This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

8684 

Vol. 90, No. 20 

Friday, January 31, 2025 

NUCLEAR REGULATORY 

COMMISSION 

10 CFR Part 73 

[NRC–2024–0167] 

Law Enforcement Response in Power 

Reactor Physical Protection Programs 

In proposed rule 2025–974 beginning 

on page 5743 in the issue of Friday, 

January 17, 2025 make the following 

correction: 

On page 5744, in the third column, 

under the heading ‘‘III. Proposed 

Interpretation’’, in the second line 

‘‘§ 3.55(b)(1) through (3),’’ should read 

‘‘§ 73.55(b)(1) through (3),’’. 

[FR Doc. C1–2025–00974 Filed 1–30–25; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2025–0010; Project 

Identifier MCAI–2024–00270–T] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

(Type Certificate Previously Held by 

Yabora ̃ Indu ́ stria Aerona ́utica S.A.; 

Embraer S.A.; Empresa Brasileira de 

Aerona ́utica S.A. (EMBRAER)) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2006–20–08, which applies to all 

Embraer S.A. Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP airplanes. AD 2006–20–08 

requires repetitive inspections to detect 

cracking or failure of the rod ends and 

fittings of the aileron power control 

actuator (PCA) and corrective actions if 

necessary, and provides an optional 

terminating action. Since the FAA 

issued AD 2006–20–08, it has been 

determined that there was an error in 

identifying a maintenance task number. 

This proposed AD would continue to 

require the actions in AD 2006–20–08 

and corrects an error in a task number, 

as specified in an Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC) AD, which is 

proposed for incorporation by reference 

(IBR). The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by March 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–2025–0010; 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 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 ANAC material identified in 

this proposed AD, contact National Civil 

Aviation Agency (ANAC), Aeronautical 

Products Certification Branch (GGCP), 

Rua Dr. Orlando Feirabend Filho, 230— 

Centro Empresarial Aquarius—Torre 

B—Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́

dos Campos—SP, Brazil; telephone 55 

(12) 3203–6600; email pac@anac.gov.br; 

website anac.gov.br/en/. You may find 

this material on the ANAC website at 

sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. It is also available at 

regulations.gov under Docket No. FAA– 

2025–0010. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

FOR FURTHER INFORMATION CONTACT: 

Hassan Ibrahim, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 206–231–3653; email 

hassan.m.ibrahim@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 the ADDRESSES section. Include 

‘‘Docket No. FAA–2025–0010; Project 

Identifier MCAI–2024–00270–T’’ at the 

beginning of your comments. The most 

helpful comments reference a specific 

portion of the proposal, explain the 

reason for any recommended change, 

and include supporting data. The FAA 

will consider all comments received by 

the closing date and may amend this 

proposal because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

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

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Hassan Ibrahim, 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 8685 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 206–231–3653; 

email hassan.m.ibrahim@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 issued AD 2006–20–08, 

Amendment 39–14777 (71 FR 58487, 

October 4, 2006) (AD 2006–20–08), for 

all Embraer Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP airplanes. AD 2006–20–08 was 

prompted by an MCAI originated by 

Departmento de Aviacao Civil (DAC), 

which was the aviation authority for 

Brazil (now known as ANAC). DAC 

issued AD 1999–02–01R6, dated June 

21, 2004, to correct an unsafe condition. 

AD 2006–20–08 requires repetitive 

inspections to detect cracking or failure/ 

breaking of the rod ends and fittings of 

the aileron PCA, corrective actions if 

necessary, and provides an optional 

terminating action for the requirements. 

The FAA issued AD 2006–20–08 to 

detect and correct cracking or breaking 

of the rod ends and connecting fittings 

of the aileron PCA, which could result 

in reduced controllability of the 

airplane. 

Actions Since AD 2006–20–08 Was 

Issued 

Since the FAA issued AD 2006–20– 

08, ANAC superseded AD 1999–02– 

01R6, dated June 21, 2004, and issued 

ANAC AD 1999–02–01R7, effective May 

6, 2024; corrected October 11, 2024 

(ANAC AD 1999–02–01R7) (also 

referred to as the MCAI), to correct an 

unsafe condition for all Embraer S.A. 

