Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 18083-18084 [2015-07492]

Download as PDF 18083 Rules and Regulations Federal Register Vol. 80, No. 64 Friday, April 3, 2015 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0904; Directorate Identifier 2014–NE–14–AD; Amendment 39– 18129; AD 2015–07–01] 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 certain Rolls-Royce plc (RR) RB211–524 turbofan engines with certain part number (P/N) low-pressure turbine (LPT) stage 3 turbine blades installed. This AD requires implementation of a life limit for certain P/N LPT stage 3 turbine blades and replacement of affected blades that reach or exceed the life limit. This AD was prompted by reports of LPT stage 3 turbine blade failures, release of blades, and subsequent in-flight shutdowns. We are issuing this AD to prevent failure of LPT stage 3 turbine blades and subsequent release of blade debris, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. DATES: This AD becomes effective May 8, 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: 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 asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:21 Apr 02, 2015 Jkt 235001 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2014–0904. 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–2014– 0904; 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: Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7765; fax: 781–238– 7199; email: kenneth.steeves@faa.gov. 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 December 2, 2014 (79 FR 71363). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Since 2006, a number of low pressure turbine (LPT) Stage 3 blade failures have been reported, each resulting in engine inflight shut-down. Engineering analysis on those occurrences indicates that blades with an accumulated life of 11,000 flight cycles (FC) or more have an increased risk of failure. This condition, if not detected and corrected, could lead to release of LPT Stage 3 blade debris and consequent (partial or complete) loss of engine power, possibly resulting in reduced control of the aeroplane. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter supports the NPRM (79 FR 71363, December 2, 2014). Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD affects 2 engines installed on airplanes of U.S. registry. We also estimate that it will take about 120 hours per engine to comply with this AD. The average labor rate is $85 per hour. Parts cost is zero. Based on these figures, we estimate the cost of this AD on U.S. operators to be $20,400. 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 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: E:\FR\FM\03APR1.SGM 03APR1 18084 Federal Register / Vol. 80, No. 64 / Friday, April 3, 2015 / Rules and Regulations (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. LK55386, LK86483, or LK86503, that exceeds 11,000 flight cycles since new. (2) If you cannot determine the accumulated flight cycles, remove any LPT stage 3 turbine blade, P/N LK55386, LK86483, or LK86503, within 200 flight cycles after the effective date of this AD. (3) After the effective date of this AD, do not install any LPT stage 3 turbine blade, P/ N LK55386, LK86483, or LK86503, on any engine if the blade has accumulated 11,000 or more flight cycles since new. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (g) Related Information PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2015–07–01 Rolls-Royce plc: Amendment 39–18129; Docket No. FAA–2014–0904; Directorate Identifier 2014–NE–14–AD. (a) Effective Date This AD becomes effective May 8, 2015. (b) Affected ADs None. asabaliauskas on DSK5VPTVN1PROD with RULES (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211–524B–02, RB211–524B–B–02, RB211–524B2–19, RB211–524B2–B–19, RB211–524B3–02, RB211–524C2–19, and RB211–524C2–B–19 turbofan engines with low-pressure turbine (LPT) stage 3 turbine blade, part number (P/N) LK55386, LK86483, or LK86503, installed. (d) Reason This AD was prompted by reports of LPT stage 3 turbine blade failure, release of blades, and subsequent in-flight shutdown. We are issuing this AD to prevent failure of LPT stage 3 turbine blades and subsequent release of blade debris, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Remove from service before further flight any LPT stage 3 turbine blade, P/N VerDate Sep<11>2014 16:21 Apr 02, 2015 Jkt 235001 (f) Alternative Methods of Compliance (AMOCs) (1) For more information about this AD, contact Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7765; fax: 781–238– 7199; email: kenneth.steeves@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2014–0210, dated September 19, 2014, for more information. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0904-0002. (3) RR Alert Non-Modification Service Bulletin No. RB.211–72–AH790, Revision 1, dated November 5, 2014, which is not incorporated by reference in this AD, can be obtained from Rolls-Royce plc, using the contact information in paragraph (g)(4) of this AD. (4) 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: 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. (h) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on March 26, 2015. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–07492 Filed 4–2–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 95 [Docket No. 31012; Amdt. No. 519] IFR Altitudes; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas. DATES: Effective Date: 0901 UTC, April 30, 2015. FOR FURTHER INFORMATION CONTACT: Harry Hodges, Flight Procedure Standards Branch (AMCAFS–420), Flight Technologies and Programs Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd. Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082 Oklahoma City, OK 73125) telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This amendment to part 95 of the Federal Aviation Regulations (14 CFR part 95) amends, suspends, or revokes IFR altitudes governing the operation of all aircraft in flight over a specified route or any portion of that route, as well as the changeover points (COPs) for Federal airways, jet routes, or direct routes as prescribed in part 95. SUMMARY: The Rule The specified IFR altitudes, when used in conjunction with the prescribed changeover points for those routes, ensure navigation aid coverage that is adequate for safe flight operations and free of frequency interference. The reasons and circumstances that create the need for this amendment involve matters of flight safety and operational efficiency in the National Airspace System, are related to published aeronautical charts that are essential to the user, and provide for the safe and efficient use of the navigable airspace. In addition, those various reasons or E:\FR\FM\03APR1.SGM 03APR1

