104462 Federal Register / Vol. 89, No. 246 / Monday, December 23, 2024 / Proposed Rules 

Deutsche Aircraft GmbH (Type Certificate 

Previously Held by 328 Support Services 

GmbH; AvCraft Aerospace GmbH; 

Fairchild Dornier GmbH; Dornier 

Luftfahrt GmbH): Docket No. FAA– 

2024–2667; Project Identifier MCAI– 

2024–00473–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by February 6, 

2025. 

(b) Affected ADs 

This AD replaces AD 2024–03–07, 

Amendment 39–22677 (89 FR 17723, March 

12, 2024) (AD 2024–03–07). 

(c) Applicability 

This AD applies to all Deutsche Aircraft 

GmbH Model 328–100 and 328–300 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by operator reports 

of worn and ruptured bonding straps inside 

the feeder wing tanks and in both outer and 

inner wing tanks. The FAA is issuing this AD 

to address damaged bonding straps. The 

unsafe condition, if not addressed, could 

result in the loss of bonding function and, in 

combination with a lightning strike, create a 

source of ignition in a fuel tank, possibly 

resulting in a fire or explosion and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2024–0154, dated 

August 2, 2024 (EASA AD 2024–0154). 

(h) Exceptions to EASA AD 2024–0154 

(1) Where EASA AD 2024–0154 refers to 

July 26, 2023 (the effective date of EASA AD 

2023–0137), this AD requires using April 16, 

2024 (the effective date of AD 2024–03–07). 

(2) Where EASA AD 2024–0154 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

section of EASA AD 2024–0154. 

(4) Where paragraph (3) of EASA AD 2024– 

0154 specifies if ‘‘any damage is detected as 

defined in the inspection ASB,’’ this AD 

requires replacing those words with ‘‘any 

worn or ruptured bonding strap is detected.’’ 

(5) Where paragraph (4) of EASA AD 2024– 

0154 specifies ‘‘Modification of an aeroplane 

in accordance with the instructions of the 

modification SB,’’ this AD requires replacing 

those words with ‘‘Accomplishing a 

modification, including doing detailed 

inspections, of an airplane in accordance 

with the instructions of the modification SB, 

and doing corrective actions if any worn or 

ruptured bonding strap is detected as 

specified in paragraph (3).’’ 

(i) 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 (j) 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. 

(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 EASA; or Deutsche Aircraft 

GmbH’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(j) Additional Information 

For more information about this AD, 

contact Joe Salameh, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3536; email joe.salameh@faa.gov. 

(k) 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) European Union Aviation Safety Agency 

(EASA) AD 2024–0154, dated August 2, 

2024. 

(ii) [Reserved] 

(3) For EASA material identified in this 

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

50668 Cologne, Germany; telephone +49 221 

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

website easa.europa.eu. You may find this 

material on the EASA website at 

ad.easa.europa.eu. 

(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-locationsoremailfr.inspection@nara.gov. 

Issued on December 17, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–30549 Filed 12–20–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2668; Project 

Identifier AD–2024–00561–E] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2023–09–06, which applies to all CFM 

International, S.A. Model (CFM) LEAP– 

1A23, LEAP–1A24, LEAP–1A24E1, 

LEAP–1A26, LEAP–1A26CJ, LEAP– 

1A26E1, LEAP–1A29, LEAP–1A29CJ, 

LEAP–1A30, LEAP–1A32, LEAP–1A33, 

LEAP–1A33B2, and LEAP–1A35A 

(LEAP–1A) engines. AD 2023–09–06 

requires replacement of certain highpressure turbine (HPT) rotor stage 1 

disks (HPT stage 1 disks), forward outer 

seals, and compressor rotor stages 6–10 

spools. AD 2023–09–06 also prohibits 

installation of an HPT stage 1 disk, 

forward outer seal, or compressor rotor 

stages 6–10 spool that has a part number 

and serial number identified in the 

service information onto any engine. 

Since the FAA issued AD 2023–09–06, 

the manufacturer identified additional 

affected parts that were manufactured 

from material suspected to have reduced 

material properties due to iron 

inclusion, which prompted this AD. 

