### 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:

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.

■ 2. Revise § 1003.10 by adding a new paragraph (e), to read as follows: **§ 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.

Dated: July 8, 2014. James M. Cole, Deputy Attorney General.
[FR Doc. 2014–16279 Filed 7–10–14; 8:45 am]

**BILLING CODE 4410–30–P 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 ADto 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 informationidentified 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: http:// 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 http:// 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


### 39957 Federal Register / Vol. 79, No. 133 / Friday, July 11, 2014 / Rules and Regulations

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** 

■ 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): 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.


### 39958 Federal Register / Vol. 79, No. 133 / Friday, July 11, 2014 / Rules and Regulations

(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 http://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: http://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 DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1059; Directorate Identifier 2013–NE–36–AD; Amendment 39–**  **17896; AD 2014–14–02]**

**RIN 2120–AA64**

**Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop**  **Engines**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  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. 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–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. **FOR FURTHER INFORMATION CONTACT :**  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 :** 

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 21, 2014 (79 FR 15707). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

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 nozzleadapters is achieved through conical metalto-metal surface seating. An additional O-ring seal on the fitting was installed to arrest anyfuel 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.