Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 70076-70078 [2019-27430]

Download as PDF 70076 Federal Register / Vol. 84, No. 245 / Friday, December 20, 2019 / Proposed Rules By the Securities and Exchange Commission. Vanessa A. Countryman, Secretary. Dated: November 21, 2019. Mark A. Calabria, Director, Federal Housing Finance Agency. Dated: November 21, 2019. By the Department of Housing and Urban Development. John L. Garvin, General Deputy Assistant Secretary for Housing. [FR Doc. 2019–27490 Filed 12–19–19; 8:45 am] BILLING CODE 4810–33–P; 6210–01–P; 3064–01–P; 8070–01–P; 8011–01–P; 4210–67–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–1056; Product Identifier 2018–SW–047–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2009–25–09 for Eurocopter France (now Airbus Helicopters) Model SA 330 F, G, and J helicopters. AD 2009–25–09 currently requires re-adjusting the torque of the main gearbox (MGB) flexible coupling bolts. Since the FAA issued AD 2009–25–09, Airbus Helicopters has modified the MGB overhaul and repair procedures, which corrects the unsafe condition. Additionally, the FAA-validation for Model SA330F and G helicopters has been cancelled. This proposed AD would retain the requirements of AD 2009–25–09 but would revise the applicability by excluding Model SA330F and G helicopters and exclude MGBs that have been subject to the modified procedures. The actions of this proposed AD are intended to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by February 18, 2020. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. jbell on DSKJLSW7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:20 Dec 19, 2019 Jkt 250001 • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 1056; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed 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/technicalsupport.html. You may view service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Jignesh Patel, Aerospace Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email jignesh.patel@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views. The FAA also invites comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. The FAA will file in the docket all comments received, as well as a report PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, the FAA will consider all comments received on or before the closing date for comments. The FAA will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. The FAA may change this proposal in light of the comments received. Discussion The FAA issued AD 2009–25–09, Amendment 39–16128 (74 FR 66045, December 14, 2009) (‘‘AD 2009–25–09’’) for Eurocopter France (now Airbus Helicopters) Model SA 330 F, G, and J helicopters. AD 2009–25–09 requires readjusting the tightening torque load of the MGB input flexible coupling-toflange attachment bolts. AD 2009–25–09 was prompted by EASA AD No. 2008– 0049–E, dated March 3, 2008 and corrected March 7, 2008 (EASA AD 2008–0049–E), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition on Model SA 330 F, G, and J helicopters. The actions of AD 2009–25–29 were intended to prevent progressive fatigue failure of the coupling discs, caused by excessive fretting on the faces and in the bolt holes of the coupling discs, which could result in loss of the MGB input, loss of the drive transmission, and subsequent loss of control of the helicopter. Actions Since AD 2009–25–09 Was Issued Since the FAA issued AD 2009–25– 09, EASA has issued AD No. 2008– 0049R1, dated December 18, 2015 (EASA AD 2008–0049R1). EASA advises that since EASA AD 2008– 0049–E was issued, Airbus Helicopters has improved its procedures for assembling the flexible coupling-toflanges during MGB overhaul and maintenance of individual flexible couplings. EASA further states that the improved maintenance procedures ensure the correct torqueing of the attachment bolts of the flexible couplings. Because of these improved procedures, EASA AD 2008–0049R1 states that installing a coupling-to-flange assembly that has been subject to improved maintenance procedures after April 1, 2015, is an acceptable method to comply with the requirements of that AD. The FAA agrees with EASA’s determination and therefore proposes to change AD 2009–25–09 accordingly. Additionally, at the request of Airbus Helicopters, Model SA330F and G helicopters have been removed from the E:\FR\FM\20DEP1.SGM 20DEP1 Federal Register / Vol. 84, No. 245 / Friday, December 20, 2019 / Proposed Rules FAA Type Certificate Data Sheet (TCDS). According to Airbus Helicopters, none of these aircraft models are in existence. EASA, the state of design, has also removed these models from its TCDS. As a result, the FAA is removing these models from the applicability. 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 proposing this AD after evaluating all known relevant information and determining that an unsafe condition is likely to exist or develop on other helicopters of the same type design. Related Service Information Under 1 CFR Part 51 Authority for This Rulemaking The FAA reviewed Eurocopter Emergency Alert Service Bulletin No. 05.95, Revision 0, dated March 3, 2008, and Airbus Helicopters Emergency Alert Service Bulletin No. 05.95, Revision 1, dated October 22, 2015. This service information describes procedures for readjusting or checking the tightening torque load of the hardware attaching the flexible coupling to the sliding coupling flange and the bolts attaching the flexible coupling to the fixed coupling flange. Revision 1 of this service information excludes from its applicability certain flexible coupling assemblies that have undergone the improved procedures. 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. 