### 9515 Federal Register / Vol. 76, No. 34 / Friday, February 18, 2011 / Proposed Rules

(4) If the bent area of the engaged tooth of the upper pulley wheel securing plate has no crack found per the inspection of paragraph (f)(2) of this AD, but the propeller track value measured is not within the allowable tolerances per paragraph (f)(3) of this AD, before further flight, readjust the torque of the upper pulley wheel grooved nut using the updated aircraft technical documentation following the procedure on page 6.12 of the G 103 C TWIN III SL Maintenance Manual, Date of Issue December, 1991, Revision 9, dated May 24, 2002, as specified in Grob Aircraft Service Letter SL 869–01, dated June 9, 2009. Ensure accordingly that the propeller track is within the allowable tolerances following the procedure on page 4.9 of the G 103 C TWIN III SL POH, Date of Issue December, 1991, Revision 6, dated July 20, 2009, as specified in Grob Aircraft Service Letter SL 869–01, dated June 9, 2009. If the propeller track is out of the allowable tolerance, then contact GROB for further instructions.

(5) If any crack is found in the bent area of the engaged tooth of the upper pulley wheel securing plate per the inspection in paragraph (f)(2) of this AD, before further flight, do the following actions:

(i) Remove the upper pulley wheel grooved nut and then look at the securing plate to identify if other teeth are available to be bent to secure the grooved nut. Do not bend an already bent tooth. If all teeth of the securing plate are already bent, replace the securing plate with a serviceable one.

(ii) Screw back the upper pulley wheel grooved nut (and its securing plate) and tighten it, applying the torque following page 6.12 of the G 103 C TWIN III SL Maintenance Manual, Date of Issue December, 1991, Revision 9, dated May 24, 2002, as specified in Grob Aircraft Service Letter SL 869–01, dated June 9, 2009. Ensure accordingly that the propeller track is within the allowable tolerances following the procedure on page 4.9 of the G 103 C TWIN III SL POH, Date of Issue December, 1991, Revision 6, dated July 20, 2009, as specified in Grob Aircraft Service Letter SL 869–01, dated June 9, 2009. If the propeller track is out of the allowable tolerances, then contact GROB for further instructions.

FAA AD Differences

Note 2: 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: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; 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, a Federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer,
AES–200.

Related Information

(h) Refer to the following documents for related information:

(1) MCAI EASA AD No.: 2010–0107, dated June 11, 2010;

(2) Grob Aircraft Service Bulletin MSB 869–24/1, dated July 20, 2009;

(3) Grob Aircraft Service Letter SL–869–01, dated June 9, 2009;

(4) G 103 C Twin III SL Pilot’s Operating Handbook (POH) (dated December 1991), pages 0.2A, 0.3, 0.4, and 4.9, Revision 6, dated July 20, 2009; and

(5) G 103 C Twin III SL Maintenance Manual (dated December 1991), page 6.12, Revision 9, dated May 24, 2002; and pages 0.1A, 0.2, 0.3, 4.2, and 6.6, Revision 10, dated December 15, 2006.

(i) For service information related to this AD, contact GROB Aircraft AG,Lettenbachstrasse 9, 86874 TussenhausenMattsies, Germany; telephone: +49 (0) 8268– 998–0; fax: +49 (0) 8268–998–200; e-mail productsupport@grob-aircraft.com; Internet: http://www.grob-aircraft.eu. 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.

Issued in Kansas City, Missouri, on February 11, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–3660 Filed 2–17–11; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0115; Directorate Identifier 2010–NE–40–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Turbomeca S.A. ARRIEL 2B and 2B1 Turboshaft**  **Engines**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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 cases of Gas Generator (GG) Turbine Blade rupture occurred in service on ARRIEL 2 twin engine applications and recently one on a single engine helicopter. For the case occurring in flight on a single engine helicopter (ARRIEL 2B1 engine), the pilot performed an emergency autorotation, landing the helicopter without further incident. We are proposing this AD to prevent rupture of a GG turbine blade, whichcould result in an uncommanded inflight shutdown and an emergency autorotation landing or accident.

**DATES :**  We must receive comments on this proposed AD by April 4, 2011.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

• Fax: (202) 493–2251. Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: noria-dallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, or go to: http:// www.turbomeca-support.com for the service information identified in this proposed AD.


### 9516 Federal Register / Vol. 76, No. 34 / Friday, February 18, 2011 / Proposed Rules

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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone (800) 647–5527) is the same as the Mail address provided in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  James Gray, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803– 5299; e-mail: james.e.gray@faa.gov; telephone (781) 238–7742; fax (781)
238–7199.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2011–0115; Directorate Identifier 2010–NE–40–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc. ). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78).

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 2010–0198, dated October 1, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Several cases of Gas Generator (GG) Turbine Blade rupture occurred in service on ARRIEL 2 twin engine applications and recently one on a single engine helicopter. For the case occurring in flight on a single engine helicopter (ARRIEL 2B1 engine), the pilot performed an emergency autorotation, landing the helicopter without further incident.

The design of ARRIEL 2 engines (containment shield around the GG turbine)allows debris from a blade or the disc interblade area to be contained in the event of rupture. However, the rupture of a GG Turbine Blade may lead to an uncommandedIn Flight Shut-Down which, on a singleengine helicopter, could ultimately lead to an emergency autorotation landing.

The most probable root cause of the ruptures is an excitation of one of the vibration modes of the GG Turbine Blade in conjunction with several secondary contributing factors which are deemed sufficient to reduce the stress margin of the blade to a level consistent with the rate of occurrences of ruptures encountered.

Turbome  ́ ca has released TU166 modification which consists of inserting Blade dampers between the GG Turbine Disc and the GG Turbine Blade platform. Introduction of these dampers minimizes the effects of HP blade vibratory excitation and increases the blade tolerance for this type of
stress. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Turbomeca S.A. has issued Mandatory Service Bulletin A292 72 3166, Version B, dated September 20, 2010. 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 Proposed AD

This product has been approved by the aviation authority of France, and is approved for operation in the United States. Pursuant to our bilateral agreement with France, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 537 products of U.S. registry. We also estimate that it would take about 60 work-hours per product to comply with this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $3,900 per product. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $4,833,000. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation:

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 proposed 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. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:


### 9517 Federal Register / Vol. 76, No. 34 / Friday, February 18, 2011 / Proposed Rules

**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:

Turbomeca S.A.: Docket No. FAA–2011– 0115; Directorate Identifier 2010–NE– 40–AD.

Comments Due Date

(a) We must receive comments by April 4,
2011.
Affected Airworthiness Directives (ADs)

(b) None.
Applicability

(c) This AD applies to Turbomeca S.A. ARRIEL 2B and 2B1 turboshaft engines not modified by TU166 modification. These engines are installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters.

Reason

(d) This AD results from: Several cases of Gas Generator (GG) Turbine Blade rupture occurred in service on ARRIEL 2 twin engine applications and recently one on a single engine helicopter. For the case occurring in flight on a single engine helicopter (ARRIEL 2B1 engine), the pilot performed an emergency autorotation, landing the helicopter without further incident.

We are issuing this AD to prevent rupture of a GG turbine blade, which could result in an uncommanded in-flight shutdown and an emergency autorotation landing or accident.
Actions and Compliance

(e) Unless already done, do the following actions.

(1) Accomplish TU166 modification in accordance with the instructions specified within Turbome  ́ ca Mandatory Service Bulletin (MSB) A292 72 3166 Version B, dated September 20, 2010, when the GG Turbine is replaced or when the engine or Module M03 is going through overhaul or repair, or within 1,300 cycles-in-service after the effective date of this AD, whichever occurs first.

