Federal Register / Vol. 78, No. 228 / Tuesday, November 26, 2013 / Rules and Regulations 70487 

Delaying the implementation of these 

provisions, which make a sounder, more 

stable program, would be contrary to the 

public interest. 

If FCIC is required to delay the 

implementation of this rule until 30 

days after the date of publication, the 

provisions of this rule could not be 

implemented until the 2015 crop year 

for those crops having a contract change 

date prior to the effective date of this 

publication. 

For the reasons stated above, good 

cause exists to make these policy 

changes effective upon publication in 

the Federal Register. 

List of Subjects in 7 CFR Part 457 

Crop insurance, Extra long staple 

cotton, Reporting and recordkeeping 

requirements. 

Final Rule 

Accordingly, as set forth in the 

preamble, the Federal Crop Insurance 

Corporation amends 7 CFR part 457 

effective for the 2014 and succeeding 

crop years as follows: 

PART 457—COMMON CROP 

INSURANCE REGULATIONS 

■ 1. The authority citation for 7 CFR 

part 457 continues to read as follows: 

Authority: 7 U.S.C. 1506(1), 1506(o). 

■ 2. Amend § 457.105 as follows: 

■ a. Amend the introductory text by 

removing ‘‘2012’’ and adding ‘‘2014’’ in 

its place; 

■ b. Revise section 9; and 

■ c. Revise section 11. 

The revisions read as follows: 

§ 457.105 Extra long staple cotton crop 

insurance provisions. 

* * * * * 

9. Duties in the Event of Damage or 

Loss. 

(a) In addition to your duties under 

section 14 of the Basic Provisions, in the 

event of damage or loss: 

(1) You must give us notice if you 

intend to replant any acreage originally 

planted to ELS cotton to AUP cotton. 

(2) The cotton stalks must remain 

intact for our inspection. The stalks 

must not be destroyed, and required 

samples must not be harvested, until the 

earlier of our inspection or 15 days after 

harvest of the balance of the unit is 

completed and written notice of 

probable loss is given to us. 

(b) Representative samples are 

required in accordance with section 14 

of the Basic Provisions. 

* * * * * 

11. Late Planting. 

(a) A late planting period is applicable 

to ELS cotton, if allowed by the Special 

Provisions. 

(b) If the Special Provisions do not 

provide for a late planting period, any 

ELS cotton that is planted after the final 

planting date will not be insured unless 

you were prevented from planting it by 

the final planting date. Such acreage 

will be insurable, and the production 

guarantee and premium for the acreage 

will be determined in accordance with 

section 16 of the Basic Provisions. 

* * * * * 

Signed in Washington, DC, on November 

21, 2013. 

Brandon Willis, 

Manager, Federal Crop Insurance 

Corporation. 

[FR Doc. 2013–28319 Filed 11–25–13; 8:45 am] 

BILLING CODE 3410–08–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0750; Directorate 

Identifier 2013–NE–25–AD; Amendment 39– 

17672; AD 2013–23–17] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for RollsRoyce plc (RR) RB211–535E4–37, 

–535E4–B–37, –535E4–C–37, 

RB211Trent 768–60, 772–60, and 772B– 

60 turbofan engines. This AD requires 

removal of certain high-pressure (HP) 

and intermediate-pressure (IP) turbine 

discs before their accumulated cyclic 

lives have reached the revised limits. 

This AD was prompted by a report of an 

HP disc contaminated with a steel 

inclusion. We are issuing this AD to 

prevent failure of the HP or IP turbine 

disc, uncontained engine failure, and 

damage to the airplane. 

DATES: This AD becomes effective 

December 11, 2013. 

We must receive comments on this 

AD by January 10, 2014. 

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 and follow 

the instructions for sending your 

comments electronically. 

• Mail: 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 AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, DE24 8BJ, UK; phone: 44–0– 

1332–242424; fax: 44–0–1332–249936; 

email: http://www.rolls-royce.com/

contact/civil_team.jsp. 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; 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 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: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2013– 

0155, dated July 18, 2013 (referred to 

herein after as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a recent inspection of a high 

pressure (HP) turbine disc forged by a 

specific supplier, the disc was found to be 

contaminated with a steel inclusion, due to 

an inadequate cleaning procedure in the 

operation of the melt furnace, following a 

steel melt. Analysis of melt and inspection 

data concluded that all discs manufactured 

from the batch of material in which this steel 

inclusion was found, had a significant risk of 

containing steel inclusions. Rolls-Royce has 

carried out an analysis of the effect of the 


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70488 Federal Register / Vol. 78, No. 228 / Tuesday, November 26, 2013 / Rules and Regulations 

steel inclusions on the Declared Safe Cyclic 

Lives (DSCL) of the affected HP and 

intermediate pressure (IP) turbine discs. This 

analysis concluded that the currently 

published DSCL cannot be supported for 

several discs containing the subject 

inclusions. 

This condition, if not corrected, could lead 

to an uncontained HP or IP turbine disc 

failure, possibly resulting in damage to, and 

reduced control of, the aeroplane. 

For the reasons described above, this AD 

requires removal from service of certain HP 

and IP turbine discs before their accumulated 

cyclic lives have reached the revised limits. 

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 it in Docket No. FAA– 

2013–0750. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of the United 

Kingdom 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 issuing 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. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2013–0750; 

Directorate Identifier 2013–NE–25–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 with FAA 

personnel concerning this 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). 

Costs of Compliance 

We estimate that this AD will affect 

20 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 0 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Required parts will cost 

about $4,000 per engine. Based on these 

figures, we estimate the total cost of this 

AD to U.S. operators is $80,000. 

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 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 this AD: 

(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 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. 

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): 

2013–23–17 Rolls-Royce plc: Amendment 

39–17672; Docket No. FAA–2013–0750; 

Directorate Identifier 2013–NE–25–AD. 

(a) Effective Date 

This AD is effective December 11, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–535E4–37, –535E4–B–37, –535E4–C– 

37, RB211 Trent 768–60, 772–60, and 772B– 

60 turbofan engines with turbine disc part 

numbers (P/Ns) and serial numbers (S/Ns) 

listed in Table 1 to paragraph (c) of this AD. 


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Federal Register / Vol. 78, No. 228 / Tuesday, November 26, 2013 / Rules and Regulations 70489 

TABLE 1 TO PARAGRAPH (C)—NEW REDUCED CYCLIC LIFE LIMITS FOR HIGH-PRESSURE (HP)/INTERMEDIATE-PRESSURE

(IP) TURBINE DISCS

Engine P/Ns S/Ns New reduced cyclic life 

limit 

RB211–535E4–37,–535E4–B–37, –535E4–C–37 .......... UL39767 ............................ LDRCZ19900 ..................... 11,400 flight cycles (FCs). 

UL39767 ............................ LDRCZ19903.

UL39767 ............................ LDRCZ19904.

RB211 Trent 768–60, 772–60, and 772B–60 ................. FK26893 ............................ LDRCZ19901 ..................... 8,687 FCs. 

FK26893 ............................ LDRCZ20081.

FK26893 ............................ LDRCZ20082.

FK26893 ............................ LDRCZ20084.

FK26893 ............................ LDRCZ20088.

FK26893 ............................ LDRCZ20089.

FK26893 ............................ LDRCZ20090.

FK26893 ............................ LDRCZ20093.

FK26893 ............................ LDRCZ20094.

FK26893 ............................ LDRCZ20097.

FK26893 ............................ LDRCZ20099.

FK26893 ............................ LDRCZ20100.

FK20795 or FW53118 ....... LDREB12176 ..................... 9,270 FCs. 

FK20795 or FW53118 ....... LDREB12177.

FK20795 or FW53118 ....... LDREB12178.

FK20795 or FW53118 ....... LDREB12179.

FK20795 or FW53118 ....... LDREB12180.

(d) Reason 

This AD was prompted by a report of an 

HP disc contaminated with a steel inclusion. 

We are issuing this AD to prevent failure of 

the HP or IP turbine disc, uncontained engine 

failure, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Remove from service, within 30 days, 

any HP or IP disc identified in Table 1 to 

paragraph (c) of this AD that has exceeded 

the new cyclic life limit, or before the disc 

accumulates flight cycles that equal the new 

reduced cyclic life limit listed in Table 1 to 

paragraph (c) of this AD, whichever is later. 

(2) Do not approve for return to service any 

engine with any installed HP or IP turbine 

disc listed in Table 1 to paragraph (c) of this 

AD, if the disc exceeds the new reduced 

cyclic life limit listed in Table 1 to paragraph 

(c) of this AD. 

(f) 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. 

(g) 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 MCAI European Aviation 

Safety Agency AD 2012–0155, dated July 18, 

2013. 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–2013–0750. 

(3) Rolls-Royce plc, Alert NonModification Service Bulletin No. RB.211– 

72–AH215, dated December 6, 2012 and 

RB.211–72–AH152, Revision 1, dated July 3, 

2013, which are not incorporated by 

reference in this AD, can be obtained from 

RR using the contact information in 

paragraph (g)(4) of this AD. 

(4) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, DE24 

8BJ, UK; phone: 44–0–1332–242424; fax: 44– 

0–1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp. 

(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. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

November 8, 2013. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–28221 Filed 11–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0880; Directorate 

Identifier 2013–NE–28–AD; Amendment 39– 

17667; AD 2013–23–12] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211 Trent 553– 

61, 553A2–61, 556–61, 556A2–61, 

556B–61, 556B2–61, 560–61, and 

560A2–61 turbofan engines. This AD 

requires replacement or repair of the 

low-pressure (LP) compressor fan blade 

set before reaching a specified number 

of flight cycles since new (FCSN) or 

flight cycles since last leading edge 

profile blade repair (FCSLR). This AD 

was prompted by reports of erosion of 

the leading edge profile of the LP 

compressor blade set contributing to fan 

blade flutter. We are issuing this AD to 

prevent failure of the LP compressor 

blades, which could lead to an 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective 

December 11, 2013. 

We must receive comments on this 

AD by January 10, 2014. 


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