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 


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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 and 

that 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: 


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(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 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 46 / Monday, March 10, 2014 / Rules and Regulations 13199 

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 


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