Agencies

[Federal Register Volume 80, Number 64 (Friday, April 3, 2015)]
[Rules and Regulations]
[Pages 18083-18084]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07492]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

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


Federal Register / Vol. 80, No. 64 / Friday, April 3, 2015 / Rules 
and Regulations

[[Page 18083]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0904; Directorate Identifier 2014-NE-14-AD; 
Amendment 39-18129; AD 2015-07-01]
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 certain 
Rolls-Royce plc (RR) RB211-524 turbofan engines with certain part 
number (P/N) low-pressure turbine (LPT) stage 3 turbine blades 
installed. This AD requires implementation of a life limit for certain 
P/N LPT stage 3 turbine blades and replacement of affected blades that 
reach or exceed the life limit. This AD was prompted by reports of LPT 
stage 3 turbine blade failures, release of blades, and subsequent in-
flight shutdowns. We are issuing this AD to prevent failure of LPT 
stage 3 turbine blades and subsequent release of blade debris, which 
could lead to failure of one or more engines, loss of thrust control, 
and damage to the airplane.

DATES: This AD becomes effective May 8, 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: 
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. It is also available on the Internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2014-0904.

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-2014-
0904; 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: Kenneth Steeves, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7765; 
fax: 781-238-7199; email: kenneth.steeves@faa.gov.

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 December 2, 2014 (79 FR 
71363). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Since 2006, a number of low pressure turbine (LPT) Stage 3 blade 
failures have been reported, each resulting in engine in-flight 
shut-down. Engineering analysis on those occurrences indicates that 
blades with an accumulated life of 11,000 flight cycles (FC) or more 
have an increased risk of failure.
    This condition, if not detected and corrected, could lead to 
release of LPT Stage 3 blade debris and consequent (partial or 
complete) loss of engine power, possibly resulting in reduced 
control of the aeroplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM (79 FR 71363, December 2, 2014).

Conclusion

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

Costs of Compliance

    We estimate that this AD affects 2 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 120 hours 
per engine to comply with this AD. The average labor rate is $85 per 
hour. Parts cost is zero. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $20,400.

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 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:

[[Page 18084]]

    (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):

2015-07-01 Rolls-Royce plc: Amendment 39-18129; Docket No. FAA-2014-
0904; Directorate Identifier 2014-NE-14-AD.

(a) Effective Date

    This AD becomes effective May 8, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-524B-02, 
RB211-524B-B-02, RB211-524B2-19, RB211-524B2-B-19, RB211-524B3-02, 
RB211-524C2-19, and RB211-524C2-B-19 turbofan engines with low-
pressure turbine (LPT) stage 3 turbine blade, part number (P/N) 
LK55386, LK86483, or LK86503, installed.

(d) Reason

    This AD was prompted by reports of LPT stage 3 turbine blade 
failure, release of blades, and subsequent in-flight shutdown. We 
are issuing this AD to prevent failure of LPT stage 3 turbine blades 
and subsequent release of blade debris, which could lead to failure 
of one or more engines, loss of thrust control, and damage to the 
airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service before further flight any LPT stage 3 
turbine blade, P/N LK55386, LK86483, or LK86503, that exceeds 11,000 
flight cycles since new.
    (2) If you cannot determine the accumulated flight cycles, 
remove any LPT stage 3 turbine blade, P/N LK55386, LK86483, or 
LK86503, within 200 flight cycles after the effective date of this 
AD.
    (3) After the effective date of this AD, do not install any LPT 
stage 3 turbine blade, P/N LK55386, LK86483, or LK86503, on any 
engine if the blade has accumulated 11,000 or more flight cycles 
since new.

(f) 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.

(g) Related Information

    (1) For more information about this AD, contact Kenneth Steeves, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7765; fax: 781-238-7199; email: 
kenneth.steeves@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0210, 
dated September 19, 2014, for more information. You may examine the 
MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0904-0002.
    (3) RR Alert Non-Modification Service Bulletin No. RB.211-72-
AH790, Revision 1, dated November 5, 2014, which is not incorporated 
by reference in this AD, can be obtained from Rolls-Royce plc, using 
the contact information in paragraph (g)(4) of this AD.
    (4) 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: 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.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on March 26, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-07492 Filed 4-2-15; 8:45 am]
 BILLING CODE 4910-13-P

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