This proposed AD would retain the 

requirements to replace certain HPT 

stage 1 disks, forward outer seals, and 

compressor rotor stages 6–10 spools and 

expand the applicability to include 

additional affected parts manufactured 

from the same material suspected to 

have reduced material properties due to 

iron inclusion. 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 February 6, 

2025. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 


khammond on DSK9W7S144PROD with PROPOSALS
Federal Register / Vol. 89, No. 246 / Monday, December 23, 2024 / Proposed Rules 104463 

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–2024–2668; 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 CFM material identified in this 

proposed AD, contact CFM, GE Aviation 

Fleet Support, 1 Neumann Way, M/D 

Room 285, Cincinnati, OH 45215; 

phone: (877) 432–3272; email: 

aviation.fleetsupport@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: 

Mehdi Lamnyi, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, 

Des Moines, WA 98198; phone: (781) 

238–7743; email: mehdi.lamnyi@

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–2024–2668; Project 

Identifier AD–2024–00561–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 Mehdi Lamnyi, 

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 issued AD 2023–09–06, 

Amendment 39–22429 (88 FR 32092, 

May 19, 2023) (AD 2023–09–06), for all 

CFM Model LEAP–1A engines. AD 

2023–09–06 was prompted by a 

manufacturer investigation that revealed 

that certain HPT stage 1 disks, forward 

outer seals, and compressor rotor stages 

6–10 spools were manufactured from 

material suspected to have reduced 

material properties due to iron 

inclusion. AD 2023–09–06 requires 

replacement of certain HPT stage 1 

disks, forward outer seals, and 

compressor rotor stages 6–10 spools. 

The agency issued AD 2023–09–06 to 

prevent fracture and consequent 

uncontained failure of certain HPT stage 

1 disks, forward outer seals, and 

compressor rotor stages 6–10 spools. 

Actions Since AD 2023–09–06 Was 

Issued 

Since the FAA issued AD 2023–09– 

06, further analysis by the manufacturer 

identified additional affected parts that 

were manufactured from material 

suspected to have reduced material 

properties due to iron inclusion. This 

condition, 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 CFM Service 

Bulletin LEAP–1A–72–00–0507–01A– 

930A–D, Issue 001, dated January 24, 

2024, which identifies the part numbers 

and serial numbers of HPT stage 1 disks, 

forward outer seals, and compressor 

rotor stages 6–10 spools with potentially 

reduced material properties and 

specifies procedures for replacement of 

these parts. 

This proposed AD would also require 

the following material, which the 

Director of the Federal Register 

approved for incorporation by reference 

as of June 23, 2023 (88 FR 32092, May 

19, 2023): 

• CFM Service Bulletin LEAP–1A– 

72–00–0470–01A–930A–D, Issue 003, 

dated March 3, 2023. 

• CFM Service Bulletin LEAP–1A– 

72–00–0493–01A–930A–D, Issue 002, 

dated November 17, 2022. 

• CFM Service Bulletin LEAP–1A– 

72–00–0496–01A–930A–D, Issue 001, 

dated March 7, 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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain all of 

the requirements of AD 2023–09–06. 

This proposed AD would require 

replacement of certain HPT stage 1 

disks, forward outer seals, and 

compressor rotor stages 6–10 spools. 

This proposed AD would also prohibit 

installation of an HPT stage 1 disk, 

forward outer seal, or compressor rotor 

stages 6–10 spool that has a part number 

and serial number identified in the 

material incorporated by reference onto 

any engine. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 42 

engines installed on airplanes of U.S. 

registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 


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104464 Federal Register / Vol. 89, No. 246 / Monday, December 23, 2024 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace HPT stage 1 disk (42 affected parts).8 work-hours × $85 per hour = 

$680.

$215,635 (pro-rated) ...................... $216,315 $9,085,230 

Replace forward outer seal (24 affected parts).8 work-hours × $85 per hour = 

$680.

$47,500 (pro-rated) ........................ 48,180 1,156,320 

Replace compressor rotor stages 

6–10 spool (15 affected parts).

8 work-hours × $85 per hour = 

$680.

$37,660 (pro-rated) ........................ 38,340 575,100 

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 

2023–09–06, Amendment 39–22429 (88 

FR 32092, May 19, 2023); and 

■ b. Adding the following new 

airworthiness directive: 

CFM International, S.A.: Docket No. FAA– 

2024–2668; Project Identifier AD–2024– 

00561–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by February 6, 

2025. 

(b) Affected ADs 

This AD replaces AD 2023–09–06, 

Amendment 39–22429 (88 FR 32092, May 19, 

2023) (AD 2023–09–06). 

(c) Applicability 

This AD applies to CFM International, S.A. 

Model (CFM) LEAP–1A23, LEAP–1A24, 

LEAP–1A24E1, LEAP–1A26, LEAP–1A26CJ, 

LEAP–1A26E1, LEAP–1A29, LEAP–1A29CJ, 

LEAP–1A30, LEAP–1A32, LEAP–1A33, 

LEAP–1A33B2, and LEAP–1A35A engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section; 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by a manufacturer 

investigation that revealed that certain highpressure turbine (HPT) rotor stage 1 disks 

(HPT stage 1 disks), forward outer seals, and 

compressor rotor stages 6–10 spools were 

manufactured from material suspected to 

have reduced material properties due to iron 

inclusion. The FAA is issuing this AD to 

prevent fracture and consequent uncontained 

failure of certain HPT stage 1 disks, forward 

outer seals, and compressor rotor stages 6–10 

spools. 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 

(1) For engines with an installed HPT stage 

1 disk, forward outer seal or compressor rotor 

stages 6–10 spool having a part number (P/ 

N) and serial number (S/N) identified in 

Compliance, paragraph 3.E., Tables 1 through 

9, of CFM Service Bulletin (SB) LEAP–1A– 

72–00–0496–01A–930A–D, Issue 001, dated 

March 7, 2023 (CFM SB LEAP–1A–72–00– 

0496–01A–930A–D): At the next piece-part 

exposure of the HPT stage 1 disk, forward 

outer seal, or compressor rotor stages 6–10 

spool, as applicable, or before exceeding the 

applicable cycles since new (CSN) threshold 

identified in Compliance, paragraph 3.E., 

Tables 1 through 9, of CFM SB LEAP–1A– 

72–00–0496–01A–930A–D, whichever occurs 

first after June 23, 2023 (the effective date of 

AD 2023–09–06); or if the applicable CSN 

threshold has been exceeded as of June 23, 

2023 (the effective date of AD 2023–09–06), 

within 50 flight cycles (FCs) from June 23, 

2023 (the effective date of AD 2023–09–06); 

remove the HPT stage 1 disk, forward outer 

seal, or compressor rotor stages 6–10 spool, 

as applicable, from service and replace with 

a part eligible for installation. 

(2) For engines with an installed forward 

outer seal having a P/N and S/N identified 

in Compliance, paragraph 3.E., Tables 1 

through 2, of CFM SB LEAP–1A–72–00– 

0470–01A–930A–D, Issue 003, dated March 

3, 2023 (CFM SB LEAP–1A–72–00–0470– 

01A–930A–D): At the next piece-part 

exposure of the forward outer seal, or before 

exceeding the applicable CSN threshold 

identified in Compliance, paragraph 3.E., 

Tables 1 through 2, of CFM SB LEAP–1A– 

72–00–0470–01A–930A–D, whichever occurs 

first after June 23, 2023 (the effective date of 

AD 2023–09–06); or if the applicable CSN 

threshold has been exceeded as of June 23, 

2023 (the effective date of AD 2023–09–06), 

within 50 FCs from June 23, 2023 (the 

effective date of AD 2023–09–06); remove the 

forward outer seal from service and replace 

with a part eligible for installation. 

(3) For engines with an installed HPT stage 

1 disk having a P/N and S/N identified in 

Compliance, paragraph 3.E., Tables 1 through 

2, of CFM SB LEAP–1A–72–00–0493–01A– 

930A–D, Issue 002, dated November 17, 2022 

(CFM SB LEAP–1A–72–00–0493–01A–930A– 

D): At the next piece-part exposure of the 

HPT stage 1 disk, or before exceeding the 

applicable CSN threshold identified in 

Compliance, paragraph 3.E., Tables 1 through 


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Federal Register / Vol. 89, No. 246 / Monday, December 23, 2024 / Proposed Rules 104465 

2, of CFM SB LEAP–1A–72–00–0493–01A– 

930A–D, whichever occurs first after June 23, 

2023 (the effective date of AD 2023–09–06); 

or if the applicable CSN threshold has been 

exceeded as of June 23, 2023 (the effective 

date of AD 2023–09–06), within 50 FCs from 

June 23, 2023 (the effective date of AD 2023– 

09–06), remove the HPT stage 1 disk from 

service and replace with a part eligible for 

installation. 

(4) For engines with an installed HPT stage 

1 disk having a P/N and S/N identified in 

Compliance, paragraph 3.E., Tables 1 through 

2, of CFM SB LEAP–1A–72–00–0507–01A– 

930A–D, Issue 001, dated January 24, 2024 

(CFM SB LEAP–1A–72–00–0507–01A–930A– 

D): At the next piece-part exposure of the 

HPT stage 1 disk, or before exceeding the 

applicable CSN threshold identified in 

Compliance, paragraph 3.E., Tables 1 through 

2, of CFM SB LEAP–1A–72–00–0507–01A– 

930A–D, whichever occurs first after the 

effective date of this AD; or if the applicable 

CSN threshold has been exceeded as of the 

effective date of this AD, within 50 FCs from 

the effective date of this AD; remove the HPT 

stage 1 disk from service and replace with a 

part eligible for installation. 

(h) Definition 

For the purpose of this AD, a ‘‘part eligible 

for installation’’ is an HPT stage 1 disk, 

forward outer seal, or compressor rotor stages 

6–10 spool that does not have a P/N and S/ 

N identified in the service information listed 

in paragraphs (g)(1) through (4) of this AD. 

(i) Installation Prohibition 

After the effective date of this AD, do not 

install an HPT stage 1 disk, forward outer 

seal, or compressor rotor stages 6–10 spool 

that has a P/N and S/N identified in the 

service information listed in paragraphs (g)(1) 

through (4) of this AD on any engine. 

(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 Mehdi Lamnyi, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: (781) 238–7743; 

email: mehdi.lamnyi@faa.gov. 

(l) 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 [DATE 35 DAYS AFTER 

PUBLICATION OF THE FINAL RULE]. 

(i) CFM Service Bulletin LEAP–1A–72–00– 

0507–01A–930A–D, Issue 001, dated January 

24, 2024. 

(ii) [Reserved] 

(4) The following material was approved 

for IBR on June 23, 2023 (88 FR 32092, May 

19, 2023). 

(i) CFM Service Bulletin LEAP–1A–72–00– 

0470–01A–930A–D, Issue 003, dated March 

3, 2023. 

(ii) CFM Service Bulletin LEAP–1A–72– 

00–0493–01A–930A–D, Issue 002, dated 

November 17, 2022. 

(iii) CFM Service Bulletin LEAP–1A–72– 

00–0496–01A–930A–D, Issue 001, dated 

March 7, 2023. 

(5) For CFM material identified in this AD, 

contact CFM International, S.A., GE Aviation 

Fleet Support, 1 Neumann Way, M/D Room 

285, Cincinnati, OH 45215; phone: (877) 

432–3272; email: aviation.fleetsupport@

ge.com. 

(6) 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. 

(7) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

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

Issued on December 17, 2024. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–30539 Filed 12–20–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2663; Project 

Identifier MCAI–2023–00200–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

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 Airbus Helicopters Model 

EC225LP helicopters. This proposed AD 

was prompted by the identification of 

missing electrical bonding on a certain 

part-numbered additional and optional 

search light (search light). This 

proposed AD would require installing 

an electrical bonding braid modification 

and prohibit installing that partnumbered search light unless the 

modification is done. These actions are 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

proposed for incorporation by reference. 

The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this NPRM by February 6, 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–2024–2663; 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 EASA material identified in this 

proposed AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; phone: +49 221 8999 000; 

email: ADs@easa.europa.eu; website: 

easa.europa.eu. You may find the EASA 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N 321, Fort Worth, TX 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. It is also available 

at regulations.gov under Docket No. 

FAA–2024–2663. 

FOR FURTHER INFORMATION CONTACT: Kurt 

Ladendorf, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (817) 222– 

5254; email: Kurt.D.Ladendorf@faa.gov. 


khammond on DSK9W7S144PROD with PROPOSALS