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

(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, which 

could 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. 

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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 uncommanded 

In 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: 

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

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 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS