Federal Register / Vol. 89, No. 235 / Friday, December 6, 2024 / Rules and Regulations 96863 

employees, and institutions 

participating in or administering USDA 

programs are prohibited from 

discriminating based on race, color, 

national origin, religion, sex, gender 

identity (including gender expression), 

sexual orientation, disability, age, 

marital status, family/parental status, 

income derived from a public assistance 

program, political beliefs, or reprisal or 

retaliation for prior civil rights activity, 

in any program or activity conducted or 

funded by USDA (not all bases apply to 

all programs). Remedies and complaint 

filing deadlines vary by program or 

incident. 

Program information may be made 

available in languages other than 

English. Persons with disabilities who 

require alternative means of 

communication to obtain program 

information (e.g., Braille, large print, 

audiotape, American Sign Language) 

should contact the responsible Mission 

Area, agency, staff office; or the 711 

Relay Service. 

To file a program discrimination 

complaint, a complainant should 

complete a Form AD–3027, USDA 

Program Discrimination Complaint 

Form, which can be obtained online at 

https://www.usda.gov/sites/default/ 

files/documents/ad-3027.pdf, from any 

USDA office, by calling (866) 632–9992, 

or by writing a letter addressed to 

USDA. The letter must contain the 

complainant’s name, address, telephone 

number, and a written description of the 

alleged discriminatory action in 

sufficient detail to inform the Assistant 

Secretary for Civil Rights (ASCR) about 

the nature and date of an alleged civil 

rights violation. The completed AD– 

3027 form or letter must be submitted to 

USDA by: 

(1) Mail: U.S. Department of 

Agriculture, Office of the Assistant 

Secretary for Civil Rights, 1400 

Independence Avenue SW, Washington, 

DC 20250–9410; or 

(2) Fax: (833) 256–1665 or (202) 690– 

7442; or 

(3) Email: Program.Intake@usda.gov. 

Joaquin Altoro, 

Administrator, Rural Housing Service. 

[FR Doc. 2024–28299 Filed 12–5–24; 8:45 am] 

BILLING CODE 3410–XV–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2546; Project 

Identifier AD–2024–00574–A; Amendment 

39–22902; AD 2024–24–11] 

RIN 2120–AA64 

Airworthiness Directives; Cirrus 

Design Corporation 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 

Cirrus Design Corporation (Cirrus) 

Model SR20, SR22, and SR22T 

airplanes. This AD was prompted by a 

report of failure of the upper power 

lever. This AD requires repetitively 

inspecting (visual) the upper power 

lever for any crack(s) and depending on 

the results of any visual inspection, 

either inspecting (fluorescent penetrant) 

or replacing the upper power lever. This 

AD also requires reporting all inspection 

results to the FAA. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective December 

23, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 23, 2024. 

The FAA must receive comments on 

this AD by January 21, 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–2024–2546; 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 Cirrus material identified in 

this AD, contact Cirrus Design 

Corporation, 4515 Taylor Circle, Duluth, 

MN 55811; phone: (218) 788–3000; fax: 

(218) 788–3525; email: fieldservice@

cirrusaircraft.com; website: 

cirrusaircraft.com. 

• 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–2024–2546. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Koenig, Aviation Safety 

Engineer, FAA, 1801 S Airport Road, 

Wichita, KS 67209; phone: (847) 294– 

7127; email: gregory.l.koenig@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 the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2024–2546; Project Identifier AD–2024– 

00574–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 


lotter on DSK11XQN23PROD with RULES1
96864 Federal Register / Vol. 89, No. 235 / Friday, December 6, 2024 / Rules and Regulations 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Gregory Koenig, 

Aviation Safety Engineer, FAA, 1801 S 

Airport Road, Wichita, KS 67209. 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 is issuing this AD to correct 

an unsafe condition on certain Cirrus 

Model SR20, SR22, and SR22T 

airplanes. The FAA received a report 

that a Cirrus Model SR20 airplane was 

involved in an incident where the upper 

power lever failed while advancing to 

full throttle in preparation for takeoff. 

The flight was successfully aborted by 

cutting fuel to the airplane. After the 

incident, an additional 26 upper power 

levers have been reported to have 

cracks. The available data indicates that 

the probability of visual inspection 

methods to detect cracks in the upper 

power levers are inadequate, and 

therefore a fluorescent penetrant 

inspection (FPI) is also necessary if 

cracks are not detected during the visual 

inspection. These cracks have only been 

discovered on upper power levers that 

include a takeoff/go-around switch. This 

condition, if not addressed, could result 

in loss of engine thrust control and 

reduced control of the airplane. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed Cirrus SR2X 

Service Bulletin SB2X–76–05, dated 

October 29, 2024 (Cirrus SB2X–76–05). 

This material specifies procedures for 

inspecting the upper power lever and 

replacement of the upper power lever if 

cracks are found. 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 the 

ADDRESSES section. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the material 

described previously, except as 

discussed under ‘‘Differences Between 

this AD and the Referenced Material.’’ 

This AD also requires sending all 

inspection results to the FAA. 

Differences Between This AD and the 

Referenced Material 

The effectivity in Cirrus SB2X–76–05 

specifies certain airplane serial numbers 

through 9749, but this AD is applicable 

to Model SR20, SR22, and SR22T 

airplanes, certificated in any category, 

that are equipped with upper power 

lever part number (P/N) 19181–001, 

19181–002, or 46505–001. 

Cirrus SB2X–76–05 specifies that the 

compliance time is within 10 flight 

hours for airplanes with 2,000 flight 

hours or more, but this AD has a 

compliance time of before an upper 

power lever accumulates 1,200 hours 

time-in-service (TIS), within 10 hours 

TIS on the upper power lever after the 

effective date of this AD, or within 15 

days after the effective date of this AD, 

whichever occurs later. This compliance 

time was developed based on data 

received from the 27 reported incidents, 

which indicated that an incident 

occurred as low as 2,948 hours TIS and 

that this unsafe condition could occur 

on airplanes with 1,200 hours TIS 

accumulated on the upper power lever. 

Based on this incident data, coupled 

with the fact that a large number of 

airplanes are either approaching or over 

1,200 hours TIS and the propagation 

rate for this unsafe condition is 

unknown, the FAA’s risk assessment 

was that the accumulation of 2,000 

flight hours or more would not 

adequately mitigate the unsafe 

condition. 

Cirrus SB2X–76–05 includes an 

action to revise the aircraft maintenance 

manual (AMM) by including a 

temporary revision that specifies 

repetitive inspections every 2,000 hours 

TIS, but this AD does not require this 

AMM revision. Instead, this AD requires 

repetitive inspections at intervals not to 

exceed 110 hours TIS. While Cirrus 

specifies a repetitive inspection every 

2,000 hours TIS, the FAA is requiring a 

repetitive inspection at a frequency that 

considers the potential development 

and propagation of these cracks beyond 

1,200 hours TIS. 

Cirrus SB2X–76–05 does not specify 

reporting inspection results and this AD 

requires reporting inspection results to 

the FAA. 

Cirrus SB2X–76–05 specifies to return 

cracked (damaged) upper power levers 

to Cirrus, but this AD does not require 

this action. This AD, instead, requires 

removing any cracked (damaged) upper 

power lever from service. 

Replacing the upper power lever with 

P/N 19181–001, 19181–002, or 46505– 

001 does not terminate the requirements 

of this AD. The inspection would be 

required before any affected upper 

power lever accumulates 1,200 hours 

TIS. 

Interim Action 

The FAA considers this AD to be an 

interim action. The manufacturer is 

currently developing a terminating 

action that will address the unsafe 

condition identified in this AD. Once 

the modification is developed, 

approved, and available, the FAA might 

consider additional rulemaking. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(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 cracking in the upper 

power lever leads to failure of the upper 

power lever, which could result in loss 

of engine thrust control and reduced 

control of the airplane. The FAA’s 

initial analysis based on crack data from 

the reported incidents shows that this 

condition could occur on airplanes with 

1,200 hours TIS accumulated on the 

upper power lever. Since a large 

percentage of the Cirrus Model SR20, 

SR22, and SR22T airplanes have 

exceeded or are approaching 1,200 

hours TIS and because the propagation 

rate for this unsafe condition is 

unknown, an inspection of the upper 

power lever is required within 10 hours 

TIS or 15 days after the effective date of 

this AD, whichever occurs later, for 

airplanes before accumulating 1,200 

hours TIS to detect cracks in the upper 

power lever. These compliance times 

are shorter than the time necessary for 

the public to comment and for 

publication of the final rule. 

Accordingly, notice and opportunity for 

prior public comment are unnecessary, 

pursuant to 5 U.S.C. 553(b). 

In addition, for the foregoing 

reason(s), the FAA finds that good cause 


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Federal Register / Vol. 89, No. 235 / Friday, December 6, 2024 / Rules and Regulations 96865 

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

making this amendment effective in less 

than 30 days. 

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 6,811 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 

Perform visual inspection ......................... 2 work-hours × $85 per hour = $170 per 

inspection.

$0 $170 per inspection $1,157,870 per inspection. 

Report inspection results .......................... 1 work-hour × $85 per hour = $85 per inspection.0 $85 per inspection $578,935 per inspection. 

The FAA estimates the following 

costs to do any necessary replacements 

that would be required based on the 

results of the inspection. The agency has 

no way of determining the number of 

airplanes that might need this 

replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Perform FPI .................................................................. 2 work-hours × $85 per hour = $170 per inspection ... $0 $170 

Replace upper power lever .......................................... 1 work-hour × $85 per hour = $85 ............................... 50 135 

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. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to be 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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: 

2024–24–11 Cirrus Design Corporation: 

Amendment 39–22902; Docket No. 

FAA–2024–2546; Project Identifier AD– 

2024–00574–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective December 23, 2024. 

(b) Affected ADs 

None. 


lotter on DSK11XQN23PROD with RULES1
96866 Federal Register / Vol. 89, No. 235 / Friday, December 6, 2024 / Rules and Regulations 

(c) Applicability 

This AD applies to Cirrus Design 

Corporation Model SR20, SR22, and SR22T 

airplanes, certificated in any category, that 

are equipped with upper power lever part 

number (P/N) 19181–001, 19181–002, or 

46505–001. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7603, Power Lever. 

(e) Unsafe Condition 

This AD was prompted by a report of 

failure of the upper power lever. The FAA is 

issuing this AD to detect and address cracks 

in the upper power lever. The unsafe 

condition, if not addressed, could result in 

loss of engine thrust control and reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Initially, at whichever time occurs latest 

in paragraphs (g)(1)(i) through (iii) of this AD 

and thereafter at intervals not to exceed 110 

hours time-in-service (TIS), visually inspect 

the upper power lever in accordance with 

paragraphs A. through F. of the 

Accomplishment Instructions in Cirrus SR2X 

Service Bulletin SB2X–76–05, dated October 

29, 2024 (Cirrus SB2X–76–05). 

(i) Before any upper power lever identified 

in paragraph (c) of this AD accumulates 1,200 

hours TIS, 

Note 1 to paragraph (g)(1)(i): These parts 

are not serialized. If by checking the logbook, 

you cannot determine how many hours the 

upper power lever has since installation, 

then you may use the hours TIS of the 

airplane. 

(ii) Within 10 hours TIS on the upper 

power lever after the effective date of this 

AD; or 

(iii) Within 15 days after the effective date 

of this AD. 

(2) If any crack(s) are found during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace the 

upper power lever with a new (zero hours 

TIS) upper power lever and do the actions in 

accordance with paragraphs L. through N. of 

the Accomplishment Instructions in Cirrus 

SB2X–76–05, as applicable. 

