This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

22136 

Vol. 80, No. 76 

Tuesday, April 21, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0625; Directorate 

Identifier 2015–NE–09–AD] 

RIN 2120–AA64 

Airworthiness Directives; GE Aviation 

Czech s.r.o. Turboprop 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 

serial number GE Aviation Czech s.r.o. 

M601E–11, M601E–11A, and M601F 

turboprop engines with certain part 

number (P/N) gas generator turbine 

(GGT) blades, installed. This proposed 

AD was prompted by the determination 

that certain GGT blades are susceptible 

to blade failure. This proposed AD 

would require removing from service 

any affected engine with certain GGT 

blades installed. We are proposing this 

AD to prevent GGT blade failure, which 

could lead to engine failure and loss of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 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. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact GE Aviation 

Czech s.r.o., Beranovy ́ch 65, 199 02 

Praha 9—Letnˇ any, Czech Republic; 

phone: +420 222 538 111; fax: +420 222 

538 222. 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– 

0625; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The 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: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238– 

7199; email: robert.green@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–2015–0625; Directorate Identifier 

2015–NE–09–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 based on 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 with FAA 

personnel concerning 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 EASA AD 2015– 

0015, dated January 30, 2015 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

It has been demonstrated that non-shot 

peened Gas Generator Turbine (GGT) blades 

are susceptible to blade separation in the 

shank area due to their reduced fatigue life. 

This condition, if not corrected, could lead 

to an in-flight engine shutdown and, 

consequently, reduced control of the 

aeroplane. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0625. 

Related Service Information under 1 

CFR Part 51 

GE Aviation Czech s.r.o. has issued 

Alert Service Bulletin (ASB) No. 

M601E–11/30, dated December 23, 

2014, and ASB No. M601E–11/31, 

M601E–11A/18, M601F/28, dated 

December 23, 2014. The ASBs describe 

procedures for removal and replacement 

of GGT blades that are not shot peened. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the Czech 

Republic, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has 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 provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require removing 

from service any affected engine with 

GGT blades installed that are not shot 

peened. 

Costs of Compliance 

We estimate that this proposed AD 

affects one engine installed on an 

airplane of U.S. registry. We also 

estimate that it would take about 64 

hours per engine to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Required parts cost about 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 76 / Tuesday, April 21, 2015 / Proposed Rules 22137 

$28,765 per engine. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$34,205. 

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): 

GE Aviation Czech s.r.o. (Type Certificate 

previously held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.): 

Docket No. FAA–2015–0625; Directorate 

Identifier 2015–NE–09–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain serial number 

(S/N) GE Aviation Czech s.r.o. M601E–11, 

M601E–11A, and M601F turboprop engine 

models, with gas generator turbine (GGT) 

blade, part number (P/N) M601–3372.6 or 

M601–3372.51, installed, as follows: 

(1) Model M601E–11: S/Ns 862001, 

863008, 894018, 034005, 034006, 034007, 

034008, 041003, and 042002. 

(2) Model M601E–11A: S/Ns 042003, 

042004, 044001, 044002, and 961001. 

(3) Model M601F: S/Ns 024001, 002001, 

003001, 024001, 934001, 934002, 961001. 

(d) Reason 

This AD was prompted by the 

determination that certain GGT blades are 

susceptible to blade failure. These blades are 

identified as blade P/Ns M601–3372.6 and 

M601–3372.51, and are installed on an 

engine S/N identified in paragraph (c) of this 

AD. We are issuing this AD to prevent GGT 

blade failure, which could lead to engine 

failure and loss of the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. After the effective date of this AD: 

(1) Do not return to service any affected 

engine with GGT blade, P/N M601–3372.6 or 

M601–3372.51, installed, after 300 hours 

time in service or six months, whichever 

occurs first, after the effective date of this 

AD. 

(2) If the affected engines are subsequently 

disassembled or overhauled, the non-shot 

peened GGT blades, P/N M601–3372.6 or 

M601–3372.51, are not eligible for 

installation in any other engine after removal. 

(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 Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0015, dated January 

30, 2015, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2015–0625. 

(3) GE Aviation Czech s.r.o. Alert Service 

Bulletin (ASB) No. M601E–11/30, dated 

December 23, 2014, which is co-published as 

one document with M601D–1/31, M601Z/29, 

and M601T/24, and ASB No. M601E–11/31, 

M601E–11A/18, M601F/28, dated December 

23, 2014, which is co-published as one 

document with M601D–1/32, M601Z/30, 

M601E/61, M601T/25, M601FS/12, M601F– 

22/25, M601F–32/23, and M601E–21/28, are 

not incorporated by reference in this AD. The 

ASBs can be obtained from GE Aviation 

Czech s.r.o. using the contact information in 

paragraph (g)(4) of this proposed AD. 

(4) For service information identified in 

this proposed AD, contact GE Aviation Czech 

s.r.o., Beranovy ́ch 65, 199 02 Praha 9— 

Letnˇ any, Czech Republic; phone: +420 222 

538 111; fax: +420 222 538 222. 

(5) 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 7, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–09002 Filed 4–20–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0363; Directorate 

Identifier 2014–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Rolls-Royce plc (RR) RB211 Trent 

768–60, 772–60, and 772B–60 turbofan 

engines. The NPRM proposed to require 


tkelley on DSK3SPTVN1PROD with PROPOSALS