33768 Federal Register / Vol. 78, No. 108 / Wednesday, June 5, 2013 / Proposed Rules 

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 (Eurocopter): Docket No. 

FAA–2013–0480; Directorate Identifier 

2012–SW–090–AD. 

(a) Applicability 

This AD applies to Eurocopter Model SA– 

365N, SA–365N1, AS–365N2, AS 365 N3, EC 

155B, EC155B1, AS332C, AS332L, AS332L1, 

AS332L2, and EC225LP helicopters with an 

EADS Sogerma pilot or co-pilot seat, part 

number (P/N) 2510106–03–00 or P/N 

2510106–06–00, with a serial number 720 

through 1451, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

missing weld on a seat rear beam, which 

could result in failure of the seat and injury 

to the pilot during a hard landing. 

(c) Comments Due Date 

We must receive comments by August 5, 

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 

(1) Within 50 hours time-in-service, using 

a mirror, inspect the rear beam of each seat 

for weld beads in the areas depicted in the 

Appendix, Figure 1, of Eurocopter Alert 

Service Bulletin (ASB) No. AS365–25.01.18 

for model SA–365N, SA–365N1, AS–365N2, 

and AS 365 N3 helicopters; ASB No. EC155– 

25A114 for model EC155 B and EC155B1 

helicopters; ASB No. AS332–25.02.49 for 

model AS332C, AS332L, AS332L1, and 

AS332 L2 helicopters; and ASB No. EC225– 

25A110 for model EC225LP helicopters. All 

ASBs are Revision 1 and dated August 9, 

2012. 

(2) If any weld bead is missing from the 

rear beam, before further flight, remove the 

seat and replace it with an airworthy seat. 

(3) Do not install a seat listed in paragraph 

(a) of this AD on any helicopter unless it has 

been inspected as required by this AD. 

(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 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0206, dated October 2, 2012. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2510: Flight Compartment Equipment. 

Issued in Fort Worth, Texas, on May 28, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13300 Filed 6–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0478; Directorate 

Identifier 2012–SW–092–AD] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. (Type Certificate Currently Held 

by AgustaWestland S.p.A.) Helicopters 

(Agusta) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Agusta Model A109C, A109E, A109S, 

A109K2, and AW109SP helicopters. 

This proposed AD would require 

inspecting the lock wires securing the 

tail rotor (T/R) duplex bearing locking 

nut (locking nut) to determine whether 

any lock wires are missing or damaged. 

This proposed AD is prompted by 

reports of loosening T/R locking nuts, 

which if not corrected, could result in 

failure of the T/R and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 5, 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: 

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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 108 / Wednesday, June 5, 2013 / Proposed Rules 33769 

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. 2012– 

0195–E, dated September 24, 2012, and 

corrected September 25, 2012 (AD 

2012–0195–E), to correct an unsafe 

condition for certain Agusta Model 

A109E, A109LUH, A109S, AW109SP, 

A109C, and A109K2 helicopters. EASA 

advises that they have received reports 

of the T/R locking nut, part number (P/ 

N) 109–0130–97, loosening on A109 

helicopters. According to EASA, an 

investigation revealed that, in every 

occurrence, one or both of the lock 

wires securing the locking nut were 

either damaged or absent from the T/R. 

EASA states that this condition, if not 

detected and corrected, could lead to 

failure of the T/R function and 

subsequent loss of control of the 

helicopter. The EASA AD requires 

repetitively inspecting the lock wires 

which secure the T/R locking nut for 

missing and damaged lock wires. The 

EASA AD also requires removing and 

reassembling the housing and slider 

group of the T/R rotating controls, 

which is terminating action for the 

repetitive inspections. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, 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 helicopters of the same 

type design. 

Related Service Information 

Agusta has published Bollettino 

Tecnico (BT) No. 109–134 for Model 

A109C helicopters, BT No. 109EP–121 

for Model A109E helicopters, BT No. 

109S–48 for Model A109S helicopters, 

BT No. 109K–54 for Model A109K2 

helicopters, and BT No. 109SP–051 for 

Model AW109SP helicopters. All of the 

BTs are dated September 21, 2012. The 

BTs specify procedures for inspecting 

the lock wires of the T/R locking nut 

and for removing and reassembling the 

housing and slider group of the T/R 

rotating controls. 

Proposed AD Requirements 

This proposed AD would require: 

• Within 5 hours time-in-service (TIS) 

inspecting both lock wires which secure 

the T/R locking nut to the housing to 

determine that both wires are present 

and not damaged. If only one wire is 

installed and it is not damaged, before 

further flight, installing a second lock 

wire. If one or both lock wires are 

installed, and either one or both are 

damaged, before further flight, removing 

and reassembling the housing and slider 

group of the T/R rotating controls. 

• Within 25 hours TIS from the initial 

inspection, and thereafter at intervals 

not exceeding 25 hours TIS, inspecting 

both lock wires to determine that both 

wires are present and not damaged. If 

one or both lock wires are installed, and 

either one or both are damaged, before 

further flight, removing and 

reassembling the housing and slider 

group of the T/R rotating controls. 

• Within 100 hours TIS, removing 

and reassembling the housing and slider 

group of the T/R rotating controls. 

• Removing and reassembling the 

housing and slider group of the T/R 

rotating controls, either within 100 

hours TIS or because a lock wire is 

damaged, is terminating action for the 

repetitive inspections. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD requires reassembling 

the housing and slider group within 100 

flight hours or 7 months, while the 

proposed AD would require this action 

within 100 hours TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 146 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 rate of $85 per hour, 

inspecting the lock wire will require 

about 0.25 work-hour, for a cost per 

helicopter of $22 and a total cost to U.S. 

operators of $3,212 per inspection cycle. 

If necessary, installing a lock wire will 

require about 0.25 work-hour and the 

required parts cost would be negligible, 

for a cost per helicopter of $22 and a 

total cost to U.S. operators of $3,212. 

Removing and reassembling the housing 

and slider group of the T/R rotating 

controls would require about 8 workhours, for a cost per helicopter of $680 

and a total cost to U.S. operators of 

$99,280. 

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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
33770 Federal Register / Vol. 78, No. 108 / Wednesday, June 5, 2013 / Proposed Rules 

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): 

Agusta S.P.A. Helicopters (Type Certificate 

Currently Held by Agustawestland 

S.P.A.) (AGUSTA): Docket No. FAA– 

2013–0478; Directorate Identifier 2012– 

SW–092–AD. 

(a) Applicability 

This AD applies to Agusta Model A109C, 

A109S, and A109K2 helicopters, all serial 

numbers; Model A109E helicopters, serial 

number (S/N) 11002 through 11807 except S/ 

N 11796; and Model AW109SP helicopters, 

S/N 22202 through 22278, except S/N 22239, 

22264, 22266, 22272, 22273, 22275, and 

22277, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

missing or broken lock wire securing the tail 

rotor (T/R) duplex bearing locking nut 

(locking nut). This condition could result in 

loosening of the locking nut, failure of the T/ 

R, and subsequent loss of control of the 

helicopter. 

(c) Comments Due Date 

We must receive comments by August 5, 

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 

(1) Within 5 hours time-in-service (TIS), 

inspect each lock wire securing the T/R 

locking nut to the housing. 

(i) If only one lock wire is installed and it 

is not damaged, before further flight, install 

a second lock wire. 

(ii) If one or both lock wires are installed, 

and either one or both are damaged, before 

further flight, remove and reassemble the 

housing and slider group of the T/R rotating 

controls. 

(2) Within 25 hours TIS from the 

inspection required by paragraph (e)(1) of 

this AD, and thereafter at intervals not 

exceeding 25 hours TIS, inspect the lock 

wires which secure the T/R locking nut to the 

housing. If either lock wire is missing or 

damaged, before further flight, remove and 

reassemble the housing and slider group of 

the T/R rotating controls. 

(3) Within 100 hours TIS, remove and 

reassemble the housing and slider group of 

the T/R rotating controls. 

(4) Removing and reassembling the 

housing and slider group of the T/R rotating 

controls as required by either paragraph 

(e)(1)(ii) or (e)(2) is terminating action for this 

AD. 

(f) Special flight permit 

Special flight permits are prohibited. 

(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) Agusta Bollettino Tecnico (BT) No. 

109–134 for Model A109C helicopters, BT 

No. 109EP–121 for Model A109E helicopters, 

BT No. 109S–48 for Model A109S 

helicopters, BT No. 109K–54 for Model 

A109K2 helicopters, and BT No. 109SP–051 

for Model AW109SP helicopters, all dated 

September 21, 2012, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

service information identified in this 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0195–E, dated September 24, 2012, and 

corrected September 25, 2012. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400: Tail Rotor System. 

Issued in Fort Worth, Texas, on May 28, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–13293 Filed 6–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0481; Directorate 

Identifier 2011–SW–003–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. 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 

Helicopter Textron, Inc. (Bell) Model 

206A, 206B, 206L, 206L–1, 206L–3, 

206L–4, and 407 helicopters with an 

Apical Industries, Inc. (Apical) 

emergency float kit installed under 

supplemental type certificate (STC) 

number SR01535LA. This proposed AD 

would require inspecting, labeling, and 

replacing the float inflation hoses. This 

proposed AD is prompted by an 

incident in which the floats installed on 

a helicopter failed to deploy. The 

proposed actions are intended to 

prevent failure of the emergency 

floatation gear to deploy during an 

emergency event. 

DATES: We must receive comments on 

this proposed AD by August 5, 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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS