Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 5909 

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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5910 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 

59461). The NPRM 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. The NPRM 

proposed to require reducing the 

approved life limits of the affected 

turbine wheels and performing an 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

An anonymous commenter supported 

the NPRM (79 FR 59461, October 2, 

2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes, e.g., verb tense changes and 

word changes appropriate to a final rule. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

59461, October 2, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 59461, 

October 2, 2014). 

Related Service Information 

We reviewed: 

• Rolls-Royce (RR) Alert Service 

Bulletin (ASB) No. AE 2100D2–A–72– 

085, dated July 25, 2013. 

• RR ASB No. AE 2100D3–A–72–277, 

dated July 25, 2013. 

• RR ASB No. AE 2100P–A–72–019, 

dated July 25, 2013. 

• RR ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014. 

• RR ASB No. AE 3007A–A–72–408, 

Revision 1, dated August 29, 2014. 

• RR ASB No. AE 3007C–A–72–316, 

dated December 6, 2013. 

These service bulletins describe 

procedures for inspecting high-pressure 

turbine (HPT) stage 2 wheels and 

identify life-limit reduction for all 

affected HPT wheels. You can find this 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0462. 

Costs of Compliance 

We estimate that this AD will affect 

664 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 1 hour to perform an ECI 

in the bore of the turbine wheel for 

affected engines. The average labor rate 

is $85 per hour. We estimate the prorated replacement cost would be 

$30,688 for a 1st stage gas generator 

turbine wheel; $63,693 for a HPT stage 

1 wheel; $13,941 for an HPT stage 2 

wheel; and $13,186 for a 4th stage 

turbine wheel. We also estimate that 

these parts would be replaced during an 

engine shop visit at no additional labor 

cost. Based on these figures, we estimate 

the total cost of this AD on U.S. 

operators to be $11,317,969. 

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 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): 

2015–02–08 Roll-Royce Corporation (Type 

Certificate previously held by Allison 

Engine Company): Amendment 39– 

18075; Docket No. FAA–2014–0462; 

Directorate Identifier 2014–NE–06–AD. 

(a) Effective Date 

This AD is effective March 11, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce 

Corporation (RRC) AE 2100D2, 2100D2A, 

2100D3, and 2100P turboprop engines and 

AE 3007A1, A1/1, A1/3, A1E, A1P, A2, A3, 

C, C1, and C2 turbofan engines: 

(1) With an installed 1st stage gas generator 

turbine wheel, part number (P/N) 23079946, 

23088906, or 23089692, all serial numbers 

(S/Ns) listed in Table 2 and Table 3 of RRC 

Alert Service Bulletin (ASB) No. AE 2100D2– 

A–72–085, dated July 25, 2013; and in Table 

2 and Table 3 of RRC ASB No. AE 2100D3– 

A–72–277, dated July 25, 2013. 

(2) With an installed high-pressure turbine 

(HPT) stage 1 or HPT stage 2 wheel, P/N 

23079946, 23088906, 23088784, 23084520, 

23084781, 23088817, or 23088818, all S/Ns 

listed in Table 1 through Table 7 of RRC ASB 

No. AE 3007A–A–72–407, Revision 1, dated 

August 29, 2014, except those S/Ns excluded 

by Table 1, Table 2, Table 4, and Table 5 of 

RRC ASB No. AE 3007A–A–72–407, Revision 

1, dated August 29, 2014. 

(3) With an installed HPT stage 2 wheel, 

P/N 23084520 or 23088818, all S/Ns listed in 

Table 1 and Table 2 of RRC ASB No. AE 

3007C–A–72–316, dated December 6, 2013, 

except those S/Ns excluded by Table 1 of 

RRC ASB No. AE 3007C–A–72–316, dated 

December 6, 2013. 

(4) With an installed 4th stage turbine 

wheel, P/N 23083536, all S/Ns listed in Table 

2 of RRC ASB No. AE 2100P–A–72–019, 

dated July 25, 2013. 

