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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32459 

also proposed removing Bell Model 

206L–3 and 206L–4 helicopters having 

Rolls-Royce 250–C20R engines installed 

under STC No. SR00036SE from the 

applicability because that engine is not 

affected by the unsafe condition. The 

SNPRM also proposed changing the 

procedures for modifying the RFM 

Limitations Section from inserting 

revised RFM pages to inserting a copy 

of this AD into the RFM or by making 

pen and ink changes. 

Comments 

We gave the public the opportunity to 

comment on the SNPRM (79 FR 59695, 

October 3, 2014) but we received no 

comments. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCCA, its 

technical representative, has notified us 

of the unsafe condition described in the 

TCCA AD. We are issuing this AD 

because we evaluated all information 

provided by TCCA, reviewed the 

relevant information, considered the 

comment received, 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. 

Differences Between This AD and the 

TCCA AD 

The TCCA AD requires compliance 

within 10 calendar days; this AD 

requires compliance within 30 days. 

This AD is applicable to Model 206L– 

1 helicopters with Engine Upgrade Kit 

P/N 206–706–520 installed because the 

same unsafe condition exits on this 

model, and the TCCA AD is not. 

Related Service Information 

Bell issued ASB No. 206L–05–134, 

Revision A, dated April 9, 2007, which 

describes procedures for installing a 

placard on the instrument panel below 

the main rotor RPM (Nr)/power turbine 

RPM (N2) dual tachometer and for 

inserting the RFM changes into the 

flight manual. Revision A of the ASB 

was issued to exclude Bell Model 206L– 

3 and 206L–4 helicopters with 250– 

C20R engines installed under STC No. 

SR00036SE from the requirements of the 

ASB. 

Costs of Compliance 

We estimate that this AD will affect 

616 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Based on an average labor rate 

of $85 per work-hour, amending the 

RFM requires about 0.5 work-hour, for 

a cost per helicopter of about $43 and 

a cost to U.S. operators of $26,488. 

Installing the decal requires about 0.2 

work-hour, and required parts cost $20, 

for a cost per helicopter of $37 and a 

cost to U.S. operators of $22,792. Based 

on these estimates, the total cost of this 

AD is $80 per helicopter and $49,280 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): 

2015–12–02 Bell Helicopter Textron Canada 

Limited (Bell): Amendment 39–18175; 

Docket No. FAA–2013–0489; Directorate 

Identifier 2008–SW–003–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Bell Model 206L–1 with an Engine 

Upgrade Kit part number (P/N) 206–706– 

520–101 installed; 

(2) Bell Model 206L–3, serial number (S/ 

N) 51001 through 51612, except those with 

a Rolls-Royce 250–C20R engine installed 

under Supplemental Type Certificate (STC) 

No. SR00036SE; and 

(3) Bell Model 206L–4, S/N 52001 through 

52313, except those with a Rolls-Royce 250– 

C20R engine installed under STC No. 

SR00036SE. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

third stage turbine vibration, which could 

result in turbine failure, engine power loss, 

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 

Within 30 days: 

(1) Install placard P/N 230–075–213–117, 

or equivalent, on the instrument panel 

directly below the dual tachometer. 

(2) Revise the Operating Limitations 

section of the Rotorcraft Flight Manual (RFM) 

by inserting a copy of this AD into the RFM 

or by making pen and ink changes as follows: 

(i) In the Power Plant section, beneath the 

Power Turbine RPM header, add: Avoid 

continuous operations 71.8% to 91.5%. 

(ii) In the Placards and Decals section, add: 

‘‘AVOID CONT OPS 71.8% TO 91.5% N2’’ 

with the location identification ‘‘Location: 

Instrument Panel.’’ 


tkelley on DSK3SPTVN1PROD with RULES
32460 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

(f) 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 

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. 

(g) Additional Information 

(1) Bell Alert Service Bulletin No. 206L– 

05–134, Revision A, dated April 9, 2007, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. 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 a copy of the service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) STC No. SR00036SE, amended October 

20, 1995; and reissued January 23, 2014, may 

be found on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2013–0489. 

(3) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2005–28R1, dated June 14, 2007. You 

may view the TCCA AD on the Internet at 

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

FAA–2013–0489. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250, Turbine Section. 

Issued in Fort Worth, Texas, on May 29, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13852 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–2014–1020; Directorate 

Identifier 2013–SW–078–AD; Amendment 

39–18172; AD 2015–11–09] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Type Certificate 

Previously Held by Schweizer Aircraft 

Corporation) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (type 

certificate previously held by Schweizer 

Aircraft Corporation) (Sikorsky) Model 

269D and Model 269D Configuration A 

helicopters. This AD requires reducing 

the life limit of the ring gear carrier 

assembly. This AD was prompted by 

cracks in the ring gear carrier assembly. 

The actions are intended to reduce the 

life of the ring gear carrier assembly to 

prevent failure of the main rotor 

transmission, loss of engine power to 

the main rotor, 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 Sikorsky 

Aircraft Corporation, Customer Service 

Engineering, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

Winged-S or 203–416–4299; email 

sikorskywcs@sikorsky.com. You may 

review a copy of 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 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: 

Norman Perenson, Aviation Safety 

Engineer, New York Aircraft 

Certification Office, Propulsion & 

Services Branch, FAA, 1600 Stewart 

Ave., Westbury, New York; telephone 

(516) 228–7337; email 

Norman.Perenson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 15, 2014, at 79 FR 

74037, 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 Sikorsky Model 269D 

and Model 269D Configuration A 

helicopters with a certain partnumbered ring carrier assembly 

installed. The NPRM proposed to 

require reducing the life limit of the ring 

carrier assembly from 6,000 hours timein-service (TIS) to 5,000 hours TIS by 

revising the Airworthiness Limitations 

Section of the applicable maintenance 

manual and by removing from service 

any ring carrier assembly that exceeded 

the new life limit. The NPRM was 

prompted by the discovery of a crack in 

the ring gear carrier assembly, which 

extended around the entire 

circumference of the flange and 

intersected some of the bolt holes but 

did not propagate ‘‘bolt hole to bolt 

hole.’’ A metallurgical evaluation 

determined that fretting caused multiple 

origin fatigue cracking on the ring gear 

carrier assembly. The proposed 

requirements were intended to reduce 

the life of the ring gear carrier assembly 

to prevent failure of the main rotor 

transmission, loss of engine power to 

the main rotor, and subsequent loss of 

control of the helicopter. 

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 74037, December 15, 

2014). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

Sikorsky issued 269D Helicopter Alert 

Service Bulletin No. ASB DB–040A, 

Revision A, dated December 4, 2012, to 

implement a reduction in service life of 

the ring gear carrier assembly, part 

number 269A5194, from 6,000 flight 

hours to 5,000 flight hours. 


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