This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

9513 

Vol. 76, No. 34 

Friday, February 18, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0127; Directorate 

Identifier 2010–CE–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; BURKHART 

GROB LUFT-UND Model G 103 C Twin 

III SL Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

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: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

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. 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. 

For service information identified in 

this proposed AD, contact GROB 

Aircraft AG, Lettenbachstrasse 9, 86874 

Tussenhausen-Mattsies, 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. 

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 this proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090. 

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–2011–0127; Directorate Identifier 

2010–CE–065–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 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 proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2010–0107, dated June 11, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

For the reasons stated above, this AD 

requires to inspect the propeller assembly 

attachment, to verify that the propeller track 

is within the allowable tolerances and, 

depending on findings, to accomplish the 

relevant corrective actions. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Burkhart Grob Luft-Und has issued 

the following documents. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI: 

• Grob Aircraft Service Bulletin No. 

MSB–869–24/1, dated July 20, 2009; 

• Grob Aircraft Service Letter SL– 

869–01, dated June 9, 2009; 

• 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; 

• G 103 C Twin III SL Maintenance 

Manual (dated December 1991), page 

6.12, Revision 9, dated May 24, 2002; 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

9514 Federal Register / Vol. 76, No. 34 / Friday, February 18, 2011 / Proposed Rules 

and pages 0.1A, 0.2, 0.3, 4.2, and 6.6, 

Revision 10, dated December 15, 2006. 

FAA’s Determination and Requirements 

of the Proposed 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 this State of 

Design Authority, 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 and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed 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 proposed 

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 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 4 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $680, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $100, for a cost of $610 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 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: 

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: 

BURKHART GROB LUFT-UND: Docket No. 

FAA–2011–0127; Directorate Identifier 

2010–CE–065–AD. 

Comments Due Date 

(a) We must receive comments by April 4, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BURKHART GROB 

LUFT-UND G 103 C Twin III SL gliders, all 

serial numbers, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 61: Propellers/Propulsors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The in-flight loss of a propeller and pulley 

wheel from the engine of a Grob G 103 C 

Twin III SL powered sailplane has been 

reported. 

Grob Aircraft AG suspects that the possible 

reasons for this loss can be due to an 

incorrect propeller track (the play at the 

propeller tip) and/or to a damaged propeller 

nut securing plate. 

Those conditions, if not corrected, could 

also result in loosening of parts and, 

consequently could result in damage to the 

sailplane and possible injury to persons on 

the ground. 

For the reasons stated above, this AD 

requires to inspect the propeller assembly 

attachment, to verify that the propeller track 

is within the allowable tolerances and, 

depending on findings, to accomplish the 

relevant corrective actions. 

Actions and Compliance 

(f) Unless already done, within 30 days 

after the effective date of this AD, do the 

following actions: 

(1) Update the glider documentation 

following Grob Aircraft Service Bulletin No. 

MSB–869–24/1, dated July 20, 2009, by 

inserting the following pages: 

(i) Into the 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. 

(ii) Into the G 103 C Twin III SL 

Maintenance Manual (dated December, 1991) 

or FAA-approved maintenance program: 

pages 0.1A, 0.2, 0.3, 4.2, and 6.6, Revision 10, 

dated December 15, 2006. 

(2) Inspect for cracks at the bent area of the 

engaged tooth of the upper pulley wheel 

securing plate following the procedure to 

access the area found 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. 

(3) Verify that the propeller track (the play 

at the propeller tip) 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. 

Note 1: The torque values and tolerances 

of the upper pulley wheel grooved nut have 

been standardized in the POH and 

maintenance manual. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

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. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS