Federal Register / Vol. 89, No. 194 / Monday, October 7, 2024 / Rules and Regulations 80995 

paragraphs (h)(5)(i) through (iii) of this AD, 

as applicable. 

(i) The inspections required by paragraph 

(1) of EASA AD 2023–0035 that have been 

accomplished before the effective date of this 

AD using Leonardo Helicopters Alert Service 

Bulletin No. 119–098, dated March 13, 2019 

(ASB 119–098, original issue) but this credit 

is limited to the torque tube assembly batch 

numbers identified in ASB 119–098, original 

issue. 

(ii) The inspections required by paragraph 

(1) of EASA AD 2023–0035 that have been 

accomplished before the effective date of this 

AD using Leonardo Helicopters ASB No. 

119–098, Revision A, dated March 31, 2021 

(ASB 119–098, Revision A) but this credit is 

limited to the torque tube assembly batch 

numbers identified in ASB 119–098, 

Revision A. 

(iii) Replacing an affected part, as defined 

in EASA AD 2023–0035, with a serviceable 

part, as defined in EASA AD 2023–0035, 

required by paragraph (3) of EASA AD 2023– 

0035 that has been accomplished before the 

effective date of this AD using ASB 119–098, 

original issue; or ASB 119–098, Revision A. 

(6) Where the material referenced in EASA 

AD 2023–0035 specifies to return a torque 

tube assembly to the manufacturer, this AD 

does not include that requirement. 

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

section of EASA AD 2023–0035. 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2023–0035 specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(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 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. 

(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 Sungmo Cho, Aviation Safety 

Engineer, FAA, 1600 Stewart Ave., Suite 410, 

Westbury, NY 11590; phone: (781) 238–7241; 

email: Sungmo.D.Cho@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 the AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0035, dated February 10, 

2023. 

(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; 

internet 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 Pkwy., 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 August 28, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–23065 Filed 10–4–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0997; Project 

Identifier MCAI–2022–01306–R; Amendment 

39–22832; AD 2024–17–07] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

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 multiple reports of cracks 

found on tail rotor (TR) damper bracket 

assemblies. This AD requires 

accomplishing repetitive detailed visual 

inspections (DVIs) of certain partnumbered TR damper bracket 

assemblies for corrosion and cracks and, 

depending on the results, taking 

corrective action. This AD also prohibits 

installing an affected TR damper bracket 

assembly unless it is new. 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 November 

12, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 12, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0997; 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 EASA material identified in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; phone 

+49 221 8999 000; email: ADs@

easa.europa.eu; internet: 

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. The EASA material 

is also available at regulations.gov under 

Docket No. FAA–2024–0997. 

Other Related Material: For Leonardo 

Helicopters material, contact Leonardo 

S.p.A., Emanuele Bufano, Head of 

Airworthiness, Viale G. Agusta 520, 

21017 C. Costa di Samarate (Va) Italy; 

phone: (+39) 0331–225074; fax: (+39) 

0331–229046; or at customer

portal.leonardocompany.com/en-US/. 

FOR FURTHER INFORMATION CONTACT: 

Sungmo Cho, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (781) 238– 

7241; email: Sungmo.D.Cho@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 Leonardo S.p.a. Model AB139 

and AW139 helicopters. The NPRM 

published in the Federal Register on 

April 10, 2024 (89 FR 25194). The 

NPRM was prompted by EASA AD 

2022–0154, dated August 1, 2022 (EASA 

AD 2022–0154; also referred to as the 

MCAI), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA AD 2022– 

0154 stated that during scheduled 


lotter on DSK11XQN23PROD with RULES1
80996 Federal Register / Vol. 89, No. 194 / Monday, October 7, 2024 / Rules and Regulations 

inspections, some TR damper bracket 

assemblies were found cracked and that 

subsequent investigation revealed that 

the cracks originated from the outer 

edges of the TR damper bracket lug 

bores and were due to stress corrosion. 

