5906 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 

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 

(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): 

2015–02–07 Lycoming Engines (Type 

Certificate previously held by Textron 

Lycoming Division, AVCO Corporation): 

Amendment 39–18074; Docket No. 

FAA–2014–0540; Directorate Identifier 

2014–NE–10–AD. 

(a) Effective Date 

This AD is effective March 11, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Lycoming Engines 

wide deck aerobatic reciprocating engines 

that have either an ‘‘A’’ or an ‘‘E’’ at the end 

of the serial number (e.g., L–12345–51A, or 

L–12345–51E) and are equipped with a frontmounted propeller governor. Affected 

reciprocating engine models include, but are 

not limited to Lycoming Engines AEIO–320– 

D1B; AEIO–360–A1E, –A1E6, –B1H, –H1B; 

AEIO–540–D4A5, –D4B5, –D4D5, –L1B5, 

–L1B5D, –L1D5; AEIO–580–B1A; and IO– 

540–K1K5 (with aerobatic kit installed). 

(d) Unsafe Condition 

This AD was prompted by propeller 

governor shaft set screws coming loose due 

to improper installation. We are issuing this 

AD to prevent the propeller governor shaft 

set screw from coming loose, causing damage 

to the engine and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

After the effective date of this AD, at each 

installation of the propeller governor shaft set 

screw, secure the set screw in place in 

accordance with the instructions of 

Lycoming Engines Service Instruction No. 

1343B, dated June 15, 2007. Use a threadlocking, anaerobic, single-component sealing 

compound that meets military specification 

Mil–S–46163A, Type III, Grade R, and peen 

the crankcase hole threads. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, New York Aircraft 

Certification Office, FAA, may approve 

AMOCs to 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 Norm Perenson, Aerospace Engineer, 

New York Aircraft Certification Office, FAA, 

Engine & Propeller Directorate, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

phone: 516–228–7337; fax: 516–794–5531; 

email: norman.perenson@faa.gov. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Lycoming Engines Service Instruction 

No. 1343B, dated June 15, 2007. 

(ii) Reserved. 

(3) For Lycoming Engines service 

information identified in this AD, contact 

Lycoming Engines, 652 Oliver Street, 

Williamsport, PA 17701; phone: 800–258– 

3279; fax: 570–327–7101; Internet: http://

www.lycoming.com/Lycoming/SUPPORT/

TechnicalPublications/Service

Instructions.aspx. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

January 13, 2015. 

Thomas A. Boudreau, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–01281 Filed 2–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28059; Directorate 

Identifier 2007–NE–13–AD; Amendment 39– 

18087; AD 2015–02–20] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2013–15– 

10 that applies to certain Rolls-Royce 

plc (RR) RB211 turbofan engines. AD 

2013–15–10 required inspecting the 

intermediate-pressure compressor (IPC) 

rotor shaft rear balance land for cracks. 

This AD requires inspecting the IPC 

rotor shaft rear balance land for cracks, 

eliminates a terminating action, expands 

one inspection, and eliminates certain 

other inspections. We are issuing this 

AD to detect cracking on the IPC rotor 

shaft rear balance land, which could 

lead to uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective March 11, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of certain publications listed in 

this AD as of March 11, 2015. 

The Director of the Federal Register 

approved the IBR of certain other 

publications listed in this AD as of 

October 8, 2013 (78 FR 54149, 

September 3, 2013) and as of June 29, 

2012 (77 FR 31176, May 25, 2012). 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE24 8BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http://


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www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://

www.aeromanager.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. 

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–2007– 

28059; 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 mandatory 

continuing airworthiness information, 

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: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7765; fax: 781–238– 

7199; email: kenneth.steeves@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–15–10, 

Amendment 39–17526 (78 FR 54149, 

September 3, 2013), (‘‘AD 2013–15– 

10’’). AD 2013–15–10 applied to the 

specified products. The NPRM 

published in the Federal Register on 

September 11, 2014 (79 FR 54220). The 

NPRM proposed to retain the 

requirements of AD 2013–15–10 for 

inspecting the IPC rotor shaft rear 

balance land for cracks. The NPRM also 

proposed to require that the repetitive 

in-shop eddy current inspections (ECIs) 

in AD 2013–15–10 be performed even 

after modifying certain engines. The 

NPRM also proposed to eliminate 

repetitive on-wing inspections for 

certain other engines, and eliminate 

certain in-shop visual inspections for all 

engines. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 54220, September 11, 2014). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes, e.g., paragraph references and 

referencing the latest version of certain 

service information incorporated by 

reference. 

Related Service Information 

We reviewed RR Alert NonModification Service Bulletin (NMSB) 

No. RB.211–72–AH059, dated December 

11, 2012; RR Alert NMSB No. RB.211– 

72–AH058, Revision 1, dated July 7, 

2014; RR Alert NMSB No. RB.211–72– 

AG270, Revision 4, dated March 21, 

2011; RR Alert NMSB No. RB.211–72– 

AG085, Revision 2, dated July 7, 2011; 

RR Alert NMSB No. RB.211–72–AG264, 

Revision 5, dated March 21, 2011; and 

RR NMSB No. RB.211–72–G448, 

Revision 4, dated August 21, 2014. The 

service information describes 

procedures for performing borescope 

inspections and ECIs of the IPC rotor 

shaft rear balance land. You can find 

this information in the AD docket on the 

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

!docketBrowser;rpp=25;po=0;D=FAA2007-28059. 

Costs of Compliance 

We estimate that this AD will affect 

about 136 engines installed on airplanes 

of U.S. registry. We also estimate that it 

will take about 14 hours per engine to 

perform the inspections required by this 

AD. The average labor rate is $85 per 

hour. Replacement parts are estimated 

to cost about $2,271 per engine. Based 

on these figures, we estimate the cost of 

the AD on U.S. operators to be $470,696. 

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 

(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 part 39 of the Federal 

Aviation Regulations (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 

removing airworthiness directive (AD) 

2013–15–10, Amendment 39–17526 (78 

FR 54149, September 3, 2013), and 

adding the following new AD: 

2015–02–20 Rolls-Royce plc: Amendment 

39–18087; Docket No. FAA–2007–28059; 

Directorate Identifier 2007–NE–13–AD. 

(a) Effective Date 

This AD is effective March 11, 2015. 

(b) Affected ADs 

This AD supersedes AD 2013–15–10, 

Amendment 39–17526 (78 FR 54149, 

September 3, 2013). 

(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, 

560A2–61, 768–60, 772–60, 772B–60, 875– 

17, 877–17, 884–17, 884B–17, 892–17, 892B– 

17, 895–17, 970–84, 970B–84, 972–84, 972B– 


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84, 977–84, 977B–84, and 980–84 turbofan 

engines. 

(d) Unsafe Condition 

This AD was prompted by reports of cracks 

in Trent 500, Trent 700, and Trent 800 

intermediate-pressure compressor (IPC) rotor 

shaft rear balance lands and analysis that 

determined similar cracks may exist in Trent 

900 engines. We are issuing this AD to detect 

cracking on the IPC rotor shaft rear balance 

land, which could lead to uncontained 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) RB211-Trent 700 Engines—Rear Balance 

Land Inspections 

(i) Within 625 cycles-in-service (CIS) after 

June 29, 2012, or before the next flight after 

the effective date of this AD, whichever 

occurs later, borescope inspect the IPC rotor 

shaft rear balance land. Use RR Alert NonModification Service Bulletin (NMSB) No. 

RB.211–72–AG270, Revision 4, dated March 

21, 2011, paragraphs 3.A.(2)(a) through 

3.A.(2)(c) and 3.A.(3)(a) through 3.A.(3)(c) for 

in-shop procedures, or paragraphs 3.B.(2)(a) 

through 3.B.(2)(c) and 3.B.(4)(a) through 

3.B.(4)(c), for on-wing procedures, to do the 

inspection. 

(ii) Thereafter, repeat the inspection within 

every 625 cycles-since-last inspection (CSLI). 

You may count CSLI from the last borescope 

inspection or the last eddy current inspection 

(ECI), whichever occurred later. 

(iii) At each shop visit after the effective 

date of this AD, perform an ECI of the IPC 

rotor shaft rear balance land. Use RR Alert 

NMSB No. RB.211–72–AG085, Revision 2, 

dated July 7, 2011, paragraphs 3.A. through 

3.B., to do the inspection. 

(iv) To meet the requirement of paragraph 

(e)(1)(i) of this AD, instead of a borescope 

inspection, you may perform an ECI using 

paragraph (e)(1)(iii) of this AD. 

(2) RB211-Trent 800 Engines—Rear Balance 

Land Inspections 

(i) Within 475 CIS after June 29, 2012, or 

before the next flight after the effective date 

of this AD, whichever occurs later, borescope 

inspect the IPC rotor shaft rear balance land. 

Use RR Alert NMSB No. RB.211–72–AG264, 

Revision 5, dated March 21, 2011, paragraphs 

3.A.(2)(a) through 3.A.(2)(c) and 3.A.(3)(a) 

through 3.A.(3)(c), for in-shop procedures, or 

paragraphs 3.B.(2)(a) through 3.B.(2)(c) and 

3.B.(4)(a) through 3.B.(4)(c), for on-wing 

procedures, to do the inspection. 

(ii) Thereafter, repeat the inspection within 

every 475 CSLI. You may count CSLI from 

the last borescope inspection or the last ECI, 

whichever occurred later. 

(iii) At each shop visit after the effective 

date of this AD, perform an ECI of the IPC 

rotor shaft rear balance land. Use RR Alert 

NMSB No. RB.211–72–AG085, Revision 2, 

dated July 7, 2011, paragraphs 3.A. through 

3.B., to do the inspection. 

(iv) To meet the requirement of paragraph 

(e)(2)(i) of this AD, instead of a borescope 

inspection, you may perform an ECI using 

paragraph (e)(2)(iii) of this AD. 

(3) RB211-Trent 500 Engines—Rear Balance 

Land Inspections 

(i) Within 340 CIS after October 8, 2013, or 

before the next flight after the effective date 

of this AD, whichever occurs later, borescope 

inspect the IPC rotor shaft rear balance land. 

Use RR Alert NMSB No. RB.211–72–AH058, 

Revision 1, dated July 7, 2014, paragraphs 

3.A.(2)(a) through 3.A.(2)(c), 3.A.(3)(a) 

through 3.A.(3)(d), and 3.A.(5)(a) through 

3.A.(5)(c), for on-wing procedures, to do the 

inspection. 

(ii) Thereafter, repeat the inspection within 

every 340 CSLI. You may count CSLI from 

the last borescope inspection or the last ECI, 

whichever occurred later. 

(iii) At each shop visit after the effective 

date of this AD, perform an ECI of the IPC 

rotor shaft rear balance land. Use RR NMSB 

No. RB.211–72–G448, Revision 4, dated 

August 21, 2014, paragraphs 3.D.(4) through 

3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) 

through 3.D.(8)(w), and 3.D.(11) to do the 

inspection. 

(iv) To meet the requirement of paragraph 

(e)(3)(i) of this AD, instead of a borescope 

inspection, you may perform an ECI using 

paragraph (e)(3)(iii) of this AD. 

(4) RB211-Trent 900 Engines—Rear Balance 

Land Inspections 

(i) Within 280 flight cycles after October 8, 

2013, or before the next flight after the 

effective date of this AD, whichever occurs 

later, borescope inspect the IPC rotor shaft 

rear balance land. Use RR Alert NMSB No. 

RB.211–72–AH059, dated December 11, 

2012, paragraphs 3.A.(2)(a) through 

3.A.(2)(c), 3.A.(3)(a) through 3.A.(3)(d), and 

3.A.(5)(a) through 3.A.(5)(c) for on-wing 

procedures, to do the inspection. 

(ii) Thereafter, repeat the inspection within 

every 280 CSLI. You may count CSLI from 

the last borescope inspection or the last ECI, 

whichever occurred last. 

(iii) At each shop visit after the effective 

date of this AD, perform an ECI of the IPC 

rotor shaft rear balance land. Use RR NMSB 

No. RB.211–72–G448, Revision 4, dated 

August 21, 2014, paragraphs 3.D.(4) through 

3.D.(5), 3.D.(6)(f) through 3.D.(7)(w), 3.D.(8)(f) 

through 3.D.(8)(w), and 3.D.(11) to do the 

inspection. 

(iv) To meet the requirement of paragraph 

(e)(4)(i) of this AD, instead of a borescope 

inspection, you may perform an ECI using 

paragraph (e)(4)(iii) of this AD. 

