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Federal Register / Vol. 86, No. 244 / Thursday, December 23, 2021 / Rules and Regulations Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 901 Locust, Room 301, Kansas City, MO 64106; phone: 816 3294165; fax: 816
3294090; email: jim.rutherford@faa.gov.
2 Refer to European Union Aviation Safety Agency EASA AD 20200056, dated March 13, 2020, for more information. You may examine the EASA AD in the AD docket at https www.regulations.gov by searching for and locating Docket No. FAA20210792.
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. 552a 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 Solo Kleinmotoren GmbH Service Bulletin No. 460011, Ausgabe 1 English translation: Issue 1, dated August 19, 2019.
Note 1 to paragraph j2i: This service information contains German to English translation. EASA used the English translation in referencing the document from Stemme AG. For enforceability purposes, the FAA will cite the service information in English as it appears on the document.
ii Reserved 3 For service information identified in this AD, contact Solo Kleinmotoren GmbH, Postfach 600152, D71050 Sindelfingen, Germany; phone: +49 703 13010; fax: +49
703 1301136; email: aircraft@sologermany.com; website: https
aircraft.solo.global/gb/.
4 You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call 816 3294148.
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: fr.inspection@nara.gov, or go to:
https www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on November 18, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202127636 Filed 122221; 8:45 am
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BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210872; Project Identifier MCAI202100312R; Amendment 3921866; AD 20212607
RIN 2120AA64

Airworthiness Directives; Airbus Helicopters Federal Aviation Administration FAA, DOT.
ACTION: Final rule.
AGENCY:

The FAA is superseding Airworthiness Directive AD 202011
05, which applied to all Airbus Helicopters Model EC120B helicopters.
AD 20201105 required repetitive inspections of the tail rotor TR hub body for cracks and applicable corrective actions if necessary, and repetitive replacement of the attachment bolts, washers, and nuts of the TR hub body. This AD was prompted by a report of recurrent loss of tightening torque on several attachment bolts on the TR hub body. This AD retains certain requirements of AD 20201105, adds repetitive inspections, requires additional corrective actions, and updates applicable service information.
The FAA is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 27, 2022.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of January 27, 2022.
ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052;
telephone 972 6410000 or 800 232
0323; fax 972 6413775; or at https
www.airbus.com/helicopters/services/
technical-support.html. You may view this service information 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 817 2225110. It is also available at https www.regulations.gov by searching for and locating Docket No.
FAA202100872.
SUMMARY:

Examining the AD Docket You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20210872; or in person at Docket Operations between 9 a.m. and 5 p.m.,
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Monday through Friday, except Federal holidays. The AD docket contains this final rule, the European Union Aviation Safety Agency EASA AD, 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 FAA issued a notice of proposed rulemaking NPRM to amend 14 CFR
part 39 to supersede AD 20201105, Amendment 3921130 85 FR 31042, May 22, 2020, AD 20201105. AD
20201105 applied to Airbus Helicopters Model EC120B helicopters, all serial numbers. The NPRM
published in the Federal Register on October 8, 2021 86 FR 56220. In the NPRM, the FAA proposed to retain some of the requirements of AD 2020
1105, and proposed to require, within 15 hours time-in-service TIS or 7 days, whichever occurs first, performing repetitive inspections of the TR hub body for a crack and depending on the inspection results, removing the affected parts from service. The NPRM also proposed to require inspecting the TR
spline flange for corrosion, impacts, fretting, wear, and a crack and depending on the inspection results, removing the TR splined flange from service. For helicopters with 9,000 or more total hours TIS or with unknown total hours TIS, the NPRM proposed to require, within 15 hours TIS or 7 days, whichever occurs first, and thereafter at intervals not to exceed 1,000 hours TIS, removing from service any bolt, washer, and nut installed on the TR hub body, replacing them with airworthy parts, inspecting the TR splined flange, and depending on the inspection results, removing the TR splined flange from service.
Additionally, the NPRM proposed to require, for helicopters with less than 9,000 total hours TIS, within 1,000
hours TIS or before accumulating 9,000
total hours TIS, whichever occurs first, and thereafter at intervals not to exceed 1,000 hours TIS, removing from service any bolt, washer, and nut installed on the TR hub body replacing them with
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