Model EMB–145, –145ER, –145MR, 

–145LR, –145XR, –145MP, and –145EP 

airplanes. The MCAI states that after 

ANAC AD 1999–02–01R6 was issued it 

was identified that the visual inspection 

task number referenced on requirement 

(c) of that AD (AMM TASK 27–12–01– 

212–002–A00, ‘‘Aileron PCA Rod Ends/ 

Fitting, Lugs for Integrity and General 

Condition’’) was incorrect. ANAC AD 

1999–02–01R7 was issued to replace the 

task reference to MRB–145/1150 TASK 

27–12–01–212–002–A05. For airplanes 

identified in paragraph (c) of ANAC AD 

1999–02–01R7, accomplishing 

repetitive inspections as specified in 

MRB–145/1150 TASK 27–12–01–212– 

002–A05 are necessary to address the 

unsafe condition. 

The FAA is proposing this AD to 

detect and correct cracking or breaking 

of the rod ends and connecting fittings 

of the aileron PCA, which could result 

in reduced controllability of the 

airplane. You may examine the MCAI in 

the AD docket at regulations.gov under 

Docket No. FAA–2025–0010. 

Explanation of Retained Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2006–20–08, this proposed AD would 

retain certain requirements of AD 2006– 

20–08. Those requirements are 

referenced in ANAC AD 1999–02–01R7, 

which, in turn, is referenced in 

paragraph (g) of this proposed AD. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

ANAC AD 1999–02–01R7 specifies 

procedures for repetitive inspections to 

detect cracking and failure of the rod 

ends and PCA fittings of the aileron 

PCA and corrective actions if necessary, 

and provides an optional terminating 

action. Corrective actions include 

replacing cracked and failed rod ends 

and PCA fittings. 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 

This product has been approved by 

the aviation authority of another 

country and is 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 referenced above. The FAA 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain 

certain requirements of AD 2006–20–08. 

This proposed AD would require 

accomplishing the actions specified in 

ANAC AD 1999–02–01R7 described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate ANAC AD 1999–02–01R7 

by reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with ANAC AD 1999–02– 

01R7 in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Material required by ANAC AD 1999– 

02–01R7 for compliance will be 

available at regulations.gov under 

Docket No. FAA–2025–0010 after the 

FAA final rule is published. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 272 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

operators 

Retained actions from AD 2006–20–08 ...... 1 work-hour × $85 per hour = $85 .............. None ........ $85 $23,120 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per product 

24 work-hours × $85 per hour = $2,040 ..................................................................................................... $19,817 $21,857 


ddrumheller on DSK120RN23PROD with PROPOSALS1
8686 Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 

The FAA estimates the following 

costs to do any necessary on-condition 

action that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need this 

on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per product 

24 work-hours × $85 per hour = $2,040 ..................................................................................................... $19,817 $21,857 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

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) 2006–20–08, Amendment 39– 

14777 (71 FR 58487, October 4, 2006); 

and 

■ b. Adding the following new AD: 

Embraer S.A. (Type Certificate Previously 

Held by Yabora ̃ Indu ́ stria Aerona ́utica 

S.A.; Embraer S.A.; Empresa Brasileira 

de Aerona ́utica S.A. (EMBRAER)): 

Docket No. FAA–2025–0010; Project 

Identifier MCAI–2024–00270–T. 

(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 2006–20–08, 

Amendment 39–14777 (71 FR 58487, October 

4, 2006) (AD 2006–20–08). 

(c) Applicability 

This AD applies to all Embraer S.A. (Type 

Certificate previously held by Yabora ̃

Indu ́ stria Aerona ́utica S.A.; Embraer S.A.; 

Empresa Brasileira de Aerona ́utica S.A. 

(EMBRAER)) Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP airplanes, certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of 

broken rod ends of the aileron power control 

actuator (PCA) at the aileron or at the wing 

structure connection points and a 

determination that an incorrect task number 

was published in AD 2006–20–08. The FAA 

is issuing this AD to address cracking or 

breaking of the rod ends and connecting 

fittings of the aileron PCA. The unsafe 

condition, if not addressed, could result in 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraphs (h) and 

(i) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC) AD 1999–02–01R7, 

effective May 6, 2024; corrected October 11, 

2024 (ANAC AD 1999–02–01R7). 

(h) Exceptions to ANAC AD 1999–02–01R7 

(1) Where ANAC AD 1999–02–01R7 refers 

to ‘‘21 jul. 2004,’’ this AD requires using 

November 8, 2006 (the effective date of AD 

2006–20–08). 

(2) This AD does not adopt paragraph (f) 

of ANAC AD 1999–02–01R7. 

(3) Where ANAC AD 1999–02–01R7 

specifies ‘‘operating days,’’ this AD requires 

replacing that text with ‘‘days.’’ 

(4) Where paragraphs (a)2. and (a)3. of 

ANAC AD 1999–02–01R7 specify to replace 

cracked and failed rod ends and PCA fittings, 

for this AD, all applicable replacements must 

be done before further flight. 

(5) Where paragraph (a) of ANAC AD 

1999–02–01R7 does not specify an initial 

compliance time for the repetitive 

inspections, for this AD the initial 

compliance time for the inspection is at the 

applicable time identified in paragraph 

(h)(5)(i), (ii), or (iii) of this AD. 

(i) For airplanes that have PCAs with part 

number (P/N) 394900–1003 or 394900–1005, 

do the initial inspection within 3 days after 

November 8, 2006. 

(ii) For airplanes that have PCAs with P/ 

N 394900–1007, do the initial inspection 

within 14 days after November 8, 2006. 

(iii) For airplanes that have PCAs with P/ 

Ns 418800–1001, 418800–1003, 418800– 

9003, 418800–1005, 418800–9005, 418800– 

1007, or 418800–9007; and that have new 

reinforced PCA fittings installed in 

accordance with paragraph (k) or (l) of AD 

2006–20–08 or paragraph (b) of ANAC AD 

1999–02–01R7, do the initial inspection 

within 500 flight hours after November 8, 

2006. 

(6) Where paragraph (b) of ANAC AD 

1999–02–01R7 specifies to accomplish an 

installation within ‘‘6000 operating cycles,’’ 

for this AD, the compliance time is at the 

applicable time specified in paragraph 

(h)(6)(i) or (ii) of this AD. 

(i) For airplanes with PCAs with P/N 

394900–1003, 394900–1005, or 394900–1007: 

At the later of the times in paragraphs 

(h)(6)(i)(A) or (B) of this AD. 

(A) Before the airplane accumulates 6,000 

total flight hours. 

(B) Within 3 days or 25 flight hours after 

November 8, 2006 (the effective date of AD 

2006–20–08), whichever occurs later. 

(ii) For airplanes with PCAs with P/N 

418800–1001, 418800–1003, 418800–9003, 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 8687 

418800–1005, 418800–9005, 418800–1007, or 

418800–9007: Before the airplane 

accumulates 6,000 total flight cycles or 

within 600 flight cycles after November 8, 

2006 (the effective date of AD 2006–20–08), 

whichever occurs later. 

(7) Where paragraph (c) of ANAC AD 

1999–02–01R7 specifies to do an inspection 

in accordance with a task, for this AD, 

inspections done before the effective date of 

this AD using AMM Task 27–12–01–212– 

002–A00 or using a method approved by 

either the Manager, International Validation 

Branch, FAA, or ANAC (or its delegated 

agent) are acceptable methods of compliance. 

Inspections done on or after the effective date 

of this AD must be done using the task 

identified in paragraph (c) of ANAC AD 

1999–02–01R7 or using a method approved 

as specified in paragraph (k)(2) of this AD. 

(8) Where paragraph (c) of ANAC AD 

1999–02–01R7 specifies to accomplish the 

initial inspection ‘‘in conjunction with the 

new PCA fittings and reinforcement 

provisions referred on item (b) above,’’ this 

AD requires replacing that text with ‘‘Within 

500 flight hours after accomplishing the 

installation and reinforcements provisions 

referred to item (b) above.’’ 

(9) Where paragraph (c) of ANAC AD 

1999–02–01R7 specifies to accomplish the 

inspections ‘‘every 500 flight hours’’ this AD 

requires replacing that text with ‘‘at intervals 

not to exceed 500 flight hours.’’ 

(10) Where paragraph (d) of ANAC AD 

1999–02–01R7 specifies to accomplish the 

inspections ‘‘every 1000 flight hours’’ this 

AD requires replacing that text with ‘‘at 

intervals not exceeding 1,000 flight hours.’’ 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

replacement specified in paragraph (a)2. of 

ANAC AD 1999–02–01R7 and the optional 

terminating actions specified in paragraph (d) 

of ANAC AD 1999–02–01R7, if those actions 

were performed before the effective date of 

this AD using EMBRAER Service Bulletin 

145–27–0061, dated October 19, 1999. 

(j) No Return of Parts 

Where the service information identified in 

ANAC AD 1999–02–01R7 specifies to send 

parts to the parts manufacturer, that action is 

not required by this AD. 

(k) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) 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 

responsible Flight Standards 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 (l)(1) of this AD and 

email to: AMOC@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved previously for AD 

2006–20–08 are approved as AMOCs for the 

corresponding provisions of ANAC AD 1999– 

02–01R7 that are required by paragraph (g) of 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or ANAC; or ANAC’s 

authorized Designee. If approved by the 

ANAC Designee, the approval must include 

the Designee’s authorized signature. 

(l) Additional Information 

(1) For more information about this AD, 

contact Hassan Ibrahim, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3653; email hassan.m.ibrahim@faa.gov. 

(2) For EMBRAER material identified in 

this AD that is not incorporated by reference, 

contact Embraer S.A., Technical Publications 

Section (PC 060), Av. Brigadeiro Faria Lima, 

2170—Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—Brasil; telephone +55 12 

3927–5852 or +55 12 3309–0732; fax +55 12 

3927–7546; email distrib@embraer.com.br; 

website flyembraer.com. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 this AD specifies otherwise. 

(i) Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC) AD 1999–02–01R7, effective May 6, 

2024; corrected October 11, 2024. 

(ii) [Reserved] 

(3) For ANAC material identified in this 

AD, contact ANAC, Aeronautical Products 

Certification Branch (GGCP), Rua Dr. Orlando 

Feirabend Filho, 230—Centro Empresarial 

Aquarius—Torre B—Andares 14 a 18, Parque 

Residencial Aquarius, CEP 12.246–190—Sa ̃o 

Jose ́ dos Campos—SP, Brazil; telephone 55 

(12) 3203–6600; email pac@anac.gov.br; 

website anac.gov.br/en/. You may find this 

material on the ANAC website at 

sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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 23, 2025. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2025–01884 Filed 1–30–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2025–0015; Project 

Identifier AD–2024–00615–E] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain General Electric Company (GE) 

Model GEnx–1B64, GEnx–1B64/P1, 

GEnx–1B64/P2, GEnx–1B67, GEnx– 

1B67/P1, GEnx–1B67/P2, GEnx–1B70, 

GEnx–1B70/75/P1, GEnx–1B70/75/P2, 

GEnx–1B70/P1, GEnx–1B70/P2, GEnx– 

1B70C/P1, GEnx–1B70C/P2, GEnx– 

1B74/75/P1, GEnx–1B74/75/P2, GEnx– 

1B76/P2, GEnx–1B76A/P2, and GEnx– 

2B67/P engines. This proposed AD was 

prompted by a manufacturer 

investigation that revealed certain highpressure turbine (HPT) stage 1 and HPT 

stage 2 disks were manufactured from 

powder metal material suspected to 

contain iron inclusion. This proposed 

AD would require replacement of 

affected HPT stage 1 and HPT stage 2 

disks with parts eligible for installation. 

The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by March 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–2025–0015; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this NPRM, any comments 

received, and other information. The 


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