AD 2020-24-07

This AD is effective January 12, 2021.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 2, 2017 (81 FR 95854, December 29, 2016), and January 30, 2019 (83 FR 66093, December 26, 2018).

For service information identified in this final rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may the view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-0570.

George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email george.schwab@faa.gov.

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018) (AD 2018-26-02), and add a new AD. AD 2018-26-02 applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters with an ARRIEL 2B1 engine with the two-channel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 (for Model AS350B3 helicopters) or MOD 073773 (for Model EC130B4 helicopters) installed, and Model AS350B3 and EC130T2 helicopters with an ARRIEL 2D engine installed. The NPRM published in the Federal Register on June 11, 2020 (85 FR 35604). The NPRM proposed to retain the inspection requirements of AD 2018-26-02 and include inspecting the wiring, performing an insulation test, inspecting the pilot and copilot throttle twist grip controls, and testing the pilot and copilot throttle twist grip controls for proper functioning. The NPRM also proposed to include calendar compliance times for the repetitive inspections at intervals depending on operating conditions.

AD 2018-26-02 was prompted by EASA AD No. 2017-0059, dated April 6, 2017, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advised that the switches in the engine “IDLE” or “FLIGHT” control system could be affected by the corrosive effects of a salt-laden atmosphere, which could lead to engine power loss. EASA advised that this condition, if not detected and corrected, could, in case of failure of the other switch, prevent the pilot from switching from “IDLE” to “FLIGHT” mode during training of autorotation landing, making aborting the autorotation impossible, resulting in unintended touchdown.

After AD 2018-26-02 was issued, the FAA received comments from one commenter requesting the FAA clarify why the compliance time for the repetitive inspections required in AD 2018-26-02 was given in terms of hours time-in-service (TIS) without also requiring calendar compliance times. The commenter stated that a lot of operators do not operate their aircraft 660 hours TIS in a year and asked whether the FAA is concerned with calendar time. The FAA agreed; since the unsafe condition involves corrosion, which has a direct relationship between calendar time and airworthiness, it is necessary to add calendar time compliance times for all required actions including the repetitive inspections.

The FAA gave the public the opportunity to participate in developing this final rule, but the FAA did not receive any comments on the NPRM or on the determination of the cost to the public.

These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA's bilateral agreement with the European Union, EASA has notified the FAA of the unsafe condition described in its AD. The FAA is issuing this AD after evaluating all of the information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of the same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

The FAA considers this AD to be an interim action. If final action is later identified, the FAA might consider further rulemaking then.

The EASA AD requires the initial inspections within 10 flight hours or 7 days; this AD requires compliance before the next autorotation training flight, 100 hours TIS, or 6 months, whichever occurs earlier, as the unsafe condition only occurs when transitioning the throttle in-flight from flight to idle and back to flight, such as during a practice autorotation.

Additionally, the EASA AD requires installing Airbus Helicopters MOD 074263; this AD does not as it does not correct the unsafe condition.

The FAA reviewed one document that co-publishes three Airbus Helicopters Emergency Alert Service Bulletin (EASB) identification numbers: No. 05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.41, Revision 2, dated June 15, 2015, for the non-FAA type certificated Model AS550C3 helicopter; and No. 05A009, Revision 3, dated June 15, 2015, for Model EC130B4 helicopters. EASB Nos. 05.00.61 and 05A009 are incorporated by reference in AD 2018-26-02 and are retained for the requirements of this AD. EASB No. 05.00.41 is not incorporated by reference in AD 2018-26-02 and is not incorporated by reference in this AD. This service information applies to helicopters with an ARRIEL 2B1 engine installed and describes procedures for a functional check and installation of protection for micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).

The FAA also reviewed one document that co-publishes three Airbus Helicopters EASB identification numbers: No. 05.00.77, Revision 1, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.52, Revision 1, dated June 15, 2015, for the non-FAA type certificated Model AS550C3 helicopter; and No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 helicopters. EASB Nos. 05.00.77 and 05A014 are incorporated by reference in AD 2018-26-02 and are retained for the requirements of this AD. EASB No. 05.00.52 is not incorporated by reference in AD 2018-26-02 and is not incorporated by reference in this AD. This service information applies to helicopters with an ARRIEL 2D engine installed and describes procedures for a check of the protection for micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).

This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.

The FAA estimates that this AD affects 617 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour.

Inspecting the wiring, performing an insulation test, inspecting the pilot and copilot throttle twist grip controls, and testing the pilot and copilot throttle twist grip controls takes about 4 work-hours, for an estimated cost of $340 per helicopter and $209,780 for the U.S. fleet per inspection cycle.

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 because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

The FAA has determined that 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.

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

1. The authority citation for part 39 continues to read as follows:

2. The FAA amends § 39.13 by:

a. Removing Airworthiness Directive (AD) 2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018); and

b. Adding the following new AD: