AD 2021-05-05

The FAA is superseding Airworthiness Directive (AD) 2016-23- 05, which applied to certain Airbus Helicopters Model SA-365N1, AS- 365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2016- 23-05 required repetitive checks of the oil level of the tail rotor gearbox and, if necessary, filling the oil to the maximum level; and replacement of a certain control rod double bearing (bearing) with a new bearing. This AD retains the requirements of AD 2016-23-05 and also requires modifying the helicopter by replacing the tail gearbox (TGB) control shaft guide bushes; repetitive inspections of the TGB magnetic plug and corrective actions if necessary; repetitive replacements of the bearing; and modifying the helicopter by replacing the TGB; as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. This AD also adds helicopters to the applicability. This AD was prompted by reports of occurrencesof loss of yaw control due to failure of the TGB bearing. 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 removing Airworthiness Directive (AD) 2016-23-05, Amendment 39-18712 (81 FR 85126, November 25, 2016), and adding the following new AD: \n\n2021-05-05 Airbus Helicopters: Amendment 39-21448 Docket No. FAA- 2020-1123; Project Identifier MCAI-2020-01294-R. \n\n(a) Effective Date \n\n\n\tThis airworthiness directive (AD) is effective April 16, 2021. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2016-23-05, Amendment 39-18712 (81 FR 85126, November 25, 2016) (AD 2016-23-05). \n\n(c) Applicability \n\n\n\tThis AD applies to Airbus Helicopters Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters, certificated in any category, all serial numbers. \n\n(d) Subject \n\n\n\tJoint Aircraft System Component (JASC) Code 65, Tail Rotor. \n\n(e) Reason \n\n\n\tThis AD was prompted by reports of occurrences of loss of yaw control due to failure of the tail gearbox (TGB) control rod double bearing (bearing). This AD was also prompted by the determination that additional inspections, replacements, and modifications are necessary to address the unsafe condition. The FAA is issuing this AD to address damage to the bearing, which could result in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter. \n\n(f) Compliance \n\n\n\tComply with this AD within the 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) AD2017-0125, dated July 21, 2017 (EASA AD 2017-0125). \n\n(h) Exceptions to EASA AD 2017-0125 \n\n\n\t(1) Where EASA AD 2017-0125 refers to its effective date, this AD requires using the effective date of this AD. \n\t(2) Where EASA AD 2017-0125 refers to June 4, 2011 (the effective date of EASA AD 2011-0105), this AD requires using the effective date of this AD. \n\t(3) Where EASA AD 2017-0125 refers to May 25, 2016 (the effective date of EASA AD 2016-0197R1), this AD requires using the effective date of this AD. \n\t(4) The ''Remarks'' section of EASA AD 2017-0125 does not apply to this AD. \n\t(5) Where paragraph (2) of EASA AD 2017-0125 requires inspections (checks) to be done ''in accordance with the instructions of Paragraph 3.B.1 of the applicable inspection ASB,'' for this AD, those instructions are for reference only and are not required for the actions in paragraph (2) of EASA AD 2017-0125. The inspections (checks) required by paragraph (2) of EASA AD 2017-0125 may be performed bythe owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. \n\t(6) Where paragraph (5) of EASA AD 2017-0125 specifies to ''accomplish the applicable corrective action(s) in accordance with the instructions of Paragraph 3.B.1 of the applicable inspection ASB,'' for this AD, a qualified mechanic must add oil to the TGB to the ''max'' level if the oil level is not at maximum. The instructions are for reference only and are not required for the actions in paragraph (5) of EASA AD 2017-0125. \n\t(7) Where EASA AD 2017-0125 refers to flight hours (FH), this AD requires using hours time-in-service. \n\t(8) Where EASA AD 2017-0125 requires action after the last flight of the day or ''ALF,'' this AD requires those actions before the first flight of theday. \n\t(9) Where the service information referred to in EASA AD 2017- 0125 specifies to perform a metallurgical analysis and contact the manufacturer if collected particles are not clearly characterized, this AD does not require contacting the manufacturer to determine the characterization of the particles collected. \n\t(10) Although service information referenced in EASA AD 2017- 0125 specifies to scrap parts, this AD does not include that requirement. \n\t(11) Although service information referenced in EASA AD 2017- 0125 specifies reporting information to Airbus Helicopters and filling in a ''particle detection'' follow-up sheet, this AD does not include those requirements. \n\t(12) Although service information referenced in EASA AD 2017- 0125 specifies returning certain parts to an approved workshop, this AD does not include that requirement. \n\t(13) Where paragraph (6) of EASA AD 2017-0125 refers to ''any discrepancy,'' for this AD, discrepancies include the presence of particles and other conditions such as abrasions, scales, flakes, and splinters. \n\n(i) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Strategic Policy Rotorcraft Section, 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 Strategic Policy Rotorcraft Section, send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110. Information may be emailed to: 9-ASW-FTW-AMOC-Requests@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(j) Related Information \n\n\n\tFor more information about this AD, contact Kathleen Arrigotti, Aviation Safety Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3218; email kathleen.arrigotti@faa.gov. \n\n(k) 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 2017-0125, dated July 21, 2017. \n\t(ii) (Reserved). \n\t(3) For EASA AD 2017-0125, 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 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. 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- 2020-1123. \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 fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\n((Page 13975)) \n\n\n\n\n\tIssued on February 17, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2021-05142 Filed 3-11-21; 8:45 am) BILLING CODE 4910-13-P

Discussion \n\n\n\tThe EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0125, dated July 21, 2017 (EASA AD 2017-0125) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus Helicopters Model SA 365 N1, AS 365 N2, AS 365 N3, SA 366 G1, EC 155 B, and EC 155 B1 helicopters. EASA AD 2017-0125 supersedes EASA AD 2017-0007, dated January 13, 2017, which superseded EASA AD 2016-0097R1, dated May 25, 2016 (which corresponds to FAA AD 2016-23-05). EASA AD 2017-0125 adds helicopters to the applicability, adds repetitive inspections of the magnetic plug after bearing replacement, requires the use of the revised Airbus Helicopters Alert Service Bulletin (ASB) instructions, and requires replacement of the TGB with a modified unit, which terminates the repetitive inspections. \n\tThe FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016-23-05, Amendment 39-18712 (81 FR 85126, November 25, 2016) (AD 2016-23-05). AD 2016-23-05 applied to certain Airbus Helicopters Model SA-365N1, AS-365N2, AS 365 N3, SA- 366G1, EC 155B, and EC155B1 helicopters. The NPRM published in the Federal Register on December 14, 2020 (85 FR 80689). The NPRM was prompted by a determination that additional inspections, replacements, and modifications are necessary to address the unsafe condition. The NPRM proposed to retain the requirements of AD 2016-23-05 and also require modifying the helicopter by replacing the TGB control shaft guide bushes; repetitive inspections of the TGB magnetic plug and corrective actions if necessary; repetitive replacements of the bearing; and modifying the helicopter by replacing the TGB; as specified in an EASA AD. The NPRM also proposed to add helicopters to the applicability. \n\n((Page 13973)) \n\n\n\tThe FAA is issuing this AD to address damage to the bearing, which could result in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter. See the MCAI for additional background information. \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\nUpdate to the Costs of Compliance \n\n\n\tThe FAA has updated the costs for the new required actions and on- condition actions based on data received since the NPRM was issued. \n\nConclusion \n\n\n\tThe FAA reviewed the relevant data 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: \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\nRelated Service InformationUnder 1 CFR Part 51 \n\n\n\tEASA AD 2017-0125 describes procedures for modifying the helicopter by replacing TGB control shaft guide bushes, repetitive inspections (checks) of the oil level of the tail rotor gearbox and, if necessary, filling the oil to the maximum level, repetitive inspections of the TGB magnetic plug for the presence of particles and corrective actions if necessary (corrective actions include removing the TGB, complying with certain work cards to address particles and other conditions such as abrasions, scales, flakes, and splinters, and replacing the bearing), repetitive replacements of the bearing; and modifying the helicopter by replacing the TGB. \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\nExplanation of Retained Requirements \n\n\n\tAlthough this AD does not explicitly restate the requirements of AD 2016-23-05, this AD retains certain requirements of AD 2016-23-05. Those requirements are referenced in paragraphs (2) and (5) of EASA AD 2017-0125, which, in turn, is referenced in paragraph (g) of this AD. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 52 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: \n\n\n\tEstimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- \n\tCost on U.S. \n\tAction Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Retained actions from AD 2016- 17 work-hours x $85 $1,125........... $2,570........... $133,640. \n\t23-05. per hour = $1,445. New actions.................... 71 work-hours x $85 Up to $155,300... Up to $161,335... Up to $8,389,420. \n\tper hour = $6,035. ---------------------------------------------------------------------------------------------------------------- \n\n\n\n\n\tEstimated Costs for Optional Actions ------------------------------------------------------------------------ \n\tCost per \n\tLabor cost Parts cost product ------------------------------------------------------------------------ Up to 8 work-hours x $85 per hour = $0 $680 \n\t$680................................. ------------------------------------------------------------------------ \n\n\n\n\n\tEstimated Costs of On-Condition Actions ------------------------------------------------------------------------ \n\tCost per \n\tLabor cost Parts cost product ------------------------------------------------------------------------ Up to 4 work-hours x $85 per hour = Up to $1,395 Up to $1,735 \n\t$340................................. ------------------------------------------------------------------------ \n\n\n\tAccording to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in this cost estimate. \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\n((Page 13974)) \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.