··-·· INTOII.MATIO ··· .. N -:;; 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 , 

57, 62,63,65, 69, 81, 161, 182, 183, 184,186, 

187, 189, 223, 234 , 274 (4 2 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 

Nuclear Waste Policy Act 142(b) and 14 

. 10162(b), 10168(c), (d)). 

o issu 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 J also 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, -32PTH1, 

-37PTH, , - 61BT, - 61BTH, and 

- 69BTH. 

* * * 

For the Nuclear Regulatory Commis 

Michael F. Weber, 

Acting Executive 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 of the helicopter. 

DATES: This AD is effective April14, 

2014. 

The Director of the Federal Register 

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.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:/ 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, an d 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 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 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 

abo wo k-hours to perform the 

odi · ation Parts cost about $312. The 

ot sRf r he modification is abou1--• ,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 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 traJ],sportation, Aircraft, Aviation 

saf~,<Incorporation by reference, 

Sreiy. 

Adoption of the 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-2-67 A-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, 

Acting Directorate 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