8870 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2024–26–07 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)): Amendment 39–22922; 

Docket No. FAA–2024–2133; Project 

Identifier MCAI–2024–00243–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 11, 2025. 

(b) Affected ADs 

None. 

(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)) airplanes specified in 

paragraphs (c)(1) and (2) of this AD, 

certificated in any category. 

(1) Model EMB–135ER, –135KE, –135KL, 

and –135LR airplanes. 

(2) Model EMB–145, –145EP, –145ER, 

–145LR, –145MP, –145MR, and –145XR 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a structural 

assessment that indicated certain central 

fuselage longitudinal splices are subjected to 

fatigue damage on multiple sites due to loose 

fasteners, which may reduce the structural 

residual strength below the required levels. 

The FAA is issuing this AD to address 

undetected fatigue damage on certain central 

fuselage longitudinal splices. The unsafe 

condition, if not addressed, could result in 

reduced structural integrity 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, Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC) AD 2024–04–03R01, 

effective May 31, 2024 (ANAC AD 2024–04– 

03R01). 

(h) Exceptions to ANAC AD 2024–04–03R01 

(1) Where ANAC AD 2024–04–03R01 refers 

to its effective date, this AD requires using 

the effective date of this AD. 

(2) Where paragraphs (b)(1) and (2) of 

ANAC AD 2024–04–03R01 specify the initial 

compliance time for the external detailed 

inspection, for this AD, the initial 

compliance time for doing the external 

detailed inspection is prior to the 

accumulation of 44,000 total flight cycles, or 

within 500 flight cycles after the effective 

date of this AD, whichever occurs later. 

(3) Where paragraph (b)(3) of ANAC AD 

2024–04–03R01 specifies ‘‘If any 

discrepancies are found, contact Embraer,’’ 

this AD requires replacing that text with ‘‘If 

any discrepancy (including cracking) is 

detected during an inspection required by 

paragraph (g) of this AD, repair the 

discrepancy (including cracking) before 

further flight using a method approved by the 

Manager, International Validation Branch, 

FAA; or ANAC; or Embraer’s ANAC Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature.’’ 

(4) Paragraph (d) of ANAC AD 2024–04– 

03R01 specifies to report inspection results to 

ANAC and Embraer within a certain 

compliance time. For this AD, report 

inspection results after each inspection 

required by paragraph (g) of this AD at the 

applicable times specified in paragraph 

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

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(5) This AD does not adopt paragraph (e) 

of ANAC AD 2024–04–03R01. 

(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, mail it to the address identified in 

paragraph (j) of this AD. Information may be 

emailed to: AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the 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 ANAC; or ANAC’s 

authorized Designee. If approved by the 

ANAC Designee, the approval must include 

the Designee’s authorized signature. 

(j) Additional Information 

For more information about this AD, 

contact Hassan Ibrahim, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: 206–231– 

3653; email: Hassan.M.Ibrahim@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 this AD specifies otherwise. 

(i) Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC) AD 2024–04–03R01, effective May 

31, 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 

ANAC AD 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 Street, 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 6, 2025. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–02144 Filed 2–3–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1299; Project 

Identifier MCAI–2023–00237–A; Amendment 

39–22925; AD 2025–01–01] 

RIN 2120–AA64 

Airworthiness Directives; BrittenNorman Aerospace Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Britten-Norman Aerospace Ltd. Model 

BN–2, BN–2A, BN–2A–2, BN–2A–3, 

BN–2A–6, BN–2A–8, BN–2A–9, BN– 

2A–20, BN–2A–21, BN–2A–26, BN–2A– 

27, BN–2B–20, BN–2B–21, BN–2B–26, 

BN–2B–27, BN–2T, BN2T–4R, and 

BN2T–4S airplanes; and certain Model 

BN2A MK. III, BN2A MK. III–2, and 

BN2A MK. III–3 airplanes. This AD was 

prompted by the determination that, in 

order to ensure the continued structural 

integrity of certain landing gear and 

associated components, it is necessary 

to require removal of these components 

from service prior to exceeding 

established fatigue lives. This AD 


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Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 8871 

requires determining the number of 

landings on affected main landing gears 

(MLGs), nose landing gears (NLGs), and 

associated components; removing from 

service any part that has reached or 

exceeded the established fatigue life and 

installing a replacement part; and 

prohibiting the installation of any 

affected part unless the number of 

landings for that part is below the 

established fatigue life. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 11, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 11, 2025. 

ADDRESSES:

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No.FAA–2024–1299; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, the mandatory 

continuing airworthiness information 

(MCAI), any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

Material Incorporated by Reference: 

• For Britten-Norman material 

identified in this AD, contact BrittenNorman Aerospace Ltd., Bembridge 

Airport, Bembridge, Isle of Wight, UK, 

PO35 5PR; phone: +44 20 3371 4000; 

email: customer.support@brittennorman.com; website: brittennorman.com/approvals-technicalpublications. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. It is also 

available at regulations.gov under 

Docket No. FAA–2024–1299. 

FOR FURTHER INFORMATION CONTACT: 

Beenal Desai, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (609) 485– 

9930; email: beenal.desai@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Britten-Norman Aerospace Ltd. 

Model BN–2, BN–2A, BN–2A–2, BN– 

2A–3, BN–2A–6, BN–2A–8, BN–2A–9, 

BN–2A–20, BN–2A–21, BN–2A–26, BN– 

2A–27, BN–2B–20, BN–2B–21, BN–2B– 

26, BN–2B–27, BN–2T, BN2T–4R, and 

BN2T–4S (Islander) airplanes; and 

Model BN2A MK. III, BN2A MK. III–2, 

and BN2A MK. III–3 (Trislander) 

airplanes, fitted with landing gear and 

associated components manufactured by 

Fairey Hydraulics Ltd (FHL) and 

Britten-Norman Aircraft (BNA). The 

NPRM published in the Federal 

Register on May 17, 2024 (89 FR 43342). 

The NPRM was prompted by AD G– 

2023–0001, dated February 8, 2023, 

issued by Civil Aviation Authority 

(CAA), which is the aviation authority 

for the United Kingdom (UK) (UK CAA 

AD G–2023–0001) (also referred to as 

the MCAI). The MCAI states that to 

ensure the continued safe operation of 

certain Islander’s and Trislander’s NLG, 

MLG, and associated components, the 

manufacturer and the UK CAA 

determined that affected parts exceeding 

the established fatigue lives must be 

removed from service and that 

installation of parts that have reached 

their established fatigue lives must be 

prohibited. 

In the NPRM, the FAA proposed to 

require determining the number of 

landings on affected MLGs, NLGs, and 

associated components; removing from 

service any part that has reached or 

exceeded the established fatigue life and 

installing a replacement part; and 

prohibiting the installation of any 

affected part unless the number of 

landings for that part is below the 

established fatigue life. The FAA is 

issuing this AD to address the unsafe 

condition on these products. Exceeding 

the established fatigue life, if not 

addressed, could result in failure of the 

structural integrity of the landing gear 

and associated components, which 

could result in damage to the airplane 

and injury to occupants. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–1299. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

one individual commenter. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Include a Method for 

Calculating Landings Per Flight Hour 

The commenter stated that in the 

United States landings are not required 

to be tracked on general aviation or 

commercial use non turbo prop 

airplanes. The commenter also 

mentioned that AD 2002–25–03, 

Amendment 39–12978 (67 FR 76106, 

December 11, 2002) provides a 

calculation of 3 landings per flight hour 

to calculate the number of landings, but 

this calculation is not realistic for all 

airplane operations and should be reevaluated. The commenter explained it 

is difficult to take off and land three 

times in an hour with taxi, loading, and 

unloading of passengers and cargo. The 

commenter stated that if a routine flight 

was 30 minutes to an hour, then 1 or 2 

landings for 1 flight hour should be 

considered by the FAA. The FAA infers 

that the commenter is requesting that 

the NPRM be revised to include a 

method for calculating landings per 

flight hour. 

The FAA partially agrees with the 

commenter’s request. The FAA 

acknowledges that landings are not 

required to be tracked on domestic 

general aviation airplanes. The 

compliance time for this AD is based on 

the number of landings because the 

affected MLGs, NLGs, and associated 

components that are showing fatigue are 

used during landing operations. 

The FAA revised paragraph (h)(1) of 

this AD to specify how to calculate for 

an unknown number of landings and 

requires using 3 landings per 1 hour 

time-in-service (TIS). The FAA 

disagrees with using the calculation of 

1 or 2 landings per 1 hour TIS because 

the 3 landings per 1 hour TIS 

calculation is a conservative estimate 

and has been used in previous ADs. The 

FAA received information from BrittenNorman that supported using a 

calculation of 3 landings per 1 hour TIS. 

In addition, Britten-Norman does not 

have any data to substantiate decreasing 

the number of landings to 1 or 2 

landings per 1 hour TIS. The FAA 

disagrees with referring to ‘‘flight 

hours’’ and is referring to TIS because 

‘‘flight hours’’ are not defined in FAA 

regulations but TIS is defined in FAA 

regulations and is used with respect to 

maintenance records. 

Request for Extension of Fatigue Life 

Landings by 30 Percent 

The commenter requested that the 

FAA allow a 30-percent increase of the 

fatigue life values specified in Tables 1, 

2, and 3 of Section 6 in Britten-Norman 

Service Bulletin SB 298, Issue 3, dated 

July 7, 2023 (Britten-Norman SB 298, 

Issue 3). The commenter stated that 

other countries allow the affected 

airplanes to operate with heavier gross 

weights than the United States allows, 

which reduces the fatigue lives of the 

affected components by shortening 

them. The commenter suggested a 

periodic eddy current inspection to 

determine the fatigue life value. 


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8872 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 

The FAA disagrees with both the 

commenter’s request for a 30-percent 

fatigue life value increase and the 

commenter’s suggestion to use a 

periodic eddy current inspection to 

determine the fatigue life value. The 

commenter did not provide 

substantiating data to support the 

requested changes. Britten-Norman 

provided the fatigue lives for the 

affected MLGs, NLGs, and associated 

components for the worldwide fleet 

based on its analysis of the unsafe 

condition and does not have data to 

substantiate increasing the fatigue life 

by 30-percent. The FAA agrees with this 

determination for airplanes on the U.S. 

registry. Operators may submit a 

proposal, with substantiating data, for 

revised requirements that affect the 

fatigue life value by requesting an 

alternative method of compliance 

(AMOC) using the procedures specified 

in paragraph (j) of this AD. 

The FAA has not changed this AD 

regarding this comment. 

Request for Compliance Time Based on 

Operating Environments and 

Conditions 

The commenter stated that operating 

environments and conditions should 

also be considered when establishing 

compliance times. The commenter 

explained that these are excellent cargo 

and passenger airplanes and are flown 

all over the world in remote places with 

short, unimproved runways of dirt and 

gravel. The commenter stated that these 

are extreme operating conditions that 

most airplanes do not encounter and the 

comparison between airplanes operated 

in the United States and airplanes 

operated in other countries are not 

equal. 

The FAA disagrees with the 

commenter’s request to change the 

compliance time based on airplane 

operating environments and conditions. 

There is no current requirement to track 

the hours spent flying in different 

conditions. Additionally, operators may 

not know an airplane’s entire flight or 

maintenance history. Without this 

detailed knowledge of each airplane, it 

would be impossible for the FAA to 

develop a special set of inspections 

based on airplane operating 

environments and conditions. However, 

operators may submit a proposal, with 

substantiating data, for revised 

requirements by requesting an AMOC 

using the procedures specified in 

paragraph (j) of this AD. 

The FAA has not changed this AD 

regarding this comment. 

Request To Allow Continued Use of 

Parts That Exceed Fatigue Life Until 

Replacement Parts Are Available 

The commenter requested that the 

MLG, NLG, and associated components 

that exceed the fatigue lives specified in 

in Tables 1, 2, and 3 of Section 6 in 

Britten-Norman SB 298, Issue 3, be 

allowed to continue to be used in 

service until replacement parts are 

available. The commenter referred to 

paragraph 2, ‘‘Corrective Action,’’ of UK 

CAA AD G–2023–0001, which states 

‘‘Any main or nose landing gear or 

component which exceed the fatigue life 

stated in Tables 1, 2 or 3 must be 

withdrawn from service immediately.’’ 

