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

Federal Register / Vol. 78, No. 119 / Thursday, June 20, 2013 / Proposed Rules 37161 

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 

We propose to adopt a new AD for 

Sikorsky Model S–76A, B, and C 

helicopters. This proposed AD would 

require, depending on the hours timein-service (TIS) of each part, either a 

one-time nondestructive inspection 

(NDI) or a visual inspection 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 proposed AD would require 

applying white paint to a portion of 

each spindle cuff assembly or blade fold 

cuff assembly lower cuff plate to 

enhance the existing inspection 

procedure. This proposed AD is 

prompted by the discovery of five 

cracked spindle cuffs found during 

aircraft overhaul. 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. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Sikorsky issued S–76 Alert Service 

Bulletin ASB 76–65–67A, Revision A, 

dated July 18, 2012 (ASB), which 

specifies performing an NDI of the 

upper and lower cuff plate on each 

spindle cuff assembly or blade fold cuff 

assembly for a crack, either by eddy 

current, fluorescent penetrant, or 

ultrasonic inspection. If a crack 

indication is detected and not verified, 

the ASB specifies performing a different 

NDI to verify a crack. If there is a crack, 

the ASB specifies removing the spindle 

cuff assembly or blade fold cuff 

assembly from service. If a crack cannot 

be verified, the ASB specifies contacting 

Sikorsky for further instruction. Finally, 

if no crack is found, the ASB specifies 

applying white paint to a portion of the 

spindle cuff assembly or blade fold cuff 

assembly lower cuff plate to enhance 

the existing inspection procedure. 

Proposed AD Requirements 

This proposed AD would require 

within 150 hours TIS: 

• For each spindle cuff assembly or 

blade cuff assembly with 1,900 or more 

hours TIS, conducting an NDI by a 

qualified inspector by following 

specified portions of the ASB. 

• For each spindle cuff assembly or 

blade cuff assembly with less than 1,900 

hours TIS, visually inspecting each 

white paint application area for a crack 

by using a 5x or higher power 

magnifying glass. 

• If there is a crack, before further 

flight, replacing each cracked spindle 

cuff assembly or cracked blade fold cuff 

assembly with an airworthy assembly. 

• If there is no crack, applying white 

paint by following specified portions of 

the ASB. 

This proposed AD also prohibits 

installing an affected spindle cuff 

assembly or blade cuff fold assembly on 

any helicopter unless it has been 

inspected in accordance with the 

requirements of this AD. 

Differences Between This Proposed AD 

and the Service Information 

The ASB specifies contacting the 

manufacturer if suspect cracks are not 

confirmed in the spindle cuff assembly 

or blade fold cuff assembly; this 

proposed AD would not require 

contacting the manufacturer. This 

proposed AD applies to spindle cuff 

assembly, part number (P/N) 76102– 

08001–043, which was inadvertently 

omitted in the ASB. The manufacturer 

has stated that they will issue an ASB 

in the future that will also apply to this 

spindle cuff assembly. The ASB applies 

to spare parts; this proposed AD does 

not. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 181 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD, based on an average labor 

cost of $85 per work hour: It would take 

2.5 work hours to do an NDI and 2 work 

hours to apply the white paint. It would 

cost $15 in materials for the paint for 

each helicopter. Based on these 

estimates, it would cost a total of $398 

per helicopter and $72,038 for the fleet. 

If it is necessary to replace a spindle 

cuff assembly or a blade cuff assembly, 

it would take 2.5 work hours and an 

estimated parts cost of $54,000, for a 

total cost of $54,212 for each helicopter. 

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

37162 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): 

Sikorsky Aircraft Corporation: Docket No. 

FAA–2013–0514; Directorate Identifier 

2012–SW–068–AD. 

(a) Applicability 

This AD applies to Model S–76A, S–76B, 

and S–76C helicopters with a serial number 

up to and including 760822 and with a 

spindle cuff assembly, part number (P/N) 

76102–08001–043, –045 or –046, or a blade 

fold cuff assembly, P/N 76150–09601–041, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a spindle cuff assembly or blade fold 

cuff assembly. This condition could result in 

failure of a spindle cuff assembly or blade 

fold cuff assembly, loss of a rotor blade, 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 unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

Within 150 hours time-in-service (TIS): 

(1) For each spindle cuff assembly or blade 

cuff assembly with 1,900 or more hours TIS, 

conduct a nondestructive (NDI) inspection by 

following the Accomplishment Instructions, 

paragraph 3.B., of Sikorsky S–76 Alert 

Service Bulletin ASB 76–65–67A, Revision 

A, dated July 18, 2012 (ASB), except this AD 

does not require you to contact Sikorsky 

Aircraft Corporation. This inspection must be 

done by a level 2 or higher technician with 

National Aerospace Standard 410 or 

equivalent certification. 

(2) For each spindle cuff assembly or blade 

cuff assembly with less than 1,900 hours TIS, 

visually inspect the area indicated in Figure 

4 of the ASB as ‘‘white paint application 

area’’ for a crack by using a 5x or higher 

power magnifying glass. 

(3) If there is a crack, before further flight, 

replace the cracked part. 

(4) If there is no crack, apply white paint 

by following the Accomplishment 

Instructions, paragraph 3.D., of the ASB. 

(5) Do not install an affected spindle cuff 

assembly or blade fold cuff assembly on any 

helicopter unless it has been inspected in 

accordance with paragraphs (d)(1) through 

(d)(4) of this AD. 

(e) Special Flight Permit 

Special flight permits will not be issued. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Nicholas Faust, Aviation Safety Engineer, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; telephone (781) 238– 

7763; email nicholas.faust@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 

For service information identified in this 

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. 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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220 Main Rotor Head. 

Issued in Fort Worth, Texas, on June 12, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–14699 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–2013–0518; Directorate 

Identifier 2009–SW–021–AD] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. (Type Certificate Currently Held 

by AgustaWestland S.p.A) (Agusta) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Agusta 

Model A109A, A109AII, and A109C 

helicopters with a certain third stage 

turbine wheel installed. This proposed 

AD would require installing a placard 

on the instrument panel and revising 

the limitations section of the rotorcraft 

flight manual (RFM). This proposed AD 

is prompted by several incidents of 

third stage engine turbine wheel 

failures, which were caused by 

excessive vibrations at certain engine 

speeds during steady-state operations. 

The proposed actions are intended to 

alert pilots to avoid certain engine 

speeds during steady-state operations, 

prevent failure of the third stage engine 

turbine, engine power loss, 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 Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39–0331–711133; 

fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 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: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email 

chinh.vuong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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