Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 52185 

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. 

(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 

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 

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, 


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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. 

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 

■ 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. 

(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. 


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Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 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/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] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2015–0772] 

Drawbridge Operation Regulation; 

Housatonic River, Stratford, CT 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of deviation from 

drawbridge regulation. 

SUMMARY: 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. 

DATES: 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. 

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 


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