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 


ddrumheller on DSK120RN23PROD with PROPOSALS1
8688 Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 

street address for Docket Operations is 

listed above. 

Material Incorporated by Reference: 

• For GE material identified in this 

proposed AD, contact GE, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ge.com; website: 

ge.com. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. 

FOR FURTHER INFORMATION 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. 

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–2025–0015; Project 

Identifier AD–2024–00615–E’’ 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 revise 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 Alexei Marqueen, 

Aviation Safety Engineer, FAA, 2200 

South 216th Street, Des Moines, WA 

98198. 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 was notified by the 

manufacturer of the detection of iron 

inclusion in a turbine disk 

manufactured from the same powder 

metal material used to manufacture 

certain HPT stage 1 and HPT stage 2 

disks for 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. Further 

investigation by the manufacturer 

determined that the iron inclusion is 

attributed to deficiencies in the 

manufacturing process and may cause 

reduced material properties and a lower 

fatigue life capability, which may result 

in premature fracture and uncontained 

failure. The manufacturer also informed 

the FAA that additional risk 

assessments determined that there were 

no failed events associated with the 

discovery of this iron inclusion material 

on these engines, but concluded that 

replacement of the affected HPT stage 1 

and HPT stage 2 disks is necessary to 

prevent any future failed events. The 

exposure of HPT stage 1 and HPT stage 

2 disks to iron inclusion, if not 

addressed, could result in uncontained 

debris release, damage to the engine, 

and damage to the airplane. 

FAA’s Determination 

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. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed GE GEnx–1B 

Service Bulletin 72–0542 R00, dated 

April 15, 2024 (GE GEnx–1B SB 72– 

0542 R00). The FAA also reviewed GE 

GEnx–2B Service Bulletin 72–0471 R00, 

dated April 15, 2024. This material 

specifies the affected part numbers, 

serial numbers, and cyclic removal 

thresholds for the HPT stage 1 and HPT 

stage 2 disks. 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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

replacement of certain HPT stage 1 disks 

and HPT stage 2 disks. Depending on 

the part numbers and serial numbers of 

the affected HPT stage 1 disks and HPT 

stage 2 disks, this NPRM proposes to 

require these actions to be accomplished 

at the next piece-part exposure after the 

effective date of this proposed AD or 

before the affected HPT stage 1 disks 

and HPT stage 2 disks reach the cyclic 

removal threshold of up to 10,100 cycles 

since new. 

Differences Between This Proposed AD 

and the Referenced Material 

GE GEnx–1B SB 72–0542 R00 uses the 

terms ‘‘HPT rotor stage 1 disk’’ and 

‘‘HPT rotor stage 2 disk,’’ while this 

proposed AD uses the terms ‘‘HPT stage 

1 disk’’ and ‘‘HPT stage 2 disk.’’ 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect one 

engine installed on an airplane of U.S. 

registry. The FAA estimates that no 

engines installed on airplanes of U.S. 

registry would require replacement of 

the HPT stage 2 disk. 

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 

Replace HPT stage 1 disk .................... 8 work-hours × $85 per hour = $680 ................ $757,416 (prorated) ..... $758,096 $758,096 

Replace HPT stage 2 disk .................... 8 work-hours × $85 per hour = $680 ................ 278,101 (prorated) ....... 278,781 0 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 8689 

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 adding 

the following new airworthiness 

directive: 

General Electric Company: Docket No. FAA– 

2025–0015; Project Identifier AD–2024– 

00615–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 17, 

2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company 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 with at least one of the 

following installed: 

(1) High Pressure Turbine (HPT) stage 1 

disk having part number (P/N) 2383M83G03 

and a serial number (S/N) listed in Table 1 

of GE GEnx–1B Service Bulletin 72–0542 

R00, dated April 15, 2024 (GE GEnx–1B SB 

72–0542 R00); 

(2) HPT stage 2 disk having P/N 

2300M84P02 and a S/N listed in Table 2 of 

GE GEnx–1B SB 72–0542 R00; 

(3) HPT stage 1 disk having P/N 

2383M83G03 and a S/N listed in Table 1 of 

GE GEnx–2B Service Bulletin 72–0471 R00, 

dated April 15, 2024 (GE GEnx–2B SB 72– 

0471 R00); or 

(4) HPT stage 2 disk having P/N 

2300M84P02 and a S/N listed in Table 2 of 

GE GEnx–2B SB 72–0471 R00. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by a manufacturer 

investigation that revealed certain HPT stage 

1 disks and HPT stage 2 disks were 

manufactured from powder metal material 

suspected to contain iron inclusion. The FAA 

is issuing this AD to prevent premature 

fracture and uncontained failure. The unsafe 

condition, if not addressed, could result in 

uncontained debris release, damage to the 

engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

At the applicable time specified in 

paragraphs (g)(1) through (4) of this AD, 

remove each affected HPT stage 1 disk and 

HPT stage 2 disk from service and replace 

with a part eligible for installation. 

