Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 9001 

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): 

The Boeing Company: Docket No. FAA– 

2013–0089; Directorate Identifier 2012– 

NM–166–AD. 

(a) Comments Due Date 

We must receive comments by March 25, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 747–24A2360, Revision 1, 

dated May 2, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 24, Electrical Power. 

(e) Unsafe Condition 

This AD was prompted by reports of 

auxiliary power unit (APU) faults due to 

power feeder cable chafing. We are issuing 

this AD to detect and correct chafing of the 

APU power feeder cables within a flammable 

fluid leakage zone, which, with arcing, could 

result in fire and structural damage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection, Related Investigative and 

Corrective Actions 

Except as required by paragraph (h)(2) of 

this AD, within the compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–24A2360, 

Revision 1, dated May 2, 2012: Do a detailed 

inspection for damage (e.g., surface finish 

integrity, excessive wear or possible heat 

damage) of the APU power feeder cables 

within each wire bundle on the left and right 

of the bulkhead, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–24A2360, Revision 1, dated May 2, 2012; 

except as required by paragraph (h)(1) of this 

AD. If no damage is found during this 

inspection, before further flight, replace the 

clamp(s) and install grommets, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–24A2360, 

Revision 1, dated May 2, 2012. Do all 

applicable related investigative and 

correction actions before further flight. 

(h) Exceptions to the Service Information 

(1) If any damage is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–24A2360, 

Revision 1, dated May 2, 2012, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the damage using a 

method approved in accordance with 

paragraph (k) of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–24A2360, Revision 1, dated May 2, 2012, 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, any 

wiring support clamp, except for part number 

TA025097L16, in any area of the airplane, as 

specified in Boeing Alert Service Bulletin 

747–24A2360, Revision 1, dated May 2, 2012. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–24A2360, dated January 

18, 2012, which is not incorporated by 

reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6482; fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced 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. 

Issued in Renton, Washington, on January 

19, 2013. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02717 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–2013–0056; Directorate 

Identifier 2012–NE–48–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hamilton 

Sundstrand Corporation Propellers 

ACTION: Notice of proposed rulemaking 

(NPRM), DOT. 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Hamilton Sundstrand Corporation 

14SF–7, 14SF–15, and 14SF–23 series 

propellers using certain Hamilton 

Sundstrand Corporation auxiliary 

pumps and motors (auxiliary feathering 

pumps). This proposed AD was 

prompted by a report of a propeller not 

moving into the feathering position after 

an engine in-flight shutdown. This 

proposed AD would require removing 

certain serial numbers (S/Ns) of 

auxiliary feathering pumps from service. 

We are proposing this AD to prevent 

propellers from failing to move into the 

feathering position after an engine inflight shutdown. Propellers failing to 

feather can cause high drag on the 

propeller, asymmetric thrust, and 

difficulty of, or impossibility in, 

controlling the airplane. 

DATES: We must receive comments on 

this proposed AD by March 25, 2013. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

9002 Federal Register / Vol. 78, No. 26 / Thursday, February 7, 2013 / Proposed Rules 

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 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. 

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; email: 

michael.schwetz@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– 

2013–0056; Directorate Identifier 2012– 

NE–48–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 a report of an engine inflight shutdown on a Bombardier DHC– 

8–400 airplane, where the propeller did 

not move into the feathering position. 

Bombardier was in contact with 

Hamilton Sundstrand Corporation 

inquiring about the auxiliary feathering 

pump used on the Hamilton Sundstrand 

Corporation propellers. Hamilton 

Sundstrand Corporation found the 

auxiliary feathering pump used on their 

14SF series propeller is a similar design 

as that used on the DHC–8–400 

airplane. The Hamilton Sundstrand 

investigation revealed some of their 

auxiliary feathering pump motors had 

internal corrosion that may cause the 

stator magnets in the pump motor to fail 

and rotate into the path of the armature, 

preventing the pump from feathering 

the propeller. This condition, if not 

corrected, could result in propellers 

failing to feather, causing high drag on 

the propeller, asymmetric thrust, and 

difficulty of, or impossibility in, 

controlling the airplane. 

Relevant Service Information 

We reviewed Hamilton Sundstrand 

Corporation Alert Service Bulletin 

(ASB) No. 14SF–61–A165, dated 

September 25, 2012. The ASB lists by S/ 

N the affected Hamilton Sundstrand 

Corporation auxiliary feathering pumps, 

part number (P/N) 782655–3 

(Aerocontrolex P/N 4122–006009) and 

provides instructions for getting the 

pumps modified. 

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 

removing the affected auxiliary 

feathering pumps from service. 

Costs of Compliance 

We estimate that this proposed AD 

affects 284 Hamilton Sundstrand 

Corporation 14SF–7, 14SF–15, and 

14SF–23 series propellers using affected 

auxiliary feathering pumps installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 1.5 

hours per propeller to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Required parts cost is 

$6,000 per propeller. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,740,210. 

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. 

(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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

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