(3) If no crack(s) are found during any 

inspection required by (g)(1) of this AD, 

before further flight, perform a fluorescent 

penetrant inspection in accordance with 

paragraphs G. through J. of the 

Accomplishment Instructions in Cirrus 

SB2X–76–05. 

(i) If any crack(s) are found during any 

inspection required by paragraph (g)(3) of 

this AD, before further flight, replace the 

upper power lever with a new (zero hours 

TIS) upper power lever and do the actions in 

accordance with paragraphs L. through N. of 

the Accomplishment Instructions in Cirrus 

SB2X–76–05, as applicable. 

(ii) If no crack(s) are found during any 

inspection required by paragraph (g)(3) of 

this AD, reinstall the existing upper power 

lever and do the actions in accordance with 

paragraphs L. through N. of the 

Accomplishment Instructions in Cirrus 

SB2X–76–05, as applicable. 

(4) Cirrus SB2X–76–05 specifies to return 

cracked (damaged) upper power levers to 

Cirrus, this AD does not require that action 

but requires removing any cracked (damaged) 

upper power lever from service. 

(h) Reporting Requirement 

Within 5 days after the inspections 

required by paragraphs (g)(1) and (3) of this 

AD or within 5 days after the effective date 

of this AD, whichever occurs later, report all 

inspection results to the FAA at the address 

specified in paragraph (j) of this AD. The 

report must include the airplane registration 

and serial number, results of each inspection, 

the airplane’s hours TIS, and any additional 

operator/mechanic comments. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Central 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 

Central Certification Branch, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: AMOC@faa.gov. 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 Gregory Koenig, Aviation Safety 

Engineer, FAA, 1801 S Airport Road, 

Wichita, KS 67209; phone: (847) 294–7127; 

email: gregory.l.koenig@faa.gov. 

(k) 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) Cirrus SR2X Service Bulletin SB2X–76– 

05, dated October 29, 2024. 

(ii) [Reserved] 

(3) For Cirrus material identified in this 

AD, contact Cirrus Design Corporation, 4515 

Taylor Circle, Duluth, MN 55811; phone: 

(218) 788–3000; fax: (218) 788–3525; email: 

fieldservice@cirrusaircraft.com; website: 

cirrusaircraft.com. 

(4) 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. 

(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 27, 2024. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2024–28552 Filed 12–3–24; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2024–1396; Airspace 

Docket No. 24–AEA–3] 

RIN 2120–AA66 

Amendment of VOR Federal Airways 

V–258, V–519, and RNAV Route T–426; 

and Revocation of Jet Routes J–213 

and J–526, and VOR Federal Airway V– 

59 in the Vicinity of Beckley, WV 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Very High 

Frequency Omnidirectional Range 

(VOR) Federal Airways V–519 and Area 

Navigation (RNAV) Route T–426; and 

revokes Jet Routes J–213 and J–526, and 

VOR Federal Airways V–59 and V–258. 

The FAA is taking this action due to the 

planned decommissioning of the VOR 

portion of the Beckley, WV (BKW), 

VOR/Distance Measuring Equipment 

(VOR/DME) navigational aid (NAVAID). 

The Beckley VOR is being 

decommissioned in support of the 

FAA’s VOR Minimum Operational 

Network (MON) program. 

DATES: Effective date 0901 UTC, 

February 20, 2025. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR part 51, subject to the annual 

revision of FAA Order JO 7400.11 and 

publication of conforming amendments. 

ADDRESSES: A copy of the Notice of 

Proposed Rulemaking (NPRM), all 

comments received, this final rule, and 

all background material may be viewed 

online at www.regulations.gov using the 

FAA Docket number. Electronic 

retrieval help and guidelines are 

available on the website. It is available 

24 hours each day, 365 days each year. 

FAA Order JO 7400.11J, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at www.faa.gov/air_traffic/ 

publications/. You may also contact the 

Rules and Regulations Group, Office of 

Policy, Federal Aviation 

Administration, 600 Independence 

Avenue SW, Washington, DC 20597; 

telephone: (202) 267–8783. 


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