32456 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

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 ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0075R1, dated 

April 24, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0568-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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) Zodiac Aerospace Service Bulletin 

766983–28–002, Revision 1, dated March 24, 

2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Zodiac Aerospace, Technical 

Publication Department, 61 Rue Pierre 

Curie—CS20001, 78373 Plaisir Cedex, 

France; phone: +33 (0)1 61 34 19 24; fax: +33 

(0)1 61 34 21 13; email: yann.laine@

zodiacaerospace.com; Internet: http://

www.zodiacaerospace.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 May 18, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13319 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0646; Directorate 

Identifier 2013–SW–053–AD; Amendment 

39–18174; AD 2015–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters (previously Eurocopter 

France) Model AS355E, AS355F, 

AS355F1, and AS355F2 helicopters 

with a Fueltron flowmeter installed. 

This AD requires removing each 

flowmeter, replacing the fuel system 

hoses, and disabling the electrical 

connections for the flowmeter 

installation. This AD was prompted by 

a report of particle contamination 

creating an obstruction in a flowmeter 

which resulted in an uncontrolled 

flame-out of the engine. The actions of 

this AD are intended to prevent 

obstruction of the fuel supply to the 

flowmeter, which could result in engine 

flame-out and subsequent loss of control 

of the helicopter. 

DATES: This AD is effective July 14, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 14, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

Helicopters, 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. It is also available 

on the Internet at http://

www.regulations.gov in Docket No. 

FAA–2014–0646. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office 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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 15, 2014, at 79 FR 

54925, 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, and 

AS355F2 helicopters with a certain 

flowmeter installed. The NPRM 

proposed to require, within 750 hours 

time-in-service, removing the flowmeter 

from each engine, replacing the fuel 

hose with part number (P/N) 704A34– 

416–029 for the left-hand (LH) engine 

and P/N 704A34–416–030 for the righthand (RH) engine, removing the 

flowmeter indicator, and disabling the 

flowmeter electrical connections. The 

proposed requirements were intended to 

prevent obstruction of the fuel supply to 

the flowmeter, which could result in 

engine flame-out and subsequent loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2013–0205, dated September 9, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Eurocopter (now Airbus 

Helicopters) Model AS355 E, AS355 F, 

AS355 F1, and AS355 F2 helicopters 

with modification 350A070791 

(installation of the Fueltron flowmeter), 

except helicopters with modification 

355A085801 (removal of the Fueltron 

flowmeter). EASA advises, after landing, 

an AS355 helicopter experienced an 

uncontrolled flame-out of the No. 1 

engine caused by particle contamination 

in the fuel that obstructed the Fueltron 

flowmeter. EASA further states that 

because the flowmeter installation is 

identical on both engines, this condition 

could lead to flame-out of both engines 

in flight, possibly resulting in reduced 

control of the helicopter. EASA AD No. 

2013–0205 requires removing the 


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Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32457 

flowmeter from each engine, modifying 

the fuel line system with new fuel lines, 

removing the flowmeter indicator, and 

disabling the flowmeter electrical 

connections. Since we issued the NPRM 

(79 FR 54925, September 15, 2014), the 

title of the approving official for 

Alternative Methods of Compliance 

(AMOCs) has changed. Thus, we have 

revised the title of the approving official 

from the Manager of the Regulations and 

Policy Group to the Manager of the 

Safety Management Group. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (79 FR 54925, September 15, 

2014). 

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 

these same type designs 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 design approval holder is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter issued Alert Service 

Bulletin (ASB) No. AS355–28.00.20, 

Revision 0, dated June 6, 2013, for 

Model AS355 E, AS355 F, AS355 F1, 

and AS355 F2 helicopters, which 

describes procedures for removing and 

disabling the Fueltron flowmeter 

installation. The ASB corresponds to 

Eurocopter modification 355A085801. 

This 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. 

Costs of Compliance 

We estimate that this AD will affect 

47 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, removing the flowmeter 

installation requires about 4 workhours, and required parts cost about 

$1,600, for a cost per helicopter of 

$1,940 and a total cost of $91,180 for the 

fleet. 

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: 

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): 

2015–12–01 Airbus Helicopters (Previously 

Eurocopter France): Amendment 39– 

18174; Docket No. FAA–2014–0646; 

Directorate Identifier 2013–SW–053–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model AS355E, AS355F, AS355F1, and 

AS355F2 helicopters, certificated in any 

category, with a Fueltron flowmeter part 

number (P/N) 704A37–670–001 installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

obstruction of the fuel supply to the 

flowmeter, which could result in engine 

shutdown and subsequent loss of control of 

the helicopter. 