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. Proposed AD Requirements Regulatory Findings This proposed AD would retain the attachment hardware torque verification and re-adjustment requirements of AD 2009–25–09, and would revise the applicability paragraph by excluding Model SA330F and G helicopters and by excluding input flexible coupling flange assemblies that have been installed in an MGB that has been overhauled after April 1, 2015. The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation: 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 Costs of Compliance jbell on DSKJLSW7X2PROD with PROPOSALS Re-adjusting the tightening torque on the flexible coupling-to-flange attachment bolts would take about 8 work-hours for an estimated cost of $680 per helicopter and $10,880 to the U.S. fleet. For MGB input flexible coupling flange assemblies with more than 75 hours time-in-service, inspecting the tightening torque load on the flexible coupling-to-flange attachment bolts would take about 10 work-hours for an estimated cost of $850 per helicopter and $13,600 to the U.S. fleet. If required, replacing a damaged flexible coupling would take about 1 work-hour in addition to those required for disassembling and inspecting the flexible coupling flange assembly and required parts would cost about $2,046 for an estimated cost of $2,131 per helicopter. The FAA estimates that this proposed AD affects 16 helicopters of U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on these numbers, the FAA estimates that operators may incur the following costs in order to comply with this AD. VerDate Sep<11>2014 17:20 Dec 19, 2019 Jkt 250001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 70077 under the criteria of the Regulatory Flexibility Act. The FAA prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 2009–25–09, Amendment 39–16128 (74 FR 66045, December 14, 2009), and adding the following new AD: ■ Airbus Helicopters (Previously Eurocopter France): Docket No. FAA–2019–1056; Directorate Identifier 2018–SW–047–AD. (a) Comments Due Date The FAA must receive comments by February 18, 2020. (b) Affected ADs This AD replaces AD 2009–25–09, Amendment 39–16128 (74 FR 66045, December 14, 2009). (c) Applicability This AD applies to Airbus Helicopters (previously Eurocopter France) Model SA330J helicopters, certificated in any category, with a main gearbox (MGB) input flexible coupling flange assembly part number 330A–32937401 installed that has been modified per MOD 0752416 and MOD 0752419, excluding: (1) Assemblies that have been subject to a maintenance scheduled inspection per Working Card 65.32.601 since new or since a complete overhaul of the MGB; and (2) Assemblies installed on an MGB that has undergone complete overhaul after April 1, 2015, and that have not been replaced since the complete overhaul of the MGB. (d) Unsafe Condition This AD defines the unsafe condition as progressive fatigue failure of the coupling discs, caused by excessive fretting on the faces and in the bolt holes of the coupling discs. This condition, if not corrected, could result in loss of the MGB input, loss of the drive transmission, and subsequent loss of control of the helicopter. E:\FR\FM\20DEP1.SGM 20DEP1 70078 Federal Register / Vol. 84, No. 245 / Friday, December 20, 2019 / Proposed Rules (e) Actions and Compliance jbell on DSKJLSW7X2PROD with PROPOSALS 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. (1) For MGB input flexible coupling flange assemblies with less than 50 hours time-inservice (TIS) since new or since a complete overhaul of the MGB, re-adjust the tightening torque load of the 6 nuts on the flexible coupling-to-flange attachment bolts. Accomplish this re-adjustment between 50 hours TIS and 75 hours TIS since new or since a complete overhaul of the MGB in accordance with paragraph 2.B.2.a. of Eurocopter Emergency Alert Service Bulletin No. 05.95, Revision 0, dated March 3, 2008 (EASB 05.95) or Airbus Helicopters Emergency Alert Service Bulletin No. 05.95, Revision 1, dated October 22, 2015 (EASB 05.95 Rev 1). (2) For MGB input flexible coupling flange assemblies with 50 hours TIS and 75 or less hours TIS since new or since a complete overhaul of the MGB, either: (i) Upon or before reaching 75 hours TIS since new or since a complete overhaul of the MGB, re-adjust the tightening torque load of the 6 nuts on the flexible coupling-to-flange attachment bolts in accordance with paragraph 2.B.2.a. of EASB 05.95 or EASB 05.95 Rev 1; or (ii) Upon or before reaching 125 hours TIS since new or since a complete overhaul of the MGB, inspect the tightening torque load of the 6 nuts on the flexible coupling-to-flange attachment bolts in accordance with paragraph 2.B.2.b. of EASB 05.95 or EASB 05.95 Rev 1, except you are not required to contact the manufacturer. (3) For MGB input flexible coupling flange assemblies that have more than 75 hours TIS since new or since a complete overhaul of the MGB, within the next 50 hours TIS, inspect the tightening torque load of the 6 nuts on the flexible coupling-to-flange attachment bolts, in accordance with paragraph 2.B.2.b. of EASB 05.95 or EASB 05.95 Rev 1, except you are not required to contact the manufacturer. (4) Prior to installing an MGB that contains an input flexible coupling flange assembly that has been modified per MOD 0752416 and MOD 0752419, you must comply with the provisions of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, FAA, may approve AMOCs for this AD. Send your proposal to: Jignesh Patel, Aerospace Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. VerDate Sep<11>2014 17:20 Dec 19, 2019 Jkt 250001 (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008–0049R1, dated December 18, 2015. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 6310, Engine/Transmission Coupling. Issued in Fort Worth, Texas, on December 11, 2019. Gaetano A. Sciortino, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–27430 Filed 12–19–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0988; Product Identifier 2019–NM–175–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Canada Limited Partnership (Type Certificate Previously Held by C Series Aircraft Limited Partnership (CSALP); Bombardier, Inc.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD–500–1A11 airplanes. This proposed AD was prompted by reports that, under certain combinations of airplane configuration and flight conditions, higher than anticipated temperatures could lead to an engine fire warning nuisance message. This proposed AD would require installation of Integrated Air Systems Controller (IASC) software version 5.0. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by February 3, 2020. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Bombardier, Inc., 400 Coˆte-Vertu Road West, Dorval, Que´bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0988; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Thomas Niczky, Aerospace Engineer, Avionics and Electrical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7347; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2019–0988; Product Identifier 2019–NM–175–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments, without change, to https:// www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact the agency receives about this NPRM. E:\FR\FM\20DEP1.SGM 20DEP1

