Federal Register / Vol. 90, No. 1 / Thursday, January 2, 2025 / Rules and Regulations 17 

AD requires replacing that text with ‘‘use a 

permanent marker.’’ 

(4) Where paragraph (3) of EASA 

Emergency AD 2024–0237–E states 

‘‘discrepancy,’’ for the purpose of this AD, a 

‘‘discrepancy’’ is defined as the lines on the 

piston rod and the bolt do not stay aligned 

to each other while rotating the tail rotor 

actuator, or the line is not aligned on the 

piston rod, the cardan-pivot joint assembly, 

the lever assembly, and the bolt after 

connecting the tail rotor actuator upper 

control rod and the bellcrank. 

(5) Where paragraph (3) of EASA 

Emergency AD 2024–0237–E states to 

‘‘contact AH for applicable repair 

instructions and, within the compliance time 

specified in those instructions, accomplish 

those instructions accordingly,’’ this AD 

requires replacing that text with ‘‘accomplish 

corrective action in accordance with a 

method approved by the Manager, 

International Validation Branch, FAA; or 

EASA; or Airbus Helicopters Deutschland 

GmbH’s EASA Design Organization Approval 

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

must include the DOA-authorized signature.’’ 

(6) Where paragraphs (4) and (5) of EASA 

Emergency AD 2024–0237–E specify 

accomplishing corrective actions, this AD 

requires accomplishing corrective actions in 

accordance with a method approved by the 

Manager, International Validation Branch, 

FAA; or EASA; or Airbus Helicopters 

Deutschland GmbH’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

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

section of EASA Emergency AD 2024–0237– 

E. 

(i) No Reporting Requirement 

Although the material referenced in EASA 

Emergency AD 2024–0237–E specifies to 

submit certain information to the 

manufacturer, this AD does not require that 

action. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 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 Tara Lucas, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (206) 231–3189; 

email: Tara.Lucas@faa.gov. 

(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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) Emergency AD 2024–0237–E, dated 

December 9, 2024. 

(ii) [Reserved] 

(3) For EASA material identified in this 

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

50668 Cologne, Germany; phone: +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, 

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. 

(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 December 17, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–31500 Filed 12–30–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2719; Project 

Identifier MCAI–2024–00664–R; Amendment 

39–22923; AD 2024–26–08] 

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 AB139 and 

AW139 helicopters. This AD was 

prompted by reports of broken main 

landing gear (MLG) shock absorber 

piston rod eye ends. This AD requires 

repetitively inspecting the MLG shock 

absorber piston rod eye ends, reporting 

the results of the inspection, and, 

depending on the results, replacing the 

MLG shock absorber assembly. It also 

prohibits installing certain MLG shock 

absorber assemblies unless specific 

requirements are met, as 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 January 17, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 17, 2025. 

The FAA must receive comments on 

this AD by February 18, 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–2024–2719; 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–2024–2719. 

FOR FURTHER INFORMATION CONTACT: 

Adam Hein, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (316) 946– 

4116; email: Adam.Hein@faa.gov. 

SUPPLEMENTARY INFORMATION: 


ddrumheller on DSK120RN23PROD with RULES1
18 Federal Register / Vol. 90, No. 1 / Thursday, January 2, 2025 / Rules and Regulations 

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– 

2024–2719; Project Identifier MCAI– 

2024–00664–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 Adam Hein, Aviation 

Safety Engineer, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued a series of ADs, the 

most recent being EASA Emergency AD 

2024–0211–E, dated November 7, 2024 

(EASA Emergency AD 2024–0211–E) 

(also referred to as the MCAI), to correct 

an unsafe condition on all Leonardo 

S.p.a. Model AB139 and AW139 

helicopters. The MCAI states that there 

have been reports of broken MLG shock 

absorber piston rod eye ends and the 

consequent investigation determined 

that the cause was fatigue cracking. The 

FAA is issuing this AD to address 

fatigue cracking of the MLG shock 

absorber piston rod eye ends. The 

unsafe condition, if not detected and 

corrected, could result in structural 

failure of the MLG possibly resulting in 

damage to the helicopter and injury to 

occupants. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2719. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed EASA Emergency 

AD 2024–0211–E, which requires 

repetitive ultrasonic inspections of the 

piston rod eye ends of MLG shock 

absorber assembly having part number 

(P/N) 3G3210V00333 or P/N 

3G3210V01031 (vendor P/N 

1654B0000–01 or P/N 1654C0000–01 

respectively) and, depending on 

findings, replacing the MLG shock 

absorber assembly. EASA Emergency 

AD 2024–0211–E also requires reporting 

the inspection results to Leonardo. 

