46762 Federal Register / Vol. 86, No. 159 / Friday, August 20, 2021 / Rules and Regulations 

4F5350A04152 and removing that part 

from service accordingly instead. 

Costs of Compliance 

The FAA estimates that this AD 

affects 4 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. 

Replacing a tail gearbox fitting takes 

about 48 work-hours and parts cost 

about $30,000 for an estimated cost of 

$34,080 per helicopter and $136,320 for 

the U.S. fleet, per replacement cycle. 

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 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. 

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: 

2021–17–16 Leonardo S.p.a.: Amendment 

39–21699; Docket No. FAA–2021–0455; 

Project Identifier 2018–SW–031–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective September 24, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

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

AW189 helicopters, certificated in any 

category, with tail gearbox fitting part 

number (P/N) 4F5350A04152 installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

(e) Unsafe Condition 

This AD was prompted by fatigue testing 

and analyses. The FAA is issuing this AD to 

prevent parts from remaining in service 

beyond their fatigue life. The unsafe 

condition, if not addressed, could result in 

failure of a part, which could result in loss 

of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Before further flight after the effective date 

of this AD: 

(1) Determine the total hours time-inservice (TIS) and total number of landings of 

tail gearbox fitting P/N 4F5350A04152. For 

purposes of this AD, a landing is counted 

anytime a 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. If the total hours TIS 

and total number of landings cannot be 

determined, before further flight, remove the 

part from service. 

(2) Remove any part from service that has 

reached or exceeded its life limit as follows. 

Thereafter, remove any part from service on 

or before reaching its life limit as follows. 

Tail gearbox fitting P/N 4F5350A04152: 

14,600 total hours TIS or 57,300 total 

landings, whichever occurs first. 

(h) 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 (i)(1) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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. 

(i) Related Information 

(1) For more information about this AD, 

contact Kristi Bradley, Program Manager, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

kristin.bradley@faa.gov. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD 2018–0087, dated April 18, 2018. 

You may view the EASA AD on the internet 

at https://www.regulations.gov in Docket No. 

FAA–2021–0455. 

(j) Material Incorporated by Reference 

None. 

Issued on August 13, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17841 Filed 8–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0672; Project 

Identifier MCAI–2021–00304–R; Amendment 

39–21693; AD 2021–17–10] 

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 certain 

Leonardo S.p.a. Model A109A, A109A 

II, A109C, A109E, A109K2, A109S, and 

AW109SP helicopters, having a certain 

rotor brake kit installed. This AD was 


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Federal Register / Vol. 86, No. 159 / Friday, August 20, 2021 / Rules and Regulations 46763 

prompted by a report of un-commanded 

activation of the rotor brake system 

before take-off due to a jammed rotor 

brake control cable and subsequent 

partially open brake control valve. This 

AD requires repetitive inspections of the 

rotor brake control cable and 

replacement of the rotor brake control 

cable, if necessary, 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 becomes effective 

September 7, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 7, 2021. 

The FAA must receive comments on 

this AD by October 4, 2021. 

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 

https://www.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. 

For material incorporated by reference 

(IBR) in this AD, contact the EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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–2021– 

0672. 

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–2021– 

0672; 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, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Darren Gassetto, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; phone: (516) 228–7323; email: 

Darren.Gassetto@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0067, 

dated March 9, 2021 (EASA AD 2021– 

0067), to correct an unsafe condition on 

Leonardo S.p.a. (formerly Finmeccanica 

S.p.A., AgustaWestland S.p.A., Agusta 

S.p.A., Costruzioni Aeronautiche 

Giovanni Agusta) Model A109A, 

A109AII, A109C, A109E, A109K2, 

A109S, and AW109SP helicopters with 

a certain rotor brake kit installed. 

EASA AD 2021–0067 was prompted 

by a report of un-commanded activation 

of the rotor brake system before take-off 

due to a jammed rotor brake control 

cable and subsequent partially open 

brake control valve. This resulted in 

hydraulic pressure delivered to the rotor 

brake, even with the rotor brake lever in 

the OFF position. To address this 

condition, EASA AD 2021–0067 

requires repetitive inspections of the 

rotor brake control cable and 

replacement, if necessary. The FAA is 

issuing this AD to address uncommanded activation of the rotor brake 

system, which could lead to failure of 

the rotor brake system with consequent 

damage to surrounding critical 

equipment, resulting in loss of control 

of the helicopter. 

Related IBR Material Under 1 CFR Part 

51 

EASA AD 2021–0067 specifies, 

within 50 hours and thereafter at 

intervals not to exceed 100 hours, 

repetitively inspecting the rotor brake 

control cable and replacing the control 

cable if the cylindrical nipple does not 

rotate freely, if the control cable jams 

when running inside the sheath, or if 

there is any damage or wear. EASA AD 

2021–0067 also prohibits installing an 

affected rotor brake control cable on any 

helicopter unless it first passes the 

required inspection and requires 

reporting information to the 

manufacturer. 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 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 determining that the unsafe 

condition described previously is likely 

to exist or develop on other products of 

these same type designs. 

Requirements of This AD 

This AD requires accomplishing the 

actions specified in EASA AD 2021– 

0067, described previously, as 

incorporated by reference, except for 

any differences identified 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 initially worked with 

Airbus and EASA to develop a process 

to use some EASA ADs as the primary 

source of information for compliance 

with requirements for corresponding 

FAA ADs. The FAA has since 

coordinated with other manufacturers 

and civil aviation authorities to use this 

process. As a result, EASA AD 2021– 

0067 is incorporated by reference in this 

FAA final rule. This AD would, 

therefore, require compliance with 

EASA AD 2021–0067 in its entirety, 

through that incorporation, except for 

any differences identified in the 

regulatory text of this AD. Using 

common terms that are the same as the 

heading of a particular section in the 

EASA AD 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 the EASA 

AD. Service information required by 

EASA AD 2021–0067 for compliance is 

available on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0672. 

FAA’s Justification and Determination 

of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (5 U.S.C.) 

authorizes agencies to dispense with 

notice and comment procedures for 

rules when the agency, for ‘‘good cause’’ 

finds that those procedures are 


khammond on DSKJM1Z7X2PROD with RULES
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‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

seeking comment prior to the 

rulemaking. 

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 waiving notice 

and comment prior to adoption of this 

rule because un-commanded activation 

of the rotor brake system due to a 

jammed rotor brake control cable and 

subsequent partially open brake control 

valve could lead to failure of the rotor 

brake system, with consequent loss of 

control of the helicopter. In addition, 

the compliance time for the required 

action is shorter than the time necessary 

for the public to comment and for 

publication of the final rule. Based on 

the average flight-hour utilization rates 

of these helicopters, the initial 

corrective actions must be completed 

within about two months. Therefore, 

notice and opportunity for prior public 

comment are impracticable and contrary 

to public interest pursuant to 5 U.S.C. 

553(b)(3)(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. 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2021–0672; Project Identifier MCAI– 

2021–00304–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the AD, 

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 AD 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 https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this AD. 

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 Darren Gassetto, 

Aerospace Engineer, COS Program 

Management Section, Operational 

Safety Branch, FAA, 1600 Stewart Ave., 

Suite 410, Westbury, NY 11590; phone: 

(516) 228–7323; email: 

Darren.Gassetto@faa.gov. Any 

commentary that the FAA receives that 

is not specifically designated as CBI will 

be placed in the public docket for this 

rulemaking. 

Regulatory Flexibility Act (RFA) 

The requirements of the 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 notice and comment, RFA 

analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 153 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR INSPECTION

Labor cost Parts cost Cost per helicopter Cost on U.S. operators 

1 work-hour × $85 per hour = $85 ........................................... $0 $85 per inspection cycle ......... $13,005 per inspection cycle. 

The FAA estimates the following 

costs to do any on-condition 

replacement that would be required 

based on the results of the inspections. 

The FAA has no way of determining the 

number of helicopters that might need 

this replacement: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS * 

Action Labor cost Parts cost Cost per 

helicopter 

Replacement ................................................................. 3 work-hours × $85 per hour = $255 ........................... $615 $870 

Reporting ...................................................................... 1 work-hour × $85 per hour = $85 ............................... 0 85 

The FAA has included all known 

costs in this cost estimate. According to 

the manufacturer, however, some or all 

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 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 

be approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, 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 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 86, No. 159 / Friday, August 20, 2021 / Rules and Regulations 46765 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood Pkwy., 

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 

The FAA determined that this AD 

would not have federalism implications 

under Executive Order 13132. This AD 

would 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 this regulation: 

(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: 

2021–17–10 Leonardo S.p.a: Amendment 

39–21693; Docket No. FAA–2021–0672; 

Project Identifier MCAI–2021–00304–R. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 7, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

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

A109A, A109A II, A109C, A109E, A109K2, 

A109S, and AW109SP helicopters, 

certificated in any category, with a rotor 

brake kit identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0067, dated March 9, 2021 (EASA AD 2021– 

0067). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Codes 6321, Main Rotor Brake. 

(e) Unsafe Condition 

This AD was prompted by a report of uncommanded activation of the rotor brake 

system before take-off due to a jammed rotor 

brake control cable and subsequent partially 

open brake control valve. The FAA is issuing 

this AD to address un-commanded activation 

of the rotor brake system, which could lead 

to failure of the rotor brake system, with 

consequent damage to surrounding critical 

equipment, and 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, EASA AD 2021–0067. 

