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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70490 Federal Register / Vol. 78, No. 228 / Tuesday, November 26, 2013 / Rules and Regulations 

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: 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 

Airworthiness Directive 2013–0214, 

dated September 16, 2013 (referred to 

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

an unsafe condition for the specified 

products. The MCAI states: 

Erosion of the leading edge profile of Trent 

500 engines’ low pressure (LP) compressor 

blades is proven to contribute to fan flutter, 

a risk that is mitigated by regular restoration 

of the leading edge of these blades. Recently, 

Rolls-Royce has conducted a review 

regarding the in-service restoration of the 

leading edge profile of LP compressor blades. 

The results of this review concluded that not 

all LP compressor blades have been restored 

as intended. 

This condition, if not corrected, could lead 

to fan flutter, LP compressor blade cracking 

and uncontained LP compressor blade 

failures, possibly resulting in damage to, and 

reduced control of, the aeroplane. 

For the reasons described above, this AD 

requires initial and repetitive leading edge 

restoration of the LP compressor blades. 

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– 

2013–0880. 

Relevant Service Information 

RR has issued Alert Non-Modification 

Service Bulletin No. RB.211–72–AH149, 

Revision 1, dated May 3, 2013 and 

RB.211–72–H464, dated August 28, 

2013. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 

No domestic operators use this 

product. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less 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–2013–0880; 

Directorate Identifier 2013–NE–28–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 would affect 

0 engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 6 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Based on these figures, we 

estimate the total cost of this AD to U.S. 

operators is $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 

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, 


rmajette on DSK2TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 228 / Tuesday, November 26, 2013 / Rules and Regulations 70491 

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): 

2013–23–12 Rolls-Royce plc: Amendment 

39–17667; Docket No. FAA–2013–0880; 

Directorate Identifier 2013–NE–28–AD. 

(a) Effective Date 

This AD is effective December 11, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to 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. 

(d) Reason 

This AD was prompted by reports of 

erosion of the leading edge profile of the lowpressure (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. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) If on the effective date of this AD, the 

LP compressor fan blades: 

(i) Have less that 3,750 flight cycles since 

new (FCSN) or flight cycles since last leading 

edge profile blade repair (FCSLR), replace or 

repair the LP compressor fan blade set before 

accumulating 4,000 FCSN or FCSLR; 

(ii) Have 3,750 or more FCSN or FCSLR, 

but less than 4,400 FCSN or FCSLR, replace 

or repair the LP compressor fan blade set 

within 250 flight cycles (FC), but not later 

than 4,500 FCSN or FCSLR; 

(iii) Have 4,400 FCSN or FCSLR or more, 

replace or repair the LP compressor fan blade 

set within 100 FC; or 

(iv) Have FCSN or FCSLR that are 

unknown, replace or repair the LP 

compressor fan blade set within 100 FC. 

(2) Thereafter, replace or repair the LP 

compressor fan blade set within every 4,000 

FCSN or FCSLR. 

(f) Definition 

LP compressor fan blades eligible for 

installation are: 

(1) LP compressor fan blades with less than 

4,000 FCSN; or 

(2) LP compressor fan blades with less than 

4,000 FCSLR, if LP compressor fan blades 

were repaired using RR Alert NonModification Service Bulletin No. RB.211– 

72–AH149, Revision 1, dated May 3, 2013 or 

earlier version or, for initial restoration only, 

RB.211–72–H464, dated August 28, 2013. 

(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 MCAI European Aviation 

Safety Agency, AD 2013–0214, dated 

September 16, 2013, 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–2013–0880. 

(3) Rolls-Royce plc Alert Non-Modification 

Service Bulletin No. RB.211–72–AH149, 

Revision 1, dated May 3, 2013 and RB.211– 

72–H464, dated August 28, 2013, which are 

not incorporated by reference in this AD, can 

be obtained from RR, using the contact 

information in paragraph (h)(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. 

(i) 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. 2013–28178 Filed 11–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30930; Amdt. No. 3565] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective November 

26, 2013. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

26, 2013. 

ADDRESSES: Availability of matter 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 


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