Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5689 

(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 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP–BRASIL; telephone: 

+55 12 3927–5852 or +55 12 3309–0732; fax: 

+55 12 3927–7546; e-mail: 

distrib@embraer.com.br; Internet: http:// 

www.flyembraer.com. 

(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 January 

22, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1930 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0889; Directorate 

Identifier 2009–NE–35–AD; Amendment 39– 

16189; AD 2010–03–06] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 2B and 2B1 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: 

Several events of uncoupling of the lowpressure (LP) fuel pump impeller and the 

high-pressure (HP) fuel pump shaft have 

been reported on Arriel 2 engines which do 

not incorporate Modification TU 147. In most 

cases the ‘‘low fuel pressure switch’’ 

enlightened, the pilot activated the aircraft 

booster pump in accordance with the Flight 

Manual Instructions and landed safely with 

no other incident. One case, on a singleengine helicopter, led to a sudden engine 

power loss. The uncoupling of the LP fuel 

pump impeller and the HP fuel pump shaft 

may lead to a limitation of engine power or, 

at worst, an uncommanded in-flight 

shutdown. On a single-engine helicopter, the 

result may be an emergency autorotation 

landing. 

We are issuing this AD to prevent a 

forced autorotation landing or an 

accident. 

DATES: This AD becomes effective 

March 11, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

March 11, 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. 

Contact Turbomeca, 40220 Tarnos, 

France; telephone (33) 05 59 74 40 00, 

fax (33) 05 59 74 45 15, for the service 

information identified in this AD. 

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 November 5, 2009 (74 FR 

57277). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Several events of uncoupling of the LP fuel 

pump impeller and the HP fuel pump shaft 

have been reported on Arriel 2 engines which 

do not incorporate Modification TU 147. In 

most cases the ‘‘low fuel pressure switch’’ 

enlightened, the pilot activated the aircraft 

booster pump in accordance with the Flight 

Manual Instructions and landed safely with 

no other incident. One case, on a singleengine helicopter, led to a sudden engine 

power loss. The uncoupling of the LP fuel 

pump impeller and the HP fuel pump shaft 

may lead to a limitation of engine power or, 

at worst, an uncommanded in-flight 

shutdown. On a single-engine helicopter, the 

result may be an emergency autorotation 

landing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

One commenter, a private citizen, 

states that the labor rate of $80 per 

work-hour referenced in the proposed 

AD is underestimated. He states that it 

should be at least $95 per work-hour. 

We partially agree. The work-hour 

labor rate estimate is established by the 

FAA’s Regulatory Analysis Division 

which recently published a new rate; 

$85 per work-hour. We changed the AD 

to reflect this increase. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI requires checking the 

transmissible torque between the LP 

pump impeller and the HP pump shaft 

within 550 engine flight hours from the 

effective date of the AD, but no later 

than June 30, 2010. 

This AD requires checking the 

transmissible torque between the LP 

pump impeller and the HP pump shaft 

within 550 engine flight hours from the 

effective date of the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

414 engines installed on helicopters of 

U.S. registry. We also estimate that it 

will take about 2.5 work-hours per 

engine to comply with this AD. The 

average labor rate is $85 per work-hour. 

Replacement HP/LP pump metering 

units (HMUs) will cost about $12,000 

per engine. Based on these figures, if all 

of the HMUs were to fail the check, we 

estimate the cost of the AD to U.S. 

operators to be $5,055,975. 

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 


cprice-sewell on DSK2BSOYB1PROD with RULES
5690 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 

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: 

2010–03–06 Turbomeca: Amendment 39– 

16189. Docket No. FAA–2009–0889; 

Directorate Identifier 2009–NE–35–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 11, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca Arriel 2B 

and 2B1 turboshaft engines that have not 

incorporated Modification TU 147. These 

engines are installed on, but not limited to, 

Eurocopter AS 350 B3 and EC 130 B4 

helicopters. 

Reason 

(d) 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. We are 

issuing this AD to prevent a forced 

autorotation landing or an accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 550 engine flight hours from the 

effective date of this AD, check the 

transmissible torque between the lowpressure (LP) pump impeller and the highpressure (HP) pump shaft of the HP/LP pump 

metering unit (HMU). Use paragraph 2 of the 

Instructions to be Incorporated of Turbomeca 

Mandatory Service Bulletin No. A292 73 

2830, Version B, dated July 10, 2009, to do 

the check. 

(2) If the check is compliant, apply the 

nominal tightening torque to the screw of the 

LP pump impeller. 

(3) If the check is not compliant, replace 

the HP/LP pump HMU with a unit that has 

not incorporated Modification TU 147 but 

has passed the check, or with a unit that has 

incorporated Modification TU 147. 

FAA AD Differences 

(f) This AD differs from the MCAI and/or 

service information as follows: 

(1) The MCAI requires the checking of the 

transmissible torque between the LP pump 

impeller and the HP pump shaft within 550 

engine flight hours from the effective date of 

the AD, but no later than June 30, 2010. 

(2) This AD requires the checking of the 

transmissible torque between the LP pump 

impeller and the HP pump shaft within 550 

engine flight hours from the effective date of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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 European Aviation 

Safety Agency Airworthiness Directive 2009– 

0184, dated August 14, 2009, for 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. 

Material Incorporated by Reference 

(j) You must use Turbomeca Mandatory 

Service Bulletin No. A292 73 2830, Version 

B, dated July 10, 2009, to do the 

transmissible torque check required by this 

AD. 

(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. 

(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 

January 21, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–1735 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1081; Directorate 

Identifier 2009–CE–058–AD; Amendment 

39–16187; AD 2010–03–04] 

RIN 2120–AA64 

Airworthiness Directives; PIAGGIO 

AERO INDUSTRIES S.p.A. Model P–180 

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) 

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: 


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