(5) RB211-Trent 500, RB211-Trent 700, 

RB211-Trent 800, and RB211-Trent 900 

Engines IPC Balance Weight Removal 

(i) RB211-Trent 500 engines. At the next 

shop visit after the effective date of this AD, 

remove the IPC balance weights, part 

numbers (P/Ns) AS44695–150, AS44695– 

175, AS44695–200, AS44695–225, AS44695– 

250, AS44695–275, and AS44695–300. 

(ii) RB211-Trent 700 engines. At the next 

shop visit after the effective date of this AD, 

remove the IPC balance weights, P/Ns 

AS44695–150, AS44695–175, AS44695–200, 

AS44695–225, AS44695–250, AS44695–275, 

and AS44695–300. 

(iii) RB211-Trent 800 engines. At the next 

shop visit after the effective date of this AD, 

remove the IPC balance weights, P/Ns 

AS44695–150, AS44695–175, AS44695–200, 

AS44695–225, AS44695–250, AS44695–275, 

and AS44695–300. 

(iv) RB211-Trent 900 engines. At the next 

shop visit after the effective date of this AD, 

remove the IPC balance weights, P/Ns 

AS44695–150, AS44695–175, AS44695–200, 

AS44695–225, AS44695–250, AS44695–275, 

and AS44695–300. 

(v) Once you have removed the IPC balance 

weights, P/Ns AS44695–150, AS44695–175, 

AS44695–200, AS44695–225, AS44695–250, 

AS44695–275, and AS44695–300, do not reinstall them on any IPC shaft rear balance 

land. 

(6) RB211-Trent 500, RB211-Trent 700, 

RB211-Trent 800, and RB211-Trent 900 

Engines—Terminating Action to Repetitive 

Borescope Inspections 

(i) Removal of the IPC balance weights as 

described in paragraph (e)(5) of this AD 

terminates the repetitive borescope 

inspection requirements in paragraphs (e)(1) 

through (e)(4) of this AD. However, at each 

shop visit you must still do the ECI required 

by paragraphs (e)(1) through (e)(4) of this AD. 

(ii) Reserved. 

(f) Credit for Previous Actions 

(1) RB211-Trent 700 Engines 

(i) If you borescope inspected an RB211- 

Trent 700 engine, before the effective date of 

this AD, using RR Alert NMSB No. RB.211– 

72–AG270, Revision 1, dated December 14, 

2009; or Revision 2, dated December 21, 

2010; or Revision 3, dated February 25, 2011, 

you have met the requirements of paragraph 

(e)(1)(i) of this AD. 

(ii) If you eddy current inspected an 

RB211-Trent 700 engine, before the effective 

date of this AD, using RR Alert NMSB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, you met the ECI 

requirement of paragraph (e)(1)(iii) of this 

AD. However, you are still required to 

perform the repetitive inspections required 

by paragraphs (e)(1)(ii) and (e)(1)(iii) of this 

AD. 

(2) RB211-Trent 800 Engines 

(i) If you borescope inspected an RB211- 

Trent 800 engine, before the effective date of 

this AD, using RR Alert NMSB No. RB.211– 

72–AG264, Revision 3, dated December 21, 

2010; or Revision 4, dated February 25, 2011, 

you met the requirements of paragraph 

(e)(2)(i) of this AD. 

(ii) If you eddy current inspected an 

RB211-Trent 800 engine, before the effective 

date of this AD, using RR Alert NMSB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, you met the ECI 

requirement of paragraph (e)(2)(iii) of this 

AD. However, you are still required to 

perform the repetitive inspections required 

by paragraphs (e)(2)(ii) and (e)(2)(iii) of this 

AD. 

(3) RB211-Trent 500 Engines 

(i) If you borescope inspected an RB211- 

Trent 500 engine, before the effective date of 

this AD, using RR Alert NMSB RB.211–72– 

AH058, dated December 13, 2012; or RR 

NMSB No. RB.211–72–G448, Revision 2, 

dated December 23, 2010; or Revision 3, 


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dated July 7, 2011, you met the requirement 

of paragraph (e)(3)(i) of this AD. 

(ii) If you eddy current inspected an 

RB211-Trent 500 engine, before the effective 

date of this AD, using RR NMSB No. RB.211– 

72–G448, Revision 2, dated December 23, 

2010; or Revision 3, dated July 7, 2011, you 

met the ECI requirement of paragraph 

(e)(3)(iii) of this AD. However, you are still 

required to perform the repetitive inspections 

required by paragraphs (e)(3)(ii) and (e)(3)(iii) 

of this AD. 

(4) RB211-Trent 900 engines 

(i) If you borescope inspected an RB211- 

Trent 900 engine, before the effective date of 

this AD, using RR Alert NMSB RB.211–72– 

AH059, dated December 11, 2012; or RR 

NMSB No. RB.211–72–G448, Revision 2, 

dated December 23, 2010; or Revision 3, 

dated July 7, 2011, you met the requirements 

of paragraph (e)(4)(i) of this AD. 

(ii) If you eddy current inspected an 

RB211-Trent 900 engine, before the effective 

date of this AD, using RR NMSB No. RB.211– 

72–G448, Revision 2, dated December 23, 

2010; or Revision 3, dated July 7, 2011, you 

met the ECI requirement of paragraph 

(e)(4)(iii) of this AD. However, you are still 

required to perform the repetitive inspections 

required by paragraphs (e)(4)(ii) and (e)(4)(iii) 

of this AD. 

(g) Definition 

For the purpose of this AD, a shop visit is 

defined as the introduction of an engine into 

the shop and disassembly sufficient to 

expose the IPC module rear face. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to make your 

request. You may email your request to: 

ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Kenneth Steeves, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7765; fax: 781–238– 

7199; email: kenneth.steeves@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0152, dated June 20, 

2014, and corrected on June 25, 2014, for 

more information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2007-28059-0028. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 11, 2015. 

(i) Rolls-Royce plc (RR) Non-Modification 

Service Bulletin (NMSB) No. RB.211–72– 

G448, Revision 4, dated August 21, 2014. 

(ii) RR Alert NMSB No. RB.211–72–AH058, 

Revision 1, dated July 7, 2014. 

(4) The following service information was 

approved for IBR on October 8, 2013 (78 FR 

54149, September 3, 2013). 

(i) RR Alert NMSB No. RB.211–72–AH059, 

dated December 11, 2012. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on June 29, 2012, (77 FR 

31176, May 25, 2012). 

(i) RR Alert NMSB No. RB.211–72–AG270, 

Revision 4, dated March 21, 2011. 

(ii) RR Alert NMSB No. RB.211–72–AG085, 

Revision 2, dated July 7, 2011. 

(iii) RR Alert NMSB No. RB.211–72– 

AG264, Revision 5, dated March 21, 2011. 

(6) For RR service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

http://www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://www.

aeromanager.com. 

(7) You may view this service information 

at 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. 

(8) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

January 16, 2015. 

Thomas A. Boudreau, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–01557 Filed 2–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0462; Directorate 

Identifier 2014–NE–06; Amendment 39– 

18075; AD 2015–02–08] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboprop and Turbofan 

Engines (Type Certificate Previously 

Held by Allison Engine Company) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce Corporation (RRC) AE 2100 

series turboprop engines and AE 3007A 

and 3007C series turbofan engines. This 

AD was prompted by reports of pitting 

in the wheel bores and subsequent RRC 

analysis that concluded that lower life 

limits are needed for the affected 

turbine wheels. This AD requires a 

reduction for the approved life limits of 

the affected turbine wheels. This AD 

also requires an eddy current inspection 

(ECI) of certain RRC engines with 

affected turbine wheels. We are issuing 

this AD to prevent uncontained failure 

of the turbine wheels, damage to the 

engine, and damage to the airplane. 

DATES: This AD is effective March 11, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 11, 2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce Corporation, 450 South Meridian 

Street, Mail Code NB–01–06, 

Indianapolis, IN 46225; phone: 317– 

230–1667; email: CMSEindyOSD@rollsroyce.com; Internet: www.rollsroyce.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. 

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–2014– 

0462, 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: Kyri 

Zaroyiannis, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

Small Airplane Directorate, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–7836; fax: 847–294– 

7834; email: kyri.zaroyiannis@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain RRC AE 2100 series 

turboprop engines and AE 3007A and 

3007C series turbofan engines. The 

NPRM published in the Federal 

Register on October 2, 2014 (79 FR 


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