Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 39956-39958 [2014-16184]

Download as PDF 39956 Federal Register / Vol. 79, No. 133 / Friday, July 11, 2014 / Rules and Regulations distribution of power and responsibilities among the various levels of government. Therefore, in accordance with section 6 of Executive Order 13132, the Department has determined that this rule does not have sufficient federalism implications to warrant preparation of a federalism summary impact statement. F. Executive Order 12988 (Civil Justice Reform) This rule has been prepared in accordance with the standards in sections 3(a) and 3(b)(2) of Executive Order 12988. G. Paperwork Reduction Act The provisions of the Paperwork Reduction Act of 1995, Public Law 104– 13, 44 U.S.C. chapter 35, and its implementing regulations, 5 CFR part 1320, do not apply to this interim rule because there are no new or revised recordkeeping or reporting requirements. H. Congressional Review Act This action pertains to agency management and personnel and, accordingly, is not a ‘‘rule’’ as that term is used by the Congressional Review Act (CRA) (Subtitle E of the Small Business Regulatory Enforcement Fairness Act (SBREFA)), 5 U.S.C. 804(3). Therefore, the reports to Congress and the Government Accountability Office specified by 5 U.S.C. 801 are not required. List of Subjects in 8 CFR Part 1003 Administrative practice and procedure, Aliens, Immigration, Legal services, Organization and functions (Government agencies). Accordingly, for the reasons stated in the preamble, the Attorney General amends part 1003 of chapter V of title 8 of the Code of Federal Regulations as follows: PART 1003—EXECUTIVE OFFICE FOR IMMIGRATION REVIEW 1. The authority citation for part 1003 continues to read as follows: tkelley on DSK3SPTVN1PROD with RULES ■ Authority: 5 U.S.C. 301; 6 U.S.C. 521; 8 U.S.C. 1101, 1103, 1154, 1155, 1158, 1182, 1226, 1229, 1229a, 1229b, 1229c, 1231, 1254a, 1255, 1324d, 1330, 1361, 1362; 28 U.S.C. 509, 510, 1746; sec. 2 Reorg. Plan No. 2 of 1950; 3 CFR, 1949–1953 Comp., p. 1002; section 203 of Pub. L. 105–100, 111 Stat. 2196–200; sections 1506 and 1510 of Pub. L. 106–386, 114 Stat. 1527–29, 1531–32; section 1505 of Pub. L. 106–554, 114 Stat. 2763A– 326 to –328. § 1003.10 Immigration judges. * * * * (e) Temporary immigration judges. (1) Designation. The Director is authorized to designate or select temporary immigration judges as provided in this paragraph (e). (i) The Director may designate or select, with the approval of the Attorney General, former Board members, former immigration judges, administrative law judges employed within or retired from EOIR, and administrative law judges from other Executive Branch agencies to serve as temporary immigration judges for renewable terms not to exceed six months. Administrative law judges from other Executive Branch agencies must have the consent of their agencies to be designated as temporary immigration judges. (ii) In addition, the Director may designate, with the approval of the Attorney General, Department of Justice attorneys with at least 10 years of legal experience in the field of immigration law to serve as temporary immigration judges for renewable terms not to exceed six months. (2) Authority. A temporary immigration judge shall have the authority of an immigration judge to adjudicate assigned cases and administer immigration court matters, as provided in the immigration laws and regulations, subject to paragraph (e)(3) of this section. (3) Assignment of temporary immigration judges. The Chief Immigration Judge is responsible for the overall oversight and management of the utilization of temporary immigration judges and for evaluating the results of the process. The Chief Immigration Judge shall ensure that each temporary immigration judge has received a suitable level of training to enable the temporary immigration judge to carry out the duties assigned. [FR Doc. 2014–16279 Filed 7–10–14; 8:45 am] BILLING CODE 4410–30–P 2. Revise § 1003.10 by adding a new paragraph (e), to read as follows: 16:49 Jul 10, 2014 Jkt 232001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0876; Directorate Identifier 2013–NE–27–AD; Amendment 39– 17895; AD 2014–14–01] 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 Trent 768– 60, 772–60, and 772B–60 turbofan engines. This AD requires modification of the engine by removing an electronic engine control (EEC) incorporating EEC software standard A14 or earlier and installing an EEC eligible for installation. This AD was prompted by an uncontained multiple turbine blade failure on an RR RB211 Trent 772B turbofan engine. We are issuing this AD to prevent failure of the intermediatepressure (IP) turbine disk drive arm or burst of the high-pressure turbine disk, which could lead to uncontained engine failure and damage to the airplane. DATES: This AD becomes effective August 15, 2014. ADDRESSES: For service information identified in this AD, contact RollsRoyce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332–242424; fax: 011– 44–1332–249936; email: https:// www.rolls-royce.com/contact/civil_ team.jsp; or Web site: https:// www.aeromanager.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781– 238–7125. SUMMARY: Examining the AD Docket Dated: July 8, 2014. James M. Cole, Deputy Attorney General. ■ VerDate Mar<15>2010 DEPARTMENT OF TRANSPORTATION * You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0876; 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 E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 79, No. 133 / Friday, July 11, 2014 / Rules and Regulations 39957 Conclusion Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Discussion Costs of Compliance 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 March 3, 2014 (79 FR 11722). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: We estimate that this AD affects about 72 engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 hour per engine to comply with this AD. The average labor rate is $85 per hour. There are no required parts. Based on these figures, we estimate the cost of this AD on U.S. operators to be $6,120. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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: We disagree. EASA AD 2013–0190, dated August 20, 2013 required compliance by December 31, 2018. We proposed compliance at next shop visit or December 31, 2018, whichever comes first, to achieve more timely mitigation of the unsafe condition. We did not change this AD. An operator of an A330 aeroplane fitted with RR Trent 772B engines experienced an engine uncontained multiple turbine blade failure. Investigation results showed that High-Pressure/Intermediate-Pressure (HP/IP) oil vent tubes may be affected by carbon deposit and may also be damaged by their outer heat shields, which in this case led to combustion inside the tube. The consequent chain of events resulted in an engine internal fire which caused the failure of the IP turbine disc drive arm. This condition, if not corrected, could lead to uncontained multiple turbine blade failures or an HP/IP turbine disc burst, possibly resulting in damage to, and reduced control of, the aeroplane. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Modify Description of Failure Mode tkelley on DSK3SPTVN1PROD with RULES RR requested that we define the failure mode as IP turbine disc drive arm failure and multiple IP turbine blade release to be consistent with descriptions in the RR service bulletin and the European Aviation Safety Agency (EASA) AD. We disagree. EASA AD 2013–0190, dated August 20, 2013, states that the failure mode is multiple turbine blade failures or HP/IP turbine disc burst. We did not change this AD. Request That FAA Require the Same Compliance Date as the EASA AD RR requested that we modify the compliance date to be consistent with the compliance date required in EASA AD 2013–0190, dated August 20, 2013. VerDate Mar<15>2010 16:49 Jul 10, 2014 Jkt 232001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–14–01 Rolls-Royce plc: Amendment 39–17895; Docket No. FAA–2013–0876; Directorate Identifier 2013–NE–27–AD. (a) Effective Date This AD becomes effective August 15, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211 Trent 768–60, 772–60, and 772B–60 turbofan engines prior to engine serial number 42066. (d) Reason This AD was prompted by an uncontained multiple turbine blade failure on an RR RB211 Trent 772B turbofan engine. We are issuing this AD to prevent failure of the intermediate-pressure turbine disc drive arm or burst of the high-pressure turbine disk, which could lead to uncontained engine failure and damage to the airplane. (e) Actions and Compliance After the effective date of this AD, at the next engine shop visit or by December 31, 2018, whichever occurs first, modify the engine by removing any electronic engine control (EEC) that incorporates EEC software standard A14 or earlier and installing an EEC eligible for installation. (f) Installation Prohibition After modification of an engine as required by paragraph (e) of this AD, do not install an EEC with software standard A14 or earlier into that engine. E:\FR\FM\11JYR1.SGM 11JYR1 39958 Federal Register / Vol. 79, No. 133 / Friday, July 11, 2014 / Rules and Regulations (g) Definitions