### 39795 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

TABLE 

### 7—A LL 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Airbus— Revision— Dated—

AOT A330–24A3042 ........................................................................................................................................... 02 April 12, 2007. AOT A330–24A3044 ........................................................................................................................................... 03 May 26, 2008. AOT A340–24A4056 ........................................................................................................................................... 02 April 12, 2007. AOT A340–24A4057 ............................................................................................................... ............................ 03 December 20, 2007. AOT A340–24–A5020 ......................................................................................................................................... 02 April 12, 2007. AOT A340–24A5021 ............................................................................................................... ............................ 02 December 20, 2007. Mandatory Service Bulletin A330–24–3045 ........................................................................................................ 01 October 1, 2008. Mandatory Service Bulletin A340–24–4058 ........................................................................................................ 01 October 1, 2008. Mandatory Service Bulletin A340–24–5022 ........................................................................................ ................ 01 November 27, 2008.
(The AOT document number, revision level, and date are indicated on only page 1 of these documents.)

(1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.



### TABLE 

### 8—N EW 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Airbus— Revision— Dated—

AOT A330–24A3044 ........................................................................................................................................... 03 May 26, 2008. AOT A340–24A4057 ............................................................................................................... ............................ 03 December 20, 2007. AOT A340–24A5021 ............................................................................................................... ............................ 02 December 20, 2007. Mandatory Service Bulletin A330–24–3045 ........................................................................................................ 01 October 1, 2008. Mandatory Service Bulletin A340–24–4058 ........................................................................................................ 01 October 1, 2008. Mandatory Service Bulletin A340–24–5022 ........................................................................................ ................ 01 November 27, 2008.

(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 9 of this AD on June 26, 2007 (72 FR 31973, June 11, 2007).



### TABLE 

### 9—M ATERIAL 

### P REVIOUSLY 

### I NCORPORATED BY 

### R EFERENCE

Airbus all operators telex— Revision level— Dated—

A330–24A3042 ................................................................................................................... ...................................... 02 April 12, 2007. A340–24A4056 ................................................................................................................... ...................................... 02 April 12, 2007. A340–24A5020 ................................................................................................................... ...................................... 02 April 12, 2007.

(3) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80, e-mail: airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com.

(4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221.

(5) You may also review copies of the service information that is incorporated by reference 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 Renton, Washington, June 23,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–16181 Filed 7–12–10; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0684; Directorate Identifier 2010–CE–031–AD; Amendment**  **39–16360; AD 2010–14–15]**

**RIN 2120–AA64**

**Airworthiness Directives; Aircraft Industries a.s. (Type Certificate G60EU**  **Previously Held by LETECKE  ́**  **ZA  ́**  **VODY a.s. and LET Aeronautical Works)**  **Model L–13 Blanik Gliders**

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


### 39796 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

**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:

A fatal accident occurred to a L–13 BLANI  ́K sailplane, in which the main spar of the right wing failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control of the sailplane.

The preliminary investigation has revealed that the fracture may have been due to fatigue. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective July 19, 2010.

On July 19, 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 August 27, 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.: 2010–0122–E, dated June 23, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

A fatal accident occurred to a L–13
BLANI  ́ K sailplane, in which the main spar of the right wing failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control of the sailplane.

The preliminary investigation has revealed that the fracture may have been due to fatigue.

The Emergency AD 2010–0119–E required immediate inspection of the main spar at the root of the wing to detect fatigue cracking and the accomplishment of the relevant corrective actions as necessary. In addition, this AD 2010–0119–E imposed operational limitations. This AD retains the requirements of AD 2010–0119–E, which is superseded, and extends the applicability to L–13 A
BLANI  ́ K sailplanes. The requirements of this AD are considered as interim action to immediately address this unsafe condition. If, as a result of the on-going investigation, a terminating action is later identified, further mandatory actions might be considered.
You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Aircraft Industries a.s. has issued Mandatory Bulletin MB No.: L13/109a, dated June 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 a fatal accident occurred in an L–13 Blanik glider. The main spar of the right wing of the accident glider failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control. The preliminary investigation has revealed that the fracture may have been due to fatigue. 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–2010–0684; Directorate Identifier 2010–CE–031–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.


### 39797 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

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: 2010–14–15 Aircraft Industries a.s. (Type Certificate G60EU Previously Held by LETECKE  ́ ZA  ́ VODY a.s. and LET Aeronautical Works): Amendment 39– 16360; Docket No. FAA–2010–0684; Directorate Identifier 2010–CE–031–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective July 19, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Models L–13 Blanik gliders, all serial numbers, certificated in any category. Subject

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

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

A fatal accident occurred to a L–13 BLANI  ́ K sailplane, in which the main spar of the right wing failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control of the sailplane.

The preliminary investigation has revealed that the fracture may have been due to fatigue.

The Emergency AD 2010–0119–E required immediate inspection of the main spar at the root of the wing to detect fatigue cracking and the accomplishment of the relevant corrective actions as necessary. In addition, this AD 2010–0119–E imposed operational limitations. This AD retains the requirements of AD 2010–0119–E, which is superseded, and extends the applicability to L–13 A BLANI  ́ K sailplanes. The requirements of this AD are considered as interim action to immediately address this unsafe condition. If, as a result of the on-going investigation, a terminating action is later identified, further mandatory actions might be considered.
Actions and Compliance

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

(1) As of July 19, 2010, aerobatics maneuvers ( i.e., roll, loop, stalled turn, immelmann turn, half roll, and inverted flight) are prohibited. Before further flight after July 19, 2010, insert a copy of this AD into the flight manual to comply with the requirements of this paragraph. The chapter

‘‘ Aerobatics ’’ in ‘‘ Pilot’s Notes for the L–13 sailplane ’’ (flight manual) is not valid.

(2) Before further flight after July 19, 2010, inspect the wing critical areas following Aircraft Industries a.s. Mandatory Bulletin MB No.: L13/109a, dated June 18, 2010, except use a 10X magnifier.

(3) If any cracks are found during the inspection required by paragraph (f)(2) of this AD, no further flights are permitted. (4) Within 10 days after the inspection required by paragraph (f)(2) of this AD, submit the following information requested by Aircraft Industries a.s. Mandatory Bulletin MB No.: L13/109a, dated June 18, 2010, for further assessment. Send information to the address listed in paragraph (i)(2) of this AD.

(i) Appendix No. 1, Summary of L–13 glider Log book record; and

(ii) Paragraph H. RECORD IN GLIDER LOGBOOK AFTER BULLETIN EXECUTION.

Note 1: The above limitation is an interim solution until a final action is identified, at which time the European Aviation Safety Agency (EASA) and the FAA may consider further AD action.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows. The service information requires a visual inspection with a 6X magnifier. We are requiring a 10X magnifier to detect cracks that could go undetected using only a 6X magnifier.

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: 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 FAAapproved 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

(h) Refer to MCAI EASA Emergency AD No.: 2010–0122–E, dated June 23, 2010; and Aircraft Industries a.s. Mandatory Bulletin MB No.: L13/109a, dated June 18, 2010, for related information.
Material Incorporated by Reference

(i) You must use Aircraft Industries a.s. Mandatory Bulletin MB No.: L13/109a, dated June 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


### 39798 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations

this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Aircraft Industries, a.s., Na Za

 ́ honech 1177, 686 04 Kunovice, Czech Republic; phone: +420 572 817 660; fax: +420 572 816 112; Internet: http://www.let.cz/; email: ots@let.cz.

(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 June 28, 2010. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–16382 Filed 7–12–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0382; Directorate Identifier 2009–NM–211–AD; Amendment**  **39–16361; AD 2010–14–16]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Model DHC–8–400, –401, and –402**  **Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing 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:

Several cases have been reported where a loss of fluid in the No.2 hydraulic system has caused the power transfer unit (PTU) to overspeed, resulting in pressure fluctuations and increased fluid flow within the No. 1 hydraulic system. In one case, the hydraulic system control logic did not shut down the PTU and the overspeed condition persisted, resulting in the illumination of the No.1 HYD FLUID HOT caution light.
* * * * * The unsafe condition is possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective August 17, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 17, 2010.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 2, 2008 (73 FR 47818, August 15, 2008).

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 10, 2007 (72 FR 30968, June 5, 2007).

**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 :**  Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7303; fax (516) 794–5531.

**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 April 21, 2010 (75 FR 20787), and proposed to supersede AD 2008–17–06, Amendment 39–15644 (73 FR 47818, August 15, 2008). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

Since we issued AD 2008–17–06, a modification of the power transfer unit (PTU) control logic, including the provision of automatic PTU shutdown in the event of loss of fluid in the No. 2 hydraulic system, has been developed. The modification addresses the identified unsafe condition. In addition, the applicability has been revised to remove airplanes having serial number 4185 and subsequent, since an equivalent modification has been installed in production on these airplanes. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF– 2006–08R1, dated August 31, 2009 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

Several cases have been reported where a loss of fluid in the No.2 hydraulic system has caused the power transfer unit (PTU) to overspeed, resulting in pressure fluctuations and increased fluid flow within the No. 1 hydraulic system. In one case, the hydraulic system control logic did not shut down the PTU and the overspeed condition persisted, resulting in the illumination of the No. 1 HYD FLUID HOT caution light.

As an interim action to avoid possible loss of both the No. 1 and No. 2 hydraulic systems, the Airplane Flight Manual (AFM) has been revised to include pulling the HYD PWR XFER circuit breaker in the event of the loss of all hydraulic fluid in the No. 2 hydraulic system.

Insertion of the resultant Temporary Amendment (TA) No. 13 into the AFM was mandated in the original issue of this [Canadian] directive. This instruction * * * remains in effect until * * * this [revised] directive is accomplished.

Revision 1 of this directive * * * mandates modification of the PTU control logic, including the provision of automatic PTU shutdown in the event of loss of fluid in the No. 2 hydraulic system. In addition, the applicability of the [Canadian] directive has been revised to remove aircraft Serial Number (SN) 4185 and subsequent, since an equivalent modification has been installed in production on these aircraft. The unsafe condition is possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. 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 received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

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