### 71538 Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations

Material Incorporated by Reference

(i) You must use DAHER-SOCATA TBM 700 A & B Pilot’s Operating Handbook (POH), Temporary Revision No. 3, dated March 2009; and DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–168, dated December 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 SOCATA—Direction des services, 65921 Tarbes Cedex 9, France; telephone: 33 (0) 62 41 73 00; fax: + 33 (0) 62 41 76 54; or for the U.S.A.: SOCATA NORTH AMERICA, North Perry Airport, 7501 South Airport Rd., Pembroke Pines, Florida 33023; telephone: 1 (954) 893 1400; fax: 1 (954) 964 4141; Internet: http:// mysocata.com/.

(3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148.

(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 November 4, 2010. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–28612 Filed 11–23–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1110; Directorate Identifier 2010–NM–052–AD; Amendment**  **39–16517; AD 2010–23–27]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A340–500 and A340–600 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 A340–642 operator reported [fault
messages ‘‘ Main Fuel Pump 4 ’’ and ‘‘Eng 4 Stall/Surge ’’ ] * * * and finally the engine had an auto shutdown [along] with [fault
message ‘‘Engine 4 Fail ’’ ] * * *.
* * * * *

Simultaneous loss of at least two Main Pumps along with other potential failures related to the in-service event may lead to a dual engine loss.
* * * * *

This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective December 9, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 9, 2010.

We must receive comments on this AD by January 10, 2011.

**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 2010–0013, dated January 26, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

An A340–642 operator reported a Main Fuel Pump 4 fault that occurred during descent. Afterwards it was followed by a 2 times Eng 4 Stall/Surge Message and finally the engine had an auto shutdown with Message Engine 4 Fail.

Analysis of the A340–500/600 aircraft fuelpump electrical-circuit design has shown that when a main fuel pump becomes unserviceable and the fuel pressure indication system indicates abnormal High (HI) pressure, these unwanted conditions

occur: —There is no Electronic Centralized Aircraft

Monitor (ECAM) caution or fault light of the unserviceable fuel pump. —The crew cannot manually set the standby

fuel pump to ‘ON’ because of the main pump pressure abnormal HI condition. Simultaneous loss of at least two Main Pumps along with other potential failures related to the in-service event may lead to a dual engine loss. This AD mandates the modification of the main and standby pump wiring logic which will let the related standby fuel pump be set ‘ON’ irrespective of the status of the main fuel pump pressure switch in each of the conditions that follow: —After the main fuel pump becomes

unserviceable; —When the push-button switch of the related

main fuel pump is set to ‘OFF’, even if the fuel pump pressure indicates abnormally HI. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued Mandatory Service Bulletin A340–28–5050, including Appendix 1, dated October 8, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe


### 71539 Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations

condition exists and is likely to exist or develop on other products of the same type design.

There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future.

Differences Between the 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.

FAA’s Determination of the Effective Date

Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘ Docket No. FAA–2010–1110; Directorate Identifier 2010–NM–052– AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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. 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: 2010–23–27 Airbus: Amendment 39–16517. Docket No. FAA–2010–1110; Directorate Identifier 2010–NM–052–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective December 9, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A340– 541 and A340–642 airplanes, certificated in any category. Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

(e) The mandatory continued airworthiness information (MCAI) states:

An A340–642 operator reported [fault
messages ‘‘ Main Fuel Pump 4 ’’ and ‘‘Eng 4 Stall/Surge ’’ ] * * * and finally the engine had an auto shutdown [along] with [fault
message ‘‘Engine 4 Fail ’’ ] * * *.
* * * * *

Simultaneous loss of at least two Main Pumps along with other potential failures related to the in-service event may lead to a dual engine loss.
* * * * *
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Actions

(g) Within 13,500 flight hours after the effective date of this AD, modify the equipment and the wiring connected to the main and standby pumps in the left and right wing, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A340–28–5050, dated October 8, 2009.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(h) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Airplane Directorate, 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: 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. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District


### 71540 Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations

Office. The AMOC approval letter must specifically reference this AD.

(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

(i) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0013, dated January 26, 2010; and Airbus Mandatory Service Bulletin A340–28–5050, dated October 8, 2009; for related information.
Material Incorporated by Reference

(j) You must use Airbus Mandatory Service Bulletin A340–28–5050, including Appendix 1, dated October 8, 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 Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; e-mail airworthiness.A330–A340@airbus.com;
Internet http://www.airbus.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.

(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 November 2, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–28591 Filed 11–23–10; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1137; Directorate Identifier 2010–SW–079–AD; Amendment**  **39–16523; AD 2010–19–51]**

**RIN 2120–AA64**

**Airworthiness Directives; Bell Helicopter Textron Canada Model 222,**  **222B, 222U, 230, and 430 Helicopters**

**AGENCY :**  Federal Aviation Administration, DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010–19–51, which was sent previously to all known U.S. owners and operators of the specified model Bell Helicopter Textron Canada (Bell) helicopters by individual letters. This AD requires inspecting parts of the main rotor hydraulic servo actuator (servo actuator) for certain conditions and replacing any unairworthy parts before further flight. This AD is prompted by a collective servo actuator malfunction and a subsequent investigation that revealed the output piston rod assembly (piston rod) had fractured at the threaded end because of stress corrosion cracking. Also, during the investigation of that servo actuator malfunction, a nonconforming grind relief was discovered on a separate piston rod. The actions specified by this AD are intended to detect corrosion or a nonconforming piston rod that, if not detected and corrected, could result in failure of the piston rod, failure of the servo actuator, and subsequent loss of control of the helicopter.

**DATES :**  Effective December 9, 2010, to all persons except those persons to whom it was made immediately effective by Emergency AD 2010–19–51, issued on August 31, 2010, which contained the requirements of this amendment.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 9, 2010.

Comments for inclusion in the Rules Docket must be received on or before January 24, 2011.

**ADDRESSES :**  Use one of the following addresses to submit comments on this AD:

• 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

You may get the service information identified in this AD from Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272, or at http:// www.bellcustomer.com/files/.

Examining the Docket: You may examine the docket that contains the AD, any comments, and other information 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 Docket Operations office (telephone (800) 647– 5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  J.R. Holton, Jr., Aviation Safety Engineer, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–4964, fax (817)
222–5961.

**SUPPLEMENTARY INFORMATION :**  On August 31, 2010, the FAA issued Emergency AD 2010–19–51 for the specified model helicopters, which requires inspecting parts of the servo actuator for certain conditions and replacing any unairworthy parts before further flight. That action was prompted by a collective servo actuator malfunction and a subsequent investigation that revealed the output piston rod assembly (piston rod) had fractured at the threaded end because of stress corrosion cracking. Also, during the investigation of that servo actuator malfunction, a nonconforming grind relief was discovered on a separate piston rod. This condition, if not detected and corrected, could result in failure of the piston rod, failure of the servo actuator, and subsequent loss of control of the helicopter.

Transport Canada, the airworthiness authority for Canada, has issued Canadian AD No. CF–2010–29, dated August 26, 2010 to correct an unsafe