Federal Register / Vol. 86, No. 64 / Tuesday, April 6, 2021 / Rules and Regulations 17703

approved AMOC, notify your appropriate of this material at NARA, email fedreg.legal@ www.regulations.gov by searching for principal inspector, or lacking a principal nara.gov, or go to: https://www.archives.gov/ and locating Docket No. FAA–2013– inspector, the manager of the responsible federal-register/cfr/ibr-locations.html. 0752; or in person at Docket Operations Flight Standards Office. Issued on February 8, 2021. between 9 a.m. and 5 p.m., Monday (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions Lance T. Gant, through Friday, except Federal holidays. from a manufacturer, the instructions must Director, Compliance & Airworthiness The AD docket contains this AD, the be accomplished using a method approved Division, Aircraft Certification Service. European Aviation Safety Agency (now by the Manager, Large Aircraft Section, [FR Doc. 2021–07003 Filed 4–5–21; 8:45 am] European Union Aviation Safety International Validation Branch, FAA; or BILLING CODE 4910–13–P Agency) (EASA) AD, any service EASA; or Airbus SAS’s EASA Design information that is incorporated by Organization Approval (DOA). If approved by reference, any comments received, and the DOA, the approval must include the DEPARTMENT OF TRANSPORTATION other information. The street address for DOA-authorized signature. Docket Operations is U.S. Department of (3) Required for Compliance (RC): Except Federal Aviation Administration as required by paragraphs (i) and (j)(2) of this Transportation, Docket Operations, AD, if any service information contains M–30, West Building Ground Floor, procedures or tests that are identified as RC, 14 CFR Part 39 Room W12–140, 1200 New Jersey those procedures and tests must be done to [Docket No. FAA–2013–0752; Product Avenue SE, Washington, DC 20590. comply with this AD; any procedures or tests Identifier 2009–SW–44–AD; Amendment 39– FOR FURTHER INFORMATION CONTACT: that are not identified as RC are 21490; AD 2021–07–13] Kristi Bradley, Aviation Safety Engineer, recommended. Those procedures and tests RIN 2120–AA64 General Aviation & Rotorcraft Section, that are not identified as RC may be deviated International Validation Branch, FAA, from using accepted methods in accordance with the operator’s maintenance or Airworthiness Directives; Pacific 10101 Hillwood Pkwy., Fort Worth, TX inspection program without obtaining Scientific Company Seat Restraint 76177; telephone (817) 222–5110; email approval of an AMOC, provided the System Rotary Buckle Assemblies [email protected]. procedures and tests identified as RC can be SUPPLEMENTARY INFORMATION: done and the airplane can be put back in an AGENCY: Federal Aviation airworthy condition. Any substitutions or Administration (FAA), DOT. Discussion changes to procedures or tests identified as ACTION: Final rule. The FAA issued a supplemental RC require approval of an AMOC. notice of proposed rulemaking (SNPRM) SUMMARY: (k) Related Information The FAA is adopting a new to amend 14 CFR part 39 by adding an airworthiness directive (AD) for certain AD that would apply to Pacific For more information about this AD, Pacific Scientific Company rotary contact Kathleen Arrigotti, Aerospace Scientific Company buckle part Engineer, Large Aircraft Section, buckle assemblies (buckles). This AD numbers (P/Ns) 1111430 and 1111475, International Validation Branch, FAA, 2200 requires inspecting each buckle all dash numbers. The SNPRM South 216th St., Des Moines, WA 98198; including its buckle handle vane, and published in the Federal Register on telephone and fax 206–231–3218; email depending on the results, removing the September 24, 2020 (85 FR 60100). The [email protected]. buckle from service and installing an FAA preceded the SNPRM with a notice (l) Material Incorporated by Reference airworthy buckle. This AD also of proposed rulemaking (NPRM) that prohibits installing the affected buckles. published in the Federal Register on (1) The Director of the Federal Register This AD was prompted by several approved the incorporation by reference September 5, 2013 (78 FR 54594). The (IBR) of the service information listed in this reports of cracked buckle handles. The NPRM proposed to require inspecting paragraph under 5 U.S.C. 552(a) and 1 CFR actions of this AD are intended to each buckle for a crack and the part 51. address an unsafe condition on these thickness of the buckle handle vane. (2) You must use this service information products. Depending on the inspection results, the as applicable to do the actions required by DATES: This AD is effective May 11, NPRM proposed to require replacing the this AD, unless this AD specifies otherwise. (3) The following service information was 2021. buckle. The NPRM also proposed to approved for IBR on May 11, 2021. The Director of the Federal Register prohibit installing an affected buckle on (i) European Union Aviation Safety Agency approved the incorporation by reference any helicopter or airplane. The SNPRM (EASA) AD 2020–0167, dated July 27, 2020. of a certain document listed in this AD proposed to the same requirements (ii) [Reserved] as of May 11, 2021. except with longer compliance times to (4) For EASA AD 2020–0167, contact the ADDRESSES: For service information accomplish the inspections. The EASA, Konrad-Adenauer-Ufer 3, 50668 identified in this final rule, contact SNPRM also corrected the name of Cologne, Germany; telephone +49 221 8999 Meggitt Services, 1785 Voyager Ave., Pacific Scientific Aviation Services to 000; email [email protected]; internet Pacific Scientific Company, updated the www.easa.europa.eu. You may find this Simi Valley, CA 93063, telephone 877– EASA AD on the EASA website at https:// 666–0712 or at CustomerResponse@ estimated costs of compliance, edited ad.easa.europa.eu. meggitt.com. You may view the the Applicability paragraph by adding a (5) You may view this material at the FAA, referenced service information at the note to clarify that an affected buckle Airworthiness Products Section, Operational FAA, Office of the Regional Counsel, could be included as a component of a Safety Branch, 2200 South 216th St., Des Southwest Region, 10101 Hillwood different part-numbered restraint system Moines, WA. For information on the Pkwy., Room 6N–321, Fort Worth, TX assembly and reference Appendix 1 of availability of this material at the FAA, call 76177. It is also available on the internet Pacific Scientific Service Bulletin SB 206–231–3195. This material may be found at https://www.regulations.gov by 25–1111432, dated May 22, 2007 (SB in the AD docket on the internet at https:// 25–1111432), which lists the P/Ns of www.regulations.gov by searching for and searching for and locating Docket No. locating Docket No. FAA–2020–0854. FAA–2013–0752. potentially affected restraint systems, updated the names of certain (6) You may view this material that is Examining the AD Docket incorporated by reference at the National potentially-affected Type Certificate Archives and Records Administration You may examine the AD docket on holders, and updated the contact (NARA). For information on the availability the internet at https:// information name and contact

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information from Pacific Scientific SA1751SW, which allows installation of proposal in the SNPRM and will neither Aviation Services to Meggitt Services. certain affected buckles on Mitsubishi increase the economic burden on any The NPRM was prompted by EASA MU–2B series aircraft. operator nor increase the scope of this AD 2007–0256, dated September 19, The FAA partially agrees. The FAA AD. 2007, issued by EASA, which is the agrees that affected buckles could be Technical Agent for the Member States installed on Mitsubishi Heavy Differences Between This AD and the EASA AD of the European Union, to correct an Industries, Ltd., Model MU–2B series unsafe condition for certain Pacific airplanes; however, the applicability The EASA AD applies to certain Scientific Company Seat Restraint only identifies possible installations on buckles used on certain restraint System Plastic Rotary Buckle Handles. airplanes and helicopters by ‘‘make’’ systems that are known to be installed According to EASA, Pacific Scientific and not ‘‘models.’’ Accordingly, the on, but not limited to, certain Company reported several instances of FAA has added Mitsubishi Heavy Eurocopter (now Airbus Helicopters) cracked handles on certain buckles with Industries, Ltd., to the list of airplanes model helicopters. The applicability of a date of manufacture from November that affected buckles could be installed the EASA AD is limited to rotorcraft 2004 through May 2007. Testing on on in the applicability of this final rule. only and is not intended for airplanes. Since the affected buckles may be buckles with a cracked handle indicated Extension of Compliance Time that in some circumstances, a load installed in other aircraft resulting in placed on the restraint system prevents MHIA requested extending the the same unsafe condition, this AD a strap from releasing as intended when compliance time to at least 12 months, applies to the same certain buckles, the buckle is rotated. EASA states in its as replacement parts could be in short which may be installed on but not AD that this failure to release is possible supply. MHIA states that it has limited to certain airplanes and when a passenger weighs more than 50 attempted to contact the product helicopters. This AD does not require kg (approximately 110 lbs.) and an support representative at Meggitt returning the unairworthy buckle aircraft is upside down. Services located in Simi Valley, CA in assembly to the manufacturer, and this order to obtain additional technical AD does not apply to spare parts that Comments information; however, no formal are not installed on an aircraft. Also, After the SNPRM was published, the response had been received from this AD applies to buckle P/Ns 1111430 FAA received comments from two Meggitt Services when MHIA submitted and 1111475, all dash numbers, and is commenters. this comment on November 9, 2020. not dependent on the restraint P/Ns. MHIA expressed concern that with The EASA AD requires inspecting the Request for Credit limited support from Meggitt Services, buckles within 30 days, whereas this NetJets QC requested that this AD owners and operators of affected AD requires inspecting the buckle allow credit for compliance with Cessna airplanes will have difficulty meeting handle for a crack within 6 months and Citation Service Letter (SL) 560–25–09, the compliance requirements because of the buckle handle vane thickness within Cessna Citation SL560XL–25–10, or a potential lack of sufficient 12 months instead. The EASA AD Cessna Citation SL750–25–15, each replacement parts. requires a repetitive inspection of each dated December 10, 2007. NetJets QC The FAA acknowledges MHIA’s buckle for cracks before any flight for up also requested that provisions be written concern about contacting Meggitt to 6 months following the effective date in the AD for logbook/Illustrated Parts Services and has re-confirmed that its of the EASA AD until the buckle is Catalog (IPC) research sign-off, since contact information is accurate. The replaced. This AD does not require an these buckles may not be installed on FAA disagrees with changing the inspection for cracks before any flight newly-manufactured aircraft. compliance time to inspect an affected for the 6 months until the affected The FAA disagrees with both buckle handle for a crack from 6 months buckles are replaced. The EASA AD requests. This AD is an appliance AD to 12 months based on a potential lack identifies suspect parts by date of that applies to Pacific Scientific of sufficient replacement parts. The manufacture, and this AD does not. Company buckles P/Ns 1111430 and FAA has not received any information Finally, the EASA AD allows for 1111475, all dash numbers, without to indicate that there is an insufficient marking a seat as ‘‘un-operative’’ and regard to date of manufacture, whereas number of replacement parts that would this AD does not. each SL distinguishes the affected parts necessitate extending the compliance Related Service Information Under 1 by date of manufacture. If an affected time from that stated in the proposed CFR Part 51 buckle is not installed on an aircraft, AD. then this AD does not apply, and credit The FAA reviewed SB 25–1111432, FAA’s Determination and provisions are not necessary to which specifies inspecting each buckle relieve this AD’s requirements for the These products have been approved P/Ns 1111430–XX and 1111475–XX concerned aircraft. However, this AD by EASA and are approved for operation with a date of manufacture between does not prohibit using maintenance in the United States. Pursuant to the November 2004 and May 2007, to records to determine if an affected FAA’s bilateral agreement with the identify whether the handle is one buckle is installed. Using an IPC is not European Union, EASA has notified the susceptible to cracking by checking the an acceptable method to determine an FAA of the unsafe condition described P/N on the reverse side of the buckle aircraft’s configuration. in its AD. The FAA is issuing this AD assembly or by measuring the thickness after evaluating all of the information of the handle vane. If the buckle is Addition of MU–2B Aircraft provided by EASA and determining the identified as a ‘‘suspect’’ buckle, this Mitsubishi Heavy Industries America, unsafe condition exists and is likely to service information provides procedures Inc. (MHIA) suggested that the FAA add exist or develop on other products and for removing the buckle and replacing it ‘‘Mitsubishi MU–2B series aircraft’’ to that air safety and the public interest with an acceptable buckle. Information the list of aircraft models that could be require adopting the AD requirements as in this service information also advises affected by this AD. MHIA stated that proposed with the changes described that buckles with a cracked handle Mitsubishi Heavy Industries, Ltd., holds previously. These changes are should be removed from service Supplemental Type Certificate No. consistent with the intent of the immediately.

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This service information is reasonably List of Subjects in 14 CFR Part 39 (2) Within 12 months, measure the available because the interested parties thickness of the buckle handle vane as Air transportation, Aircraft, Aviation depicted in Figure 3 of SB 25–1111432. If the have access to it through their normal safety, Incorporation by reference, course of business or by the means handle vane thickness is 0.125 inch or Safety. greater, before further flight, remove the identified in the ADDRESSES section. Adoption of the Amendment buckle from service and replace it with an Costs of Compliance airworthy buckle. Accordingly, under the authority (3) As of the effective date of this AD, do The FAA estimates that this AD will delegated to me by the Administrator, not install a buckle or a restraint system with affect 1,435 restraint systems installed the FAA amends 14 CFR part 39 as a buckle, P/N 1111430 or 1111475, all dash on aircraft of U.S. Registry. Labor rates follows: numbers, with a handle vane thickness of are estimated at $85 per work-hour. 0.125 inch or greater on any airplane or Based on these numbers, the FAA PART 39—AIRWORTHINESS helicopter. estimates that operators may incur the DIRECTIVES (f) Alternative Methods of Compliance following costs in order to comply with ■ (AMOCs) this AD. 1. The authority citation for part 39 continues to read as follows: (1) The Manager, International Validation Inspecting a buckle costs a minimal Branch, FAA, may approve AMOCs for this amount and takes a nominal amount of Authority: 49 U.S.C. 106(g), 40113, 44701. AD. Send your proposal to: Kristi Bradley, time. Replacing a buckle takes about 0.5 § 39.13 [Amended] Aviation Safety Engineer, General Aviation & work-hour and parts cost about $636 for Rotorcraft Section, International Validation ■ an estimated cost of $679 per buckle 2. The FAA amends § 39.13 by adding Branch, FAA, 10101 Hillwood Pkwy., Fort and up to $974,365 for the U.S. fleet. the following new airworthiness Worth, TX 76177; telephone (817) 222–5110; directive: email [email protected]. Authority for This Rulemaking 2021–07–13 Pacific Scientific Company: (2) For operations conducted under a 14 Amendment 39–21490; Docket No. CFR part 119 operating certificate or under Title 49 of the United States Code 14 CFR part 91, subpart K, the FAA suggests specifies the FAA’s authority to issue FAA–2013–0752; Product Identifier 2009–SW–44–AD. that you notify your principal inspector, or rules on aviation safety. Subtitle I, lacking a principal inspector, the manager of section 106, describes the authority of (a) Applicability the local flight standards district office or the FAA Administrator. Subtitle VII: This airworthiness directive (AD) applies certificate holding district office, before Aviation Programs, describes in more to Pacific Scientific Company rotary buckle operating any aircraft complying with this detail the scope of the Agency’s assembly (buckle), part numbers (P/Ns) AD through an AMOC. authority. 1111430 and 1111475, all dash numbers. (g) Additional Information The FAA is issuing this rulemaking These buckles may be installed on but not limited to Bombardier Inc., Learjet Inc., The subject of this AD is addressed in under the authority described in Mitsubishi Heavy Industries, Ltd., Textron European Aviation Safety Agency (now Subtitle VII, Part A, Subpart III, Section Aviation, Inc. (Type Certificate (TC) European Union Aviation Safety Agency) 44701: General requirements. Under previously held by Cessna Aircraft (EASA) AD 2007–0256, dated September 19, that section, Congress charges the FAA Company), and Viking Air Limited (TC 2007. You may view the EASA AD on the with promoting safe flight of civil previously held by de Havilland, Inc.) model internet at https://www.regulations.gov in aircraft in air commerce by prescribing airplanes and Airbus Helicopters (TC Docket No. FAA–2013–0752. regulations for practices, methods, and previously held by Eurocopter France) model (h) Subject procedures the Administrator finds helicopters, certificated in any category. Note 1 to paragraph (a): The rotary buckle Joint Aircraft Service Component (JASC) necessary for safety in air commerce. Code: 2500, Cabin Equipment/Furnishings. This regulation is within the scope of may be included as a component of a different part-numbered restraint system (i) Material Incorporated by Reference that authority because it addresses an assembly. Pacific Scientific Service Bulletin (1) The Director of the Federal Register unsafe condition that is likely to exist or SB 25–1111432, dated May 22, 2007 (SB 25– approved the incorporation by reference of develop on helicopters identified in this 1111432), Appendix 1, includes a list of the service information listed in this rulemaking action. these restraint system P/Ns. paragraph under 5 U.S.C. 552(a) and 1 CFR Regulatory Findings (b) Unsafe Condition part 51. (2) You must use this service information This AD will not have federalism This AD defines the unsafe condition as a as applicable to do the actions required by cracked rotary buckle handle, which could implications under Executive Order this AD, unless the AD specifies otherwise. prevent a strap from releasing as intended 13132. This AD will not have a (i) Pacific Scientific Service Bulletin SB when the buckle is rotated. substantial direct effect on the States, on 25–1111432, dated May 22, 2007. the relationship between the national (c) Effective Date (ii) [Reserved] government and the States, or on the This AD becomes effective May 11, 2021. (3) For service information identified in distribution of power and this AD, contact Meggitt Services, 1785 (d) Compliance responsibilities among the various Voyager Ave., Simi Valley, CA 93063, You are responsible for performing each telephone 877–666–0712 or at levels of government. [email protected]. For the reasons discussed above, I action required by this AD within the specified compliance time unless it has (4) You may view this service information certify that this AD: already been accomplished prior to that time. at the FAA, Office of the Regional Counsel, (1) Is not a ‘‘significant regulatory Southwest Region, 10101 Hillwood Pkwy., action’’ under Executive Order 12866, (e) Required Actions Room 6N–321, Fort Worth, TX 76177. For (2) Will not affect intrastate aviation (1) Within 6 months, inspect the buckle information on the availability of this in Alaska, and handle for a crack. If the buckle handle is material at the FAA, call 817–222–5110. (5) You may view this service information (3) Will not have a significant cracked, before further flight, remove the buckle as depicted in Figure 5 and by that is incorporated by reference at the economic impact, positive or negative, following the Procedures, paragraph 9, of SB National Archives and Records on a substantial number of small entities 25–1111432, and replace it with an airworthy Administration (NARA). For information on under the criteria of the Regulatory buckle, except you are not required to return the availability of this material at NARA, Flexibility Act. the removed buckle to Pacific Scientific. email [email protected], or go to: https://

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www.archives.gov/federal-register/cfr/ibr- by searching for and locating Docket No. airworthiness standards. The NPRM locations.html. FAA–2020–1173. proposed to require installing a cyclic stick weight compensation modification Issued on March 25, 2021. Examining the AD Docket Lance T. Gant, to correct this unsafe condition, which Director, Compliance & Airworthiness You may examine the AD docket on if not corrected may lead to subsequent Division, Aircraft Certification Service. the internet at https:// loss of control of the helicopter, as www.regulations.gov by searching for [FR Doc. 2021–06979 Filed 4–5–21; 8:45 am] specified in an EASA AD. and locating Docket No. FAA–2020– BILLING CODE 4910–13–P 1173; or in person at Docket Operations Comments between 9 a.m. and 5 p.m., Monday The FAA gave the public the DEPARTMENT OF TRANSPORTATION through Friday, except Federal holidays. opportunity to participate in developing The AD docket contains this final rule, this final rule. The FAA received no Federal Aviation Administration any comments received, and other comments on the NPRM or on the information. The address for Docket determination of the cost to the public. Operations is U.S. Department of 14 CFR Part 39 Conclusion Transportation, Docket Operations, [Docket No. FAA–2020–1173; Project M–30, West Building Ground Floor, The FAA reviewed the relevant data Identifier MCAI–2020–00299–R; Amendment Room W12–140, 1200 New Jersey and determined that air safety and the 39–21489; AD 2021–07–12] Avenue SE, Washington, DC 20590. public interest require adopting this final rule as proposed, except for minor RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: Kristi Bradley, Aviation Safety Engineer, editorial changes. The FAA has determined that these minor changes: Airworthiness Directives; Airbus General Aviation & Rotorcraft Section, • Are consistent with the intent that Helicopters Deutschland GmbH International Validation Branch, FAA, was proposed in the NPRM for Helicopters 10101 Hillwood Pkwy., Fort Worth, TX addressing the unsafe condition; and 76177; telephone 817–222–5110; email • AGENCY: Federal Aviation [email protected]. Do not add any additional burden Administration (FAA), DOT. upon the public than was already SUPPLEMENTARY INFORMATION: ACTION: Final rule. proposed in the NPRM. Discussion The FAA also determined that these changes will not increase the economic SUMMARY: The FAA is adopting a new EASA, which is the Technical Agent airworthiness directive (AD) for Airbus burden on any operator or increase the for the Member States of the European scope of this final rule. Helicopters Deutschland GmbH Model Union, has issued EASA AD 2018–0063, EC135P1, EC135P2, EC135P2+, dated March 22, 2018 (EASA AD 2018– Related Service Information Under 1 EC135P3, EC135T1, EC135T2, 0063) (also referred to as the Mandatory CFR Part 51 EC135T2+, and EC135T3 helicopters. Continuing Airworthiness Information, EASA AD 2018–0063 describes This AD was prompted by a or the MCAI), to correct an unsafe reassessment of the flight control procedures for modifying the helicopter condition for Airbus Helicopters by retrofitting the cyclic stick weight system. This AD requires modification Deutschland GmbH (AHD) formerly of the cyclic stick, as specified in a compensation. Eurocopter Deutschland GmbH (ECD), This material is reasonably available European Aviation Safety Agency (now Eurocopter Espan˜ a S.A, Model EC135 European Union Aviation Safety because the interested parties have P1, EC135 P2, EC135 P2+, EC135 P3, access to it through their normal course Agency) (EASA) AD, which is EC135 T1, EC135 T2, EC135 T2+, EC135 incorporated by reference. The FAA is of business or by the means identified T3, EC635 P2+, EC635 P3, EC635 T1, in the ADDRESSES section. issuing this AD to address the unsafe EC635 T2+ and EC635 T3 helicopters, condition on these products. all variants, all serial numbers (S/Ns) up Differences Between This AD and the DATES: This AD is effective May 11, to 1263 inclusive and S/N 1265, if MCAI 2021. equipped with autopilot, and S/N 2001 The EASA AD applies to certain The Director of the Federal Register up to 2024 inclusive, except S/N 2006, serial-numbered EC635-series approved the incorporation by reference 2008, 2013, 2017, 2019, 2020 and 2022. helicopters with an autopilot installed, of a certain document listed in this AD The FAA issued a notice of proposed whereas this AD does not apply to the as of May 11, 2021. rulemaking (NPRM) to amend 14 CFR Model EC635-series helicopters because ADDRESSES: For material incorporated part 39 by adding an AD that would these models are not FAA type- by reference (IBR) in this AD, contact apply to certain Model EC135P1, certificated. The EASA AD requires a the EASA, Konrad-Adenauer-Ufer 3, EC135P2, EC135P2+, EC135P3, calendar compliance time, whereas this 50668 Cologne, Germany; telephone +49 EC135T1, EC135T2, EC135T2+, and AD requires using hours time-in-service. 221 8999 000; email ADs@ EC135T3 helicopters. The NPRM easa.europa.eu; internet published in the Federal Register on Costs of Compliance www.easa.europa.eu. You may find this January 19, 2021 (86 FR 5040). The The FAA estimates that this AD material on the EASA website at https:// NPRM was prompted by a reassessment affects 331 helicopters of U.S. registry. ad.easa.europa.eu. You may view this of the flight control system, which Labor rates are estimated at $85 per material at the FAA, Office of the revealed that uncommanded work-hour. Based on these numbers, the Regional Counsel, Southwest Region, disengagement of the main rotor trim FAA estimates that operators may incur 10101 Hillwood Pkwy., Room 6N–321, actuators during flight with the the following costs in order to comply Fort Worth, TX 76177. For information autopilot engaged and hands-off with this AD. on the availability of this material at the controls could result in high roll and Modifying the cyclic stick weight FAA, call 817–222–5110. It is also pitch rates, which would require pilot compensator takes about 8 work-hours available in the AD docket on the intervention within a reaction time and parts cost about $1,300 for an internet at https://www.regulations.gov below that required by current estimated cost of about $1,980 per

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