Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 65925-65927 [2015-21729]

Download as PDF Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations (i) Boeing Special Attention Service Bulletin 737–57–1318, dated May 15, 2013. (ii) Reserved. (5) For Boeing service information identified in this 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. (6) You may view this service information at 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. (7) You may view this service information that is incorporated by reference 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/ibrlocations.html. Issued in Renton, Washington, on October 11, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–26993 Filed 10–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0593; Directorate Identifier 2015–NE–08–AD; Amendment 39– 18254; AD 2015–17–21] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting 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 AD requires reducing the cyclic life limits for certain high-pressure turbine (HPT) disks, removing those disks that have exceeded the new life limit, and replacing them with serviceable parts. This AD was prompted by RR updating the life limits for certain 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. DATES: This AD becomes effective December 2, 2015. The Director of the Federal Register approved the incorporation by reference Lhorne on DSK5TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 15:03 Oct 27, 2015 Jkt 238001 of a certain publication listed in this AD as of December 2, 2015. ADDRESSES: For service information identified in this AD, contact RollsRoyce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44–1332–242424; fax: 011– 44–1332–249936; email: http:// 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0593. 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–2015– 0593; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the mandatory continuing airworthiness information (MCAI), 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: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The NPRM was published in the Federal Register on April 29, 2015 (80 FR 23737). The NPRM proposed 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. PO 00000 Frm 00045 Fmt 4700 Sfmt 4700 65925 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 23737, April 29, 2015). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed. Related Service Information Under 1 CFR Part 51 We reviewed Task 05–00–01–800– 000, ‘‘Recording and Control of the Lives of Parts’’, dated July 1, 2015, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015; and Task 05–10–01–800–000, ‘‘Group A Parts Lives—CONFIG–1’’, dated July 1, 2014, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)– 6RR, Revision 49, dated July 1, 2015. This service information provides revised life limits for the affected HPT 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. Related Service Information We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211– 72–G188, Revision No. 1, dated October 30, 2013. The NMSB describes the updated lifing analysis of the affected HPT disks. Costs of Compliance We estimate that this 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 AD. The average labor rate is $85 per hour. The pro-rated cost of required parts would be about $12,213 per engine. Based on these figures, we estimate the cost of this 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. E:\FR\FM\28OCR1.SGM 28OCR1 65926 Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 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 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 this AD: (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. 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: ■ Lhorne on DSK5TPTVN1PROD with RULES Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2015–17–21 Rolls-Royce plc: Amendment 39–18254; Docket No. FAA–2015–0593; Directorate Identifier 2015–NE–08–AD. VerDate Sep<11>2014 15:03 Oct 27, 2015 Jkt 238001 (a) Effective Date This AD becomes effective December 2, 2015. (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. Control of the Lives of Parts’’, dated July 1, 2015, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015; and Task 05– 10–01–800–000, ‘‘Group A Parts Lives— CONFIG–1’’, dated July 1, 2014, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015 with a total accumulated cyclic life that is less than the applicable life limit specified in those Tasks. (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. (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. (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 Task 05–00–01–800–000, ‘‘Recording and Control of the Lives of Parts’’, dated July 1, 2015, of the Rolls-Royce (RR) RB211–535E4– 37/23 Time Limits Manual (TLM), publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015 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 05–10–01–800–000, ‘‘Group A Parts Lives—CONFIG–1’’, dated July 1, 2014, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015 