Federal Register / Vol. 85, No. 248 / Monday, December 28, 2020 / Rules and Regulations 84201 

(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 December 10, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–28406 Filed 12–23–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0792; Project 

Identifier 2018–SW–049–AD; Amendment 

39–21368; AD 2020–26–13] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–92A helicopters. This AD was 

prompted by seven incidents of fatigue 

cracks in the horizontal stabilizer root 

fitting FWD (forward root fitting). This 

AD requires establishing the life limit of 

certain part-numbered forward root 

fittings, establishing the life limit of 

certain part-numbered stabilizer strut 

fittings, repetitively inspecting certain 

parts, and depending on the inspection 

results, removing parts from service. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective February 1, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 1, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact your 

local Sikorsky Field Representative or 

Sikorsky’s Service Engineering Group at 

Sikorsky Aircraft Corporation, 124 

Quarry Road, Trumbull, CT 06611; 

telephone 1–800–946–4337 (1–800– 

Winged–S); email wcs_cust_service_

eng.gr-sik@lmco.com. Operators may 

also log on to the Sikorsky 360 website 

at https://www.sikorsky360.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. For information on the 

availability of this material at the FAA, 

call 817–222–5110. It is also available 

on the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0792. 

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– 

0792; 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: 

Dorie Resnik, Aerospace Engineer, 

Boston ACO Branch, 1200 District 

Avenue, Burlington, Massachusetts 

01803; telephone 781–238–7693; email 

dorie.resnik@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 Sikorsky Model S–92A 

helicopters with certain part-numbered 

horizontal stabilizer assemblies 

(stabilizer assembly), certain partnumbered forward root fittings, or 

certain part-numbered stabilizer strut 

fittings installed. The NPRM published 

in the Federal Register on September 

17, 2020 (85 FR 58007). The NPRM was 

prompted by seven incidents of fatigue 

cracks in forward root fittings. Fatigue 

cracking in a forward root fitting 

degrades the load path and increases the 

load on other assembly parts, 

particularly at the aft horizontal 

stabilizer attachment points. 

The NPRM proposed to require 

establishing the life limit of certain partnumbered forward root fittings and 

certain part-numbered stabilizer strut 

fittings. The NPRM also proposed to 

require repetitively inspecting each 

stabilizer assembly attachment bolt and 

barrel nut set, each forward root fitting, 

each attachment fitting including the 

bolt holes and fastener holes, condition 

of the fasteners, and each attachment 

fitting mating surface. Depending on the 

inspection results, the NPRM proposed 

to require removing parts from service. 

Finally, the NPRM proposed to prohibit 

installing certain stabilizer assemblies 

on any helicopter. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

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. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed. 

Related Service Information under 1 

CFR Part 51 

The FAA reviewed S–92 Maintenance 

Manual, SA S92A–AMM–000, 

Temporary Revision (TR) 55–33, dated 

March 24, 2020 (TR 55–33), which adds 

additional part numbers (P/Ns) to the 

Horizontal Stabilizer—Maintenance 

Practices and specifies procedures for 

inspecting each forward root fitting and 

aft root fitting bolt holes and fasteners, 

each forward and aft root fitting mating 

surface for wear of the abrasion-resistant 

Teflon coating, procedures for 

chemically striping the abrasionresistant Teflon coating from the entire 

mounting pad, applying alodine, and 

applying an abrasion-resistant Teflon 

coating. This service information also 

describes procedures for removing and 

installing a stabilizer (Tasks 55–11–01– 

900–001 and 55–11–01–900–002), 

checking the torque stabilization (Task 

55–11–01–280–001), and inspecting the 

stabilizer and attaching hardware (Task 

55–11–01–210–004). This service 

information also provides assembly 

diagrams and lists interchangeable 

stabilizer P/Ns and compatible strut P/ 

Ns. 

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 also reviewed S–92 

Maintenance Manual SA S92A–AWL– 

000, TR No. 4–58, dated October 2, 2017 

(TR 4–58), and S–92 Maintenance 

Manual SA S92A–AWL–000, TR No. 4– 

66 dated November 20, 2019 (TR 4–66). 

This service information revises Task 4– 

00–00–200–000, Table 1 Replacement 

Schedule, dated November 30, 2015. 

Both TR 4–58 and 4–66 revise the 

Airworthiness Limitations Schedule by 

removing certain part-numbered 

components, introducing new partVerDate Sep<11>2014 16:58 Dec 26, 2020 Jkt 253001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\28DER1.SGM 28DER1

tkelley on DSKBCP9HB2PROD with RULES
84202 Federal Register / Vol. 85, No. 248 / Monday, December 28, 2020 / Rules and Regulations 

numbered components, and establishing 

replacement intervals and recurring 

inspections for the forward root fitting 

and the horizontal stabilizer strut fitting. 

TR 4–58 also specifies inspecting the 

horizontal stabilizer and attaching 

hardware at a recurring interval of 250 

hours time in service (TIS). 

Differences Between This AD and the 

Service Information 

The service information requires 

returning affected parts to a Sikorsky 

specialist; this AD does not. 

Costs of Compliance 

The FAA estimates that this AD 

affects 85 helicopters of U.S. registry. 

Labor costs are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Visually inspecting the stabilizer 

assembly and attached hardware will 

take about 3 work-hours for an 

estimated cost of $255 per helicopter 

and $21,675 for the U.S. fleet per 

inspection cycle. 

If required, replacing a hat bushing 

and both upper fittings and lower 

fittings will take about 1 work-hour and 

parts will cost about $10,000 for an 

estimated cost of $10,085 per 

replacement. 

If required, replacing the upper and 

lower support strut rod ends, including 

lug and conical fitting, will take about 

1 work-hour and parts will cost about 

$10,000 for an estimated cost of $10,085 

per replacement. 

If required, performing a fluorescent 

penetrant inspection will take about 3 

work-hours for an estimated cost of 

$255 per inspection. 

If required, replacing a stabilizer 

assembly will take about 6 work-hours 

and parts will cost about $312,000 for 

an estimated cost of $312,510 per 

replacement. 

If required, replacing a forward root 

fitting will take about 10 work-hours 

and parts will cost about $25,000 for an 

estimated cost of $25,850 per 

replacement. 

If required, replacing a stabilizer strut 

fitting will take about 10 work-hours 

and parts will cost about $10,000 for an 

estimated cost of $10,850 per 

replacement. 

If required, replacing a forward root 

fitting and an aft attachment fitting will 

take about 20 work-hours and parts will 

cost about $50,000 for an estimated cost 

of $51,700 per replacement. 

If required, removing wear or 

corrosion and applying corrosion 

preventative compound will take about 

0.5 work-hour and parts will cost a 

nominal amount for an estimated cost of 

$43 per action. 

If required, replacing a stabilizer 

attachment bolt and barrel nut set will 

take about 1 work-hour and parts will 

cost about $500 for an estimated cost of 

$585 per replacement. 

If required, replacing a fastener will 

take about 0.1 work-hour and parts will 

cost a nominal amount for an estimated 

cost of $9 per fastener. 

If required, removing the abrasionresistant Teflon coating to inspect each 

forward and aft attachment fitting 

mating surface will take about 5 workhours for an estimated cost of $425 per 

inspection. 

If required, applying alodine or 

equivalent and applying abrasionresistant Teflon coating will take about 

5 work hours with minimal parts cost 

for an estimated cost of $425 per 

application. 

According to Sikorsky, 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 

for affected individuals. As a result, the 

FAA has included all costs 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. 

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 adding 

the following new airworthiness 

directive: 

2020–26–13 Sikorsky Aircraft Corporation: 

Amendment 39–21368; Docket No. 

