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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Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 53155 

superseding AD 2003–15–06, 

Amendment 39–13249 (68 FR 44610, 

July 30, 2003), with a proposed AD. The 

proposed AD applies to 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 HP compressor rotor rear 

stage 5 and 6 discs and cone shafts, P/ 

Ns FK25230 and FK27899 installed. We 

published the proposed AD in the 

Federal Register on April 27, 2009 (74 

FR 19025). That action proposed to 

require changing the life calculating 

method to use ‘‘Standard Duty Cycles’’ 

with ‘‘Multiple Flight Profile 

Monitoring’’ and ‘‘Flight Cycles’’ with 

‘‘Heavy Flight Profile Monitoring’’, and 

reducing the lives of the affected parts 

to 5,000 ‘‘Standard Duty Cycles’’ or 

‘‘5,000 Flight cycles’’, respectively. 

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. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

One commenter, Kenya Airways 

Limited, requests that in the compliance 

section, we insert ‘‘Rolls-Royce plc Alert 

Service Bulletin No. RB.211–72–AE082, 

Revision 7, dated June 18, 2008, 

pertains to the subject of this AD.’’ 

We do not agree. That information 

already exists in paragraph (k) of the 

AD. We did not change the AD. 

One commenter, American Airlines, 

states that the FAA should include a 

reasonable schedule for operators to 

manage the replacement of parts with 

lives already in excess of the proposed 

reduced limit, to avoid unnecessary and 

unreasonable hardship once the final 

rule becomes effective. 

We do not agree. We have confirmed 

that all U.S. operators are already 

operating to the reduced life limit 

specified in this AD. There are no U.S. 

operators with parts lives in excess of 

the reduced limit. We did not change 

the AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

94 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 installed on airplanes 

of U.S. registry. Removal of these HP 

compressor rotor rear stage 5 and 6 discs 

and cone shafts will not impose any 

additional labor costs if performed at 

the time of scheduled engine overhaul. 

The prorated life loss is about $225,000 

per engine. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $21,150,000. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 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); 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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 

removing Amendment 39–13249 (68 FR 

44610, July 30, 2003), and by adding a 

new airworthiness directive, 

Amendment 39–16048, to read as 

follows: 

2009–21–09 Rolls-Royce plc: Amendment 

39–16048. Docket No. FAA–2009–1369; 

Directorate Identifier 2003–NE–03–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 20, 2009. 

Affected ADs 

(b) This AD supersedes AD 2003–15–06, 

Amendment 39–13249. 

Applicability 

(c) This AD applies to 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 highpressure (HP) compressor rotor rear stage 5 

and 6 discs and cone shafts, part numbers 

FK25230 and FK27899 installed. These 

engines are installed on, but not limited to, 

Boeing 777 series airplanes. 

Unsafe Condition 

(d) 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. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 


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53156 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 

(f) For operators using ‘‘Multiple Flight 

Profile Monitoring’’ (Flight Profiles ‘‘A’’ 

through ‘‘F’’), remove HP compressor rotor 

rear stage 5 and 6 discs and cone shafts from 

service at or before accumulating 5,000 

‘‘Standard Duty Cycles’’. Guidance on 

‘‘Multiple Flight Profile Monitoring’’ can be 

found in the Aircraft Maintenance Manual, 

Chapter 70–01–10. 

(g) For operators using ‘‘Heavy Flight 

Profile Monitoring’’, remove HP compressor 

rotor rear stage 5 and 6 discs and cone shafts 

from service at or before accumulating 5,000 

‘‘Flight Cycles’’. Guidance on ‘‘Heavy Flight 

Profile Monitoring’’ can be found in the 

Aircraft Maintenance Manual, Chapter 70– 

01–10. 

Alternative Methods of Compliance 

(h) 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 

(i) 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. 

(j) European Aviation Safety Agency AD 

2007–0004, dated January 8, 2007, also 

addresses the subject of this AD. 

(k) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–72–AE082, Revision 7, dated 

June 18, 2008, pertains to the subject of this 

AD. Contact Rolls-Royce plc, P.O. Box 31, 

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

242424; fax 44 (0) 1332 249936, for a copy 

of this service information. 

(l) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124– 

2207, for a copy of the Aircraft Maintenance 

Manual referenced in this AD. 

Material Incorporated by Reference 

(m) None. 

Issued in Burlington, Massachusetts, on 

October 8, 2009. 

Diane S. Romanosky, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–24855 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–2009–0907; Directorate 

Identifier 2009–NM–072–AD; Amendment 

39–16042; AD 2009–21–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated 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: 

An A340–300 aeroplane experienced the 

opening of the engine n°3 lower left thrust 

reverser pivoting door during climb. 

This event was the result of a primary lock 

malfunction and non-engagement of the 

secondary lock. 

* * * * * 

Deployment of one thrust reverser door in 

flight and during the take-off constitutes an 

unsafe condition. 

* * * * * 

Deployment of one thrust reverser door 

in flight or during take-off could result 

in reduced controllability of the 

airplane. This AD requires actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

November 2, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in the AD 

as of November 2, 2009. 

We must receive comments on this 

AD by November 16, 2009. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, 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 AD, the regulatory 

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 FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0063, 

dated March 11, 2009, and corrected 

March 20, 2009 (referred to after this as 

‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

An A340–300 aeroplane experienced the 

opening of the engine n°3 lower left thrust 

reverser pivoting door during climb. 

This event was the result of a primary lock 

malfunction and non-engagement of the 

secondary lock. 

Preliminary investigations have revealed 

two main findings: 

—The primary lock lever arm of the affected 

door was contaminated with lubrication 

fluid, which is a known contributor to 

incorrect operation; 

—The actuator of the deployed door was 

found with 3 shim sets installed whereas 

the system is designed for a maximum of 

one shim set. It is considered that 

installation of three shim sets has a 

detrimental effect on the secondary lock 

capacity to engage in case of primary lock 

failure. 

Deployment of one thrust reverser door in 

flight and during the take-off constitutes an 

unsafe condition. 

In order to ensure that the fleet is clear 

from unauthorized actuator shimming 

configurations which may lead to nonengagement of the secondary lock, EASA AD 

2008–0074 required a one-time visual 

inspection to check that no more than one 

shim set per pivoting door actuator was 

installed. 


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