DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[4910-13-P] 

[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 Adminjstration (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-fl ight shutdown, forced landing, and damage to the helicopter. 

DATES: This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

The Director of the federal Register approved the incorporation by reference of a 

certain publication listed in this AD as of [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

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 inforn1ation 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. F AA-20 15-0900. 

Examining the AD Docket 

You may examine the AD docket on the Intemet 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 tlus AD, the mandatory continuing airworthiness 

infom1ation (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 W 12- 140, 1200 New Jersey Avenue SE., 

Washinf,rton, 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-fl ight 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, due to a 

link loss between pump driver and oil pump shaft. 

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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 , 20 15). 

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 thjs 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 I 06, describes the authority of the FAA Administrator. 

"Subtitle VII: Aviation Programs," describes in more detail the scope of the Agency's 

authority. 

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We are issuing this rulemaking under the authority described in "Subtitle VII, 

Part A, Subpart III, Section 44 701: 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 Executi ve Order 12866, 

(2) Is not a "significant rule" under the DOT Regulatory Policies and Procedures 

( 44 FR I I 034, February 26, 1979), 

(3) Wi ll 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: 

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PART 39 -AIRWORTHINESS DIRECTIVES 

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

Authori ty: 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 20 15-NE-12-AD. 

(a) Effective Date 

This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Turbomeca S.A. AtTius 2F turboshaft engines with oi l 

pump, part number (PIN) 0319155050, installed, except for: 

(1) Engines, equipped with an oil pump, PIN 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. 

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(c) Actions a nd 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 EI-1. 

(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 1 00 EH. 

(iv) For engines with 800 El-l 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) e ligible 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, ofTurbomeca S.A. MSB No. 319 79 4834, Version B, dated October 2 1, 

2014, are not required by this AD. 

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(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. 

(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: phi1ip.haberlen@faa.gov. 

(2) Refer to MCAJ European Aviation Safety Agency AD 2015-0049, dated 

March 17, 2015 (Corrected May 7, 20 15), for more infom1ation. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/#!documentDetail;D=F AA-20 I 5-0900-0002. 

(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. 

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(ii) Reserved. 

(3) For service information identified in this proposed AD, contact Turbomeca, 

S.A., 40220 Tamas, France; phone: 33 (0)5 59 74 40 00; te lex: 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 infom1ation on the 

ava il ability of this material at the FAA, call 781-238-71 25. 

(5) You may view this service information at the National Archives and Records 

Administration (NARA). For information on the ava il ability of this material at NARA, 

call 202-74 1-6030, or go to: http://www.archivcs.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on August 17. 2015. 

~\l Gf~y Diane S. Romanosky, 

Acting Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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