37158 Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 

Eurocopter France Helicopters: Docket No. 

FAA–2013–0524; Directorate Identifier 

2012–SW–084–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS332C, AS332L, 

AS332L1, AS332L2 and EC225LP 

helicopters, certificated in any category, that 

have never undergone a window-jettison test. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the presence of sealant on an emergency exit 

window panel. This condition could result in 

the window failing to jettison, preventing the 

helicopter occupants from exiting the aircraft 

during an emergency. 

(c) Comments Due Date 

We must receive comments by August 19, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

Within 110 hours time-in-service (TIS), 

visually inspect each jettisonable emergency 

exit window panel (window) by doing the 

following: 

(1) Lift the extrusion slightly using a flat 

tool that does not cause scoring. 

(2) Inspect for sealant on the inside and 

outside of the window between the window 

and the extrusion and between the extrusion 

and the structure. 

Note 1 to paragraph (e)(1)(2): The presence 

of a sealant bead on the extrusion parting 

lines, on the window pull-out seal parting 

lines, and on the pull-out straps is expected, 

as shown in Figure 1 of Eurocopter Alert 

Service Bulletin No. AS332–56.00.04 or ASB 

No. EC225–56A002, both dated August 8, 

2012 (ASB), as appropriate for your model 

helicopter. 

(3) If there is no sealant as shown in Photo 

1 of Figure 2 of the ASB, no further action 

is required. 

(4) If there is sealant between the structure 

and the profile as shown in Photo 2 of Figure 

2 of the ASB or if you cannot determine 

whether there is sealant, remove the 

extrusion. 

(5) Remove all sealant from the extrusion, 

the window, and the structure. 

(6) If there is any crazing, cracking or other 

damage on the extrusion, replace with an 

airworthy extrusion. 

(f) 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. 

(g) Additional Information 

(1) Eurocopter ASB No. AS332–56.00.04 

and ASB No. EC225–56A002, both dated 

August 8, 2012, contain 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. 

2012–0152, dated August 13, 2012. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5220, Emergency Exits. 

Issued in Fort Worth, Texas, on June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–14701 Filed 6–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0526; Directorate 

Identifier 2008–SW–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 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 Bell 

Model 206L–4 and 407 helicopters. This 

proposed AD would require replacing or 

reworking certain aft bearing caps. This 

proposed AD is prompted by the 

manufacture of certain freewheel aft 

bearing caps without a lubrication 

channel to allow oil flow into the aft 

bearing support assembly. The proposed 

actions are intended to prevent failure 

of the freewheel unit and subsequent 

loss of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• 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 

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 Bell 

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

Fort Worth, Texas 76101, telephone 

(817) 280–3391, fax (817) 280–6466. 

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: Eric 

Haight, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Policy Group, Fort Worth, Texas 76137, 

telephone (817) 222–5110, email: 

eric.haight@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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 37159 

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 

Transport Canada Civil Aviation 

(TCAA), which is the aviation authority 

for Canada, has issued TCAA AD No. 

CF–2004–17R1, dated February 11, 2005 

(AD No. CF–2004–17R1), which 

requires replacing or reworking 

freewheel assemblies on the Bell Model 

206L–4 and 407 helicopters. TCAA 

advises of a manufacturing oversight 

where a lubrication channel was not 

machined into the aft bearing cap of 

some freewheel units to allow oil flow 

into the aft bearing support assembly. 

TCAA states that lack of lubrication may 

adversely affect the durability and 

potentially the function of the freewheel 

unit. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCAA, 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 helicopters of the same 

type design. 

Related Service Information 

Bell has issued Alert Service Bulletin 

(ASB) No. 206L–04–129 for the Model 

206L–4 and No. 407–04–66 for the 

Model 407, both Revision A, and both 

dated December 1, 2004. The ASBs 

specify identifying the affected 

freewheel aft bearing caps. The ASBs 

also provide separate procedures, 

depending on whether helicopters are 

‘‘not exclusively used for training’’ or 

‘‘exclusively used for training,’’ for 

replacing or reworking the freewheel 

cap assembly and replacing the output 

shaft, part number (P/N) 406–040–517– 

101, and sprag and retainer, P/N 406– 

040–580–103. TCCA classified these 

ASBs as mandatory and issued AD No. 

CF–2004–17R to ensure the continued 

airworthiness of these helicopters. 

