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: 

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Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Proposed Rules 24855 

During a continued airworthiness review, a 

potential unsafe condition was identified that 

could result from a disconnected aileron trim 

tab occurring above an altitude of 10.000 feet. 

This condition, if not corrected, could lead, 

in case of a disconnection of an aileron trim 

tab, to undamped aeroplane vibrations, 

potentially resulting in structural failure. 

To address this potential unsafe condition, 

Pilatus Aircraft Ltd. issued SB No. 27–021 to 

provide instructions for replacement of the 

aileron tab counter balance weight. 

For the reason described above, this AD 

requires replacement of the aileron tab 

counter balance weight with a new, slightly 

heavier, aileron tab counter balance weight. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–1177. 

Related Service Information Under 1 

CFR Part 51 

Pilatus Aircraft Ltd. has issued 

PILATUS PC–12 Service Bulletin No: 

27–021, dated January 20, 2015. The 

PILATUS PC–12 Service Bulletin No: 

27–021, dated January 20, 2015, 

describes procedures to replace the 

aileron tab counter balance weight. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this NPRM. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 303 products of U.S. registry. 

We also estimate that it would take 

about 5.5 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $1,000 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $444,652.50, or 

$1,467.50 per product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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, 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 AD: 

Pilatus Aircraft Ltd.: Docket No. FAA–2015– 

1177; Directorate Identifier 2015–CE– 

009–AD. 

(a) Comments Due Date 

We must receive comments by June 15, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Pilatus 

Aircraft Ltd. model and serial number 

airplanes, certificated in any category. 

(1) Model PC–12/47, manufacturer serial 

numbers (MSNs) 684 through MSN 888; and 

(2) Model PC–12/47E, MSNs 545, and 1001 

through 1520. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by 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 AD to prevent 

a disconnected aileron trim tab, which could 

lead to undamped airplane vibrations, 

potentially resulting in structural failure. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) For airplanes equipped with aileron 

trim tab assembly, part number (P/N) 

527.15.12.037 or 527.15.12.038; or aileron 

assembly, P/N 557.05.12.015, 557.05.12.016, 

557.05.12.017, or 557.05.12.018, within 12 

months after the effective date of this AD, 

replace the aileron tab counter balance 

weight and re-identify the aileron trim tab 

assembly following the instructions of Pilatus 

PC–12 Service Bulletin No: 27–021, dated 

January 20, 2015. 

(2) For an airplane that on the effective 

date of this AD has an aileron trim tab 

assembly, P/N 27.15.12.037 or 527.15.12.038, 

installed: After modification of that airplane 

as required by paragraph (f)(1) of this AD, do 

not install another aileron trim tab assembly 

with P/N 527.15.12.037 or 527.15.12.038. 

(3) For an airplane that on the effective 

date of this AD does not have an aileron trim 

tab assembly, P/N 27.15.12.037 or 

527.15.12.038, installed: After the effective 

date of this AD, do not install an aileron trim 

tab assembly with P/N 527.15.12.037 or 

527.15.12.038. 

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24856 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Proposed Rules 

(4) After the effective date of this AD, you 

are allowed to install on an airplane an 

aileron assembly, having a P/N 

557.05.12.015, 557.05.12.016, 557.05.12.017, 

or 557.05.12.018, provided that an aileron 

trim tab assembly, P/N 527.15.12.037 or 

527.15.12.038 is not installed on the airplane. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: 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. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2015–0060, dated 

April 10, 2015, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–1177. 

For service information related to this 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.pilatus-aircraft.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. 

Issued in Kansas City, Missouri, on April 

23, 2015. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–10073 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–2015–0277; Directorate 

Identifier 2015–NE–05–AD] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International S.A. 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 

CFM International S.A. (CFM) CFM56– 

7B series turbofan engines. This 

proposed AD was prompted by reports 

of uncommanded in-flight shutdowns 

(IFSDs) on CFM CFM56–7B engines 

following rupture of the 73-tooth 

gearshaft located in the engine accessory 

gearbox (AGB). This proposed AD 

would require magnetic chip detector 

(MCD) inspection of the affected 

gearshafts until removal. We are 

proposing this AD to prevent failure of 

certain engine AGB gearshafts, which 

could lead to failure of one or more 

engines, loss of thrust control, and 

damage to the airplane. 

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 AD, contact CFM International Inc., 

Aviation Operations Center, 1 Neumann 

Way, M/D Room 285, Cincinnati, OH 

45125; phone: 877–432–3272; fax: 877– 

432–3329; 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–2015– 

0277; 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: Kyle 

Gustafson, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7183; fax: 781–238– 

7199; email: kyle.gustafson@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– 

2015–0277; Directorate Identifier 2015– 

NE–05–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 have received reports of 

uncommanded IFSDs on CFM CFM56– 

7B engines following rupture of the 73- 

tooth gearshaft located in the engine 

AGB. CFM has identified an affected 

population of 73-tooth gearshafts that 

show premature wear on the teeth due 

to inadequate shot peening. In the 

process of its investigation, CFM 

identified an additional population of 

41-tooth gearshafts that is subject to the 

same premature wear. The affected 

population of 73-tooth and 41-tooth 

gearshafts exhibit a surface finish that 

leads to loss in oil film effectiveness, 

causing micro-pitting which eventually 

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