Federal Aviation Administration (FAA), DOT.
Final rule; removal of airworthiness directive (AD).
The FAA is removing AD 2015–17–01, which applied 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 required 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 is removing AD 2015–17–01.
This AD becomes effective September 11, 2020.
You may examine the AD docket on the internet at
Matt Fuller, AD Program Manager, Continued Operational Safety Branch, Airworthiness Products Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by removing AD 2015–17–01, Amendment 39–18234 (80 FR 50554, August 20, 2015) (“AD 2015–17–01”), that applied to certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. The NPRM published in the
The FAA gave the public the opportunity to participate in developing this final rule. The FAA has considered the comment received. Mr. Warren LaBare indicated support for the NPRM.
The FAA reviewed the relevant data, considered the comment received, 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.
This AD adds no cost. This AD removes AD 2015–17–01 from 14 CFR part 39; therefore, operators are no longer required to show compliance with that AD.
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 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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
This AD is effective September 11, 2020.
This AD replaces AD 2015–17–01, Amendment 39–18234 (80 FR 50554, August 20, 2015).
This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, with tail rotor hub pitch horn (pitch horn) assembly, part number (P/N) 350A121368.01, 350A121368.02, 350A121368.03, or 350A121368.04, with a pitch horn, P/N 350A121368.XX, where XX stands for a two-digit dash number, installed. The pitch horn may be marked with either the pitch horn assembly P/N or pitch horn P/N.
For more information about this AD, contact Matt Fuller, AD Program Manager, Continued Operational Safety Branch, Airworthiness Products Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email