### 13196 Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations

the Standardized NUHOMS ® Cask System, and the current Amendment No. 11 continues to be effective for existing users. While current CoC users may comply with the new requirements in Amendment No. 13, this would be a voluntary decision on the part of current users. For these reasons, Amendment No. 13 to CoC No. 1004 does not constitute backfitting under 10 CFR 72.62, 10 CFR 50.109(a)(1), or otherwise represent an inconsistency with the issue finality provisions applicable to combined licenses in 10 CFR part 52. Accordingly, no backfit analysis or additional documentation addressing the issue finality criteria in 10 CFR part 52 has been prepared by the staff. XII. Congressional Review Act

The Office of Management and Budget has not found this to be a major rule as defined in the Congressional Review Act. List of Subjects in 10 CFR Part 72

Administrative practice and procedure, Criminal penalties, Manpower training programs, Nuclear materials, Occupational safety and health, Penalties, Radiation protection, Reporting and recordkeeping requirements, Security measures, Spent fuel, Whistleblowing.

For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; the Nuclear Waste Policy Act of 1982, as amended; and 5 U.S.C. 552 and 553; the NRC is adopting the following amendments to 10 CFR part 72.

**PART 72—LICENSING REQUIREMENTS FOR THE**  **INDEPENDENT STORAGE OF SPENT NUCLEAR FUEL, HIGH-LEVEL**  **RADIOACTIVE WASTE, AND REACTOR-RELATED GREATER THAN**  **CLASS C WASTE**

■ 1. The authority citation for part 72 continues to read as follows:

Authority: Atomic Energy Act secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182, 183, 184, 186, 187, 189, 223, 234, 274 (42 U.S.C. 2071, 2073, 2077, 2092, 2093, 2095, 2099, 2111, 2201, 2232, 2233, 2234, 2236, 2237, 2238, 2273, 2282, 2021); Energy Reorganization Act secs. 201, 202, 206, 211 (42 U.S.C. 5841, 5842, 5846, 5851); National Environmental Policy Act sec. 102 (42 U.S.C. 4332); Nuclear Waste Policy Act secs. 131, 132, 133, 135, 137, 141, 148 (42 U.S.C. 10151, 10152, 10153, 10155, 10157, 10161, 10168); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note); Energy Policy Act of 2005, Pub. L. No. 109–58, 119 Stat. 549 (2005).

Section 72.44(g) also issued under secs. Nuclear Waste Policy Act 142(b) and 148(c), (d) (42 U.S.C. 10162(b), 10168(c), (d)). Section 72.46 also issued under Atomic Energy Act sec. 189 (42 U.S.C. 2239); Nuclear Waste Policy Act sec. 134 (42 U.S.C. 10154). Section 72.96(d) also issued under Nuclear Waste Policy Act sec. 145(g) (42 U.S.C. 10165(g)). Subpart J also issued under Nuclear Waste Policy Act secs. 117(a), 141(h) (42 U.S.C. 10137(a), 10161(h)). Subpart K is also issued under sec. 218(a) (42 U.S.C. 10198).

■ 2. In § 72.214, Certificate of Compliance 1004 is revised to read as follows:

**§ 72.214 List of approved spent fuel storage casks.** 
* * * * * Certificate Number: 1004. Initial Certificate Effective Date: January

23, 1995. Amendment Number 1 Effective Date:

April 27, 2000. Amendment Number 2 Effective Date:

September 5, 2000. Amendment Number 3 Effective Date:

September 12, 2001. Amendment Number 4 Effective Date:

February 12, 2002. Amendment Number 5 Effective Date:

January 7, 2004. Amendment Number 6 Effective Date:

December 22, 2003. Amendment Number 7 Effective Date:

March 2, 2004. Amendment Number 8 Effective Date:

December 5, 2005. Amendment Number 9 Effective Date:

April 17, 2007. Amendment Number 10 Effective Date:

August 24, 2009. Amendment Number 11 Effective Date:

January 7, 2014. Amendment Number 12 Effective Date:

Amendment not issued by the NRC. Amendment Number 13 Effective Date:

May 24, 2014. SAR Submitted by: Transnuclear, Inc. SAR Title: Final Safety Analysis Report

for the Standardized NUHOMS ® Horizontal Modular Storage System for Irradiated Nuclear Fuel. Docket Number: 72–1004. Certificate Expiration Date: January 23,

2015. Model Number: NUHOMS ® –24P,

–24PHB, –24PTH, –32PT, –32PTH1, –37PTH, –52B, –61BT, –61BTH, and –69BTH.

