Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 23737-23739 [2015-09816]

Download as PDF 23737 Proposed Rules Federal Register Vol. 80, No. 82 Wednesday, April 29, 2015 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44–1332–242424; fax: 011–44– 1332–249936; email: https://www.rollsroyce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2015–0593; Directorate Identifier 2015–NE–08–AD] You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0593; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The 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: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238– 7199; email: wego.wang@faa.gov. SUPPLEMENTARY INFORMATION: 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) RB211–535E4–37, RB211–535E4–B–37, and RB211– 535E4–C–37 turbofan engines. This proposed AD was prompted by RR updating the life limits for certain highpressure turbine (HPT) disks. This proposed AD would require reducing the cyclic life limits for certain HPT disks, removing those disks that have exceeded the new life limit, and replacing them with serviceable parts. We are proposing this AD to prevent failure of the HPT disk, which could result in uncontained disk release, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by June 29, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. For service information identified in this proposed AD, Rolls-Royce plc, mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:59 Apr 28, 2015 Jkt 235001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–0593; Directorate Identifier 2015–NE–08–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 based on 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 with FAA personnel concerning this proposed AD. PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2014– 0249R1, dated February 18, 2015 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: An engineering analysis, carried out by RR, of the lives of critical parts of the RB211– 535E4–37 engine, has resulted in reduced cyclic life limits for certain high pressure (HP) turbine discs. The reduced limits are published in the RR RB211–535E4–37 Time Limits Manual (TLM): 05–10–01–800–000, current Revision dated July 2014. Operation of critical parts beyond these reduced cyclic life limits may result in part failure, possibly resulting in the release of high-energy debris, which may cause damage to the aeroplane and/or injury to the occupants. You may obtain further information by examining the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0593. Related Service Information Under 1 CFR Part 51 We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211– 72–G188, Revision No. 1, dated October 30, 2013, and RR RB211–535E4–37, Time Limits Manual (TLM): 05–10–01– 800–000, Revision dated July 1, 2014; and RR RB211–535E4–37, TLM: 05–00– 01–800–000, Revision dated July 1, 2014. The NMSB describes the updated lifing analysis of the affected HP turbine disks. The TLMs provide revised life limits for the affected HP turbine disks. This service information is reasonably available because the interested parties have access to it through their normal course of business or see ADDRESSES for other ways to access this service information. 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 E:\FR\FM\29APP1.SGM 29APP1 23738 Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules 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 reducing the cyclic life limits for certain HPT disks, removing those disks that have exceeded the new life limit, and replacing them with serviceable parts. Costs of Compliance We estimate that this proposed AD affects 650 engines installed on airplanes of U.S. registry. We also estimate that it would take about 0 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Pro-rated cost of required parts cost would be about $12,213 per engine. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $7,938,450. mstockstill on DSK4VPTVN1PROD with PROPOSALS 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), Jkt 235001 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: 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. 16:59 Apr 28, 2015 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. ■ Authority for This Rulemaking VerDate Sep<11>2014 (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. 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): ■ Rolls-Royce plc: Docket No. FAA–2015– 0593; Directorate Identifier 2015–NE–08–AD. (a) Comments Due Date We must receive comments by June 29, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all Rolls-Royce plc (RR), RB211–535E4–37, RB211–535E4–B–37, and RB211–535E4–C–37 turbofan engines. (d) Reason This AD was prompted by RR updating the life limits for certain high-pressure turbine (HPT) disks. We are issuing this AD to prevent failure of the HPT disk, which could result in uncontained disk release, damage to the engine, and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) After the effective date of this AD, use RR RB211–535E4–37 Time Limits Manual (TLM): 05–10–01–800–000, Revision dated July 1, 2014 (referred to hereafter as ‘the TLM’), to determine the new life limits for the affected engine models and configurations, with the exception of those engine models mentioned in paragraph (e)(2) of this AD. (2) For RR RB211–535E4–B–37 or RB211– 535E4–C–37 engines with an affected HPT disk that was previously installed on an RB211–535E4–37 engine operated under Flight Plan A, use task 05–00–01–800–000 in the TLM to re-calculate equivalent cycles since new to obtain the new life limit. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 (3) If an affected engine model has an HPT disk installed with P/N UL27681 or UL39767, remove the affected HPT disk before the accumulated cyclic life exceeds either 19,500 flight cycles (FCs) under Flight Plan A, or 14,700 FCs under Flight Plan B, or within 25 FCs after the effective date of this AD, whichever occurs later. (4) For all affected engines, other than those specified in paragraph (e)(3) in this AD, remove each HPT disk before exceeding its applicable life limit as specified in the TLM. (5) Install an HPT disk eligible for installation. (f) Definition For the purpose of this AD, a part eligible for installation is one with a part number listed in the TLM with a total accumulated cyclic life that is less than the applicable life limit specified in the TLM. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE–AD–AMOC@faa.gov. (h) Related Information (1) For more information about this AD, contact Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238–7199; email: wego.wang@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2014–0249R1, dated February 18, 2015, for more information. You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2015–0593. (3) RR Non-Modification Service Bulletin No. RB.211–72–G188, Revision No. 1, dated October 30, 2013, and RR RB211–535E4–37, TLM: 05–10–01–800–000, Revision dated July 1, 2014; and RR RB211–535E4–37, TLM: 05–00–01–800–000, Revision dated July 1, 2014, which are not incorporated by reference in this AD, can be obtained from Rolls-Royce plc, using the contact information in paragraph (h)(4) of this proposed AD. (4) For service information identified in this proposed 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: https://www.rolls-royce.com/contact/ civil_team.jsp; Internet: https:// www.aeromanager.com. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. E:\FR\FM\29APP1.SGM 29APP1 Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules Issued in Burlington, Massachusetts, on April 22, 2015. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–09816 Filed 4–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0932; Directorate Identifier 2014–NM–205–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–8 series airplanes. This proposed AD was prompted by a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings were missing or had moved out of the holes. This proposed AD would require installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. We are proposing this AD to prevent detachment of the quick-release pin, which could result in separation of the lateral support tie rod and subsequent detachment of the module and consequent injuries to passengers or flightcrew. SUMMARY: We must receive comments on this proposed AD by June 15, 2015. 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 mstockstill on DSK4VPTVN1PROD with PROPOSALS DATES: VerDate Sep<11>2014 16:59 Apr 28, 2015 Jkt 235001 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.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. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0932. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0932; 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: Stanley Chen, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6585; fax: 425–917–6590; email: stanley.chen@ faa.gov. 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– 2015–0932; Directorate Identifier 2014– NM–205–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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 23739 personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings of the outboard stowage bin module were missing or had moved out of the holes, and pins were installed incorrectly. These bushings were designed to prevent disengagement of the quick release pins; however, migration of the bushings deters this. It was determined that the interference fit of the bushings in the attachment brackets was incorrect. Subsequently, installation of the quick release pins during production has caused bushings to migrate or detach. This condition, if not corrected, could result in separation of the lateral support tie rod, detachment of the outboard stowage bin module, and consequent injuries to passengers or flightcrew. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 747–25– 3649, dated July 24, 2014. The service information describes procedures for installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. Refer to this service information for information on the procedures and compliance times. This service information is reasonably available; see ADDRESSES for ways to access this service information. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information identified previously. Explanation of ‘‘RC’’ Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee, to enhance the AD system. One enhancement was a E:\FR\FM\29APP1.SGM 29APP1

Agencies

[Federal Register Volume 80, Number 82 (Wednesday, April 29, 2015)]
[Proposed Rules]
[Pages 23737-23739]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09816]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / 
Proposed Rules

[[Page 23737]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0593; Directorate Identifier 2015-NE-08-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) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-
C-37 turbofan engines. This proposed AD was prompted by RR updating the 
life limits for certain high-pressure turbine (HPT) disks. This 
proposed AD would require reducing the cyclic life limits for certain 
HPT disks, removing those disks that have exceeded the new life limit, 
and replacing them with serviceable parts. We are proposing this AD to 
prevent failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by June 29, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    For service information identified in this proposed AD, Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: https://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. You may view this service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material at 
the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0593; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information (MCAI), the regulatory evaluation, any comments received, 
and other information. The 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: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7134; fax: 
781-238-7199; email: wego.wang@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0593; 
Directorate Identifier 2015-NE-08-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 based on 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 
with FAA personnel concerning 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 2014-0249R1, dated February 18, 2015 (referred to hereinafter as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    An engineering analysis, carried out by RR, of the lives of 
critical parts of the RB211-535E4-37 engine, has resulted in reduced 
cyclic life limits for certain high pressure (HP) turbine discs. The 
reduced limits are published in the RR RB211-535E4-37 Time Limits 
Manual (TLM): 05-10-01-800-000, current Revision dated July 2014.
    Operation of critical parts beyond these reduced cyclic life 
limits may result in part failure, possibly resulting in the release 
of high-energy debris, which may cause damage to the aeroplane and/
or injury to the occupants.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2015-0593.

Related Service Information Under 1 CFR Part 51

    We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211-
72-G188, Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014; and RR RB211-535E4-37, TLM: 05-00-01-800-000, Revision dated July 
1, 2014. The NMSB describes the updated lifing analysis of the affected 
HP turbine disks. The TLMs provide revised life limits for the affected 
HP turbine disks. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or see ADDRESSES for other ways to access this 
service information.

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

[[Page 23738]]

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 reducing the cyclic life limits 
for certain HPT disks, removing those disks that have exceeded the new 
life limit, and replacing them with serviceable parts.

Costs of Compliance

    We estimate that this proposed AD affects 650 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 0 
hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Pro-rated cost of required parts cost would be 
about $12,213 per engine. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $7,938,450.

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.

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-2015-0593; Directorate 
Identifier 2015-NE-08-AD.

(a) Comments Due Date

    We must receive comments by June 29, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR), RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-C-37 turbofan engines.

(d) Reason

    This AD was prompted by RR updating the life limits for certain 
high-pressure turbine (HPT) disks. We are issuing this AD to prevent 
failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) After the effective date of this AD, use RR RB211-535E4-37 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014 (referred to hereafter as `the TLM'), to determine the new life 
limits for the affected engine models and configurations, with the 
exception of those engine models mentioned in paragraph (e)(2) of 
this AD.
    (2) For RR RB211-535E4-B-37 or RB211-535E4-C-37 engines with an 
affected HPT disk that was previously installed on an RB211-535E4-37 
engine operated under Flight Plan A, use task 05-00-01-800-000 in 
the TLM to re-calculate equivalent cycles since new to obtain the 
new life limit.
    (3) If an affected engine model has an HPT disk installed with 
P/N UL27681 or UL39767, remove the affected HPT disk before the 
accumulated cyclic life exceeds either 19,500 flight cycles (FCs) 
under Flight Plan A, or 14,700 FCs under Flight Plan B, or within 25 
FCs after the effective date of this AD, whichever occurs later.
    (4) For all affected engines, other than those specified in 
paragraph (e)(3) in this AD, remove each HPT disk before exceeding 
its applicable life limit as specified in the TLM.
    (5) Install an HPT disk eligible for installation.

(f) Definition

    For the purpose of this AD, a part eligible for installation is 
one with a part number listed in the TLM with a total accumulated 
cyclic life that is less than the applicable life limit specified in 
the TLM.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7134; fax: 781-238-7199; email: 
wego.wang@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-
0249R1, dated February 18, 2015, for more information. You may 
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2015-0593.
    (3) RR Non-Modification Service Bulletin No. RB.211-72-G188, 
Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, TLM: 
05-10-01-800-000, Revision dated July 1, 2014; and RR RB211-535E4-
37, TLM: 05-00-01-800-000, Revision dated July 1, 2014, which are 
not incorporated by reference in this AD, can be obtained from 
Rolls-Royce plc, using the contact information in paragraph (h)(4) 
of this proposed AD.
    (4) For service information identified in this proposed 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: https://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.


[[Page 23739]]


    Issued in Burlington, Massachusetts, on April 22, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-09816 Filed 4-28-15; 8:45 am]
 BILLING CODE 4910-13-P

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