AD 2020-24-07

The FAA is superseding Airworthiness Directive (AD) 2018-26-02 for Airbus Helicopters (previously Eurocopter France) Model AS350B3, EC130B4, and EC130T2 helicopters. AD 2018-26-02 required inspecting the pilot's and co-pilot's throttle twist for proper operation. This new AD retains the requirements of AD 2018-26-02 and adds calendar time compliance times for the required actions. This AD was prompted by a public comment that prompted additional review. The actions of this AD are intended to address an unsafe condition on these products.

Final rule.

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by: 0 a. Removing Airworthiness Directive (AD) 2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018); and 0 b. Adding the following new AD: \n\n2020-24-07 Airbus Helicopters: Amendment 39-21337; Docket No. FAA- 2020-0570; Product Identifier 2019-SW-121-AD. \n\n(a) Applicability \n\n\n\tThis airworthiness directive (AD) applies to the following Airbus Helicopters, certificated in any category: \n\t(1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the two-channel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine installed; \n\t(2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the two-channel FADEC and with new twist grip MOD 073773 installed; and \n\t(3) Model EC130T2 helicopters with an ARRIEL 2D engine installed. \n\n(b) Unsafe Condition \n\n\n\tThis AD defines the unsafe condition as failure of one of the two contactors, 53Ka or 53Kb, which can prevent switching from ''IDLE'' mode to ''FLIGHT'' mode during autorotation training making it impossible to recover from a practice autorotation and compelling the pilot to continue the autorotation to the ground. This condition could result in unintended touchdown to the ground at a flight-idle power setting during a practice autorotation, damage to the helicopter, and injury to occupants. \n\n(c) Affected ADs \n\n\n\tThis AD replaces AD 2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018). \n\n(d) Effective Date \n\n\n\tThis AD becomes effective January 12, 2021. \n\n(e) Compliance \n\n\n\tYou are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. \n\n(f) Required Actions \n\n\n\t(1) Before the next practice autorotation, within 100 hours time-in-service (TIS), or 6 months, whichever occurs first, inspect the wiring, perform an insulation test, inspect the pilot and copilot throttle twist grip controls, and test the pilot and copilot throttle twist grip controls for proper functioning by following the Accomplishment Instructions, paragraph 3.B.1 through 3.B.6, of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 2B1 engine; EASB No. 05.00.77, Revision 1, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 2D engine; EASB No. 05A009, Revision 3, dated June 15, 2015, for Model EC130B4 helicopters; or EASB No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 helicopters, as appropriate for your model helicopter. \n\t(2) Repeat the inspections in paragraph (f)(1) of this AD at intervals not to exceed the following compliance times. For purposes of this AD, salt laden conditions exist when a helicopter performs a flight from a takeoff and landing area, heliport, or airport less than 0.5 statute mile from salt water or performs a flight within 0.5 statute mile from salt water below an altitude of 1,000 ft. above ground or sea level. \n\t(i) For helicopters that have operated in salt laden conditions since the previous inspection required by this AD, at intervals not to exceed 330 hours TIS or 6 months, whichever occurs first. \n\t(ii) For helicopters that have not operated in salt laden conditions since the previous inspection required by this AD, at intervals not to exceed 660 hours TIS or 12 months, whichever occurs first. \n\n(g) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: GeorgeSchwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177; telephone 817-222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. \n\t(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. \n\n(h) Additional Information \n\n\n\tThe subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) AD No. 2017-0059, dated April 6, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2020-0570. \n\n(i) Subject \n\n\n\tJoint Aircraft Service Component (JASC) Code: 7697, Engine Control System Wiring. \n\n(j) Material Incorporated by Reference \n\n\n\t(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. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(3) The following service information was approved for IBR on February 2, 2017 (81 FR 95854, December 29, 2016). \n\t(i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3, dated June 15, 2015. \n\t(ii) Airbus Helicopters EASB No. 05A009, Revision 3, dated June 15, 2015. \n\n\n\tNote 1 to paragraph (j)(3): Airbus Helicopters EASB Nos. 05.00.61 and 05A009, both Revision 3 and dated June 15, 2015, are co-published as one document along with Airbus Helicopters EASB No. 05.00.41, Revision 2, dated June 15, 2015, which is not incorporated by reference in this AD. \n\n\n\t(4) The following service information was approved for IBR on January 30, 2019 (83 FR 66093, December 26, 2018). \n\t(i) Airbus Helicopters EASB No. 05.00.77, Revision 1, dated June 15, 2015. \n\t(ii) Airbus Helicopters EASB No. 05A014, Revision 1, dated June 15, 2015. \n\n\n\tNote 2 to paragraph (j)(4): Airbus Helicopters EASB Nos. 05.00.77 and 05A014, both Revision 1 and dated June 15, 2015, are co-published as one document along with Airbus Helicopters EASB No. 05.00.52, Revision 1, dated June 15, 2015, which is not incorporated by reference in this AD. \n\n\n\t(5) For service information identified in this AD, 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. \n\t(6) 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. For information on the availability of this material at the FAA,call 817-222-5110. \n\n((Page 78957)) \n\n\n\t(7) You may view this service information 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. \n\n\n\tIssued on November 17, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-26867 Filed 12-7-20; 8:45 am) BILLING CODE 4910-13-P

Discussion \n\n\n\tThe 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 \n\n((Page 78955)) \n\n073773 (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. \n\tAD 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. \n\nActions Since AD 2018-26-02 Was Issued \n\n\n\tAfter 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. \n\nComments \n\n\n\tThe 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. \n\nFAA's Determination \n\n\n\tThese 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 theunsafe 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. \n\nInterim Action \n\n\n\tThe FAA considers this AD to be an interim action. If final action is later identified, the FAA might consider further rulemaking then. \n\nDifferences Between This AD and the EASA AD \n\n\n\tThe 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. \n\tAdditionally, the EASA AD requires installing Airbus Helicopters MOD 074263; this AD does not as it does not correct the unsafe condition. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tThe 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). \n\tThe 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). \n\tThis 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. \n\nCosts of Compliance \n\n\n\tThe 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. \n\tInspecting 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. \n\nAuthority for This Rulemaking \n\n\n\tTitle 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. \n\tThe 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. \n\n((Page 78956)) \n\nRegulatory Findings \n\n\n\tThe 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. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a ''significant regulatory action'' under Executive Order 12866, \n\t(2) Will not affectintrastate aviation in Alaska, and \n\t(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. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.