* * * * *

Dated at Rockville, Maryland, this 30th day of December 2013.

For the Nuclear Regulatory Commission. Michael F. Weber, Acting Executive Director for Operations.
[FR Doc. 2014–05108 Filed 3–7–14; 8:45 am]

**BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0555; Directorate Identifier 2010–SW–047–AD; Amendment**  **39–17779; AD 2014–05–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 and MBB–BK 117 C–2 helicopters. This AD requires inspecting the flight-control bearings repetitively, replacing any loose bearing with an airworthy flight-control bearing, and installing bushings and washers. This AD was prompted by the discovery during a routine inspection of loose flight control bearings because of incorrect installation. The actions of this AD are intended to prevent the affected control lever from shifting, contacting the helicopter structure, and reducing control of the helicopter.

**DATES :**  This AD is effective April 14,
2014.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of April 14, 2014.

**ADDRESSES :**  For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.eurocopter.com/techpub. 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


### 13197 Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations

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 Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email matthew.fuller@ faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On July 3, 2013, at 78 FR 40047, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to add an AD that would apply to ECD Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, serial number (S/N) 0005 through 00829, with a tail rotor control lever, part number (P/N) L672M2802205 or L672M1012212; cyclic control lever, P/N L671M1005250; collective control lever assembly, P/N L671M2020108; or collective control plate, P/N L671M5040207; installed. The NRPM proposed that the AD also would apply to Model MBB–BK 117 C–2 helicopters, S/N 9004 through 9310, with a tail rotor control lever assembly, P/N B672M1007101 or B672M1807101; tail rotor control lever, P/N B672M1002202 or L672M2802205; or lateral control lever assembly, P/N B670M1008101, installed.

The NPRM proposed to require inspecting the flight-control bearings repetitively, replacing any loose bearing with an airworthy flight-control bearing, and installing bushings and washers. The proposed requirements were intended to prevent the affected control lever from shifting, contacting the helicopter structure, and reducing control of the helicopter.

The NPRM was prompted by AD No. 2010–0058, dated March 30, 2010, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued the AD to correct an unsafe condition for the ECD Model MBB–BK 117 C–2, EC 135 and EC 635 helicopters. EASA advises that during an inspection of an MBB–BK 117 C–2, ‘‘bearings were detected which had not been correctly fixed.’’ As some bearings on the EC 135 and MBB–BK 117 C–2 type designs are installed with the same procedure, they are equally affected by the possibility of the unsafe condition. EASA states that this condition, if not corrected, could result in the affected control lever shifting in the axial direction, contacting the helicopter structure, and subsequently reducing control of the helicopter.

Comments

We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (78 FR 40047, July 3, 2013).

FAA’s Determination

These helicopters have been approved by the aviation authority of the Federal Republic of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in its 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.

Differences Between This AD and the EASA AD

Differences between this AD and the EASA AD are:

• The EASA AD is applicable to the EC 635 helicopter, whereas this AD is not because the EC 635 helicopter is not type certificated in the U.S.

• The EASA AD requires an initial inspection within 50 flight hours or one month, whichever occurs first after May 31, 2008, and a modification within the next 12 months. This AD requires the modification within 100 hours TIS or at the next annual inspection, whichever occurs first, and no inspection until after the modification has been accomplished.

Related Service Information

Eurocopter has issued Alert Service Bulletin (ASB) MBB BK117 C–2–67A– 010, Revision 3, dated February 8, 2010, and ASB EC135–67A–019, Revision 3, dated December 16, 2009. These ASBs specify:

• Within the next 50 flight hours (FHs), inspecting the affected bearings and, if necessary, rebonding any affected bearings or replacing the lever assembly.

• Within 12 months, retrofitting bushings on the levers to prevent movement of the bearings.

