34284 Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Bell Helicopter Textron Canada Limited 

(Bell): 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–3, serial number 

(S/N) 51001 through 51612; and 

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

52313. 

(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) Comments Due Date 

We must receive comments by August 6, 

2013. 

(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) For Model 206L–3 helicopters, revise 

the Operating Limitations section of the 

Model 206L–3 Rotorcraft Flight Manual 

(RFM) by inserting Section 1, Limitations, 

pages 1–7 and 1–8, of Bell BHT–206L3– 

FM–1, revision 6, dated April 26, 2005. 

(3) For Model 206L–4 helicopters, revise 

the Operating Limitations section of the 

Model 206L–4 RFM by inserting Section 1, 

Limitations, pages 1–6 and 1–13, of Bell 

BHT–206L4–FM–1, Revision 2, dated August 

22, 2008. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@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) The subject of this AD is addressed in 

Transport Canada AD No. CF–2005–28R1, 

dated June 14, 2007 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

Issued in Fort Worth, Texas, on May 29, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13483 Filed 6–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0940; Directorate 

Identifier 2012–NE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Turbomeca S.A. Arriel 

2D turboshaft engines. The existing AD 

currently requires replacing the 

hydromechanical metering unit (HMU) 

at a reduced life. Since we issued that 

AD, further cases of deterioration of 

HMU rotating components have been 

reported before the HMU reached the 

replacement interval in that AD. The 

proposed AD would maintain the 

existing AD requirements and would 

also require inspections of the HMU. We 

are proposing this AD to prevent an 

uncommanded in-flight shutdown of the 

engine, and possible loss of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by August 6, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Turbomeca, 40220 


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Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 34285 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: frederick.zink@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0940; Directorate Identifier 

2012–NE–26–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On January 11, 2013, we issued AD 

2013–01–07, Amendment 39–17321 (78 

FR 6725, January 31, 2013), for all 

Turbomeca S.A. Arriel 2D turboshaft 

engines. That AD requires replacing the 

HMU at a reduced life. That AD resulted 

from a low fuel pressure event caused 

by deterioration and a loss of the lowpressure drive function within the 

HMU. We issued that AD to prevent an 

uncommanded in-flight shutdown of the 

engine, and possible loss of the 

helicopter. 

Actions Since Existing AD Was Issued 

Since we issued AD 2013–01–07 (78 

FR 6725, January 31, 2013), further 

cases of deterioration of HMU rotating 

components have been reported before 

the HMU reached the replacement 

interval in that AD. Also since we 

issued AD 2013–01–07, the European 

Aviation Safety Agency (EASA) issued 

AD 2013–0079, dated March 22, 2013. 

EASA’s AD imposes the same reduced 

life as AD 2013–01–07, and, also 

requires inspections of the HMU. 

Relevant Service Information 

We reviewed Turbomeca S.A. Alert 

Mandatory Service Bulletin (MSB) No. 

A292 73 2847, Version B, dated March 

6, 2013. The Alert MSB describes 

procedures for inspecting and/or 

replacing the HMU. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would maintain 

the existing AD requirements of AD 

2013–01–07 (78 FR 6725, January 31, 

2013), and would also require 

inspections of the HMU. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 56 Arriel 2D turboshaft 

engines installed on helicopters of U.S. 

registry. We also estimate that it would 

take about two hours per engine to 

comply with this proposed AD. The 

average labor rate is $85 per hour. 

Required parts would cost about 

$14,400 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators is 

$815,920. 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2013–01–07, Amendment 39–17321 (78 

FR 6725, January 31, 2013), and adding 

the following new AD: 

Turbomeca S.A: Docket No. FAA–2012– 

0940; Directorate Identifier 2012–NE– 

26–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 6, 2013. 


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34286 Federal Register / Vol. 78, No. 110 / Friday, June 7, 2013 / Proposed Rules 

(b) Affected ADs 

This AD supersedes AD 2013–01–07, 

Amendment 39–17321 (78 FR 6725, January 

31, 2013). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arriel 2D turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by further cases of 

deterioration of hydromechanical metering 

unit (HMU) rotating components that have 

been reported before the HMU reached the 

replacement interval in AD 2013–01–07 (78 

FR 6725, January 31, 2013). We are issuing 

this AD to prevent an uncommanded in-flight 

shutdown of the engine, and possible loss of 

the helicopter. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Replace inter-pump complete sleeve, 

and inspect the female splines and HMU 

high-pressure (HP) pump and low-pressure 

(LP) pump male splines for corrosion, 

scaling, cracks and wear, at the following: 

(i) Before exceeding 400 HMU operating 

hours since new if the HMU has 375 or fewer 

operating hours on the effective date of this 

AD; or 

(ii) Within 25 HMU operating hours if the 

HMU has more than 375 operating hours on 

the effective date of this AD; and 

(iii) Thereafter, at intervals not to exceed 

400 HMU operating hours. 

(iv) Use Section 2.B.(1) of the Instructions 

to be Incorporated of Turbomeca S.A. Alert 

Mandatory Service Bulletin (MSB) No. A292 

73 2847, Version B, dated March 6, 2013, to 

accomplish the replacement and visual 

inspection required by paragraph (e)(1) of 

this AD. 

(v) If the HMU does not pass the initial or 

repetitive visual inspections required by 

paragraph (e)(1) of this AD, then before next 

flight, replace the affected HMU with an 

HMU eligible for installation. 

(2) Replace the rotating components of the 

HP and LP pumps, including the complete 

sleeve, or replace the HMU with an HMU 

eligible for installation at the following: 

(i) Before exceeding 800 HMU operating 

hours since new; or 

(ii) Within 800 HMU operating hours since 

last replacement of LP and HP fuel pumps 

rotating components; whichever occurs later. 

(iii) Thereafter, replace the LP and HP fuel 

pump rotating components within every 800 

HMU operating hours. 

(iv) Use Section 2.B.(1) of the Instructions 

to be Incorporated of Turbomeca S.A. Alert 

MSB No. A292 73 2847, Version B, dated 

March 6, 2013, to accomplish the 

replacements required by paragraph (e)(2) of 

this AD. 

(f) Credit for Previous Actions 

If before the effective date of this AD, you 

complied with Turbomeca S.A. Alert MSB 

No. A292 73 2847, Version A, dated May 29, 

2012, you met the initial inspection 

requirements in paragraph (e) of this AD. 

However, you must still comply with the 

repetitive inspection requirements of this 

AD. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any HMU onto any engine, or install 

any engine onto any helicopter, unless the 

HMU is in compliance with this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) European Aviation Safety Agency AD 

2013–0079, dated March 22, 2013, 

Turbomeca S.A. Alert MSB No. A292 73 

2847, Version B, dated March 6, 2013, and 

Turbomeca Maintenance Manual Task 73– 

23–00–802–A01, pertain to the subject of this 

AD. 

(3) For service information identified in 

this AD, contact Turbomeca, 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. 

Issued in Burlington, Massachusetts, on 

June 3, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–13509 Filed 6–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0490; Directorate 

Identifier 2008–SW–004–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bell Model 407 helicopters. This 

proposed AD would require installing a 

placard beneath the NR/NP dual 

tachometer and revising the limitations 

section of the rotorcraft flight manual 

(RFM). This proposed AD is prompted 

by several incidents of third stage 

engine turbine wheel failures, which 

were caused by excessive vibrations at 

certain engine speeds during steadystate operations. The proposed actions 

are intended to alert pilots to avoid 

certain engine speeds during steadystate operations, prevent failure of the 

third stage engine turbine, engine power 

loss, and subsequent loss of control of 

the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 6, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed 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. 

FOR FURTHER INFORMATION CONTACT: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email 

chinh.vuong@faa.gov. 


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