The commenter stated that if 

replacement parts are not available then 

the proposed AD would not only ground 

the fleet but close businesses that rely 

on these airplanes. 

The FAA disagrees with allowing 

parts that exceed the fatigue life to be 

allowed in-service until replacement 

parts are available. While the FAA 

acknowledges the commenter’s concern 

regarding immediately removing parts 

that exceed the specified fatigue lives 

from service, this AD does not require 

immediately removing from service 

affected parts that exceed the specified 

fatigue lives. Paragraph (h)(2) of this AD 

provides a grace period of 30 days after 

the effective date of this AD for 

replacing affected parts that exceed the 

specified fatigue lives. Britten-Norman 

has confirmed that the landing gear is 

still in production and spares are 

available. To the extent replacement 

parts may not be available, the FAA 

cannot base its AD action on whether 

replacement parts are available or can 

be produced. While every effort is made 

to avoid grounding airplanes, the FAA 

must address the unsafe condition. 

Operators may submit a proposal for 

revised requirements, with 

substantiating data, by requesting an 

AMOC using the procedures specified 

in paragraph (j) of this AD. 

The FAA has not changed this AD 

regarding this comment. 

Conclusion 

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 referenced 

above. The FAA reviewed the relevant 

data, considered the comments 

received, and determined that air safety 

requires adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes and any changes described 

previously, this AD is adopted as 

proposed in the NPRM. None of the 

changes increase the economic burden 

on any operator. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed Britten-Norman 

SB 298, Issue 3. This material provides 

procedures for identifying the affected 

MLGs, NLGs, and associated 

components that need to have the 

number of landings tracked and 

provides the associated fatigue life. This 

material also specifies to remove from 

service any affected part that exceeds 

the specified fatigue life. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 87 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Determine the number of landings accumulated on affected MLGs, NLGs, and associated components.1 work-hour × $85 per hour 

= $85.

$0 $85 ................... $7,395. 

Replace MLG ....................................................................... 16 work-hours × $85 per 

hour = $1,360.

30,000 31,360 .............. 2,728,320. 

Replace NLG ....................................................................... 16 work-hours × $85 per 

hour = $1,360.

35,000 36,360 .............. 3,163,320. 


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Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 8873 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replace associated components ........................................ Up to 4 work-hours × $85 

per hour = $340.

4,000 Up to 4,340 ...... Up to 377,580. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will 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 Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2025–01–01 Britten-Norman Aerospace 

Ltd.: Amendment 39–22925; Docket No. 

FAA–2024–1299; Project Identifier 

MCAI–2023–00237–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 11, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Britten-Norman 

Aerospace Ltd. airplanes, certificated in any 

category, fitted with Fairey Hydraulics Ltd or 

Britten-Norman Aircraft landing gear and 

associated landing gear components, 

identified in paragraphs (c)(1) and (2) of this 

AD. 

(1) Model BN–2, BN–2A, BN–2A–2, BN– 

2A–3, BN–2A–6, BN–2A–8, BN–2A–9, BN– 

2A–20, BN–2A–21, BN–2A–26, BN–2A–27, 

BN–2B–20, BN–2B–21, BN–2B–26, BN–2B– 

27, BN–2T, BN2T–4R, and BN2T–4S 

airplanes. 

(2) Model BN2A MK. III, BN2A MK. III–2, 

and BN2A MK. III–3 airplanes. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 3200, Landing Gear System. 

(e) Unsafe Condition 

This AD was prompted by the 

determination that in order to ensure the 

continued structural integrity of certain 

landing gear and associated components, it is 

necessary to require removal of these 

components from service prior to exceeding 

established fatigue lives. Exceeding the 

established fatigue life, if not addressed, 

could result in failure of the structural 

integrity of the landing gear and associated 

components, which could result in damage to 

the airplane and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definitions 

For the purpose of this AD: 

(1) An ‘‘affected part’’ is a main landing 

gear (MLG), nose landing gear (NLG), or 

component identified in Table 1, 2, or 3 of 

Section 6 in Britten-Norman SB 298, Issue 3, 

dated July 7, 2023 (Britten-Norman SB 298, 

Issue 3). 