• After the retrofit, repeating the inspection every 800 FHs or 36 months for the Model EC 135 helicopters, whichever comes first, and 600 FHs or 24 months, whichever comes first, for the Model MBB–BK 117 C–2 helicopters. EASA classified these ASBs as mandatory and issued AD 2010–0058 to ensure the continued airworthiness of these helicopters. Costs of Compliance

We estimate that this AD affects 175 Model EC135 and 112 Model MBB–BK 117 C–2 helicopters of U.S. Registry andthat labor costs average $85 per workhour. Based on these estimates, we expect the following costs:

• For EC135 helicopters, it takes about 32 work-hours to perform the modification. Parts cost about $312. The total cost for the modification is about $3,032 per helicopter and $530,600 for the U.S. operator fleet. The repetitive inspections require 6.5 work-hours for a cost of about $553 per helicopter and about $96,775 for the fleet per inspection cycle.

• For MBB–BK 117 C–2 helicopters, it takes about 32 work-hours to perform the modification. Parts cost about $396. The total cost for the modification is $3,116 per helicopter and $348,992 for the U.S. operator fleet. The cost for the repetitive inspections thereafter is about $85 per helicopter and $9,520 for the fleet per inspection cycle. 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:


### 13198 Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations

(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):
2014–05–06 Eurocopter Deutschland GmbH: Amendment 39–17779; Docket No. FAA–2013–0555; Directorate Identifier 2010–SW–047–AD.
(a) Applicability

This AD applies to the following helicopters, certificated in any category:

(1) Eurocopter Deutschland GmbH (ECD) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, serial number (S/N) 0005 through 00829, with a tail rotor control lever, part number (P/N) L672M2802205 or L672M1012212; cyclic control lever, P/N L671M1005250; collective control lever assembly, P/N L671M2020108; or collective control plate, P/N L671M5040207; installed; and

(2) Model MBB–BK 117 C–2 helicopters, S/ N 9004 through 9310, with a tail rotor control lever assembly, P/N B672M1007101 or B672M1807101; tail rotor control lever, P/N B672M1002202 or L672M2802205; or lateral control lever assembly, P/N B670M1008101, installed.

(b) Unsafe Condition

This AD defines the unsafe condition as incorrectly installed flight control bearings. This condition could cause the affected control lever to shift and contact the helicopter structure, resulting in reduced control of the helicopter. (c) Effective Date This AD becomes effective April 14, 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 Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters:

(i) Within the next 100 hours time-inservice (TIS) or at the next annual inspection, whichever occurs, modify the left-hand (LH) and right-hand (RH) guidance units and the cyclic shaft by installing bushings and washers to prevent shifting of the bearings in the axial direction as follows:

(A) Remove and disassemble the LH guidance unit and install a bushing, P/N L672M1012260, between the bearing block and the lever of the LH guidance unit as depicted in Detail A of Figure 5 of Eurocopter Alert Service Bulletin EC135–67A–019, Revision 3, dated December 16, 2009 (EC135 ASB).

(B) For helicopters without a yaw brake, remove and disassemble the RH guidance unit and install a bushing, P/N L672M1012260, between the bearing block and the lever as depicted in Detail B of Figure 5 of EC135 ASB.

(C) Remove and disassemble the cyclic shaft and install a washer, P/N L671M1005260, between the bearing block and the lever as depicted in Detail C of Figure 6 of EC135 ASB.

(D) Remove the collective control rod from the bellcrank and install a washer, P/N L221M1042208, on each side of the collective control rod and bellcrank as depicted in Detail D of Figure 6 of EC135 ASB.

(E) At intervals not to exceed 800 hours TIS or 36 months, whichever occurs first, inspect the bearings in the LH guidance unit, RH guidance unit, cyclic control, upper guidance unit, and linear voltage differential transducer plate for play. If any bearing is loose, replace the affected bearing with an airworthy bearing.

(2) For Model MBB–BK 117 C–2 helicopters:

(i) Within the next 100 hours TIS or at the next annual inspection, whichever occurs first, modify the LH and RH guidance units and the lateral control lever by installing bushings and washers to prevent shifting of the bearings in the axial direction as follows:

(A) Remove and disassemble the RH guidance unit and install a bushing, P/N L672M1012260, between the lever and the bracket as depicted in Detail B of Figure 4 of Eurocopter Alert Service Bulletin MBB BK117 C–2–67A–010, Revision 3, dated February 8, 2010 (BK117 ASB). Remove and disassemble the LH guidance unit and install a bushing, P/N L672M1012260, between the lever and the bracket as depicted in Detail C of Figure 4 of BK117 ASB.

(B) Remove the lateral control lever and install new bushings in accordance with the Accomplishment Instructions, paragraphs 3.C(9)(a) through 3.C(9)(g), of BK 117 ASB.

(C) Identify the modified lever assembly by writing ‘‘MBB BK117 C–2–67A–010’’ on the lever with permanent marking pen and protect with a single layer of lacquer (CM 421 or equivalent).

(D) Apply corrosion preventive paste (CM 518 or equivalent) on the shank of the screws and install airworthy parts as depicted in Figure 5 of BK117 ASB.

(E) At intervals not to exceed 600 hours TIS or 24 months, whichever occurs first, inspect the bearings in the RH guidance unit, LH guidance unit, and lateral control guidance unit for play. If any bearing is loose, replace the affected bearing with an airworthy bearing.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email matthew.fuller@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. 2010–0058, dated March 30, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2013–0555.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control.
(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) Eurocopter Alert Service Bulletin EC135–67A–019, Revision 3, dated December 16, 2009.

(ii) Eurocopter Alert Service Bulletin MBB BK117 C–2–67A–010, Revision 3, dated February 8, 2010.

(3) For Eurocopter service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http://www.eurocopter.com/ techpub.

(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


### 13199 Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations

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 February 20, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2014–04589 Filed 3–7–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0109; Directorate Identifier 2013–SW–049–AD; Amendment**  **39–17772; AD 2014–04–13]**

**RIN 2120–AA64**

**Airworthiness Directives; Agusta S.p.A. Helicopters** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP helicopters. This AD requires inspecting the tail rotor (T/R) blade for a crack, corrosion, nick, scratch, dent, or other damage and replacing or repairing the blade, depending on the damage. This AD is prompted by reports of T/R blade failures caused by fatigue cracking that originated from surface damage. These actions are intended to prevent failure of the T/R blade and subsequent loss of control of the helicopter.

**DATES :**  This AD becomes effective March 25, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of March 25, 2014.

We must receive comments on this AD by May 9, 2014.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.

• Fax: 202–493–2251.

• Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

For service information identified in this AD, contact Agusta Westland, 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/technicalbulletins. 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.

**FOR FURTHER INFORMATION CONTACT :**  Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email robert.grant@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments.

Discussion

On April 22, 2008, we issued AD 2008–10–03, Amendment 39–15509 (73 FR 24858, May 6, 2008) for Bell Helicopter Textron Helicopters (Bell) Model 204B, 205A, 205A–1, 205B, 210, 212, 412, 412CF, and 412EP helicopters. AD 2008–10–03 required certain checks and inspections of each T/R blade at specified intervals and repairing or replacing, as applicable, any unairworthy T/R blade. AD 2008–10–03 was prompted by eight reports of fatigue cracking of T/R blades installed on Bell Model 212 and 412 helicopters (three failures on Bell Model 212 and five failures on Bell Model 412) with a T/R blade, part number (P/N) 212–010–750– 009, –105, and –107. Three of the Model 412 failures occurred during flight.

After we issued AD 2008–10–03, an accident attributed to a T/R failure occurred. Because of this accident, we determined that a second, more detailed inspection was necessary to allow for an earlier detection of a crack or other damage. As a result, on July 11, 2013, we issued AD 2013–15–02, Amendment 39–17518 (78 FR 45845, July 30, 2013), which superseded AD 2008–10–03. These actions were intended to prevent failure of the T/R blade and subsequent loss of helicopter control.

Although similar failures have not been reported on Agusta helicopters, T/ R blade P/N 212–010–750 may be installed on Agusta Model AB205A1, AB212, AB412, and AB412 EP helicopters. As a result, EASA, which is the Technical Agent for the Member States of the European Union, issued AD No. 2013–0185, dated August 14, 2013, to correct an unsafe condition for Agusta Model AB205A1, AB212, AB412, and AB412 EP helicopters. EASA advised that Bell reported some failures in T/R blade P/N 212–010–750 (all dash numbers), which originated from a fatigue crack derived from surface damages. EASA consequently requires detailed visual inspections of the T/R blade surface for nicks, dents, scratches, corrosion or cracks. EASA also requires repair or replacement of the T/R blade, depending on the outcome of those inspections.

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