Lastly, EASA Emergency AD 2024– 

0211–E prohibits installing an affected 

MLG shock absorber assembly on any 

helicopter unless its requirements are 

met. 

This material is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI referenced 

above. The FAA is issuing this AD after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the MCAI, described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this AD. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, EASA Emergency AD 

2024–0211–E is incorporated by 

reference in this AD. This AD requires 

compliance with EASA Emergency AD 

2024–0211–E in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this AD. Using 

common terms that are the same as the 

heading of a particular section in EASA 

Emergency AD 2024–0211–E does not 

mean that operators need comply only 

with that section. For example, where 

the AD requirement refers to ‘‘all 

required actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA Emergency AD 2024– 

0211–E. Material required by EASA 

Emergency AD 2024–0211–E for 

compliance will be available at 

regulations.gov under Docket No. FAA– 

2024–2719 after this AD is published. 

Interim Action 

The FAA considers that this AD is an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking then. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b) of the Administrative 

Procedure Act (APA) (5 U.S.C. 551 et 

seq.) authorizes agencies to dispense 

with notice and comment procedures 

for rules when the agency, for ‘‘good 

cause,’’ finds that those procedures are 

‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

providing notice and seeking comment 

prior to issuance. Further, section 

553(d) of the APA authorizes agencies to 

make rules effective in less than thirty 

days, upon a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies forgoing notice 

and comment prior to adoption of this 

rule because the MLG shock absorber 

assembly is part of an assembly that is 

critical to the control of a helicopter 

during landings, which is a critical 

phase of flight. The FAA has no 

information pertaining to the extent of 

fatigue damage in MLG shock absorber 

piston rod eye ends that may currently 

exist in helicopters or how quickly the 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 90, No. 1 / Thursday, January 2, 2025 / Rules and Regulations 19 

condition may propagate to failure, 

therefore, the initial instance of the 

inspections must be accomplished 

within 10 to 100 hours time-in-service, 

a time period of approximately 10 days 

to three months based on the average 

flight-hour utilization rates of these 

helicopters. Accordingly, notice and 

opportunity for prior public comment 

are impracticable and contrary to the 

public interest pursuant to 5 U.S.C. 

553(b). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forgo 

notice and comment. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because the 

FAA has determined that it has good 

cause to adopt this rule without prior 

notice and comment, RFA analysis is 

not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 144 helicopters of U.S. registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Inspecting the MLG shock absorber 

piston rod takes 1 work-hour for a cost 

of $85 per helicopter and $12,240 for 

the U.S. fleet, per inspection cycle. 

Reporting the results takes 1 work-hour 

for a cost of $85 per helicopter and 

$12,240 for the U.S. fleet, per inspection 

cycle. 

If required, replacing a MLG shock 

absorber assembly takes 20 work-hours 

and parts cost up to $39,105 for a cost 

of up to $40,805 per assembly. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to take 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden, to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

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: 

2024–26–08 Leonardo S.p.a. Helicopters: 

Amendment 39–22923; Docket No. 

FAA–2024–2719; Project Identifier 

MCAI–2024–00664–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 17, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Leonardo S.p.a. Model 

AB139 and AW139 helicopters, certificated 

in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 3210, Main Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by reports of 

broken main landing gear (MLG) shock 

absorber piston rod eye ends. The FAA is 

issuing this AD to address fatigue cracking of 

the MLG shock absorber piston rod eye ends. 

The unsafe condition, if not addressed, could 

result in structural failure of the MLG and 

consequent damage to the helicopter and 

injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition 

For the purpose of this AD, a landing is 

counted anytime the helicopter lifts off into 

the air and then lands again regardless of the 

duration of the landing and regardless of 

whether the engine is shutdown. 

(h) Requirements 

Except as specified in paragraph (i) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with European Union Aviation 

Safety Agency Emergency AD 2024–0211–E, 

dated November 7, 2024 (EASA Emergency 

AD 2024–0211–E). 

(i) Exceptions to EASA Emergency AD 2024– 

0211–E 

(1) Where EASA Emergency AD 2024– 

0211–E requires compliance in terms of flight 

hours, this AD requires using hours time-inservice. 

(2) Where EASA Emergency AD 2024– 

0211–E refers to its effective date, this AD 

requires using the effective date of this AD. 


ddrumheller on DSK120RN23PROD with RULES1
20 Federal Register / Vol. 90, No. 1 / Thursday, January 2, 2025 / Rules and Regulations 

(3) Where Note 2 of EASA Emergency AD 

2024–0211–E specifies procedures for 

calculating the number of landings if the 

number of landings since new is not known: 

if the ‘‘FH’’ (total hours time-in-service) 

accumulated on the affected part, as defined 

in EASA Emergency AD 2024–0211–E, 

cannot be determined, this AD requires using 

the total hours-time-in-service on the 

helicopter for that calculation. 

(4) Where paragraph (1) of EASA 

Emergency AD 2024–0211–E specifies 

accomplishing special detailed inspections 

(SDIs), this AD requires the landing gear in 

the fully extended position for the SDIs. 

(5) Where paragraph (1) of EASA 

Emergency AD 2024–0211–E specifies 

accomplishing SDIs and the material 

referenced in EASA Emergency AD 2024– 

0211–E specifies that the ultrasonic testing 

inspections must be performed by personnel 

qualified in accordance with the nondestructive testing requirements of EN4179/ 

NAS410 for Level II or higher, or of an 

equivalent standard recognized by the 

competent authority, this AD requires the 

ultrasonic testing inspections be 

accomplished by a Level II or Level III 

inspector certified in the FAA-acceptable 

standards for nondestructive inspection 

personnel. 

Note 1 to paragraph (i)(5): Advisory 

Circular 65–31B contains examples of FAAacceptable Level II and Level III qualification 

standards criteria for inspection personnel 

doing nondestructive test inspections. 

(6) Where paragraph (2) of EASA 

Emergency AD 2024–0211–E states 

‘‘discrepancies, as identified in the EASB, 

are,’’ this AD requires replacing that text with 

‘‘a cracked or broken piston rod eye end, or 

an ultrasonic testing inspection indication 

equal to or greater than 80% full screen 

height (FSH) within the recording gate, as 

defined in the material referenced in EASA 

Emergency AD 2024–0211–E, of an upper or 

lower piston rod eye end, is.’’ 

(7) Where the material referenced in EASA 

Emergency AD 2024–0211–E specifies 

sending parts to Leonardo Helicopters [LH], 

this AD does not require that action. 

(8) Where paragraph (3) of EASA 

Emergency AD 2024–0211–E allows credit 

for the initial instance of the (ultrasonic 

testing) inspection required by paragraph (1) 

of EASA Emergency AD 2024–0211–E, this 

AD allows that credit if the ultrasonic testing 

inspection that was previously done was 

accomplished by a Level II or Level III 

inspector certified in the FAA-acceptable 

standards for nondestructive inspection 

personnel. 

Note 2 to paragraph (i)(8): Advisory 

Circular 65–31B contains examples of FAAacceptable Level II and Level III qualification 

standards criteria for inspection personnel 

doing nondestructive test inspections. 

(9) Where paragraph (5) of EASA 

Emergency AD 2024–0211–E specifies 

reporting inspection results to Leonardo 

within 10 days after accomplishment of any 

inspection required by paragraph (1) of EASA 

Emergency AD 2024–0211–E, this AD 

requires reporting inspection results of each 

instance of the inspection required by 

paragraph (1) of EASA Emergency AD 2024– 

0211–E at the applicable compliance times 

specified in paragraph (i)(9)(i) or (ii) of this 

AD. This AD does not require submitting 

information to Liebherr. 

(i) For an inspection done on or after the 

effective date of this AD: Submit the report 

within 10 days after the inspection. 

(ii) For an inspection done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

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

section of EASA Emergency AD 2024–0211– 

E. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) 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)(1) 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 

(1) For more information about this AD, 

contact Adam Hein, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (316) 946– 

4116; email: Adam.Hein@faa.gov. 

(2) For advisory circular material identified 

in this AD that is not incorporated by 

reference, go to faa.gov/regulations_policies/ 

advisory_circulars/index.cfm/go/ 

document.information/documentID/1023552. 

(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) European Union Aviation Safety Agency 

(EASA) Emergency AD 2024–0211–E, dated 

November 7, 2024. 

(ii) [Reserved] 

(3) For EASA material identified in this 

AD, contact EASA, Konrad-Adenauer-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. 

(4) 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. 

(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 December 23, 2024. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2024–31511 Filed 12–30–24; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2669; Project 

Identifier MCAI–2024–00660–R; Amendment 

39–22915; AD 2024–26–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Helicopters Model H160–B 

helicopters. This AD was prompted by 

a report of excessive axial play of the 

rotating scissors spherical bearings. This 

AD requires measuring the axial play of 

the rotating scissors spherical bearings 

and, depending on the results, 

accomplishing corrective action and 

reporting inspection results, as 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 January 17, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 17, 2025. 

The FAA must receive comments on 

this AD by February 18, 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 


ddrumheller on DSK120RN23PROD with RULES1