Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 9003 

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 adding 

the following new airworthiness 

directive (AD): 

Hamilton Sundstrand Corporation: Docket 

No. FAA–2013–0056; Directorate 

Identifier 2012–NE–48–AD. 

(a) Comments Due Date 

We must receive comments by March 25, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Hamilton Sundstrand 

Corporation 14SF–7, 14SF–15, and 14SF–23 

series propellers, using Hamilton Sundstrand 

Corporation auxiliary pumps and motors 

(auxiliary feathering pumps), part number 

(P/N) 782655–3 (Aerocontrolex P/N 4122– 

006009), with the following serial numbers 

(S/Ns): 

(1) S/Ns 1 through 365, excluding 95, 108, 

122, 177, 193, 278, 285, 293, 297, 310, and 

362. 

(2) S/Ns 366 through 710, excluding 387, 

405, 423, 481, 506, 574, 584, 596, 632, and 

669. 

(3) S/Ns 711 through 1035, excluding 733, 

824, 852, and 994. 

(4) S/Ns 1036 through 1475, excluding 

1038, 1054, 1081, 1086, 1098, and 1177. 

(5) S/Ns 1476 through 1615, excluding 

1523. 

(6) S/Ns 4516 through 4521. 

(d) Unsafe Condition 

This AD was prompted by a report of a 

propeller not moving into the feathering 

position after an engine in-flight shutdown. 

We are issuing this AD to prevent propellers 

from failing to move into the feathering 

position after an engine in-flight shutdown. 

Propellers failing to feather can cause high 

drag on the propeller, asymmetric thrust, and 

difficulty of or impossibility in controlling 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Auxiliary Feathering Pump Removal 

Remove the affected auxiliary feathering 

pumps from service at the following: 

(1) Not later than April 30, 2013, for the 

affected S/Ns listed in paragraph (c)(1) of this 

AD. 

(2) Not later than October 31, 2013, for the 

affected S/Ns listed in paragraph (c)(2) of this 

AD. 

(3) Not later than April 30, 2014, for the 

affected S/Ns listed in paragraph (c)(3) of this 

AD. 

(4) Not later than October 31, 2014, for the 

affected S/Ns listed in paragraph (c)(4) of this 

AD. 

(5) Not later than April 30, 2015, for the 

affected S/Ns listed in paragraph (c)(5) of this 

AD. 

(6) Not later than April 30, 2014, for the 

affected S/Ns listed in paragraph (c)(6) of this 

AD. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any auxiliary feathering pump listed 

as affected in paragraph (c) this AD, unless 

the auxiliary feathering pump has been 

properly modified. Properly modified 

auxiliary feathering pumps will have the 

letter ‘‘M’’ following the pump S/N, as 

described in Hamilton Sundstrand 

Corporation Alert Service Bulletin No. 14SF– 

61–A165, dated September 25, 2012. 

(h) 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. 

(i) Related Information 

(1) 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. 

(2) For service information identified in 

this AD, contact Hamilton Sundstrand 

Propeller Technical Team, One Hamilton 

Road, Mail Stop 1–3–AB43, Windsor Locks, 

CT 06096–1010; fax: 860–654–5107. 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. 2013–02719 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–2012–1329; Directorate 

Identifier 2012–NE–46–AD] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Engine Alliance GP7270 and GP7277 

turbofan engines. This proposed AD was 

prompted by damage to the highpressure compressor (HPC) stage 7–9 

spool caused by failure of the baffle 

plate feature on affected HPC stage 6 

disks. This proposed AD would require 

initial and repetitive borescope 

inspections of the baffle plate feature 

and removal from service of the HPC 

stage 6 disk before further flight, if the 

plate is missing material. This proposed 

AD would also require mandatory 

removal from service of these HPC stage 

6 disks at the next HPC module 

exposure. We are proposing this AD to 

prevent uncontained failure of the HPC 

stage 7–9 spool, uncontained engine 

failure, and damage to 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 proposed AD, contact Engine 

Alliance, 411 Silver Lane, East Hartford, 

CT 06118, phone: 800–565–0140; Web 

site: https://www.engine

allianceportal.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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

9004 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 

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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–1329; Directorate Identifier 2012– 

NE–46–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 

We received reports of the baffle plate 

feature failing on HPC stage 6 disks, part 

number (P/N) 382–100–505–0 from high 

cycle fatigue. The failures resulted in 

material from the baffle plate feature 

causing damage to the HPC stage 7–9 

spool, causing the spool to crack. Engine 

Alliance has introduced a redesigned 

HPC stage 6 disk with a different P/N, 

to eliminate the failures. This condition, 

if not corrected, could result in 

uncontained failure of the HPC stage 

7–9 spool, uncontained engine failure, 

and damage to the airplane. 

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 require 

initial and repetitive borescope 

inspections of the HPC stage 6 disk 

baffle plate feature and removal from 

service of any HPC stage 6 disk, P/N 

382–100–505–0, before further flight if 

the feature is missing any material. This 

proposed AD would also require 

mandatory removal from service of 

these HPC stage 6 disks at the next HPC 

module exposure, but no later than 

accumulating 6,800 cycles-since-new on 

the disk. 

Costs of Compliance 

We estimate that this proposed AD 

would affect no engines installed on 

airplanes of U.S. registry, and the cost 

to U.S. operators to be $0. 

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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

Engine Alliance: Docket No. FAA–2012– 

1329; Directorate Identifier 2012–NE– 

46–AD. 

(a) Comments Due Date 

We must receive comments by April 8, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Engine Alliance 

GP7270 and GP7277 turbofan engines with a 

high-pressure compressor (HPC) stage 6 disk, 

part number (P/N) 382–100–505–0, installed. 

(d) Unsafe Condition 

This AD was prompted by damage to the 

HPC stage 7–9 spool caused by failure of the 

baffle plate feature on affected HPC stage 6 

disks. We are issuing this AD to prevent 

uncontained failure of the HPC stage 7–9 

spool, uncontained engine failure, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Borescope Inspections 

(1) For HPC stage 6 disks with fewer than 

1,000 cycles-since-new (CSN) on the effective 

date of this AD, initially borescope inspect 

the baffle plate feature on the disk (360 

degrees) before accumulating 1,500 CSN. 

(2) For HPC stage 6 disks with 1,000 CSN 

or more on the effective date of this AD, 

initially borescope inspect the baffle plate 

feature on the disk (360 degrees) within the 

next 500 cycles-in-service (CIS). 

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Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 9005 

(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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS