AD 2020-11-05

The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report of recurrent loss of tightening torque on several attachment bolts of the tail rotor hub body. This AD requires repetitive inspections of the tail rotor hub body for cracks and applicable corrective actions if necessary, and repetitive replacement of the attachment bolts, washers, and nuts of the tail rotor hub body. The FAA is issuing this AD to address the unsafe condition on these products.

Final rule; request for comments.

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 (AD): \n\n2020-11-05 Airbus Helicopters: Amendment 39-21130; Docket No. FAA- 2020-0455; Product Identifier 2019-SW-105-AD. \n\n(a) Effective Date \n\n\n\tThis AD becomes effective June 8, 2020. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to Airbus Helicopters Model EC120B helicopters, certificated in any category, all serial numbers. \n\n(d) Subject \n\n\n\tJoint Aircraft Service Component (JASC) Code 6400, Tail rotor system. \n\n(e) Reason \n\n\n\tThis AD was prompted by a report of recurrent loss of tightening torque on several attachment bolts on the tail rotor hub body. The FAA is issuing this AD to address this condition, which could lead to cracking and potential loss of the tail rotor drive and consequent loss of yaw 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) Definitions \n\n\n\t(1) For the purposes of this AD, an affected part is any tail rotor hub body part number C642A0100103. \n\t(2) For the purposes of this AD, a serviceable part is any affected part that is new (not previously installed on any helicopter); or any affected part on which an inspection has been done as specified in the instructions of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 0, dated October 29, 2019, or Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019, and there were no cracks. \n\n(h) Repetitive Inspection of the Tail Rotor Hub Body \n\n\n\tWithin 15 hours time-in-service (TIS) or 7 days, whichever occurs first after the effective date of this AD: Inspect the affected part (as defined in paragraph (g)(1) of this AD) for cracking in accordance with the instructions of section 3.B.2 of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. Thereafter, repeat the inspection at intervals not to exceed 15 hours TIS. \n\n(i) Corrective Actions \n\n\n\t(1) If, during any inspection required by paragraph (h) of this AD, there are any cracks, before next flight, replace the tail rotor hub body with a serviceable part (as defined in paragraph (g)(2) of this AD) and replace the bolts, washers, and nuts with new bolts, washers, and nuts, in accordance with the instructions of section 3.B.3 of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019, and inspect the tail rotor splined flange for the conditions identified in figure 1 to paragraph (i)(1) of this AD and at the areas identified in figure 2 to paragraph (i)(1) of this AD in accordance with the instructions of section 1.E.2 of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. \n\n\n\tNote 1 to paragraph (i)(1): You may refer to ''Detailed Check-- Splined Flange,'' Task 64-21-00, 6-5, Airbus Aircraft Maintenance Manual (AMM) Version B, dated April 7, 2014, which pertains to the tail rotor splined flange inspection. \n\n\n\n((Page 31045)) \n\n\n\n(GRAPHIC) (TIFF OMITTED) TR22MY20.000 \n\n(GRAPHIC) (TIFF OMITTED) TR22MY20.001 \n\n\n\t(2) If, during any inspection of the tail rotor splined flange required by paragraph (i)(1) of this AD, the condition of the part exceeds the criteria as specified in figure 1 to paragraph (i)(1) of this AD, before next flight, replace the tail rotor splined flange with an airworthy tail rotor splined flange in accordance with the instructions of section 3.B.4 of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. \n\n(j) Replacement of Attachment Bolts, Washers, and Nuts of the Tail Rotor Hub Body \n\n\n\tWithin the applicable compliance time specified in figure 3 to paragraph (j) of this AD, replace the attachment bolts, washers, \n\n((Page 31046)) \n\nand nuts of the tail rotor hub body with new bolts, washers, and nuts in accordance with the instructions of Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. Thereafter, repeat the replacement of the bolts, washers, and nuts at intervals not to exceed 1,000 hours TIS. (GRAPHIC) (TIFF OMITTED) TR22MY20.002 \n\n\n\t(k) Parts Installation Limitation \n\n\n\tAs of the effective date of this AD, it is allowed to install on any helicopter an affected part, provided it is a serviceable part, as defined in paragraph (g) of this AD. \n\n(l) Credit for Previous Actions \n\n\n\tThis paragraph provides credit for actions required by paragraphs (h) through (j) of this AD, if those actions wereperformed before the effective date of this AD using Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 0, dated October 29, 2019. \n\n(m) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 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, 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(n) Related Information \n\n\n\tThe subject of this AD is addressed in European Union Aviation Safety Agency (EASA) AD 2019-0272R1, dated November 18, 2019. This EASA AD may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA- 2020-0455. \n\n(o) 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) Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. \n\t(ii) (Reserved) \n\t(3) 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(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. \n\t(5) 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 May 18, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-11082 Filed 5-21-20; 8:45 am) \n\tBILLING 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 2019-0272R1, dated November 18, 2019 (referred to after this as the Mandatory Continuing Airworthiness Information or ''the MCAI''), to correct an unsafe condition for all Airbus Helicopters EC120B helicopters. EASA advises that an inspection of the tail rotor hub body revealed a recurring loss of tightening torque on several attachment bolts. EASA advises that this condition, if not detected and corrected, could lead to cracking and potential loss of the tail rotor drive and consequent loss of yaw control of the helicopter. The MCAI requires repetitive inspections of the tail rotor hub body for cracks and applicable corrective actions if necessary, as well as repetitive replacement of the associated attachment bolts, washers, and nuts. \n\tYou may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searchingfor and locating Docket No. FAA-2020-0455. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tAirbus Helicopters has issued Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. This service information describes procedures for repetitive inspections of the tail rotor hub body for cracks and applicable corrective actions if necessary, and repetitive replacement of the attachment bolts, washers, and nuts of the tail rotor hub body. Corrective actions include replacing the tail rotor hub body and associated bolts, washers, and nuts, and an inspection of the splined flange and the tail rotor hub body, and, if necessary, replacing the splined flange. \n\tThis service information is reasonably available because the interested parties \n\n((Page 31043)) \n\nhave access to it through their normal course of business or by the means identified in the ADDRESSES section. \n\nOther Related Service Information \n\n\n\tAirbus Helicopters has issued Emergency Alert Service Bulletin 05A020, Revision 0, dated October 29, 2019. The actions specified in this service bulletin are the same as those specified in Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019. However, Airbus Helicopters Emergency Alert Service Bulletin 05A020, Revision 1, dated November 8, 2019, revised the compliance time for repetitive inspections of the tail rotor hub body for cracks from within every 15 hours time-in-service (TIS) but not to exceed 7 days, to within every 15 hours TIS. \n\tAirbus has issued ''Detailed Check--Splined Flange,'' Task 64-21- 00, 6-5, Airbus Aircraft Maintenance Manual (AMM), Version B, dated April 7, 2014. This service information describes inspection criteria and inspection areas for a detailed check of the tail rotor splined flange. \n\nFAA's Determination \n\n\n\tThis product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA'sbilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI and service information referenced above. The FAA is issuing this AD after evaluating all pertinent information and determining the unsafe condition exists and is likely to exist or develop on other products of the same type design. \n\nRequirements of This AD \n\n\n\tThis AD requires accomplishing the actions specified in the service information described previously, except as discussed under ''Differences Between this AD and the MCAI or Service Information.'' \n\nDifferences Between This AD and the MCAI \n\n\n\tWhere Note 1 of the MCAI allows a non-cumulative tolerance of 100 hours TIS to be applied to the compliance times for the initial replacement of bolts, washers, and nuts (Table 1 of the MCAI) to allow for synchronization of the required inspections with other maintenance tasks, this AD does not allow a non-cumulative tolerance of 100 hours TIS to be applied to the compliance times for the initial replacement of bolts, washers, and nuts (Figure 3 to paragraph (j) of this AD). \n\nFAA's Justification for Immediate Adoption and Determination of the Effective Date \n\n\n\tSection 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ''good cause,'' finds that those procedures are ''impracticable, unnecessary, or contrary to the public interest.'' Under this section, an agency, upon finding good cause, may issue a final rule without seeking comment prior to the rulemaking. Similarly, Section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. \n\tAn unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving noticeand comment prior to adoption of this rule because recurrent loss of tightening torque on several tail rotor hub body attachment bolts could lead to cracking and potential loss of the tail rotor drive and consequent loss of yaw control of the helicopter. The FAA determined a compliance time of 15 hours TIS or 7 days, whichever occurs first, is required to correct the unsafe condition. This compliance time is shorter than the time necessary for the public to comment and for publication of the final rule. \n\tAccordingly, notice and opportunity for prior public comment are impracticable pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the reasons stated above, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days. \n\nComments Invited \n\n\n\tThis AD is a final rule that involves requirements affecting flight safety, and the FAA did not precede it by notice and opportunity for public comment. However, the FAA invites you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ''Docket No. FAA-2020-0455; Product Identifier 2019-SW-105-AD'' at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this AD. The FAA will consider all comments received by the closing date and may amend this AD based on those comments. \n\tThe FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact received about this AD. \n\nRegulatory Flexibility Act \n\n\n\tThe requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 90 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 per Cost on U.S. \n\tLabor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- 1 work-hour x $85 per hour = $85............................. $0 $85 $7,650 ---------------------------------------------------------------------------------------------------------------- \n\n\n\tThe FAA has received no definitive data that would enable it to provide cost estimates for the on-condition actions specified in this AD. \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 \n\n((Page 31044)) \n\n44701: 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\tThe FAA 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 and \n\t(2) Will not affect intrastate aviation in Alaska. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.