Airworthiness Directives; Rolls-Royce Corporation Turboprop and Turbofan Engines (Type Certificate Previously Held by Allison Engine Company), 5909-5911 [2015-01282]

Download as PDF Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 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 RB211Trent 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. tkelley on DSK3SPTVN1PROD with RULES (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. VerDate Sep<11>2014 20:27 Feb 03, 2015 Jkt 235001 (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. 5909 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. AGENCY: 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: 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 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 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) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\04FER1.SGM 04FER1 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). tkelley on DSK3SPTVN1PROD with RULES 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 VerDate Sep<11>2014 20:27 Feb 03, 2015 Jkt 235001 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. 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. 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. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 § 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 E:\FR\FM\04FER1.SGM 04FER1 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 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. (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 (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. tkelley on DSK3SPTVN1PROD with RULES (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. RIN 2120–AA64 (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. 20:27 Feb 03, 2015 Jkt 235001 14 CFR Part 39 [Docket No. FAA–2014–0138; Directorate Identifier 2013–NM–020–AD; Amendment 39–18086; AD 2015–02–19] Airworthiness Directives; Airbus Airplanes 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: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Discussion 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 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 AGENCY: SUMMARY: (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. VerDate Sep<11>2014 Federal Aviation Administration 5911 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\04FER1.SGM 04FER1

Agencies

[Federal Register Volume 80, Number 23 (Wednesday, February 4, 2015)]
[Rules and Regulations]
[Pages 5909-5911]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01282]


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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 
Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-01-06, 
Indianapolis, IN 46225; phone: 317-230-1667; email: royce.com">CMSEindyOSD@rolls-royce.com; Internet: www.rolls-royce.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

[[Page 5910]]

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 pro-
rated 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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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

[[Page 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: 
royce.com">CMSEindyOSD@rolls-royce.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]
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