(h) Exceptions to EASA AD 2021–0067 

(1) Where EASA AD 2021–0067 requires 

compliance from its effective date, this AD 

requires using the effective date of this AD. 

(2) This AD does not require the 

‘‘Remarks’’ section of EASA AD 2021–0067. 

(3) Where EASA AD 2021–0067 requires 

compliance in terms of flight hours (FH), this 

AD requires using hours time-in-service. 

(4) Where paragraph (2) of EASA AD 2021– 

0067 requires replacing the affected part if 

any defect is found, for purposes of this AD, 

a defect also includes compromised integrity 

of the control cable strands (e.g., fraying or 

a kink). 

(5) Where the service information required 

by EASA AD 2021–0067 specifies replacing 

the affected part if any damage is found, for 

purposes of this AD, damage includes clicks 

or breakings when the rotor brake lever is 

moved forward and backward. 

(i) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the actions of this AD can be performed, 

provided the rotor brake system is deactivated or rendered inoperable. 

(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. 

Information may be emailed to: 9-AVS-AIR730-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) Related Information 

For more information about this AD, 

contact Darren Gassetto, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; phone: (516) 228–7323; email: 

Darren.Gassetto@faa.gov. 

(l) 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 2021–0067, dated March 9, 2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0067, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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–2021–0672. 

(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 

fr.inspection@nara.gov, or go to https://

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


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46766 Federal Register / Vol. 86, No. 159 / Friday, August 20, 2021 / Rules and Regulations 

Issued on August 12, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–17974 Filed 8–18–21; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0686; Project 

Identifier MCAI–2021–00687–R; Amendment 

39–21701; AD 2021–17–18] 

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 A109C, A109K2, 

A109E, A109S, and AW109SP 

helicopters. This AD was prompted by 

a report of a crack on the tail rotor (TR) 

mast. This AD requires an inspection of 

certain TR sleeve assemblies for 

discrepancies, an inspection of certain 

TR shaft assemblies for discrepancies, a 

repetitive measurement of the position 

of the bushing of the TR sleeve assembly 

in relation to the pitch change slider 

assembly, and corrective actions if 

necessary, 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 becomes effective 

September 7, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 7, 2021. 

The FAA must receive comments on 

this AD by October 4, 2021. 

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 

https://www.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. 

For material incorporated by reference 

(IBR) in this AD, contact the EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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–2021– 

0686. 

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–2021– 

0686; 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, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; phone: (516) 228–7330; email: 

andrea.jimenez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2021–0144, dated June 17, 2021 (EASA 

AD 2021–0144) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for all Leonardo S.p.a. 

Model A109C, A109K2, A109E, A109S, 

and AW109SP helicopters. 

This AD was prompted by a report of 

a crack on the TR mast. The FAA is 

issuing this AD to address cracking on 

the TR mast, which could lead to failure 

of the TR mast, with consequent loss of 

control of the helicopter. See the MCAI 

for additional background information. 

Related IBR Material Under 1 CFR Part 

51 

EASA AD 2021–0144 specifies 

procedures for an inspection of certain 

TR sleeve assemblies for discrepancies; 

an inspection of certain TR shaft 

assemblies for abnormal wear condition, 

corrosion, fretting, crack, and damage; a 

repetitive measurement of the position 

of the bushing of the TR sleeve assembly 

in relation to the pitch change slider 

assembly for any dimensional change; a 

repetitive inspection of a certain 

inspection area of the TR gearbox for 

discrepancies; and corrective actions. 

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 the State 

of Design Authority, the FAA has been 

notified of the unsafe condition 

described in the MCAI referenced 

above. The FAA is issuing this AD after 

evaluating all pertinent information and 

determining that the unsafe condition 

exists and is likely to exist or develop 

on other products of the same type 

design. 

Requirements of This AD 

This AD requires accomplishing the 

actions specified in EASA AD 2021– 

0144, described previously, as 

incorporated by reference, except for 

any differences identified as exceptions 

in the regulatory text of this AD and 

except as discussed under ‘‘Differences 

Between this AD and the MCAI.’’ 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA initially worked with 

Airbus and EASA to develop a process 

to use certain EASA ADs as the primary 

source of information for compliance 

with requirements for corresponding 

FAA ADs. The FAA has since 

coordinated with other manufacturers 

and civil aviation authorities to use this 

process. As a result, EASA AD 2021– 

0144 is incorporated by reference in this 

FAA final rule. This AD, therefore, 

requires compliance with EASA AD 

2021–0144 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 the 

EASA AD 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 


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