Airworthiness Directives; Airbus Helicopters, 63440-63443 [2020-22241]

Download as PDF 63440 Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2020–20–15 Airbus SAS: Amendment 39– 21271; Docket No. FAA–2020–0348; Product Identifier 2020–NM–054–AD. (a) Effective Date This AD is effective November 12, 2020. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus SAS airplanes specified in paragraphs (c)(1) through (7) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020– 0083, dated April 3, 2020 (‘‘EASA AD 2020– 0083’’). (1) Model A330–202, –203, –223, and –243 airplanes. (2) Model A330–223F and –243F airplanes. (3) Model A330–302, –303, –323, and –343 airplanes. (4) Model A330–941 airplanes. (5) Model A340–313 airplanes. (6) Model A340–541 airplanes. (7) Model A340–642 airplanes. khammond on DSKJM1Z7X2PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings. (e) Reason This AD was prompted by the results of laboratory tests on non-rechargeable lithium batteries installed in emergency locator transmitters (ELTs), which highlighted a lack of protection against currents of 28 volts DC or 115 volts AC that could lead to thermal runaway and a battery fire. The FAA is issuing this AD to address local (temporary) fires in non-rechargeable lithium batteries installed in ELTs, which could result in damage to the airplane and injury to occupants. VerDate Sep<11>2014 16:24 Oct 07, 2020 Jkt 253001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2020–0083. (h) Exceptions to EASA AD 2020–0083 (1) Where EASA AD 2020–0083 refers to its effective date, this AD requires using the effective date of this AD. (2) The ‘‘Remarks’’ section of EASA AD 2020–0083 does not apply to this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): For any service information referenced in EASA AD 2020–0083 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 telephone and fax 206–231–3229; email vladimir.ulyanov@faa.gov. (k) Material Incorporated by Reference (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. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2020–0083, dated April 3, 2020. (ii) [Reserved] (3) For information about EASA AD 2020– 0083, contact the EASA, Konrad-AdenauerUfer 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. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. 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–2020–0348. (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. Issued on September 24, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–22235 Filed 10–7–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0410; Product Identifier 2019–SW–030–AD; Amendment 39–21274; AD 2020–21–01] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS–365N2, AS 365N3, EC 155B, EC155B1, and SA– 365N1 helicopters. This AD requires modifying the main gearbox (MGB) tail rotor (T/R) drive flange installation. SUMMARY: E:\FR\FM\08OCR1.SGM 08OCR1 Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations This AD was prompted by several reported occurrences of loss of tightening torque of the Shur-Lok nut, which serves as a retainer of the T/R drive flange. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective November 12, 2020. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of November 12, 2020. ADDRESSES: 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 view the 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–2020–0410. khammond on DSKJM1Z7X2PROD with RULES Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0410; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Union Aviation Safety Agency (EASA) AD, any service information that is incorporated by reference, any comments received, and other information. The street address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, Airworthiness Products Section, General Aviation and Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email Matthew.Fuller@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model AS– 365N2, AS 365N3, EC 155B, EC155B1, and SA–365N1 helicopters with modification 0763B64 installed, except those with modification 0763C81. The NPRM published in the Federal VerDate Sep<11>2014 16:24 Oct 07, 2020 Jkt 253001 Register on April 23, 2020, (85 FR 22688). The NPRM proposed to require within 600 hours time-in-service, modifying the MGB T/R drive flange installation by removing the sliding flange from the flexible coupling and installing the sliding flange with aft output stop part number 365A32–7836– 20 added, as per helicopter model and configuration. The NPRM also proposed to require removing from service certain washers, degreasing the bolt threads, applying a sealant between the interlay mating surfaces, and applying torque to the nuts. The proposed requirements were intended to prevent loosening and disengagement of the Shur-Lok nut threads, possibly resulting in reduction of T/R drive control, rear transmission vibrations, and subsequent loss of control of the helicopter. The NPRM was prompted by EASA AD No. 2019–0046, dated March 11, 2019 (EASA AD 2019–0046), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale) Model SA 365 N1, AS 365 N2, AS 365 N3, EC 155 B, and EC 155 B1 helicopters, all serial numbers, with modification 0763B64 installed, except those with 07 63C81 installed. EASA advises of reported occurrences of loss of tightening torque of the Shur-Lok nut, which serves as a retainer of the T/R drive flange of the MGB. EASA also advises of subsequent investigation that determined that these