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 part number (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) of this AD, remove each HPT disk before exceeding its applicable life limit as specified in Task 05– 00–01–800–000, ‘‘Recording and Control of the Lives of Parts’’, dated July 1, 2015, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015; and Task 05–10–01–800– 000, ‘‘Group A Parts Lives—CONFIG–1’’, dated July 1, 2014, of the RR RB211–535E4– 37/23 TLM, publication reference T– 211(535)–6RR, Revision 49, dated July 1, 2015. (5) Install an HPT disk eligible for installation. (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 http://www.regulations.gov by searching for and locating it in Docket No. FAA–2015–0593. (b) Affected ADs None. (f) Definition For the purpose of this AD, a part eligible for installation is one with a P/N listed in Task 05–00–01–800–000, ‘‘Recording and PO 00000 Frm 00046 Fmt 4700 Sfmt 4700 (i) 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) Task 05–00–01–800–000, ‘‘Recording and Control of the Lives of Parts’’, dated July 1, 2015, of the Rolls-Royce (RR) RB211– 535E4–37/23 Time Limits Manual (TLM), publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015. (ii) Task 05–10–01–800–000, ‘‘Group A Parts Lives—CONFIG–1’’, dated July 1, 2014, of the RR RB211–535E4–37/23 TLM, publication reference T–211(535)–6RR, Revision 49, dated July 1, 2015. (3) 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. (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/ibrlocations.html. E:\FR\FM\28OCR1.SGM 28OCR1 Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations Issued in Burlington, Massachusetts, on August 21, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–21729 Filed 10–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4207; Directorate Identifier 2015–NM–123–AD; Amendment 39–18304; AD 2015–21–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 2015–16– 01 for certain The Boeing Company Model airplanes. AD 2015–16–01 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2015–16–01 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. This AD retains all actions required by AD 2015–16–01. This AD was prompted by the discovery of a typographical error in AD 2015–16–01 that referred to a nonexistent paragraph. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane. DATES: This AD is effective November 12, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 15, 2015 (80 FR 48013, August 11, 2015). The Director of the Federal Register approved the incorporation by reference Lhorne on DSK5TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 15:03 Oct 27, 2015 Jkt 238001 of certain other publications listed in this AD as of November 7, 2012 (77 FR 60296, October 3, 2012). We must receive any comments on this AD by December 14, 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 http://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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this 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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4207. 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–2015– 4207; 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 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: Francis Smith, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6596; fax: 425–917–6590; email: Francis.Smith@faa.gov. PO 00000 Frm 00047 Fmt 4700 Sfmt 4700 65927 SUPPLEMENTARY INFORMATION: Discussion On July 22, 2015, we issued AD 2015– 16–01, Amendment 39–18226 (80 FR 48013, August 11, 2015), for certain The Boeing Company Model 737 airplanes. AD 2015–16–01 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the AWM with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2015–16–01 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. AD 2015– 16–01 resulted from the report of a flightcrew not receiving an aural warning during a lack of cabin pressurization event. We issued AD 2015–16–01 to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane. Actions Since AD 2015–16–01 Was Issued Since we issued AD 2015–16–01, Amendment 39–18226 (80 FR 48013, August 11, 2015), we have discovered a typographical error in paragraph (j)(1)(iii) of AD 2015–16–01. That error referred to paragraph (j)(4), which is a paragraph that does not exist in AD 2015–16–01. The correct reference is paragraph (j)(1)(iv) of AD 2015–16–01. We have changed paragraph (j)(1)(iii) of this AD accordingly. We have also revised paragraph (g)(2) of this AD to remove a limitation to use only Boeing Special Attention Service Bulletin 737–21–1165, Revision 3, dated July 16, 2014, after the effective date of AD 2015–16–01, Amendment 39–18226 (80 FR 48013, August 11, 2015). Related Service Information Under 1 CFR Part 51 We reviewed the following service information: • Boeing Alert Service Bulletin 737– 31A1325, Revision 2, dated June 5, 2014. • Boeing Alert Service Bulletin 737– 31A1332, Revision 4, dated October 31, 2013. E:\FR\FM\28OCR1.SGM 28OCR1

