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Federal Register / Vol. 86, No. 198 / Monday, October 18, 2021 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210612; Project Identifier MCAI202100650R; Amendment 3921755; AD 20212017
RIN 2120AA64

Airworthiness Directives; Leonardo S.p.a. Helicopters
Examining the AD Docket
Federal Aviation Administration FAA, DOT.
ACTION: Final rule.
AGENCY:

The FAA is superseding emergency Airworthiness Directive AD
20182352, which applied to all Leonardo S.p.a. Model AW169 and AW189 helicopters. AD 20182352
required inspecting the nut, cotter pin, lock-wire, and hinge bracket connected to the tail rotor servo-actuator TRA
feedback lever link, and each connection of the TRA feedback lever link, and repair if necessary. AD 2018
2352 also required applying a paint stripe or torque seal on the nut and reporting certain information. This AD
requires repetitive inspections of the TRA, repetitive inspections and checks of the tail rotor duplex bearings TR
DB, installation of an improved TRA
and TR DB, repetitive installations and checks of thermal strips, replacement of the improved TR DB life limit, and applicable corrective actions, as specified in a European Union Aviation Safety Agency EASA AD, which is incorporated by reference. This AD was prompted by a report of an accident of a Model AW169 helicopter, which was observed to have lost yaw control prior to the accident and a determination that certain inspections and checks of the TR
DB, installation of an improved TRA
and TR DB, certain other actions, and applicable corrective actions are necessary to address the unsafe condition. The FAA is issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective November 22, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of November 22, 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

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SUMMARY:

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ad.easa.europa.eu. You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 8172225110. It is also available in the AD docket on the internet at https www.regulations.gov by searching for and locating Docket No.
FAA20210612.
You may examine the AD docket on the internet at https
www.regulations.gov by searching for and locating Docket No. FAA2021
0612; 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 W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; telephone 516 2287330; 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
20200197, dated September 10, 2020
EASA AD 20200197, to correct an unsafe condition for all Leonardo S.p.A.
formerly Finmeccanica S.p.A., AgustaWestland S.p.A. Model AW169
and AW189 helicopters.
The FAA issued a notice of proposed rulemaking NPRM to amend 14 CFR
part 39 to supersede Emergency AD
20182352, Product Identifier 2018
SW093AD, dated November 8, 2018
Emergency AD 20182352.
Emergency AD 20182352 applied to all Leonardo S.p.a. Model AW169 and AW189 helicopters. The NPRM
published in the Federal Register on August 5, 2021 86 FR 42754. The NPRM was prompted by a report of an accident of a Model AW169 helicopter, which was observed to have lost yaw control prior to the accident and a determination that certain inspections and checks of the TR DB, installation of an improved TRA and TR DB, certain other actions, and applicable corrective actions are necessary to address the
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unsafe condition. The NPRM proposed to require repetitive inspections of the TRA, repetitive inspections and checks of the TR DB, installation of an improved TRA and TR DB, repetitive installations and checks of thermal strips, replacement of the improved TR
DB life limit, and applicable corrective actions, as specified in an EASA AD.
The FAA is issuing this AD to address failure of the TRA feedback lever. This condition could result in loss of tail rotor control and subsequent loss of control of the helicopter. See the EASA
AD 20200197 for additional background information.
Discussion of Final Airworthiness Directive 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.
Related Service Information Under 1
CFR Part 51
EASA AD 20200197 requires the following actions:
Repetitive inspections of the slippage marking of the castellated nut installed on the back-end of the affected TRA.
Repetitive inspections of the roughness and breakaway force of the affected TR DB.
Repetitive installations of a thermal strip on the spacer next to the TR DB.
Repetitive checks of the condition of the thermal strip and the indicated temperature.
Repetitive inspections/checks for particles and additional roughness of the TR DB.
Installation of an improved TRA.
Installation of an improved TR DB.
Repetitive replacements of the improved TR DB life limit.
An inspection of an affected TR DB if the thermal strip is detached, partially detached, or unreadable.
Reporting information to the manufacturer.

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