(d) Unsafe Condition 

This AD was prompted by reports of 

pitting in the wheel bores and subsequent 

RRC analysis that concluded that lower life 


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Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 5911 

limits are needed for the 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. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For all RRC AE 3007A1, A1/1, A1/3, 

A1E, A1P, and A3 series engines with an 

HPT stage 2 wheel P/N and S/N identified in 

RRC ASB No. AE 3007A–A–72–408, Revision 

1, dated August 29, 2014, at each shop visit 

after the effective date of this AD, eddy 

current inspect the bore of the affected HPT 

stage 2 wheels. Use RRC ASB No. AE 3007A– 

A–72–408, Revision 1, August 29, 2014, to do 

the inspection. Do not return to service any 

wheel that fails the inspection required by 

this AD. 

(2) Thirty days after the effective date of 

this AD, do not return to service any engine 

that has a turbine wheel with a P/N and an 

S/N listed in any of the following RRC ASBs 

whose wheel life exceeds the new life limits 

identified in the following RRC ASBs: 

(i) RRC ASB No. AE 2100D2–A–72–085, 

dated July 25, 2013; 

(ii) RRC ASB No. AE 2100D3–A–72–277, 

dated July 25, 2013; 

(iii) RRC ASB No. AE 2100P–A–72–019, 

dated July 25, 2013; 

(iv) RRC ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014; or 

(v) RRC ASB No. AE 3007C–A–72–316, 

dated December 6, 2013. 

(f) Installation Prohibition 

Thirty days after the effective date of this 

AD, do not install an affected wheel, as 

identified in paragraph (c) of this AD, into 

any RRC AE 3007C2 engine. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance is not an engine shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

For more information about this AD, 

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. 

(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. 

(i) Rolls-Royce Alert Service Bulletin (ASB) 

No. AE 2100D2–A–72–085, dated July 25, 

2013. 

(ii) Rolls-Royce ASB No. AE 2100D3–A– 

72–277, dated July 25, 2013. 

(iii) Rolls-Royce ASB No. AE 2100P–A–72– 

019, dated July 25, 2013. 

(iv) Rolls-Royce ASB No. AE 3007A–A–72– 

407, Revision 1, dated August 29, 2014. 

(v) Rolls-Royce ASB No. AE 3007A–A–72– 

408, Revision 1, dated August 29, 2014. 

(vi) Rolls-Royce ASB No. AE 3007C–A–72– 

316, dated December 6, 2013. 

(3) For RRC service information identified 

in this AD, contact Rolls-Royce Corporation, 

450 South Meridian Street, Mail Code NB– 

01–06, Indianapolis, IN 46225; phone: 317– 

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

(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. 2015–01282 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–2014–0138; Directorate 

Identifier 2013–NM–020–AD; Amendment 

39–18086; AD 2015–02–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 95–24–04 

for all Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes; and 

Model A300 C4–605R Variant F 

airplanes. AD 95–24–04 required 

inspections to detect cracks at the aft 

spar web of the wings, and repair if 

necessary. This new AD reduces certain 

compliance times, and expands the 

applicability. This AD was prompted by 

a determination that the inspection 

threshold and interval must be reduced 

to allow timely detection of cracks and 

accomplishment of applicable repairs, 

because of cracking in the rear spar web 

of the wings between certain ribs due to 

fatigue-related high shear stress. We are 

issuing this AD to detect and correct 

fatigue-related cracking, which could 

result in reduced structural integrity of 

the wing. 

DATES: This AD becomes effective 

March 11, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 11, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 27, 1995 (60 FR 

58213, November 27, 1995). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0138; or in person at the Docket 

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. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this 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. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 95–24–04, 

Amendment 39–9436 (60 FR 58213, 

November 27, 1995). AD 95–24–04 

applied to all Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes; and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). The NPRM 


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