34960 Federal Register / Vol. 78, No. 112 / Tuesday, June 11, 2013 / Proposed Rules 

FR 11001, March 16, 2009), and adding 

the following new AD: 

Bell Helicopter Textron, Inc.: Docket No. 

FAA–2013–0500; Directorate Identifier 

2012–SW–45–AD. 

(a) Applicability 

This AD applies to Model 412 and 412EP 

helicopters with a main rotor yoke assembly 

(yoke), part number (P/N) 412–010–101–123, 

–127, –129, or –133, installed; and Model 

412CF helicopters with a yoke, P/N 412–010– 

101–127 or –129, installed; certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking of a yoke, failure of the yoke, 

and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD supersedes AD 2009–05–09, 

Amendment 39–15833 (74 FR 11001, March 

16, 2009). 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time, unless it has been 

accomplished previously. 

(e) Required Actions 

Within 10 hours time-in-service (TIS): 

(1) Review the helicopter records to 

determine all of the helicopter models on 

which an affected yoke has been installed 

since its production and the hours TIS of 

each affected yoke. 

(2) If an affected part-numbered yoke is 

installed or has ever been installed on a 

Model 412CF helicopter or on a Model 412 

or 412EP helicopter with a (BHT–412–SI–62) 

slope landing kit, P/N 412–704–012–101, 

installed, do the following: 

(i) Reidentify the P/N on the side of the 

yoke by using a vibrating stylus and etching 

two lines through the last three digits of the 

existing P/N and etching ‘‘137FM’’ adjacent 

to where you etched through the last three 

digits of the original P/N. This converts each 

affected yoke P/N to a new yoke P/N 412– 

010–101–137FM. The serial number remains 

the same. 

Note 1 to paragraph (e)(2)(i) of this AD: 

The ‘‘FM’’ P/N suffix denotes a fieldmodified part. 

(ii) Treat the etched surface with chemical 

film, and apply primer and paint. 

(iii) Record the reidentified P/N on the 

applicable component history card or 

equivalent record. 

(3) If you cannot determine all the model 

helicopters on which an affected yoke has 

been installed since its production or 

whether it has ever been installed on a Model 

412 or 412EP helicopter with a (BHT–412– 

SI–62) slope landing kit, P/N 412–704–012– 

101, installed, perform the actions required 

by paragraphs (e)(2)(i) through (e)(2)(iii) of 

this AD. 

(4) For each reidentified yoke, P/N 412– 

010–101–137FM, reduce the retirement life 

from 5,000 hours TIS to 4,500 hours TIS. 

Record the revised life limit on the 

applicable component history card or 

equivalent record. 

(5) Revise the Airworthiness Limitations 

section of the applicable maintenance 

manual or the Instructions for Continued 

Airworthiness by reducing the retirement life 

from 5,000 hours TIS to 4,500 hours TIS for 

each reidentified yoke, P/N 412–010–101– 

137FM. 

(f) Special Flight Permit 

Special flight permits will not be issued. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

ASW–170, Aviation Safety Engineer, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5170, fax (817) 222– 

5783; email 7-avs-asw-170@faa.gov. 

(2) For operations conducted under 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. 

(h) Additional Information 

Bell Helicopter Textron, Inc. Alert Service 

Bulletins No. 412–08–128 and No. 412CF– 

08–35, both Revision A and both dated April 

14, 2009, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Bell Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 280– 

3391; fax (817) 280–6466; or at http:// 

www.bellcustomer.com/files/. You may 

review service information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(i) Subject 

Joint Aircraft System/Component (JASC) 

Code: 6220 Main Rotor Head. 

Issued in Fort Worth, Texas, on June 3, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13797 Filed 6–10–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0501; Directorate 

Identifier 2011–SW–036–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

EC 155B and EC155B1 helicopters. This 

proposed AD would require repetitively 

inspecting the lower and upper front 

and rear fittings (fittings) that attach the 

upper fin to the fenestron for a crack. If 

there is a crack, this AD would require 

removing all four fittings from service. 

This proposed AD would also require, 

within a specified time, removing all 

fittings from service, and the fittings 

would not be eligible to be installed on 

any helicopter. This AD is prompted by 

the loss of an upper fin in flight. The 

proposed actions are intended to detect 

a crack in the fittings to prevent loss of 

the upper fin and subsequent loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 12, 2013. 

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 proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 112 / Tuesday, June 11, 2013 / Proposed Rules 34961 

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 proposed 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. 

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 

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 might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 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 proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2011– 

0108, dated June 7, 2011, to correct an 

unsafe condition for Eurocopter Model 

EC 155B and EC155B1 helicopters. 

EASA advises of an in-flight loss of a fin 

on a Model EC155B1 helicopter. 

According to EASA, a crack in the 

fittings attaching the upper fin to the 

fenestron (tail rotor assembly) was 

discovered during an investigation. As a 

result, EASA issued an emergency AD 

to mandate repetitive inspections of the 

upper fin attachment fittings. EASA 

states that Eurocopter has now 

developed modification (MOD) 0754B40 

to increase the strength of the fuselagefin junction fittings by installing two 

reinforced single-piece fittings to 

replace the affected fittings, which is 

terminating action for the repetitive 

inspection requirements. EASA 

subsequently issued AD No. 2011–0108, 

which superseded its emergency AD, to 

require installation of MOD 0754B40 

and to retain the repetitive inspection 

requirements until the MOD is installed. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin No. 05A017, 

Revision 2, dated December 9, 2010, 

which specifies repetitively inspecting 

the fittings for a crack and replacing 

each fitting if there is a crack. 

Eurocopter has also issued Service 

Bulletin No. 53–029, Revision 1, dated 

March 10, 2011, which specifies 

replacing the fittings with reinforced 

fittings in accordance with MOD 

0754B40. 

Proposed AD Requirements 

This proposed AD would require 

repetitively inspecting certain partnumbered fittings for a crack, and if 

there is a crack, removing the fittings 

from service before further flight. Also, 

within 180 hours time-in-service (TIS), 

this AD proposes removing certain partnumbered fittings from service. 

Replacing the fittings with airworthy 

fittings not listed in the applicability 

paragraph of this proposed AD would be 

terminating action for the requirements 

of this AD. The affected fittings would 

not eligible to be installed on any 

helicopter. 

Differences Between This Proposed AD 

and the EASA AD 

This AD would not require replacing 

the upper fin to fenestron fittings with 

reinforced fittings in accordance with 

MOD 0754B40 within 6 calendar 

months as stated in the EASA AD but 

rather would require removing the 

affected fittings from service within the 

equivalent 180 hours TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 9 helicopters of U.S. 

Registry. We estimate that operators 

would incur the following costs in order 

to comply with this AD, based on an 

average labor rate of $85 per work hour. 

It would take 1 work hour to inspect the 

fittings and about 3 inspections would 

occur before replacement. It would take 

8 work hours to replace the fittings and 

required parts would cost $3,311. Based 

on these figures, the total cost would be 

$4,246 per helicopter and $38,214 for 

the U.S. fleet. 

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 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
34962 Federal Register / Vol. 78, No. 112 / Tuesday, June 11, 2013 / Proposed Rules 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Eurocopter France: Docket No. FAA–2013– 

0501; Directorate Identifier 2011–SW– 

036–AD. 

(a) Applicability 

This AD applies to Model EC 155B and 

EC155B1 helicopters with lower front fitting 

part number (P/N) 365A23–4240–01, upper 

front fitting P/N 365A23–4242–01, lower rear 

fitting P/N 365A23–4241–01, or upper rear 

fitting P/N 365A23–4243–01 (fittings) 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a fitting. This condition could result 

in loss of the upper fin during flight and 

subsequent loss of control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time. 

