Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations 90091 

with a method approved by the Manager, 

International Validation Branch, FAA; or 

EASA; or Leonardo S.p.a. Helicopters’ EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(8) Where paragraph (1) of EASA AD 2022– 

0037 specifies to ‘‘interpret the results 

(PASSED or FAILED) in accordance with the 

instructions of PART I of the ASB;’’ for this 

AD, replace that text with, ‘‘interpret the 

results by using Tables 1 and 2 to paragraph 

(h)(8) of this AD and the inspection results 

recorded in Annex E of the service 

information referenced in EASA AD 2022– 

0037.’’ 

TABLE 1 TO PARAGRAPH (h)(8)—SCISSOR COUPLING INSPECTION INTERPRETATION

Maximum 

torque force 

check 

Dimensional check 2nd maximum torque 

force check 

Scissor coupling check 

outcome 

Passed ........................................... N/A ................................................ N/A ................................................ Passed. 

Failed ............................................. Passed .......................................... Passed .......................................... Passed. 

Failed ............................................. Failed ............................................ N/A ................................................ Failed. 

Failed ............................................. Passed .......................................... Failed ............................................ Failed. 

TABLE 2 TO PARAGRAPH (h)(8)—AXIAL

PLAY INSPECTION INTERPRETATION

Axial play value is 0.25 mm or less Passed. 

Axial play value is more than 0.25 

mm or the ball bearing is dislodged.

Failed. 

(9) This AD does not require compliance 

with paragraph (2) of EASA AD 2022–0037. 

This AD also does not include Note 1 of 

EASA AD 2022–0037. 

(10) Where paragraph (3) of EASA AD 

2022–0037 specifies compliance times of 

‘‘200 FH;’’ for this AD, replace each instance 

of that text with, ‘‘55 hours time-in-service.’’ 

This AD does not include Note 3 of EASA 

AD 2022–0037. 

(11) Where the service information 

referenced in EASA AD 2022–0037 cautions 

that only approved personnel (Leonardo 

Helicopters facilities, Leonardo authorized 

component repair centers within the 

approved capabilities or customers trained by 

Leonardo Helicopters for specific activities) 

are permitted to perform the bushing 

replacement; this AD does not include those 

cautions. 

(12) Where paragraph (10) of EASA AD 

2022–0037 specifies reporting inspection 

results (including the inspection results of no 

findings) to Leonardo within 30 days, this 

AD requires reporting inspection results at 

the applicable time in paragraph (h)(12)(i) or 

(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(13) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2022–0037. 

(i) Special Flight Permits 

Special flight permits are prohibited. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (k) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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 Jared Hyman, Aviation Safety 

Engineer, FAA, 1600 Stewart Ave., Suite 410, 

Westbury, NY 11590; telephone (781) 238– 

7799; email 9-AVS-AIR-BACO-COS@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2022–0037, dated March 7, 2022; 

corrected March 15, 2022. 

(ii) [Reserved] 

(3) For EASA AD 2022–0037, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

easa.europa.eu. You may find the EASA 

material on the EASA website at 

ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

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 December 14, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–28773 Filed 12–28–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2404; Project 

Identifier MCAI–2023–01268–A; Amendment 

39–22648; AD 2023–26–05] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Model PC– 

24 airplanes. This AD was prompted by 

a determination that the titanium 

threaded bolts at the forward end of the 

short rudder trim tab actuating rods 

could be subject to unexpectedly high 

oscillating loads due to aerodynamic 

forces acting on the rudder trim tab. 

This AD requires periodic replacement 

of affected titanium threaded bolts, a 

one-time inspection of the rudder mass 

balance arm and other elements of the 

rudder trim tab installation for correct 

attachment, damage (gouges), cracks, 

deformation, surface finish, and 

corrosion on any surrounding parts and, 

depending on findings, accomplishment 

of applicable corrective actions, as 

specified in a European Union Aviation 

Safety Agency (EASA) emergency AD, 

which is incorporated by reference. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective January 3, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 3, 2024. 

The FAA must receive comments on 

this AD by February 12, 2024. 


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90092 Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations 

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–2023–2404; 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, 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 material identified in this final 

rule, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; phone: 

+49 221 8999 000; email: ADs@

easa.europa.eu; website: 

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, 901 Locust, 

Kansas City, MO 64106. 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–2023–2404. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

(816) 329–4059; email: doug.rudolph@

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–2023–2404; 

Project Identifier MCAI–2023–01268– 

A’’ 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 Doug Rudolph, 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590. Any commentary that the 

FAA receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

2023–0219–E, dated December 19, 2023 

(EASA Emergency AD 2023–0219–E) 

(also referred to as the MCAI), to correct 

an unsafe condition on certain Pilatus 

Model PC–24 airplanes. The MCAI 

states it was determined that the 

titanium threaded bolts at the forward 

end of the short rudder trim tab 

actuating rods could be subject to 

unexpectedly high oscillating loads due 

to aerodynamic forces acting on the 

rudder trim tab. If not corrected, this 

condition could lead to failure of the 

bolt with consequent damage to the 

rudder and rudder trim tab, which 

could result in loss of rudder control 

and reduced or loss of control of the 

airplane. The MCAI identifies the 

affected parts as titanium threaded 

bolts, part number (P/N) 527.20.24.489, 

installed on the rudder trim tab short 

control rods. The MCAI identifies the 

serviceable part as any threaded 

titanium bolt, having P/N 527.20.24.489 

that is new and not previously installed. 

To address the unsafe condition, 

Pilatus, pending the development of a 

new design installation, issued Pilatus 

PC–24 Service Bulletin 27–009, dated 

December 18, 2023, which specifies 

instructions to replace the affected part 

and a one-time inspection of the rudder 

mass balance arm and other elements of 

the rudder trim tab installation for 

correct attachment, damage, cracks, 

deformation, surface finish, and 

corrosion on any surrounding parts. The 

MCAI requires periodic replacement of 

affected parts, a one-time inspection of 

the rudder mass balance arm and other 

elements of the rudder trim tab 

installation and, depending on findings, 

accomplishment of applicable corrective 

actions. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–2404. 

Related Service Information Under 1 

CFR Part 51 

EASA Emergency AD 2023–0219–E 

specifies procedures for periodic 

replacement of affected parts, a one-time 

inspection of the rudder mass balance 

arm and other elements of the rudder 

trim tab installation and, depending on 

findings, accomplishment of applicable 

corrective actions. 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in ADDRESSES. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI described above. 

The FAA is issuing this AD after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in EASA Emergency 

AD 2023–0219–E, described previously, 

as incorporated by reference, except for 

any differences identified as exceptions 

in the regulatory text of this AD and 

except as discussed under ‘‘Differences 

Between this AD and EASA Emergency 

AD 2023–0219–E.’’ 

Differences Between This AD and EASA 

Emergency AD 2023–0219–E 

Paragraph (4) of EASA Emergency AD 

2023–0219–E requires contacting Pilatus 


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Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations 90093 

for corrective actions if damage is found 

on the rudder mass balance arm during 

the one-time inspection, but this AD 

requires approval for corrective actions 

in accordance with a method approved 

by the Manager, International Validation 

Branch, FAA; EASA; or Pilatus’ EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval 

must include the DOA-authorized 

signature. 

Interim Action 

The FAA considers that this AD is an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking. 

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 failure of titanium 

threaded bolts installed at the forward 

end of the short rudder trim tab 

actuating rods, if not addressed, could 

lead to damage to the rudder and rudder 

trim tab, which could result in loss of 

rudder control and reduced or loss of 

control of the airplane. Analysis shows 

that these bolts could fail without notice 

once the airplane accumulates 300 

hours time-in-service (TIS) and of the 

112 airplanes affected by this AD, 75 

have already accumulated more than 

300 hours TIS and need these bolts 

replaced within 10 hours TIS after the 

effective date of this AD. 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 the 

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 112 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Replacement of affected titanium threaded bolts.9 work-hours × $85 per 

hour = $765 per replacement cycle.

$220 per replacement 

cycle.

$985 per replacement 

cycle.

$110,320 per replacement 

cycle. 

Inspection of rudder mass 

balance arm and other 

elements of the rudder 

trim tab installation.

1 work-hour × $85 per 

hour = $85.

$0 ...................................... $85 .................................... $9,520. 

The corrective actions that may be 

required as a result of the inspection 

could vary significantly from airplane to 

airplane. The FAA has no data to 

determine the costs to accomplish the 

corrective actions or the number of 

airplanes that may require corrective 

actions. 

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 

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. 


ddrumheller on DSK120RN23PROD with RULES1
90094 Federal Register / Vol. 88, No. 249 / Friday, December 29, 2023 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2023–26–05 Pilatus Aircraft Ltd.: 

Amendment 39–22648; Docket No. 

FAA–2023–2404; Project Identifier 

MCAI–2023–01268–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 3, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–24 Airplanes, as identified in 

European Union Aviation Safety Agency 

(EASA) Emergency AD 2023–0219–E, dated 

December 19, 2023 (EASA Emergency AD 

2023–0219–E), certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2721, Rudder Tab Control System. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that the titanium threaded bolts installed at 

the forward end of the short rudder trim tab 

actuating rods could be subject to 

unexpectedly high oscillating loads due to 

aerodynamic forces acting on the rudder trim 

tab. The FAA is issuing this AD to address 

the unsafe condition. The unsafe condition, 

if not addressed, could result in failure of 

titanium threaded bolts with consequent 

damage to the rudder and rudder trim tab, 

which could result in in loss of rudder 

control and reduced or loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA Emergency AD 

2023–0219–E. 

(h) Exceptions to EASA Emergency AD 2023– 

0219–E 

(1) Where EASA Emergency AD 2023– 

0219–E refers to its effective date, this AD 

requires using the effective date of this AD. 

(2) Where EASA Emergency AD 2023– 

0219–E requires compliance in terms of flight 

hours, this AD requires using hours time-inservice. 

(3) Where paragraph (4) of EASA 

Emergency AD 2023–0190–E specifies to 

‘‘contact Pilatus to obtain approved 

instructions, and within the compliance 

time(s) specified therein, accomplish those 

instructions accordingly;’’ for this AD, 

replace that text with ‘‘accomplish corrective 

action in accordance with a method 

approved by the Manager, International 

Validation Branch, FAA; or EASA; or Pilatus 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(4) Where the service information 

referenced in EASA Emergency AD 2023– 

0190–E specifies to ‘‘Return bellcrank bolts 

with damage to Pilatus Aircraft Ltd.’’ and 

‘‘Return the two threaded bolts (3) (that you 

removed) to Pilatus Aircraft Ltd.’’, this AD 

does not require those actions. 

(5) Where the service information 

referenced in EASA Emergency AD 2023– 

0190–E specifies ‘‘Discard the two lock 

washers (2)’’, for this AD, replace that text 

with ‘‘Remove the two lock washers (2) from 

service.’’ 

(6) This AD does not adopt the Remarks 

paragraph of EASA Emergency AD 2023– 

0190–E. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, International Validation 

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 International Validation 

Branch, mail it to the address identified in 

paragraph (j) of this AD or email to: 9-AVSAIR-730-AMOC@faa.gov. If mailing 

information, also submit information by 

email. 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 Doug Rudolph, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (816) 329– 

4059; email: doug.rudolph@faa.gov. 

(k) 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) European Union Aviation Safety Agency 

(EASA) Emergency AD 2023–0219–E, dated 

December 19, 2023. 

(ii) [Reserved] 

(3) For EASA Emergency AD 2023–0219– 

E, contact EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; phone: +49 221 

8999 000; email: ADs@easa.europa.eu; 

website: easa.europa.eu. You may find this 

EASA Emergency AD on the EASA website 

at ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. 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 December 22, 2023. 

Caitlin Locke, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–28866 Filed 12–27–23; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket Number USCG–2023–0907] 

RIN 1625–AA00 Safety Zone; Fireworks 

Display, Pacific Ocean, Westport, WA 

AGENCY: Coast Guard, Department of 

Homeland Security (DHS). 

ACTION: Temporary final rule. 

SUMMARY: The Coast Guard is 

establishing a temporary safety zone for 

certain waters of the Pacific Ocean. This 

action is necessary to provide for the 

safety of life on these navigable waters 

near Westport, Washington, during a 

fireworks display on January 1, 2024. 

This regulation prohibits persons and 

vessels from entering the safety zone 

unless authorized by the Captain of the 

Port Sector Columbia River or a 

designated representative. 

DATES: This rule is effective from 11:30 

p.m. on December 31, 2023, to 1 a.m. on 

January 1, 2024. 

ADDRESSES: To view documents 

mentioned in this preamble as being 

available in the docket, go to https://

www.regulations.gov, type USCG–2023– 

0907 in the search box and click 

‘‘Search.’’ Next, in the Document Type 

column, select ‘‘Supporting & Related 

Material.’’ 

FOR FURTHER INFORMATION CONTACT: If 

you have questions about this rule, call 

or email Lieutenant Carlie Gilligan, 

Waterways Management Division, 

Sector Columbia River, Coast Guard; 

telephone 503–240–9319, email 

SCRWWM@uscg.mil. 

SUPPLEMENTARY INFORMATION: 

I. Table of Abbreviations 

CFR Code of Federal Regulations 

COTP Captain of the Port Columbia River 

DHS Department of Homeland Security 

FR Federal Register 

NPRM Notice of proposed rulemaking 

§ Section 

U.S.C. United States Code 


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