11410 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 

torque of the T/R plug by increasing the 

torque up to 30.5 Nm and inspect for any 

movement the moment torque is applied. 

(i) If there is no movement and the 

tightening torque is at least 30.5 Nm, before 

further flight, install lockwire by following 

the Accomplishment Instructions, part I, 

paragraph 4, of Leonardo Helicopters 

Emergency Alert Service Bulletin (EASB) No. 

119–105, Revision A, dated June 3, 2020 

(EASB 119–105 Rev A). 

(ii) If there is any movement or the 

tightening torque is less than 30.5 Nm, before 

further flight, comply with paragraph (f)(2) of 

this AD. 

(2) Within 50 hours TIS, unless required 

before further flight by paragraph (f)(1)(ii) of 

this AD, and thereafter at intervals not to 

exceed 200 hours TIS, inspect to determine 

whether the P/N and serial number (S/N) are 

visible on the outboard and inboard faces of 

the T/R duplex bearing by following the 

Accomplishment Instructions, part II, 

paragraphs 4 through 13 (except paragraphs 

9.1, 13.1, and 13.2), of EASB 119–105 Rev A. 

Instead of the excluded steps, do the 

following: 

Note 1 to paragraph (f)(2): You are not 

required to discard parts and you may use 

equivalent tooling to that identified in EASB 

119–105 Rev A. 

(i) If the P/N and S/N markings are visible 

on the outboard or inboard face of the T/R 

duplex bearing, before further flight, remove 

from service the T/R duplex bearing, internal 

spacer P/N 129–0160–43–101 (internal 

spacer), external spacer P/N 129–0160–44– 

101 (external spacer), bearing liner assembly, 

and T/R control rod P/N 109–0135–02–101 

(T/R control rod). 

(ii) If the P/N and S/N markings are not 

visible on the inboard face of the T/R duplex 

bearing, before further flight, inspect the T/ 

R duplex bearing, T/R plug, and nut by 

following the Accomplishment Instructions, 

part II, paragraphs 14 and 15 (but not 

paragraphs 15.1 through 15.2), of EASB 119– 

105 Rev A. For purposes of this inspection, 

damage to the races may be indicated by nonmovement of the inner race, movement of the 

outer race, deformation, roughness, or 

incorrect installation; and damage to the 

threads of the T/R plug and nut may be 

indicated by uneven threads, missing 

threads, or cross-threading. 

(A) If the T/R duplex bearing has any rough 

rotation, brinelling, spalling, chipping, 

flaking, evidence of overheated bearing balls, 

or damage to the races, before further flight, 

remove from service the T/R duplex bearing, 

the internal spacer, the external spacer, the 

bearing liner assembly, and the T/R control 

rod. 

(B) If the T/R plug or nut has any damaged 

threads, before further flight, remove from 

service the affected part. 

(C) Reassemble the T/R duplex bearing 

assembly by following the Accomplishment 

Instructions, part II, paragraphs 16 through 

31, of EASB 119–105 Rev A. 

(3) As of the effective date of this AD, do 

not install a T/R duplex bearing P/N 129– 

0160–11–103 on any helicopter unless you 

have complied with the requirements in 

paragraph (f)(2) of this AD. 

(g) Credit for Previous Actions 

(1) Accomplishment of AD 2020–13–02 

before the effective date of this AD is 

considered acceptable for compliance with 

paragraph (f)(1) and the initial inspection 

required by paragraph (f)(2) of this AD. 

(2) Actions accomplished before the 

effective date of this AD in accordance with 

the procedures specified in Leonardo 

Helicopters EASB No. 119–100, dated August 

7, 2019, or Leonardo Helicopters EASB No. 

119–105, dated May 18, 2020, are considered 

acceptable for compliance with the 

corresponding actions specified in paragraph 

(f)(1) and the initial inspection required by 

paragraph (f)(2) of this AD. 

(h) Special Flight Permits 

Special flight permits are prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

David Hatfield, Aviation Safety Engineer, 

Aircraft Systems Section, Technical 

Innovation Policy Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone 817–222–5110; email 9-ASW-FTWAMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, the FAA suggests 

that you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(j) Additional Information 

(1) Leonardo Helicopters EASB No. 119– 

100, dated August 7, 2019, and Leonardo 

Helicopters EASB No. 119–105, dated May 

18, 2020, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Emanuele Bufano, Head of Airworthiness, 

Viale G.Agusta 520, 21017 C.Costa di 

Samarate (Va) Italy; telephone +39–0331– 

225074; fax +39–0331–229046; or at https:// 

www.leonardocompany.com/en/home. You 

may view a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD No. 2020–0128, dated June 4, 

2020. You may view the EASA AD on the 

internet at https://www.regulations.gov in 

Docket No. FAA–2020–1026. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400, Tail Rotor System. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Leonardo Helicopters Emergency Alert 

Service Bulletin No. 119–105, Revision A, 

dated June 3, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, Leonardo S.p.A. Helicopters, 

Emanuele Bufano, Head of Airworthiness, 

Viale G. Agusta 520, 21017 C. Costa di 

Samarate (Va) Italy; telephone +39–0331– 

225074; fax +39–0331–229046; or at https:// 

www.leonardocompany.com/en/home. 

(4) You may view this service information 

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 service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email fedreg.legal@nara.gov, or go to: https:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on January 29, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–03663 Filed 2–24–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0649; Product 

Identifier 2019–SW–061–AD; Amendment 

39–21410; AD 2021–03–07] 

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 certain 

Leonardo S.p.a. (Leonardo) Model 

AB139 and AW139 helicopters. This AD 

requires removing certain engine 

mounting rods from service and 

prohibits their installation on any 

helicopter. This AD was prompted by a 

report of non-conforming engine 

mounting rods. The actions of this AD 

are intended to address an unsafe 

condition on these products. 

DATES: This AD is effective April 1, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of April 1, 2021. 

Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11411 

ADDRESSES: For service information 

identified in this final rule, contact 

Leonardo S.p.a. Helicopters, Emanuele 

Bufano, Head of Airworthiness, Viale 

G.Agusta 520, 21017 C.Costa di 

Samarate (Va) Italy; telephone +39– 

0331–225074; fax +39–0331–229046; or 

at https://www.leonardocompany.com/ 

en/home. You may view the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. It is also 

available on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0649. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0649; 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 AD, the 

European Union Aviation Safety Agency 

(EASA) AD, any service information 

that is incorporated by reference, any 

comments received, and other 

information. The street 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. 

FOR FURTHER INFORMATION CONTACT: 

Kristi Bradley, Aviation Safety Engineer, 

General Aviation & Rotorcraft Section, 

International Validation Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5110; email 

kristin.bradley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Leonardo Model AB139 and 

AW139 helicopters with certain serialnumbered engine mounting rods part 

number (P/N) 3G7120V00132. The 

NPRM published in the Federal 

Register on July 9, 2020 (85 FR 41219). 

The NPRM proposed to require 

removing the affected engine mounting 

rods from service and proposed to 

prohibit installing an affected engine 

mounting rod on any helicopter. The 

proposed requirements were intended to 

prevent failure of an affected engine 

mounting rod, which could possibly 

result in loss of control of the 

helicopter. 

The NPRM was prompted by EASA 

AD No. 2019–0149, dated June 24, 2019, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Leonardo S.p.a. (formerly 

Finmeccanica S.p.A., AgustaWestland 

S.p.A., Agusta S.p.A.; and 

AgustaWestland Philadelphia 

Corporation, formerly Agusta Aerospace 

Corporation) Model AB139 and AW139 

helicopters with certain serial numbered 

engine mounting rods P/N 

3G7120V00132 installed. EASA advises 

of reports of a production nonconformity on a specific batch of these 

engine mounting rods. EASA further 

advises that this non-conformity 

degrades the material strength of the 

engine mounting rods. 

EASA states this condition, if not 

corrected, could lead to failure of an 

affected engine mounting rod, possibly 

resulting in loss of control of the 

helicopter. Accordingly, the EASA AD 

requires removing from service each 

affected engine mounting rod, emailing 

a completed ‘‘Scrap Report’’ to 

Leonardo Helicopters Division, and 

installing a serviceable engine mounting 

rod. The EASA AD also prohibits 

installing an affected engine mounting 

rod on any helicopter. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule, but the FAA did not 

receive any comments on the NPRM or 

on the determination of the cost to the 

public. 

FAA’s Determination 

These helicopters have been approved 

by 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 its AD. The FAA is issuing this AD 

after evaluating all of the information 

provided by EASA and determining the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires emailing a 

completed ‘‘Scrap Report’’ to Leonardo 

Helicopters Division at the same 

compliance time as the engine mounting 

rod removal, whereas this AD does not. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Leonardo 

Helicopters Alert Service Bulletin (ASB) 

No. 139–593, Revision A, dated June 14, 

2019 (ASB 139–593, Revision A), which 

specifies procedures to replace the 

engine outboard and inboard mounting 

rods from the Number 1 and Number 2 

engines. 

This service information 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. 

Other Related Service Information 

The FAA reviewed Leonardo 

Helicopters ASB No. 139–593, dated 

June 11, 2019. This service information 

contains the same procedures as ASB 

139–593, Revision A. However, ASB 

139–593, Revision A expands the 

applicability from certain serialnumbered Model AB139 and AW139 

helicopters to all Model AB139 and 

AW139 helicopters with affected engine 

mounting rods installed. 

The FAA also reviewed Leonardo 

Helicopters AMP DM 39–A–71–21–05– 

00A–520A–B, AMP DM 39–A–71–21– 

05–00A–720A–B, AMP DM 39–A–71– 

21–06–00A–520A–B, AMP DM 39–A– 

71–21–06–00A–720A–B, AMP DM 39– 

A–71–21–07–00A–520A–B, AMP DM 

39–A–71–21–07–00A–720A–B, AMP 

DM 39–A–71–21–08–00A–520A–B, and 

AMP DM 39–A–71–21–08–00A–720A– 

B, all dated October 4, 2019. This 

service information specifies 

instructions for removing and installing 

the outboard and inboard engine 

mounting rods. 

Costs of Compliance 

The FAA estimates that this AD 

affects up to 126 helicopters of U.S. 

Registry. The FAA estimates that 

operators may incur the following costs 

in order to comply with this AD. Labor 

costs are estimated at $85 per workhour. 

Replacing an engine mounting rod 

requires about 8 work-hours and parts 

cost about $1,000 for an estimated cost 

of $1,680 per engine mounting rod. 

According to Leonardo Helicopter’s 

service information, some of the costs of 

this AD may be covered under warranty, 

thereby reducing the cost impact on 

affected individuals. The FAA does not 

control warranty coverage by Leonardo 

Helicopters. Accordingly, all costs are 

included in this cost estimate. 

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. 

11412 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 

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 helicopters 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. 

Adoption of 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: 

2021–03–07 Leonardo S.p.a.: Amendment 

39–21410; Docket No. FAA–2020–0649; 

Product Identifier 2019–SW–061–AD. 

(a) Applicability 

This airworthiness directive (AD) applies 

to Leonardo S.p.a. Model AB139 and AW139 

helicopters, certificated in any category, with 

an engine mounting rod part number (P/N) 

3G7120V00132 with a serial number (S/N) 

listed in Figures 2 or 3 of Leonardo 

Helicopters Alert Service Bulletin No. 139– 

593, Revision A, dated June 14, 2019 (ASB 

139–593), installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

non-conforming engine mounting rod. This 

condition could result in structural failure of 

the engine mounting rod and subsequent loss 

of control of the helicopter. 

(c) Effective Date 

This AD becomes effective April 1, 2021. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Before further flight, determine the total 

hours time-in-service (TIS) of each engine 

mounting rod. 

(2) Before reaching 225 total hours TIS or 

within 25 hours TIS, whichever occurs later, 

with the battery and any other electrical 

power supply disconnected, remove from 

service the engine mounting rod as follows: 

(i) For the Number 1 engine outboard 

mounting rod, remove from service the 

Number 1 engine outboard mounting rod and 

install an airworthy Number 1 engine 

outboard mounting rod as shown in Detail 

‘‘B’’ of Figure 1 of ASB 139–593 and by 

following the Accomplishment Instructions, 

paragraphs 3.1 and 3.2 of ASB 139–593, 

except you are not required to discard the 

Number 1 engine outboard mounting rod or 

comply with the ‘‘Scrap Report’’ instruction 

in paragraph 3.1 of ASB 139–593. 

Note 1 to paragraphs (e)(2)(i) through (iv): 

Figure 1 of ASB 139–593 shows the engine 

outboard and inboard mounting rod 

assemblies for the left-hand side only, the 

right-hand side is symmetrical. 

(ii) For the Number 1 engine inboard 

mounting rod, remove from service the 

Number 1 engine inboard mounting rod and 

install an airworthy Number 1 engine 

inboard mounting rod as shown in Detail ‘‘C’’ 

of Figure 1 of ASB 139–593 and by following 

the Accomplishment Instructions, paragraphs 

3.3 and 3.4 of ASB 139–593, except you are 

not required to discard the Number 1 engine 

inboard mounting rod or comply with the 

‘‘Scrap Report’’ instruction in paragraph 3.3 

of ASB 139–593. 

(iii) For the Number 2 engine outboard 

mounting rod, remove from service the 

Number 2 engine outboard mounting rod and 

install an airworthy Number 2 engine 

outboard mounting rod as shown in Detail 

‘‘B’’ of Figure 1 of ASB 139–593 and by 

following the Accomplishment instructions, 

paragraphs 4.1 and 4.2 of ASB 139–593, 

except you are not required to discard the 

Number 2 engine outboard mounting rod or 

comply with the ‘‘Scrap Report’’ instruction 

in paragraph 4.1 of ASB 139–593. 

(iv) For the Number 2 engine inboard 

mounting rod, remove from service the 

Number 2 engine inboard mounting rod and 

install an airworthy Number 2 engine 

inboard mounting rod as shown in Detail ‘‘C’’ 

of Figure 1 of ASB 139–593 and by following 

the Accomplishment instructions, paragraphs 

4.3 and 4.4 of ASB 139–593, except you are 

not required to discard the Number 2 engine 

inboard mounting rod or comply with the 

‘‘Scrap Report’’ instruction in paragraph 4.3 

of ASB 139–593. 

(3) As of the effective date of this AD, do 

not install on any helicopter an engine 

mounting rod with a P/N and 

S/N listed in paragraph (a) of this AD. 

(f) Credit for Previous Actions 

Actions accomplished before the effective 

date of this AD in accordance with the 

procedures specified in Leonardo Helicopters 

Alert Service Bulletin No. 139–593, dated 

June 11, 2019, are considered acceptable for 

compliance with the corresponding actions 

specified in paragraphs (e)(1) and (2) of this 

AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, may approve AMOCs for this 

AD. Send your proposal to: Kristi Bradley, 

Aviation Safety Engineer, General Aviation & 

Rotorcraft Section, International Validation 

Branch, FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222–5110; 

email 9-AVS-AIR-730-AMOC@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, the FAA suggests 

that you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

(1) Leonardo Helicopters Alert Service 

Bulletin No. 139–593, dated June 11, 2019, 

and Leonardo Helicopters AMP DM 39–A– 

71–21–05–00A–520A–B, AMP DM 39–A–71– 

21–05–00A–720A–B, AMP DM 39–A–71–21– 

06–00A–520A–B, AMP DM 39–A–71–21–06– 

00A–720A–B, AMP DM 39–A–71–21–07– 

00A–520A–B, AMP DM 39–A–71–21–07– 

00A–720A–B, AMP DM 39–A–71–21–08– 

00A–520A–B, and AMP DM 39–A–71–21– 

08–00A–720A–B, all dated October 4, 2019, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. For service information 

identified in this AD, contact Leonardo S.p.a. 

