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. 

11414 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2020–0086 describes 

procedures for repetitive replacement of 

the flapping hinge components and 

repetitive inspections of the spindle 

bolts, inner ring, and needle bearings of 

each flapping hinge, and corrective 

action. The inspection procedures 

include repetitive inspections of the 

spindle bolts for cracking; repetitive 

inspections of the inner ring for 

spalling, brinelling, and cracking; and 

repetitive inspections of the needle 

bearings for spalling. The corrective 

actions include replacement of any 

affected component with a serviceable 

part. 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. 

Differences Between This AD and the 

MCAI 

Although the service information 

referenced in EASA AD 2020–0086 

specifies to return affected parts and 

submit a form to the manufacturer, this 

AD does not include those 

requirements. 

Where paragraph (1) of EASA AD 

2020–0086 refers to a compliance time 

of ‘‘within 25 flight hours or during the 

next scheduled 50 FH inspection, 

whichever occurs later . . . ,’’ for the 

initial replacement, this AD requires 

completion within 25 hours time-inservice after the effective date of this 

AD. 

Costs of Compliance 

The FAA estimates that this AD 

affects 26 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

8 work-hours × $85 per hour = $680 .......................................................................................... $11,630 $12,310 $320,060 

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. 

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 

removing Airworthiness Directive (AD) 

2018–05–09, Amendment 39–19218 (83 

FR 10360, March 9, 2018), and adding 

the following new AD: 

2021–03–01 Airbus Helicopters: 

Amendment 39–21404; Docket No. 

FAA–2020–0983; Project Identifier 

MCAI–2020–00542–R. 

(a) Effective Date 

This Airworthiness Directive (AD) is 

effective April 1, 2021. 

(b) Affected ADs 

This AD removes AD 2018–05–09, 

Amendment 39–19218 (83 FR 10360, March 

9, 2018) (AD 2018–05–09). 

(c) Applicability 

This AD applies to all Airbus Helicopters 

Model AS332C, AS332C1, AS332L, 

AS332L1, and SA330J helicopters, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Codes 6420, Tail Rotor Head; 6720, Tail 

Rotor Control System. 

(e) Reason 

This AD was prompted by a report of a 

damaged flapping hinge link (hinge) on a tail 

rotor (T/R) blade. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2020–0086, dated 

April 14, 2020 (EASA AD 2020–0086). 

(h) Exceptions to EASA AD 2020–0086 

(1) Where EASA AD 2020–0086 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2020–0086 does not apply to this AD. 

(3) Although the service information 

referenced in EASA AD 2020–0086 specifies 

to return affected parts and submit a form to 

the manufacturer, this AD does not include 

those requirements. 

(4) Where paragraph (9) of EASA AD 2020– 

0086 refers to ‘‘any discrepancy,’’ for the 

purposes of this AD, discrepancies include 

spalling, brinelling, and cracking on the 

inner ring, and spalling on the bearing 

needles. 

(5) Where EASA AD 2020–0086 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11415 

(6) Where paragraph (1) of EASA AD 2020– 

0086 refers to a compliance time of ‘‘within 

25 flight hours or during the next scheduled 

50 FH inspection, whichever occurs later 

. . . , ’’ for the initial replacement, this AD 

requires completion within 25 hours time-inservice after the effective date of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, 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 Strategic Policy 

Rotorcraft Section, send it to: Manager, 

Strategic Policy Rotorcraft Section, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5110. Information 

may be emailed to: 9-ASW-FTW-AMOCRequests@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. 

(j) Related Information 

For more information about this AD, 

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. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0086, dated April 14, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0086, 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 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(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. This 

material may be found in the AD docket on 

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

by searching for and locating Docket No. 

FAA–2020–0983. 

(5) You may view this material 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/ibr-locations.html. 

Issued on January 21, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03662 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–2020–0860; Product 

Identifier 2019–SW–005–AD; Amendment 

39–21416; AD 2021–03–13] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited (Type Certificate 

Previously Held by Bell Helicopter 

Textron Canada Limited) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bell Textron Canada Limited (type 

certificate previously held by Bell 

Helicopter Textron Canada Limited) 

Model 429 helicopters. This AD was 

prompted by the introduction of a new 

life limit for the centrifugal force 

bearing (CFB). This AD requires 

determining the accumulated retirement 

index number (RIN) and removing each 

affected CFB from service before it 

accumulates 8,000 total RIN. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective April 1, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J 1R4; 

telephone 450–437–2862 or 800–363– 

8023; fax 450–433–0272; or at https://

www.bellcustomer.com. 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. 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. 

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– 

0860; 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 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: Matt 

Fuller, AD Program Manager, Continued 

Operational Safety Branch, 

Airworthiness Products Section, 

General Aviation and Rotorcraft Unit, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5110; email matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, issued Transport Canada AD 

CF–2019–03, dated January 31, 2019 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or the MCAI), to correct an unsafe 

condition for certain Bell Helicopter 

Textron Canada Limited (now Bell 

Textron Canada Limited) Model 429 

helicopters. TCCA advises that an 

airworthiness limitations schedule 

document introduces a new life limit for 

CFB part number (P/N) 429–310–003– 

103, a component that was not 

previously included. Failure to observe 

the CFB life limit could result in 

excessive vibration and loss of control 

of the helicopter. You may examine the 

MCAI in the AD docket on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0860. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bell Helicopter Textron 

Canada Limited (now Bell Textron 

Canada Limited) Model 429 helicopters. 

The NPRM published in the Federal 

Register on October 1, 2020 (85 FR 

61879). The NPRM was prompted by the 

introduction of a new life limit for the 

CFB. The NPRM proposed to require 

determining the accumulated RIN and 

removing each affected CFB from 

service before it accumulates 8,000 total 

RIN. The FAA is issuing this AD to 

address a CFB remaining in service 

beyond its fatigue life. Failure to 

observe the CFB life limit could result 

in excessive vibration and loss of 

control of the helicopter. See the MCAI 

for additional background information.