Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 52185-52187 [2015-21202]

Download as PDF Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations effective date of this AD: Do the rototest inspection within 2,000 flight cycles or 4,000 flight hours after the effective date of this AD, whichever occurs first, but no later than before the accumulation of 46,000 total flight cycles or 92,000 total flight hours, whichever occurs first. (3) For airplanes that have less than 36,200 total flight cycles or 72,400 total flight hours as of the effective date of this AD: Do the rototest inspection before exceeding 38,200 total flight cycles or 76,400 total flight hours, whichever occurs first. (h) Corrective Action If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. Lhorne on DSK5TPTVN1PROD with RULES (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9–ANM–116– AMOC–REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0310, dated December 20, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0455-0002. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this VerDate Sep<11>2014 12:56 Aug 27, 2015 Jkt 235001 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) Airbus Service Bulletin A320–53–1257, dated December 21, 2012. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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 Renton, Washington, on August 13, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–20951 Filed 8–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0900; Directorate Identifier 2015–NE–12–AD; Amendment 39– 18251; AD 2015–17–18] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arrius 2F turboshaft engines with a certain part number oil pump installed. This AD requires inspection, and if necessary, replacement before further flight of the oil pump driver assembly and/or the oil pump shaft, or the oil pump itself. This AD was prompted by cases of deterioration of the gas generator front bearing due to a link loss between the pump driver and the oil pump shaft. We are issuing this AD to prevent link loss between the pump driver and the oil pump shaft, which could lead to an SUMMARY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 52185 engine in-flight shutdown, forced landing, and damage to the helicopter. DATES: This AD becomes effective October 2, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 2, 2015. ADDRESSES: For service information identified in this AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0900. 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–2015– 0900; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, 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: Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7770; fax: 781–238– 7199; email: philip.haberlen@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The NPRM was published in the Federal Register on May 21, 2015 (80 FR 29224). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: A risk of an in-flight shutdown (IFSD) has been identified on an ARRIUS 2F engine, due to deterioration of gas generator front bearing. This could be the result of lack of lubrication, E:\FR\FM\28AUR1.SGM 28AUR1 52186 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations due to a link loss between pump driver and oil pump shaft. This condition, if not detected and corrected, could lead to cases of IFSD, possibly resulting in forced landing with consequent damage to the helicopter and injury to occupants. Related Service Information Under 1 CFR Part 51 Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319 79 4834, Version B, dated October 21, 2014. The MSB describes procedures for inspecting the oil pump driver assembly on the oil pump shaft, the pump driver splines, and the oil pump splines. 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 of this AD. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 29224, May 21, 2015). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed. Lhorne on DSK5TPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects about 96 engines installed on helicopters of U.S. registry. We also estimate that it would take about two hours per engine to comply with this AD. The average labor rate is $85 per hour. Required parts would cost about $17,312 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,678,272. 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 VerDate Sep<11>2014 12:56 Aug 27, 2015 Jkt 235001 products identified in this rulemaking action. Regulatory Findings We 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2015–17–18 Turbomeca S.A.: Amendment 39–18251; Docket No. FAA–2015–0900; Directorate Identifier 2015–NE–12–AD. (a) Effective Date This AD becomes effective October 2, 2015. (b) Affected ADs None. Frm 00014 Fmt 4700 (d) Reason This AD was prompted by cases of deterioration of the gas generator front bearing due to a link loss between the pump driver and the oil pump shaft. We are issuing this AD to prevent link loss between the pump driver and the oil pump shaft, which could lead to an engine in-flight shutdown, forced landing, and damage to the helicopter. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Inspect the pump driver assembly on the oil pump shaft, the pump driver splines, and the oil pump splines, using paragraph 2.4.2, Operating Instructions, of Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 319 79 4834, Version B, dated October 21, 2014, as follows: (i) For engines with fewer than 250 engine hours (EH), accumulated since new, since last overhaul, or since last installation of an affected oil pump, whichever occurred later, inspect before exceeding 300 EH, accumulated since new, since last overhaul, or since last installation of an affected oil pump, as applicable. (ii) For engines with 250 EH or more, but fewer than 300 EH, accumulated since new, since last overhaul, or since last installation of an affected oil pump, whichever occurred later, inspect within 50 EH. (iii) For engines with 300 EH or more, but fewer than 800 EH, accumulated since new, since last overhaul, or since last installation of an affected oil pump, whichever occurred later, inspect within 100 EH. (iv) For engines with 800 EH or more, accumulated since new, since last overhaul, or since last installation of an affected oil pump, whichever occurred later, inspect during the next scheduled 500 EH inspection. (2) If any oil pump drive assembly and/or oil pump shaft, or the oil pump itself, fails the inspection required by this AD, then before further flight, replace the failed part(s) with part(s) eligible for installation. (3) The instruction to report inspection results and the instruction to return a compliance certificate to Turbomeca S.A. as stated in paragraph 2.4.2, Operating Instructions, of Turbomeca S.A. MSB No. 319 79 4834, Version B, dated October 21, 2014, are not required by this AD. (f) Credit for Previous Action (c) Applicability This AD applies to all Turbomeca S.A. Arrius 2F turboshaft engines with oil pump, part number (P/N) 0319155050, installed, except for: (1) Engines, equipped with an oil pump, P/N 0319155050, that were overhauled in a Turbomeca repair center after January 1, 2013, and PO 00000 (2) Engines with a serial number of 34776 or higher, provided that the oil pump was not replaced on that engine since the first flight of that engine on a helicopter. Sfmt 4700 If you inspected the oil pump driver assembly on the oil pump shaft, the pump driver splines, and the oil pump splines, and replaced any part(s) with part(s) eligible for installation before the effective date of this AD in accordance with Turbomeca S.A. MSB No. 319 79 4834, Version A, dated November 25, 2013, you met the requirements of this AD. E:\FR\FM\28AUR1.SGM 28AUR1 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations (g) Alternative Methods of Compliance (AMOCs) DEPARTMENT OF HOMELAND SECURITY The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (h) Related Information (1) For more information about this AD, contact Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7770; fax: 781–238–7199; email: philip.haberlen@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2015–0049, dated March 17, 2015 (Corrected May 7, 2015), for more information. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-0900-0002. (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 the AD specifies otherwise. (i) Turbomeca S.A. MSB No. 319 79 4834, Version B, dated October 21, 2014. (ii) Reserved. (3) For service information identified in this proposed AD, contact Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information 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 Burlington, Massachusetts, on August 17, 2015. Diane S. Romanosky, Acting Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–21202 Filed 8–27–15; 8:45 am] Lhorne on DSK5TPTVN1PROD with RULES BILLING CODE 4910–13–P VerDate Sep<11>2014 12:56 Aug 27, 2015 Jkt 235001 Coast Guard 33 CFR Part 117 [Docket No. USCG–2015–0772] Drawbridge Operation Regulation; Housatonic River, Stratford, CT Coast Guard, DHS. Notice of deviation from drawbridge regulation. AGENCY: ACTION: The Coast Guard has issued a temporary deviation from the operating schedule that governs the Devon Bridge, across the Housatonic River, mile 3.9, at Stratford, CT. This deviation is necessary to perform superstructure repairs and timber ties replacement. This deviation allows the bridge to remain in the closed position for 50 days. SUMMARY: This deviation is effective from 8 a.m. on October 5, 2015 to 8 a.m. on November 23, 2015. ADDRESSES: The docket for this deviation, [USCG–2015–0772] is available at http://www.regulations.gov. Type the docket number in the ‘‘SEARCH’’ box and click ‘‘SEARCH.’’ Click on Open Docket Folder on the line associated with this deviation. You may also visit the Docket Management Facility in Room W12–140, on the ground floor of the Department of Transportation West Building, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: If you have questions on this temporary deviation, contact Ms. Judy K. LeungYee, Project Officer, First Coast Guard District, telephone (212) 514–4330, email judy.k.leung-yee@uscg.mil. If you have questions on viewing the docket, call Ms. Cheryl Collins, Program Manager, Docket Operations, telephone (202) 366–9826. SUPPLEMENTARY INFORMATION: The Devon Bridge, mile 3.9, across Housatonic River has a vertical clearance in the closed position of 19 feet at mean high water and 25 feet at mean low water. The existing bridge operating regulations are found at 33 CFR 117.207(b). The waterway is transited by seasonal recreational vessels. Connecticut DOT requested this temporary deviation from the normal operating schedule to perform superstructure repairs and timber ties replacement. DATES: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 52187 Under this temporary deviation, the Devon Bridge will operate according to the schedule below: a. From 8 a.m. on October 5, 2015 through 4 a.m. on October 9, 2015, the bridge will not open to marine traffic. b. From 4 a.m. on October 9, 2015 through 8 a.m. on October 12, 2015, the bridge will open fully on signal upon 24 hour advance notice. c. From 8 a.m. on October 12, 2015 through 4 a.m. on October 16, 2015, the bridge will not open to marine traffic. d. From 4 a.m. on October 16, 2015 through 8 a.m. on October 19, 2015, the bridge will open fully on signal upon 24 hour advance notice. e. From 8 a.m. on October 19, 2015 trough 4 a.m. on October 23, 2015, the bridge will not open to marine traffic. f. From 4 a.m. on October 23, 2015 through 8 a.m. on October 26, 2015, the bridge will open fully on signal upon 24 hour advance notice. g. From 8 a.m. on October 26, 2015 through 4 a.m. on October 30, 2015, the bridge will not open to marine traffic. h. From 4 a.m. on October 30, 2015 through 8 a.m. on November 2, 2015, the bridge will open fully on signal upon 24 hour advance notice. i. From 8 a.m. on November 2, 2015 through 4 a.m. on November 6, 2015, the bridge will not open to marine traffic. j. From 4 a.m. on November 6, 2015 through 8 a.m. on November 9, 2015, the bridge will open fully on signal upon 24 hour advance notice. k. From 8 a.m. on November 9, 2015 through 4 a.m. on November 13, 2015, the bridge will not open to marine traffic. l. From 4 a.m. on November 13, 2015 through 8 a.m. on November 16, 2015, the bridge will open fully on signal upon 24 hour advance notice. m. From 8 a.m. on November 16, 2015 through 4 a.m. on November 20, 2015, the bridge will not open to marine traffic. n. From 4 a.m. on November 20, 2015 through 8 a.m. on November 23, 2015, the bridge will open fully on signal upon 24 hour advance notice. The bridge will not be able to open in the event of an emergency. There is no alternate route for vessel traffic; however, vessels that can pass under the closed draws during this closure may do so at any time. The Coast Guard will inform the users of the waterway through our Local and Broadcast Notice to Mariners of the change in operating schedule for the bridge so that vessels can arrange their transits to minimize any impact caused by the temporary deviation. In accordance with 33 CFR 117.35(e), the drawbridge must return to its regular E:\FR\FM\28AUR1.SGM 28AUR1