(d) Required Actions 

(1) Within 15 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 55 

hours TIS: 

(i) Using an appropriate light source and a 

10x or higher power magnifying glass, 

inspect each front (c) and rear (d) upper 

fitting and each front (e) and rear (f) lower 

fitting for a crack as depicted in Figure 1 of 

Eurocopter Emergency Alert Service Bulletin 

No. 05A017, Revision 2, dated December 9, 

2010 (ASB). Inspect the hatched area as 

depicted in Details B, C, and D of Figure 2 

of the ASB. A high-resolution (more than 2 

million pixels) digital camera or dyepenetrant inspection may be used to facilitate 

the crack inspection. 

(ii) If there is a crack in any fitting, before 

further flight, remove all four fittings from 

service. 

(2) Within 180 hours TIS, remove the 

fittings from service. 

(3) Do not install lower front fitting P/N 

365A23–4240–01, upper front fitting P/N 

365A23–4242–01, lower rear fitting P/N 

365A23–4241–01, and upper rear fitting P/N 

365A23–4243–01 on any helicopter. 

(e) Credit for Actions Previously Completed 

Inspections accomplished before the 

effective date of this AD in accordance with 

the procedures specified in Eurocopter 

Emergency Alert Service Bulletin No. 

05A017, Revision 2, dated December 9, 2010; 

Revision 1, dated January 27, 2010; and 

Revision 0, dated September 28, 2007, are 

considered acceptable for compliance with 

the inspection specified in paragraph (d)(1) 

of this AD. 

(f) Special flight permits 

Special flight permits will not be issued. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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. 

(h) Additional Information 

(1) Eurocopter Service Bulletin No. 53–029, 

Revision 1, dated March 10, 2011, which is 

not incorporated by reference, contains 

additional information about the subject of 

this AD. 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0108, dated June 7, 2011. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5530 Vertical Stabilizer Structure. 

Issued in Fort Worth, Texas, on June 3, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13799 Filed 6–10–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF EDUCATION 

34 CFR Part 75 and Chapter III 

[CFDA Number: 84.250C and 84.250D] 

American Indian Vocational 

Rehabilitation Services Program; 

Proposed Waivers and Extensions of 

the Project Periods 

AGENCY: Rehabilitation Services 

Administration, Office of Special 

Education and Rehabilitative Services, 

Department of Education. 

ACTION: Proposed waivers and 

extensions of project periods. 

SUMMARY: These proposed waivers and 

extensions of project periods would 

affect two sets of grantees under the 

American Indian Vocational 

Rehabilitation Services (AIVRS) 

Program in the Rehabilitation Services 

Administration (RSA): eight grantees 

with 60-month projects initially funded 

in fiscal year (FY) 2007 (72 FR 11851) 

and twenty-four grantees with 60-month 

projects initially funded in FY 2008 (73 

FR 6491). For FY 2013, the Secretary 

proposes to waive the regulations that 

generally limit project periods to 60 

months and that restrict project period 

extensions involving the obligation of 

additional Federal funds. The Secretary 

proposes these actions in order to 

extend the 60-month projects for the 

grants initially funded in FY 2007 for a 

seventh year, and the grants initially 

funded in FY 2008 for a sixth year. The 

32 AIVRS grants would be extended 

through September 30, 2014. 

The proposed waivers and extensions 

would enable the 32 grantees to request 

funds and continue to receive Federal 

funding beyond September 30, 2013, 

when the project period ends. The 

grantees must meet all of the AIVRS 

program and other applicable 

requirements while receiving funds 

under this program. Further, if the 

proposed waivers and extensions are 

made final, RSA would not announce a 

new competition in FY 2013 or make 

new awards in FY 2013. 

DATES: We must receive your comments 

on or before July 11, 2013. 

ADDRESSES: Submit all comments on 

this notice to August Martin, U.S. 

Department of Education, 400 Maryland 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS