Federal Register / Vol. 90, No. 19 / Thursday, January 30, 2025 / Proposed Rules 8507 

(3) For affected HPT stage 1 disks 

identified in Table 1 to paragraph (c) of this 

AD that are not included in paragraph (g)(1) 

of this AD, at the next piece part exposure 

or before the affected HPT stage 1 disk 

exceeds 8,600 cycles since new (CSN), 

whichever occurs first after the effective date 

of this AD, remove the affected HPT stage 1 

disk from service and replace with a part 

eligible for installation. 

(4) For affected HPT stage 2 disks 

identified in Table 1 to paragraph (c) of this 

AD that are not included in paragraph (g)(2) 

of this AD, at the next piece part exposure 

or before the affected HPT stage 2 disk 

exceeds 12,000 CSN, whichever occurs first 

after the effective date of this AD, remove the 

affected HPT stage 2 disk from service and 

replace with a part eligible for installation. 

(h) Definitions 

For the purpose of this AD: 

(1) A ‘‘part eligible for installation’’ is any 

HPT stage 1 disk or HPT stage 2 disk that 

does not have a P/N and S/N identified in 

Table 1 to paragraph (c) of this AD. 

(2) A ‘‘piece part exposure’’ is when the 

affected part is removed from the engine and 

completely disassembled. 

(i) Grace Period for HPT Stage 1 Disk 

Replacement 

For affected HPT stage 1 disks having 

greater than 8,550 CSN on the effective date 

of this AD, the replacement required by 

paragraph (g)(3) of this AD may be deferred 

up to 50 flight cycles after the effective date 

of this AD. 

(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 AIR–520 Continued 

Operational Safety Branch, send it to the 

attention of the person identified in 

paragraph (k) of this AD and email to: 

AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Additional Information 

For more information about this AD, 

contact Alexei Marqueen, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238–7178; 

email: alexei.t.marqueen@faa.gov. 

(l) Material Incorporated by Reference 

None. 

Issued on January 21, 2025. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–01728 Filed 1–29–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2025–0013; Project 

Identifier MCAI–2024–00375–A] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio 

Aviation S.p.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2023–25–03, which applies to certain 

Piaggio Aviation S.p.A. (Piaggio) Model 

P–180 airplanes. AD 2023–25–03 

requires a one-time detailed inspection 

of the horizontal stabilizer (HS) central 

box for corrosion; an assessment of the 

corrosion level; and depending on the 

determination, repetitive detailed 

inspections of the HS central box for 

corrosion and the internal composite 

structure for surface cracks, distortion, 

and damage; and repair or replacement 

of the HS assembly. Repair or 

replacement of the HS assembly is 

terminating action for the repetitive 

inspections. Since the FAA issued AD 

2023–25–03, it was determined that AD 

2023–25–03 imposed an unintended 

restriction that is not in the mandatory 

continuing airworthiness information 

(MCAI). This proposed AD would retain 

certain actions of AD–2023–25–03 and 

would remove the unintended 

restriction. The FAA is proposing this 

AD to address the unsafe condition on 

these products. 

DATES: The FAA must receive comments 

on this NPRM by March 17, 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–2025–0013; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this NPRM, the MCAI, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Material Incorporated by Reference: 

• For Piaggio material identified in 

this proposed AD, contact Piaggio 

Aviation S.p.A., P180 Customer 

Support, via Pionieri e Aviatori d’Italia, 

snc—16154 Genoa, Italy; phone: +39 

331 679 74 93; email: technicalsupport@

piaggioaerospace.it. 

• 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. 

FOR FURTHER INFORMATION CONTACT: 

William McCully, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

(404) 474–5548; email: 

william.mccully@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–2025–0013; Project Identifier 

MCAI–2024–00375–A’’ 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 the proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 


lotter on DSK11XQN23PROD with PROPOSALS1
8508 Federal Register / Vol. 90, No. 19 / Thursday, January 30, 2025 / Proposed Rules 

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 William McCully, 

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 

The FAA issued AD 2023–25–03, 

Amendment 39–22630 (88 FR 90085, 

December 29, 2023) (AD 2023–25–03), 

for certain Piaggio Model P–180 

airplanes. 

