Airworthiness Directives; Airbus Helicopters, 48366-48368 [2018-20487]

Download as PDF 48366 Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations describes the unsafe condition as cracking found in the wing rear spar web at the wing station (WS) where the flap outboard hinge is attached. We are issuing this AD to detect and correct cracks in the wing rear spars and the flap/aileron hinge arm support brackets. This condition, if not corrected, could result in structural failure with consequent loss of control of the airplane. daltland on DSKBBV9HB2PROD with RULES (f) Actions and Compliance Unless already done, do the actions in paragraphs (f)(1) through (5) of this AD: (1) Within 400 hours time-in-service (TIS) after October 30, 2018 (the effective date of this AD) or within 6 months after October 30, 2018 (the effective date of this AD), whichever occurs first, visually inspect the left-hand and right-hand wing rear spar and flap/aileron hinge arm support brackets by following the Accomplishment Instructions of Viking DHC–2 Beaver Service Bulletin Number: V2/0009, Revision A, dated February 10, 2017 (SB V2/0009, Revision A). (2) For airplanes with an agricultural configuration installed (SOO Mod 2/984), within 400 hours TIS after October 30, 2018 (the effective date of this AD) or within 6 months after October 30, 2018 (the effective date of this AD), whichever occurs first, inspect the exterior store support arm bracket at WS 101.24 by following the Accomplishment Instructions of SB V2/0009, Revision A. (3) If any discrepancies are found during the inspections required in paragraphs (f)(1) and (2) of this AD, before further flight, repair or replace using a method approved by the Manager, New York ACO Branch, FAA; Transport Canada; or Viking Air Limited’s Transport Canada Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (4) Within 30 days after completing the inspections required in paragraphs (f)(1) and (2) of this AD, using the Operator Reply Form on page 7 of SB V2/0009, Revision A, report the inspection results to Viking Air Limited at the address specified in paragraph (i)(3) of this AD. (5) As of October 30, 2018 (the effective date of this AD), do not install a wing on any airplane affected by this AD unless it has been inspected as specified in paragraphs (f)(1) of this AD and paragraph (f)(2) of this AD, if applicable, and is found free of any discrepancies. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Aziz Ahmed, Aerospace Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228–7329; fax: (516) 794–5531; email: aziz.ahmed@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight VerDate Sep<11>2014 16:30 Sep 24, 2018 Jkt 244001 Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada; or Viking Air Limited’s Transport Canada DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524. (h) Related Information Refer to MCAI Transport Canada AD Number CF–2017–17, dated May 18, 2017, for related information. You may examine the MCAI on the internet at https:// www.regulations.gov/document?D=FAA2017-0867-0002. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Viking DHC–2 Beaver Service Bulletin Number: V2/0009, Revision A, dated February 10, 2017. (ii) Reserved. (3) For Viking DHC–2 Beaver service information identified in this AD, contact Viking Air Limited Technical Support, 1959 De Havilland Way, Sidney, British Columbia, Canada, V8L 5V5; telephone: (North America) (800) 663–8444; fax: (250) 656– 0673; email: technical.support@ vikingair.com; internet: http:// www.vikingair.com/support/serviceBulletins. (4) You may view this service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. In addition, you can access this service information on the internet at http:// PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 www.regulations.gov by searching for and locating Docket No. FAA–2017–0867. (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, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on September 7, 2018 Melvin J. Johnson, Aircraft Certification Service, Deputy Director, Policy and Innovation Division, AIR–601. [FR Doc. 2018–20802 Filed 9–24–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0438; Product Identifier 2017–SW–062–AD; Amendment 39–19410; AD 2018–19–10] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This AD requires measuring a vibration level in the tail rotor (T/R) drive. This AD was prompted by reports of bearing degradation. The actions of this AD are intended to prevent an unsafe condition on these helicopters. DATES: This AD is effective October 30, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You may review 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0438; or in person at Docket Operations E:\FR\FM\25SER1.SGM 25SER1 daltland on DSKBBV9HB2PROD with RULES Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations 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 (EASA) AD, the economic evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647– 5527) 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: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email rao.edupuganti@faa.gov. SUPPLEMENTARY INFORMATION: control of the helicopter. To address this unsafe condition and as an interim measure, the EASA AD requires two vibration level measurements of the forward portion of the tail rotor drive line, one before and one after cleaning the MGB oil cooler fan, and replacing the bearings if excessive level or level trends are detected. The EASA AD also specifies that after the effective date of the AD, only those MGB oil cooler fan assembly bearings that are new or that have passed the vibration level measurements may be installed. Discussion These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of the same type design and that air safety and the public interest require adopting the AD requirements as proposed. On May 17, 2018, at 83 FR 22886, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. The NPRM proposed to require measuring the T/R drive