Agencies

[Federal Register Volume 80, Number 167 (Friday, August 28, 2015)]
[Rules and Regulations]
[Pages 52185-52187]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21202]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0900; Directorate Identifier 2015-NE-12-AD; 
Amendment 39-18251; AD 2015-17-18]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Arrius 2F turboshaft engines with a certain part number 
oil pump installed. This AD requires inspection, and if necessary, 
replacement before further flight of the oil pump driver assembly and/
or the oil pump shaft, or the oil pump itself. This AD was prompted by 
cases of deterioration of the gas generator front bearing due to a link 
loss between the pump driver and the oil pump shaft. We are issuing 
this AD to prevent link loss between the pump driver and the oil pump 
shaft, which could lead to an engine in-flight shutdown, forced 
landing, and damage to the helicopter.

DATES: This AD becomes effective October 2, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 2, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; 
telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA. For information on the availability of 
this material at the FAA, call 781-238-7125. It is also available on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-0900.

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-2015-
0900; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the mandatory continuing airworthiness information 
(MCAI), the regulatory evaluation, any comments received, and other 
information. The address for the Docket Office (phone: 800-647-5527) is 
Document Management Facility, 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: Philip Haberlen, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7770; 
fax: 781-238-7199; email: philip.haberlen@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 21, 2015 (80 FR 
29224). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A risk of an in-flight shutdown (IFSD) has been identified on an 
ARRIUS 2F engine, due to deterioration of gas generator front 
bearing. This could be the result of lack of lubrication,

[[Page 52186]]

due to a link loss between pump driver and oil pump shaft.
    This condition, if not detected and corrected, could lead to 
cases of IFSD, possibly resulting in forced landing with consequent 
damage to the helicopter and injury to occupants.

Related Service Information Under 1 CFR Part 51

    Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319 
79 4834, Version B, dated October 21, 2014. The MSB describes 
procedures for inspecting the oil pump driver assembly on the oil pump 
shaft, the pump driver splines, and the oil pump splines. 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 of this AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 29224, May 21, 
2015).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

Costs of Compliance

    We estimate that this AD affects about 96 engines installed on 
helicopters of U.S. registry. We also estimate that it would take about 
two hours per engine to comply with this AD. The average labor rate is 
$85 per hour. Required parts would cost about $17,312 per engine. Based 
on these figures, we estimate the cost of this AD on U.S. operators to 
be $1,678,272.

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 products identified in this 
rulemaking action.

Regulatory Findings

    We 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-17-18 Turbomeca S.A.: Amendment 39-18251; Docket No. FAA-2015-
0900; Directorate Identifier 2015-NE-12-AD.

(a) Effective Date

    This AD becomes effective October 2, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Turbomeca S.A. Arrius 2F turboshaft 
engines with oil pump, part number (P/N) 0319155050, installed, 
except for:
    (1) Engines, equipped with an oil pump, P/N 0319155050, that 
were overhauled in a Turbomeca repair center after January 1, 2013, 
and
    (2) Engines with a serial number of 34776 or higher, provided 
that the oil pump was not replaced on that engine since the first 
flight of that engine on a helicopter.

(d) Reason

    This AD was prompted by cases of deterioration of the gas 
generator front bearing due to a link loss between the pump driver 
and the oil pump shaft. We are issuing this AD to prevent link loss 
between the pump driver and the oil pump shaft, which could lead to 
an engine in-flight shutdown, forced landing, and damage to the 
helicopter.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Inspect the pump driver assembly on the oil pump shaft, the 
pump driver splines, and the oil pump splines, using paragraph 
2.4.2, Operating Instructions, of Turbomeca S.A. Mandatory Service 
Bulletin (MSB) No. 319 79 4834, Version B, dated October 21, 2014, 
as follows:
    (i) For engines with fewer than 250 engine hours (EH), 
accumulated since new, since last overhaul, or since last 
installation of an affected oil pump, whichever occurred later, 
inspect before exceeding 300 EH, accumulated since new, since last 
overhaul, or since last installation of an affected oil pump, as 
applicable.
    (ii) For engines with 250 EH or more, but fewer than 300 EH, 
accumulated since new, since last overhaul, or since last 
installation of an affected oil pump, whichever occurred later, 
inspect within 50 EH.
    (iii) For engines with 300 EH or more, but fewer than 800 EH, 
accumulated since new, since last overhaul, or since last 
installation of an affected oil pump, whichever occurred later, 
inspect within 100 EH.
    (iv) For engines with 800 EH or more, accumulated since new, 
since last overhaul, or since last installation of an affected oil 
pump, whichever occurred later, inspect during the next scheduled 
500 EH inspection.
    (2) If any oil pump drive assembly and/or oil pump shaft, or the 
oil pump itself, fails the inspection required by this AD, then 
before further flight, replace the failed part(s) with part(s) 
eligible for installation.
    (3) The instruction to report inspection results and the 
instruction to return a compliance certificate to Turbomeca S.A. as 
stated in paragraph 2.4.2, Operating Instructions, of Turbomeca S.A. 
MSB No. 319 79 4834, Version B, dated October 21, 2014, are not 
required by this AD.

(f) Credit for Previous Action

    If you inspected the oil pump driver assembly on the oil pump 
shaft, the pump driver splines, and the oil pump splines, and 
replaced any part(s) with part(s) eligible for installation before 
the effective date of this AD in accordance with Turbomeca S.A. MSB 
No. 319 79 4834, Version A, dated November 25, 2013, you met the 
requirements of this AD.

[[Page 52187]]

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Philip Haberlen, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7770; fax: 781-238-7199; email: 
philip.haberlen@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0049, 
dated March 17, 2015 (Corrected May 7, 2015), for more information. 
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0900-0002.

(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 the AD specifies otherwise.
    (i) Turbomeca S.A. MSB No. 319 79 4834, Version B, dated October 
21, 2014.
    (ii) Reserved.
    (3) For service information identified in this proposed AD, 
contact Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 
40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.
    (5) You may view this service information 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/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 17, 2015.
Diane S. Romanosky,
Acting Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-21202 Filed 8-27-15; 8:45 am]
 BILLING CODE 4910-13-P