AD 2023–25–03 was prompted by 

MCAI originated by the European Union 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union. EASA 

issued EASA AD 2023–0007, dated 

January 13, 2023 (EASA AD 2023–0007, 

also referred to as the MCAI) to correct 

an unsafe condition identified as a 

finding of corrosion inside the HS 

central box of a Piaggio Model P–180 

airplane during scheduled maintenance. 

A subsequent investigation and 

inspection of 16 other Piaggio Model P– 

180 airplanes of various configurations 

and ages revealed that corrosion of 

differing levels of severity was found on 

various aluminum alloy reinforcements 

in the HS central box of all the 

inspected airplanes. The MCAI also 

states that this corrosion was caused by 

the formation of a humid environment 

inside the HS central box, from water 

ingress and/or condensation. Further 

investigation revealed that airplanes left 

in prolonged inactivity or parked 

outside are more prone to develop 

corrosion damage. 

AD 2023–25–03 requires a one-time 

detailed inspection of the HS central 

box for corrosion; an assessment of the 

corrosion level; and depending on the 

determination, repetitive detailed 

inspections of the HS central box for 

corrosion and the internal composite 

structure for surface cracks, distortion, 

and damage; and repair or replacement 

of the HS assembly. Repair or 

replacement of the HS assembly is 

terminating action for the repetitive 

inspections. The FAA issued AD 2023– 

25–03 to address corrosion on various 

aluminum alloy reinforcements in the 

HS central box caused by a humid 

environment inside the box from water 

ingress and/or condensation. 

Actions Since AD 2023–25–03 Was 

Issued 

Since the FAA issued AD 2023–25– 

03, it was determined that a portion of 

paragraph (g)(4)(ii) of that AD includes 

an unintended requirement to replace 

the HS assembly after 660 hours timein-service (TIS) or 13 months, 

whichever occurs first, following a 

finding of level 2 corrosion. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2025–0013. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

This proposed AD would require 

Piaggio Aerospace Service Bulletin 80– 

0489, Revision 2, dated November 30, 

2022, which the Director of the Federal 

Register approved for incorporation by 

reference as of February 2, 2024 (88 FR 

90085, December 29, 2023). 

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. 

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 and material 

referenced above. The FAA is issuing 

this NPRM after determining that the 

unsafe condition described previously is 

likely to exist or develop on other 

products of the same type design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD retains all the 

actions of AD–2023–05 except for the 

requirement to replace the HS assembly 

after 660 hours TIS or 13 months, 

whichever occurs first, following a 

finding of level 2 corrosion. This 

proposed AD would also require 

accomplishing the actions specified in 

the material already described except as 

discussed under ‘‘Differences Between 

this Proposed AD and the MCAI.’’ 

Differences Between This Proposed AD 

and the MCAI 

The MCAI requires contacting the 

manufacturer for a determination of the 

corrosion level if any corrosion is found 

during the initial inspection of the HS 

central box, and if it is determined that 

level 2 or 3 corrosion is present, having 

the manufacturer provide the threshold 

and intervals for doing repetitive 

inspections of the HS central box. This 

proposed AD would require contacting 

either the FAA, EASA, or Piaggio’s 

EASA Design Organization Approval 

(DOA). If approved by the DOA, the 

approval must include the DOAauthorized signature. 

Although Piaggio Aerospace Service 

Bulletin 80–0489, Revision 2, dated 

November 30, 2022, specifies to record 

the image of the location of corroded 

areas, this proposed AD would not 

require that action. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 102 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Initial inspection of HS central box for corrosion.6 work-hours × $85 per hour = $510 ............. $0 $510 $52,020 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repetitive inspections of HS central box 

for corrosion.

6 work-hours × $85 per hour = $510, per 

inspection cycle.

$0 $510, per inspection cycle. 


lotter on DSK11XQN23PROD with PROPOSALS1
Federal Register / Vol. 90, No. 19 / Thursday, January 30, 2025 / Proposed Rules 8509 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per product 

Repetitive inspections for surface cracks, 

distortion, and damage.

6 work-hours × $85 per hour = $510, per 

inspection cycle.

$0 $510, per inspection cycle. 

Replace HS assembly ............................. 10 work-hours × $85 per hour = $850 .... $150,000 $150,850. 