vibration level without balancing, cleaning the fan, and repeating the vibration level measurement. If the difference between the two amplitude values is greater than 0.75 inch per second (ips), the NPRM proposed to require replacing each T/R fan bearing. The proposed requirements were intended to prevent degradation of the main gearbox (MGB) oil cooler fan bearing (bearing), which could result in loss of MGB and engine oil cooling function, loss of the rear transmission, and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2017–0159, dated August 25, 2017, 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 AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. EASA advises of two occurrences on Model AS355 military helicopters in which the MGB bearing installed on the T/R drive shaft experienced significant degradation. EASA states that while investigation has not determined the cause of the failures, this condition may also occur on other Model AS355 helicopters due to design commonality. According to EASA, this condition, if not detected and corrected, could result in loss of MGB and engine oil cooling function, loss of the rear transmission, and subsequent loss of VerDate Sep<11>2014 16:30 Sep 24, 2018 Jkt 244001 Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination Interim Action We consider this AD to be an interim action. The manufacturer is currently developing a terminating action for the unsafe condition described in this AD. If a terminating action is identified, we may consider further rulemaking then. Related Service Information Airbus Helicopters has issued Alert Service Bulletin No. AS355–05.00.77, Revision 0, dated July 3, 2017, which contains procedures for checking the condition of the fan assembly bearings by measuring the vibration levels of the first section of the T/R drive. Costs of Compliance We estimate that this AD affects 104 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work-hour, measuring the vibration levels requires about 5 work-hours, for a cost of $425 per helicopter and $44,200 for the U.S. fleet. If required, replacing both fan assembly bearings requires about 8 work-hours, and required parts cost $1,064, for a cost of $1,744 per helicopter. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 48367 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. We are 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) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and (4) 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. We prepared an economic evaluation of the estimated costs to comply with this 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. 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: ■ E:\FR\FM\25SER1.SGM 25SER1 48368 Federal Register / Vol. 83, No. 186 / Tuesday, September 25, 2018 / Rules and Regulations 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): ■ 2018–19–10 Airbus Helicopters: Amendment 39–19410; Docket No. FAA–2018–0438; Product Identifier 2017–SW–062–AD. (a) Applicability This AD applies to Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as degradation of a main gearbox (MGB) oil cooler fan assembly bearing. This condition could result in loss of MGB and engine oil cooling function, loss of the rear transmission, and subsequent loss of control of the helicopter. DEPARTMENT OF TRANSPORTATION (1) Airbus Helicopters Alert Service Bulletin No. AS355–05.00.77, Revision 0, dated July 3, 2017, 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 http://www.helicopters.airbus. com/website/en/ref/Technical-Support_ 73.html. You may review a copy of the 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 Aviation Safety Agency (EASA) AD No. 2017–0159, dated August 25, 2017. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA–2018–0438. (c) Effective Date This AD becomes effective October 30, 2018. (h) Subject (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. Issued in Fort Worth, Texas, on September 12, 2018. Scott A. Horn, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor Driveshaft. (e) Required Actions (1) Within 165 hours time-in-service (TIS): (i) Measure the tail rotor (T/R) drive vibration level without balancing the T/R drive, and record the amplitude value. (ii) Clean the oil cooler fan. (iii) Measure the T/R drive vibration level without balancing the T/R drive, and record the amplitude value. (iv) Calculate the difference between the two amplitude values. If the difference is greater than 0.75 inch per second (ips), before further flight, replace each oil cooler fan assembly bearing. (2) After the effective date of this AD, do not install an oil cooler fan assembly bearing with more than 0 hours TIS unless the requirements of this AD have been accomplished. daltland on DSKBBV9HB2PROD with RULES (g) Additional Information (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: Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest 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 16:30 Sep 24, 2018 Jkt 244001 [FR Doc. 2018–20487 Filed 9–24–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 91 [Docket No.: FAA–2018–0838; Amdt. No. 91–352] RIN 2120–AL34 Amendment of the Prohibition Against Certain Flights in the Pyongyang Flight Information Region (FIR) (ZKKP) Correction In rule document 2018–20173 appearing on pages 47059–47065 in the issue of September 18, 2018, make the following correction: On page 47061, in the second column, in the third line, ‘‘September 18, 2010’’ should read ‘‘September 18, 2020’’. [FR Doc. C1–2018–20173 Filed 9–24–18; 8:45 am] BILLING CODE 1301–00–D PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 97 [Docket No. 31213; Amdt. No. 3817] 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 September 25, 2018. 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 September 25, 2018. 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, call 202–741–6030, or go to: http://www.archives.gov/ federal_register/code_of_federal_ regulations/ibr_locations.html. E:\FR\FM\25SER1.SGM 25SER1

Agencies

[Federal Register Volume 83, Number 186 (Tuesday, September 25, 2018)]
[Rules and Regulations]
[Pages 48366-48368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20487]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0438; Product Identifier 2017-SW-062-AD; Amendment 
39-19410; AD 2018-19-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N 
helicopters. This AD requires measuring a vibration level in the tail 
rotor (T/R) drive. This AD was prompted by reports of bearing 
degradation. The actions of this AD are intended to prevent an unsafe 
condition on these helicopters.

DATES: This AD is effective October 30, 2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0438; or in person at Docket Operations

[[Page 48367]]

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 (EASA) AD, the economic evaluation, any comments received, and 
other information. The street address for Docket Operations (phone: 
800-647-5527) 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: Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, 
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    On May 17, 2018, at 83 FR 22886, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 by adding an AD that would apply to Airbus Helicopters Model 
AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. The NPRM 
proposed to require measuring the T/R drive vibration level without 
balancing, cleaning the fan, and repeating the vibration level 
measurement. If the difference between the two amplitude values is 
greater than 0.75 inch per second (ips), the NPRM proposed to require 
replacing each T/R fan bearing. The proposed requirements were intended 
to prevent degradation of the main gearbox (MGB) oil cooler fan bearing 
(bearing), which could result in loss of MGB and engine oil cooling 
function, loss of the rear transmission, and subsequent loss of control 
of the helicopter.
    The NPRM was prompted by AD No. 2017-0159, dated August 25, 2017, 
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 AS355E, AS355F, AS355F1, AS355F2, and AS355N 
helicopters. EASA advises of two occurrences on Model AS355 military 
helicopters in which the MGB bearing installed on the T/R drive shaft 
experienced significant degradation. EASA states that while 
investigation has not determined the cause of the failures, this 
condition may also occur on other Model AS355 helicopters due to design 
commonality. According to EASA, this condition, if not detected and 
corrected, could result in loss of MGB and engine oil cooling function, 
loss of the rear transmission, and subsequent loss of control of the 
helicopter. To address this unsafe condition and as an interim measure, 
the EASA AD requires two vibration level measurements of the forward 
portion of the tail rotor drive line, one before and one after cleaning 
the MGB oil cooler fan, and replacing the bearings if excessive level 
or level trends are detected. The EASA AD also specifies that after the 
effective date of the AD, only those MGB oil cooler fan assembly 
bearings that are new or that have passed the vibration level 
measurements may be installed.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of the same type 
design and that air safety and the public interest require adopting the 
AD requirements as proposed.

Interim Action

    We consider this AD to be an interim action. The manufacturer is 
currently developing a terminating action for the unsafe condition 
described in this AD. If a terminating action is identified, we may 
consider further rulemaking then.

Related Service Information

    Airbus Helicopters has issued Alert Service Bulletin No. AS355-
05.00.77, Revision 0, dated July 3, 2017, which contains procedures for 
checking the condition of the fan assembly bearings by measuring the 
vibration levels of the first section of the T/R drive.

Costs of Compliance

    We estimate that this AD affects 104 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD.
    At an average labor rate of $85 per work-hour, measuring the 
vibration levels requires about 5 work-hours, for a cost of $425 per 
helicopter and $44,200 for the U.S. fleet. If required, replacing both 
fan assembly bearings requires about 8 work-hours, and required parts 
cost $1,064, for a cost of $1,744 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.
    We are 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) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this 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.

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:


[[Page 48368]]


    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):

2018-19-10 Airbus Helicopters: Amendment 39-19410; Docket No. FAA-
2018-0438; Product Identifier 2017-SW-062-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS355E, AS355F, 
AS355F1, AS355F2, and AS355N helicopters, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as degradation of a main 
gearbox (MGB) oil cooler fan assembly bearing. This condition could 
result in loss of MGB and engine oil cooling function, loss of the 
rear transmission, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective October 30, 2018.

(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 165 hours time-in-service (TIS):
    (i) Measure the tail rotor (T/R) drive vibration level without 
balancing the T/R drive, and record the amplitude value.
    (ii) Clean the oil cooler fan.
    (iii) Measure the T/R drive vibration level without balancing 
the T/R drive, and record the amplitude value.
    (iv) Calculate the difference between the two amplitude values. 
If the difference is greater than 0.75 inch per second (ips), before 
further flight, replace each oil cooler fan assembly bearing.
    (2) After the effective date of this AD, do not install an oil 
cooler fan assembly bearing with more than 0 hours TIS unless the 
requirements of this AD have been accomplished.

(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: 
Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy 
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, we suggest 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. AS355-
05.00.77, Revision 0, dated July 3, 2017, 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 http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review a copy of the 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 Aviation 
Safety Agency (EASA) AD No. 2017-0159, dated August 25, 2017. You 
may view the EASA AD on the internet at http://www.regulations.gov 
in Docket No. FAA-2018-0438.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor 
Driveshaft.

    Issued in Fort Worth, Texas, on September 12, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-20487 Filed 9-24-18; 8:45 am]
 BILLING CODE 4910-13-P