### 30295 Federal Register / Vol. 76, No. 101 / Wednesday, May 25, 2011 / Proposed Rules

features involving hydrophobic window coatings in lieu of windshield wipers. Type Certification Basis

Under the provisions of 14 CFR 21.17, GALP must show that the Model G250 airplane meets the applicable provisions of part 25 as amended by Amendments 25–1 through 25–117.

If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Model G250 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.

Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, the special conditions would also apply to the other model.

In addition to the applicable airworthiness regulations and special conditions, the Model G250 airplane must comply with the fuel-vent and exhaust-emission requirements of 14 CFR part 34 and the noise-certification requirements of 14 CFR part 36; and the FAA must issue a finding of regulatory adequacy under § 611 of Public Law 92– 574, the ‘‘Noise Control Act of 1972. ’’

The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type-certification basis under § 21.17(a)(2). Novel or Unusual Design Features

The Model G250 will incorporate the following novel or unusual design features:

The GALP Model G250 airplane flight-deck design incorporates a hydrophobic coating to provide adequate pilot-compartment view in the presence of precipitation. Sole reliance on such a coating, without windshield wipers, constitutes a novel or unusual design feature for which the applicable airworthiness regulations do not contain adequate or appropriate safety standards. Therefore, special conditions are required that provide the level of safety equivalent to that established by the regulations.

Discussion

14 CFR 25.773(b)(1) requires a means to maintain a clear portion of the windshield for both pilots to have a sufficiently extensive view along the flight path during precipitation conditions. The regulations require this means to maintain such an area during precipitation in heavy rain at speeds up to 1.5 V SR1 . Hydrophobic windshield coatings may depend to some degree on airflow to maintain a clear-vision area. The heavy rain and high speed conditions specified in the current rule do not necessarily represent the limiting condition for this new technology. For example, airflow over the windshield, which may be necessary to remove moisture from the windshield, may not be adequate to maintain a sufficientlyclear area of the windshield in lowspeed flight or during surface operations. Alternatively, airflow over the windshield may be disturbed during such critical times as the approach toland, where the airplane is at a higherthan-normal pitch attitude. In these cases, areas of airflow disturbance or separation on the windshield could cause failure to maintain a clear-vision area on the windshield. Applicability

As discussed above, these special conditions are applicable to the GALP Model G250 airplane. Should GALP apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well.

Conclusion

This action affects only certain novel or unusual design features on the GALP Model G250 airplane. It is not a rule of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane. List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting and recordkeeping requirements.

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Proposed Special Conditions

Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the GALP Model G250 airplane.

The airplane must have a means to maintain a clear portion of the windshield, during precipitation conditions, enough for both pilots to have a sufficiently extensive view along the ground or flight path in normal taxi and flight attitudes of the airplane. This means must be designed to function, without continuous attention on the part of the crew, in conditions from light misting precipitation to heavy rain, at speeds from fully stopped in still air to 1.5 V SR1 with lift and drag devices retracted.

Issued in Renton, Washington, on May 19,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–12943 Filed 5–24–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0530; Directorate Identifier 2011–CE–012–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; SOCATA Model TBM 700 Airplanes** 

**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:

A TBM 700 operator reported a case of elevator trim tab actuator jamming once the trim tab arrived to stop.

The investigations conducted by the trim tab actuator manufacturer have shown that there was a discrepancy with PRECILEC manufacturing process of elevator trim tab actuator which caused this event. It has been determined as well that this discrepancy is limited to a batch of Serial Numbers (S/N).

If not detected and corrected, a jammed trim tab could lead to unusual control forces, resulting in lower controllability, particularly if combined with adverse flight conditions at landing. 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 July 11, 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,


### 30296 Federal Register / Vol. 76, No. 101 / Wednesday, May 25, 2011 / Proposed Rules

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 SOCATA— Direction des Services—65921 Tarbes Cedex 9—France; telephone +33 (0) 62 41 7300, fax +33 (0) 62 41 76 54, or for North America: SOCATA NORTH AMERICA, 7501 South Airport Road, North Perry Airport (HWO), Pembroke Pines, Florida 33023; telephone: (954) 893–1400; fax: (954) 964–4141; e-mail: mysocata@socata.daher.com; Internet: http://mysocata.com. 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 :**  Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; 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–2011–0530; Directorate Identifier 2011–CE–012–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:// 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.: 2011–0060, dated March 29, 2011 (Correction: March 30, 2011) (referred to after this as ‘‘the MCAI’’ ), to correct an unsafe condition for the specified products. The MCAI states:

A TBM 700 operator reported a case of elevator trim tab actuator jamming once the trim tab arrived to stop.

The investigations conducted by the trim tab actuator manufacturer have shown that there was a discrepancy with PRECILEC manufacturing process of elevator trim tab actuator which caused this event. It has been determined as well that this discrepancy is limited to a batch of Serial Numbers (S/N).

If not detected and corrected, a jammed trim tab could lead to unusual control forces, resulting in lower controllability, particularly if combined with adverse flight conditions at landing.

For the reasons described above, this AD requires the inspection of the elevators trim tab actuator P/N 6071017251 for identification of S/N and, in case of findings, the replacement of the affected ones with serviceable units. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

DAHER-SOCATA has issued Mandatory Service Bulletin SB 70–190– 27, dated January 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 377 products of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $32,045, or $85 per product.

In addition, we estimate that any necessary follow-on actions would take about 7 work-hours and require parts costing $0, for a cost of $595 per product. We have no way of determining the number of products that may need these actions.

According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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.


### 30297 Federal Register / Vol. 76, No. 101 / Wednesday, May 25, 2011 / Proposed Rules

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:

SOCATA: Docket No. FAA–2011–0530; Directorate Identifier 2011–CE–012–AD.

Comments Due Date

(a) We must receive comments by July 11,
2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to SOCATA Model TBM 700 airplanes, serial numbers 1 through 530, certificated in any category.
Subject

(d) Air Transport Association of America (ATA) Code 27: Flight Controls.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states: A TBM 700 operator reported a case of elevator trim tab actuator jamming once the trim tab arrived to stop.

The investigations conducted by the trim tab actuator manufacturer have shown that there was a discrepancy with PRECILEC manufacturing process of elevator trim tab actuator which caused this event. It has been determined as well that this discrepancy is limited to a batch of Serial Numbers (S/N).

If not detected and corrected, a jammed trim tab could lead to unusual control forces, resulting in lower controllability, particularly if combined with adverse flight conditions at landing.

For the reasons described above, this AD requires the inspection of the elevators trim tab actuator P/N 6071017251 for identification of S/N and, in case of findings, the replacement of the affected ones with serviceable units.
Actions and Compliance

(f) Unless already done, do the following actions:

(1) Within 12 months after the effective date of this AD, identify the serial number (S/N) of Left Hand and Right Hand PRECILECelevator trim tab actuators following DAHERSOCATA Mandatory Service Bulletin SB 70– 190–27, dated January 2011.

(2) If, as a result of the inspection required by paragraph (f)(1) of this AD you find any affected elevator trim tab actuator as listed in DAHER-SOCATA Mandatory Service Bulletin SB 70–190–27, dated January 2011, installed on an airplane, before further flight, replace it with a serviceable part following DAHER-SOCATA Mandatory Service Bulletin SB 70–190–27, dated January 2011.

(3) After the effective date of this AD, do not install on an airplane any PRECILEC elevator trim tab actuator part number6071017251 with an S/N listed in DAHERSOCATA Mandatory Service Bulletin SB 70– 190–27, dated January 2011, unless it hasbeen repaired in accordance with DAHERSOCATA Mandatory Service Bulletin SB 70– 190–27, dated January 2011.

Note 1: Trim tab actuators repaired by a service center are identified with screw green colored locking varnish as shown in figure 2 of DAHER-SOCATA Mandatory Service Bulletin SB 70–190–27, dated January 2011.

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: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; 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 MCAI European Aviation Safety Agency (EASA) AD No.: 2011–0060, dated March 29, 2011 (Correction: March 30, 2011); and DAHER-SOCATA Mandatory Service Bulletin SB 70–190–27, dated January 2011, for related information. For service information related to this AD, contact SOCATA—Direction des Services— 65921 Tarbes Cedex 9—France; telephone +33 (0) 62 41 7300, fax +33 (0) 62 41 76 54, or for North America: SOCATA NORTH AMERICA, 7501 South Airport Road, North Perry Airport (HWO), Pembroke Pines, Florida 33023; telephone: (954) 893–1400; fax: (954) 964–4141; e-mail: mysocata@socata.daher.com; Internet: http:// mysocata.com. 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 May
18, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–12967 Filed 5–24–11; 8:45 am]

**BILLING CODE 4910–13–P**