Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34221 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0330; Directorate 

Identifier 2008–NE–43–AD; Amendment 39– 

15961; AD 2009–14–11] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. ARRIUS 2F 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: 

On several ARRIUS 2F engines, the 

clearance between the P3 air pipe P/N 

0319719180 and the rear right bulkhead P/N 

0319998240 has been found to be too small. 

Investigations have shown that both P3 air 

pipe and rear right bulkhead were compliant 

to the design. The Turbomeca Engineering 

Department concluded that the tolerance of 

assembly established during the design could 

result in some rubbing between parts. 

Rubs between the pipe and the bulkhead 

may lead to premature wearing and finally 

rupture of the P3 air pipe. The loss of P3 air 

pressure would then force the fuel control 

system to idle which could have a 

detrimental effect in critical phases of flight. 

We are issuing this AD to prevent an 

uncommanded power loss, which could 

result in an emergency autorotation 

landing or accident. 

DATES: This AD becomes effective 

August 19, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

August 19, 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 

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 April 13, 2009 (74 FR 

16809). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

On several ARRIUS 2F engines, the 

clearance between the P3 air pipe P/N 

0319719180 and the rear right bulkhead P/N 

0319998240 has been found to be too small. 

Investigations have shown that both P3 air 

pipe and rear right bulkhead were compliant 

to the design. The Turbomeca Engineering 

Department concluded that the tolerance of 

assembly established during the design could 

result in some rubbing between parts. 

Rubs between the pipe and the bulkhead 

may lead to premature wearing and finally 

rupture of the P3 air pipe. The loss of P3 air 

pressure would then force the fuel control 

system to idle which could have a 

detrimental effect in critical phases of flight. 

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. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

94 engines installed on helicopters of 

U.S. registry. We also estimate that it 

will take about 1 work-hour per engine 

to comply with this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $705 per 

engine. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $73,790. 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 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. 


srobinson on DSKHWCL6B1PROD with RULES
34222 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–14–11 Turbomeca S.A.: Amendment 

39–15961. Docket No. FAA–2009–0330; 

Directorate Identifier 2008–NE–43–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 19, 2009. 

Affected ADs 

(b) None. 

Applicability 

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

ARRIUS 2F turboshaft engines with P3 air 

pipe, part number 0319719180, installed. 

These engines are installed on, but not 

limited to, Eurocopter EC120B helicopters. 

Reason 

(d) Rubs between the pipe and the 

bulkhead may lead to premature wearing and 

finally rupture of the P3 air pipe. The loss 

of P3 air pressure would then force the fuel 

control system to idle which could have a 

detrimental effect in critical phases of flight. 

We are issuing this AD to prevent an 

uncommanded power loss, which could 

result in an emergency autorotation landing 

or accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions within 100 operating hours after the 

effective date of this AD. Use paragraphs 

2.B.(1) through 2.C.(2) of Turbomeca 

Mandatory Service Bulletin No. 319 75 4810, 

dated May 14, 2008. 

(1) Visually inspect P3 air pipe (first 

section) and RH rear half-wall. 

(2) Inspect play between P3 air pipe (first 

section) and RH rear half-wall. 

(3) Replace P3 air pipe (first section) if any 

damage is found. 

(4) Readjust the first section of the P3 air 

pipe if the inspected clearance is found to be 

not compliant. 

(5) If the play after readjusting the first 

section of the P3 air pipe is still less than 0.5 

mm, repeat paragraphs (e)(1) through (e)(4) of 

this AD within intervals of 100 hours timesince-last inspection. 

(6) Replace RH rear half-wall if any damage 

is found. 

FAA AD Differences 

(f) None. 

Other FAA AD Provisions 

(g) 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 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0134R1, dated February 17, 

2009, and Turbomeca S.A. Mandatory 

Service Bulletin No. 319 75 4810, dated May 

14, 2008, for related information. Contact 

Turbomeca, 40220 Tarnos, France; telephone 

33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5 

59 74 45 15, for a copy of this service 

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. 

Material Incorporated by Reference 

(j) You must use Turbomeca Mandatory 

Service Bulletin No. 319 75 4810, dated May 

14, 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 (0)5 59 74 40 00; telex 

570 042; fax 33 (0)5 59 74 45 15. 

(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 

June 30, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16113 Filed 7–14–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0137; Directorate 

Identifier 2008–NM–201–AD; Amendment 

39–15967; AD 2009–15–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300, and A340–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

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: 

Several reports have been received from 

A330 and A340 operators concerning chafing 

of the electrical harness behind the lavatory, 

located at L (level) 53, resulting in a number 

of short-circuits. This harness contains cables 

for lighting, plugs, loudspeakers and oxygen 

controls and indications. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks (up to 32% of all seats) not being 

supplied with oxygen, possibly causing 

personal injuries. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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 

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 February 23, 2009 (74 FR 

8036). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received from 

A330 and A340 operators concerning chafing 

of the electrical harness behind the lavatory, 

located at L (level) 53, resulting in a number 

of short-circuits. This harness contains cables 

for lighting, plugs, loudspeakers and oxygen 

controls and indications. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks (up to 32% of all seats) not being 

supplied with oxygen, possibly causing 

personal injuries. 

For the reasons described above, AD 2008– 

0154 was issued to require a wiring 

modification of the affected harnesses on 

right and left sides of the passenger 

compartment between frames (FR) 39.1 and 

39.2 and between FR 53.3 and 53.4, on premodification 48825 aircraft (i.e. nonenhanced cabin). 


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