Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 2067 

Previous Credit 

(i) Initial inspection of LP turbine rear 

frames before the effective date of this AD 

performed using the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0579, original issue, 

Revision 1, Revision 2, Revision 3, or 

Revision 4, satisfy the requirements of 

paragraphs (f)(1), (f)(2), (g)(1), and (g)(2) of 

this AD. 

(j) Initial inspection of LP turbine rear 

frames before the effective date of this AD 

performed using the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0558, original issue, 

Revision 1, or Revision 2, satisfy the 

requirements of paragraphs (h)(1) and (h)(2) 

of this AD. 

Alternative Methods of Compliance 

(k) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(l) European Aviation Safety Agency AD 

2009–0009 (corrected), dated January 27, 

2009, also addresses the subject of this AD. 

(m) Contact Antonio Cancelliere, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine and Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

antonio.cancelliere@faa.gov; telephone (781) 

238–7751; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

specified in the following Table 1 to perform 

the inspections required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in the following Table 1 in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact CFM International, Technical 

Publications Department, 1 Neumann Way, 

Cincinnati, OH 45215; telephone (513) 552– 

2800; fax (513) 552–2816, for a copy of this 

service information. You may review copies 

at the FAA, New England Region, 12 New 

England Executive Park, Burlington, MA; or 

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. 

TABLE 1—INCORPORATION BY REFERENCE

Service Bulletin No. Page Revision Date 

CFM56–7B S/B 72–0558 ................................................................................. All ................................ 3 March 30, 2009. 

Total Pages: 22 

CFM56–7B S/B 72–0579 ................................................................................. All ................................ 5 March 30, 2009 

Total Pages: 23 

Issued in Burlington, Massachusetts, on 

December 23, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31043 Filed 1–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0503; Directorate 

Identifier 2009–NE–12–AD; Amendment 39– 

16172; AD 2010–02–01] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Model Arriel 1B, 1D, and 1D1 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The rupture of the Reduction Gear Box 

Intermediate Pinion may result in an 

overspeed of the Power Turbine and, 

subsequently, an uncommanded engine inflight shutdown. This could lead to an 

emergency autorotation landing on a singleengine helicopter. 

We are issuing this AD to prevent the 

rupture of the reduction gear box 

intermediate pinion, which could result 

in an overspeed of the power turbine, an 

uncommanded in-flight shutdown of the 

engine, and an emergency autorotation 

landing. 

DATES: This AD becomes effective 

February 18, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

February 18, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 12, 2009 (74 FR 27946). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several events of rupture of the Arriel 1 

Reduction Gear Box Intermediate Pinion 

have been reported in service. The ruptures 

have been determined to be originated at the 

pinion teeth root due to increased vibratory 

stresses. This increase in vibratory stresses is 

mainly caused by increased teeth wear over 

engine life time. 

The rupture of the Reduction Gear Box 

Intermediate Pinion may result in an 

overspeed of the Power Turbine and, 

subsequently, an uncommanded engine inflight shutdown. This could lead to an 

emergency autorotation landing on a singleengine helicopter. 

To reduce the level of vibratory stresses 

and improve tooth resistance, Turbome ́ca 

modification incorporates the addition of a 

damping ring below the teeth and a shot 

peening of the teeth roots. These 

modifications reduce the risk of incipient 

fatigue cracks. 

This AD requires the replacement of all 

Reduction Gear Box Intermediate Pinions 

with Pinions incorporating Turbome ́ca 

modification TU 232. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 


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2068 Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD would affect about 

13 products of U.S. registry. We also 

estimate that it would take about 6 

work-hours per product to comply with 

this AD. The average labor rate is $80 

per work-hour. Required parts would 

cost about $1,272 per product. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $22,776. 

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); and 

3. 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 AD: 

2010–02–01 Turbomeca S.A.: Amendment 

39–16172: Docket No. FAA–2009–0503; 

Directorate Identifier 2009–NE–12–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 18, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca Arriel 

1B, 1D, and 1D1 turboshaft engines. These 

engines are installed on, but not limited to, 

Eurocopter France AS350B, AS350BA, 

AS350B1, and AS350B2 helicopters. 

Reason 

(d) This AD results from several events of 

rupture of the Arriel 1 reduction gear box 

intermediate pinions. We are issuing this AD 

to prevent the rupture of the reduction gear 

box intermediate pinion, which could result 

in an overspeed of the power turbine, an 

uncommanded in-flight shutdown of the 

engine, and an emergency autorotation 

landing. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(f) No later than 28 February 2011, replace 

the Reduction Gear Box Intermediate Pinions 

(P/N 0 292 70 779 0) with Pinions 

incorporating Turbome ́ca modification TU 

232 in accordance with Turbome ́ca 

Mandatory Service Bulletin 292 72 0276 

Version B dated 06 November 2008. 

FAA AD Differences 

(g) None. 

(h) Alternative Methods of Compliance 

(AMOCs): The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2009–0002, dated January 7, 2009, 

for related information. 

(j) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use Turbomeca Mandatory 

Service Bulletin No. 292 72 0276, Version B, 

dated November 6, 2008, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Turbomeca, 40220 Tarnos, 

France; telephone: 33 05 59 74 40 00; fax: 33 

05 59 74 45 15, or go to: http:// 

www.turbomeca-support.com. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or 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 

December 31, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–337 Filed 1–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employee Benefits Security 

Administration 

29 CFR Part 2510 

RIN 1210–AB02 

Definition of ‘‘Plan Assets’’— 

Participant Contributions 

AGENCY: Employee Benefits Security 

Administration, Department of Labor. 


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