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(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


### 69040 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations

for the Member States of the European Union, to correct an unsafe condition for Agusta Model A109K2, A109E, A119, and AW119MKII helicopters. EASA advises that during an overhaul of an A119 main transmission, P/N 109– 0400–05–103, a crack on the Gleason crown, P/N 109–0403–07–103, was found. EASA further states that the crack originated from the bottom of one of the 40 threaded holes in the Gleason crown, and that this part-numbered Gleason crown is also installed on Model A109 helicopters. EASA states that this condition, if not corrected, could cause damage to or loss of the main rotor drive and loss of control of the helicopter. To correct this unsafe condition, EASA AD No. 2013–0118 requires repetitive magnetic particle inspections of the Gleason crown and, if there is a crack, replacing the Gleason crown with a different part-numbered Gleason crown. EASA AD No. 2013– 0118 also prohibits 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, as Gleason crown, P/ N 109–0403–07–103, is a component of these assemblies.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (79 FR 41462, July 16, 2014).

FAA’s Determination

These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed, except for minor editorial changes. These changes are consistent with the intent of the proposals in the NPRM (79 FR 41462, July 16, 2014) and will not increase the economic burden on any operator nor increase the scope of the AD.

Differences Between This AD and the EASA AD

This AD requires compliance within 200 hours TIS for main transmissions with 2,400 or more hours. The EASA AD requires different compliance times, depending on the number of flight hours the transmission has accumulated.

Related Service Information

We reviewed Agusta Bollettino Tecnico (BT) No. 109EP–128 for Model A109E helicopters, Agusta BT No. 109K–57 for Model A109K2 helicopters, and Agusta BT No. 119–058 for Model A119 and AW119MKII helicopters, each Revision A and dated May 28, 2013. Each BT describes procedures for performing a magnetic particle inspection on the Gleason crown, P/N 109–0403–07–103, for a crack. If there is a crack, each BT specifies replacing the Gleason crown assembly with a Gleason crown assembly, P/N 109–0401–27–107.

We also reviewed Agusta BT No. 109EP–126 for Model A109E helicopters, Agusta BT No. 109K–56 for Model A109K2 helicopters, and Agusta BT No. 119–053 for Model A119 and AW119MKII helicopters, each dated December 20, 2012. These BTs contain procedures for upgrading the transmission system by replacing the Gleason crown assembly with a Gleason crown assembly, P/N 109–0401–27–107. Costs of Compliance

We estimate that this AD affects 218 helicopters of U.S. registry. We estimate the following costs to comply with this AD. At an average labor rate of $85 per hour, magnetic particle inspecting theGleason crown requires about 24 workhours, for an estimated cost per helicopter of $2,040, and a total cost of $444,720 for the U.S. fleet, per inspection cycle.

If required, replacing the Gleasoncrown assembly requires about 24 workhours, and required parts will cost $29,000, for a cost per helicopter of $31,040.

According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 helicopters identified in this rulemaking action. Regulatory Findings

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 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.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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):
2014–23–02 Agusta S.p.A. Helicopters (Type Certificate Currently Held By AgustaWestland S.p.A.) (Agusta): Amendment 39–18018; Docket No. FAA–2014–0472; Directorate Identifier 2013–SW–040–AD.


### 69041 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations

(a) Applicability

This AD applies 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, or 109–0400–03–109, with a Gleason crown, P/ N 109–0403–07–103, installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a Gleason crown. This condition could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective December 26,

2014. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

(1) For main transmissions with 2,400 or more hours time-in-service (TIS), within 200 hours TIS and thereafter at intervals not exceeding 1,600 hours TIS, magnetic particle inspect the Gleason crown, P/N 109–0403– 07–103, for a crack by following the procedures in:

(i) Annex 1 of Agusta Bollettino Tecnico (BT) No. 109EP–128, Revision A, dated May 28, 2013, for Model A109E helicopters;

(ii) Annex 1 of Agusta BT No. 109K–57, Revision A, dated May 28, 2013, for Model A109K2 helicopters; or

(iii) Annex 1 of Agusta BT No. 119–058, Revision A, dated May 28, 2013, for Model A119 and AW119MKII helicopters.

(2) If there is a crack, before further flight, replace the Gleason crown assembly with a Gleason Crown assembly, P/N 109–0401–27– 107. Replacing the Gleason crown assembly with P/N 109–0401–27–107 is terminating action for the inspection requirements of this AD.

(3) After the effective date of this AD, do not install 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.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: 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.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013–0118, dated June 3, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No.
FAA–2014–0472.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor Gearbox.
(i) 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) AgustaWestland Bollettino Tecnico No. 109EP–128, Revision A, dated May 28, 2013.

(ii) AgustaWestland Bollettino Tecnico No. 109K–57, Revision A, dated May 28, 2013.

(iii) AgustaWestland Bollettino Tecnico No. 119–058, Revision A, dated May 28,

2013.

(3) For AgustaWestland 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/technicalbullettins.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(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 Fort Worth, Texas, on October 30,

2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2014–26825 Filed 11–19–14; 8:45 am]

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

**Bureau of Economic Analysis**

**15 CFR Part 801**

**[Docket No. 1206013202–4700–01]**

**RIN 0691–AA83**

**Direct Investment Surveys: BE–10, Benchmark Survey of U.S. Direct**  **Investment Abroad**

**AGENCY :**  Bureau of Economic Analysis, Commerce.

**ACTION :**  Final rule.

**SUMMARY :**  This final rule amends regulations of the Department of Commerce’s Bureau of Economic Analysis (BEA) to reinstate reporting requirements for the 2014 BE–10, Benchmark Survey of U.S. Direct Investment Abroad. Benchmark surveys are conducted every five years; the prior survey covered 2009. The benchmark survey covers the universe of U.S. direct investment abroad, and is BEA’s most comprehensive survey of such investment in terms of subject matter. For the 2014 benchmark survey, BEA will make changes in the data items collected. No changes will be made to the reporting requirements for the survey. This mandatory survey will be conducted under the authority of the International Investment and Trade in Services Survey Act (the Act). Unlike many other BEA surveys conducted pursuant to the Act, a response will be required from persons subject to the reporting requirements of the BE–10, Benchmark Survey of U.S. Direct Investment Abroad, whether or not they are contacted by BEA, in order to ensure that respondents subject to the requirements for U.S. direct investment abroad are identified.

**DATES :**  This final rule is effective December 22, 2014.

**FOR FURTHER INFORMATION CONTACT :**  Patricia Abaroa, Chief, Direct Investment Division (BE–50), Bureau of Economic Analysis, U.S. Department of Commerce, Washington, DC 20230; phone (202) 606–9591.

**SUPPLEMENTARY INFORMATION :**  On August 14, 2014, BEA published a notice of proposed rulemaking that set forth revised reporting criteria for the BE–10, Benchmark Survey of U.S. Direct Investment Abroad (79 FR 47599– 47603). On September 9, 2014, BEA published a correction to the notice of proposed rulemaking to correct the Regulation Identifier Number (RIN) that was listed in the first notice (79 FR 53355). BEA received two comments on the proposed rule.