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;


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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.


### 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.