

manufacturing defect in the screws used 

inside Pacific Scientific Company 

buckle part number (P/N) 1111475 (all 

dash numbers) and P/N 1111548–01. 

The screws used to fasten the load plate 

to the body of the buckle were found to 

be susceptible to hydrogen 

embrittlement due to improper baking 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations 6009 

during the electroplating process. This 

condition leads the screwhead to 

separate from the body of the screw 

when under load, which could result in 

the buckle failing to restrain the 

occupant to the seat. This issue was 

originally identified from a suspected 

lot of screws, Lot 348994–A. Since then, 

a buckle failed in an accident, calling 

into question Lot 348601–A. Lots 

348601–A and 348994–A were the first 

two lots of screws received by Pacific 

Scientific Company from a new supplier 

and are the only suspected lots. The 

suspected buckles were manufactured 

between January 2012 and September 

2012. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

The rotary buckle may be included as 

a component of a different partnumbered restraint system assembly. 

Table 1 of Parker Meggitt Service 

Bulletin (SB) 1111475–25–001–2023, 

Revision 001, dated December 1, 2023, 

and Parker Meggitt SB 1111548–25– 

001–2023, Revision 001, dated 

December 1, 2023 (SB 1111475–25–001– 

2023 Rev 001 and SB 1111548–25–001– 

2023 Rev 001), includes a list of these 

restraint system assembly P/Ns. 

This AD applies to all helicopters 

with a Pacific Scientific Company 

buckle P/N 1111475 (all dash numbers) 

or P/N 1111548–01 installed, if the 

buckle was manufactured between 

January 2012 and September 2012, or if 

the date of manufacture of the buckle is 

unknown. These same part-numbered 

buckles may also be installed in 

airplanes; however, the FAA 

determined that a longer compliance 

time to accomplish the required actions 

is allowable for buckles installed in 

airplanes. Accordingly, the FAA plans 

to publish a separate notice of proposed 

rulemaking to address all airplanes with 

a Pacific Scientific Company buckle P/ 

N 1111475 (all dash numbers) or P/N 

1111548–01 installed. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency has determined the unsafe 

condition described previously is likely 

to exist or develop on other helicopters 

with a restraint system with a buckle as 

part of their type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed SB 1111475–25– 

001–2023 Rev 001 for buckle P/N 

1111475 and SB 1111548–25–001–2023 

Rev 001 for buckle P/N 1111548–01. 

This service information specifies 

procedures for inspecting the buckle for 

any missing or loose screw heads and, 

depending on the results, replacing the 

buckle and sending the removed buckle 

to Parker Meggitt for repair or 

replacement. If after that first 

inspection, all of the screw heads are 

intact, this service information specifies 

procedures for inspecting the buckle for 

any Torx head screws (alloy steel) and, 

depending on the results, allowing the 

buckle assembly to remain in-service 

temporarily, replacing any Torx head 

screws (alloy steel) with new hex head 

screws (stainless steel), and checking 

the functionality of the buckle. This 

service information also specifies 

procedures for removing a buckle from 

a restraint system, installing a buckle on 

a restraint system, and returning buckles 

to Parker Meggitt. If the buckle passes 

the specified inspections or is modified 

by replacing Torx head screws (alloy 

steel) with new hex head screws 

(stainless steel) screws, this service 

information specifies procedures for 

reidentifying the back of the buckle. 

This service information also identifies 

known affected restraint systems. 

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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information already described, except as 

discussed under ‘‘Differences Between 

this AD and the Service Information.’’ 

Differences Between This AD and the 

Service Information 

The service information does not 

specify any compliance times, whereas 

this AD requires accomplishing the 

required actions within three months. 

This AD also prohibits installing an 

affected buckle on any helicopter as of 

the effective date of this AD. 

The service information specifies 

sending any damaged buckles to Parker 

Meggitt for repair or replacement, and 

this AD does not. Instead, this AD 

requires replacing the buckle with an 

airworthy buckle. 

The service information allows 

buckles with a Torx head (alloy steel) 

screw to remain in service temporarily 

and be replaced at a time convenient to 

the operator, and this AD does not. If a 

buckle has any number of Torx head 

(alloy steel) screws installed, this AD 

requires replacing all four screws with 

hex head screws before further flight. 

If a screw head breaks off during 

disassembly of a buckle or if reassembly 

of a buckle is not possible, the service 

information specifies returning the 

buckle to Parker Meggitt, whereas this 

AD does not. If a screw head breaks off 

during disassembly, this AD requires 

replacing the buckle with an airworthy 

buckle. If reassembly of a buckle is not 

possible, then the buckle is not 

airworthy. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies forgoing notice 

and comment prior to adoption of this 

rule because in an otherwise survivable 

accident, hard landing, or severe 

turbulence, the buckle may fail to 

restrain the occupant. Based on the 

rotorcraft accident rate, coupled with 

not knowing the propagation rate of this 

unsafe condition into failure, the FAA 

determined that the compliance time to 

inspect affected buckles installed in 

helicopters must be within three 

months. Accordingly, notice and 

opportunity for prior public comment 

are impracticable and contrary to the 

public interest pursuant to 5 U.S.C. 

553(b)(3)(B). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forgo 

notice and comment. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because FAA 

has determined that it has good cause to 

adopt this rule without prior notice and 

comment, RFA analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects approximately 11,714 buckles 

installed on restraint systems in aircraft 

worldwide. The FAA has no way of 

knowing the number of helicopters of 


lotter on DSK11XQN23PROD with RULES1
6010 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations 

U.S. Registry that may have a restraint 

system with an affected buckle 

installed. The estimated costs on U.S. 

operators reflects the maximum possible 

costs based on affected buckles installed 

on restraint systems in aircraft 

worldwide. Labor rates are estimated at 

$85 per work-hour. Based on these 

numbers, the FAA estimates that 

operators may incur the following costs 

in order to comply with this AD. 

Inspecting a buckle will take 

approximately 0.1 work-hour for an 

estimated cost of $9 per buckle and up 

to $105,426 for the U.S. fleet. If 

required, replacing a set of screws (four) 

will take approximately 0.5 work-hour 

and parts will cost a nominal amount 

for an estimated cost of $43 per buckle. 

Replacing a buckle will take 

approximately 0.5 work-hour and parts 

will cost approximately $740 for an 

estimated cost of $783 per buckle. The 

FAA estimates a nominal cost for 

reidentifying a buckle. 

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, 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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: 

2024–01–11 Various Helicopters: 

Amendment 39–22662; Docket No. 

FAA–2024–0034; Project Identifier AD– 

2023–01154–Q. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 15, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all helicopters, certified 

in any category, with a restraint system with 

a Pacific Scientific Company rotary buckle 

assembly (buckle) part number (P/N) 

1111475 (all dash numbers) or P/N 1111548– 

01 installed having a date of manufacture 

between January 2012 and September 2012 

inclusive or an unknown date of 

manufacture. These buckles may be installed 

on, but not limited to, Airbus Helicopters 

model helicopters, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 2500, Cabin Equipment/Furnishings. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

manufacturing defect in the screws used 

inside the buckle. The FAA is issuing this 

AD to prevent cracking and missing screw 

heads when under load. The unsafe 

condition, if not addressed, could result in a 

failure of the buckle to restrain the occupant. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For helicopters with buckle P/N 

1111475 (all dash numbers), within 3 months 

after the effective date of this AD, inspect 

each buckle screw for cracked, loose, and 

missing screw heads by following the 

Accomplishment Instructions, paragraphs 

B.(1) and (2), of Parker Meggitt Service 

Bulletin (SB) 1111475–25–001–2023, 

Revision 001, dated December 1, 2023 (SB 

1111475–25–001–2023 Rev 001). 

(i) If any screw has a cracked, loose, or 

missing screw head, before further flight, 

replace the buckle with an airworthy buckle. 

(ii) If none of the four screw heads are 

cracked, loose, or missing, before further 

flight, inspect each screw to determine if any 

screw has a Torx head by using one of the 

following methods in the Accomplishment 

Instructions of SB 1111475–25–001–2023 

Rev 001: paragraph B.(4)(a) (Magnet Test); 

paragraph B.(4)(b) (Inspection); or paragraphs 

C.(2) through (4) (removing the buckle from 

the restraint system) and paragraphs D.(1)(a) 

through (d) (disassembling the buckle). 

Note 1 to paragraph (g)(1): SB 1111475– 

25–001–2023 Rev 001 refers to a magnifying 

glass as an ‘‘eye loupe.’’ 

(A) If none of the four screws have a Torx 

head, before further flight, reassemble the 

buckle (if necessary) by following the 

Accomplishment Instructions, paragraphs 

D.(1)(f) through (l), of SB 1111475–25–001– 

2023 Rev 001, and reidentify the buckle with 

‘‘INS. A’’ by following the Accomplishment 

Instructions, paragraph B.(6), of SB 1111475– 

25–001–2023 Rev 001. 

(B) If at least one of the four screws has a 

Torx head, before further flight, with the 

buckle removed, replace each Torx head 

screw with a hex head screw, reassemble the 

buckle, and reidentify the buckle with 

‘‘MOD. A’’ by following the Accomplishment 

Instructions, paragraphs D.(1)(e) through (m), 

of SB 1111475–25–001–2023 Rev 001, except 

you are not required to return any parts to 

Parker Meggitt. If a screw head breaks off 

during disassembly, before further flight, 

replace the buckle with an airworthy buckle. 

(2) For helicopters with buckle P/N 

1111548–01, within 3 months after the 

effective date of this AD, inspect each buckle 

screw for cracked, loose, and missing screw 

heads by following the Accomplishment 

Instructions, paragraph B.(1), of Parker 

Meggitt SB 1111548–25–001–2023, Revision 

001, dated December 1, 2023 (SB 1111548– 

25–001–2023 Rev 001). 

(i) If any screw has a cracked, loose, or 

missing screw head, before further flight, 

replace the buckle with an airworthy buckle. 

(ii) If none of the four screw heads are 

cracked, loose, or missing, before further 

flight, inspect each screw to determine which 

screws have a Torx head by using one of the 

following methods in the Accomplishment 

Instructions of SB 1111548–25–001–2023 

Rev 001: paragraph B.(3)(a) (except use 

Figure 6 for placement of the shim tool and 

use Figure 5 to distinguish the screw head 

types) (Inspection); or paragraph C. 

(removing the buckle from the restraint 

system) and paragraphs D.(1)(a) through (c) 

(disassembling the buckle). Before further 

flight, with the buckle removed, replace each 

Torx head screw with a hex head screw, 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations 6011 

1The Agreement Between the United States of 

America, the United Mexican States, and Canada is 

the official name of the USMCA treaty. Please be 

aware that, in other contexts, the same document 

is also referred to as the United States-MexicoCanada Agreement. 2Mexico, Canada, and the United States certified 

their preparedness to implement the USMCA on 

December 12, 2019, March 13, 2020, and April 24, 

2020, respectively. Pursuant to section 106 of the 

Bipartisan Congressional Trade Priorities and 

Accountability Act of 2015 (19 U.S.C. 4205) and 

section 151 of the Trade Act of 1974 (19 U.S.C. 

2191), the United States adopted the USMCA 

through the enactment of the United States— 

Mexico—Canada Agreement Implementation Act 

(USMCA Implementation Act), Public Law 116– 

113, 134 Stat. 11 (19 U.S.C. Chapter 29), on January 

29, 2020. Pursuant to paragraph 2 of the Protocol, 

which provides that the USMCA will take effect on 

the first day of the third month after the last 

signatory party provides written notification of the 

completion of the domestic implementation of the 

USMCA through the enactment of implementing 

legislation, the USMCA entered into force on July 

1, 2020. On December 27, 2020, subsequent to the 

USMCA’s entry into force date of July 1, 2020, the 

Consolidated Appropriations Act, 2021 

(Appropriations Act), Public Law 116–260, was 

enacted with Title VI of the Act containing 

technical corrections to the USMCA Act. All of the 

changes contained within Title VI of the 

Appropriations Act are retroactively effective on 

July 1, 2020. 

reassemble the buckle, and reidentify the 

buckle with ‘‘MOD. A’’ by following the 

Accomplishment Instructions, paragraphs 

D.(1)(d) through (m), of SB 1111548–25–001– 

2023 Rev 001, except you are not required to 

return any parts to Parker Meggitt. If a screw 

head breaks off during disassembly, before 

further flight, replace the buckle with an 

airworthy buckle. 

Note 2 to paragraph (g)(2): SB 1111548– 

25–001–2023 Rev 001 refers to a magnifying 

glass as an ‘‘eye loupe.’’ 

(3) As of the effective date of this AD, do 

not install a buckle identified in paragraph 

(c) of this AD on any helicopter unless the 

buckle is marked with ‘‘MOD. A’’ or ‘‘INS. 

A’’. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, West Certification 

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 West Certification 

Branch, send it to the attention of the person 

identified in paragraph (i) 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. 

(i) Additional Information 

For more information about this AD, 

contact David Kim, Aviation Safety Engineer, 

FAA, 3960 Paramount Boulevard, Lakewood, 

CA 90712; phone: (562) 627–5274; email: 

david.kim@faa.gov. 

(j) 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) Parker Meggitt Service Bulletin 

1111475–25–001–2023, Revision 001, dated 

December 1, 2023. 

(ii) Parker Meggitt Service Bulletin 

1111548–25–001–2023, Revision 001, dated 

December 1, 2023. 

(3) For service information identified in 

this AD, contact Parker Meggitt Services, 

1785 Voyager Avenue, Simi Valley, CA 

93063; phone: 877–666–0712; email: 

TechnicalSupport@meggitt.com; website: 

meggitt.com/services_and_support/ 

customer_experience/update-on-buckleassembly-service-bulletins. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Parkway, 

Room 6N–321, Fort Worth, TX 76177. 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 18, 2024. 

Victor Wicklund, 

Deputy Director, Deputy Director, Compliance 

& Airworthiness Division, Aircraft 

Certification Service. 

[FR Doc. 2024–01932 Filed 1–26–24; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

International Trade Administration 

19 CFR Part 356 

[Docket No. 231127–0278] 

RIN 0625–AB20 

Procedures and Rules for Article 10.12 

of the United States-Mexico-Canada 

Agreement 

AGENCY: Enforcement and Compliance, 

International Trade Administration, 

Department of Commerce. 

ACTION: Final rule. 

SUMMARY: The Department of Commerce 

(Commerce) publishes this action to 

update and make final an interim final 

rule that amended its regulations 

pertaining to the procedures and rules 

related to Article 1904 of the North 

American Free Trade Agreement 

(NAFTA) with appropriate references to 

the United States-Mexico-Canada 

Agreement (USMCA), which went into 

effect on July 1, 2020. Article 10.12 of 

the USMCA, like NAFTA Article 1904, 

provides a dispute settlement 

mechanism for purposes of reviewing 

antidumping and countervailing duty 

determinations issued by the United 

States, Canada, and Mexico. Commerce 

is amending its regulations to replace 

references to Article 1904 of NAFTA 

with references to Article 10.12 of the 

USMCA; to update outdated crossreferences to Commerce’s antidumping 

and countervailing duty regulations; 

update outdated notice, filing, service, 

and protective order procedures; and 

adopt other minor corrections and 

updates. 

DATES: This final rule is effective 30 

days after January 31, 2024. This final 

rule does not apply to any binational 

panel review under NAFTA, or any 

extraordinary challenge arising out of 

any such review, that was commenced 

before July 1, 2020. 

FOR FURTHER INFORMATION CONTACT: 

Nikki Kalbing, Assistant Chief Counsel, 

at (202) 482–4343, Spencer Neff, 

Attorney, at (202) 482–8184, or Scott 

McBride, Associate Deputy Chief 

Counsel, at (202) 482–6292. 

SUPPLEMENTARY INFORMATION: 

USCMA Background 

As background, on November 30, 

2018, the ‘‘Protocol Replacing the North 

American Free Trade Agreement with 

the Agreement Between the United 

States of America, the United Mexican 

States, and Canada’’ (the Protocol) was 

signed to replace the North American 

Free Trade Agreement (NAFTA). The 

Agreement Between the United States of 

America, the United Mexican States 

(Mexico), and Canada (the USMCA) 1 is 

attached as an annex to the Protocol and 

was subsequently amended to reflect 

certain modifications and technical 

corrections in the ‘‘Protocol of 

Amendment to the Agreement Between 

the United States of America, the United 

Mexican States, and Canada’’ (the 

Amended Protocol), which the Office of 

the United States Trade Representative 

(USTR) signed on December 10, 2019. 

The USMCA entered into force on July 

1, 2020.2

Article 10.12 of the USMCA, like 

NAFTA Article 1904, provides a dispute 

settlement mechanism for purposes of 

reviewing antidumping and 

countervailing duty determinations 

issued by the United States, Canada, 

and Mexico. The procedures and rules 

for binational panel review of 

antidumping and countervailing duty 

administrative determinations under 

Article 10.12 of the USMCA are 

virtually unchanged from Article 1904 

of NAFTA. 

Sections 421–433 and 504 of the 

USMCA Implementation Act provide 


lotter on DSK11XQN23PROD with RULES1