## ··-·····..

# - :;;
INTOII.MATION t,;pl.) 

### 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 of current users. For these reason , mendment No. 13 to CoC No. 1004 do ot constitute backfitting 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 prepared by 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 Manpower training progra s, materials, Occupational sa£ 

### ty a

alth, Penalties, Radiation ate i Re ing and recordkeepin ts, Security mea fuel, Whis owing.

For the reaso et out in t preamble and unde e authority of the Atomic Energy Act of as amended; the Energy Reorganization of 1974 , as amended; the Nuclear Waste 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 INDE DENT STORAGE OF SPENT NUCLEA EL, HIGH-LEVEL RADIOACTI ASTE, AND REACTOR-RELA GREATER THAN CLASS C WASTE

• 1. 

### The authority citation fo continues to read as follows :

Authority: Atomic Energy Act sees. 51 , 5 7, 62,63,6 5 , 69 , 81 , 161 , 182 , 183 , 184 ,1 86 , 1 87, 1 89, 223, 23 4 , 274 (4 2 

## u. s
. c
. 2071, 2073, 2077, 2092, 2093, 2095, 2099 , 2 1 11, 2201 , 2232, 2233, 2234, 2236, 2237, 2238, 2273,

8 2, 2021); Energy Reorganization Act sees. 2 02,206, 211 (42 

## u.s.c. 5 841,5842, 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. 1 0 1 0 152, 10153, 10155, 10157, 10161, 10 1 6 8 , . 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 Nuclear Waste Policy Act 142(b) and 14 . 10162(b) , 10168(c ), (d))

. o is su ed 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 

### * *

Amendment Num

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, -32PTH 1, -37PTH, , - 6 1BT,

- 61 BTH, and

- 69BTH

. * 

### * *

For the Nuclear Regulatory Commis Michael F. Weber, ActingExecutive Director for Operations. [FR Doc. 2014-05108 Filed 3-7-14 ; 8:45am] BILLING CODE 759D-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.



## v· W are adopting a new s directive (AD) for r o D utschland GmbH (ECD) od I and MBB-BK 117 C-2 t 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 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 ofthe helicopter

. DATES: 

### This AD is effective April14 , 2014.

The Director of the Federal Regi ster approved the incorporation by reference of certain documents listed in this AD as of April14, 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.e urocopter.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 :/ I www. regulations.gov or in p erson at the Docket Operation s Office between 9 a.m
. and 5 p. m
. , Monday through Friday, except Federal holi days. The AD docket contains thi s AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information , the economic evaluation, any comments received, an d other information. The street address for the Docket Operation s Off ice (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 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 (SI 0005 through 00829, with at · t r control lever, part number ( /N) L672M2802205 or L672M1 1 cyclic control lever, PIN L671M1005250; collective c 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 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**r~ceived** 

### no comments on the NPRM (¥8 FR 40047, July 3, 2013). FAA's Determination

Differences between this AD and the EASA AD are:
. .,-- • The EASA AD1.s applicable to the EC 635 helicopter, whereas this AD is not**beca~se** 

### the EC 635 helicopter is not**typ~61ftificated** 

### in the U.S.

_,rhe 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

Eurocopte; has issued Alert Service Bulle..t)n'fASB) MBB BK117 C-2-67A-**~evision** 

### 3, dated February 8, 2010, 1fid 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 inspeation every 800 FHs or 36 months for**~e** 

### 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 ofCompliance

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 abo wo k-hours to perform the

odi · ation Parts cost about $312. The ot sRf r he modification is abou 1-- • ,03 r icopter and $530,60

.0 fE>r

. p r tor fleet. The repetitive ns · r quire 6.5 work-hours for a t of $553 per helicopter and 96,7 5 for t e fleet per nspe · cyc,le.·· or MW}-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 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.

F

_ <jJ: the reasons discussed above , I ce!lf'lfy that this AD :

### 13198 

### Federal Register/Val. 79, No. 46/Monday, March 10, 2014/Rules and Regulations
(1) Is not a "significant regulijitof*y 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**i~aska** 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 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 traJ],sportation, Aircraft, Aviation**saf~ ,<** **Incorporation** by reference, 

### Sreiy. 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 <r"**~ority:** 49 U.S.C. 106(g), 0113 44 § 39.13 [Amended]
• 2. The FAA amends§ 39.13 by adding the following new airworthiness directive (AD): 2014-05--{16 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:

(l,l;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 (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, Sf 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~ever** assembly, PIN B670M1008101, installed. (b) Unsafe Condition (c) Effective Date This AD becomes effective April14, 2014

. (d) Compliance

Y

au 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+, Tl , 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 L672M1012260, between the be · g k and the lever of the LH g · c uni**~** depicted in Detai F Sl!re f uro o t Alert Servi letin A , Rev· io 3, da 

# a 6, 009 1 B).

# ~ r eli t s i a br e, e v u s le e inst I g, P 672 0 260 b the e lock e e e s d p ct etail B of iure oEC 5

C) R mov 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 of EC135 ASB.

(D) Remove the collective control rod from the bellcrank and install a washer, PIN 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 , PIN 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, PIN L672M1012260, between the lever and the bracket as,. depicted in Detail C of Figure 4 ofBKl17 ASB. This AD defines the unsafe condition as (B) Remove .the lateral control lever and incorrectly installed flight control bearings. install new bushings in accordance with the This condition could cause the affected A;s;ooriiplishment Instructions, paragraphs control lever to shift and contact the**~.C (9)(a)**  through 3.C(9)(g), of BK 117 ASB. helicopter structure, resulting in**reduce~** (C) Identify the modified lever assembly by control of the helicopter. ..,- 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 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. If any bearing is loose, replace the affected bearing with an airworthy bearing. (f) Alternative Methods of Compliance (AMOCsJ)

(1) The ager, Safety Management Gro , ay approve AMOCs for this

.**S~** d proposal to: Matt Fuller,

a "o Safety Engineer, Safety a e n oup, Rotorcraft Directorate,

, 0 e cham Blvd., Fort Worth, TX 6137 I p o e (817) 222-5110; email

. e 'faa.gov. oper tions conducted under a 14 11 operating certificate or under 4 CF rt 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 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/ tech pub. (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 ofcthis material at the FAA, call)il17) 222-5110.

(5) You may**view~** service information that is incorporated o y reference at the

### Federal Register 

### I Vol. 79, No. 46 

### I Monday, March 10, 2014 

### I 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, ActingDirectorate Manager, Rotorcraft Directorate, Aircraft Certification Service

. [FR Doc. 2014-04589 Filed 3-7-14; 8:45am) BILLING CODE 491D-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 (T/R) 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 blade failures caused by fatigue crac 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 rch 25 , 2014. irector of the Federal Register approve incorporation by reference of a certain ent listed in this AD as of March 25, 2

We must receive co AD by May 9, 2014. ADDRESSES: You may send comm any of the following methods :



### • Federal eRulemaking Docket: Go to 

### http:/ lwww.regulations.gov. Follow the online instructions for sending your comments electronically

.

• Fax:202-493-2251.



### Mail: Send comments to the U.S. Dep ent of Transportation, Docket Operatio -30 , West Building Ground Floor, m W12-140, 1200 New Jersey Avenu , Washington, DC 20590-0001. 

### • Hand Delivery: 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:

·sa final rule that involves requirement cting flight safety, and we did not provi u with notice and an opportunity to prov 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 of written comments, or if co nts are filed electronically, commenters s 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 comment period. 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) del 204B, 205A, 205A-1 , 205B, 210, 212, 41 CF, and 412EP helicopters. 2 03 required certain checks
n ·



### ~i each T/R blade at

cifi d i t vals repairing or e a i s pplicab , n · /R blade. AD -10-03

s pr t by eight reports o r of /R 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 (P/N) 212-010-750-

09 , -105, and -107. Three of the Model ilures occurred during flight. Aft e issued AD 2008-10-03, an accident a · uted to a T/R failure occurred. Beca f this accident, we determined that a se d, more detailed inspection was necessar llow for an earlier detection of a crack or r damage. As a result, on July 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 of the T/R blade and subsequent s of helicopter control. ugh similar failures have not been re don Agusta helicopters , T/ R blade P/ :::-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 of the 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 T/R 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 T/R blade surface for · s, dents, scratches, corrosion or cracks. SA also requires repair or replacemen f the T/R blade, depending on the outcome of those inspections. FAA's Determination

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

. ursuant to our bilateral