DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0463; Product Identifier 2013-SW-041-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to remove Airworthiness Directive (AD) 2015-
17-01, which applies to certain Airbus Helicopters Model AS350B,
AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E,
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2015-17-
01 requires certain inspections of each tail rotor pitch horn assembly
(pitch horn) for a crack, replacement of a cracked pitch horn, and a
repetitive visual inspection of certain pitch horns. AD 2015-17-01 is
no longer necessary because the cause of the unsafe condition has been
removed from all affected helicopter models. Accordingly, the FAA
proposes to remove AD 2015-17-01.

DATES: The FAA must receive comments on this proposed AD by July 27,
2020.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:

Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the
instructions for submitting comments.

Fax: 202-493-2251.

Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.

Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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.

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-2020-0463;
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 proposal, any comments received, and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110;
email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include "Docket No. FAA-2020-0463;
Product Identifier 2013-SW-041-AD" at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.

The FAA will post all comments received, without change, to https://www.
regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this NPRM.

Discussion

The FAA issued AD 2015-17-01, Amendment 39-18234 (80 FR 50554,
August 20, 2015) ("AD 2015-17-01"), for certain Airbus Helicopters
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D,
AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP
helicopters. AD 2015-17-01 requires certain inspections of each pitch
horn for a crack, repetitive visual inspections of certain pitch horns
for a crack, replacing a cracked pitch horn before further flight, and
before installing any pitch horn having part number 350A121368 with
more than 0 hours time-in-service, dye-penetrant inspecting it for a
crack. AD 2015-17-01 was prompted by a report of a crack in the yoke of
a pitch horn and is intended to detect a crack in the pitch horn to
prevent failure of the pitch horn, loss of the anti-torque function,
and subsequent loss of control of the helicopter. The FAA issued AD
2015-17-01 to detect a crack in the pitch horn to prevent failure of
the pitch horn, loss of the anti-torque function, and subsequent loss
of control of the helicopter.

Actions Since AD 2015-17-01 Was Issued

Since issuing AD 2015-17-01, the FAA has determined that the chin
weights installed per Airbus Modification 07 5601 (that caused the
pitch horn to crack) can only be installed on Model AS350B3
helicopters. The FAA had previously issued AD 2014-05-10, Amendment 39-
17783 (79 FR 17408, March 28, 2014), which requires Model AS350B3
helicopters to remove the chin weights. The FAA has determined that
with the chin weights removed, the unsafe condition no longer exists on
Model AS350 and AS355 helicopters.

FAA's Conclusions

Upon further consideration, the FAA has determined that AD 2015-17-
01 is no longer necessary. Accordingly, this proposed AD would remove
AD 2015-17-01. Removal of AD 2015-17-01 would not preclude the FAA from
issuing another related action or commit the FAA to any course of
action in the future.

Related Costs of Compliance

This proposed AD would add no cost. This proposed AD would remove
AD 2015-17-01 from 14 CFR part 39; therefore, operators would no longer
be required to show compliance with that AD.

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.

Regulatory Findings

The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would 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 the proposed
regulation:

(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.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-17-01, Amendment 39-18234 (80 FR 50554, August 20, 2015), and
adding the following new AD: