24852 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Proposed Rules 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of chafing of the wire bundles inside the 

electrical conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire sleeving 

into the insulation, exposing the wire 

conductors. We are issuing this AD to 

prevent chafing of the wire bundles and 

subsequent arcing between the wiring and 

the electrical conduit creating an ignition 

source in the fuel tanks, which could result 

in a fire and consequent fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 60 months after the effective date 

of this AD: Replace the wire bundles inside 

the electrical conduit of the forward and aft 

boost pumps of the numbers 1 and 4 main 

fuel tanks with new, improved wire bundles 

inserted into conduit liners, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–28A2306, 

dated October 2, 2014. Accomplishing the 

replacement required by this paragraph 

terminates the repetitive inspections required 

by paragraph (n) of AD 2011–15–03, 

Amendment 39–16750 (76 FR 41659, July 15, 

2011). 

(h) 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 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

(i) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6505; fax: 425–917–6590; 

email: tung.tran@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; phone 206–544– 

5000, extension 1; fax 206–766–5680; 

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

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on April 17, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10068 Filed 4–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0808; Directorate 

Identifier 2008–NE–18–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CT58 Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directives (ADs) 2001–18– 

06 and 2008–22–16, which apply to 

certain General Electric Company (GE) 

CT58 turboshaft engines. ADs 2001–18– 

06 and 2008–22–16 require 

recalculating the lives of life-limited 

rotating parts using a Repetitive HeavyLift (RHL) multiplying factor and 

removal from service of parts that 

exceed the recalculated cyclic or hourly 

life limit. This proposed AD would 

consolidate ADs 2001–18–06 and 2008– 

22–16, and further reduce the life 

capability of certain parts. We are 

proposing this AD to prevent failure of 

life-limited rotating parts, uncontained 

part release, damage to the engine, and 

damage to the aircraft. 

DATES: We must receive comments on 

this proposed AD by June 30, 2015. 

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 General 

Electric Company, GE Aviation, Room 

285, One Neumann Way, Cincinnati, 

OH, 45215; phone: 513- 552–3272; 

email: aviation.fleetsupport@ge.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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2008– 

0808; 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: 

Sanjana Murthy, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7750; fax: 781–238– 

7199; email: sanjana.murthy@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–2008–0808; Directorate Identifier 

2008–NE–18–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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Proposed Rules 24853 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 24, 2001, we issued AD 

2001–18–06, Amendment 39–12432 (66 

FR 47575, September 13, 2001), (‘‘AD 

2001–18–06’’), and on October 20, 2008, 

we issued AD 2008–22–16, Amendment 

39–15712 (73 FR 63629, October 27, 

2008), (‘‘AD 2008–22–16’’), for CT58 

turboshaft engines. AD 2001–18–06 

requires the use of an RHL multiplying 

factor in calculating the lives of lifelimited rotating parts used in RHL 

missions. AD 2008–22–16 addressed a 

shortfall in the life capability of 

compressor spools used in RHL 

operations. We issued ADs 2001–18–06 

and 2008–22–16 to prevent cracks in 

rotating parts that could result in an 

uncontained engine failure, damage to 

the engine, and damage to the aircraft. 

Actions Since ADs 2001–18–06 and 

2008–22–16 Were Issued 

Since we issued ADs 2001–18–06 and 

2008–22–16, GE updated the life limits 

of compressor spools. GE also updated 

how to calculate the life consumption of 

compressor spools and of life-limited 

rotating parts flown in Utility 

operations. This update resulted in 

generally reduced lives for compressor 

spools and all other life-limited parts 

used in Utility operations. GE published 

their updated life calculations for all 

life-limited parts in GE Alert Service 

Bulletin (ASB) No. CT58 S/B 72–A0162, 

Revision 16, dated January 7, 2015. 

Relevant Service Information Under 1 

CFR Part 51 

We reviewed GE ASB No. CT58 S/B 

72–A0162, Revision 16, dated January 7, 

2015. The service information describes 

procedures for calculating life limits for 

the affected life-limited rotating parts. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or see ADDRESSES for 

other ways to access this service 

information. 

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 reduce the 

life limits of certain compressor spools 

used in all operations and, through 

imposition of a new lifing methodology, 

increase the life consumption of all 

rotating parts used in Utility operations. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 60 engines installed 

on aircraft of U.S. registry. The average 

pro-rated cost of the life-limited rotating 

parts is $20,000. 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 $8,715,000. 

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: 

■ a. Removing airworthiness directives 

(AD) 2001–18–06; Amendment 39– 

12432 (66 FR 47575, September 13, 

2001); and AD 2008–22–16, 

Amendment 39–15712 (73 FR 63629, 

October 27, 2008), and 

■ b. Adding the following new AD: 

General Electric Company: Docket No. FAA– 

2008–0808; Directorate Identifier 2008– 

NE–18–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by June 30, 2015. 

(b) Affected ADs 

This AD replaces AD 2001–18–06, 

Amendment 39–12432 (66 FR 47575, 

September 13, 2001) and AD 2008–22–16, 

Amendment 39–15712 (73 FR 63629, October 

27, 2008. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CT58–100–2, CT58–110–1, 

CT58–110–2, CT58–140–1, and CT58–140–2 

turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by recalculation of 

life for parts installed on engines used in 

Utility operations, and a reduced life for 

compressor spools in all operations. We are 

issuing this AD to prevent failure of lifelimited rotating parts, uncontained part 

release, damage to the engine, and damage to 

the aircraft. 

(e) Compliance 

Do the actions required by this AD, unless 

already done. 

(1) Calculating Cyclic Life Consumption 

Re-calculate the cycles-since-new for all 

compressor spools, and for life-limited 

rotating parts other than compressor spools 

used in Utility operations. Use paragraphs 

3.A.(1) and 3.B.(1) in the Accomplishment 

Instructions of GE Alert Service Bulletin 

(ASB) No. CT58 S/B 72–A0162, Revision 16, 

dated January 7, 2015, to perform the 

calculations. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

24854 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Proposed Rules 

(2) Removal of Compressor Spools 

After the effective date of this AD, remove 

compressor spools, part numbers (P/Ns) 

5124T94G02, 6010T57G04, 6010T57G07, and 

6010T57G08 from service, before reaching 

the life limits specified in paragraph 4.(1), 

Appendix A, in GE ASB No. CT58 S/B 72– 

A0162, Revision 16, dated January 7, 2015, 

as re-calculated per paragraph (e)(1) in this 

AD. 

(3) Removal of Rotating Parts Used in Utility 

Operations Other Than Compressor Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part 

used in Utility operations other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD that exceeds its 

life limit, as re-calculated per paragraph 

(e)(1) in this AD. Use Tables I, II, III, and IV 

in paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE ASB No. 

CT58 S/B 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.(4), 

Appendix A, of this GE ASB, to determine 

when to remove these parts. 

(4) Removal of Rotating Parts Not Used in 

Utility Operations Other Than Compressor 

Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part not 

used in Utility operations other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD that exceeds its 

life limits. Use Tables I, II, III, and IV in 

paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE ASB No. 

CT58 S/B 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.(3), 

Appendix A of this GE ASB to determine 

when to remove these parts. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE–AD–AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Sanjana Murthy, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7750; fax: 781–238–7199; 

email: sanjana.murthy@faa.gov. 

(2) GE ASB No. CT58 S/B 72–A0162, 

Revision 16, dated January 7, 2015, can be 

obtained from GE using the contact 

information in paragraph (g)(3) of this 

proposed AD. 

(3) For service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, One Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(4) 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 

April 17, 2015. 

Thomas A. Boudreau, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09932 Filed 4–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1177; Directorate 

Identifier 2015–CE–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft LTD. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. Model PC–12/47 and PC– 

12/47E airplanes. This proposed 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 the aileron trim tab 

disconnecting above 10,000 feet 

altitude. We are issuing this proposed 

AD to require actions to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by June 15, 2015. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Pilatus 

Aircraft Ltd, Customer Support 

Manager, CH–6371 STANS, 

Switzerland; phone: +41 (0)41 619 33 

33; fax: +41 (0)41 619 73 11; email: 

SupportPC12@pilatus-aircraft.com; 

Internet: http://www.pilatusaircraft.com. You may review this 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1177; 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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@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–2015–1177; Directorate Identifier 

2015–CE–009–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://

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2015– 

0060, dated April 10, 2015 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS