Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 35747 

of the Interior acknowledges to exist as 

an Indian tribe pursuant to the Federally 

Recognized Indian Tribe List Act of 

1994. Tribal participation is voluntary. 

Tribes may express interest in 

participating in the advance 

notifications and may discontinue their 

participation at any time. Currently, 27 

Tribes have expressed interest in 

receiving the advance notifications. 

Tribes meeting the criteria may receive 

advance notifications after certifying 

that the Safeguards Information 

associated with the shipments of these 

materials will be adequately protected 

by complying with the requirements in 

10 CFR 73.21 and 73.22. 

After the NRC receives this 

certification and the contact information 

for the Tribal official or Tribal official’s 

designee, the NRC will add the Tribe to 

the list of advance notification contacts 

and the Tribal reservation information 

to the interactive map of Tribal 

boundaries at http://www.nrc.gov/ 

about-nrc/state-tribal/tribal-advancenotification.html. Current contact 

information can also be accessed 

throughout the year at http://nrcstp.ornl.gov/special/designee.pdf. The 

list is published annually in the Federal 

Register on or about June 30 to reflect 

any changes in information. Licensees 

should check these sites to determine 

whether they need to provide advance 

notification when they have any 

shipments meeting the criteria in 10 

CFR 71.97 or 73.37 that will pass within 

or across a participating Tribe’s 

reservation. 

Dated at Rockville, Maryland, this 10th day 

of June 2013. 

For the U.S. Nuclear Regulatory 

Commission. 

Melanie A. Galloway, 

Acting Director, Division of 

Intergovernmental Liaison and Rulemaking, 

Office of Federal and State Materials and 

Environmental Management Programs. 

[FR Doc. 2013–14159 Filed 6–13–13; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 23 

[Docket No. CE305; Special Conditions No. 

23–245–SC] 

Special Conditions: Cirrus Design 

Corporation, Model SF50; Fire 

Extinguishing for Upper Aft Fuselage 

Mounted Engine; Withdrawal 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; 

withdrawal. 

SUMMARY: The FAA is withdrawing a 

previously published notice granting 

special conditions for the Cirrus Design 

Corporation model SF50 airplane. We 

are withdrawing Special Condition No. 

23–245–SC through mutual agreement 

with Cirrus Design Corporation. 

DATES: This special condition published 

on April 20, 2010 at 75 FR 20518 is 

withdrawn, effective June 14, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Leslie B. Taylor, Federal Aviation 

Administration, Small Airplane 

Directorate, Aircraft Certification 

Service, 901 Locust, Room 301, Kansas 

City, MO 64106; telephone (816) 329– 

4134; facsimile (816) 329–4090, email 

leslie.b.taylor@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On April 20, 2010, the FAA published 

Special Condition No. 23–245–SC for 

the Cirrus Design Corporation new 

model SF50. The model SF50 is a 7-seat 

(5 adults and 2 children), pressurized, 

retractable gear, carbon composite, 

airplane with one turbofan engine 

mounted partially in the upper aft 

fuselage. 

The single turbofan engine is 

mounted on the upper aft fuselage, not 

in the pilot’s line of site. Upper aft 

fuselage mounted engine installations, 

along with the need to protect such 

installed engines from fires, were not 

envisioned in the development of the 

part 23 normal category regulations. 

The model SF50 certification project 

was granted an extension on September 

19, 2011. Amendment 23–62 (76 FR 

75736), published December 2, 2011, 

incorporated Special Condition No. 23– 

245–SC. On December 11, 2012, Cirrus 

Design Corporation elected to adjust the 

model SF50 certification basis to 14 CFR 

part 23, Amendment 62. 

Reason for Withdrawal 

The FAA is withdrawing Special 

Condition No. 23–245–SC because 

Cirrus elected to revise the model SF50 

certification basis to Amendment 23–62. 

The authority citation for this Special 

Condition withdrawal is 49 U.S.C. 

106(g), 40113 and 44701; 14 CFR 21.16 

and 21.17; and 14 CFR 11.38 and 11.19. 

Conclusion 

Withdrawal of this special condition 

does not preclude the FAA from issuing 

another notice on the subject matter in 

the future or committing the agency to 

any future course of action. 

Issued in Kansas City, Missouri on June 5, 

2013. 

Earl Lawrence, 

Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–14151 Filed 6–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1329; Directorate 

Identifier 2012–NE–46–AD; Amendment 

39–17479; AD 2013–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Engine Alliance GP7270 and GP7277 

turbofan engines. This AD was 

prompted by damage to the highpressure compressor (HPC) stage 7–9 

spool caused by failure of the baffle 

plate feature on affected HPC stage 6 

disks. This AD requires initial and 

repetitive borescope inspections of the 

baffle plate feature and removal from 

service of the HPC stage 6 disk if the 

plate is missing material. This AD also 

requires mandatory removal from 

service of these HPC stage 6 disks at the 

next HPC module exposure. We are 

issuing this AD to prevent failure of the 

HPC stage 7–9 spool, uncontained 

engine failure, and damage to the 

airplane. 

DATES: This AD is effective July 19, 

2013. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Martin Adler, Aerospace Engineer, 

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35748 Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7157; fax: 781–238–7199; email: 

martin.adler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on February 7, 2013 (78 FR 

9003). That NPRM proposed to require 

initial and repetitive borescope 

inspections of the HPC stage 6 disk 

baffle plate feature and removal from 

service of any HPC stage 6 disk, part 

number (P/N) 382–100–505–0, before 

further flight if the feature is missing 

any material. That NPRM also proposed 

to require mandatory removal from 

service of these HPC stage 6 disks at the 

next HPC module exposure, but no later 

than accumulating 6,800 cycles-sincenew on the disk. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Allow Continue-In-Service 

Limits for the Baffle Plate Feature 

Engine Alliance and Korean Airlines 

requested that we allow continue-inservice limits for the baffle plate feature. 

Engine Alliance stated that they have 

performed extensive analysis showing 

that the risk in doing so, is minimal. 

Both commenters point out the potential 

inconveniences to the flying public, and 

the potential economical and logistical 

impacts on air carriers. 

We agree. We changed paragraph 

(f)(4) of the AD to state to remove the 

HPC stage 6 disk within 50 additional 

cycles-in-service, if the baffle plate 

feature is found cracked or missing 

material. 

Request To Remove References to 

Damage Causing Cracks to the HPC 

7–9 Spool 

Engine Alliance requested that we 

remove the reference to damage causing 

cracks to the HPC 7–9 spool, in the 

Discussion paragraph of the NPRM (78 

FR 9003, February 7, 2013). Engine 

Alliance stated that there has been no 

cracking of the spools related to the 

baffle plate feature problem, to-date, but 

there is potential for cracking, and they 

suggested that we state there is potential 

for cracking. 

We partially agree. We agree that 

there has been no cracking yet. We do 

not agree with stating there is potential 

for cracking, because we wouldn’t be 

issuing an AD if cracking couldn’t 

happen. We did not change the AD. 

Request To Include Engine Alliance 

Service Bulletins (SBs) 

Engine Alliance and Korean Airlines 

requested that we include Engine 

Alliance SBs No.s EAGP7–72–237 and 

EAGP7–72–240 as terminating action for 

this AD. The SBs introduce the new 

design of the HPC stage 6 disk either by 

repair or a new part, which eliminates 

the unsafe condition. 

We partially agree. We agree that a 

repaired HPC stage 6 disk should be 

allowed to be installed as a terminating 

action for the AD, as well as installing 

the new P/N HPC stage 6 disk. We 

changed paragraph (g) in the AD from 

‘‘At next HPC module exposure, but not 

to exceed 6,800 CSN on the HPC stage 

6 disk, remove the HPC stage 6 disk, 

P/N 382–100–505–0, from service’’ to 

allow use of the repaired part. Paragraph 

(g) of this AD now reads: ‘‘At next HPC 

module exposure, but not to exceed 

6,800 CSN on the HPC stage 6 disk, 

remove the HPC stage 6 disk, P/N 382– 

100–505–0, from the engine.’’ We do not 

agree with stipulating the SBs as 

terminating actions because we do not 

want to prevent future configurations 

from being terminating action. However, 

we listed those SBs under Related 

Information in the AD. 

Request To Define When Undamaged 

Part Replacement Is Required 

Engine Alliance requested that we 

define when undamaged part 

replacement is required, from module 

level to rotor assembly exposure. They 

stated that disk removal involves a full 

teardown of the compressor module, 

which can only be performed at 

specialized repair facilities. There is 

maintenance that can be performed at 

other facilities not qualified for a full 

teardown, which could involve removal 

and installation of a complete 

compressor module. 

