Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 53153 

January 28, 2009; or 328 Support Services 

Service Bulletin SB–328J–25–235, dated 

January 28, 2009, as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. (Only the odd-numbered 

pages of these documents contain the issue 

dates of the documents.) 

(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 Global Support Center, P.O. 

Box 1252, D–82231 Wessling, Federal 

Republic of Germany; telephone +49 8153 

88111 6666; fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 30, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–24448 Filed 10–15–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0348; Directorate 

Identifier 2008–NE–39–AD; Amendment 39– 

16050; AD 2009–21–11] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. ARRIUS 1A 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: 

Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

We are issuing this AD to prevent 

failure of the balancing piston, which 

could result in an engine in-flightshutdown and the release of high-energy 

debris and damage to the helicopter. 

DATES: This AD becomes effective 

November 20, 2009. 

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 

& 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 April 17, 2009 (74 FR 

17797). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

As of the publication date of this 

Airworthiness Directive, no ARRIUS 1A 

engines in service are fitted with a balancing 

piston that has logged more than 16 000 

cycles, and the outlook for the consumption 

of cycles on the ARRIUS 1A fleet indicates 

that no balancing pistons will exceed this 

new limit for a few years’ time. 

Moreover, this new cycle life limit value 

for the balancing piston has been 

incorporated since the end of 2007 in 

ARRIUS 1A Maintenance documentation. 

Failure to comply with the new life limits 

provided in the Airworthiness Limitations 

Section of ARRIUS 1A Maintenance 

documentation could potentially result in an 

engine in-flight-shutdown and the release of 

high energy debris. 

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 

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. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI requires modifying the 

cyclic life limit value of the balancing 

piston in the engine log book as 

specified in Turbomeca Mandatory 

Service Bulletin 319 72 0811, dated 

April 30, 2008, and updating the 

approved operator’s maintenance 

program. 

We are requiring removing from 

service ARRIUS 1A engines containing 

a balancing piston, P/N 0 319 20 152 0, 

before the balancing piston meets or 

exceeds the new, reduced cyclic life 

limit value of 16,000 cycles-since-new. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD would affect about 

33 products of U.S. registry. We also 

estimate that it would take about 0.5 

work-hour per product to comply with 

this AD. The average labor rate is $80 

per work-hour. Required parts would 

cost about $5,280 per product. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $175,560. 

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 


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53154 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 

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, 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: 

2009–21–11 Turbomeca S.A.: Amendment 

39–16050. Docket No. FAA–2009–0348; 

Directorate Identifier 2008–NE–39–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 20, 2009. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca S.A. 

ARRIUS 1A turboshaft engines with 

balancing pistons, part number (P/N) 0 319 

20 152 0, installed. These engines are 

installed on, but not limited to, Eurocopter 

AS355N helicopters. 

Reason 

(d) Cycle life limit value for ARRIUS 1A 

balancing piston Part Number (P/N) 0 319 20 

152 0, initially set at 40 000 cycles, has been 

reduced to 16 000 cycles, following the 

discovery of a calculation error during a 

recent review of the ARRIUS 1 engine family 

files. 

We are issuing this AD to prevent failure 

of the balancing piston, which could result 

in an engine in-flight-shutdown and the 

release of high-energy debris and damage to 

the helicopter. 

Actions and Compliance 

(e) Unless already done, for ARRIUS 1A 

engines with a balancing piston, P/N 0 319 

20 152 0, installed, remove the engine from 

service before the balancing piston 

accumulates 16,000 cycles-since-new (CSN). 

Installation Prohibition 

(f) After the effective date of this AD, don’t 

return to service any engine that has a 

balancing piston that has accumulated 16,000 

or more CSN. 

FAA AD Differences 

(g) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) or service information as follows: 

(1) This AD requires removing from 

service, any ARRIUS 1A engine that has a 

balancing piston, P/N 0 319 20 152 0, with 

16,000 CSN installed. 

(2) We prohibit returning to service any 

ARRIUS 1A engine that has a balancing 

piston, P/N 0 319 20 152 0, with 16,000 or 

more CSN. 

Other FAA AD Provisions 

(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 Airworthiness Directive 

2008–0133, dated July 17, 2008 for related 

information. 

(j) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & 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) None. 

Issued in Burlington, Massachusetts, on 

October 8, 2009. 

Diane S. Romanosky, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–24853 Filed 10–15–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1369; Directorate 

Identifier 2003–NE–03–AD; Amendment 39– 

16048; AD 2009–21–09] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Trent 800 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Rolls-Royce plc RB211 Trent 875–17, 

Trent 877–17, Trent 884–17, Trent 892– 

17, Trent 892B–17, and Trent 895–17 

turbofan engines with high-pressure 

(HP) compressor rotor rear stage 5 and 

6 discs and cone shafts, part numbers 

(P/Ns) FK25230 and FK27899 installed. 

That AD currently requires removal 

from service of these HP compressor 

rotor rear stage 5 and 6 discs and cone 

shafts before reaching newly reduced 

life limits. This AD requires removing 

these parts at new reduced cycle limits. 

This AD results from Rolls-Royce plc 

reducing the lives of these parts and 

changing the life calculating method to 

use ‘‘Standard Duty Cycles’’ with 

‘‘Multiple Flight Profile Monitoring’’ 

and ‘‘Flight Cycles’’ with ‘‘Heavy Flight 

Profile Monitoring’’. We are issuing this 

AD to prevent stage 5 and 6 disc crack 

initiation and propagation that might 

lead to uncontained disc failure and 

damage to the airplane. 

DATES: This AD becomes effective 

November 20, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31, Derby, 

DE24 8BJ, UK, telephone 44 (0) 1332 

242424; fax 44 (0) 1332 249936. 

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: The FAA 

proposed to amend 14 CFR part 39 by 


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