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

47581 

Vol. 78, No. 151 

Tuesday, August 6, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0575; Directorate 

Identifier 2013–NE–21–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft 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 

Turbomeca S.A. ASTAZOU XIV B and 

XIV H engines. This proposed AD was 

prompted by reports of cracks on the 

2nd-stage turbine disc. This proposed 

AD would require replacement of the 

2nd-stage turbine disc. We are 

proposing this AD to prevent disc 

cracking, uncontained 2nd-stage turbine 

blade release, damage to the engine, and 

damage to the helicopter. 

DATES: We must receive comments on 

this proposed AD by October 7, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• 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 Turbomeca, 

S.A., 40220 Tarnos, France; phone: 33 

(0)5 59 74 40 00; telex: 570 042; fax: 33 

(0)5 59 74 45 15. 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 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 street address for 

the Docket Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: frederick.zink@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–2013–0575; Directorate Identifier 

2013–NE–21–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. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0111R1, 

dated June 3, 2013 (referred to 

hereinafter as ‘‘the MCAI), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Some cracks have been reported on the 

second stage turbine disc of ASTAZOU XIV 

engines inducted into a Repair Centre. These 

cracks are located in the serrations of the 

disc. The results of the technical 

investigation concluded that the cracks were 

present on non-shot peened second stage 

turbine discs (discs on which AB 138 

modification was not incorporated), and on 

second stage turbine discs that were shot 

peened during their service life (discs on 

which AB 138 modification was incorporated 

after initial service use without shot 

peening). Until now, no crack has been 

reported on second stage turbine discs shot 

peened since new, these discs accounting for 

more than half of all ASTAZOU XIV flight 

hours. It was not possible to clearly identify 

what caused the cracks. 

This condition, if not corrected, could lead 

to some events of disc serrations rupture, 

possibly resulting in uncontained second 

stage turbine blade release with consequent 

damage to, and reduced control of, the 

helicopter. 

You may obtain further information by 

examining the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

These engines have been approved by 

the aviation authority of France, and are 

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 

engines of the same type design. This 

proposed AD would require 

replacement of the 2nd-stage turbine 

disc. 

Costs of Compliance 

We estimate that this proposed AD 

affects 6 products of U.S. registry. We 


tkelley on DSK3SPTVN1PROD with PROPOSALS
47582 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Proposed Rules 

also estimate that it would take about 5 

hours per product to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Required parts cost about 

$6,560 per product. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$41,910. Our cost estimate is exclusive 

of possible warranty coverage. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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): 

Turbomeca S.A.: Docket No. FAA–2013– 

0575; Directorate Identifier 2013–NE–21–AD. 

(a) Comments Due Date 

We must receive comments by October 7, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

ASTAZOU XIV B and XIV H engines. 

(d) Reason 

This AD was prompted by reports of cracks 

on the 2nd-stage turbine disc. We are issuing 

this AD to prevent disc cracking, 

uncontained 2nd-stage turbine blade release, 

damage to the engine, and damage to the 

helicopter. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) For ASTAZOU XIV B engines that have 

not incorporated AB 138 modification 

remove 2nd-stage turbine disk part number 

(P/N) 0265260270 as follows: 

(i) For engines with 1,800 or more engine 

cycles since new (CSN) or since last overhaul 

(CSLO), remove 2nd-stage turbine disk P/N 

0265260270 within 10 operating hours after 

the effective date of this AD. 

(ii) For engines with less than 1,800 CSN 

or CSLO, remove 2nd-stage turbine disk P/N 

0265260270 within 300 operating hours after 

the effective date of this AD or before 1800 

CSN or CSLO, whichever comes first. 

(2) For ASTAZOU XIV B engines that have 

incorporated AB 138 modification, remove 

2nd-stage turbine disk P/N 0283270200 with 

P/N 0265260270 written or scratched onto 

the disk within 1,800 CSN or CSLO, or 

within 10 operating hours after the effective 

date of this AD, whichever occurs later. 

(3) For ASTAZOU XIV H engines, remove 

2nd-stage turbine disk P/N 0265260270 

within 300 operating hours after the effective 

date of this AD. 

(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. 

(h) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to European Aviation Safety 

Agency Airworthiness Directive 2013– 

0111R1, dated June 3, 2013, for more 

information. You may examine the AD on the 

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

(3) Turbomeca S.A. Alert Mandatory 

Service Bulletin (MSB) No. A283 72 0809, 

Version A, dated May 16, 2013, and 

Turbomeca S.A. Alert MSB No. A283 72 

0808, Version A, dated May 16, 2013, which 

are not incorporated by reference in this AD, 

can be obtained from Turbomeca S.A. using 

the contact information in paragraph (h)(4) of 

this AD. 

(4) For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

telex: 570 042; fax: 33 (0)5 59 74 45 15. 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 

July 19, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18908 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Fish and Wildlife Service 

50 CFR Part 17 

[Docket No. FWS–R2–ES–2013–0083; 

4500030113] 

RIN 1018–AY55 

Endangered and Threatened Wildlife 

and Plants; Endangered Species 

Status for the Sharpnose Shiner and 

Smalleye Shiner 

AGENCY: Fish and Wildlife Service, 

Interior. 

ACTION: Proposed rule. 

SUMMARY: We, the U.S. Fish and 

Wildlife Service (Service), propose to 

list the sharpnose shiner (Notropis 

oxyrhynchus) and smalleye shiner (N. 

buccula), two fish species from Texas, 

as endangered species under the 


tkelley on DSK3SPTVN1PROD with PROPOSALS