Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 20509-20511 [2013-07935]

Download as PDF Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. (4) For those engines that do not have an ESV after the effective date of this AD before the part exceeds the part life assigned in paragraph (e)(2) of this AD, remove the part from service at the next ESV. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. With the exception of parts that can be reworked using RR Service Bulletin No. RB.211–72–D365, Revision 5, dated December 13, 2012, do not reinstall any part removed per this AD into any engine. The Proposed Amendment (g) Definitions Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: (h) Alternative Methods of Compliance (AMOCs) Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ Rolls-Royce plc: Docket No. FAA–2013– 0052; Directorate Identifier 2013–NE– 02–AD. (a) Comments Due Date We must receive comments by June 4, 2013. (b) Affected Airworthiness Directives (ADs) None. (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211–535E4–37, RB211–535E4–B–37, RB211–535E4–C–37, and RB211–535E4–B– 75 turbofan engines. TKELLEY on DSK3SPTVN1PROD with PROPOSALS (d) Reason This AD was prompted by RR updating the low-cycle-fatigue life analysis for the low pressure turbine (LPT) stage 2 discs. We are issuing this AD to prevent LPT stage 2 disc failure, which could result in uncontained engine damage and damage to the airplane. (e) Actions and Compliance (1) Within 30 days after the effective date of this AD, re-calculate the cyclic life since new of each LPT stage 2 disc. Use the part lives and prorated life formulas in Appendices 1, 2, and 3 of RR Alert NonModification Service Bulletin (NMSB) No. RB.211–72–AH029, dated December 13, 2012, to make that calculation. (2) Assign the Maximum Approved Lives defined in Appendix 1 of Alert NMSB No. RB.211–72–AH029, dated December 13, 2012, to the LPT stage 2 disc based on the flight profile that will be flown. (3) For engines that have an engine shop visit (ESV) after the effective date of this AD, remove the LPT stage 2 disc from service before the part exceeds the maximum approved life assigned in paragraph (e)(2) of this AD. VerDate Mar<15>2010 16:26 Apr 04, 2013 Jkt 229001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 (f) Installation Prohibition For the purpose of this AD, an ESV is whenever engine maintenance performed prior to reinstallation requires the separation of a pair of major mating engine module flanges. Separation of flanges solely for the purpose of shipment without subsequent internal maintenance is not a shop visit. ■ 20509 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. (i) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7754; fax: 781–238–7199; email: Robert.Green@faa.gov. (2) Refer to European Aviation Safety Agency Airworthiness Directive 2012–0266, dated December 18, 2012, and RR Alert NMSB No. RB.211–72–AH029, dated December 13, 2012, for related information. (3) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–249936; or email from https://www.rolls-royce.com/contact/ civil_team.jsp; or download the publication from https://www.aeromanager.com. 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. Issued in Burlington, Massachusetts, on March 28, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–07931 Filed 4–4–13; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 [Docket No. FAA–2013–0029; Directorate Identifier 2013–NE–01–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211–535E4–B– 37 series turbofan engines. This proposed AD was prompted by recalculating the life of certain life limited parts operated to certain flight profiles. This proposed AD would require removal of affected parts using a drawdown plan. We are proposing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane. DATES: We must receive comments on this proposed AD by June 4, 2013. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332–242424; fax: 011– 44–1332–249936 or email from https:// www.rolls-royce.com/contact/ civil_team.jsp, or download the publication from 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. SUMMARY: E:\FR\FM\05APP1.SGM 05APP1 20510 Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: robert.green@faa.gov; phone: 781–238–7754; fax: 781–238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0029; Directorate Identifier 2013– NE–01–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. TKELLEY on DSK3SPTVN1PROD with PROPOSALS Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2012– 0265, dated December 18, 2012 (referred to herein after as ‘‘the MCAI’’), to correct an unsafe condition for the specified product. The MCAI states: Flight Profiles (FP) define the limits of engine operation within which the engine will qualify for use of an associated set of Critical Parts life limits. The Rolls-Royce RB211–535E4–B–37 engine previously had only one such FP and associated set of life limits published in the applicable RR Time Limits Manual. However, a recent review of operational flight data has revealed that some engines may have been operated beyond the currently valid datum FP. VerDate Mar<15>2010 16:26 Apr 04, 2013 Jkt 229001 Failure to account for the correct rate of fatigue damage associated with engine operation may lead to Critical Parts failure, possibly resulting in release of high energy debris, damage to the aeroplane and/or injury to occupants. We are proposing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information RR has issued Alert Non-Modification Service Bulletin (NMSB) No. RB.211– 72–AG875, dated December 13, 2012. The Alert NMSB introduces two new datum flight profiles (Flight Profile D and Flight Profile E) and the life-limited part lives that are the drawdown plan retirement thresholds. FAA’s Determination and Requirements of This Proposed 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 proposing 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. This proposed AD would require removal of affected parts using a drawdown plan. Differences Between the AD and the MCAI or Service Information This AD differs from EASA AD 2012– 0265, dated December 18, 2012, as follows: The EASA AD specifies replacing the affected critical parts during the module disassembly if the subsequent, anticipated time on wing (time before next shop visit) plus current life of the part will exceed the new provisional lives published in the RR Alert NMSB. We specify replacing at next shop visit (defined by the separation of a major flange). Costs of Compliance We estimate that this proposed AD would affect about 377 engines installed on airplanes of U.S. registry. Of these 377 engines, we estimate 95 engines operate to Flight Profile D or E. The average labor rate is $85 per work hour. We do not estimate any labor cost is associated with this proposed AD because the affected parts are replaced at the next shop visit. Prorated cost of PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 parts adjusted to Flight Profile D operation, would cost about $77,672 per engine. Prorated cost of parts adjusted to Flight Profile E operation, would cost about $204,981 per engine. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $11,834,655. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (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 proposed AD and placed it in the AD docket. E:\FR\FM\05APP1.SGM 05APP1 Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Rolls-Royce plc: Docket No. FAA–2013– 0029; Directorate Identifier 2013–NE– 01–AD. (a) Comments Due Date We must receive comments by June 4, 2013. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211–535E4–B–37 series turbofan engines. TKELLEY on DSK3SPTVN1PROD with PROPOSALS (d) Unsafe Condition This AD was prompted by recalculating the life of certain life limited parts operated to certain flight profiles. We are issuing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 30 days after the effective date of this AD for engines that have operated to Flight Profile D or E, recalculate the life of the low-pressure (LP) turbine disc stage 2, intermediate-pressure (IP) compressor rotor shaft (stage 1 to 6), high-pressure (HP) compressor rear rotor shaft assembly, and HP turbine disc installed on that engine. Use the part lives, prorated life formulas, and flight profiles in Appendices 2, 4, and 5 of RR Alert Non-Modification Service Bulletin (NMSB) No. RB.211–72–AG875, dated December 13, 2012, to make that calculation. (2) Within 30 days after the effective date of this AD for engines that will operate to Flight Profile D or E, assign the Maximum Approved Lives defined in Appendix 2 of RR Alert NMSB No. RB.211–72–AG875, dated December 13, 2012, to the LP turbine disc Stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, and HP turbine disc based on the flight profile that will be flown. (3) For engines that have only operated to, and will continue to operate to, Flight Profile VerDate Mar<15>2010 16:26 Apr 04, 2013 Jkt 229001 C, as defined in Appendix 5 of RR Alert NMSB No. RB.211–72–AG875, dated December 13, 2012, no further action is required by this AD. (4) For engines that incorporate an LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD that have an engine shop visit (ESV) after the effective date of this AD, remove each part from service before the part exceeds the part life assigned in paragraph (e)(2) of this AD. (5) For those engines that incorporate an LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD, that do not have an ESV after the effective date of this AD before the part exceeds the part life assigned in paragraph (e)(2) of this AD, remove the part from service at the next ESV. Issued in Burlington, Massachusetts, on March 29, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. (f) Installation Prohibition List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. § 39.13 20511 SUMMARY: After the effective date of this AD, any LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD that is re-installed in any engine after the effective date of this AD must be removed from service before the part exceeds the part life assigned in paragraph (e)(2) of this AD. (g) Definitions For the purpose of this AD, ESV is whenever engine maintenance performed prior to reinstallation requires the separation of a pair of major mating engine module flanges. Separation of flanges solely for the purpose of shipment without subsequent internal maintenance, is not an ESV. (h) 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. (i) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: robert.green@faa.gov; phone: 781– 238–7754; fax: 781–238–7199. (2) Refer to EASA AD 2012–0265, dated December 18, 2012, for related information. (3) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–249936 or email from https://www.rolls-royce.com/contact/ civil_team.jsp, or download the publication from 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. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 [FR Doc. 2013–07935 Filed 4–4–13; 8:45 am] BILLING CODE 4910–13–P CONSUMER PRODUCT SAFETY COMMISSION 16 CFR Parts 1112 and 1226 [Docket No. CPSC–2013–0014] Safety Standard for Soft Infant and Toddler Carriers Consumer Product Safety Commission. ACTION: Notice of proposed rulemaking. AGENCY: The Danny Keysar Child Product Safety Notification Act, Section 104 of the Consumer Product Safety Improvement Act of 2008 (CPSIA), requires the United States Consumer Product Safety Commission (Commission or CPSC) to promulgate consumer product safety standards for durable infant or toddler products. These standards are to be ‘‘substantially the same as’’ applicable voluntary standards or more stringent than the voluntary standard if the Commission concludes that more stringent requirements would further reduce the risk of injury associated with the product. The Commission is proposing a safety standard for soft infant and toddler carriers in response to the direction under Section 104(b) of the CPSIA.1 DATES: Submit comments by June 19, 2013. Comments related to the Paperwork Reduction Act aspects of the marking, labeling, and instructional literature of the proposed rule should be directed to the Office of Information and Regulatory Affairs, OMB, Attn: CPSC Desk Officer, FAX: 202–395–6974, or emailed to oira_submission@omb.eop.gov. Other comments, identified by Docket No. CPSC–2013–0014, may be submitted electronically or in writing: ADDRESSES: 1 The Commission voted 2–1 to approve publication of this proposed rule. Chairman Inez M. Tenenbaum and Commissioner Robert S. Adler voted to approve publication, and Commissioner Nancy A. Nord voted against publication. Commissioner’s statements concerning this or any other Commission action may be viewed by clicking on a specific Commissioner’s name and selecting ‘‘Statements’’ on the Commission’s Web site at https://www.cpsc.gov/en/About-CPSC/ Commissioners/, or obtained from the Commission’s Office of the Secretary. E:\FR\FM\05APP1.SGM 05APP1

Agencies

[Federal Register Volume 78, Number 66 (Friday, April 5, 2013)]
[Proposed Rules]
[Pages 20509-20511]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-07935]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0029; Directorate Identifier 2013-NE-01-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Rolls-Royce plc (RR) RB211-535E4-B-37 series turbofan engines. This 
proposed AD was prompted by recalculating the life of certain life 
limited parts operated to certain flight profiles. This proposed AD 
would require removal of affected parts using a drawdown plan. We are 
proposing this AD to prevent the failure of critical rotating parts, 
which could result in uncontained failure of the engine and damage to 
the airplane.

DATES: We must receive comments on this proposed AD by June 4, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, 
DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936 or email 
from https://www.rolls-royce.com/contact/civil_team.jsp, or download 
the publication from 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.

[[Page 20510]]

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; email: 
robert.green@faa.gov; phone: 781-238-7754; fax: 781-238-7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0029; 
Directorate Identifier 2013-NE-01-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2012-0265, dated December 18, 2012 (referred to herein after as 
``the MCAI''), to correct an unsafe condition for the specified 
product. The MCAI states:

    Flight Profiles (FP) define the limits of engine operation 
within which the engine will qualify for use of an associated set of 
Critical Parts life limits. The Rolls-Royce RB211-535E4-B-37 engine 
previously had only one such FP and associated set of life limits 
published in the applicable RR Time Limits Manual.
    However, a recent review of operational flight data has revealed 
that some engines may have been operated beyond the currently valid 
datum FP.
    Failure to account for the correct rate of fatigue damage 
associated with engine operation may lead to Critical Parts failure, 
possibly resulting in release of high energy debris, damage to the 
aeroplane and/or injury to occupants.

    We are proposing this AD to prevent the failure of critical 
rotating parts, which could result in uncontained failure of the engine 
and damage to the airplane. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    RR has issued Alert Non-Modification Service Bulletin (NMSB) No. 
RB.211-72-AG875, dated December 13, 2012. The Alert NMSB introduces two 
new datum flight profiles (Flight Profile D and Flight Profile E) and 
the life-limited part lives that are the drawdown plan retirement 
thresholds.

FAA's Determination and Requirements of This Proposed 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 proposing 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. This proposed AD would require removal of 
affected parts using a drawdown plan.

Differences Between the AD and the MCAI or Service Information

    This AD differs from EASA AD 2012-0265, dated December 18, 2012, as 
follows: The EASA AD specifies replacing the affected critical parts 
during the module disassembly if the subsequent, anticipated time on 
wing (time before next shop visit) plus current life of the part will 
exceed the new provisional lives published in the RR Alert NMSB. We 
specify replacing at next shop visit (defined by the separation of a 
major flange).

Costs of Compliance

    We estimate that this proposed AD would affect about 377 engines 
installed on airplanes of U.S. registry. Of these 377 engines, we 
estimate 95 engines operate to Flight Profile D or E. The average labor 
rate is $85 per work hour. We do not estimate any labor cost is 
associated with this proposed AD because the affected parts are 
replaced at the next shop visit. Prorated cost of parts adjusted to 
Flight Profile D operation, would cost about $77,672 per engine. 
Prorated cost of parts adjusted to Flight Profile E operation, would 
cost about $204,981 per engine. Based on these figures, we estimate the 
cost of the proposed AD on U.S. operators to be $11,834,655.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (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 proposed AD and placed it in the AD docket.

[[Page 20511]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Rolls-Royce plc: Docket No. FAA-2013-0029; Directorate Identifier 
2013-NE-01-AD.

(a) Comments Due Date

    We must receive comments by June 4, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-535E4-B-37 series 
turbofan engines.

(d) Unsafe Condition

    This AD was prompted by recalculating the life of certain life 
limited parts operated to certain flight profiles. We are issuing 
this AD to prevent the failure of critical rotating parts, which 
could result in uncontained failure of the engine and damage to the 
airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 30 days after the effective date of this AD for 
engines that have operated to Flight Profile D or E, recalculate the 
life of the low-pressure (LP) turbine disc stage 2, intermediate-
pressure (IP) compressor rotor shaft (stage 1 to 6), high-pressure 
(HP) compressor rear rotor shaft assembly, and HP turbine disc 
installed on that engine. Use the part lives, prorated life 
formulas, and flight profiles in Appendices 2, 4, and 5 of RR Alert 
Non-Modification Service Bulletin (NMSB) No. RB.211-72-AG875, dated 
December 13, 2012, to make that calculation.
    (2) Within 30 days after the effective date of this AD for 
engines that will operate to Flight Profile D or E, assign the 
Maximum Approved Lives defined in Appendix 2 of RR Alert NMSB No. 
RB.211-72-AG875, dated December 13, 2012, to the LP turbine disc 
Stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor 
rear rotor shaft assembly, and HP turbine disc based on the flight 
profile that will be flown.
    (3) For engines that have only operated to, and will continue to 
operate to, Flight Profile C, as defined in Appendix 5 of RR Alert 
NMSB No. RB.211-72-AG875, dated December 13, 2012, no further action 
is required by this AD.
    (4) For engines that incorporate an LP turbine disc stage 2, IP 
compressor rotor shaft (stage 1 to 6), HP compressor rear rotor 
shaft assembly, or HP turbine disc whose part life is defined by 
paragraph (e)(1) of this AD that have an engine shop visit (ESV) 
after the effective date of this AD, remove each part from service 
before the part exceeds the part life assigned in paragraph (e)(2) 
of this AD.
    (5) For those engines that incorporate an LP turbine disc stage 
2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear 
rotor shaft assembly, or HP turbine disc whose part life is defined 
by paragraph (e)(1) of this AD, that do not have an ESV after the 
effective date of this AD before the part exceeds the part life 
assigned in paragraph (e)(2) of this AD, remove the part from 
service at the next ESV.

(f) Installation Prohibition

    After the effective date of this AD, any LP turbine disc stage 
2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear 
rotor shaft assembly, or HP turbine disc whose part life is defined 
by paragraph (e)(1) of this AD that is re-installed in any engine 
after the effective date of this AD must be removed from service 
before the part exceeds the part life assigned in paragraph (e)(2) 
of this AD.

(g) Definitions

    For the purpose of this AD, ESV is whenever engine maintenance 
performed prior to reinstallation requires the separation of a pair 
of major mating engine module flanges. Separation of flanges solely 
for the purpose of shipment without subsequent internal maintenance, 
is not an ESV.

(h) 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.

(i) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; email: robert.green@faa.gov; phone: 781-238-7754; fax: 781-
238-7199.
    (2) Refer to EASA AD 2012-0265, dated December 18, 2012, for 
related information.
    (3) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936 
or email from https://www.rolls-royce.com/contact/civil_team.jsp, or 
download the publication from 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.

    Issued in Burlington, Massachusetts, on March 29, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-07935 Filed 4-4-13; 8:45 am]
BILLING CODE 4910-13-P
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