Proposed AD Requirements 

This proposed AD would require for 

each affected freewheel assembly, 

within 50 hours time-in-service (TIS), 

removing and disassembling the 

freewheel assembly, replacing the sprag, 

retainer, and the aft seal and visually 

inspecting the remaining freewheel part 

details for a missing channel. Also, the 

proposed AD would require, if the 

channel is missing, before further flight, 

replacing the cap assembly with an 

airworthy cap or reworking and 

reidentifying the existing cap by using 

a vibrating stylus to add the letter ‘‘R’’ 

to the serial number of the reworked 

cap. Reworking or replacing the affected 

cap assembly is terminating action for 

the requirements of this AD. 

Differences Between This Proposed AD 

and the TCAA AD 

This proposed AD differs from the 

TCAA AD as follows: 

• We would not use a calendar time, 

which has already passed. 

• We would require all affected 

helicopters to comply within 50 hours 

TIS; the TCAA AD has different 

compliance times as stipulated by the 

calculated average engine start cycle 

count identified in the applicable ASB, 

and a 300-hour TIS terminating action 

for modifying all affected helicopters. 

• We would not require referencing 

compliance with the ASBs as does the 

TCAA AD, and we would not require 

you to provide an affected cap for 

rework to Bell Tennessee nor require the 

original cap to be reworked by Bell 

Tennessee. 

• We would not require any action on 

‘‘spare’’ parts before installation on a 

helicopter but would require before 

installing any replacement bearing 

support assembly, ensuring that the 

rework has been done. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 212 Model 206L–4 

helicopters and 540 Model 407 

helicopters of U.S. registry; however, we 

estimate that only 80 helicopters are 

affected. We estimate that operators may 

incur the following costs in order to 

comply with this AD: It would take 

about 16 work hours to replace the 

freewheel unit for all the affected parts 

at an average labor rate of $85 per work 

hour. Required parts would cost about 

$21,600 per helicopter. Based on these 

figures, we estimate the total cost per 

helicopter would be $22,900 and the 

total cost of the proposed AD on U.S. 

operators would be $1,836,800. 

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; 

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: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

37160 Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 

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): 

Bell Helicopter Textron Canada: Docket No. 

FAA–2013–0526; Directorate Identifier 

2008–SW–14–AD. 

(a) Applicability 

This AD applies to Model 206L–4 and 407 

helicopters, with a freewheel aft bearing cap 

(cap), part number (P/N) 406–040–509–101, 

with a serial number with a prefix of ‘‘A–’’ 

and Nos. 1833 through 1912, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

certain caps being manufactured without a 

lubrication channel to allow oil flow into the 

aft bearing support assembly, which could 

result in failure of the freewheel unit and 

subsequent loss of control of the helicopter. 

(c) Comments Due Date 

We must receive comments by August 19, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 50 hours time-in-service (TIS): 

(1) Remove and disassemble each 

freewheel assembly. 

(2) Replace the sprag and retainer (item 7), 

the output shaft (item 10), and the aft seal 

(item 3), as depicted in Figure 2 of Bell Alert 

Service Bulletin (ASB) No. 206L–04–129 for 

the Model 206L–4 and ASB No. 407–04–66 

for the Model 407, both Revision A, and both 

dated December 1, 2004. 

(3) Visually inspect the remaining 

freewheel part details for a missing channel. 

(4) If the channel is missing, replace or 

rework the cap assembly by following the 

instructions depicted in Figure 3 of ASB 

206L–04–129 or ASB 407 04–66, as 

applicable for your model helicopter. Using 

a vibrating stylus, mark the letter ‘‘R’’ at the 

end of the serial number on the cap 

assembly. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Eric Haight, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

Fort Worth, Texas 76137, telephone (817) 

222–5110, email: eric.haight@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

Transport Canada Civil Aviation AD No. CF– 

2004–17R1, dated February 11, 2005. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300: Main Rotor Drive System. 

Issued in Fort Worth, Texas, on June 13, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–14693 Filed 6–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0514; Directorate 

Identifier 2012–SW–068–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 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 

Sikorsky Model S–76A, B, and C 

helicopters to require certain 

inspections of each spindle cuff 

assembly or blade fold cuff assembly for 

a crack. If there is a crack, this proposed 

AD would require replacing the cracked 

part. If there is no crack, this AD would 

require applying white paint to the 

inspection area to enhance the existing 

inspection procedure. This proposed 

AD is prompted by the discovery of 

cracks in the spindle cuffs. The 

proposed actions are intended to 

prevent failure of a spindle cuff 

assembly or blade fold cuff assembly, 

loss of a rotor blade, and subsequent 

loss of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 19, 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 

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 Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT 06614; telephone (800) 

562–4409; email 

tsslibrary@sikorsky.com; or at http:// 

www.sikorsky.com; 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: 

Nicholas Faust, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, Engine & Propeller Directorate, 

12 New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone (781) 238–7763; email 

nicholas.faust@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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS