### 69037 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations

FAA–2014–0256; Directorate Identifier 2013–NM–214–AD.
(a) Effective Date

This AD is effective December 26, 2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 777–200LR, –300, –300ER, and 777F series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 777–27–0115, dated May 22,
2013. (d) Subject

Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

This AD was prompted by reports of dual pitch rate sensor (PRS) failures causing the primary flight computers to transition from primary mode to secondary mode, resulting in autopilot disconnects. We are issuing this AD to prevent a dual PRS failure that could cause an automatic disengagement of the autopilot and autoland, which may prevent continued safe flight and landing if disengagement occurs at low altitude and the flight crew is unable to safely assume control and execute a go-around or manual landing.
(f) Compliance

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

Within 60 months after the effective date of this AD, inspect to determine the part numbers of all four PRSs, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27– 0115, dated May 22, 2013. For airplanes in group 1, as identified in Boeing Special Attention Service Bulletin 777–27–0115, dated May 22, 2013: A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the PRS can be conclusively determined from that review.
(h) Replacement

If any PRS having P/N 402875–05–01 is found during the inspection required by paragraph (g) of this AD: Before further flight, replace with a PRS having P/N 402875–03– 01, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27–0115, dated May 22,
2013.
(i) Parts Installation Prohibition

As of the effective date of this AD, no person may install a PRS having P/N 402875–05–01 on any airplane.
(j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov

.

(2) 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.

(k) Related Information

For more information about this AD, contact Douglas Tsuji, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6546; fax: 425–917– 6590; email: douglas.tsuji@faa.gov.
(l) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Boeing Special Attention Service Bulletin 777–27–0115, dated May 22, 2013.

(ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com.

(4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(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 November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–26831 Filed 11–19–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0489; Directorate Identifier 2014–NM–048–AD; Amendment**  **39–18022; AD 2014–23–06]**

**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 certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the main landing gear (MLG). This AD requires modifying the MLG by installing a new bracket on the left and right lower aft-wing planks. We are issuing this AD to prevent incorrect installation of the brake hydraulic lines, which could cause the brakes and the anti-skid system to operate incorrectly, and consequent catastrophic failure of the airplane during a high-speed rejected takeoff.

**DATES :**  This AD becomes effective December 26, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 26, 2014.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0489 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 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.


### 69038 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations

**FOR FURTHER INFORMATION CONTACT :**  Fabio Buttitta, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7303; 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 certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on August 4, 2014 (79 FR 45135).

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–10, dated February 12, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states:

Cases of inboard and outboard hydraulic brake lines connected to the incorrect port of the swivel assembly on the main landing gear were found in service, including a runway overrun event. Cross-connected brake hydraulic lines can cause the brakes and/or the anti-skid system to operate incorrectly. During a high speed rejected take-off, inability for the brakes to operate correctly could be catastrophic.

This [Canadian] AD mandates themodification to prevent inadvertent crossconnection of the inboard and outboard hydraulic brake lines.

The required action in this AD includes installing a new bracket on the left and right lower aft-wing planks of the MLG. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0489-
0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 45135, August 4, 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 45135, August 4, 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 45135, August 4, 2014). Costs of Compliance

We estimate that this AD affects 526 airplanes of U.S. registry.

We also estimate that it will take about 6 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 $375 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $465,510, or $885 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-2014-0489; 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):
2014–23–06 Bombardier, Inc.: Amendment 39–18022. Docket No. FAA–2014–0489; Directorate Identifier 2014–NM–048–AD.

(a) Effective Date

This AD becomes effective December 26,
2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent.
(d) Subject

Air Transport Association (ATA) of America Code 32, Landing Gear.

(e) Reason

This AD was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the main landing gear (MLG). We are issuing this AD to prevent incorrect installation of the brake hydraulic lines, which could cause the brakes and the anti-skid system to operate incorrectly, and consequent catastrophic failure of theairplane during a high-speed rejected takeoff.


### 69039 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations

(f) Compliance

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

Within 6,600 flight hours after the effective date of this AD, but no later than 36 months after the effective date of this AD: Modify the MLG by installing a new bracket on the left and right lower aft-wing planks, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–32–110, dated December 19, 2013.

(h) Other FAA AD Provisions

The following provisions also apply to this AD:

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

(i) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–10, dated February 12, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0489-0002.
(j) 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–32– 110, dated December 19, 2013.

(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 November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–26985 Filed 11–19–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0472; Directorate Identifier 2013–SW–040–AD; Amendment**  **39–18018; AD 2014–23–02]**

**RIN 2120–AA64**

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

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD requires repetitively performing a magnetic particle inspection of the Gleason crown for a crack. This AD was prompted by a report of a crack that was found on a Gleason crown, which if not detected, could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective December 26, 2014.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of December 26, 2014.

**ADDRESSES :**  For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39–0331– 664757; fax 39–0331–664680; or at http://www.agustawestland.com/ technical-bullettins. 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. 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 :**  Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email rao.edupuganti@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On July 16, 2014, at 79 FR 41462, 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 A109E, A109K2, A119, and AW119 MKII helicopters with a main transmission, part number (P/N) 109–0400–03–103, 109–0400–05–103, and 109–0400–03–109, with a Gleason crown, P/N 109–0403–07–103, installed. The NPRM proposed to require, for main transmissions with 2,400 or more hours time-in-service (TIS), performing repetitive magnetic particle inspections of the Gleason crown for a crack. If there is a crack, the NPRM proposed replacing the Gleason crown assembly before further flight. The NPRM also proposed to prohibit installing a Gleason crown, P/N 109–0403–07–103, or a Gleason crown assembly, P/N 109–0401–27–101 or P/N 109–0401–27–109, on any helicopter. The proposed requirements were intended to detect a crack, which could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.

The NPRM was prompted by AD No. 2013–0118, dated June 3, 2013, issued by EASA, which is the Technical Agent