DEPARTMENT OF TRANSPORTATION (1) For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (2) For the purpose of this AD, an EEC ‘‘eligible for installation’’ is any EEC that does not contain software standard A14 or earlier. (h) Credit for Previous Actions (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) 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 2013–0190, dated August 20, 2013, for more information. You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/ #!docketDetail;D=FAA-2013-0876. (3) RR Alert Service Bulletin No. RB.211– 73–AG829, dated April 18, 2012, which is not incorporated by reference in this AD, can be obtained from Rolls-Royce plc, using the contact information in paragraph (j)(4) of this AD. (4) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–249936; email: https://www.rolls-royce.com/contact/civil_ team.jsp; or Web site: 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. tkelley on DSK3SPTVN1PROD with RULES (k) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on June 30, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–16184 Filed 7–10–14; 8:45 am] BILLING CODE 4910–13–P 16:49 Jul 10, 2014 14 CFR Part 39 [Docket No. FAA–2013–1059; Directorate Identifier 2013–NE–36–AD; Amendment 39– 17896; AD 2014–14–02] Jkt 232001 Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7117; fax: 781–238– 7199; email: kevin.dickert@faa.gov. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Discussion Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop Engines 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 March 21, 2014 (79 FR 15707). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: If before the effective date of this AD you removed from an engine any EEC that had EEC software standard A14 or earlier and your engine no longer has an EEC with software standard A14 or earlier, you have met the requirements of this AD. VerDate Mar<15>2010 Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW120, PW121, PW121A, PW124B, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD requires removal of the O-ring seal from the fuel manifold fitting. This AD was prompted by reports of fuel leaks at the interface between the fuel manifold and the fuel nozzle that resulted in engine fire. We are issuing this AD to prevent in-flight fuel leakage, which could lead to engine fire, damage to the engine, and damage to the airplane. DATES: This AD becomes effective August 15, 2014. ADDRESSES: For service information identified in this AD, contact Pratt & Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, J4G 1A1; phone: 800–268–8000; fax: 450–647–2888; Web site: www.pwc.ca. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. SUMMARY: 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–2013– 1059; 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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 There have been reported incidences of fuel leaks at the interface between the flexible fuel manifold and the fuel nozzle. On occasion, these events resulted in an engine fire on PW100 series engine installations. The data indicates that nearly all of the subject manifold fuel leaks were caused by inadequate B-nut torque application during installation, after maintenance work was performed on the fuel nozzle/manifold. Sealing of the fitting connections between the fuel manifolds and the fuel nozzle adapters is achieved through conical metalto-metal surface seating. An additional O-ring seal on the fitting was installed to arrest any fuel leak past the conical sealing surfaces. Inservice experience has indicated that leakage past the sealing surfaces, as a result of improper torquing during installation of the manifold, may not be immediately evident until the failure of the O-ring seal allows the fuel to leak into the nacelle area. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Mandate Incorporation of Service Bulletins UTair Aviation JSC requested that we mandate incorporation of P&WC Service Bulletins (SBs) PW100–72–21841, Revision No. 1, dated November 29, 2013; and PW100–72–21848, Revision No. 1, dated November 15, 2013, in the AD. The commenter suggested that incorporation by reference of these SBs would improve safety compared to the compliance proposed in the NPRM (79 FR 15707, March 21, 2014). We disagree. We note that prior to implementation of these SBs, an operator would need to remove the affected O-ring seals, which would fulfill the requirements of this AD. We do not find that requiring accomplishing these service bulletins through incorporation by reference in this AD is necessary. We did not change this AD. E:\FR\FM\11JYR1.SGM 11JYR1

Agencies

[Federal Register Volume 79, Number 133 (Friday, July 11, 2014)]
[Rules and Regulations]
[Pages 39956-39958]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16184]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0876; Directorate Identifier 2013-NE-27-AD; 
Amendment 39-17895; AD 2014-14-01]
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 Trent 768-60, 772-60, and 772B-60 turbofan 
engines. This AD requires modification of the engine by removing an 
electronic engine control (EEC) incorporating EEC software standard A14 
or earlier and installing an EEC eligible for installation. This AD was 
prompted by an uncontained multiple turbine blade failure on an RR 
RB211 Trent 772B turbofan engine. We are issuing this AD to prevent 
failure of the intermediate-pressure (IP) turbine disk drive arm or 
burst of the high-pressure turbine disk, which could lead to 
uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective August 15, 2014.

ADDRESSES: For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, 
DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: 
https://www.rolls-royce.com/contact/civil_team.jsp; or Web site: 
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-2013-
0876; 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

[[Page 39957]]

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 March 3, 2014 (79 FR 
11722). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    An operator of an A330 aeroplane fitted with RR Trent 772B 
engines experienced an engine uncontained multiple turbine blade 
failure. Investigation results showed that High-Pressure/
Intermediate-Pressure (HP/IP) oil vent tubes may be affected by 
carbon deposit and may also be damaged by their outer heat shields, 
which in this case led to combustion inside the tube. The consequent 
chain of events resulted in an engine internal fire which caused the 
failure of the IP turbine disc drive arm.
    This condition, if not corrected, could lead to uncontained 
multiple turbine blade failures or an HP/IP turbine disc burst, 
possibly resulting in damage to, and reduced control of, the 
aeroplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Modify Description of Failure Mode

    RR requested that we define the failure mode as IP turbine disc 
drive arm failure and multiple IP turbine blade release to be 
consistent with descriptions in the RR service bulletin and the 
European Aviation Safety Agency (EASA) AD.
    We disagree. EASA AD 2013-0190, dated August 20, 2013, states that 
the failure mode is multiple turbine blade failures or HP/IP turbine 
disc burst. We did not change this AD.

Request That FAA Require the Same Compliance Date as the EASA AD

    RR requested that we modify the compliance date to be consistent 
with the compliance date required in EASA AD 2013-0190, dated August 
20, 2013.
    We disagree. EASA AD 2013-0190, dated August 20, 2013 required 
compliance by December 31, 2018. We proposed compliance at next shop 
visit or December 31, 2018, whichever comes first, to achieve more 
timely mitigation of the unsafe condition. We did not change this AD.

Conclusion

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

Costs of Compliance

    We estimate that this AD affects about 72 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
hour per engine to comply with this AD. The average labor rate is $85 
per hour. There are no required parts. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $6,120.

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:
    (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):

2014-14-01 Rolls-Royce plc: Amendment 39-17895; Docket No. FAA-2013-
0876; Directorate Identifier 2013-NE-27-AD.

(a) Effective Date

    This AD becomes effective August 15, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211 Trent 768-60, 
772-60, and 772B-60 turbofan engines prior to engine serial number 
42066.

(d) Reason

    This AD was prompted by an uncontained multiple turbine blade 
failure on an RR RB211 Trent 772B turbofan engine. We are issuing 
this AD to prevent failure of the intermediate-pressure turbine disc 
drive arm or burst of the high-pressure turbine disk, which could 
lead to uncontained engine failure and damage to the airplane.

(e) Actions and Compliance

    After the effective date of this AD, at the next engine shop 
visit or by December 31, 2018, whichever occurs first, modify the 
engine by removing any electronic engine control (EEC) that 
incorporates EEC software standard A14 or earlier and installing an 
EEC eligible for installation.

(f) Installation Prohibition

    After modification of an engine as required by paragraph (e) of 
this AD, do not install an EEC with software standard A14 or earlier 
into that engine.

[[Page 39958]]

(g) Definitions

    (1) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.
    (2) For the purpose of this AD, an EEC ``eligible for 
installation'' is any EEC that does not contain software standard 
A14 or earlier.

(h) Credit for Previous Actions

    If before the effective date of this AD you removed from an 
engine any EEC that had EEC software standard A14 or earlier and 
your engine no longer has an EEC with software standard A14 or 
earlier, you have met the requirements of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(j) 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 2013-0190, 
dated August 20, 2013, for more information. You may examine the 
MCAI in the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0876.
    (3) RR Alert Service Bulletin No. RB.211-73-AG829, dated April 
18, 2012, which is not incorporated by reference in this AD, can be 
obtained from Rolls-Royce plc, using the contact information in 
paragraph (j)(4) of this AD.
    (4) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email: https://www.rolls-royce.com/contact/civil_team.jsp; 
or Web site: 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.

(k) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on June 30, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-16184 Filed 7-10-14; 8:45 am]
BILLING CODE 4910-13-P

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