This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

23169 

Vol. 76, No. 80 

Tuesday, April 26, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0409; Directorate 

Identifier 2011–CE–011–AD; Amendment 

39–16678; AD 2011–09–16] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Glaser-Dirks 

Model DG–808C Gliders 

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: 

It has been reported by DG–808 C owners 

that the bolt at the landing gear control 

bellcrank was found mounted in the wrong 

direction. Further investigations have shown 

that in such situation, the bolt could interfere 

and damage: 

—The air brake control pushrod, and 

—The wing flap control pushrod if the 

landing gear is operated with negative flap 

settings. 

This condition, if not detected and 

corrected, may lead to reduce the 

controllability of the powered sailplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

2, 2011. 

On May 2, 2011, 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 June 10, 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 AD, contact DG-Flugzeugbau 

GmbH, Otto-Lilienthal-Weg 2, D 76 646 

Bruchsal, Germany; telephone: +49 7251 

3020 140; fax: +49 7251 3020 149; 

Internet: http://www.dg-flugzeugbau.de/ 

index-e.html; e-mail: dg@dgflugzeugbau.de. 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 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: 

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.: 

2011–0053–E, dated March 24, 2011 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

It has been reported by DG–808 C owners 

that the bolt at the landing gear control 

bellcrank was found mounted in the wrong 

direction. Further investigations have shown 

that in such situation, the bolt could interfere 

and damage: 

—The air brake control pushrod, and 

—The wing flap control pushrod if the 

landing gear is operated with negative flap 

settings. 

This condition, if not detected and 

corrected, may lead to reduce the 

controllability of the powered sailplane. 

For the reasons described above, this AD 

requires to inspect the landing gear control 

bellcrank bolt for proper installation and the 

accomplishment of the associated corrective 

actions, as applicable. 

EASA issued AD No.: 2011–0053–E 

based on their determination that this 

was a production error and a quality 

control problem. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

DG Flugzeugbau GmbH has issued 

Technical note No. 800/40, dated 

February 14, 2011; and Section A–A of 

Undercarriage control circuit Diagram 

15, dated November 2004, of DG 

Flugzeugbau GmbH Maintenance 

Manual for the Motorglider DG–808C, 

dated June 2005. 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. 

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23170 Federal Register / Vol. 76, No. 80 / Tuesday, April 26, 2011 / Rules and Regulations 

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 it has been reported that 

bolts at the landing gear control 

bellcrank were mounted in the wrong 

direction. The incorrectly mounted bolt 

could interfere and damage the air brake 

control pushrod and the wing flap 

control pushrod if the landing gear is 

operated with negative flap settings. 

This condition, if not detected and 

corrected, may lead to reducing the 

controllability of the powered sailplane. 

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–2011–0409; 

Directorate Identifier 2011–CE–011–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. 

Costs of Compliance 

We estimate that this AD will affect 5 

products of U.S. registry. We also 

estimate that it would take about 0.5 

work-hour per product to comply with 

the basic requirements of this 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 AD on U.S. operators to 

be $213, or $43 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 0.5 work-hour and require parts 

costing $250, for a cost of $293 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 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: 

2011–09–16 DG Flugzeugbau GmbH: 

Amendment 39–16678; Docket No. 

FAA–2011–0409; Directorate Identifier 

2011–CE–011–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 2, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to DG Flugzeugbau 

GmbH Glaser-Dirks Models DG–808C gliders, 

serial numbers 8–316 B 216 X 1 through 

8–417 B 316 X 76, 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: 

It has been reported by DG–808 C owners 

that the bolt at the landing gear control 

bellcrank was found mounted in the wrong 

direction. Further investigations have shown 

that in such situation, the bolt could interfere 

and damage: 

—The air brake control pushrod, and 

—The wing flap control pushrod if the 

landing gear is operated with negative flap 

settings. 

This condition, if not detected and 

corrected, may lead to reduce the 

controllability of the powered sailplane. 

For the reasons described above, this AD 

requires to inspect the landing gear control 

bellcrank bolt for proper installation and the 

accomplishment of the associated corrective 

actions, as applicable. 

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Federal Register / Vol. 76, No. 80 / Tuesday, April 26, 2011 / Rules and Regulations 23171 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before further flight after May 2, 2011 

(the effective date of this AD), inspect the 

landing gear control bellcrank bolt M6x26 

LN9037 for proper installation following 

DG–Flugzeugbau GmbH Technical note 

No. 800/40, dated February 14, 2011. 

