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: 


cprice-sewell on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5691 

An operator reported a short circuit 

between a generator power cable and an antiice shutoff valve, which was caused by 

chafing between the cable and the valve; the 

insulation of the cable and surrounding 

sleeve were worn off. 

An investigation revealed that a scarce 

clearance between the cables and adjacent 

parts, together with vibrations of generator 

power cables favoured by insufficient 

clamping, was the root cause of the damage. 

If left uncorrected, this situation could lead 

to short circuits with possible fire and/or loss 

of important aircraft systems. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 11, 2010. 

On March 11, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; fax: (816) 329–4090. 

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 19, 2009 (74 FR 

59941). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An operator reported a short circuit 

between a generator power cable and an antiice shutoff valve, which was caused by 

chafing between the cable and the valve; the 

insulation of the cable and surrounding 

sleeve were worn off. 

An investigation revealed that a scarce 

clearance between the cables and adjacent 

parts, together with vibrations of generator 

power cables favoured by insufficient 

clamping, was the root cause of the damage. 

If left uncorrected, this situation could lead 

to short circuits with possible fire and/or loss 

of important aircraft systems. 

This Airworthiness Directive (AD) requires 

an inspection to detect damaged cables/ 

sleeves, and replacement/repair as necessary; 

in addition, this AD requires to ensure that 

acceptable minimum clearances between 

cables and parts exist, and to improve 

clamping to minimize vibrations of the 

cables. 

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 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

63 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $10,710 or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $10, for a cost of $520 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is 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. 


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5692 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–03–04 PIAGGIO AERO INDUSTRIES 

S.p.A.: Amendment 39–16187; Docket 

No. FAA–2009–1081; Directorate 

Identifier 2009–CE–058–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 11, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model PIAGGIO 

P–180 airplanes, all serial numbers through 

1180, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 24: Electric Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An operator reported a short circuit 

between a generator power cable and an antiice shutoff valve, which was caused by 

chafing between the cable and the valve; the 

insulation of the cable and surrounding 

sleeve were worn off. 

An investigation revealed that a scarce 

clearance between the cables and adjacent 

parts, together with vibrations of generator 

power cables favoured by insufficient 

clamping, was the root cause of the damage. 

If left uncorrected, this situation could lead 

to short circuits with possible fire and/or loss 

of important aircraft systems. 

This Airworthiness Directive (AD) requires 

an inspection to detect damaged cables/ 

sleeves, and replacement/repair as necessary; 

in addition, this AD requires to ensure that 

acceptable minimum clearances between 

cables and parts exist, and to improve 

clamping to minimize vibrations of the 

cables. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 3 months after March 11, 2010 

(the effective date of this AD), inspect for 

minimum clearance and insulation damage 

to the generator power cables in accordance 

with Part A of the ACCOMPLISHMENT 

INSTRUCTIONS of PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009. 

(2) If, as a result of the inspection required 

by paragraph (f)(1) of this AD, any 

discrepancy (inadequate clearance or 

insulation damage) is found, before further 

flight, do all necessary corrective actions in 

accordance with Part B of the 

ACCOMPLISHMENT INSTRUCTIONS of 

PIAGGIO AERO INDUSTRIES S.p.A. Service 

Bulletin (Mandatory) N.: 80–0271, dated May 

18, 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency AD No.: 2009–0212, dated 

October 6, 2009; and PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009, for related information. 

Material Incorporated by Reference 

(i) You must use PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009, 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 Piaggio Aero Industries 

S.p.a., Via Cibrario, 4—16154 Genoa, Italy; 

telephone +39 010 06481 741; fax: +39 010 

6481 309; Internet: http:// 

www.piaggioaero.com, or e-mail: 

MMicheli@piaggioaero.it. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on January 

21, 2010. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1691 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–2009–0608; Directorate 

Identifier 2008–NM–215–AD; Amendment 

39–16188; AD 2010–03–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C and –200F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Model 747–200C and –200F series 

airplanes. This AD requires a high 

frequency eddy current (HFEC) 

inspection for cracks of certain fastener 

holes, and corrective action if necessary. 

This AD also requires repetitive 

replacements of the upper chords, straps 

(or angles), and radius fillers of certain 

upper deck floor beams, and, for any 

replacement that is done, detailed and 

open-hole HFEC inspections for cracks 

of the modified upper deck floor beams, 

and corrective actions if necessary. This 

AD results from a report from the 

manufacturer that the accomplishment 

of certain existing inspections, repairs, 

and modifications is not adequate to 

ensure the structural integrity of the 

affected 7075 series aluminum alloy 

upper deck floor beam upper chords on 

airplanes that have exceeded certain 

thresholds. We are issuing this AD to 

prevent cracking of the upper chords 

and straps (or angles) of the floor beams, 

which could lead to failure of the floor 

beams and consequent loss of 

controllability, rapid decompression, 

and loss of structural integrity of the 

airplane. 

DATES: This AD is effective March 11, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 


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