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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by:

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a. removing Airworthiness Directive AD 20181502, Amendment 39
19334 83 FR 34029, July 19, 2018; and b. adding the following new AD:

20210509 Airbus Helicopters:
Amendment 3921452; Docket No.
FAA20201132; Project Identifier MCAI202001386R.
a Effective Date This airworthiness directive AD is effective April 16, 2021.
b Affected ADs This AD replaces AD 20181502, Amendment 3919334 83 FR 34029, July 19, 2018 AD 20181502.
c Applicability This AD applies to Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP
helicopters, certificated in any category, as identified in European Union Aviation Safety Agency EASA AD 20170020R1, dated May 22, 2019 EASA AD 20170020R1.
d Subject Joint Aircraft System Component JASC
Code 6720, Tail Rotor Control System.
e Reason This AD was prompted by a report of several cases of damaged tail rotor TR pitch rod ball joints. The FAA is issuing this AD
to address damage to the elastomeric ball joint on the TR pitch change rod. This condition could result in failure of the TR
pitch change rod and subsequent loss of control of the helicopter.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g New 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 20170020R1.
h Exceptions to EASA AD 20170020R1
1 Where EASA AD 20170020R1 refers to its effective date, this AD requires using the effective date of this AD.
2 Where EASA AD 20170020R1 refers to February 9, 2017 the effective date of EASA
AD 20170020E, dated February 9, 2017, this AD requires using August 3, 2018 the effective date of AD 20181502.
3 The Remarks section of EASA AD
20170020R1 does not apply to this AD.
4 Although the service information referenced in EASA AD 20170020R1
specifies to discard certain parts, this AD
does not include that requirement.
5 Where EASA AD 20170020R1 refers to flight hours FH, this AD requires using hours time-in-service TIS.
6 Where paragraph 1 of EASA AD 2017
0020R1 specifies an initial compliance time of Before exceeding 50 FH flight hours since the last inspection per ALS
airworthiness limitations chapter 042000,
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or within 10 FH or 7 days, whichever occurs first, for this AD, the initial compliance time is within 10 hours TIS.
7 For the inspections specified in paragraph 1 of EASA AD 20170020R1:
Accomplishing the actions specified in paragraphs h7i and ii of this AD before the effective date of this AD are acceptable for compliance with the inspections specified in in paragraph 1 of EASA AD 2017
0020R1. On or after the effective date of this AD, comply with the inspections as specified in paragraph 1 of EASA AD 20170020R1.
i Manually induce a flapping movement in the TR blade until the pitch change rod rotates a minimum of 10 degrees.
ii Inspect both faces of the blade side of the ball joint elastomer for debonding, extrusion, and cracks.
8 Although the service information referenced in EASA AD 20170020R1
permits certain actions to be performed by a mechanical engineering technician or pilot, this AD requires that the actions be performed by a qualified mechanic.
i 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 International Validation Branch, send it to the attention of the person identified in paragraph j of this AD. Information may be emailed to: 9-AVS-AIR-730-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.
j Related Information For more information about this AD, contact Katherine Venegas, Aviation Safety Engineer, Cabin Safety, Mechanical and Environmental Systems Section, Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA 907124137;
phone: 5626275353; fax: 5626275210;
email: Katherine.Venegas@faa.gov.
k 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 20170020R1, dated May 22, 2019.
ii Reserved 3 For EASA AD 20170020R1, 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 EASA AD on the EASA website at https
ad.easa.europa.eu.

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