Helicopters, Emanuele Bufano, Head of 

Airworthiness, Viale G.Agusta 520, 21017 

C.Costa di Samarate (Va) Italy; telephone 

+39–0331–225074; fax +39–0331–229046; or 

at https://www.leonardocompany.com/en/ 

home. You may view a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD No. 2019–0149, dated June 24, 

2019. You may view the EASA AD on the 

internet at https://www.regulations.gov in 

Docket No. FAA–2020–0649. 

Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11413 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7120, Engine Mount Section. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Leonardo Helicopters Alert Service 

Bulletin No. 139–593, Revision A, dated June 

14, 2019. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Leonardo S.p.a. Helicopters, 

Emanuele Bufano, Head of Airworthiness, 

Viale G.Agusta 520, 21017 C.Costa di 

Samarate (Va) Italy; telephone +39–0331– 

225074; fax +39–0331–229046; or at https:// 

www.leonardocompany.com/en/home. 

(4) You may view this service information 

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 service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email fedreg.legal@nara.gov, or go to: https:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on January 27, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03660 Filed 2–24–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0983; Project 

Identifier MCAI–2020–00542–R; Amendment 

39–21404; AD 2021–03–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2018–05– 

09, which applied to all Airbus 

Helicopters Model AS332C, AS332C1, 

AS332L, and AS332L1 helicopters. AD 

2018–05–09 required inspecting the tail 

rotor (T/R) flapping hinge link (hinge) 

and reporting the results. This AD 

requires repetitive inspections of the 

spindle bolts and the inner ring and 

needle bearings of each flapping hinge, 

corrective actions if necessary, and 

repetitive replacements of affected 

flapping hinge components, as specified 

in a European Union Aviation Safety 

Agency (EASA) AD, which is 

incorporated by reference. Replacement 

of all affected flapping hinge 

components on each flapping hinge is 

terminating action for the repetitive 

inspections. This AD also expands the 

applicability. This AD was prompted by 

a report of a damaged flapping hinge on 

a T/R blade. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective April 1, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 1, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 

221 8999 000; email ADs@

easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

material on the EASA website at https:// 

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 in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–0983. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0983; 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, 

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. 

FOR FURTHER INFORMATION CONTACT: 

Daniel Moore, Aviation Safety Engineer, 

Denver ACO Branch, Compliance & 

Airworthiness Division, FAA, 26805 E 

68th Ave., Denver, CO 80249; telephone 

303–342–1095; email daniel.e.moore@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0086, dated April 14, 2020 (EASA 

AD 2020–0086) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Airbus 

Helicopters Model AS332C, AS332C1, 

AS332L, AS332L1, and SA330J 

helicopters. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2018–05–09, 

Amendment 39–19218 (83 FR 10360, 

March 9, 2018) (AD 2018–05–09). AD 

2018–05–09 applied to all Airbus 

Helicopters Model AS332C, AS332C1, 

AS332L, and AS332L1 helicopters. The 

NPRM published in the Federal 

Register on November 4, 2020 (85 FR 

70087). The NPRM was prompted by 

report of a damaged flapping hinge on 

a T/R blade. The NPRM proposed to 

require repetitive inspections of the 

spindle bolts and the inner ring and 

needle bearings of each flapping hinge, 

corrective actions if necessary, and 

repetitive replacements of affected 

flapping hinge components, as specified 

in an EASA AD. Replacement of all 

affected flapping hinge components on 

each flapping hinge is terminating 

action for the repetitive inspections. The 

NPRM also proposed to expand the 

applicability. 

The FAA is issuing this AD to address 

failure of a T/R flapping hinge. This 

condition could result in unbalance of 

the T/R, detachment of the T/R gearbox 

and hub, and subsequent loss of control 

of the helicopter. See the MCAI for 

additional background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM.