## 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 thetransmissible 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:


## 5691 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations

An operator reported a short circuitbetween 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 circuitbetween 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 alsoestimate 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.


## 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 circuitbetween 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