### 57664 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations

(Only the transmittal letter for Alert Service Bulletin (ASB) AE 3007A–A–72–367, Revision 2, dated June 22, 2009, identifies this service bulletin as an ASB; no other page of this document contains this information.)

Issued in Burlington, Massachusetts, on September 1, 2010. Robert G. Mann, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–22370 Filed 9–21–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0926; Directorate Identifier 2010–CE–024–AD; Amendment**  **39–16435; AD 2010–20–01]**

**RIN 2120–AA64**

**Airworthiness Directives; G ROB– WERKE Model G120A Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

GROB Aircraft AG has been informed that flap ribs P/N 120A–1053 and 120A–1054 have been found cracked during regular maintenance. Structural failure of the ribs may cause failure of the middle flap support which may lead to flap asymmetry due to excessive flap deformation and ultimately could result in reducing the controllability of the aeroplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective October 12, 2010.

On October 12, 2010, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

We must receive comments on this AD by November 8, 2010.

**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. 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 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 :**  Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816)
329–4090.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Emergency AD No.: 2010–0140, dated July 2, 2010 (referred to after this as ‘‘the MCAI’’ ), to correct an unsafe condition for the specified products. The MCAI states:

GROB Aircraft AG has been informed that flap ribs P/N 120A–1053 and 120A–1054 have been found cracked during regular maintenance. Structural failure of the ribs may cause failure of the middle flap support which may lead to flap asymmetry due to excessive flap deformation and ultimately could result in reducing the controllability of the aeroplane.

Pending further investigation on the root source for the cracks, including review of the original proofs of compliance, temporary limitations for flap operations were established until terminating action development.

EASA AD 2010–0065–E required a repetitive inspection of the RH and LH flap ribs. EASA AD 2010–0065–E is superseded as a terminating action has been developed by Grob Aircraft AG.

This AD, which supersedes EASA AD 2010–0065–E retaining its requirements, additionally requires accomplishment of repair N ° 1121–017 and modification N ° 1121–018 for aeroplanes on which cracks have been found or accomplishment of modification N ° 1121–018 only for aeroplanes on which no crack has been found.

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

GROB Aircraft AG has issued Service Bulletin No. ASB1121–113/1, dated May 18, 2010; Repair Instruction No. RI–1121–017, dated April 1, 2010; and Repair Instruction No. RI–1121–018, dated May 18, 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 the 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 issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This 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 have also required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a separate paragraph of the AD. These requirements take precedence over those copied from the MCAI.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because during regular maintenance, cracks have been found in the flap ribs. If not corrected, structural failure of the ribs may cause failure of the middle flap support, which could lead to flap asymmetry, due to excessive


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flap deformation, and ultimately reduce the controllability of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2010–0926; Directorate Identifier 2010–CE–024–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD:

(1) Is not a ‘‘ significant regulatory action’’ under Executive Order 12866;

(2) Is not a ‘‘ significant rule ’’ under 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 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. Adoption of the Amendment

■ Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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:

2010–20–01 GROB-WERKE: Amendment 39–16435; Docket No. FAA–2010–0926; Directorate Identifier 2010–CE–024–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective October 12, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Model G120A airplanes, all serial numbers, certificated in any category. Subject

(d) Air Transport Association of America (ATA) Code 57: Wings.

Reason

(e) GROB Aircraft AG has been informed that flap ribs P/N 120A–1053 and 120A–1054 have been found cracked during regular maintenance. Structural failure of the ribs may cause failure of the middle flap support which may lead to flap asymmetry due to excessive flap deformation and ultimately could result in reducing the controllability of the aeroplane.

Pending further investigation on the root source for the cracks, including review of the original proofs of compliance, temporary limitations for flap operations established until terminating action development.

EASA AD 2010–0065–E required a repetitive inspection of the RH and LH flap ribs. EASA AD 2010–0065–E is superseded as a terminating action has been developed by Grob Aircraft AG.

This AD, which supersedes EASA AD 2010–0065–E retaining its requirements, additionally requires accomplishment of repair N ° 1121–017 and modification N ° 1121–018 for aeroplanes on which cracks have been found or accomplishment of modification N ° 1121–018 only for aeroplanes on which no crack has been found.
Actions and Compliance

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

(1) Before further flight after October 12, 2010 (the effective date of this AD), and repetitively thereafter before the first flight of each day, inspect the right hand (RH) and left hand (LH) flap ribs for cracks following GROB Aircraft AG Service Bulletin No.: ASB1121–113/1, Accomplishment Instructions, PART A, dated May 18, 2010.

(2) If no crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, you must comply with the following conditions until the Repair Instructions in GROB Aircraft AG Repair Instruction No. RI–1121–018, dated May 18, 2010, are done:

(i) Reduction of the airplane’s maximum flap deflection to the ‘‘TAKE-OFF ’’ position and reduction of the maximum flaps extended speed VFE to 114 knots indicated airspeed (KIAS);

(ii) Modification of the placard part number (P/N) 120A–7000.113E to show reduced flap deflection of ‘‘TAKE-OFF ’’ position and maximum flaps extended speed VFE of 114 KIAS, and

(iii) Insertion into the limitations section of the airplane flight manual and/or pilots operating handbook an amendment showing that the Temporary Maximum Flap Position is TAKE-OFF and the Maximum Flap Extended Speed is 114 KIAS.

(3) If no crack is found during any inspection required in paragraph (f)(1) of this AD, within the next 12 months after the effective date of this AD, modify the LH and RH flap ribs following GROB Aircraft AG Repair Instruction No. RI–1121–018, dated May 18, 2010 and GROB Aircraft AG Service Bulletin No.: ASB1121–113/1, Accomplishment Instructions, PART B, dated May 18, 2010.

(4) If a crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, repair the applicable flap rib(s) following GROB Aircraft AG Repair Instruction No. RI–1121– 017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI–1121–018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121–113/1, Accomplishment Instructions, PART B, dated May 18, 2010.

(g) You may at any time complete GROB Aircraft AG Repair Instruction No. RI–1121– 017, dated April 1, 2010, and GROB Aircraft AG Service Bulletin No. ASB1121–113/1,


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Accomplishment Instructions, PART B, dated May 18, 2010, to terminate the repetitive inspection required in paragraph (f)(1) of this AD, and to terminate the conditions required by paragraphs (f)(2) of this AD. This repair must be done before further flight if cracks are found as required in paragraph (f)(4) of this AD.

FAA AD Differences

Note: This AD differs from the MCAI and/ or service information as follows: The MCAI allows flight with known cracks for up to 100 hours time-in-service. FAA policy is to not allow further flight with known cracks in critical structure. We require that if any cracks are found, before further flight, the crack must be repaired following the applicable GROB service information.

Other FAA AD Provisions

(h) 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: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; 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, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(i) Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2010–0140, dated July 2, 2010; GROB Aircraft AG Repair Instruction No. RI–1121–017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI–1121–018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121–113/1, dated May 18, 2010, for related information.
Material Incorporated by Reference

(j) You must use GROB Aircraft AG Repair Instruction No. RI–1121–017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI–1121–018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121–113/1, dated May 18, 2010, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in 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/service-andsupport/g-120/documentation/servicebulletins.html.

(3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768.

(4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go
to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Kansas City, Missouri, on September 14, 2010. William J. Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–23377 Filed 9–21–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0715; Directorate Identifier 2008–NM–211–AD; Amendment**  **39–16432; AD 2010–19–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Empresa Brasileira de Aeronautica S.A.**  **(EMBRAER) Model EMB–120, –120ER, –120FC, –120QC, and –120RT**  **Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This 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:

It has been found the occurrence of corrosion on the Auxiliary Power Unit (APU) mounting rods that could cause the APU rod to break, affecting the APU support structure integrity.
* * * * * APU support structure failure could result in loss of power of the APU and possible loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective October 27, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 27, 2010.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT :**  Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 19, 2009 (74 FR 41805). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

It has been found the occurrence of corrosion on the Auxiliary Power Unit (APU) mounting rods that could cause the APU rod to break, affecting the APU support structure integrity.
* * * * * APU support structure failure could result in loss of power of the APU and possible loss of control of the airplane. The required action is doing an external detailed inspection for corrosion of the APU auxiliary and center mounting rods and rod ends, and corrective actions if necessary. Corrective actions include removing corrosion, applying anticorrosive treatment, and replacing mounting rods. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comments received.