The repair of the HS assembly that 

may be required as a result of any 

inspection could vary significantly from 

airplane to airplane. The FAA has no 

data to determine the costs to 

accomplish the repair or the number of 

airplanes that may require the repair. 

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 that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

AD 2023–25–03, Amendment 39–22630 

(88 FR 90085, December 29, 2023); and 

■ b. Adding the following new 

airworthiness directive: 

Piaggio Aviation S.p.A.: Docket No. FAA– 

2025–0013; Project Identifier MCAI– 

2024–00375–A. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 17, 

2025. 

(b) Affected ADs 

This AD replaces AD 2023–25–03, 

Amendment 39–22630 (88 FR 90085, 

December 29, 2023). 

(c) Applicability 

This AD applies to Piaggio Aviation S.p.A. 

Model P–180 airplanes, serial numbers (S/ 

Ns) 1002, 1004 through 1234 inclusive, 3001 

through 3012 inclusive, and 3016, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5510, Horizontal Stabilizer Structure. 

(e) Unsafe Condition 

This AD was prompted by a report of 

corrosion on the various aluminum alloy 

reinforcements in the horizontal stabilizer 

(HS) central box caused by a humid 

environment inside the box from water 

ingress and/or condensation. The FAA is 

issuing this AD to address this condition. 

The unsafe condition, if not addressed, could 

result in reduced structural integrity of the 

HS and loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the applicable compliance time 

specified in table 1 to paragraph (g)(1) of this 

AD, do a detailed inspection of the HS 

central box for corrosion, in accordance with 

step (8), of Part A, of the Accomplishment 

Instructions in Piaggio Aerospace Service 

Bulletin 80–0489, Revision 2, dated 

November 30, 2022 (Piaggio SB 80–0489, 

Revision 2), except you are not required to 

record any images. 

TABLE 1 TO PARAGRAPH (g)(1)—HS CENTRAL BOX ONE TIME INSPECTION

P–180 Serial number 

Compliance time (hours time-in-service (TIS) or calendar time, whichever occurs first after February 2, 2024 (the effective date of AD 2023– 

25–03)) 

1002; and 1034 through 3016 inclusive ................................................... Within 220 hours TIS or 13 months after February 2, 2024 (the effective date of AD 2023–25–03). 

1004 through 1033 inclusive .................................................................... Within 320 hours TIS or 13 months after February 2, 2024 (the effective date of AD 2023–25–03). 

(2) If, during the inspection required by 

paragraph (g)(1) of this AD, any corrosion is 

detected, before next flight, contact either the 

Manager, International Validation Branch, 

FAA; European Union Aviation Safety 

Agency (EASA); or Piaggio’s EASA Design 

Organization Approval (DOA), for an 

assessment of the corrosion level (level 1, 2, 

or 3). 

Note 1 to paragraph (g)(2): Appendix 1, 

Inspection Results Form, in Piaggio SB 80– 


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8510 Federal Register / Vol. 90, No. 19 / Thursday, January 30, 2025 / Proposed Rules 

0489, Revision 2, may be used when 

contacting the FAA, EASA, or Piaggio’s 

EASA DOA. 

(3) If level 1 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, no further action is required by this 

AD. 

(4) If level 2 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, do the action in either paragraph 

(g)(4)(i) or (ii) of this AD. 

(i) Before further flight, replace the HS 

assembly or repair the HS assembly in 

accordance with instructions from either the 

Manager, International Validation Branch, 

FAA; EASA; or Piaggio’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(ii) Within 400 hours TIS or 12 months, 

whichever occurs first after the inspection 

required by paragraph (g)(1) of this AD, and 

thereafter at intervals not to exceed 400 hours 

TIS or 12 months, whichever occurs first 

after the most recent inspection, repeat the 

inspection required by paragraph (g)(1) of 

this AD. In addition, inspect the internal 

composite structure of the HS central box for 

surface cracks, distortion, and damage. After 

each repetitive inspection, before further 

flight, assess the inspection findings as 

required by paragraph (g)(2) of this AD. If it 

is determined that the level 2 corrosion has 

worsened since the last inspection; or if any 

surface cracks, distortion, or damage is found 

during any inspection; before further flight, 

replace the HS assembly or repair the HS 

assembly in accordance with instructions 

from either the Manager, International 

Validation Branch, FAA; EASA; or Piaggio’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. These inspections must be 

repeated at intervals not to exceed 400 hours 

TIS or 12 months, whichever occurs first 

after the most recent inspection. 