(1) For engines identified in paragraph 

(c)(1) of this AD, at the next piece-part 

exposure after the effective date of this AD 

or before the affected HPT stage 1 disk 

exceeds the cyclic removal threshold listed 

in Table 1 of GE GEnx–1B SB 72–0542 R00, 

whichever occurs first. 

(2) For engines identified in paragraph 

(c)(2) of this AD, at the next piece-part 

exposure after the effective date of this AD 

or before the affected HPT stage 2 disk 

exceeds the cyclic removal threshold listed 

in Table 2 of GE GEnx–1B SB 72–0542 R00, 

whichever occurs first. 

(3) For engines identified in paragraph 

(c)(3) of this AD, at the next piece-part 

exposure after the effective date of this AD 

or before the affected HPT stage 1 disk 

exceeds the cyclic removal threshold listed 

in Table 1 of GE GEnx–2B SB 72–0471 R00, 

whichever occurs first. 

(4) For engines identified in paragraph 

(c)(4) of this AD, at the next piece-part 

exposure after the effective date of this AD 

or before the affected HPT stage 2 disk 

exceeds the cyclic removal threshold listed 

in Table 2 of GE GEnx–2B SB 72–0471 R00, 

whichever occurs first. 

(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 with 

a P/N and S/N that is not listed in Table 1 

or Table 2 of either GEnx–1B SB 72–0542 

R00 or GEnx–2B SB 72–0471 R00. 

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

affected HPT stage 1 disk or HPT stage 2 disk 

is removed from the engine. 

(i) 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 (j) 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. 

(j) 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. 

(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) GE GEnx–1B Service Bulletin (SB) 72– 

0542 R00, dated April 15, 2024. 

(ii) GE GEnx–2B SB 72–0471 R00, dated 

April 15, 2024. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
8690 Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Proposed Rules 

(3) For GE material identified in this AD, 

contact General Electric Company, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ge.com; website: 

ge.com. 

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

Airworthiness Products Section, Operational 

Safety Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on January 27, 2025. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02016 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–2025–0012; Project 

Identifier AD–2024–00219–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

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 The Boeing Company Model 

757–200, –200CB, and –300 series 

airplanes. This proposed AD was 

prompted by a report of cracking found 

in new locations at a certain body 

station (STA) during frame segment 

replacement repairs, including in the 

web at the K-hole between certain 

stringers, in the outer chord above the 

lower hinge intercostal, and in the inner 

chord and web between certain 

stringers. This proposed AD would 

require an inspection or records check 

for the presence of approved or local 

repairs, repetitive eddy current 

inspections for cracking, and applicable 

on-condition actions. 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–2025–0012; 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 

street address for Docket Operations is 

listed above. 

Material Incorporated by Reference: 

• For the Boeing material identified 

in this proposed AD, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 

2600 Westminster Blvd., MC 110–SK57, 

Seal Beach, CA 90740–5600; telephone 

562–797–1717; website 

myboeingfleet.com. 

• For the Aviation Partners Boeing 

material identified in this proposed AD, 

contact Aviation Partners Boeing, 2811 

South 102nd St., Suite 200, Seattle, WA 

98168; telephone 206–830–7699; fax 

206–767–0535; email leng@

aviationpartners.com; website 

aviationpartnersboeing.com. 

• 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. 

Boeing Alert Requirements Bulletin 

757–53A0123 RB, dated March 13, 

2024, is also available at regulations.gov 

under Docket No. FAA–2025–0012. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Ha, Aviation Safety Engineer, 

FAA, 2200 South 216th St., Des Moines, 

WA 98198; phone: 562–627–5238; 

email: wayne.ha@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–2025–0012; Project 

Identifier AD–2024–00219–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 Wayne Ha, Aviation 

Safety Engineer, FAA, 2200 South 216th 

St., Des Moines, WA 98198; phone: 

562–627–5238; email: wayne.ha@

faa.gov. Any commentary that the FAA 

receives that is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA has received a report 

indicating that cracks were found in 

new locations at STA 1640 during frame 

segment replacement repairs, including 

in the web at the K-hole between 

stringer S–9 and S–10, in the outer 

chord above the lower hinge intercostal, 

and in the inner chord and web between 

S–10 and S–19. The existing inspection 

program for the STA 1640 frame is not 

sufficient to detect cracks in these 

locations because most of the frame is 

hidden by adjacent structure that makes 

the maintenance planning data (MPD) 

document inspections inadequate to 

detect cracks before they reach a critical 

size. Additionally, existing ADmandated inspections are at other 

locations. Undetected cracks in the 


ddrumheller on DSK120RN23PROD with PROPOSALS1