That condition, if not detected and 

corrected, could lead to fracture of the 

affected part (TR damper bracket 

assembly), TR blade loss, unbalance or 

damage to the tail or other parts of the 

helicopter, possibly resulting in failure 

of the TR damper, and consequent loss 

of control of the helicopter. Therefore, 

EASA AD 2022–0154 required repetitive 

DVIs of the affected part for cracks and 

corrosion, and, depending on findings, 

replacing the affected part with a 

serviceable part. 

After EASA AD 2022–0154 was 

issued, new occurrences were reported 

on additional serial-numbered and partnumbered TR damper bracket 

assemblies that were not included in the 

initial batch of affected parts and it was 

determined that additional TR damper 

bracket assemblies must also be 

inspected. Consequently, EASA issued 

EASA AD 2022–0205, dated October 4, 

2022 (EASA AD 2022–0205), to retain 

the requirements of EASA AD 2022– 

0154, which is superseded, expand the 

definition of ‘‘affected part,’’ and require 

the DVIs for all affected parts. 

In the NPRM, the FAA proposed to 

require accomplishing repetitive DVIs of 

certain part-numbered TR damper 

bracket assemblies for corrosion and 

cracks and, depending on the results, 

taking corrective action. In the NPRM, 

the FAA also proposed to prohibit 

installing an affected TR damper bracket 

assembly unless it is new. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

You may examine EASA AD 2022– 

0205 in the AD docket at regulations.gov 

under Docket No. FAA–2024–0997. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

one anonymous commenter. The 

commenter supported the NPRM 

without change. 

Conclusion 

These products have been approved 

EASA and are approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with the European 

Union, EASA has notified the FAA of 

the unsafe condition described in the 

MCAI referenced above. The FAA 

reviewed the relevant data, considered 

the comment received, and determined 

that air safety requires adopting the AD 

as proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on these products. Except for 

minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Material Under 1 CFR Part 51 

EASA AD 2022–0205 requires 

repetitive DVIs of the TR damper 

bracket assembly for cracks and 

corrosion. Depending on the results of 

these inspections, EASA AD 2022–0205 

requires removing any corrosion, 

replacing any cracked part or a part 

which the corrosion cannot be removed 

with a serviceable part, and reporting 

any discrepancies to Leonardo. EASA 

AD 2022–0205 allows installing an 

affected part on any helicopter, 

provided it is a serviceable part, which 

is an affected part that is new. EASA AD 

2022–0205 also allows installing any TR 

damper bracket assembly that is not an 

affected part as defined within. 

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 ADDRESSES section. 

Other Related Material 

The FAA also reviewed Leonardo 

Helicopters Alert Service Bulletin No. 

139–724, Revision B, dated September 

29, 2022. This material specifies 

procedures for inspecting and if 

necessary, replacing certain partnumbered and serial-numbered TR 

damper bracket assemblies. 

Differences Between This AD and EASA 

AD 2022–0205 

EASA AD 2022–0205 requires 

reporting certain information to 

Leonardo, whereas this AD does not. 

Costs of Compliance 

The FAA estimates that this AD 

affects 126 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. 

A DVI of the TR damper bracket 

assembly takes approximately 1 workhour for an estimated cost of $85 per 

helicopter and up to $10,710 for the 

U.S. fleet, per inspection cycle. 

If required, removing corrosion from 

the TR damper bracket assembly takes 

approximately 1 work-hour for an 

estimated cost of $85 per helicopter. 

If required, removing a TR damper 

bracket assembly and replacing it with 

a serviceable part takes approximately 8 

work-hours and parts cost 

approximately $4,540 for an estimated 

cost of $5,220 per TR damper bracket 

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. 

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: 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 89, No. 194 / Monday, October 7, 2024 / Rules and Regulations 80997 

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: 

2024–17–07 Leonardo S.p.a.: Amendment 

39–22832; Docket No. FAA–2024–0997; 

Project Identifier MCAI–2022–01306–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 12, 2024. 

(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: 6400, Tail Rotor System. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracks found on tail rotor (TR) damper 

bracket assemblies. The FAA is issuing this 

AD to detect and address corrosion or cracks 

on the TR damper bracket assembly. The 

unsafe condition, if not addressed, could lead 

to fracture of the affected part (TR damper 

bracket assembly), TR blade loss, unbalance 

or damage to the tail or other parts of the 

helicopter, possibly resulting in failure of the 

TR damper, and consequent loss of control of 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraphs (h) and 

(i) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, European Union 

Aviation Safety Agency (EASA) AD 2022– 

0205, dated October 4, 2022 (EASA AD 

2022–0205). 

(h) Exceptions to EASA AD 2022–0205 

(1) Where EASA AD 2022–0205 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2022–0205 refers to its 

effective date and August 15, 2022 (the 

effective date of EASA AD 2022–0154, dated 

August 1, 2022), this AD requires using the 

effective date of this AD. 

(3) Where paragraph (4) of EASA AD 2022– 

0205 states to ‘‘replace the affected part with 

a serviceable part in accordance with the 

instructions of section 3 of the ASB;’’ for this 

AD, replace that text with ‘‘remove the 

affected part, as defined in EASA AD 2022– 

0205, from service and replace it with a 

serviceable part, as defined in EASA AD 

2022–0205, in accordance with the 

instructions of section 3 of the ASB.’’ 

(4) Where the material referenced in 

paragraph (4) of EASA AD 2022–0205 

specifies to perform detailed visual 

inspections (DVIs) and ‘‘If no cracks are 

found, but suspected evidences of corrosion 

signs are found, gently polish the interested 

area,’’ for the purposes of this AD, 

‘‘suspected signs of corrosion’’ and 

‘‘suspected evidences of corrosion signs’’ are 

signs of discoloration, pitting, flaking, or rust 

stains. 

(5) Where the material referenced in 

paragraph (4) of EASA AD 2022–0205 

specifies to discard certain parts, this AD 

requires removing those parts from service. 

(6) This AD does not require compliance 

with paragraph (6) of EASA AD 2022–0205. 

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

section of EASA AD 2022–0205. 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2022–0205 specifies to reporting certain 

information to the manufacturer, this AD 

does not include that requirement. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

initial instance of the detailed visual 

inspections (DVIs) required by paragraph (g) 

of this AD, for TR damper bracket assemblies 

identified in Table 1 of EASA AD 2022–0205, 

if those actions were performed before the 

effective date of this AD using Leonardo 

Helicopters Alert Service Bulletin No. 139– 

724, Revision A, dated September 19, 2022. 

(k) 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 § 39.19. In accordance 

with § 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 

certification office, send it to the attention of 

the person identified in paragraph (l)(1) of 

this AD. If sending information directly to 

the manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (l)(1) of this AD or email to: 9- 

AVS-AIR-730-AMOC@faa.gov. If mailing 

information, also submit information by 

email. 

(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. 

(l) Additional Information 

(1) For more information about this AD, 

contact Sungmo Cho, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (781) 238– 

7241; email: Sungmo.D.Cho@faa.gov. 

(2) For Leonardo Helicopters material 

identified in this AD that is not incorporated 

by reference, contact Leonardo S.p.A., 

Emanuele Bufano, Head of Airworthiness, 

Viale G. Agusta 520, 21017 C. Costa di 

Samarate (Va) Italy; phone: (+39) 0331– 

225074; fax: (+39) 0331–229046; or at 

customerportal.leonardocompany.com/enUS/. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the material listed in this paragraph under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2022–0205, dated October 4, 

2022. 

(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; 

internet: 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 Pkwy., 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 August 22, 2024. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2024–23066 Filed 10–4–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 31570; Amdt. No. 581] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas. 

DATES: Effective: 0901 UTC, 31 October 

2024. 


lotter on DSK11XQN23PROD with RULES1