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examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0142-0002.

(2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (cc)(9) and (cc)(10) of this AD.
(cc) 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 this AD specifies otherwise.

(3) The following service information was approved for IBR on March 17, 2015.

(i) Airbus Service Bulletin A300–57–0255, including Inspection Reporting Form, dated January 13, 2012.

(ii) Airbus Service Bulletin A300–57–6112, including Inspection Reporting Form, dated January 13, 2012.

(iii) Airbus Service Bulletin A310–57– 2090, Revision 02, dated June 18, 2010.

(iv) Airbus Service Bulletin A310–57– 2101, including Inspection Reporting Form, dated January 13, 2012.

(4) The following service information was approved for IBR on September 11, 2012 (77 FR 46937, August 7, 2012).

(i) Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18,
2010.

(ii) Airbus Mandatory Service Bulletin A300–57–0251, including Appendix 01, dated August 8, 2007.

(iii) Airbus Mandatory Service Bulletin A300–57–6106, Revision 03, dated January 26, 2012.

(iv) Airbus Mandatory Service Bulletin A300–57–6107, including Appendix 01, August 8, 2007.

(5) The following service information was approved for IBR on May 29, 2012 (77 FR 24367, April 24, 2012).

(i) Airbus Mandatory Service Bulletin A300–57–0249, Revision 03, dated January 18, 2012.

(ii) Airbus Mandatory Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012.

(6) The following service information was approved for IBR on September 17, 2008 (73 FR 47032, August 13, 2008).

(i) Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007.

(ii) Airbus Service Bulletin A310–57–2091, excluding Appendix 01, dated May 22, 2007.

(iii) Airbus A310 Repair Instruction R572– 49121, Issue C, dated May 2007.

(7) The following service information was approved for IBR on February 6, 2007 (72 FR 2612, January 22, 2007).

(i) Airbus Service Bulletin A310–57A2088, excluding Appendix 01, dated November 6,
2006.

(ii) Reserved. (8) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// www.airbus.com.

(9) You may view this 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.

(10) 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 January 21, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–01710 Filed 2–9–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0750; Directorate Identifier 2014–NM–147–AD; Amendment**  **39–18097; AD 2015–03–01]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of dislodged engine fan cowl panels. This AD requires installing additional attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures. We are issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl panels.

**DATES :**  This AD becomes effective March 17, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 17, 2015.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0750; or in person at the Docket 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.

For service information identified in this AD, contact Bombardier, Inc., 400 Co

ˆ te-Vertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.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–2014–
0750.

**FOR FURTHER INFORMATION CONTACT :**  Andreas Rambalakos, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7345; fax
516–794–5531.

**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 all Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on October 2, 2014 (79 FR 59459).

Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, has issued Canadian Airworthiness Directive CF– 2014–20, dated July 9, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states:

There have been a number of engine fan cowl panel dislodgement incidents reported on the Bombardier CL–600–2B19 aeroplane fleet. The dislodged panels may cause damage to the fuselage and flight control surfaces of the aeroplane. Also, the debris from a dislodged panel may result in runway contamination and has the potential of causing injury on the ground.

Although the majority of the subject panel dislodgements were reported on the first or second flight after an engine maintenance task was performed that required removal and reinstallation of the subject panels, the frequency of the dislodgements indicates that the existing attachment design is prone to human (maintenance) error.

Bombardier has attempted to mitigate this issue by issuing maintenance advisories emphasizing the proper installation of engine fan cowl panels. In order to further mitigate the potential safety hazard of the subject panel dislodgement, Bombardier has issued


### 7299 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations

Service Bulletin (SB) 601R–71–034 to install additional fasteners for the attachment of the engine fan cowl panels to the nacelle’s
structure.

This [Canadian] AD is issued to mandate compliance with Bombardier SB 601R–71–
034.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0750-
0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 59459, October 2, 2014) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 59459, October 2, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 59459, October 2, 2014).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

We reviewed Bombardier Service Bulletin 601R–71–034, Revision B, dated August 1, 2014. The service information describes procedures for installing additional attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures. This service information is reasonably available; see **ADDRESSES** for ways to access this service information. Costs of Compliance

We estimate that this AD affects 518 airplanes of U.S. registry.

We also estimate that it will take about 9 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $5,248 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $3,114,734, or $6,013 per product. 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 that 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; 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. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0750; 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 Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. 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):
2015–03–01 Bombardier, Inc.: Amendment 39–18097. Docket No. FAA–2014–0750; Directorate Identifier 2014–NM–147–AD.
(a) Effective Date

This AD becomes effective March 17, 2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to all Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, all manufacturer serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason

This AD was prompted by reports of dislodged engine fan cowl panels. We are issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl panels.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Fastener Installation

Within 6,000 flight hours after the effective date of this AD: Install attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–71–034, Revision B, dated August 1,
2014.
(h) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 601R–71–034, dated March 31, 2014; or Service Bulletin 601R–71–034, Revision A, dated April 28, 2014. This service information is not incorporated by reference in this AD.
(i) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft


### 7300 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations

Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO,the approval must include the DAOauthorized signature.
(j) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–20, dated July 9, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0750-0002.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD.
(k) 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 this AD specifies otherwise.

(i) Bombardier Service Bulletin 601R–71– 034, Revision B, dated August 1, 2014.

(ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com.

(4) You may view this 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.

(5) 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 January 30, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–02282 Filed 2–9–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0465; Directorate Identifier 2013–SW–044–AD; Amendment**  **39–18089; AD 2015–02–21]**

**RIN 2120–AA64**

**Airworthiness Directives; Agusta S.p.A. (Type Certificate Currently Held**  **by AgustaWestland S.p.A.) (Agusta) Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Agusta AB139 and AW139 helicopters to require replacing certain single-braidedflexible hydraulic hoses with doublebraided flexible hydraulic hoses. This AD was prompted by occurrences of leaking flexible hydraulic hoses. The actions of this AD are intended to prevent loss of hydraulic power and subsequent loss of helicopter control.

**DATES :**  This AD is effective March 17,
2015.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of March 17, 2015.

**ADDRESSES :**  For service information identified in this AD, contact Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39- 0331–711133; fax 39 0331 711180; or at http://www.agustawestland.com/technicalbullettins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is also available on the Internet
at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0465. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matt.wilbanks@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On July 16, 2014, at 79 FR 41464, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Agusta Model AB139 and AW139 helicopters with a flexible hydraulic hose, part number (P/N) A494AE2E00E0670X, A494AE3E00E0424X, A494AE3E00E0530X, A494AE3E00E0570X, A494AE3E00E0580X, A494AE3E00E0620X, A494AE3E00E0930X, A494AE6E14E0348X, or A494AE6E21E0330X, installed. The NPRM proposed to require replacing these single-braided flexible hydraulic hoses with double-braided flexible hydraulic hoses. The proposed requirements were intended to prevent loss of hydraulic power and subsequent loss of helicopter control.

The NPRM was prompted by AD No. AD No. 2013–0177, dated August 8, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Agusta Model AB139 and AW139 helicopters. EASA advises that leaking hydraulic systemflexible hoses have been reported on inservice helicopters. An investigation indicated that single braided flexible hydraulic hoses, which are part of the original design for Model AB139 and AW139 helicopters, may not be strong enough to cope with the hydraulic system pressure over long periods. If not corrected, this condition could lead to other hydraulic system leaks, possibly resulting in loss of hydraulic power and reduced control of the helicopter, EASA