We agree. We changed paragraph (i) 

in the AD from: ‘‘For the purpose of this 

AD, HPC module exposure is defined as 

separation of the flanges between the 

compressor case and the combustion 

diffuser case’’ to: ‘‘For the purpose of 

this AD, HPC module exposure is 

defined as disassembly of the 

compressor to where the HPC rotor 

assembly is removed and accessible.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 9003, 

February 7, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 9003, 

February 7, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

no engines installed on airplanes of U.S. 

registry, and the cost to U.S. operators 

to be $0. 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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 

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Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 35749 

(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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2013–12–02 Engine Alliance: Amendment 

39–17479; Docket No. FAA–2012–1329; 

Directorate Identifier 2012–NE–46–AD. 

(a) Effective Date 

This AD is effective July 19, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Engine Alliance 

GP7270 and GP7277 turbofan engines with a 

high-pressure compressor (HPC) stage 6 disk, 

part number (P/N) 382–100–505–0, installed. 

(d) Unsafe Condition 

This AD was prompted by damage to the 

HPC stage 7–9 spool caused by failure of the 

baffle plate feature on affected HPC stage 6 

disks. We are issuing this AD to prevent 

failure of the HPC stage 7–9 spool, 

uncontained engine failure, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Borescope Inspections 

(1) For HPC stage 6 disks with fewer than 

1,000 cycles- since- new (CSN) on the 

effective date of this AD, initially borescope 

inspect the baffle plate feature on the disk 

(360 degrees) before accumulating 1,500 

CSN. 

(2) For HPC stage 6 disks with 1,000 CSN 

or more on the effective date of this AD, 

initially borescope inspect the baffle plate 

feature on the disk (360 degrees) within the 

next 500 cycles-in-service (CIS). 

(3) Thereafter, repetitively borescope 

inspect the baffle plate feature on the disk 

(360 degrees) within every 500 CIS. 

(4) Remove the HPC stage 6 disk within 50 

additional CIS, if the baffle plate feature is 

found cracked or missing material. 

(g) Mandatory Removal From Service of 

Affected HPC Stage 6 Disks 

At next HPC module exposure, but not to 

exceed 6,800 CSN on the HPC stage 6 disk, 

remove the HPC stage 6 disk, P/N 382–100– 

505–0, from the engine. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install any HPC stage 6 disk, P/N 382–100– 

505–0, into any HPC module. 

(i) Definition 

For the purpose of this AD, HPC module 

exposure is defined as disassembly of the 

compressor to where the HPC rotor assembly 

is removed and accessible. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Martin Adler, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7157; fax: 781–238– 

7199; email: martin.adler@faa.gov. 

(2) Engine Alliance Service Bulletin Nos. 

EAGP7–72–236, EAGP7–72–237, and 

EAGP7–72–240, pertain to the subject of this 

AD. 

(3) For service information identified in 

this AD, contact Engine Alliance, 411 Silver 

Lane, East Hartford, CT 06118, phone: 800– 

565–0140; Web site: 

https://www.engineallianceportal.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. 

(l) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

June 7, 2013. 

Robert J. Ganley, 

Acting Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–14040 Filed 6–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1221; Directorate 

Identifier 2012–NM–151–AD; Amendment 

39–17474; AD 2013–11–14] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300 series airplanes. This AD was 

prompted by reports of hydraulic fluid 

contamination (including contamination 

caused by hydraulic fluid in its liquid, 

vapor, and/or solid (coked) form) found 

in the strut forward dry bay. This AD 

requires repetitive general visual 

inspections of the strut forward dry bay 

for the presence of hydraulic fluid, and 

related investigative and corrective 

actions (including checking drain lines 

for blockage due to hydraulic fluid 

coking, and cleaning or replacing drain 

lines to allow drainage) if necessary. We 

are issuing this AD to detect and correct 

hydraulic fluid contamination of the 

strut forward dry bay, which could 

result in hydrogen embrittlement of the 

titanium forward engine mount 

bulkhead fittings, and consequent 

inability of the fittings to carry engine 

loads, resulting in engine separation. 

Hydraulic embrittlement also could 

cause a through-crack formation across 

the fittings through which an engine fire 

could breach into the strut, resulting in 

an uncontained strut fire. 

DATES: This AD is effective July 19, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 19, 2013. 

ADDRESSES: 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; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the 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. 

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