## ··-·····..

# · :;;

INtOII.MATION CPO 

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

the Standardized NUHOMS®Cask tern, and the current Amendment No. continues to be effective for rs. While current CoC users may camp 'th the new requirements in Amendment 13, this would be a voluntary decision the part ofcurrent users. For these reason , mendment No. 13 to CoC No. 1004 do ot constitutebackfitting under 10 72.62, 10 CFR 50.109(a)(1), or othe represent an inconsistency with the issue finality provisions applicable to combined licenses in 10 CFR part 52. Accordingly, no backfit analysis or ditional documentation addressing the ue finality criteria in 10 CFR part 52 has n preparedby the staff. al Review Act ement and Budget has not found this to major rule as defined in the Congressio Review Act.

Administrative practice a procedure, Criminal penalti 

### s Manpowertraining progra 

### s, materials, Occupational sa£ 

### ty a

alth, Penalties, Radiation ote · Re ing and recordkeepin ts, Security mea fuel, Whis owing.

Forthe reaso et out in t preamble and unde e authority ofthe Atomic Energy Act of as amended; the Energy Reorganization of 1974, as amended; the NuclearWaste icy Act of 1982, as amended; and 5 U

.. 552 and 553; the NRC is adopting the following amendments to 10 CFR part 72. P RT 72-LICENSING IREMENTS FOR THE IND DENT STORAGE OF SPENT NUCLEA EL, HIGH-LEVEL RADIOACTI ASTE, AND REACTOR-RELA GREATER THAN CLASS C WASTE

• 1. The authority citationfo continues to read as follows :

Authority: Atomic Energy Act sees. 51, 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,

82, 2021); Energy Reorganization Act sees. 2 02,206, 211 (42 

## u.s.c. 5841,5842, 5846, 1); National Environmental Policy Act sec. 1 42 U.S.C. 4332); Nuclear Waste Policy Act se 31, 132, 133, 135, 137, 141, 148 (42 

## u.s
.c. 10 10152, 10153, 10155, 10157, 10161, 10168 , . 1704, 112 Stat. 2750 (44 U.S.C. 3504 not ergy Policy Act of 2005 , Pub. L. No. 109-58, Stat. 549 (2005).

Section 72.44(g) also issued under NuclearWaste Policy Act 142(b) and 14 . 10162(b), 10168(c), (d)).
o issued under Atomic Energy Act sec
. 42 U

.S.C

. 2239) ; Nuclear Waste Policy Act sec. 4 (42 U.S.C. 10154). Section 72.96(d) also iss under Nuclear Waste Policy Act sec. 145(g U.S.C. 10165(g)). Subpart

### Jalso issued r Nuclear Waste Policy Act sees. 117 a 41(h) (42 U.S.C. 10137(a), 10161(h))

. Subpart also issued under sec. 218(a) (42 U.S

.C. 10198).
• 2. In§ 72.214,Certificate of

ompliance 1004 is revised to read as

§72.21 st of approved spent fuel storage cas 

### * * Certificate Number: Initial Certificate Effect!

23, 1995. Amendment Num

April 27, Amen ent t



### y en ent anu ry 7 en ent Nu 6 Effective Date: ecember 22, 2003. Amendment Number 7 E

March 2, 2004. Amendment Number 8 Effective

December 5, 2005. Amendment Number 9 Effective Date:

April17, 2007. Amendment Number 10 Effective Date:

August 24, 2009

. A dment Number 11 Effective Date:

Jan 7, 2014. Amendme umber 12 Effective Date:

Amendmen issuedby the NRC. Amendment Num 3 Effective Date:

May 24, 2014. SAR Submitted by: Transn SAR Title: Final Safety Analys1

for the Standardized NUHOMS® Horizontal Modular Storage System for Irradiated Nuclear Fuel. Docket Number: 72-1004. Certificate Expiration Date: January 23 , 015. umber: NUHOMS®-24P, -24P -24PTH, -32PT, -32PTH1 , -37PTH, , -61BT, -61BTH, and -69BTH. * 

### * *

For the Nuclear Regulatory Commis Michael F. Weber, ActingExecutiveDirector for Operations. [FR Doc. 2014-05108 Filed 3-7-14; 8:45am] BILLING CODE 759(H)1-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.



