Airworthiness Directives; Airbus Helicopters, 78954-78957 [2020-26867]

Download as PDF 78954 Federal Register / Vol. 85, No. 236 / Tuesday, December 8, 2020 / Rules and Regulations period in the year prior to the assessment period. (c) Is a top-tier foreign savings and loan holding company on December 31 of the assessment period, with $100 billion or more in total consolidated assets, as determined based on the average of the foreign savings and loan holding company’s total consolidated assets reported for the assessment period on the reporting forms applicable during the assessment period, provided, however, that if any such company has filed only one reporting form during the assessment period, the Board shall use an average of the foreign savings and loan holding company’s total consolidated assets reported on that reporting form and on the reporting form for the corresponding period in the year prior to the assessment period, or (d) Is a nonbank financial company supervised by the Board. 5. Section 246.4 is amended by revising paragraph (c)(1) and by adding new paragraphs (d)(3) and (4) to read as follows: § 246.4 Assessments. * * * * * (c) Assessment rates. Assessment rates means, with regard to a given assessment period, the two rates published by the Board for the calculation of assessments for Category IV and ‘‘other’’ firms and for Category I, II, and III firms. (1)(i) The assessment rate for Category IV and ‘‘other’’ firms will be calculated according to this formula: Assessment rate = [(Net Assessment Basis × Category IV and ‘‘other’’ firms’ share of total assessable assets of all assessed companies) × (1¥S)] Category IV and ‘‘other’’ firms’ total assessable assets (ii) The assessment rate for Category I, II, and III firms will be calculated according to this formula: Assessment rate = [(Net Assessment Basis × Category I, II, and III firms’ share of total assessable assets of all assessed companies) + (Net Assessment Basis × Category IV and ‘‘other’’ firms’ share of total assessable assets × S)] Category I, II, and III firms’ total assessable assets * * * * * (d) * * * (3) Net Assessment Basis is the assessment basis, as defined by paragraph (d)(2), net of the total $50,000 base amount charged to all assessed companies. Net Assessment Basis = assessment basis¥(number of assessed companies × $50,000). (4) The variable S represents the estimated share of total costs attributable to changes in supervisory and regulatory responsibilities resulting from EGRRCPA for Category IV and ‘‘other’’ firms. S = 0.1 (10 percent). * * * * * SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018–26– 02 for Airbus Helicopters (previously Eurocopter France) Model AS350B3, EC130B4, and EC130T2 helicopters. AD 2018–26–02 required inspecting the pilot’s and co-pilot’s throttle twist for proper operation. This new AD retains the requirements of AD 2018–26–02 and adds calendar time compliance times for the required actions. This AD was prompted by a public comment that prompted additional review. The actions of this AD are intended to address an unsafe condition on these products. By order of the Board of Governors of the Federal Reserve System. Ann Misback, Secretary of the Board. DATES: [FR Doc. 2020–25623 Filed 12–7–20; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0570; Product Identifier 2019–SW–121–AD; Amendment 39–21337; AD 2020–24–07] jbell on DSKJLSW7X2PROD with RULES RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: VerDate Sep<11>2014 16:00 Dec 07, 2020 Jkt 253001 This AD is effective January 12, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 2, 2017 (81 FR 95854, December 29, 2016), and January 30, 2019 (83 FR 66093, December 26, 2018). 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 the view this 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– 0570. ADDRESSES: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2020–0570; 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 Aviation Safety Agency (now 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: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email george.schwab@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2018–26–02, Amendment 39–19532 (83 FR 66093, December 26, 2018) (AD 2018–26–02), and add a new AD. AD 2018–26–02 applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters with an ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 (for Model AS350B3 helicopters) or MOD E:\FR\FM\08DER1.SGM 08DER1 Federal Register / Vol. 85, No. 236 / Tuesday, December 8, 2020 / Rules and Regulations 073773 (for Model EC130B4 helicopters) installed, and Model AS350B3 and EC130T2 helicopters with an ARRIEL 2D engine installed. The NPRM published in the Federal Register on June 11, 2020 (85 FR 35604). The NPRM proposed to retain the inspection requirements of AD 2018–26–02 and include inspecting the wiring, performing an insulation test, inspecting the pilot and copilot throttle twist grip controls, and testing the pilot and copilot throttle twist grip controls for proper functioning. The NPRM also proposed to include calendar compliance times for the repetitive inspections at intervals depending on operating conditions. AD 2018–26–02 was prompted by EASA AD No. 2017–0059, dated April 6, 2017, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advised that the switches in the engine ‘‘IDLE’’ or ‘‘FLIGHT’’ control system could be affected by the corrosive effects of a saltladen atmosphere, which could lead to engine power loss. EASA advised that this condition, if not detected and corrected, could, in case of failure of the other switch, prevent the pilot from switching from ‘‘IDLE’’ to ‘‘FLIGHT’’ mode during training of autorotation landing, making aborting the autorotation impossible, resulting in unintended touchdown. Actions Since AD 2018–26–02 Was Issued After AD 2018–26–02 was issued, the FAA received comments from one commenter requesting the FAA clarify why the compliance time for the repetitive inspections required in AD 2018–26–02 was given in terms of hours time-in-service (TIS) without also requiring calendar compliance times. The commenter stated that a lot of operators do not operate their aircraft 660 hours TIS in a year and asked whether the FAA is concerned with calendar time. The FAA agreed; since the unsafe condition involves corrosion, which has a direct relationship between calendar time and airworthiness, it is necessary to add calendar time compliance times for all required actions including the repetitive inspections. jbell on DSKJLSW7X2PROD with RULES Comments The FAA gave the public the opportunity to participate in developing this final rule, but the FAA did not receive any comments on the NPRM or on the determination of the cost to the public. VerDate Sep<11>2014 16:00 Dec 07, 2020 Jkt 253001 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 of the information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of the same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action The FAA considers this AD to be an interim action. If final action is later identified, the FAA might consider further rulemaking then. Differences Between This AD and the EASA AD The EASA AD requires the initial inspections within 10 flight hours or 7 days; this AD requires compliance before the next autorotation training flight, 100 hours TIS, or 6 months, whichever occurs earlier, as the unsafe condition only occurs when transitioning the throttle in-flight from flight to idle and back to flight, such as during a practice autorotation. Additionally, the EASA AD requires installing Airbus Helicopters MOD 074263; this AD does not as it does not correct the unsafe condition. Related Service Information Under 1 CFR Part 51 The FAA reviewed one document that co-publishes three Airbus Helicopters Emergency Alert Service Bulletin (EASB) identification numbers: No. 05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.41, Revision 2, dated June 15, 2015, for the non-FAA type certificated Model AS550C3 helicopter; and No. 05A009, Revision 3, dated June 15, 2015, for Model EC130B4 helicopters. EASB Nos. 05.00.61 and 05A009 are incorporated by reference in AD 2018– 26–02 and are retained for the requirements of this AD. EASB No. 05.00.41 is not incorporated by reference in AD 2018–26–02 and is not incorporated by reference in this AD. This service information applies to helicopters with an ARRIEL 2B1 engine installed and describes procedures for a functional check and installation of protection for micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode). The FAA also reviewed one document that co-publishes three Airbus Helicopters EASB identification PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 78955 numbers: No. 05.00.77, Revision 1, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.52, Revision 1, dated June 15, 2015, for the non-FAA type certificated Model AS550C3 helicopter; and No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 helicopters. EASB Nos. 05.00.77 and 05A014 are incorporated by reference in AD 2018–26–02 and are retained for the requirements of this AD. EASB No. 05.00.52 is not incorporated by reference in AD 2018–26–02 and is not incorporated by reference in this AD. This service information applies to helicopters with an ARRIEL 2D engine installed and describes procedures for a check of the protection for microcontacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode). 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. Costs of Compliance The FAA estimates that this AD affects 617 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. Inspecting the wiring, performing an insulation test, inspecting the pilot and copilot throttle twist grip controls, and testing the pilot and copilot throttle twist grip controls takes about 4 workhours, for an estimated cost of $340 per helicopter and $209,780 for the U.S. fleet per inspection cycle. 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 products identified in this rulemaking action. E:\FR\FM\08DER1.SGM 08DER1 78956 Federal Register / Vol. 85, No. 236 / Tuesday, December 8, 2020 / Rules and Regulations Regulatory Findings The FAA has 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. 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 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: a. Removing Airworthiness Directive (AD) 2018–26–02, Amendment 39– 19532 (83 FR 66093, December 26, 2018); and ■ b. Adding the following new AD: ■ ■ jbell on DSKJLSW7X2PROD with RULES 2020–24–07 Airbus Helicopters: Amendment 39–21337; Docket No. FAA–2020–0570; Product Identifier 2019–SW–121–AD. (a) Applicability This airworthiness directive (AD) applies to the following Airbus Helicopters, certificated in any category: (1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the two-channel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine installed; (2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the two-channel FADEC and with new twist grip MOD 073773 installed; and (3) Model EC130T2 helicopters with an ARRIEL 2D engine installed. (b) Unsafe Condition This AD defines the unsafe condition as failure of one of the two contactors, 53Ka or VerDate Sep<11>2014 16:00 Dec 07, 2020 Jkt 253001 53Kb, which can prevent switching from ‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during autorotation training making it impossible to recover from a practice autorotation and compelling the pilot to continue the autorotation to the ground. This condition could result in unintended touchdown to the ground at a flight-idle power setting during a practice autorotation, damage to the helicopter, and injury to occupants. (c) Affected ADs This AD replaces AD 2018–26–02, Amendment 39–19532 (83 FR 66093, December 26, 2018). (d) Effective Date This AD becomes effective January 12, 2021. (e) 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. (f) Required Actions (1) Before the next practice autorotation, within 100 hours time-in-service (TIS), or 6 months, whichever occurs first, inspect the wiring, perform an insulation test, inspect the pilot and copilot throttle twist grip controls, and test the pilot and copilot throttle twist grip controls for proper functioning by following the Accomplishment Instructions, paragraph 3.B.1 through 3.B.6, of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 2B1 engine; EASB No. 05.00.77, Revision 1, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 2D engine; EASB No. 05A009, Revision 3, dated June 15, 2015, for Model EC130B4 helicopters; or EASB No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 helicopters, as appropriate for your model helicopter. (2) Repeat the inspections in paragraph (f)(1) of this AD at intervals not to exceed the following compliance times. For purposes of this AD, salt laden conditions exist when a helicopter performs a flight from a takeoff and landing area, heliport, or airport less than 0.5 statute mile from salt water or performs a flight within 0.5 statute mile from salt water below an altitude of 1,000 ft. above ground or sea level. (i) For helicopters that have operated in salt laden conditions since the previous inspection required by this AD, at intervals not to exceed 330 hours TIS or 6 months, whichever occurs first. (ii) For helicopters that have not operated in salt laden conditions since the previous inspection required by this AD, at intervals not to exceed 660 hours TIS or 12 months, whichever occurs first. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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. (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) AD No. 2017–0059, dated April 6, 2017. You may view the EASA AD on the internet at https:// www.regulations.gov in Docket No. FAA– 2020–0570. (i) Subject Joint Aircraft Service Component (JASC) Code: 7697, Engine Control System Wiring. (j) 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 the AD specifies otherwise. (3) The following service information was approved for IBR on February 2, 2017 (81 FR 95854, December 29, 2016). (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3, dated June 15, 2015. (ii) Airbus Helicopters EASB No. 05A009, Revision 3, dated June 15, 2015. Note 1 to paragraph (j)(3): Airbus Helicopters EASB Nos. 05.00.61 and 05A009, both Revision 3 and dated June 15, 2015, are co-published as one document along with Airbus Helicopters EASB No. 05.00.41, Revision 2, dated June 15, 2015, which is not incorporated by reference in this AD. (4) The following service information was approved for IBR on January 30, 2019 (83 FR 66093, December 26, 2018). (i) Airbus Helicopters EASB No. 05.00.77, Revision 1, dated June 15, 2015. (ii) Airbus Helicopters EASB No. 05A014, Revision 1, dated June 15, 2015. Note 2 to paragraph (j)(4): Airbus Helicopters EASB Nos. 05.00.77 and 05A014, both Revision 1 and dated June 15, 2015, are co-published as one document along with Airbus Helicopters EASB No. 05.00.52, Revision 1, dated June 15, 2015, which is not incorporated by reference in this AD. (5) 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. (6) 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. E:\FR\FM\08DER1.SGM 08DER1 Federal Register / Vol. 85, No. 236 / Tuesday, December 8, 2020 / Rules and Regulations (7) 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/ibrlocations.html. Issued on November 17, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–26867 Filed 12–7–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOUSING AND URBAN DEVELOPMENT 24 CFR Part 100 [Docket No. FR–6138–F–02] RIN 2529–AA99 Fair Housing Act Design and Construction Requirements; Adoption of Additional Safe Harbors Office of the Assistant Secretary for Fair Housing and Equal Opportunity, HUD. ACTION: Final rule. jbell on DSKJLSW7X2PROD with RULES AGENCY: SUMMARY: This rule amends HUD’s Fair Housing Act design and construction regulations by incorporating by reference the 2009 edition of the International Code Council (ICC) Accessible and Usable Buildings and Facilities (ICC A117.1–2009) standard, as a safe harbor. The Accessible and Usable Buildings and Facilities standard is a technical standard for the design of facilities that are accessible to persons with disabilities. This rule also designates the 2009, 2012, 2015 and 2018 editions of the International Building Code (IBC) as safe harbors under the Fair Housing Act. The IBC is a model building code and not law, but it was adopted as law by various states and localities. The IBC provides minimum standards for public safety, health, and welfare as they are affected by building construction. DATES: Effective Date: March 8, 2021. The incorporation by reference of certain publications listed in the rule is approved by the Director of the Federal Register as of March 8, 2021. The incorporation by reference of certain other publications listed in the rule is approved by the Director of the Federal Register as of November 24, 2008. FOR FURTHER INFORMATION CONTACT: Lynn Grosso, Director, Office of Enforcement, Office of Fair Housing and Equal Opportunity, Department of Housing and Urban Development, 451 VerDate Sep<11>2014 16:00 Dec 07, 2020 Jkt 253001 Seventh Street SW, Washington, DC 20410–2000; telephone number (202) 708–2333 (this is not a toll-free number). Hearing- or speech-impaired individuals may access this number via TTY by calling the toll-free Federal Information Relay Service at (800) 877– 8339. SUPPLEMENTARY INFORMATION: I. Background Title VIII of the Civil Rights Act of 1968, as amended, (42 U.S.C. 3601 et seq.) (the ‘‘Fair Housing Act’’ or ‘‘Act’’) prohibits discrimination in housing and housing-related transactions based on race, color, religion, national origin, sex, disability and familial status.1 The Act provides, inter alia, that unlawful discrimination against persons with disabilities includes the failure to design and construct covered multifamily dwellings for first occupancy after March 13, 1991, in a manner that ‘‘(1) the public and common use portions of such dwellings are readily accessible to and usable by handicapped persons; (2) all the doors designed to allow passage into and within all premises within such dwellings are sufficiently wide to allow passage by handicapped persons in wheelchairs; and (3) all premises within such dwellings contain the following features of adaptive design: (a) An accessible route into and through the dwelling; (b) light switches, electrical outlets, thermostats, and other environmental controls in accessible locations; (c) reinforcements in bathroom walls to allow later installation of grab bars; and (d) usable kitchens and bathrooms such that an individual in a wheelchair can maneuver about the space.’’ 2 The Fair Housing Act does not contain specific technical design criteria that need to be followed to comply with the design and construction requirements. It does provide, however, that compliance with the appropriate requirements of the ‘‘American National Standard for buildings and facilities providing accessibility and usability for physically handicapped people (commonly referred to as ANSI A117.1), suffices to satisfy the requirements of [42 U.S.C. 3604(f)(3)(C)(iii)],’’ which states the Act’s design and construction 1 The Fair Housing Act refers to people with ‘‘handicaps.’’ Subsequently, in the Americans with Disabilities Act of 1990 and other legislation, Congress adopted the term ‘‘persons with disabilities’’ or ‘‘disability,’’ which is the preferred usage. Accordingly, this document hereinafter uses the terms ‘‘persons with disabilities,’’ ‘‘disability,’’ or ‘‘disabled,’’ unless directly quoting the Fair Housing Act. 2 42 U.S.C. 3604(f)(3)(C). PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 78957 requirements for the interiors of covered multifamily dwellings. The Fair Housing Act directs HUD to ‘‘provide technical assistance to states and units of local government and other persons to implement [the design and construction requirements].’’ 3 On March 6, 1991 (56 FR 9472), HUD published the ‘‘Final Fair Housing Accessibility Guidelines’’ which set forth specific technical guidance for designing covered multifamily dwellings to be consistent with the Act. Section I of the Guidelines states, ‘‘[t]hese guidelines are intended to provide a safe harbor for compliance with the accessibility requirements of the Fair Housing Act.’’ On June 24, 1994 (59 FR 33362), HUD published its ‘‘Supplement to Notice of Fair Housing Accessibility Guidelines: Questions and Answers about the Guidelines.’’ HUD published a Fair Housing Act Design Manual (Design Manual) in 1996 that was reissued in 1998 with minor changes. The Design Manual is also a safe harbor for compliance with the Act.4 Since HUD published its Fair Housing Act final rule on January 23, 1989 (54 FR 3232), the ANSI A117.1 accessibility standard has been updated several times. HUD, as a member of the A117 Committee that updates the A117.1 standard, participates in these updates. HUD also periodically reviewed these updated standards, as part of its mandate to provide technical assistance to state and local governments to incorporate the Act’s design and construction requirements into their laws and procedures for review and approval of newly constructed multifamily dwellings. HUD published a final rule on October 24, 2008 (73 FR 63614) that incorporated by reference ICC/ANSI–2003 and clarified that compliance with the appropriate requirements of CABO/ANSI A117.1– 1992 and ICC/ANSI–1998 continued to meet the design and construction requirements of the Fair Housing Act. See 24 CFR 100.201a(b)(1). The 2008 final rule also updated the regulations to reference certain editions of the IBC as safe harbors for compliance with the accessibility requirements in the Fair Housing Act. HUD’s final rule codified these additional design and construction standards that HUD recognized as safe harbors at § 100.205(e). 3 42 U.S.C. 3604(f)(5)(C). Fair Housing Design Manual, August 1996, revised 1998, is available at https:// www.huduser.gov/portal/publications/PDF/ FAIRHOUSING/fairfull.pdf. 4 The E:\FR\FM\08DER1.SGM 08DER1

Agencies

[Federal Register Volume 85, Number 236 (Tuesday, December 8, 2020)]
[Rules and Regulations]
[Pages 78954-78957]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-26867]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0570; Product Identifier 2019-SW-121-AD; Amendment 
39-21337; AD 2020-24-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-26-02 
for Airbus Helicopters (previously Eurocopter France) Model AS350B3, 
EC130B4, and EC130T2 helicopters. AD 2018-26-02 required inspecting the 
pilot's and co-pilot's throttle twist for proper operation. This new AD 
retains the requirements of AD 2018-26-02 and adds calendar time 
compliance times for the required actions. This AD was prompted by a 
public comment that prompted additional review. The actions of this AD 
are intended to address an unsafe condition on these products.

DATES: This AD is effective January 12, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 2, 
2017 (81 FR 95854, December 29, 2016), and January 30, 2019 (83 FR 
66093, December 26, 2018).

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 the view this 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-2020-0570.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2020-0570; 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 Aviation 
Safety Agency (now 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: George Schwab, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
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 to remove AD 2018-26-02, Amendment 39-19532 (83 FR 66093, 
December 26, 2018) (AD 2018-26-02), and add a new AD. AD 2018-26-02 
applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters 
with an ARRIEL 2B1 engine with the two-channel Full Authority Digital 
Engine Control (FADEC) and with new twist grip modification (MOD) 
073254 (for Model AS350B3 helicopters) or MOD

[[Page 78955]]

073773 (for Model EC130B4 helicopters) installed, and Model AS350B3 and 
EC130T2 helicopters with an ARRIEL 2D engine installed. The NPRM 
published in the Federal Register on June 11, 2020 (85 FR 35604). The 
NPRM proposed to retain the inspection requirements of AD 2018-26-02 
and include inspecting the wiring, performing an insulation test, 
inspecting the pilot and copilot throttle twist grip controls, and 
testing the pilot and copilot throttle twist grip controls for proper 
functioning. The NPRM also proposed to include calendar compliance 
times for the repetitive inspections at intervals depending on 
operating conditions.
    AD 2018-26-02 was prompted by EASA AD No. 2017-0059, dated April 6, 
2017, issued by EASA, which is the Technical Agent for the Member 
States of the European Union. EASA advised that the switches in the 
engine ``IDLE'' or ``FLIGHT'' control system could be affected by the 
corrosive effects of a salt-laden atmosphere, which could lead to 
engine power loss. EASA advised that this condition, if not detected 
and corrected, could, in case of failure of the other switch, prevent 
the pilot from switching from ``IDLE'' to ``FLIGHT'' mode during 
training of autorotation landing, making aborting the autorotation 
impossible, resulting in unintended touchdown.

Actions Since AD 2018-26-02 Was Issued

    After AD 2018-26-02 was issued, the FAA received comments from one 
commenter requesting the FAA clarify why the compliance time for the 
repetitive inspections required in AD 2018-26-02 was given in terms of 
hours time-in-service (TIS) without also requiring calendar compliance 
times. The commenter stated that a lot of operators do not operate 
their aircraft 660 hours TIS in a year and asked whether the FAA is 
concerned with calendar time. The FAA agreed; since the unsafe 
condition involves corrosion, which has a direct relationship between 
calendar time and airworthiness, it is necessary to add calendar time 
compliance times for all required actions including the repetitive 
inspections.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule, but the FAA did not receive any comments on 
the NPRM or on the determination of the cost to the public.

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

Interim Action

    The FAA considers this AD to be an interim action. If final action 
is later identified, the FAA might consider further rulemaking then.

Differences Between This AD and the EASA AD

    The EASA AD requires the initial inspections within 10 flight hours 
or 7 days; this AD requires compliance before the next autorotation 
training flight, 100 hours TIS, or 6 months, whichever occurs earlier, 
as the unsafe condition only occurs when transitioning the throttle in-
flight from flight to idle and back to flight, such as during a 
practice autorotation.
    Additionally, the EASA AD requires installing Airbus Helicopters 
MOD 074263; this AD does not as it does not correct the unsafe 
condition.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes three Airbus 
Helicopters Emergency Alert Service Bulletin (EASB) identification 
numbers: No. 05.00.61, Revision 3, dated June 15, 2015, for Model 
AS350B3 helicopters; No. 05.00.41, Revision 2, dated June 15, 2015, for 
the non-FAA type certificated Model AS550C3 helicopter; and No. 05A009, 
Revision 3, dated June 15, 2015, for Model EC130B4 helicopters. EASB 
Nos. 05.00.61 and 05A009 are incorporated by reference in AD 2018-26-02 
and are retained for the requirements of this AD. EASB No. 05.00.41 is 
not incorporated by reference in AD 2018-26-02 and is not incorporated 
by reference in this AD. This service information applies to 
helicopters with an ARRIEL 2B1 engine installed and describes 
procedures for a functional check and installation of protection for 
micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
    The FAA also reviewed one document that co-publishes three Airbus 
Helicopters EASB identification numbers: No. 05.00.77, Revision 1, 
dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.52, 
Revision 1, dated June 15, 2015, for the non-FAA type certificated 
Model AS550C3 helicopter; and No. 05A014, Revision 1, dated June 15, 
2015, for Model EC130T2 helicopters. EASB Nos. 05.00.77 and 05A014 are 
incorporated by reference in AD 2018-26-02 and are retained for the 
requirements of this AD. EASB No. 05.00.52 is not incorporated by 
reference in AD 2018-26-02 and is not incorporated by reference in this 
AD. This service information applies to helicopters with an ARRIEL 2D 
engine installed and describes procedures for a check of the protection 
for micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT 
mode).
    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.

Costs of Compliance

    The FAA estimates that this AD affects 617 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.
    Inspecting the wiring, performing an insulation test, inspecting 
the pilot and copilot throttle twist grip controls, and testing the 
pilot and copilot throttle twist grip controls takes about 4 work-
hours, for an estimated cost of $340 per helicopter and $209,780 for 
the U.S. fleet per inspection cycle.

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 products identified in this rulemaking action.

[[Page 78956]]

Regulatory Findings

    The FAA has 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.
    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:
0
a. Removing Airworthiness Directive (AD) 2018-26-02, Amendment 39-19532 
(83 FR 66093, December 26, 2018); and
0
b. Adding the following new AD:

2020-24-07 Airbus Helicopters: Amendment 39-21337; Docket No. FAA-
2020-0570; Product Identifier 2019-SW-121-AD.

(a) Applicability

    This airworthiness directive (AD) applies to the following 
Airbus Helicopters, certificated in any category:
    (1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the 
two-channel Full Authority Digital Engine Control (FADEC) and with 
new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine 
installed;
    (2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the 
two-channel FADEC and with new twist grip MOD 073773 installed; and
    (3) Model EC130T2 helicopters with an ARRIEL 2D engine 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of one of the 
two contactors, 53Ka or 53Kb, which can prevent switching from 
``IDLE'' mode to ``FLIGHT'' mode during autorotation training making 
it impossible to recover from a practice autorotation and compelling 
the pilot to continue the autorotation to the ground. This condition 
could result in unintended touchdown to the ground at a flight-idle 
power setting during a practice autorotation, damage to the 
helicopter, and injury to occupants.

(c) Affected ADs

    This AD replaces AD 2018-26-02, Amendment 39-19532 (83 FR 66093, 
December 26, 2018).

(d) Effective Date

    This AD becomes effective January 12, 2021.

(e) 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.

(f) Required Actions

    (1) Before the next practice autorotation, within 100 hours 
time-in-service (TIS), or 6 months, whichever occurs first, inspect 
the wiring, perform an insulation test, inspect the pilot and 
copilot throttle twist grip controls, and test the pilot and copilot 
throttle twist grip controls for proper functioning by following the 
Accomplishment Instructions, paragraph 3.B.1 through 3.B.6, of 
Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 
05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3 
helicopters with an ARRIEL 2B1 engine; EASB No. 05.00.77, Revision 
1, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 
2D engine; EASB No. 05A009, Revision 3, dated June 15, 2015, for 
Model EC130B4 helicopters; or EASB No. 05A014, Revision 1, dated 
June 15, 2015, for Model EC130T2 helicopters, as appropriate for 
your model helicopter.
    (2) Repeat the inspections in paragraph (f)(1) of this AD at 
intervals not to exceed the following compliance times. For purposes 
of this AD, salt laden conditions exist when a helicopter performs a 
flight from a takeoff and landing area, heliport, or airport less 
than 0.5 statute mile from salt water or performs a flight within 
0.5 statute mile from salt water below an altitude of 1,000 ft. 
above ground or sea level.
    (i) For helicopters that have operated in salt laden conditions 
since the previous inspection required by this AD, at intervals not 
to exceed 330 hours TIS or 6 months, whichever occurs first.
    (ii) For helicopters that have not operated in salt laden 
conditions since the previous inspection required by this AD, at 
intervals not to exceed 660 hours TIS or 12 months, whichever occurs 
first.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: George Schwab, Aviation 
Safety Engineer, Safety Management Section, Rotorcraft Standards 
Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 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.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (now European Union Aviation Safety Agency) AD No. 2017-0059, 
dated April 6, 2017. You may view the EASA AD on the internet at 
https://www.regulations.gov in Docket No. FAA-2020-0570.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 7697, Engine 
Control System Wiring.

(j) 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 the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
February 2, 2017 (81 FR 95854, December 29, 2016).
    (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 05.00.61, Revision 3, dated June 15, 2015.
    (ii) Airbus Helicopters EASB No. 05A009, Revision 3, dated June 
15, 2015.

    Note 1 to paragraph (j)(3): Airbus Helicopters EASB Nos. 
05.00.61 and 05A009, both Revision 3 and dated June 15, 2015, are 
co-published as one document along with Airbus Helicopters EASB No. 
05.00.41, Revision 2, dated June 15, 2015, which is not incorporated 
by reference in this AD.

    (4) The following service information was approved for IBR on 
January 30, 2019 (83 FR 66093, December 26, 2018).
    (i) Airbus Helicopters EASB No. 05.00.77, Revision 1, dated June 
15, 2015.
    (ii) Airbus Helicopters EASB No. 05A014, Revision 1, dated June 
15, 2015.

    Note 2 to paragraph (j)(4): Airbus Helicopters EASB Nos. 
05.00.77 and 05A014, both Revision 1 and dated June 15, 2015, are 
co-published as one document along with Airbus Helicopters EASB No. 
05.00.52, Revision 1, dated June 15, 2015, which is not incorporated 
by reference in this AD.

    (5) 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.
    (6) 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.

[[Page 78957]]

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

    Issued on November 17, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-26867 Filed 12-7-20; 8:45 am]
BILLING CODE 4910-13-P


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