Airworthiness Directives; Airbus Helicopters, 19080-19082 [2020-07138]

Download as PDF 19080 Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9-ASW-FTWAMOC-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 (previously European Aviation Safety Agency) (EASA) AD No. 2017–0189, dated September 22, 2017. You may view the EASA AD on the internet at https:// www.regulations.gov in Docket No. FAA– 2018–0019. (h) Subject Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor Gearbox. (i) Material Incorporated by Reference jbell on DSKJLSW7X2PROD with RULES (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 Emergency Alert Service Bulletin (EASB) No. 01.00.86, Revision 1, dated August 25, 2017. (ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated August 25, 2017. (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 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, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on March 25, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–07140 Filed 4–3–20; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:25 Apr 03, 2020 Jkt 250001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–1015; Product Identifier 2018–SW–104–AD; Amendment 39–19882; AD 2020–06–13] 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 Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires determining the accumulated hours time-in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment fittings (fittings) and bolts, and establishes new life limits. This AD was prompted by the outcome of tests and analyses performed by Airbus Helicopters. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective May 11, 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. SUMMARY: Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2019–1015; 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 (previously European Aviation Safety Agency) (EASA) AD, 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, Senior Aviation Safety Engineer, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On December 9, 2019, at 84 FR 67246, the Federal Register published the FAA’s notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, with an MGB suspension bar right-hand side (RH) rear fitting part number (P/N) 330A22–2702– 07 and bolt P/N 330A22–0135–20, MGB suspension bar left-hand side (LH) rear fitting P/N 330A22–2702–06 and bolt P/ N 330A22–0135–20, or MGB suspension bar front bolt P/N 330A22–0134–20 installed. The NPRM proposed to require within 50 hours TIS, reviewing the helicopter records to determine the total hours TIS of the MGB suspension bar RH and LH rear fittings. The NPRM also proposed to require removing from service the RH rear fitting and its bolts and the LH rear fitting and its bolts based on the accumulated total hours TIS of the fittings and other conditions. Thereafter, the NPRM proposed to require removing from service the RH rear fitting and its bolts at intervals not to exceed 1,470 hours TIS, removing from service the LH rear fitting at intervals not to exceed 13,600 hours TIS, and removing from service the LH rear bolts during each Major Inspection ‘‘G.’’ Finally, the NPRM proposed to require removing from service the front bolts during each Major Inspection ‘‘G.’’ The proposed requirements were intended to prevent structural failure of the MGB suspension bar fittings and bolts, possibly resulting in detachment of the MGB suspension bars. The NPRM was prompted by EASA AD No. 2018–0260, dated December 3, 2018, 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 AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. From review of reported Model EC 225 LP data, EASA advises that the installation of the MGB upper deck fittings of the three MGB suspension bars could lead to tightening torque loss on the fittings’ attachment screws (bolts). Due to design similarities, Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters could also be affected by the same installation condition. E:\FR\FM\06APR1.SGM 06APR1 Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations Investigations determined that a life limit reduction of the MGB suspension bar fittings and screws was necessary for these model helicopters. EASA states that this condition, if not corrected, could lead to structural failure of the MGB suspension bar fittings and screws, possibly resulting in detachment of the MGB suspension bars. Accordingly, the EASA AD requires determining the accumulated service life of the affected parts and introduced new life limits. 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 helicopters of these 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. The design approval holder is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, the FAA might consider additional rulemaking. jbell on DSKJLSW7X2PROD with RULES Differences Between This AD and the EASA AD The EASA AD allows an option for the first MGB RH rear fitting replacement to inspect torque and specifies different replacement compliance times based on the torque inspection results, whereas this AD does not. Related Service Information The FAA reviewed Airbus Helicopters Alert Service Bulletin No. AS332– 01.00.90, Revision 0, dated November 21, 2018. This service information specifies determining the accumulated hours TIS of certain part-numbered rear MGB suspension bar fittings and screws. This service information further specifies criteria to determine the initial replacement compliance time of those parts and a new life limit for those parts VerDate Sep<11>2014 16:25 Apr 03, 2020 Jkt 250001 thereafter. This service information also establishes a life limit for the front MGB attachment screws. Costs of Compliance The FAA estimates that this AD affects 14 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. Determining the total hours TIS of the rear MGB fittings takes about 0.5 workhour for an estimated cost of $43 per helicopter and $602 for the U.S. fleet. Replacing a rear MGB fitting and its set of four bolts takes about 8 workhours and parts cost about $12,937, for an estimated cost of $13,617 per replacement cycle. Replacing a set of four MGB attachment bolts takes about 4 workhours and parts cost about $224, for an estimated cost of $564 per replacement cycle. Replacing a LH rear MGB fitting takes about 8 work-hours and parts cost about $12,713, for an estimated cost of $13,393 per replacement 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 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, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 19081 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 adding the following new airworthiness directive (AD): ■ 2020–06–13 Airbus Helicopters: Amendment 39–19882; Docket No. FAA–2019–1015; Product Identifier 2018–SW–104–AD. (a) Applicability This AD applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, certificated in any category, with a main gearbox (MGB) suspension bar right-hand side (RH) rear attachment fitting (fitting) part number (P/N) 330A22–2702–07 and bolt P/N 330A22– 0135–20, MGB suspension bar left-hand side (LH) rear fitting P/N 330A22–2702–06 and bolt P/N 330A22–0135–20, or MGB suspension bar front bolt P/N 330A22–0134– 20 installed. (b) Unsafe Condition This AD defines the unsafe condition as MGB suspension bar fittings and bolts remaining in service beyond their fatigue life. This condition could result in failure of an MGB attachment assembly, detachment of an MGB suspension bar, and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective May 11, 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 (1) Within 50 hours time-in-service (TIS), review records to determine the total hours TIS of each MGB suspension bar RH and LH rear fitting. (i) For any RH rear fitting that has accumulated 1,470 or more total hours TIS, E:\FR\FM\06APR1.SGM 06APR1 19082 Federal Register / Vol. 85, No. 66 / Monday, April 6, 2020 / Rules and Regulations before further flight, remove from service the RH rear fitting and its bolts. (ii) For any RH rear fitting that has accumulated less than 1,470 total hours TIS, remove from service the RH rear fitting and its bolts before the fitting accumulates 1,470 total hours TIS. (iii) For any LH rear fitting that has accumulated 13,600 or more total hours TIS, before further flight, remove from service the LH rear fitting and its bolts. (iv) For any LH rear fitting that has accumulated less than 13,600 total hours TIS: (A) If a Major Inspection ‘‘G’’ has not been completed since the LH rear fitting has been installed, remove from service the LH rear bolts during the next Major Inspection ‘‘G’’ inspection; or Note 1 to paragraph (e)(1)(iv)(A) of this AD: Major Inspection ‘‘G’’ (7,500 hours TIS between overhauls) is defined in Maintenance Manual MET 05–29–00–601. (B) If a Major Inspection ‘‘G’’ has been completed since the LH rear fitting has been installed, before further flight, remove from service the LH rear bolts; and (C) Remove from service the LH rear fitting before the fitting accumulates 13,600 total hours TIS. (2) Thereafter following paragraph (e)(1) of this AD, remove from service any RH rear fitting and its bolts at intervals not to exceed 1,470 hours TIS, remove from service any LH rear fitting at intervals not to exceed 13,600 hours TIS, and remove from service any LH rear bolts during each Major Inspection ‘‘G.’’ (3) During the next Major Inspection ‘‘G,’’ remove from service the MGB suspension bar front bolts. Thereafter, remove from service the front bolts during each Major Inspection ‘‘G.’’ jbell on DSKJLSW7X2PROD with RULES (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email 9-ASW-FTWAMOC-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 (1) Airbus Helicopters Alert Service Bulletin No. AS332–01.00.90, Revision 0, dated November 21, 2018, which is not incorporated by reference, contains additional information about the subject of this AD. 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. You may view the VerDate Sep<11>2014 16:25 Apr 03, 2020 Jkt 250001 referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N– 321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Union Aviation Safety Agency (previously European Aviation Safety Agency) (EASA) AD No. 2018–0260, dated December 3, 2018. You may view the EASA AD on the internet at https:// www.regulations.gov in Docket No. FAA– 2019–1015. (h) Subject Joint Aircraft Service Component (JASC) Code: 6320 Main Rotor Gearbox. Issued on March 27, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–07138 Filed 4–3–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 RIN 1545–BO4 Investing in Qualified Opportunity Funds; Correcting Amendments Internal Revenue Service (IRS), Treasury. ACTION: Correcting amendments. AGENCY: This document contains corrections to Treasury Decision 9889, which was published in the Federal Register on Monday, January 13, 2020. Treasury Decision 9889 contained final regulations under the Internal Revenue Code (the ‘‘Code) that govern the extent to which taxpayers may elect the Federal income tax benefits with respect to certain equity interests in a qualified opportunity fund (QOF). DATES: These corrections are effective on April 1, 2020, and applicable as of January 13, 2020. FOR FURTHER INFORMATION CONTACT: Concerning section 1400Z–2 and these regulations generally, Alfred H. Bae, (202) 317–7006, or Kyle C. Griffin, (202) 317–4718, of the Office of Associate Chief Counsel (Income Tax and Accounting); concerning issues related to C corporations and consolidated groups, Jeremy Aron-Dine, (202) 317– 6848, or Sarah Hoyt, (202) 317–5024, of the Office of Associate Chief Counsel (Corporate); concerning issues related to gains from financial contracts, REITs, or RICs, Andrea Hoffenson or Pamela Lew, (202) 317–7053, of the Office of Associate Chief Counsel (Financial SUMMARY: Frm 00006 Fmt 4700 Background The final regulations (TD 9889) that are the subject of this correction are under section 1400Z–2 of the Code. Need for Correction As published on January 13, 2020 (85 FR 1866) contained errors that may prove to be misleading and need to be corrected. List of Subjects in 26 CFR Part 1 Income taxes, Reporting and recordkeeping requirements. [TD 9889] PO 00000 Institutions and Products); concerning issues related to investments by foreign persons, Eric Florenz, (202) 317–6941, or Milton Cahn (202) 317–6937, of the Office of Associate Chief Counsel (International); concerning issues related to partnerships, S corporations or trusts, Marla Borkson, Sonia Kothari, or Vishal Amin, at (202) 317–6850, and concerning issues related to estates and gifts, Leslie Finlow or Lorraine Gardner, at (202) 317–6859, of the Office of Associate Chief Counsel (Passthroughs and Special Industries). These numbers are not toll-free numbers. SUPPLEMENTARY INFORMATION: Sfmt 4700 Correction of Publication Accordingly, 26 CFR part 1 is corrected by making the following correcting amendments: PART 1—INCOME TAXES Paragraph 1. The authority citation continues to read in part as follows: ■ Authority: 26 U.S.C. 7805 * * * Par. 2. Section1.1400Z2–0 is amended: ■ a. By revising the entry for § 1.1400Z2(a)–1(d)(2); ■ b. In the entry for § 1.1400Z2(b)–1(h) introductory text, by removing the language ‘‘S corporations’’; and ■ c. By revising the entry for § 1.1400Z2(d)–1(a)(4). The revisions read as follows: ■ § 1.1400Z2–0 * Table of Contents. * * * * § 1.1400Z2(a)–1 Deferring tax on capital gains by investing in opportunity zones. * * * * * (d) * * * (2) Annual reporting of qualifying investments. * * * * * § 1.1400Z2(d)–1 Qualified opportunity funds and qualified opportunity zone businesses. (a) * * * (4) [Reserved] * * * * * E:\FR\FM\06APR1.SGM 06APR1