(5) If level 3 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, do the actions required by paragraph 

(g)(5)(i) or (ii) of this AD. 

(i) Before further flight after the inspection 

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

replace the HS assembly or repair the HS 

assembly in accordance with instructions 

from either the Manager, International 

Validation Branch, FAA; EASA; or Piaggio’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(ii) Within 200 hours TIS or 6 months, 

whichever occurs first after the inspection 

required by paragraph (g)(1) of this AD, and 

thereafter at intervals not to exceed 200 hours 

TIS or 6 months, whichever occurs first after 

the most recent inspection, repeat the 

inspection required by paragraph (g)(1) of 

this AD. In addition, inspect the internal 

composite structure of the HS central box for 

surface cracks, distortion, and damage. After 

each repetitive inspection, before further 

flight, assess the inspection findings as 

required by paragraph (g)(2) of this AD. If it 

is determined that the level 3 corrosion has 

worsened since the last inspection; or if any 

surface cracks, distortion, or damage is 

found; before further flight, replace the HS 

assembly or repair the HS assembly in 

accordance with instructions from either the 

Manager, International Validation Branch, 

FAA; EASA; or Piaggio’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. These 

inspections must be repeated at intervals not 

to exceed 200 hours TIS or 6 months, 

whichever occurs first after the most recent 

inspection, until a maximum of 660 hours 

TIS or 13 months, whichever occurs first 

after the inspection required by paragraph 

(g)(1) of this AD, at which time the HS 

assembly must be repaired or replaced. 

(6) Repair or replacement of the HS 

assembly is terminating action for the 

repetitive inspections required by paragraphs 

(g)(4)(ii) and (g)(5)(ii) of this AD. 

(h) Credit for Previous Actions 

You may take credit for the actions 

required by paragraphs (g)(1) through (5) of 

this AD if you performed those actions before 

the effective date of this AD using Piaggio 

Aerospace Service Bulletin 80–0489, 

Revision 1, dated May 13, 2022. 

(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: 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 William McCully, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (404) 474– 

5548; email: william.mccully@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. 

(3) The following material was approved 

for IBR on February 2, 2024 (88 FR 90085, 

December 29, 2023). 

(i) Piaggio Aerospace Service Bulletin 80– 

0489, Revision 2, dated November 30, 2022. 

(ii) [Reserved] 

(4) For Piaggio material identified in this 

AD, contact Piaggio Aviation S.p.A., P180 

Customer Support, via Pionieri e Aviatori 

d’Italia, snc—16154 Genoa, Italy; phone: +39 

331 679 74 93; email: technicalsupport@

piaggioaerospace.it. 

(5) 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. 

(6) 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, 2025. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–01968 Filed 1–29–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2024–2679 Airspace 

Docket No. 24–AAL–110] 

RIN 2120–AA66 

Revocation of Colored Federal Airway 

Green 6 (G–6) and Alaskan Very High 

Frequency Omnidirectional Range 

Federal Airways V–459 and V–496 in 

Alaska 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

revoke Colored Federal Airway Green 6 

(G–6) and Alaskan Very High Frequency 

Omnidirectional Range (VOR) Federal 

Airways V–459 and V–496 in Alaska. 

The identifier V–459 is also used for a 

VOR Federal Airway in California. This 

action is proposing to revoke the 

Alaskan V–459, not the V–459 in 

California. The FAA is proposing this 

action due to the pending 

decommissioning of the St. Marys, AK, 

Nondirectional Radio Beacon (NDB) and 

the Aniak, AK, NDB. 

DATES: Comments must be received on 

or before March 17, 2025. 

ADDRESSES: Send comments identified 

by FAA Docket No. FAA–2024–2679 

and Airspace Docket No. 24–AAL–110 

using any of the following methods: 

* Federal eRulemaking Portal: Go to 

www.regulations.gov and follow the 

online instructions for sending your 

comments electronically. 

* Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE, Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

* Hand Delivery or Courier: Take 

comments to Docket Operations in 


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