Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 51965 

10 CFR part 61’’). The public comment 

periods for the proposed rule and draft 

guidance closed on July 24, 2015. The 

NRC has decided to reopen the public 

comment periods for the proposed rule 

and draft guidance until September 21, 

2015, to allow more time for members 

of the public to develop and submit 

their comments. 

Dated at Rockville, Maryland, this 19th day 

of August, 2015. 

For the Nuclear Regulatory Commission. 

Annette L. Vietti-Cook, 

Secretary of the Commission. 

[FR Doc. 2015–21169 Filed 8–26–15; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2984; Directorate 

Identifier 2015–NE–21–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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 all 

General Electric Company (GE) GEnx– 

1B54, –1B58, –1B64, –1B67, and –1B70 

turbofan engine models. This proposed 

AD was prompted by reports of two inflight shutdowns (IFSDs) caused by 

high-pressure turbine (HPT) rotor stage 

1 blade failure. This proposed AD 

would require inspection and 

conditional removal of affected HPT 

rotor stage 1 blades. We are proposing 

this AD to prevent failure of the HPT 

rotor stage 1 blades, 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 October 26, 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, 1 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 01803. 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– 

2984; 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: 

Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7120; fax: 781–238–7199; email: 

chris.mcguire@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this NPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–2984; Directorate Identifier 2015– 

NE–21–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

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 NPRM. 

Discussion 

We propose to adopt a new AD for all 

GE GEnx–1B54, –1B58, –1B64, –1B67, 

and –1B70 turbofan engine models. This 

proposed AD was prompted by reports 

of two IFSDs caused by HPT rotor stage 

1 blade failure. This proposed AD 

would require inspection and 

conditional removal of affected HPT 

rotor stage 1 blades. This condition, if 

not corrected, could result in failure of 

the HPT rotor stage 1 blades, which 

could lead to failure of one or more 

engines, loss of thrust control, and 

damage to the airplane. 

Related Service Information 

We reviewed GE GEnx–1B Service 

Bulletin (SB) No. 72–0267 R00, dated 

April 10, 2015. The SB describes 

procedures for borescope inspection 

(BSI) of the HPT rotor stage 1 blades. 

FAA’s Determination 

We are proposing this NPRM 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 NPRM would require initial and 

repetitive BSI and conditional removal 

of affected HPT rotor stage 1 blades. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 4 engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 2 hours 

per engine to comply with this proposed 

AD. The average labor rate is $85 per 

hour. Based on these figures, we 

estimate the total cost of this proposed 

AD to U.S. operators to be $680. 

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 


rmajette on DSK2VPTVN1PROD with PROPOSALS
51966 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 

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): 

General Electric Company: Docket No. FAA– 

2015–2984; Directorate Identifier 2015– 

NE–21–AD. 

(a) Comments Due Date 

We must receive comments by October 26, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) GEnx–1B54, –1B58, –1B64, 

–1B67, and –1B70 turbofan engines with 

high-pressure turbine (HPT) rotor stage 1 

blade, part number 2305M26P06, installed. 

(d) Unsafe Condition 

This AD was prompted by reports of two 

in-flight shutdowns caused by HPT rotor 

stage 1 blade failure. We are issuing this AD 

to prevent failure of the HPT rotor stage 1 

blades, which could lead to failure of one or 

more engines, loss of thrust control, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) After the effective date of this AD, 

perform an initial borescope inspection (BSI) 

of the convex surface of the HPT rotor stage 

1 blades for axial cracks from the platform to 

30% span, within 1,000 blade cycles since 

new or 25 cycles in service, whichever comes 

later, and disposition as follows: 

(i) If any axial crack with a length greater 

than or equal to 0.3 inch is found, or if any 

axial crack of any length turning in a radial 

direction is found, or if more than one axial 

crack of any length is found, remove the 

cracked blade before further flight. 

(ii) If an axial crack is found with a length 

greater than or equal to 0.2 inch and less than 

0.3 inch, remove the cracked blade within 10 

blade cycles in service. 

(iii) If an axial crack is found with a length 

greater than or equal to 0.1 inch and less than 

0.2 inch, inspect the cracked blade within 50 

blade cycles since last inspection (CSLI). 

(iv) If an axial crack is found with a length 

less than 0.1 inch, inspect the cracked blade 

within 100 blade CSLI. 

(v) If no cracks were found, perform a BSI 

of the blades within 125 blade CSLI. 

(2) Thereafter, perform a repetitive BSI of 

the convex surface of the HPT rotor stage 1 

blades for axial cracks from the platform to 

30% span within 125 blade CSLI and 

disposition as specified in (e)(1)(i) through 

(e)(1)(v), or remove the blades from service. 

(f) Definition 

For the purpose of this AD, a ‘‘blade cycle’’ 

is defined as the number of engine cycles that 

a set of rotor blades has accrued, regardless 

of the engine(s) in which they have operated. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to 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. 

(h) Related Information 

(1) For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7120; fax: 781–238– 

7199; email: chris.mcguire@faa.gov. 

(2) GE GEnx-1B Service Bulletin No. 72– 

0267 R00, dated April 10, 2015 can be 

obtained from GE using the contact 

information in paragraph (h)(3) of this 

proposed AD. 

(3) For service information identified in 

this proposed AD, contact General Electric 

Company, GE Aviation, Room 285, 1 

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 

August 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21120 Filed 8–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3620; Directorate 

Identifier 2015–CE–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited 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 certain 

Pacific Aerospace Limited Model 750XL 

airplanes that would supersede AD 

2014–20–13. 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 fatigue cracks on the fin 

forward pickup plates, which could 

cause it to fail. 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 October 13, 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 


rmajette on DSK2VPTVN1PROD with PROPOSALS