## v· W are adopting a new 

### s directive (AD) for r o D utschland GmbH (ECD) od l and MBB-BK 117 C-2 JlEl).H':UJlt his AD requires inspecting t o trol bearings repetitively, g a y loose bearing with an irw flight-control bearing, and ailing bushings and washers. This AD was prompted by the discovery during a routine inspection ofloose flight control bearings because of incorrect installation. The actions ofthis AD are intended to preventthe affected control lever from shifting, contacting the helicopter structure, and reducing control ofthe helicopter

. DATES: This AD is effective April14, 2014.

The Director ofthe Federal Register approved the incorporation by reference ofcertain documents listed in this AD as ofApril14, 2014. ADDRESSES: For service information identified in this AD, contactAmerican 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 ofthe 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:/ I 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

### Federal Register/Val. 79, No. 46/Monday, March 10, 2014/Rules and Regulations 13197
Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 NewJersey 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 Pl, P2, P2+, Tl, T2, and T2+ helicopters, serial number (SI 0005 through 00829, with at · t r control lever, part number ( /N) L672M2802205 or L672M1 1 cyclic control lever, PIN L671M1005250; collective ntro assembly, PIN L671M202010 , collective control plate, PI L671M5040207; installed. h proposed that the AD also u apply to Model MBB-BK 117 C-2 helicopters, SIN 9004 through 9310, with a tail rotor control lever assembly, PIN B672M1007101 or B672M1807101; tail rotor control lever, PIN B672M1002202 or L672M2802205 ; or lateral control lever assembly, PIN 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 ofthe helicopter.

The NPRM was promptedby AD No. 2010-0058, dated March 30, 2010, issued byEASA, which is the Technical Agent for the Member States ofthe 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 ofan 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 ofthe unsafe condition

. EASA states that this condition, ifnot corrected, could result in the affected control lever shifting in the axial direction, contacting the helicopter structure, and subsequently reducing control ofthe helfcopter. Comments

We gave the public the opportunity to participate in developing this AD, but we rlj.ceived no comments on the NPRM (.8 FR 40047, July 3, 2013). FAA's Determination

These helicopters have been approved by the aviation authority ofthe Federal Republic ofGermany and are approved for operation in the United States. Pursuant to ourbilateral agreement with Germany, EASA, its technical representative, has notified oft unsafe condition tfsc i i 

### s

Differences between this AD and the EASA AD are: Jl

• The EASA AD-is applicable to the EC 635 helicopter, whereas this AD is not**beca~e** 'the EC 635 helicopter is not**typ~iti'tificated** in the U

.S

.

,-r'heEASA 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 inspectionuntil after the modification has been accomplished

. Related Service Information

Euroc2P-tet has issued Alert Service Bulle»n1ASB) MBB BK117 C-2-67A-**~evision** 3, dated February 8, 2010,**~d** ASB EC135-67A-Q19, Revision 3, dated December 16, 2009

. These ASBs specify:

• Within the next 50 flight hours (FHs) , inspecting the affected bearings and, ifnecessary, rebonding any affected bearings orreplacing the lever assembly.

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

• After ,the retrofit, repeating the inspeot-ion every 800 FHs or 36 months for ffte 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**2010-00~?** 

### M
ensure the continued airworthiness of these helicopters. Costs ofCompliance

We estimate that this AD affects 175 Model EC135 and 112 Model MBB-BK 117 C-2 helicopters ofU.S. Registry and that labor costs average $85 per workhour. Based on these estimates, we

- expect the following costs:

• ForEC135 helicopters, it takes abo wo k-hours to perform the

oai

. ation Parts cost about $312

. The ot

### s~f r he modification is abou .!,...<• ,03 r icopter and $530,600, fl'ir . p r tor fleet. The repeti£ive ns · quire 6.5 wqrk-hours for a t of $553 per helicopter and 96,7 5 for 

## t,Pe fleet per nspe ·**cycle ·**  or**M~BK** 117 C-2 helicopters, it takes abouf32 work-hours to perform the modification. Parts cost about $396

. The total cost for the modification is $3,116 perhelicopter and $348,992 for the U.S. operatorfleet. The cost for the repetitive inspections thereafter is about $85 perhelicopter and $9,520 for the fleet perinspection cycle.**.~** Authority for This Rulemaking •·

Title 49 ofthe 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 ofthe Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, SubpartIII, Section 44701 : "General requirements." Under that section, Congress charges the FAA with promoting safe flight ofcivil aircraft in air commerce by prescribingregulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce
. This regulation is within the scope ofthat 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 ofpower and responsibilities among the various levels ofgovernment.

F jjpthe reasons discussed above, I ce!flfy that this AD :

### 13198 

### Federal Register/Val. 79, No. 46/Monday, March 10, 2014/Rules and Regulations
(1) Is not a "significantreguliJ.tdcy action" under Executive Order 12866;

(2) Is not a "significantrule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

(3) Will not affect intrastate aviation in_.fffa;ka to the extent that itjustifies 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 ofthe Regulatory Flexibility Act.

We prepared an economic evaluation ofthe estimated costs to comply with this AD and placed it in the AD docket. List ofSubjects in 1'4 CFR Part 39

Air tral,lsportation, Aircraft, Aviation**saf~. lilcorporation**  by reference, 

### srety. Adoption ofthe Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part follows: PART 39-AIRWORTHINE DIRECTIVES

• 1. The authority citation for continues te'read as follow

. rrlty:49

## u.s.c. 106(g). 0113 44 §39.13 [Amended]

• 2. TheFAA amends§ 39.13 byadding the following new airworthiness directive (AD): 2014-05-{)6 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:

(lJ,EurocopterDeutschland GmbH (ECD) Monel EC135 Pl, P2, P2+, Tl, T2, and T2+ helicopters, serial number (SIN) 0005 through 00829, with a tail rotor control lever, part number (PIN) L672M2802205 or L672M1012212; cyclic control lever, PIN L671M1005250; collective control lever assembly, PIN L671M2020108; or collective control plate, PIN L671M5040207; installed; and

(2) Model MBB-BK 117 C-2 helicopters, Sl N 9004 through 9310, with a tail rotor control lever assembly, PIN B672M1007101 or B672M1807101; tail rotor control lever, PIN B672M1002202 or L672M2802205; or lateral**contr~ ver**  assembly, PIN B670M1008101, installed

. (b) Unsafe Condition (c) Effective Date This AD becomes effective April14, 2014. (d) Compliance

s inst I 0 260**bfl~!Ndl~tl** eee sdpct iure oEC 5

C) R ov disassemble the cyclic h ft an mstall a washer, PIN 1M1005260, between the bearing block and the lever as depicted in Detail C of Figure 6 ofEC135 ASB.

(D) Remove the collective control rod from the bellcrank and install a washer, PIN L221M1042208, on each side ofthe collective control rod and bellcrank as depicted in Detail D ofFigure 6 ofEC135 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. Ifany bearing is loose, replace the affected bearing with an airworthybearing.

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

(i) Within the next 100hours TIS or at the next annual inspection, whichever occurs first, modify the LH and RH guidance units •
.. and the lateral control leverby 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, PIN L672M1012260, between the lever and the bracket as depicted in Detail B ofFigure 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, PIN L672M1012260, between the lever and the bracket**a~**depicted in Detail C ofFigure 4 of**BK ~7**  ASB. This AD defines the unsafe condition as (B) Remov.e.the lateral control lever and incorrectly installed flight control bearings. install newbushings in accordance with the This condition could cause the affected**AJ;.~plishment** Instructions, paragraphs control lever to shift and contact the**'C(9)(a)** through 3

.C(9)(g), ofBK 117 ASB. helicopter structure, resulting in reduce (C) Identify the modified lever assembly by control ofthe helicopter

. writing "MBB BK117 C-2-67A-010" on the lever with permanent marking pen and protect with a single layer oflacquer (CM 421 or equivalent).

(D) Apply corrosion preventive paste (CM 518 or equivalent) on the shank ofthe screws and install airworthy parts as depicted in Figure 5 ofBK117 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. Ifany bearing is loose, replace the affected bearing with an airworthy bearing. (f) Alternative Methods ofCompliance (AMOCs))

(l)"The ager, Safety Management • Gro , ay approve AMOCs for this

. S**~** proposal to: Matt Fuller, a 'o Safety Engineer, Safety a e n oup, Rotorcraft Directorate, 0 e cham Blvd., Fort Worth, TX l p o e (817) 222-5110; email

. e 'faa.gov. oper tions conducted under a 14 11 operating certificate or under 4 CF t 91, subpart K, we suggest that 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 ofthis 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.govin 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 ofthe Federal Register approved the incorporation by reference (IBR) ofthe 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, contactAmerican 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/ tech pub

. (4) You may view this service information at FAA, Office ofthe Regional Counsel, SouthwestRegion, 2601 Meacham Blvd,_. Room 663 , Fort Worth, Texas 76137., F6r information on the availability ()'ftliis material at the FAA,**call~17J** 222-5110.

(5) You may**view~** service information that is incorporatedoy reference at the

### Federal Register 

### IVol. 79, No. 46 

### IMonday, March 10, 2014 

### IRules and Regulations 13199

National Archives and Records Administration (NARA)

. For information on the availability ofthis 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, ActingDirectorateManager,Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014-04589 Filed 3-7-14; 8:45am) BILLING CODE 491Q-13-P

Federal Aviation Administration
14 CFR Part 39 [Docket No. FAA-2014-0109; Directorate ntifier 2013-SW-049-AD; Amendm t 39-= 2; AD 2014-04-13]

AGENCY: 

### Federal Aviation Administration (FAA), Dep Transportation (DOT). ACTION: 

### Final rule; request for comments.
SUMMARY: 

### We are adopting a new airworthiness directive (AD) for Agusta S.

. (Agusta) Model AB412 and AB412 elicopters

. This AD requires inspecting t il rotor (TIR) blade for a crack, corrosio , ·ck, scratch, dent, or other damage and rep · the blade, depending on t mage
. This AD is prompted by reports IR 

### blade failures caused by fatigue crac that originated from surface damage. These actions are intendedto prevent failure ofthe TIR

### blade and subsequent loss ofcontrol ofthe helicopter

. DATES: 

### This AD becomes effective rch 25 , 2014. irector ofthe Federal Register approve incorporation by reference ofa certain ent listed in this AD as ofMarch 25, 2

We mustreceive co AD by May 9, 2014. ADDRESSES: 

### You may send comm any ofthe following methods:



### • Federal eRulemakingDocket: 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. Dep ent ofTransportation, Docket Operatio -30, West Building Ground Floor, m W12-140, 1200 New Jersey Avenu , Washington, DC 20590-0001. 

### • HandDelivery:Deliver to the "Mail" address between 9 a.m. and 5 p.m., Monday through Friday, except eral holidays

. the AD Docket

FOR FURTHER INFORMATION CO 

### Robert Grant, Aviation Safety Eng1 Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 

### robert.grant@jaa

.gov. SUPPLEMENTARY INFORMATION: 

### ents Invited 'sa final rule that involves requirement cting flight safety, and we did not provi u with notice and an opportunityto pro our comments prior to it becom However, we invite you to parti e in this rulemaking by submitting writte 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 ments reference a specific portion of explain the reason for any recomme d change, and include supporting da o ensure the docket does not contain · ate comments, commenters should sen one copy ofwritten comments, or ifco nts are filed electronically, commenters s d submit them only one time. We will fi 

### in the docket all comments that we receive, as well as a report summarizing each su ntive public contact with FAA person oncerning this rulemaking duri e commentperiod. We will consider all t mments we receive and may conduct a · ional rulemaking based on those com 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) del204B, 205A, 205A-1 , 205B, 210, 212, 41 CF, and 412EP helicopters. 2 03 required certain checks
n ·



### ~i each TIR 

### blade at

cifi 

### d i t vals repairing or a i s pplicab , n · IR 

### blade. AD -10-03

s pr t by eight reports o



### ,..,..,....,.., III'"KJ of IR

### blades installed on B ode and 412 helicopters (three

· res on Bell Model 212 and five failures on Bell Model412) with a T/R blade, part number (PIN) 212-010-750-

09,-105, and -107

. Three ofthe Model ilures occurred during flight. Aft e issued AD 2008-10-03 , an accident a · uted to a TIR 

### failure occurred. Beca fthis accident, we determined that a se d, more detailed inspection was necessar llow for an earlier detection ofa crack or r damage. As a result, onJuly 11 , 2 we issued AD 2013-15-02, Amendmen 39-17518 (78 FR 45845, July 30, 2013), which superseded AD 2008-10-03. These actions were intended to prevent failure ofthe TIR 

### blade and subsequent s ofhelicopter control. ugh similar failures have not beenre don Agusta helicopters, Tl Rblade PI 

### :::-010-750 may be installed on Agus odel AB205A1 , AB212, AB412, and A EP helicopters. As a result, E which is the Technical Agent for the Me States ofthe European Union, issue 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

· res in TIR 

### blade PIN 

### 212-010-750 (all numbers), which originated from a fati crack derived from surface damag SA consequently requires detailed vi inspections of the TIR 

### blade surface for · s, dents, scratches, corrosion or cracks. SA also requires repair or replacemen f the TIR 

### blade, depending on the outcome ofthose inspections. FAA's Determination

These helicopters have been approved the aviation authority ofItaly and are ved for operation in the United State

. ursuant to ourbilateral