(2) A ‘‘part eligible for installation’’ is an 

MLG, NLG, or component with a part that 

has been established to be below the 

associated fatigue life identified in Table 1, 

2, or 3 of Section 6 in Britten-Norman SB 

298, Issue 3. 

(h) Required Actions 

(1) Within 30 days after the effective date 

of this AD, determine the number of landings 

accumulated on the affected parts. For an 

unknown number of landings, calculate the 

number based on 3 landings per 1 hour timein-service. 

(2) Before accumulating the number of 

landings (fatigue life) associated with the 

applicable affected part as identified in Table 

1, 2, or 3 of Section 6 in Britten-Norman SB 

298, Issue 3, or within the next 30 days after 

the effective date of this AD, whichever 

occurs later, replace any affected part with a 

part eligible for installation. 

(3) Thereafter, replace any affected part 

with a part eligible for installation before 

accumulating the fatigue life, as identified in 

Table 1, 2, or 3 of Section 6 in BrittenNorman SB 298, Issue 3. 

(i) Parts Installation Limitation 

As of the effective date of this AD, do not 

install a MLG, NLG, or associated component 

unless it is a part eligible for installation. 

(j) 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, send it to the attention of the person 

identified in paragraph (k) 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. 

(k) Additional Information 

For more information about this AD, 

contact Beenal Desai, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (609) 485– 

9930; email: beenal.desai@faa.gov. 


lotter on DSK11XQN23PROD with RULES1
8874 Federal Register / Vol. 90, No. 22 / Tuesday, February 4, 2025 / Rules and Regulations 

(l) 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 the AD specifies otherwise. 

(i) Britten-Norman Service Bulletin SB 298, 

Issue 3, dated July 7, 2023. 

(ii) [Reserved] 

(3) For Britten-Norman material identified 

in this AD, contact Britten-Norman 

Aerospace Ltd., Bembridge Airport, 

Bembridge, Isle of Wight, UK, PO35 5PR; 

phone: +44 20 3371 4000; email: 

customer.support@britten-norman.com; 

website: britten-norman.com/approvalstechnical-publications. 

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

Airworthiness Products Section, Operational 

Safety Branch, 901 Locust, Kansas City, MO 

64106. For information on the availability of 

this material at the FAA, call (817) 222–5110. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

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

Issued on January 2, 2025. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02187 Filed 2–3–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2025–0017; Project 

Identifier MCAI–2024–00706–R; Amendment 

39–22951; AD 2025–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Leonardo S.p.a. Model A109E, A109K2, 

A109S, AB412, AB412 EP, AB139, and 

AW139 helicopters. This AD was 

prompted by a report that certain rescue 

hoist cable assemblies may be equipped 

with a defective ball end. This AD 

requires inspecting certain rescue hoist 

cable assemblies and, depending on the 

results, replacing the rescue hoist cable 

assembly. This AD also allows installing 

certain rescue hoist cable assemblies 

and certain rescue hoists provided its 

requirements are met. These actions are 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 19, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 19, 2025. 

The FAA must receive comments on 

this AD by March 21, 2025. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

regulations.gov. Follow the instructions 

for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2025–0017; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, 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 

AD, contact EASA, Konrad-AdenauerUfer 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 

Parkway, 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–2025–0017. 

FOR FURTHER INFORMATION CONTACT: Eric 

Rivera, Aviation Safety Engineer, FAA, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (847) 294– 

7166; email: eric.rivera01@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2025–0017; Project Identifier MCAI– 

2024–00706–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the final 

rule, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this final rule 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this final rule. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

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

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Eric Rivera, Aviation 

Safety Engineer, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; phone: (847) 294–7166; email: 

eric.rivera01@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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2024–0228, 

dated November 29, 2024 (EASA AD 

2024–0228) (also referred to as the 

MCAI), to correct an unsafe condition 

on Leonardo S.p.A. Model AB412, 

AB412EP, A109E, A109K2, A109S, 

AB139, and AW139 helicopters. The 


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