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Federal Register / Vol. 86, No. 50 / Wednesday, March 17, 2021 / Rules and Regulations i Exceptions to EASA AD 20200085
1 Where EASA AD 20200085 refers to its effective date, this AD requires using the effective date of this AD.
2 Where EASA AD 20200085 refers to August 16, 2017 the effective date of EASA
AD 20170138, dated August 2, 2017, this AD requires using September 13, 2018 the effective date of AD 20181602.
3 Where EASA AD 20200085 refers to December 15, 2017 the issue date of EASA
AD 20170251, this AD requires using September 13, 2018 the effective date of AD
20181602.
4 The Remarks section of EASA AD
20200085 does not apply to this AD.
5 Where paragraph 8 of EASA AD 2020
0085 specifies do not operate any airplane having installed a, and do not install on any airplane a dull finish aft engine mount inner retainer, for this AD, do not operate any airplane having installed any inner retainers affected by the production quality deficiency as defined in paragraph g of this AD, and do not install on any airplane a dull finish aft engine mount inner retainer.
6 Where paragraph 9.3 of EASA AD
20200085 refers to January 27, 2016 the effective date of EASA AD 20160010, dated January 13, 2016, this AD requires using April 3, 2017 the effective date of AD 2017
0410.
7 Where paragraph 12 of EASA AD
20200085 specifies a compliance time of before next flight after December 15, 2017, for this AD, that compliance time is within 30 days after September 13, 2018 the effective date of AD 20181602.

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j Terminating Action for AD 20161409
and AD 20170410
1 Modification of an airplane as required by paragraph h of this AD i.e., accomplishing the modification required by paragraph 3 of EASA AD 20200085, the replacement specified in paragraph 4 of EASA AD 20200085, or the modification specified in paragraph 5 of EASA AD 2020
0085, constitutes terminating action for the repetitive detailed inspections required by paragraph l of AD 20161409 for that airplane.
2 Modification of an airplane as required by paragraph h of this AD i.e., accomplishing the modification required by paragraph 3 of EASA AD 20200085, the replacement specified in paragraph 4 of EASA AD 20200085, or the modification specified in paragraph 5 of EASA AD 2020
0085, is a method of compliance with the requirements of paragraph g of AD 2017
0410 for that airplane.
k Other FAA AD Provisions The following provisions also apply to this AD:
1 Alternative Methods of Compliance AMOCs: The Manager, Large Aircraft Section, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft
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Section, International Validation Branch, send it to the attention of the person identified in paragraph l of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
i Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
ii AMOCs approved previously for AD
20181602 are approved as AMOCs for the corresponding provisions of EASA AD 2020
0085 that are required by paragraph g of this AD.
2 Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SASs EASA Design Organization Approval DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
3 Required for Compliance RC: Except as required by paragraph k2 of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operators maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
l Related Information For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax:
2062313223; email: sanjay.ralhan@faa.gov.
m 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 this AD specifies otherwise.
i European Union Aviation Safety Agency EASA AD 20200085, dated April 6, 2020.
ii Reserved 3 For EASA AD 20200085, 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 material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 2062313195. This material may be found in the AD docket on the internet at https

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www.regulations.gov by searching for and locating Docket No. FAA20200914.
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 March 1, 2021.
Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202105534 Filed 31621; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20180309; Project Identifier 2018SW014AD; Amendment 3921456; AD 20210513
RIN 2120AA64

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

The FAA is adopting a new airworthiness directive AD for Leonardo S.p.a. Leonardo Model AW189 helicopters. This AD was prompted by two reported failures of the tail plane installation forward bolts bolts. This AD requires inspecting the bolts and depending on the results of those inspections, removing certain parts from service or installing a tail plane retromod. This AD also requires torqueing certain part-numbered nuts, inspecting bolts and nuts for wear, and depending on the results of those inspections, removing parts from service. The FAA is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective April 21, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of April 21, 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 +390331225074;
fax +390331229046; or at https
www.leonardocompany.com/en/home.
You may view this service information at the FAA, Office of the Regional SUMMARY:

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