51656 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom; 

telephone 044 1332 242424; fax 044 1332 

249936. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20705 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0776; Directorate 

Identifier 2009–NE–32–AD; Amendment 39– 

16403; AD 2010–17–11] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers R408/6–123–F/17 Model 

Propellers 

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 results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Friction or contact between a propeller deice bus bar and the backplate assembly can 

cause failure of the bus bar and a consequent 

intermittent short circuit. Such a short circuit 

can cause a dual AC generator shutdown 

that, particularly in conjunction with an 

engine failure in icing conditions, could 

result in reduced controllability of the 

airplane. 

We are issuing this AD to prevent an inflight double generator failure, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

September 27, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

September 27, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

michael.schwetz@faa.gov; telephone 

(781) 238–7761; fax (781) 238–7170. 

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 September 25, 2009 (74 FR 

48870). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

Friction or contact between a propeller deice bus bar and the backplate assembly can 

cause failure of the bus bar and a consequent 

intermittent short circuit. Such a short circuit 

can cause a dual AC generator shutdown 

that, particularly in conjunction with an 

engine failure in icing conditions, could 

result in reduced controllability of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

One commenter, a private citizen, 

requests that the AD allow propellers 

modified under earlier revisions of the 

service bulletin to meet the 

requirements of the AD, as the 

modification instructions are the same. 

We agree. We added a paragraph that 

allows for previous credit for initial 

sealant application done before the 

effective date of the AD using earlier 

versions of the service bulletin. We also 

reference using Dowty Propellers Alert 

Service Bulletin No. D8400–61–A66, 

Revision 5, dated June 16, 2010 in the 

compliance section, which is the latest 

version. Since Revision 5 of the ASB 

requires repetitive applications of 

sealant, we eliminated the AD 

differences that appeared in the 

proposed AD. 

Conclusion 

We reviewed the available data, 

including the comments 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

104 propellers installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 2 work-hours per 

propeller to comply with this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $20 per 

propeller. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $18,720. 

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. 


sroberts on DSKD5P82C1PROD with RULES
Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Rules and Regulations 51657 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone 

(800) 647–5527) is provided 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: 

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: 

2010–17–11 Dowty Propellers (formerly 

Dowty Aerospace; Dowty Rotol Limited; 

and Dowty Rotol): Amendment 39– 

16403. Docket No. FAA–2009–0776; 

Directorate Identifier 2009–NE–32–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 27, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Dowty Propellers 

R408/6–123–F/17 model propellers. These 

propellers are installed on, but not limited to, 

Bombardier, Inc. (formerly de Havilland 

Canada) models DHC–8–400, DHC–8–401, 

and DHC–8–402 series airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent an in-flight double 

generator failure, which could result in 

reduced controllability of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) For R408/6–123–F/17 model propellers 

with a hub, actuator, and backplate assembly 

line-replaceable unit serial numbers below 

DAP0347, do the following initial sealant 

application within 5,000 flight hours (FH) 

after the effective date of this AD: 

(i) Apply sealant between the bus bar 

assemblies and the backplate assembly. 

(ii) Use paragraph 3 of the 

Accomplishment Instructions of Dowty 

Propellers Alert Service Bulletin No. D8400– 

61–A66, Revision 5, dated June 16, 2010, to 

do the sealant application. 

(2) Thereafter, for all R408/6–123–F/17 

model propellers, re-apply sealant as 

specified in paragraphs (e)(1)(i) through 

(e)(1)(ii) within every additional 10,000 FH. 

Installation Prohibition 

(3) After modification of all propellers on 

an airplane as required by paragraph (e)(1) of 

this AD, do not install any Dowty R408/6– 

123–F/17 propeller on that airplane unless 

sealant has been applied between the bus bar 

assemblies and the backplate assembly of 

that propeller using the requirements of this 

AD. 

FAA AD Differences 

(f) None. 

Previous Credit 

(g) Sealant application performed before 

the effective date of this AD using Dowty 

Propellers Service Bulletin No. D8400–61– 

66, dated February 9, 2007, Revision 1, dated 

May 4, 2007, Alert Service Bulletin No. 

D8400–61–A66, Revision 2, dated August 19, 

2009, Revision 3, dated November 10, 2009, 

Revision 4, dated January 19, 2010, or 

Revision 5, dated June 16, 2010, satisfies the 

initial sealant application requirement of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Boston Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(i) Refer to EASA AD 2009–0114, dated 

May 28, 2009, for related information. 

(j) Contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA 01803; e-mail: michael.schwetz@faa.gov; 

telephone (781) 238–7761; fax (781) 238– 

7170, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use Dowty Propellers Alert 

Service Bulletin No. D8400–61–A66, 

Revision 5, dated June 16, 2010, to do the 

actions required by this AD. 

(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 Dowty Propellers, Anson 

Business Park, Cheltenham Road East, 

Gloucester GL 29QN, UK; telephone: 44 (0) 

1452 716000; fax: 44 (0) 1452 716001. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20707 Filed 8–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0245; Directorate 

Identifier 2010–NE–15–AD; Amendment 39– 

16398; AD 2010–17–06] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. (P&WC) 

PW615F–A Turbofan Engines 

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 results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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 PW617F–E engine powered twin 

engined aircraft had recently experienced an 

uncommanded power reduction on one of its 

engines. Investigation showed that the Fuel 

Filter Bypass Valve poppet in the Fuel Oil 

Heat Exchanger (FOHE) on that engine had 

worn through the housing seat, allowing 

unfiltered fuel and debris to contaminate the 

Fuel Metering Unit (FMU), resulting in fuel 

flow drop and subsequent power reduction. 

P&WC has confirmed that this is a dormant 

failure that could result in an unsafe 

condition. 

The PW615F–A engine Fuel Filter Bypass 

Valve installation is very similar to that of 

PW617F–E, but so far there have been no 

operational abnormalities reported due to 

subject valve failure on PW615F–A engines. 

However, evaluation by P&WC has confirmed 

similar dormant failure of worn through 

poppets of the subject valve on some 

PW615F–A engine installations, which could 

affect both engines at the same time on an 

aircraft and may result in an unsafe 

condition. 

We are issuing this AD to prevent 

uncommanded power reduction, which 

could result in the inability to continue 

safe flight and safe landing. 


sroberts on DSKD5P82C1PROD with RULES