Agencies

[Federal Register Volume 84, Number 245 (Friday, December 20, 2019)]
[Proposed Rules]
[Pages 70076-70078]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-27430]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-1056; Product Identifier 2018-SW-047-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2009-25-09 for Eurocopter France (now Airbus Helicopters) Model SA 330 
F, G, and J helicopters. AD 2009-25-09 currently requires re-adjusting 
the torque of the main gearbox (MGB) flexible coupling bolts. Since the 
FAA issued AD 2009-25-09, Airbus Helicopters has modified the MGB 
overhaul and repair procedures, which corrects the unsafe condition. 
Additionally, the FAA-validation for Model SA330F and G helicopters has 
been cancelled. This proposed AD would retain the requirements of AD 
2009-25-09 but would revise the applicability by excluding Model SA330F 
and G helicopters and exclude MGBs that have been subject to the 
modified procedures. The actions of this proposed AD are intended to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by February 
18, 2020.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
1056; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received and other information. The 
street address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed 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 service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Jignesh Patel, Aerospace Engineer, 
Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites comments 
relating to the economic, environmental, energy, or federalism impacts 
that might result from adopting the proposals in this document. The 
most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. To ensure the docket does not contain duplicate comments, 
commenters should send only one copy of written comments, or if 
comments are filed electronically, commenters should submit only one 
time.
    The FAA will file in the docket all comments received, as well as a 
report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, 
the FAA will consider all comments received on or before the closing 
date for comments. The FAA will consider comments filed after the 
comment period has closed if it is possible to do so without incurring 
expense or delay. The FAA may change this proposal in light of the 
comments received.

Discussion

    The FAA issued AD 2009-25-09, Amendment 39-16128 (74 FR 66045, 
December 14, 2009) (``AD 2009-25-09'') for Eurocopter France (now 
Airbus Helicopters) Model SA 330 F, G, and J helicopters. AD 2009-25-09 
requires re-adjusting the tightening torque load of the MGB input 
flexible coupling-to-flange attachment bolts. AD 2009-25-09 was 
prompted by EASA AD No. 2008-0049-E, dated March 3, 2008 and corrected 
March 7, 2008 (EASA AD 2008-0049-E), issued by EASA, which is the 
Technical Agent for the Member States of the European Union, to correct 
an unsafe condition on Model SA 330 F, G, and J helicopters. The 
actions of AD 2009-25-29 were intended to prevent progressive fatigue 
failure of the coupling discs, caused by excessive fretting on the 
faces and in the bolt holes of the coupling discs, which could result 
in loss of the MGB input, loss of the drive transmission, and 
subsequent loss of control of the helicopter.

Actions Since AD 2009-25-09 Was Issued

    Since the FAA issued AD 2009-25-09, EASA has issued AD No. 2008-
0049R1, dated December 18, 2015 (EASA AD 2008-0049R1). EASA advises 
that since EASA AD 2008-0049-E was issued, Airbus Helicopters has 
improved its procedures for assembling the flexible coupling-to-flanges 
during MGB overhaul and maintenance of individual flexible couplings. 
EASA further states that the improved maintenance procedures ensure the 
correct torqueing of the attachment bolts of the flexible couplings. 
Because of these improved procedures, EASA AD 2008-0049R1 states that 
installing a coupling-to-flange assembly that has been subject to 
improved maintenance procedures after April 1, 2015, is an acceptable 
method to comply with the requirements of that AD. The FAA agrees with 
EASA's determination and therefore proposes to change AD 2009-25-09 
accordingly.
    Additionally, at the request of Airbus Helicopters, Model SA330F 
and G helicopters have been removed from the

[[Page 70077]]

FAA Type Certificate Data Sheet (TCDS). According to Airbus 
Helicopters, none of these aircraft models are in existence. EASA, the 
state of design, has also removed these models from its TCDS. As a 
result, the FAA is removing these models from the applicability.

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 proposing this AD 
after evaluating all known relevant information and determining that an 
unsafe condition is likely to exist or develop on other helicopters of 
the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Eurocopter Emergency Alert Service Bulletin No. 
05.95, Revision 0, dated March 3, 2008, and Airbus Helicopters 
Emergency Alert Service Bulletin No. 05.95, Revision 1, dated October 
22, 2015. This service information describes procedures for readjusting 
or checking the tightening torque load of the hardware attaching the 
flexible coupling to the sliding coupling flange and the bolts 
attaching the flexible coupling to the fixed coupling flange. Revision 
1 of this service information excludes from its applicability certain 
flexible coupling assemblies that have undergone the improved 
procedures.
    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.

Proposed AD Requirements

    This proposed AD would retain the attachment hardware torque 
verification and re-adjustment requirements of AD 2009-25-09, and would 
revise the applicability paragraph by excluding Model SA330F and G 
helicopters and by excluding input flexible coupling flange assemblies 
that have been installed in an MGB that has been overhauled after April 
1, 2015.

 Costs of Compliance

    The FAA estimates that this proposed AD affects 16 helicopters of 
U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this AD.
    Re-adjusting the tightening torque on the flexible coupling-to-
flange attachment bolts would take about 8 work-hours for an estimated 
cost of $680 per helicopter and $10,880 to the U.S. fleet. For MGB 
input flexible coupling flange assemblies with more than 75 hours time-
in-service, inspecting the tightening torque load on the flexible 
coupling-to-flange attachment bolts would take about 10 work-hours for 
an estimated cost of $850 per helicopter and $13,600 to the U.S. fleet.
    If required, replacing a damaged flexible coupling would take about 
1 work-hour in addition to those required for disassembling and 
inspecting the flexible coupling flange assembly and required parts 
would cost about $2,046 for an estimated cost of $2,131 per helicopter.

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.

Regulatory Findings

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    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.
    The FAA prepared an economic evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2009-25-09, Amendment 39-16128 (74 FR 66045, December 14, 2009), and 
adding the following new AD:

Airbus Helicopters (Previously Eurocopter France): Docket No. FAA-
2019-1056; Directorate Identifier 2018-SW-047-AD.

(a) Comments Due Date

    The FAA must receive comments by February 18, 2020.

(b) Affected ADs

    This AD replaces AD 2009-25-09, Amendment 39-16128 (74 FR 66045, 
December 14, 2009).

(c) Applicability

    This AD applies to Airbus Helicopters (previously Eurocopter 
France) Model SA330J helicopters, certificated in any category, with 
a main gearbox (MGB) input flexible coupling flange assembly part 
number 330A-32937401 installed that has been modified per MOD 
0752416 and MOD 0752419, excluding:
    (1) Assemblies that have been subject to a maintenance scheduled 
inspection per Working Card 65.32.601 since new or since a complete 
overhaul of the MGB; and
    (2) Assemblies installed on an MGB that has undergone complete 
overhaul after April 1, 2015, and that have not been replaced since 
the complete overhaul of the MGB.

(d) Unsafe Condition

    This AD defines the unsafe condition as progressive fatigue 
failure of the coupling discs, caused by excessive fretting on the 
faces and in the bolt holes of the coupling discs. This condition, 
if not corrected, could result in loss of the MGB input, loss of the 
drive transmission, and subsequent loss of control of the 
helicopter.

[[Page 70078]]

(e) Actions and 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.
    (1) For MGB input flexible coupling flange assemblies with less 
than 50 hours time-in-service (TIS) since new or since a complete 
overhaul of the MGB, re-adjust the tightening torque load of the 6 
nuts on the flexible coupling-to-flange attachment bolts. Accomplish 
this re-adjustment between 50 hours TIS and 75 hours TIS since new 
or since a complete overhaul of the MGB in accordance with paragraph 
2.B.2.a. of Eurocopter Emergency Alert Service Bulletin No. 05.95, 
Revision 0, dated March 3, 2008 (EASB 05.95) or Airbus Helicopters 
Emergency Alert Service Bulletin No. 05.95, Revision 1, dated 
October 22, 2015 (EASB 05.95 Rev 1).
    (2) For MGB input flexible coupling flange assemblies with 50 
hours TIS and 75 or less hours TIS since new or since a complete 
overhaul of the MGB, either:
    (i) Upon or before reaching 75 hours TIS since new or since a 
complete overhaul of the MGB, re-adjust the tightening torque load 
of the 6 nuts on the flexible coupling-to-flange attachment bolts in 
accordance with paragraph 2.B.2.a. of EASB 05.95 or EASB 05.95 Rev 
1; or
    (ii) Upon or before reaching 125 hours TIS since new or since a 
complete overhaul of the MGB, inspect the tightening torque load of 
the 6 nuts on the flexible coupling-to-flange attachment bolts in 
accordance with paragraph 2.B.2.b. of EASB 05.95 or EASB 05.95 Rev 
1, except you are not required to contact the manufacturer.
    (3) For MGB input flexible coupling flange assemblies that have 
more than 75 hours TIS since new or since a complete overhaul of the 
MGB, within the next 50 hours TIS, inspect the tightening torque 
load of the 6 nuts on the flexible coupling-to-flange attachment 
bolts, in accordance with paragraph 2.B.2.b. of EASB 05.95 or EASB 
05.95 Rev 1, except you are not required to contact the 
manufacturer.
    (4) Prior to installing an MGB that contains an input flexible 
coupling flange assembly that has been modified per MOD 0752416 and 
MOD 0752419, you must comply with the provisions of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, FAA, may approve 
AMOCs for this AD. Send your proposal to: Jignesh Patel, Aerospace 
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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2008-0049R1, dated December 18, 2015. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
the AD Docket.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6310, Engine/
Transmission Coupling.

    Issued in Fort Worth, Texas, on December 11, 2019.
Gaetano A. Sciortino,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2019-27430 Filed 12-19-19; 8:45 am]
BILLING CODE 4910-13-P

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