AD 2021-07-12

The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a reassessment of the flight control system. This AD requires modification of the cyclic stick, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the 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 adding the following new airworthiness directive: \n\n2021-07-12 Airbus Helicopters Deutschland GmbH: Amendment 39-21489; Docket No. FAA-2020-1173 Project Identifier MCAI-2020-00299-R. \n\n(a) Effective Date \n\n\n\tThis airworthiness directive (AD) is effective May 11, 2021. \n\n(b) Affected Airworthiness Directives (ADs) \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters, certificated in any category, with autopilot installed, having serial numbers (S/Ns) up to 1263 inclusive, 1265, and 2001 up to 2024 inclusive, but excluding S/N 2006, 2008, 2013, 2017, 2019, 2020, and 2022. \n\n\n\tNote 1 to Paragraph (c): Helicopters with an EC135P3H or EC135T3H designation are Model EC135P3 or EC135T3 helicopters, respectively. \n\n(d) Subject \n\n\n\tJoint Aircraft System Component (JASC) Code: 6700, Rotorcraft Flight Control. \n\n(e) Reason \n\n\n\tThis AD was prompted by a reassessment of the flight control system, which revealed that uncommanded disengagement of the main rotor trim actuators during flight with the autopilot engaged and hands-off controls could result in high roll and pitch rates requiring pilot intervention within a reaction time below that required by current airworthiness standards. The FAA is issuing this AD to require installing a cyclic stick weight compensation modification to correct this unsafe condition, which if not corrected, could result in subsequent loss of control of the helicopter. \n\n(f) Compliance \n\n\n\tComply with this AD withinthe compliance times specified, unless already done. \n\n(g) Requirements \n\n\n\tExcept as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2018-0063, dated March 22, 2018 (EASA AD 2018-0063). \n\n(h) Exceptions to EASA AD 2018-0063 \n\n\n\t(1) Where EASA AD 2018-0063 refers to its effective date, this AD requires using the effective date of this AD. \n\t(2) Where EASA AD 2018-0063 requires modifying the helicopter within 7 months, this AD requires modifying the helicopter within 200 hours time-in-service. \n\t(3) Although the service information referenced in EASA AD 2018- 0063 specifies to discard certain parts, this AD requires removing those parts from service instead. \n\t(4) The ''Remarks'' section of EASA AD 2018-0063 does not apply to this AD. \n\n(i) No Reporting Requirement \n\n\n\tAlthough the service informationreferenced in EASA AD 2018-0063 specifies to submit certain information to the manufacturer, this AD does not include that requirement. \n\n(j) Alternative Methods of Compliance (AMOCs): \n\n\n\t(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 manager of the International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. \n\t(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. \n\n(k) Related Information \n\n\n\tFor more information about this AD,contact Kristi Bradley, Aviation Safety Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email kristin.bradley@faa.gov. \n\n(l) 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 this AD specifies otherwise. \n\t(i) European Aviation Safety Agency (EASA) AD 2018-0063, dated March 22, 2018. \n\t(ii) (Reserved) \n\t(3) For EASA AD 2018-0063, 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. \n\t(4) You may view this service information at theFAA, 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. This material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA- 2020-1173. \n\t(5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email \n\n((Page 17708)) \n\nfedreg.legal@nara.gov, or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on March 24, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2021-06980 Filed 4-5-21; 8:45 am) BILLING CODE 4910-13-P

Discussion \n\n\n\tEASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0063, dated March 22, 2018 (EASA AD 2018-0063) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for Airbus Helicopters Deutschland GmbH (AHD) formerly Eurocopter Deutschland GmbH (ECD), Eurocopter Espa(ntilde)a S.A, Model EC135 P1, EC135 P2, EC135 P2+, EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 P3, EC635 T1, EC635 T2+ and EC635 T3 helicopters, all variants, all serial numbers (S/Ns) up to 1263 inclusive and S/N 1265, if equipped with autopilot, and S/N 2001 up to 2024 inclusive, except S/N 2006, 2008, 2013, 2017, 2019, 2020 and 2022. \n\tThe FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. The NPRM published in the Federal Register on January 19, 2021 (86 FR 5040). The NPRM was prompted by a reassessment of the flight control system, which revealed that uncommanded disengagement of the main rotor trim actuators during flight with the autopilot engaged and hands-off controls could result in high roll and pitch rates, which would require pilot intervention within a reaction time below that required by current airworthiness standards. The NPRM proposed to require installing a cyclic stick weight compensation modification to correct this unsafe condition, which if not corrected may lead to subsequent loss of control of the helicopter, as specified in an EASA AD. \n\nComments \n\n\n\tThe FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public. \n\nConclusion \n\n\n\tThe FAA reviewed the relevant data and determined that air safety and the public interestrequire adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: \n\tAre consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and \n\tDo not add any additional burden upon the public than was already proposed in the NPRM. \n\tThe FAA also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tEASA AD 2018-0063 describes procedures for modifying the helicopter by retrofitting the cyclic stick weight compensation. \n\tThis material 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\nDifferences Between This AD and the MCAI \n\n\n\tThe EASA AD applies to certain serial-numbered EC635-series helicopters with an autopilot installed, whereas this AD does not apply to the Model EC635-series helicopters because these models are not FAA type-certificated. The EASA AD requires a calendar compliance time, whereas this AD requires using hours time-in-service. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 331 helicopters of U.S. registry. Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates that operators may incur the following costs in order to comply with this AD. \n\tModifying the cyclic stick weight compensator takes about 8 work- hours and parts cost about $1,300 for an estimated cost of about $1,980 per \n\n((Page 17707)) \n\nmodification and $655,380 for the U.S. fleet. \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\nRegulatory Findings \n\n\n\tThis 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 affect intrastate 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.