(2) If, during the inspection required by 

paragraph (f)(1) of this AD, the bolt is found 

mounted in the wrong direction, before 

further flight, do the following actions: 

(i) Install the landing gear control bellcrank 

bolt M6x26 LN9037 and its washers and nut 

correctly following DG–Flugzeugbau GmbH 

Technical note No. 800/40, dated February 

14, 2011; and Section A–A of Undercarriage 

control circuit Diagram 15, dated November 

2004, of DG Flugzeugbau GmbH Maintenance 

Manual for the Motorglider DG–808C, dated 

June 2005. 

(ii) Inspect the air brake control pushrod 

(part number (P/N) 6St13) and the wing flap 

control pushrod (P/N 8St7) for damage. If any 

pushrod is damaged, before further flight, 

replace it with a serviceable part following 

DG–Flugzeugbau GmbH Technical note No. 

800/40, dated February 14, 2011. 

FAA AD Differences 

Note: 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 MCAI European Aviation 

Safety Agency (EASA) AD No.: 2011–0053– 

E, dated March 24, 2011, DG–Flugzeugbau 

GmbH Technical note No. 800/40, dated 

February 14, 2011; and Section A–A of 

Undercarriage control circuit Diagram 15, 

dated November 2004, of DG Flugzeugbau 

GmbH Maintenance Manual for the 

Motorglider DG–808C, dated June 2005, for 

related information. 

Material Incorporated by Reference 

(i) You must use DG–Flugzeugbau GmbH 

Technical note No. 800/40, dated February 

14, 2011; and Section A–A of Undercarriage 

control circuit Diagram 15, dated November 

2004, of DG Flugzeugbau GmbH Maintenance 

Manual for the Motorglider DG–808C, dated 

June 2005, 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 DG-Flugzeugbau GmbH, 

Otto-Lilienthal-Weg 2, D 76 646 Bruchsal, 

Germany; telephone: +49 7251 3020 140; fax: 

+49 7251 3020 149; Internet: http://www.dgflugzeugbau.de/index-e.html; e-mail: dg@dgflugzeugbau.de. 

(3) 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. 

(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 April 

19, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–10006 Filed 4–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 40 

[Docket No. RM10–8–000; Order No. 750] 

Electric Reliability Organization 

Interpretations of Interconnection 

Reliability Operations and 

Coordination and Transmission 

Operations Reliability Standards 

AGENCY: Federal Energy Regulatory 

Commission, Energy. 

ACTION: Final rule. 

SUMMARY: Pursuant to section 215 of the 

Federal Power Act, the Federal Energy 

Regulatory Commission hereby 

approves the North American Electric 

Reliability Corporation’s (NERC) 

interpretation of the Commissionapproved Reliability Standards, IRO– 

005–1, Reliability Coordination— 

Current-Day Operations, Requirement 

R12, and TOP–005–1, Operational 

Reliability Information, Requirement 

R3. Specifically, the interpretation finds 

that a transmission owner must report a 

Special Protection System that is 

operating with only one communication 

channel in service to the reliability 

coordinator and neighboring systems 

upon request, or when the loss of the 

communication channel will result in 

the failure of the Special Protection 

System to operate as designed. 

DATES: Effective Date: This rule will 

become effective May 26, 2011. 

FOR FURTHER INFORMATION CONTACT: 

Danny Johnson (Technical Information), 

Office of Electric Reliability, Federal 

Energy Regulatory Commission, 888 

First Street, NE., Washington, DC 20426. 

Telephone: (202) 502–8892. 

danny.johnson@ferc.gov. 

Richard M. Wartchow (Legal 

Information), Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street, NE., 

Washington, DC 20426. Telephone: 

(202) 502–8744. 

SUPPLEMENTARY INFORMATION: 

135 FERC ¶ 61,041 

Before Commissioners: Jon Wellinghoff, 

Chairman; Marc Spitzer, Philip D. Moeller, 

John R. Norris, and Cheryl A. LaFleur. 

Issued April 21, 2011 

1. Pursuant to section 215 of the 

Federal Power Act, the Federal Energy 

Regulatory Commission hereby 

approves the North American Electric 

Reliability Corporation’s (NERC) 

interpretation of the Commissionmstockstill on DSKH9S0YB1PROD with RULES