occurrences were the result of failure of the Shur-Lok nut locking function, which is normally ensured by two anti-rotation tabs engaged into two slots at the end of the MGB output shaft pinion. EASA states this condition could lead to the loosening and disengagement of the Shur-Lok nut threads, possibly resulting in reduction of T/R drive control, rear transmission vibrations, and subsequent loss of control of the helicopter. To address this unsafe condition, EASA issued a series of ADs, initially with EASA AD No. 2014–0165, dated July 14, 2014 (EASA AD 2014–0165), which required a one-time inspection of the radial play inside the T/R drive flange and the condition of the Shur-Lok nut. Shortly after, EASA issued EASA AD No. 2014–0179, dated July 25, 2014 (EASA AD 2014–0179) to supersede EASA AD 2014–0165. EASA AD 2014– 0179 retained the requirements of EASA AD 2014–0165 and expanded the applicability of helicopters affected by the unsafe condition. EASA later revised EASA AD 2014–0179 to Revision 1, dated July 29, 2014, to revise the applicability and specify updated PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 63441 related service information, and again to Revision 2, dated April 11, 2016 (EASA AD 2014–0179R2), to reduce the applicability and specify additional updated related service information. Since EASA issued EASA AD 2014– 0179R2, another occurrence was reported that involved an on-ground loss of T/R synchronization, resulting from disengagement of the Shur-Lok nut. This additional occurrence prompted EASA to issue EASA AD 2019–0046 to require installation of modification 07 63C81, which consists of installing a rear output stop with 5 spigots on the T/R shaft flexible coupling. According to Airbus Helicopters, the 5 spigots will come into contact with the row of 5 bolt heads of the front T/R shaft if the T/R drive flange moves backwards. This contact limits backward displacement of the T/ R drive flange and subsequently prevents T/R drive flange disengagement. Comments The FAA gave the public the opportunity to participate in developing this AD, but the FAA did not receive any comments on the NPRM. FAA’s Determination 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 information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other products of the same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–63.00.19, for Model AS365N, N1, N2, and N3 helicopters and non FAA-type certificated military Model AS365F, Fi, Fs, K, and K2 helicopters; and Airbus Helicopters ASB No. EC155– 63A013 for Model EC155B and B1 helicopters, both Revision 1 and dated January 31, 2019. This service information specifies procedures for modification 0763C81 to install a rear (aft) output stop between the T/R drive flange and T/R drive shaft. 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. E:\FR\FM\08OCR1.SGM 08OCR1 63442 Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations Costs of Compliance The FAA estimates that this AD affects 46 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. Modifying the MGB T/R drive flange installation takes about 14 work-hours and parts cost about $2,704 for an estimated cost of $3,894 per helicopter and $179,124 for the U.S. fleet. Authority for This Rulemaking 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 helicopters identified in this rulemaking action. Regulatory Findings khammond on DSKJM1Z7X2PROD with RULES 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, VerDate Sep<11>2014 16:24 Oct 07, 2020 Jkt 253001 the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2020–21–01 Airbus Helicopters: Amendment 39–21274; Docket No. FAA–2020–0410; Product Identifier 2019–SW–030–AD. (a) Applicability This AD applies to Airbus Helicopters Model AS–365N2, AS 365N3, EC 155B, EC155B1, and SA–365N1 helicopters, certificated in any category, with modification 0763B64 installed, except those with modification 0763C81. (b) Unsafe Condition This AD defines the unsafe condition as loss of tightening torque of the Shur-Lok nut, which serves as a retainer of the tail rotor (T/ R) drive flange of the main gearbox. This condition could result in loss of the Shur-Lok nut, possibly resulting in disengagement of the T/R drive flange, reduction of T/R drive control, rear transmission vibrations, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective November 12, 2020. (d) Compliance You 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. (e) Required Actions Within 600 hours time-in-service: (1) For Model AS–365N2, AS 365N3, and SA–365N1 helicopters: (i) Without removing the tail drive shaft flange (a), remove the sliding flange (b) from the flexible coupling (c) as shown in Detail ‘‘B’’ of Figure 1, PRE MOD, of Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–63.00.19, Revision 1, dated January 31, 2019 (ASB AS365–63.00.19); replace the 3 bolts (d) and remove from service the 3 washers (e). (ii) Install the sliding flange (b) with aft output stop (1) part number (P/N) 365A32– 7836–20 as shown in Detail ‘‘B’’ of Figure 1, POST MOD, of ASB AS365–63.00.19 and by following the Accomplishment Instructions, paragraph 3.B.2.b, of ASB AS365–63.00.19. (2) For Model EC 155B and EC155B1 helicopters: (i) Without removing the Shur-Lok nut (a), remove the sliding flange (b) from the flexible coupling (c) as shown in Detail ‘‘B’’ of Figure 1, PRE MOD, of Airbus Helicopters ASB No. EC155–63A013, Revision 1, dated January 31, 2019 (ASB EC155–63A013); replace the 3 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 bolts (d) and remove from service the 3 washers (e). (ii) Install the sliding flange (b) with aft output stop (1) P/N 365A32–7836–20 as shown in Detail ‘‘B’’ of Figure 1, POST MOD, of ASB EC155–63A013 and by following the Accomplishment Instructions, paragraph 3.B.2.b, of ASB EC155–63A013. Note 1 to paragraph (e)(2)(ii): ASB EC155– 63A013 refers to the ‘‘aft output stop’’ as ‘‘rear output stop.’’ (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program Manager, Airworthiness Products Section, General Aviation and Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov. (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. (g) Additional Information The subject of this AD is addressed in European Union Aviation Safety Agency (EASA) AD No. 2019–0046, dated March 11, 2019. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA 2020–0410. (h) Subject Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor Drive System. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–63.00.19, Revision 1, dated January 31, 2019. (ii) Airbus Helicopters ASB No. EC155– 63A013, Revision 1, dated January 31, 2019. (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. (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. (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, E:\FR\FM\08OCR1.SGM 08OCR1 Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on September 29, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–22241 Filed 10–7–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0902; Project Identifier AD–2020–01174–E; Amendment 39–21273; AD 2020–20–17] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: khammond on DSKJM1Z7X2PROD with RULES Examining the AD Docket The FAA is adopting a new airworthiness directive (AD) for all General Electric Company GE90–110B1 and GE90–115B model turbofan engines. This AD was prompted by an in-service occurrence of loss of engine thrust control resulting in uncommanded high thrust. This AD prohibits dispatch of an airplane if certain status messages are displayed on the engine indicating and crew alerting system (EICAS) and if certain conditions are present per the manufacturer’s service information. As a terminating action, this AD requires revision of the existing FAA-approved minimum equipment list (MEL) by incorporating into the MEL the dispatch restrictions listed in this AD. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 23, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 23, 2020. The FAA must receive comments on this AD by November 23, 2020. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– SUMMARY: VerDate Sep<11>2014 16:24 Oct 07, 2020 Jkt 253001 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: aviation.fleetsupport@ge.com; website: www.ge.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0902. You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0902; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The street address for the Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Stephen Elwin, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7236; fax: 781–238–7199; email: stephen.l.elwin@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA received a report from the manufacturer of an in-service loss of engine thrust control that occurred on October 27, 2019, resulting in uncommanded high thrust. Analysis by the manufacturer found accumulated thermal cycles of the MN4 integrated circuit in the full authority digital engine control (FADEC) through normal operation causes the solder ball joints to wear out and eventually fail over time. The failure was preceded by an inbound FADEC EICAS ‘‘ENG EEC C1’’ status message one flight before the in-service occurrence. This condition, if not addressed, could result in loss of engine thrust control and reduced control of the airplane. The FAA is issuing this AD to address the unsafe condition on these products. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 63443 FAA’s Determination The FAA is issuing this AD because the agency evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed GE GE90–100 Service Bulletin (SB) 73–0117, R01, dated August 5, 2020. The SB describes procedures for checking for an inbound FADEC EICAS ‘‘ENG EEC C1’’ status message and corresponding conditions. 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. AD Requirements This AD prohibits dispatch of the airplane if certain status messages are displayed on the EICAS and if certain conditions are present per the manufacturer’s service information. As a terminating action, this AD requires, within 120 days of the effective date of this AD, revision of the existing FAAapproved MEL by incorporating into the MEL the dispatch restrictions listed in paragraph (g) of this AD. Interim Action The FAA considers this AD interim action. The manufacturer is still reviewing the unsafe condition and the FAA will consider further rulemaking. Justification for Immediate Adoption and Determination of the Effective Date Section 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 issuance. Further, Section 553(d) of the APA authorizes agencies to make rules effective in less than 30 days, upon a finding of good cause. An 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 foregoing notice and comment prior to adoption of this rule. On October 27, 2019, a Boeing Company Model 777–300 airplane powered by GE GE90–115B model turbofan engines experienced an E:\FR\FM\08OCR1.SGM 08OCR1

Agencies

[Federal Register Volume 85, Number 196 (Thursday, October 8, 2020)]
[Rules and Regulations]
[Pages 63440-63443]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22241]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0410; Product Identifier 2019-SW-030-AD; Amendment 
39-21274; AD 2020-21-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model AS-365N2, AS 365N3, EC 155B, EC155B1, 
and SA-365N1 helicopters. This AD requires modifying the main gearbox 
(MGB) tail rotor (T/R) drive flange installation.

[[Page 63441]]

This AD was prompted by several reported occurrences of loss of 
tightening torque of the Shur-Lok nut, which serves as a retainer of 
the T/R drive flange. The actions of this AD are intended to address an 
unsafe condition on these products.

DATES: This AD is effective November 12, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of November 12, 
2020.

ADDRESSES: 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 view the 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-
0410.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0410; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this AD, the European Union Aviation Safety Agency (EASA) AD, any 
service information that is incorporated by reference, any comments 
received, and other information. The street address for Docket 
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, 
Airworthiness Products Section, General Aviation and Rotorcraft Unit, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model AS-365N2, AS 365N3, EC 155B, EC155B1, and SA-365N1 helicopters 
with modification 0763B64 installed, except those with modification 
0763C81. The NPRM published in the Federal Register on April 23, 2020, 
(85 FR 22688). The NPRM proposed to require within 600 hours time-in-
service, modifying the MGB T/R drive flange installation by removing 
the sliding flange from the flexible coupling and installing the 
sliding flange with aft output stop part number 365A32-7836-20 added, 
as per helicopter model and configuration. The NPRM also proposed to 
require removing from service certain washers, degreasing the bolt 
threads, applying a sealant between the interlay mating surfaces, and 
applying torque to the nuts. The proposed requirements were intended to 
prevent loosening and disengagement of the Shur-Lok nut threads, 
possibly resulting in reduction of T/R drive control, rear transmission 
vibrations, and subsequent loss of control of the helicopter.
    The NPRM was prompted by EASA AD No. 2019-0046, dated March 11, 
2019 (EASA AD 2019-0046), issued by EASA, which is the Technical Agent 
for the Member States of the European Union, to correct an unsafe 
condition for Airbus Helicopters (formerly Eurocopter, Eurocopter 
France, Aerospatiale) Model SA 365 N1, AS 365 N2, AS 365 N3, EC 155 B, 
and EC 155 B1 helicopters, all serial numbers, with modification 
0763B64 installed, except those with 07 63C81 installed. EASA advises 
of reported occurrences of loss of tightening torque of the Shur-Lok 
nut, which serves as a retainer of the T/R drive flange of the MGB. 
EASA also advises of subsequent investigation that determined that 
these occurrences were the result of failure of the Shur-Lok nut 
locking function, which is normally ensured by two anti-rotation tabs 
engaged into two slots at the end of the MGB output shaft pinion. EASA 
states this condition could lead to the loosening and disengagement of 
the Shur-Lok nut threads, possibly resulting in reduction of T/R drive 
control, rear transmission vibrations, and subsequent loss of control 
of the helicopter.
    To address this unsafe condition, EASA issued a series of ADs, 
initially with EASA AD No. 2014-0165, dated July 14, 2014 (EASA AD 
2014-0165), which required a one-time inspection of the radial play 
inside the T/R drive flange and the condition of the Shur-Lok nut. 
Shortly after, EASA issued EASA AD No. 2014-0179, dated July 25, 2014 
(EASA AD 2014-0179) to supersede EASA AD 2014-0165. EASA AD 2014-0179 
retained the requirements of EASA AD 2014-0165 and expanded the 
applicability of helicopters affected by the unsafe condition. EASA 
later revised EASA AD 2014-0179 to Revision 1, dated July 29, 2014, to 
revise the applicability and specify updated related service 
information, and again to Revision 2, dated April 11, 2016 (EASA AD 
2014-0179R2), to reduce the applicability and specify additional 
updated related service information. Since EASA issued EASA AD 2014-
0179R2, another occurrence was reported that involved an on-ground loss 
of T/R synchronization, resulting from disengagement of the Shur-Lok 
nut. This additional occurrence prompted EASA to issue EASA AD 2019-
0046 to require installation of modification 07 63C81, which consists 
of installing a rear output stop with 5 spigots on the T/R shaft 
flexible coupling. According to Airbus Helicopters, the 5 spigots will 
come into contact with the row of 5 bolt heads of the front T/R shaft 
if the T/R drive flange moves backwards. This contact limits backward 
displacement of the T/R drive flange and subsequently prevents T/R 
drive flange disengagement.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD, but the FAA did not receive any comments on the 
NPRM.

