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(3) Thereafter, repetitively borescope 

inspect the baffle plate feature on the disk 

(360 degrees) within every 500 CIS. 

(4) Remove the HPC stage 6 disk before 

further flight if found cracked or with 

missing material. 

(g) Mandatory Removal From Service of 

Affected HPC Stage 6 Disks 

At next HPC module exposure, but not to 

exceed 6,800 CSN on the HPC stage 6 disk, 

remove the HPC stage 6 disk, P/N 382–100– 

505–0, from service. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install any HPC stage 6 disk, P/N 382–100– 

505–0, into any HPC module. 

(i) Definition 

For the purpose of this AD, HPC module 

exposure is defined as separation of the 

flanges between the compressor case and the 

combustion diffuser case. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Martin Adler, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7157; fax: 781–238– 

7199; email: martin.adler@faa.gov. 

(2) Engine Alliance Service Bulletin No. 

EAGP7–72–236, pertains to the subject of this 

AD. 

(3) For service information identified in 

this AD, contact Engine Alliance, 411 Silver 

Lane, East Hartford, CT 06118, phone: 800– 

565–0140; Web site: https:// 

www.engineallianceportal.com. You may 

view this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

January 28, 2013. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02721 Filed 2–6–13; 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] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) 

that applies to all Dowty Propellers 

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

existing AD currently requires initial 

applications of sealant between the bus 

bar assembly and the backplate 

assembly of certain line-replaceable 

units (LRUs), and repetitive applications 

of sealant on all R408/6–123–F/17 

model propellers. Since we issued that 

AD, Dowty Propellers has introduced an 

optional terminating action to the 

applications of sealant. This proposed 

AD would add the optional terminating 

action. We are proposing this AD to 

prevent an in-flight double generator 

failure, which could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 8, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Dowty Propellers, 

Anson Business Park, Cheltenham Road 

East, Gloucester GL 29QN, UK; phone: 

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

716001. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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; phone: 781– 

238–7761; fax 781–238–7170; e- mail: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0776; Directorate Identifier 

2009–NE–32–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On August 5, 2010, we issued AD 

2010–17–11, Amendment 39–16403 (75 

FR 51656, August 23, 2010), for all 

Dowty Propellers R408/6–123–F/17 

model propellers. That AD requires 

initial applications of sealant between 

the bus bar assembly and the backplate 

assembly of LRUs serial numbers below 

DAP0347, and repetitive applications of 

sealant on all R408/6–123–F/17 model 

propellers. That AD resulted from 

mandatory continuing airworthiness 

information issued by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. We issued that AD to 

prevent an in-flight double generator 

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9006 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 

failure, which could result in reduced 

controllability of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2010–17–11 (75 

FR 51656, August 23, 2010), Dowty 

Propellers introduced an optional 

terminating action to the repetitive 

applications of sealant. That action 

consists of replacing the bus bar 

assembly with a slip ring de-icer 

harness. 

Relevant Service Information 

We reviewed Dowty Propellers 

Service Bulletin (SB) No. D8400–61–94, 

Revision 3, dated October 23, 2012. The 

SB describes procedures for replacing 

the bus bar assembly with a slip ring deicer harness. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

the requirements of AD 2010–17–11 (75 

FR 51656, August 23, 2010). This 

proposed AD would add an optional 

terminating action to the applications of 

sealant by replacing the bus bar 

assembly with a slip ring de-icer 

harness. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 104 propellers 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 2 hours per propeller to apply 

sealant and required sealant would cost 

about $20 per propeller. We also 

estimate that it would take about 3 

hours to replace the bus bar with a deicer slip ring harness and required parts 

would cost about $1,200 per propeller. 

The average labor rate is $85 per hour. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $171,080. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2010–17–11, Amendment 39–16403 (75 

FR 51656, August 23, 2010), and adding 

the following new AD: 

Dowty Propellers (formerly Dowty 

Aerospace; Dowty Rotol Limited; and 

Dowty Rotol): Docket No. FAA–2009– 

0776; Directorate Identifier 2009–NE– 

32–AD. 

(a) Comments Due Date 

We must receive comments on this AD 

action by April 8, 2013. 

(b) Affected ADs 

This AD revises AD 2010–17–11, 

Amendment 39–16403 (75 FR 51656, August 

23, 2010). 

(c) Applicability 

(1) 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. 

(d) Unsafe Condition 

This AD was prompted by the need to add 

an optional terminating action to the 

applications of sealant. We are issuing this 

AD to prevent an in-flight double generator 

failure, which could result in reduced 

controllability of the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(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 September 27, 2010, or within 100 FH 

from the effective date of this AD, whichever 

occurs later: 

(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 

apply the the sealant. 

(2) Thereafter, re-apply sealant as specified 

in paragraphs (e)(1)(i) through (e)(1)(ii) of this 

AD within every additional 10,000 FH. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any Dowty Propellers R408/6–123–F/ 

17 propeller unless sealant has been applied 

between the bus bar assembly and the 

backplate assembly as specified by this AD, 

or unless the optional terminating action as 

specified in paragraph (i) of this AD, has 

been performed. 

(g) Differences Between This AD and the 

Service Information 

None. 

(h) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) Sealant applications 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, satisfy the 

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initial sealant application requirement of this 

AD. 

(2) Re-application of sealant within 10,000 

FH since last application satisifies the 

reapplication requirement. However, unless 

you have incorporated the optional 

terminating action provided in this AD 

Revision, you must reapply the sealant per 

paragraph (e)(1)(i) of this AD. 

(3) Replacement of the bus bar assembly 

with a slip ring de-icer harness before the 

effective date of this AD using paragraph 3.A. 

of the Accomplishment Instructions of Dowty 

Propellers Service Bulletin No. D8400–61– 

94, Revision 2, dated August 29, 2012, 

satisfies the optional terminating requirement 

of this AD. 

(i) Optional Terminating Action 

As optional terminating action to the 

sealant applications of this AD, replace the 

bus bar assembly with a slip ring de-icer 

harness. Use paragraph 3.A. of the 

Accomplishment Instructions of Dowty 

Propellers Service Bulletin No. D8400–61– 

94, Revision 3, dated October 23, 2012, to do 

the replacement. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Boston Aircraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(k) Related Information 

(1) Refer to European Aviation Safety 

Agency AD 2009–0114R1 (correction: Dated 

December 13, 2012) for related information. 

(2) For more information about this AD, 

contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA 01803; phone: 781–238–7761; fax 781– 

238–7170; email: michael.schwetz@faa.gov. 

(3) For service information identified in 

this AD, contact Dowty Propellers, Anson 

Business Park, Cheltenham Road East, 

Gloucester GL 29QN, UK; phone: 44 (0) 1452 

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

view this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

January 29, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02730 Filed 2–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0024; Directorate 

Identifier 2000–NE–12–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Turbomeca S.A. 

Arrius Models 2B, 2B1, and 2F 

turboshaft engines. The existing AD 

currently requires replacement of 

injector manifolds and borescopeinspection of the flame tube and the 

high-pressure (HP) turbine area for 

possible damage. Since we issued that 

AD, we received a report that the 

corrective actions of the existing AD 

were insufficient to eliminate the unsafe 

condition. This proposed AD would 

require, depending on the engine model, 

repetitive replacements of fuel injection 

manifolds and the privilege injector, or, 

repetitive replacements of the privilege 

injector. We are proposing this AD to 

prevent an uncommanded in-flight 

shutdown of Arrius 2B1 and 2F 

turboshaft engines and damage to the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by April 8, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Turbomeca, 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 

00; telex: 570 042; fax: 33 (0)5 59 74 45 

15. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7176; fax: 781–238– 

7199; email: james.lawrence@faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0024; Directorate Identifier 

2000–NE–12–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On January 9, 2006, we issued AD 

2001–08–14R1, Amendment 39–14423 

(71 FR 2993, January 19, 2006), for all 

Arrius Models 2B, 2B1, and 2F 

turboshaft engines. That AD requires 

replacement of injector manifolds and 

borescope inspection of the flame tube 

and the HP turbine area. That AD 

resulted from reports from the Direction 

Generale de L’Aviation Civile (DGAC), 

which was the airworthiness authority 

for France, of partially or totally blocked 

fuel injection manifolds found during 

inspections at a repair workshop. We 

issued that AD to prevent engine 

flameout during rapid deceleration, or 

the inability to maintain the 2.5 minutes 

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