Agencies

[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19080-19082]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07138]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-1015; Product Identifier 2018-SW-104-AD; Amendment 
39-19882; AD 2020-06-13]
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 
Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. This AD requires determining the accumulated hours time-
in-service (TIS) of certain part-numbered main gearbox (MGB) suspension 
bar attachment fittings (fittings) and bolts, and establishes new life 
limits. This AD was prompted by the outcome of tests and analyses 
performed by Airbus Helicopters. The actions of this AD are intended to 
address an unsafe condition on these products.

DATES: This AD is effective May 11, 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.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2019-1015; 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 (previously European Aviation Safety Agency) 
(EASA) AD, 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, Senior 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

    On December 9, 2019, at 84 FR 67246, the Federal Register published 
the FAA's notice of proposed rulemaking (NPRM), which proposed to amend 
14 CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, with an MGB 
suspension bar right-hand side (RH) rear fitting part number (P/N) 
330A22-2702-07 and bolt P/N 330A22-0135-20, MGB suspension bar left-
hand side (LH) rear fitting P/N 330A22-2702-06 and bolt P/N 330A22-
0135-20, or MGB suspension bar front bolt P/N 330A22-0134-20 installed. 
The NPRM proposed to require within 50 hours TIS, reviewing the 
helicopter records to determine the total hours TIS of the MGB 
suspension bar RH and LH rear fittings. The NPRM also proposed to 
require removing from service the RH rear fitting and its bolts and the 
LH rear fitting and its bolts based on the accumulated total hours TIS 
of the fittings and other conditions. Thereafter, the NPRM proposed to 
require removing from service the RH rear fitting and its bolts at 
intervals not to exceed 1,470 hours TIS, removing from service the LH 
rear fitting at intervals not to exceed 13,600 hours TIS, and removing 
from service the LH rear bolts during each Major Inspection ``G.'' 
Finally, the NPRM proposed to require removing from service the front 
bolts during each Major Inspection ``G.''
    The proposed requirements were intended to prevent structural 
failure of the MGB suspension bar fittings and bolts, possibly 
resulting in detachment of the MGB suspension bars.
    The NPRM was prompted by EASA AD No. 2018-0260, dated December 3, 
2018, 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 AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. From 
review of reported Model EC 225 LP data, EASA advises that the 
installation of the MGB upper deck fittings of the three MGB suspension 
bars could lead to tightening torque loss on the fittings' attachment 
screws (bolts). Due to design similarities, Model AS 332 C, AS 332 C1, 
AS 332 L, and AS 332 L1 helicopters could also be affected by the same 
installation condition.

[[Page 19081]]

Investigations determined that a life limit reduction of the MGB 
suspension bar fittings and screws was necessary for these model 
helicopters.
    EASA states that this condition, if not corrected, could lead to 
structural failure of the MGB suspension bar fittings and screws, 
possibly resulting in detachment of the MGB suspension bars. 
Accordingly, the EASA AD requires determining the accumulated service 
life of the affected parts and introduced new life limits.

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 helicopters 
of these 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. The design 
approval holder is currently developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA might 
consider additional rulemaking.

Differences Between This AD and the EASA AD

    The EASA AD allows an option for the first MGB RH rear fitting 
replacement to inspect torque and specifies different replacement 
compliance times based on the torque inspection results, whereas this 
AD does not.

Related Service Information

    The FAA reviewed Airbus Helicopters Alert Service Bulletin No. 
AS332-01.00.90, Revision 0, dated November 21, 2018. This service 
information specifies determining the accumulated hours TIS of certain 
part-numbered rear MGB suspension bar fittings and screws. This service 
information further specifies criteria to determine the initial 
replacement compliance time of those parts and a new life limit for 
those parts thereafter. This service information also establishes a 
life limit for the front MGB attachment screws.

Costs of Compliance

    The FAA estimates that this AD affects 14 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.
    Determining the total hours TIS of the rear MGB fittings takes 
about 0.5 work-hour for an estimated cost of $43 per helicopter and 
$602 for the U.S. fleet.
    Replacing a rear MGB fitting and its set of four bolts takes about 
8 work-hours and parts cost about $12,937, for an estimated cost of 
$13,617 per replacement cycle.
    Replacing a set of four MGB attachment bolts takes about 4 work-
hours and parts cost about $224, for an estimated cost of $564 per 
replacement cycle.
    Replacing a LH rear MGB fitting takes about 8 work-hours and parts 
cost about $12,713, for an estimated cost of $13,393 per replacement 
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 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):

2020-06-13 Airbus Helicopters: Amendment 39-19882; Docket No. FAA-
2019-1015; Product Identifier 2018-SW-104-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category, with 
a main gearbox (MGB) suspension bar right-hand side (RH) rear 
attachment fitting (fitting) part number (P/N) 330A22-2702-07 and 
bolt P/N 330A22-0135-20, MGB suspension bar left-hand side (LH) rear 
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB 
suspension bar front bolt P/N 330A22-0134-20 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as MGB suspension bar 
fittings and bolts remaining in service beyond their fatigue life. 
This condition could result in failure of an MGB attachment 
assembly, detachment of an MGB suspension bar, and subsequent loss 
of helicopter control.

(c) Effective Date

    This AD becomes effective May 11, 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

    (1) Within 50 hours time-in-service (TIS), review records to 
determine the total hours TIS of each MGB suspension bar RH and LH 
rear fitting.
    (i) For any RH rear fitting that has accumulated 1,470 or more 
total hours TIS,

[[Page 19082]]

before further flight, remove from service the RH rear fitting and 
its bolts.
    (ii) For any RH rear fitting that has accumulated less than 
1,470 total hours TIS, remove from service the RH rear fitting and 
its bolts before the fitting accumulates 1,470 total hours TIS.
    (iii) For any LH rear fitting that has accumulated 13,600 or 
more total hours TIS, before further flight, remove from service the 
LH rear fitting and its bolts.
    (iv) For any LH rear fitting that has accumulated less than 
13,600 total hours TIS:
    (A) If a Major Inspection ``G'' has not been completed since the 
LH rear fitting has been installed, remove from service the LH rear 
bolts during the next Major Inspection ``G'' inspection; or
    Note 1 to paragraph (e)(1)(iv)(A) of this AD: Major Inspection 
``G'' (7,500 hours TIS between overhauls) is defined in Maintenance 
Manual MET 05-29-00-601.
    (B) If a Major Inspection ``G'' has been completed since the LH 
rear fitting has been installed, before further flight, remove from 
service the LH rear bolts; and
    (C) Remove from service the LH rear fitting before the fitting 
accumulates 13,600 total hours TIS.
    (2) Thereafter following paragraph (e)(1) of this AD, remove 
from service any RH rear fitting and its bolts at intervals not to 
exceed 1,470 hours TIS, remove from service any LH rear fitting at 
intervals not to exceed 13,600 hours TIS, and remove from service 
any LH rear bolts during each Major Inspection ``G.''
    (3) During the next Major Inspection ``G,'' remove from service 
the MGB suspension bar front bolts. Thereafter, remove from service 
the front bolts during each Major Inspection ``G.''

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
Matt Fuller, Senior Aviation Safety Engineer, Safety Management 
Section, Rotorcraft Standards Branch, FAA, 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

    (1) Airbus Helicopters Alert Service Bulletin No. AS332-
01.00.90, Revision 0, dated November 21, 2018, which is not 
incorporated by reference, contains additional information about the 
subject of this AD. 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. 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.
    (2) The subject of this AD is addressed in European Union 
Aviation Safety Agency (previously European Aviation Safety Agency) 
(EASA) AD No. 2018-0260, dated December 3, 2018. You may view the 
EASA AD on the internet at https://www.regulations.gov in Docket No. 
FAA-2019-1015.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320 Main Rotor 
Gearbox.

    Issued on March 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-07138 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P