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

24343 

Vol. 76, No. 84 

Monday, May 2, 2011 

DEPARTMENT OF AGRICULTURE 

Rural Business-Cooperative Service 

Rural Utilities Service 

7 CFR Part 4288 

RIN 0570–AA75 

Advanced Biofuel Payment Program; 

Correction 

AGENCY: Rural Business-Cooperative 

Service; Rural Utilities Service, USDA. 

ACTION: Correcting amendment. 

SUMMARY: The Agency published a 

document in the Federal Register of 

February 11, 2011, establishing the 

Advanced Biofuel Payment Program 

authorized under the Food, 

Conservation, and Energy Act of 2008. 

This document also established an 

application deadline for applicants to 

submit their applications for Fiscal Year 

(FY) 2010 on April 12, 2011. The 

Agency is extending the application 

period to May 6, 2011. Applications 

received after May 6, 2011, will not be 

considered for FY 2010. 

DATES: Effective Date: May 2, 2011. 

FOR FURTHER INFORMATION CONTACT: 

Requests for additional information 

should be directed to Diane Berger, 

(202) 260–1508. 

SUPPLEMENTARY INFORMATION: Under this 

Program, the Agency will enter into 

contracts with advanced biofuel 

producers to pay such producers for the 

production of eligible advanced 

biofuels. 

As published, the interim rule stated 

that applications for FY 2010 must be 

submitted by April 12, 2011. This date 

is referenced in the preamble 

SUPPLEMENTARY INFORMATION on page 

7936, column 2, lines 4 and 5 and on 

page 7966, column 2, in the last 

paragraph of the column. The Agency is 

extending the application period to May 

6, 2011. 

Need for Correction 

Due to the delay in obtaining approval 

of the application and payment forms, 

the Agency needs to extend the 

application period. The extension will 

allow the public an adequate period of 

time to complete and submit 

applications. 

List of Subjects in 7 CFR Part 4288 

Administrative practice and 

procedure, Energy-advanced biofuel, 

Renewable biomass, Reporting and 

recordkeeping. 

Accordingly, 7 CFR part 4288 is 

corrected by making the correcting 

amendment: 

PART 4288—PAYMENT PROGRAMS 

■ 1. The authority citation for part 4288 

continues to read as follows: 

Authority: 5 U.S.C. 301; 7 U.S.C. 1989. 

■ 2. Section 4288.190(b)(1) is amended 

by removing ‘‘April 12, 2011’’ and 

adding in its place ‘‘May 6, 2011’’. 

Dated: April 19, 2011. 

Dallas Tonsager, 

Under Secretary, Rural Development. 

[FR Doc. 2011–10495 Filed 4–29–11; 8:45 am] 

BILLING CODE 3410–XY–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1157; Directorate 

Identifier 2010–NM–137–AD; Amendment 

39–16674; AD 2011–09–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–101, –102, –103, 

–106, –201, –202, –301, –311, –315, 

–401, and –402 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: 

There have been several in-service reports 

of finding trapped water on the bottom of the 

cockpit windshield frames (or lower 

windshield frames) that resulted in either 

corrosion or water ingress into the cockpit. In 

one occurrence, the trapped water caused 

severe corrosion of numerous anchor nuts 

that secure the windshield to the lower 

windshield frame, such that the intended 

fastening function was seriously 

compromised. 

Corrosion of the lower windshield frames, 

including the anchor nuts that secure the 

windshield to the aircraft structure, can 

result in a serious structural degradation 

possibly leading to the loss of the windshield 

during flight. Also, water could leak into the 

cockpit and cause either a malfunction or 

failure of the electrical and electronics 

systems in the area of the cockpit instrument 

panels. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2011. 

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: 

Craig Yates, 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– 

7355; 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 November 23, 2010 (75 FR 

71369). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 


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24344 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 

There have been several in-service reports 

of finding trapped water on the bottom of the 

cockpit windshield frames (or lower 

windshield frames) that resulted in either 

corrosion or water ingress into the cockpit. In 

one occurrence, the trapped water caused 

severe corrosion of numerous anchor nuts 

that secure the windshield to the lower 

windshield frame, such that the intended 

fastening function was seriously 

compromised. 

Corrosion of the lower windshield frames, 

including the anchor nuts that secure the 

windshield to the aircraft structure, can 

result in a serious structural degradation 

possibly leading to the loss of the windshield 

during flight. Also, water could leak into the 

cockpit and cause either a malfunction or 

failure of the electrical and electronics 

systems in the area of the cockpit instrument 

panels. 

The lower windshield frames do not have 

drain provisions to prevent moisture or water 

run-off from the condensation of the 

windshields from being trapped. The 

consequences of trapped water in the lower 

windshield frames can result in unsafe 

conditions, as noted above. This Directive 

mandates the installation of a drain system 

for the lower windshield frames. 

For Model DHC–8–401 and –402 

airplanes, the installation also includes 

a related investigative action, and 

corrective actions if necessary. The 

related investigative action is an 

inspection for corrosion of the anchor 

nuts and window frame. Corrective 

actions include replacing any corroded 

anchor nut with a new or serviceable 

anchor nut, or contacting the 

manufacturer for repair instructions and 

doing the repair. 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 comment received. 

Request to Reference Revision D of 

Bombardier Service Bulletin 8–53–78 

Hawaii Island Air stated that 

Bombardier has issued new Revision D, 

dated July 6, 2010, for Service Bulletin 

8–53–78. 

We infer that Hawaii Island Air 

requested that we update our references 

to include Bombardier Service Bulletin 

8–53–78, Revision D, dated July 6, 2010. 

We agree. This service bulletin was 

revised for minor changes such as a 

serial number change and deletion of 

certain modification kits. We have 

revised paragraph (g) of this AD to 

reference Bombardier Service Bulletin 

8–53–78, Revision D, dated July 6, 2010. 

We have also added paragraph (h) of 

this AD to give credit for Bombardier 

Service Bulletin 8–53–78, Revision C, 

dated April 29, 2010. 

Revision to Applicability 

We have added Model DHC–8–101 

airplanes to the applicability of this AD 

because these airplanes are affected by 

the identified unsafe condition. There 

are no Model DHC–8–101 airplanes 

registered in the United States. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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 also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

191 products of U.S. registry. We also 

estimate that it will take about 20 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $1,660 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$641,760, or $3,360 per product. 

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 this AD: 

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 AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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: 


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Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24345 

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: 

2011–09–12 Bombardier, Inc.: Amendment 

39–16674. Docket No. FAA–2010–1157; 

Directorate Identifier 2010–NM–137–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 6, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier, Inc. 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model DHC–8–101, –102, –103, –106, 

–201, –202, –301, –311, and –315, serial 

numbers 003 through 566 inclusive. 

(2) Model DHC–8–401, and –402 airplanes, 

serial numbers 4001, 4003, 4004, 4006, and 

4008 through 4274 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 56: Windows. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been several in-service reports 

of finding trapped water on the bottom of the 

cockpit windshield frames (or lower 

windshield frames) that resulted in either 

corrosion or water ingress into the cockpit. In 

one occurrence, the trapped water caused 

severe corrosion of numerous anchor nuts 

that secure the windshield to the lower 

windshield frame, such that the intended 

fastening function was seriously 

compromised. 

Corrosion of the lower windshield frames, 

including the anchor nuts that secure the 

windshield to the aircraft structure, can 

result in a serious structural degradation 

possibly leading to the loss of the windshield 

during flight. Also, water could leak into the 

cockpit and cause either a malfunction or 

failure of the electrical and electronics 

systems in the area of the cockpit instrument 

panels. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, install a drain system in the 

cockpit windshield lower frames, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–53–78, Revision D, dated 

July 6, 2010 (for Model DHC–8–101, –102, 

–103, –106, –201, –202, –301, –311, and –315 

airplanes); or 84–53–43, dated April 27, 2010 

(for Model DHC–8–401 and –402 airplanes); 

except where these service bulletins state to 

contact the manufacturer, contact the New 

York Aircraft Certification Office or 

Transport Canada Civil Aviation (TCCA) or 

its delegated agent. Do all applicable related 

investigative and corrective actions before 

further flight. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) For Models DHC–8–101, –102, –103, 

–106, –201, –202, –301, –311, and –315 

airplanes: Modification of the drain system is 

also acceptable for compliance with the 

requirements of paragraph (g) of this AD, if 

done before the effective date of this AD, in 

accordance with Bombardier Service Bulletin 

8–53–78, dated December 23, 1999; Revision 

A, dated June 7, 2001; Revision B, dated May 

2, 2002; or Revision C, dated April 29, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–16, dated May 18, 2010; 

Bombardier Service Bulletin 8–53–78, 

Revision D, dated July 6, 2010; and 

Bombardier Service Bulletin 84–53–43, dated 

April 27, 2010; for related information. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 8–53–78, Revision D, dated July 6, 

2010; or Bombardier Service Bulletin 84–53– 

43, dated April 27, 2010; as applicable; 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 Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

e-mail thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(3) 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. 

(4) 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, on April 12, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9673 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1205; Directorate 

Identifier 2010–NM–146–AD; Amendment 

39–16677; AD 2011–09–15] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200, –200LR, 

–300, and –300ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires, 

for certain airplanes, replacing certain 

boost pump relays with ground fault 

interrupter (GFI) relays. For certain 

other airplanes, this AD requires 

installing new panels in the main 

equipment center, making certain 

wiring changes, installing new GFI 

relays in the new panels, and installing 


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