(2) Accomplishment, before the effective date of this AD, of TU166 modification in accordance with the instructions of Turbome  ́ ca MSB A292 72 3166 Version A, dated August 17, 2010, satisfies the requirement of paragraph (e)(1) of this AD.

FAA AD Differences

(f) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and or service information by the following:

(1) European Aviation Safety Agency (EASA) AD No. 2010–0198, dated October 1, 2010, applies to the ARRIEL 2B1A engine. This AD does not apply to that model because it has no U.S. type certificate. (2) EASA AD No. 2010–198 has a compliance date of ‘‘but no later than 25 months after the effective date of this AD. This AD has a compliance time of ‘‘ 1,300 cycles-in-service, ’’ based on average fleet usage data supplied by Turbomeca.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:
Alternative Methods of Compliance (AMOCs)

(h) 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

(i) Refer to MCAI EASA Airworthiness Directive 2010–0198, dated October 1, 2010, and Turbomeca S.A. Mandatory Service Bulletins A292 72 3166, Version A, dated August 17, 2010, and A292 72 3166 Version B, dated September 20, 2010, for related information. Contact Turbomeca S.A., 40220 Tarnos, France; e-mail: noriadallas@turbomeca.com; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, or go to: http://www.turbomeca-support.com, for a copy of this service information.

(j) Contact James Gray, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; e-mail: james.e.gray@faa.gov; telephone (781) 238–7742; fax (781) 238– 7199, for more information about this AD.

Issued in Burlington, Massachusetts, on February 14, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2011–3684 Filed 2–17–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF LABOR**

**Veterans’ Employment and Training Service** 

**20 CFR Part 1001**

**RIN 1293–AA18**

**Uniform National Threshold Entered Employment Rate for Veterans** 

**AGENCY :**  Veterans’ Employment and Training Service, Labor.

**ACTION :**  Notice of proposed rulemaking; request for comments.

**SUMMARY :**  The Veterans’ Employment and Training Service (VETS) of the Department of Labor (the Department) is proposing a rule to implement a uniform national threshold entered employment rate for veterans applicable to State employment service delivery systems. The Department undertakes this rulemaking in accordance with the Jobs for Veterans Act, which requires the Department to implement that threshold rate by regulation.

**DATES :**  To ensure consideration, comments must be received on or before April 19, 2011.

**ADDRESSES :**  You may submit comments, identified by Regulatory Information Number (RIN) 1293–AA18, by any one of the three following methods:

• Federal e-Rulemaking Portal: http://www.regulations.gov. Follow the Web site instructions for submitting
comments.

• Mail/Hand Delivery/Courier: Written comments, disk, and CD–ROM submissions may be mailed or delivered by hand delivery/courier to The Veterans’ Employment and Training Service, U.S. Department of Labor, 200 Constitution Avenue, NW., Room S–1325, Washington, DC 20210.

• Fax: Comments may be submitted by fax, with a cover page to the attention of Patrick Hecker, at (202) 693–4755 (this is not a toll-free number).

Instructions: Please submit your comments by only one method. All submissions received must include the agency name, as well as RIN 1293– AA18. The Department will post all comments received on http:// www.regulations.gov without making any change to the comments, including any personal information provided. The http://www.regulations.gov Web site is the Federal e-rulemaking portal and all comments posted there are available and accessible to the public. Therefore, the Department recommends that commenters safeguard their personal information such as Social Security Numbers, personal addresses, telephone numbers, and e-mail addresses. It is the responsibility of the commenter to safeguard his or her information. Also, please note that due to security concerns, postal mail delivery in Washington, DC, may be delayed. Therefore, in order to ensure that comments receive full consideration, the Department encourages the public to submit comments via the Internet as indicated above.

Docket: The Department will make all the comments it receives available for public inspection during normal business hours at the above address. If you need assistance to review the comments, the Department will provide you with appropriate aids such as readers or print magnifiers. The Department will make copies of the proposed rule available, upon request, in large print or electronic file on computer disk. The Department will consider providing the proposed rule in other formats upon request. To schedule