FAA–2020–0792; Project Identifier 

2018–SW–049–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 1, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation Model S–92A helicopters, 

certificated in any category, with the 

following installed: Horizontal stabilizer root 

fitting FWD (forward root fitting) part 

number (P/N) 92209–07111–101 or 92070– 

20125–101; or stabilizer strut fitting P/N 

92209–07404–041, 92209–07403–041, or 

92070–20117–041 installed on horizontal 

stabilizer assembly (stabilizer assembly) P/N 

92070–20117–045, 92070–20117–046, 

92070–20125–041, 92070–20125–042, 

92070–20125–043, 92070–20125–044, 

92205–07400–043, or 92205–07400–045. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 5510, Horizontal Stabilizer Structure. 

(e) Unsafe Condition 

This AD was prompted by incidents of 

fatigue cracks in a forward root fitting and 

life limit recalculations for forward root 

fitting P/N 92209–07111–101 and 92070– 

20125–101. The FAA is issuing this AD to 

prevent a forward root fitting from remaining 

in service beyond its life limit, detect fatigue 

cracking in a forward root fitting, and prevent 


tkelley on DSKBCP9HB2PROD with RULES
Federal Register / Vol. 85, No. 248 / Monday, December 28, 2020 / Rules and Regulations 84203 

increased load and stress cracking in the 

stabilizer root fitting aft. The unsafe 

condition, if not addressed, could result in 

failure of a stabilizer root fitting, separation 

of the stabilizer assembly from the helicopter, 

and subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 50 hours time-in-service (TIS): 

(i) Determine the total hours TIS of the 

forward root fitting P/N 92209–07111–101 or 

92070–20125–101. If the hours TIS of the 

forward root fitting is unknown, use the 

hours TIS of the stabilizer assembly instead. 

(A) If the forward root fitting has 

accumulated 7,900 or more total hours TIS, 

before further flight, remove the forward root 

fitting from service. 

(B) If the forward root fitting has 

accumulated less than 7,900 total hours TIS, 

before exceeding 7,900 hours TIS, remove the 

forward root fitting from service. 

(ii) Thereafter following paragraph (g)(1)(i) 

of this AD, remove the forward root fitting 

from service before accumulating 7,900 total 

hours TIS. 

(iii) For stabilizer assemblies with 

stabilizer strut fitting P/N 92070–20117–041 

installed, perform the following actions: 

(A) Determine the total hours TIS of 

stabilizer strut fitting P/N 92070–20117–041. 

(B) If the stabilizer strut fitting has 

accumulated 19,100 or more total hours TIS, 

before further flight, remove the stabilizer 

strut fitting from service. 

(C) If the stabilizer strut fitting has 

accumulated less than 19,100 total hours TIS, 

before exceeding 19,100 total hours TIS, 

remove the stabilizer strut fitting from 

service. 

(iv) Thereafter following paragraph 

(g)(1)(iii) of this AD, remove the stabilizer 

strut fitting from service before accumulating 

19,100 total hours TIS. 

(2) For helicopters with stabilizer strut 

fitting P/N 92209–07404–041 or 92209– 

07403–041 installed, within 50 hours TIS 

and thereafter at intervals not to exceed 50 

hours TIS: 

(i) Remove the support strut and using a 

cheese cloth (or similar cloth) and isopropyl 

alcohol, clean the upper and lower support 

strut rod ends, horizontal stabilizer 

attachment fitting, and the tail rotor pylon 

attachment fitting. 

(ii) Using a 10X or higher power 

magnifying glass, a flashlight, and a mirror, 

visually inspect the hat bushing and both 

upper fittings and lower fittings for a crack, 

corrosion, fretting, deformation, and wear. If 

there is a crack, corrosion, fretting, 

deformation, or wear, before further flight, 

remove the hat bushing and both upper 

fittings and lower fittings from service. 

(iii) Using a 10X or higher power 

magnifying glass, a flashlight, and a mirror, 

visually inspect both upper and lower 

support strut rod ends, including lug and 

conical fitting, and both upper and lower 

attachment fittings on the stabilizer and 

pylon including the bushings for a crack, 

corrosion, fretting, deformation, and wear. If 

there is a crack, corrosion, fretting, 

deformation, or wear, before further flight, 

remove the upper and lower support strut 

rod ends, including lug and conical fitting, 

and both upper and lower attachment fittings 

on the stabilizer from service. 

(3) Within 250 hours TIS or one year, 

whichever occurs first, and thereafter at 

intervals not to exceed 250 hours TIS or one 

year, whichever occurs first: 

(i) Remove the stabilizer assembly and 

visually inspect each stabilizer attachment 

bolt and barrel nut set for corrosion, a crack, 

and damage to the threads. For the purposes 

of this inspection, damage may be indicated 

by uneven threads, missing threads, or crossthreading. 

(A) If there is corrosion within allowable 

limits, before further flight, treat for corrosion 

in accordance with FAA-approved 

procedures. 

(B) If there is corrosion that exceeds 

allowable limits, or a crack or damage to the 

threads, before further flight, remove the bolt 

and barrel nut set from service. 

(ii) Inspect the forward root fitting and the 

aft attachment fitting by: 

(A) Gaining access to the inside of the 

horizontal stabilizer. 

(B) Using Brulin Cleaner SD 1291 (or 

equivalent) and a low-lint cloth, remove all 

traces of sealing compound, oil, and dirt from 

the stabilizer mounting surfaces. 

(C) Using a 10X magnifying glass, inspect 

for any crack, wear, and corrosion. 

(1) If there is a crack, before further flight, 

remove the affected forward root fitting and 

the affected aft attachment fitting from 

service. 

(2) If there is wear or corrosion that 

exceeds allowable limits, before further 

flight, remove the affected forward root 

fitting and the affected aft attachment fitting 

from service. 

(3) If there is wear or corrosion within 

allowable limits, before further flight, treat 

for corrosion in accordance with FAAapproved procedures. 

(D) Visually inspect each attachment fitting 

bolt hole and fastener hole for a crack, wear, 

and corrosion. 

(1) If there is a crack, before further flight, 

remove the affected forward root fitting and 

the affected aft attachment fitting from 

service. 

(2) If there is wear or corrosion that 

exceeds allowable limits, before further 

flight, remove the affected forward root 

fitting and the affected aft attachment fitting 

from service. 

(3) If there is wear or corrosion within 

allowable limits, before further flight, treat 

for corrosion in accordance with FAA 

approved procedures. 

(E) Inspect for loose or working fasteners. 

If there is a loose or working fastener, before 

further flight, remove the fastener from 

service. 

(iii) As an alternative means to inspect for 

cracks in paragraphs (g)(3)(i) and (ii) of this 

AD, perform a florescent penetrate inspection 

(FPI). 

(iv) Visually inspect each forward and aft 

attachment fitting mating surface for wear of 

the abrasion-resistant Teflon coating and 

degradation. For the purposes of this 

inspection, degradation may be indicated by 

fretting. Refer to Figure 204, of S–92 

Maintenance Manual, SA S92A–AMM–000, 

Temporary Revision 55–33, Task 55–11–01– 

210–004, dated March 24, 2020 (TR 55–33), 

for a depiction of the area to be inspected. 

For the purposes of this inspection, wear may 

be indicated by less than 100% coverage of 

the abrasion-resistant Teflon coating. If there 

is wear to the abrasion-resistant Teflon 

coating or degradation, before further flight: 

(A) Chemically strip the abrasion-resistant 

Teflon coating from the entire mounting pad 

in accordance with paragraph 7.A.(7)(a) of TR 

55–33. 

(B) FPI or eddy current inspect for a crack. 

If there is a crack, before further flight, 

remove the stabilizer assembly from service. 

(C) If there is no crack, treat the affected 

area by applying alodine or equivalent. 

Apply abrasion-resistant Teflon coating in 

accordance with paragraphs 7.A.(7)(d) 

through (e) of TR 55–33. 

(4) Installing stabilizer strut fitting P/N 

92070–20117–041 is a terminating action for 

the 50 hour TIS repetitive requirements in 

paragraph (g)(2) of this AD. 

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

not install stabilizer assembly P/N 92205– 

07400–043, 92205–07400–045, or 92205– 

07400–047 on any helicopter. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston ACO 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 

certification office, send it to the attention of 

the person identified in paragraph (j) of this 

AD. 

(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 

For more information about this AD, 

contact Dorie Resnik, Aerospace Engineer, 

Boston ACO Branch, 1200 District Avenue, 

Burlington, Massachusetts 01803; telephone 

781–238–7693; email dorie.resnik@faa.gov. 

(j) 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 the AD specifies otherwise. 

(i) S–92 Maintenance Manual, SA S92A– 

AMM–000, Temporary Revision (TR) 55–33, 

dated March 24, 2020. 

(ii) [Reserved] 

(3) For Sikorsky Aircraft Corporation 

service information identified in this AD, 

contact your local Sikorsky Field 

Representative or Sikorsky’s Service 


tkelley on DSKBCP9HB2PROD with RULES
84204 Federal Register / Vol. 85, No. 248 / Monday, December 28, 2020 / Rules and Regulations 

Engineering Group at Sikorsky Aircraft 

Corporation, 124 Quarry Road, Trumbull, CT 

06611; telephone 1–800–946–4337 (1–800– 

Winged–S); email wcs_cust_service_eng.grsik@lmco.com. Operators may also log on to 

the Sikorsky 360 website at https://

www.sikorsky360.com. 

(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 December 10, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2020–28385 Filed 12–23–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0468; Product 

Identifier 2018–SW–046–AD; Amendment 

39–21365; AD 2020–26–10] 

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. (Leonardo) Model A119 

and AW119 MKII helicopters. This AD 

requires revising the existing Rotorcraft 

Flight Manual (RFM) for your helicopter 

and installing a placard to prohibit 

intentional entry into autorotation. This 

AD would also allow replacement of an 

affected fuel control unit (FCU) as an 

optional terminating action for the RFM 

revision and placard installation. This 

AD was prompted by reports that 

certain FCUs may not have been 

calibrated to specification during 

overhaul. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD is effective February 1, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 1, 2021. 

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 this 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– 

0468. 

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– 

0468 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 Aviation Safety Agency (now 

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: 

Mitch Soth, Flight Test Engineer, 

Southwest Section, Flight Test Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5110; email mitch.soth@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 all Leonardo Model A119 and 

AW119 MKII helicopters. The NPRM 

published in the Federal Register on 

June 11, 2020 (85 FR 35602). The NPRM 

proposed to require revising the 

Limitations Section of the existing RFM 

for your helicopter and installing a 

placard to prohibit intentional entry 

into autorotation. The NPRM also 

proposed to allow replacing affected 

FCUs with non-affected FCUs as an 

optional terminating action for the RFM 

revision and placard installation. The 

proposed requirements were intended to 

address certain FCUs that may not have 

been calibrated to specification during 

overhaul, which can lead to N1 

fluctuations, hung engine starts, and the 

inability to recover power during 

autorotation training, and possibly 

result in reduced control of the 

helicopter. 

The NPRM was prompted by EASA 

AD 2018–0124, dated June 5, 2018, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for all Leonardo Model A119 

and AW119 MKII helicopters. EASA 

advises that certain FCUs may not have 

been calibrated to specification during 

overhaul, and that this condition, if not 

corrected, can lead to N1 fluctuations, 

hung engine starts, and the inability to 

recover power during autorotation 

training, possibly resulting in reduced 

control of the helicopter. To address this 

unsafe condition, the EASA AD requires 

amendment of the applicable RFM and 

installation of a placard to prohibit 

intentional entry into autorotation. The 

EASA AD also allows removal of the 

RFM limitation and placard after 

replacement of an affected FCU. 

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 design and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Interim Action 

The FAA considers this AD interim 

action. If final action is later identified, 

the FAA might consider further 

rulemaking. 

Related Service Information Under 1 

CFR Part 51 

Leonardo has issued Leonardo 

Helicopters Emergency Alert Service 

Bulletin 119–089, Revision A, dated 

June 5, 2018. This service information 

describes procedures for revising the 

RFM and installing a placard in the 

cockpit. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 


tkelley on DSKBCP9HB2PROD with RULES