(c) Effective Date 

This AD becomes effective July 14, 2015. 

(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 750 hours time-in-service: 

(i) Remove each flowmeter. 

(ii) Remove each left-hand hose, P/N 

704A34.4160.31, and install hose, P/N 

704A34–416–029, as depicted in Figures 1 

and 2 of Eurocopter Alert Service Bulletin 

No. AS355–28.00.20, Revision 0, dated June 

6, 2013 (ASB AS355–28.00.20). 

(iii) Remove each right-hand hose, P/N 

704A34.4160.32, and install hose, P/N 

704A34–416–030, as depicted in Figures 1 

and 2 of ASB AS355–28.00.20. 

(iv) Remove each flowmeter indicator and 

disable the flowmeter wiring as described in 

the Accomplishment Instructions, paragraph 

3.B.2.b., of ASB AS355–28.00.20. 

(2) After the effective date of this AD, do 

not install a flowmeter, P/N 704A37–670– 

001, on any helicopter. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 


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32458 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

2013–0205, dated September 9, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0646. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7333, Fuel Flow Sensor. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

AS355–28.00.20, Revision 0, dated June 6, 

2013. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, 2701 N. Forum Drive, Grand 

Prairie, Texas 75052; telephone (972) 641– 

0000 or (800) 232–0323; fax (972) 641–3775; 

or at http://www.airbushelicopters.com/

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on May 29, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13851 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0489; Directorate 

Identifier 2008–SW–003–AD; Amendment 

39–18175; AD 2015–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bell Helicopter Textron Canada Limited 

(Bell) Model 206L–1, 206L–3, and 

206L–4 helicopters. This AD requires 

installing a placard and revising the 

limitations section of the rotorcraft 

flight manual (RFM). This AD was 

prompted by several incidents of third 

stage engine turbine wheel failures 

caused by excessive vibrations at certain 

engine speeds during steady-state 

operations. The actions of this AD are 

intended to prevent turbine failure, 

engine power loss, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective July 14, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or 

at http://www.bellcustomer.com/files/. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the 

supplemental type certificate (STC), the 

Transport Canada Civil Aviation (TCCA) 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 7, 2013, at 78 FR 34282, 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 

certain Bell Model 206L–3 and 206L–4 

helicopters. The NPRM proposed to 

require installing a placard on the 

instrument panel below the dual 

tachometer and revising the Operating 

Limitations section of the Model 206L– 

3 and 206L–4 RFMs by inserting pages 

that limit steady-state operations 

between speeds of 71.8% and 91.5%. 

The proposed requirements were 

intended to prevent turbine failure, 

engine power loss, and subsequent loss 

of control of the helicopter. 

The NPRM was prompted by TCCA 

AD No. CF–2005–28R1, dated June 14, 

2007, to correct an unsafe condition for 

certain Model 206L–3 and 206L–4 

helicopters. TCCA, which is the aviation 

authority for Canada, advises of several 

failures of third stage turbine wheels 

used in Rolls-Royce 250–C30S and 250– 

C47B engines. According to TCCA, 

Rolls-Royce determined that detrimental 

vibrations can occur within a particular 

range of turbine speeds, and may be a 

contributing factor to these failures. Bell 

has revised the RFM and provided a 

corresponding decal to inform pilots to 

avoid steady-state operations between 

71.8% and 91.5% turbine speeds. The 

TCCA AD requires amending the RFMs, 

advising pilots of the change, and 

installing a decal as described in Bell 

Alert Service Bulletin (ASB) No. 206L– 

05–134, dated June 8, 2005, or later 

revisions. 

On October 3, 2014, at 79 FR 59695, 

the Federal Register published our 

supplemental notice of proposed 

rulemaking (SNPRM), which proposed 

to revise the applicability and change 

the procedures for updating the RFM. 

The SNPRM proposed adding Bell 

Model 206L–1 helicopters with Engine 

Upgrade Kit part number (P/N) 206– 

706–520 installed, to the applicability. 

Engine Upgrade Kit P/N 206–706–520 

replaces the Rolls-Royce 250–C28B 

engine with a Rolls-Royce 250–C30P 

engine. The condition causing the 

failures of third stage turbine wheels 

used in Rolls-Royce 250–C30S and 250– 

C–47B engines could also exist in RollsRoyce 250–C30P engines. The SNPRM 


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