FAA's Determination

    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 information provided by EASA and determining the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type designs and that air safety and the public interest 
require adopting the AD requirements as proposed.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS365-63.00.19, for Model AS365N, N1, N2, and N3 helicopters and 
non FAA-type certificated military Model AS365F, Fi, Fs, K, and K2 
helicopters; and Airbus Helicopters ASB No. EC155-63A013 for Model 
EC155B and B1 helicopters, both Revision 1 and dated January 31, 2019. 
This service information specifies procedures for modification 0763C81 
to install a rear (aft) output stop between the T/R drive flange and T/
R drive shaft.
    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.

[[Page 63442]]

Costs of Compliance

    The FAA estimates that this AD affects 46 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. Modifying the MGB T/R drive flange installation takes 
about 14 work-hours and parts cost about $2,704 for an estimated cost 
of $3,894 per helicopter and $179,124 for the U.S. fleet.

Authority for This Rulemaking

    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 helicopters identified in this rulemaking action.

Regulatory Findings

    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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2020-21-01 Airbus Helicopters: Amendment 39-21274; Docket No. FAA-
2020-0410; Product Identifier 2019-SW-030-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS-365N2, AS 365N3, 
EC 155B, EC155B1, and SA-365N1 helicopters, certificated in any 
category, with modification 0763B64 installed, except those with 
modification 0763C81.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of tightening 
torque of the Shur-Lok nut, which serves as a retainer of the tail 
rotor (T/R) drive flange of the main gearbox. This condition could 
result in loss of the Shur-Lok nut, possibly resulting in 
disengagement of the T/R drive flange, reduction of T/R drive 
control, rear transmission vibrations, and subsequent loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective November 12, 2020.

(d) Compliance

    You 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.

(e) Required Actions

    Within 600 hours time-in-service:
    (1) For Model AS-365N2, AS 365N3, and SA-365N1 helicopters:
    (i) Without removing the tail drive shaft flange (a), remove the 
sliding flange (b) from the flexible coupling (c) as shown in Detail 
``B'' of Figure 1, PRE MOD, of Airbus Helicopters Alert Service 
Bulletin (ASB) No. AS365-63.00.19, Revision 1, dated January 31, 
2019 (ASB AS365-63.00.19); replace the 3 bolts (d) and remove from 
service the 3 washers (e).
    (ii) Install the sliding flange (b) with aft output stop (1) 
part number (P/N) 365A32-7836-20 as shown in Detail ``B'' of Figure 
1, POST MOD, of ASB AS365-63.00.19 and by following the 
Accomplishment Instructions, paragraph 3.B.2.b, of ASB AS365-
63.00.19.
    (2) For Model EC 155B and EC155B1 helicopters:
    (i) Without removing the Shur-Lok nut (a), remove the sliding 
flange (b) from the flexible coupling (c) as shown in Detail ``B'' 
of Figure 1, PRE MOD, of Airbus Helicopters ASB No. EC155-63A013, 
Revision 1, dated January 31, 2019 (ASB EC155-63A013); replace the 3 
bolts (d) and remove from service the 3 washers (e).
    (ii) Install the sliding flange (b) with aft output stop (1) P/N 
365A32-7836-20 as shown in Detail ``B'' of Figure 1, POST MOD, of 
ASB EC155-63A013 and by following the Accomplishment Instructions, 
paragraph 3.B.2.b, of ASB EC155-63A013.

    Note 1 to paragraph (e)(2)(ii):  ASB EC155-63A013 refers to the 
``aft output stop'' as ``rear output stop.''

 (f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program 
Manager, Airworthiness Products Section, General Aviation and 
Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone 817-222-5110; email [email protected].
    (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.

(g) Additional Information

    The subject of this AD is addressed in European Union Aviation 
Safety Agency (EASA) AD No. 2019-0046, dated March 11, 2019. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
Docket No. FAA 2020-0410.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor 
Drive System.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-
63.00.19, Revision 1, dated January 31, 2019.
    (ii) Airbus Helicopters ASB No. EC155-63A013, Revision 1, dated 
January 31, 2019.
    (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.
    (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.
    (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,

[[Page 63443]]

email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-22241 Filed 10-7-20; 8:45 am]
BILLING CODE 4910-13-P