Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters, 47641-47643 [2020-17164]

Download as PDF Federal Register / Vol. 85, No. 152 / Thursday, August 6, 2020 / Rules and Regulations email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on June 19, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–17043 Filed 8–5–20; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–1056; Product Identifier 2018–SW–047–AD; Amendment 39–21193; AD 2020–16–09] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2009–25– 09 for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J helicopters. AD 2009–25–09 required readjusting 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 new AD retains the requirements of AD 2009–25–09 and revises the applicability by excluding Model SA330F and G helicopters and excludes MGBs that have been subject to the modified procedures. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective September 10, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 10, 2020. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 29, 2009 (74 FR 66045 December 14, 2009). 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:// jbell on DSKJLSW7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 16:05 Aug 05, 2020 Jkt 250001 www.airbus.com/helicopters/services/ technical-support.html. 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2019–1056. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in 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 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: James Blyn, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817–222–5110; email james.blyn@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2009–25–09, Amendment 39–16128 (74 FR 66045, December 14, 2009) (‘‘AD 2009–25–09’’) and add a new AD. AD 2009–25–09 applied to Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J helicopters. The NPRM published in the Federal Register on December 20, 2019 (84 FR 70076). 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), to correct an unsafe condition on Model SA 330 F, G, and J helicopters. The NPRM proposed to 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 NPRM was prompted by EASA AD No. 2008–0049R1, dated December PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 47641 18, 2015 (EASA AD 2008–0049R1), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model SA 330 J helicopters. 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 proposed to change AD 2009– 25–09 accordingly. Comments The FAA gave the public the opportunity to participate in developing this AD, but 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. Related Service Information Under 1 CFR Part 51 The FAA reviewed Eurocopter Emergency Alert Service Bulletin No. 05.95, dated March 3, 2008, and Airbus Helicopters Emergency Alert Service Bulletin No. 05.95, Revision 1, dated October 22, 2015, which specify 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. E:\FR\FM\06AUR1.SGM 06AUR1 47642 Federal Register / Vol. 85, No. 152 / Thursday, August 6, 2020 / Rules and Regulations 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. Differences Between This AD and the Service Information The service information requires contacting the manufacturer depending on the results of an inspection, but this AD does not. jbell on DSKJLSW7X2PROD with RULES Costs of Compliance The FAA estimates that this AD affects 16 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. Re-adjusting the tightening torque on the flexible coupling-to-flange attachment bolts takes about 8 workhours for an estimated cost of $680 per helicopter and $10,880 for 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 takes about 10 work-hours for an estimated cost of $850 per helicopter. If required, replacing a damaged flexible coupling takes about 1 workhour in addition to those required for disassembling and inspecting the flexible coupling flange assembly and parts 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 has determined that this AD will not have federalism implications under Executive Order 13132. This AD VerDate Sep<11>2014 16:05 Aug 05, 2020 Jkt 250001 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. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (f) Required Actions (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, 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 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. 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) 2009–25–09, Amendment 39– 16128 (74 FR 66045, December 14, 2009); and ■ b. Adding the following new AD: ■ ■ 2020–16–09 Airbus Helicopters (Type Certificate Previously Held by Eurocopter France): Amendment 39– 21193; Docket No. FAA–2019–1056; Product Identifier 2018–SW–047–AD. (a) 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. (b) 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (c) Affected ADs This AD replaces AD 2009–25–09, Amendment 39–16128 (74 FR 66045, December 14, 2009). (d) Effective Date This AD becomes effective September 10, 2020. (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. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: James Blyn, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, E:\FR\FM\06AUR1.SGM 06AUR1 Federal Register / Vol. 85, No. 152 / Thursday, August 6, 2020 / Rules and Regulations 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. (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (now European Union 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 Docket No. FAA– 2019–1056. (i) Subject Joint Aircraft Service Component (JASC) Code: 6310, Engine Transmission Coupling. jbell on DSKJLSW7X2PROD with RULES (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on September 10, 2020. (i) Airbus Helicopters Emergency Alert Service Bulletin No. 05.95, Revision 1, dated October 22, 2015. (ii) [Reserved] (4) The following service information was approved for IBR on December 29, 2009 (74 FR 66045, December 14, 2009). (i) Eurocopter Emergency Alert Service Bulletin No. 05.95, dated March 3, 2008. (ii) [Reserved] (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. (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 July 23, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2020–17164 Filed 8–5–20; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:05 Aug 05, 2020 Jkt 250001 47643 DEPARTMENT OF TRANSPORTATION Availability Federal Aviation Administration All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit the National Flight Data Center at nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from the FAA Air Traffic Organization Service Area in which the affected airport is located. FOR FURTHER INFORMATION CONTACT: Thomas J. Nichols, Flight Procedures and Airspace Group, Flight Technologies and Procedures Division, Flight Standards Service, Federal Aviation Administration. Mailing Address: FAA Mike Monroney Aeronautical Center, Flight Procedures and Airspace Group, 6500 South MacArthur Blvd., Registry Bldg. 29, Room 104, Oklahoma City, OK 73169. Telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or removes SIAPS, Takeoff Minimums and/or ODPS. The complete regulatory description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR part 97.20. The applicable FAA forms are FAA Forms 8260–3, 8260–4, 8260–5, 8260–15A, and 8260–15B when required by an entry on 8260–15A. The large number of SIAPs, Takeoff Minimums and ODPs, their complex nature, and the need for a special format make publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their graphic depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on FAA form documents is unnecessary. This amendment provides the affected CFR sections and specifies the types of SIAPs, Takeoff Minimums and ODPs with their applicable effective dates. This amendment also identifies the airport and its location, the procedure, and the amendment number. 14 CFR Part 97 [Docket No. 31323 Amdt. No. 3915] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule establishes, amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures (ODPs) for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective August 6, 2020. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 6, 2020. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: SUMMARY: For Examination 1. U.S. Department of Transportation, Docket Ops–M30, 1200 New Jersey Avenue SE, West Bldg., Ground Floor, Washington, DC 20590–0001. 2. The FAA Air Traffic Organization Service Area in which the affected airport is located; 3. The office of Aeronautical Navigation Products, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. The National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@ nara.gov or go to: https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Availability and Summary of Material Incorporated by Reference The material incorporated by reference is publicly available as listed in the ADDRESSES section. E:\FR\FM\06AUR1.SGM 06AUR1

Agencies

[Federal Register Volume 85, Number 152 (Thursday, August 6, 2020)]
[Rules and Regulations]
[Pages 47641-47643]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-17164]


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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; Amendment 
39-21193; AD 2020-16-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2009-25-09 
for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J 
helicopters. AD 2009-25-09 required 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 
new AD retains the requirements of AD 2009-25-09 and revises the 
applicability by excluding Model SA330F and G helicopters and excludes 
MGBs that have been subject to the modified procedures. The actions of 
this AD are intended to address an unsafe condition on these products.

DATES: This AD is effective September 10, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
10, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 29, 
2009 (74 FR 66045 December 14, 2009).

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 this 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-2019-
1056.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in 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 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: James Blyn, 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 2009-25-09, Amendment 39-16128 (74 FR 66045, 
December 14, 2009) (``AD 2009-25-09'') and add a new AD. AD 2009-25-09 
applied to Eurocopter France (now Airbus Helicopters) Model SA330F, G, 
and J helicopters. The NPRM published in the Federal Register on 
December 20, 2019 (84 FR 70076). 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), to correct an unsafe condition on Model SA 330 F, G, 
and J helicopters. The NPRM proposed to 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 NPRM was prompted by EASA AD No. 2008-0049R1, dated December 
18, 2015 (EASA AD 2008-0049R1), issued by EASA, which is the Technical 
Agent for the Member States of the European Union, to correct an unsafe 
condition for Airbus Helicopters Model SA 330 J helicopters. 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 proposed to change AD 
2009-25-09 accordingly.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD, but 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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Eurocopter Emergency Alert Service Bulletin No. 
05.95, dated March 3, 2008, and Airbus Helicopters Emergency Alert 
Service Bulletin No. 05.95, Revision 1, dated October 22, 2015, which 
specify 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.

[[Page 47642]]

    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.

Differences Between This AD and the Service Information

    The service information requires contacting the manufacturer 
depending on the results of an inspection, but this AD does not.

Costs of Compliance

    The FAA estimates that this AD affects 16 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.
    Re-adjusting the tightening torque on the flexible coupling-to-
flange attachment bolts takes about 8 work-hours for an estimated cost 
of $680 per helicopter and $10,880 for 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 takes about 10 work-hours 
for an estimated cost of $850 per helicopter.
    If required, replacing a damaged flexible coupling takes about 1 
work-hour in addition to those required for disassembling and 
inspecting the flexible coupling flange assembly and parts 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 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) 2009-25-09, Amendment 39-16128 
(74 FR 66045, December 14, 2009); and
0
b. Adding the following new AD:

2020-16-09 Airbus Helicopters (Type Certificate Previously Held by 
Eurocopter France): Amendment 39-21193; Docket No. FAA-2019-1056; 
Product Identifier 2018-SW-047-AD.

(a) 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.

(b) 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.

(c) Affected ADs

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

(d) Effective Date

    This AD becomes effective September 10, 2020.

(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) 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, 
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 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.

 (g) Alternative Methods of Compliance (AMOCs)

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

[[Page 47643]]

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.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (now European Union 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 Docket No. FAA-2019-
1056.

(i) Subject

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

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 10, 2020.
    (i) Airbus Helicopters Emergency Alert Service Bulletin No. 
05.95, Revision 1, dated October 22, 2015.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on 
December 29, 2009 (74 FR 66045, December 14, 2009).
    (i) Eurocopter Emergency Alert Service Bulletin No. 05.95, dated 
March 3, 2008.
    (ii) [Reserved]
    (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.
    (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 July 23, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-17164 Filed 8-5-20; 8:45 am]
BILLING CODE 4910-13-P

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