Agencies

[Federal Register Volume 80, Number 208 (Wednesday, October 28, 2015)]
[Rules and Regulations]
[Pages 65925-65927]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21729]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0593; Directorate Identifier 2015-NE-08-AD; 
Amendment 39-18254; AD 2015-17-21]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting 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 AD requires reducing the cyclic life limits 
for certain high-pressure turbine (HPT) disks, removing those disks 
that have exceeded the new life limit, and replacing them with 
serviceable parts. This AD was prompted by RR updating the life limits 
for certain 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.

DATES: This AD becomes effective December 2, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 2, 
2015.

ADDRESSES: For 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. 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. It is also available on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-0593.

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-2015-
0593; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the mandatory continuing airworthiness information 
(MCAI), 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: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on April 29, 2015 (80 FR 
23737). The NPRM proposed 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 23737, April 29, 
2015).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

Related Service Information Under 1 CFR Part 51

    We reviewed Task 05-00-01-800-000, ``Recording and Control of the 
Lives of Parts'', dated July 1, 2015, of the RR RB211-535E4-37/23 TLM, 
publication reference T-211(535)-6RR, Revision 49, dated July 1, 2015; 
and Task 05-10-01-800-000, ``Group A Parts Lives--CONFIG-1'', dated 
July 1, 2014, of the RR RB211-535E4-37/23 TLM, publication reference T-
211(535)-6RR, Revision 49, dated July 1, 2015. This service information 
provides revised life limits for the affected HPT 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.

Related Service Information

    We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211-
72-G188, Revision No. 1, dated October 30, 2013. The NMSB describes the 
updated lifing analysis of the affected HPT disks.

Costs of Compliance

    We estimate that this 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 AD. The average labor rate is $85 per hour. 
The pro-rated cost of required parts would be about $12,213 per engine. 
Based on these figures, we estimate the cost of this 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.

[[Page 65926]]

    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 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 this AD:
    (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.

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):

2015-17-21 Rolls-Royce plc: Amendment 39-18254; Docket No. FAA-2015-
0593; Directorate Identifier 2015-NE-08-AD.

(a) Effective Date

    This AD becomes effective December 2, 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 Task 05-00-01-800-
000, ``Recording and Control of the Lives of Parts'', dated July 1, 
2015, of the Rolls-Royce (RR) RB211-535E4-37/23 Time Limits Manual 
(TLM), publication reference T-211(535)-6RR, Revision 49, dated July 
1, 2015 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 05-10-01-800-000, 
``Group A Parts Lives--CONFIG-1'', dated July 1, 2014, of the RR 
RB211-535E4-37/23 TLM, publication reference T-211(535)-6RR, 
Revision 49, dated July 1, 2015 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 
part number (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) of this AD, remove each HPT disk before exceeding 
its applicable life limit as specified in Task 05-00-01-800-000, 
``Recording and Control of the Lives of Parts'', dated July 1, 2015, 
of the RR RB211-535E4-37/23 TLM, publication reference T-211(535)-
6RR, Revision 49, dated July 1, 2015; and Task 05-10-01-800-000, 
``Group A Parts Lives--CONFIG-1'', dated July 1, 2014, of the RR 
RB211-535E4-37/23 TLM, publication reference T-211(535)-6RR, 
Revision 49, dated July 1, 2015.
    (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 P/N listed in Task 05-00-01-800-000, ``Recording and 
Control of the Lives of Parts'', dated July 1, 2015, of the RR 
RB211-535E4-37/23 TLM, publication reference T-211(535)-6RR, 
Revision 49, dated July 1, 2015; and Task 05-10-01-800-000, ``Group 
A Parts Lives--CONFIG-1'', dated July 1, 2014, of the RR RB211-
535E4-37/23 TLM, publication reference T-211(535)-6RR, Revision 49, 
dated July 1, 2015 with a total accumulated cyclic life that is less 
than the applicable life limit specified in those Tasks.

(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 http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2015-0593.

(i) 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) Task 05-00-01-800-000, ``Recording and Control of the Lives 
of Parts'', dated July 1, 2015, of the Rolls-Royce (RR) RB211-535E4-
37/23 Time Limits Manual (TLM), publication reference T-211(535)-
6RR, Revision 49, dated July 1, 2015.
    (ii) Task 05-10-01-800-000, ``Group A Parts Lives--CONFIG-1'', 
dated July 1, 2014, of the RR RB211-535E4-37/23 TLM, publication 
reference T-211(535)-6RR, Revision 49, dated July 1, 2015.
    (3) 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.
    (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.



[[Page 65927]]


    Issued in Burlington, Massachusetts, on August 21, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-21729 Filed 10-27-15; 8:45 am]
 BILLING CODE 4910-13-P