74 Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 

occurs first, do an inspection of the MLG 

inboard retraction actuator bracket for any 

uncertified pin having part number (P/N) 

49131–1, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–32–044, dated May 

29, 2013. 

(h) Replacement 

If any uncertified pin having P/N 49131– 

1 is found during the inspection required by 

paragraph (g) of this AD, before further flight, 

replace all uncertified pins, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–044, 

dated May 29, 2013. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANE–170, FAA, 

New York Aircraft Certification Office (ACO), 

1600 Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone 516–228–7363; 

fax 516–794–5531, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the NYACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. Before 

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office/certificate 

holding district office. The AMOC approval 

letter must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Airworthiness Directive CF–2013–23, dated 

August 13, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating it in Docket No. 

FAA–2013–1070. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on 

December 20, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31301 Filed 12–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1090; Directorate 

Identifier 2013–SW–017–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Eurocopter France (Eurocopter) Model 

EC120B and EC130B4 helicopters. This 

proposed AD would require replacing 

parts of the sliding door star support 

attachment assembly, depending on the 

outcome of required inspections. This 

proposed AD is prompted by a report 

that passengers in a Eurocopter 

helicopter were forced to exit through 

the pilot door after landing because they 

could not open the sliding door from the 

inside. The proposed actions are 

intended to prevent failure of the sliding 

door star support attachment, which 

could inhibit operation of a sliding door 

from inside, delaying the evacuation of 

passengers during an emergency. 

DATES: We must receive comments on 

this proposed AD by March 3, 2014. 

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 

European Aviation Safety Agency 

(EASA) 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 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 75 

proposal in light of the comments we 

receive. 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2013– 

0093, dated April 15, 2013, and 

corrected on April 17, 2013. EASA 

issued AD No. 2013–0093 to correct an 

unsafe condition for Eurocopter Model 

EC120B and EC130B4 helicopters after a 

case was reported where passengers 

could not open a helicopter’s sliding 

door after landing. An investigation 

revealed a failure of the sliding door star 

axle support, EASA states. 

‘‘This condition, if not corrected, 

could delay the evacuation from the 

helicopter in case of emergency, 

possibly resulting in injury to the 

occupants,’’ according to EASA. As a 

result, EASA AD No. 2013–0093 

requires inspecting the upper and lower 

locking pin control rod end fittings to 

determine if they are twisted or broken 

and replacing the end fittings if they are 

twisted or broken. If the end fittings are 

not twisted or broken, the EASA AD 

requires performing a dye penetrant 

inspection of the star support pin and 

then reinforcing the sliding door star 

support with carbon fabric plies soaked 

with adhesive. 

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 issued Alert Service 

Bulletin (ASB) No. EC120–52A014 for 

Model EC120B helicopters and ASB No. 

EC130–52A009 for Model EC130B4 

helicopters, both Revision 1, and both 

dated January 25, 2013. The ASBs report 

that the star support pin ruptured on the 

kinematics of the sliding door locking 

system. The rupture prevents sliding 

doors from operating, the ASBs report. 

The ASBs call for visual and dye 

penetrant inspections of sections of the 

sliding door attachment assembly and 

reinforcement of the sliding door star 

support. 

Proposed AD Requirements 

This proposed AD would require, 

within 165 hours time-in-service, 

visually inspecting the upper and lower 

locking pin control rod end fittings, and 

replacing the control end fitting before 

further flight if it is bent, twisted, or 

broken. This proposed AD would also 

require cleaning and dye penetrant 

inspecting the star support pin for a 

crack, and replacing the star support pin 

before further flight if there is a crack. 

Lastly, this proposed AD would require 

reinforcing the sliding door star support 

stringer by installing three carbon fabric 

plies. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 284 helicopters of U.S. 

Registry and that labor costs average $85 

per work-hour. Based on these 

estimates, we would expect the 

following costs: 

• Visually inspecting the upper and 

lower locking pin control rod end 

fittings would require 1 work-hour and 

a minimal amount for consumable 

materials for a cost of $85 per 

helicopter, or $24,140 for the U.S. fleet. 

• Replacing the upper and lower 

locking pin control rod end fittings with 

airworthy fittings would require 5 workhours for a labor cost of $425. Parts 

would cost $242 for a cost of $667 per 

helicopter. 

• Dye penetrant inspecting the star 

support pin for a crack would require 2 

work-hours and no parts for a cost of 

$170 per helicopter. 

• Replacing the star support pin 

would require 5 work-hours. Parts 

would cost $200 for a total cost of $625 

per helicopter. 

• Installing three carbon fabric plies 

to reinforce the sliding door star support 

would require 5 work-hours. Parts 

would cost $200 for a total cost of $625 

per 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: 

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– 

1090; Directorate Identifier 2013–SW– 

017–AD. 

(a) Applicability 

This AD applies to the following 

Eurocopter France (Eurocopter) helicopters, 

certificated in any category, except those 

helicopters with modification 07 3796 or 07 

2921 installed: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

76 Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 

(a) Model EC120B helicopters, serial 

numbers up to and including 1367, with a 

sliding door, Part Number (P/N) 

C526A2370101, installed; and 

(b) Model EC130B4 helicopters with a 

sliding door, P/N C526S1101051, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

failure of the sliding door star axle support. 

This condition could prevent operation of a 

sliding door from inside, which could delay 

evacuation of passengers during an 

emergency. 

(c) Comments Due Date 

We must receive comments by March 3, 

2014. 

(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 165 hours time-in-service: 

(1) Visually inspect each upper and lower 

locking pin control rod end fitting (control 

end fitting) for a bend, twist, or breakage. If 

a control end fitting is bent, twisted, or 

broken, before further flight, replace the 

control end fitting with an airworthy control 

end fitting. 

(2) Clean and dye penetrant inspect the star 

support pin for a crack in the areas identified 

as Zone X and Zone Y in Figure 3 of 

Eurocopter Alert Service Bulletin (ASB) No. 

EC120–52A014 or ASB No. EC130–52A009, 

both Revision 1, and both dated January 25, 

2013, as applicable to your model helicopter. 

If there is a crack in the star support pin, 

before further flight, replace the star support 

pin with an airworthy star support pin. 

(3) Reinforce the sliding door star support 

stringer by installing three carbon fabric plies 

by following the Accomplishment 

Instructions, paragraph 3.B.2.d, of ASB No. 

EC120–52A014 or ASB No. EC130–52A009, 

as applicable to your model helicopter, 

except this AD does not require you to 

comply with paragraph 3.C. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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 (EASA) AD 

2013–0093, dated April 15, 2013. You may 

view the EASA AD in Docket No. FAA– 

2013–1090 on the Internet at http://

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5220, Emergency Exits. 

Issued in Fort Worth, Texas, on December 

18, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate,Aircraft Certification Service. 

[FR Doc. 2013–31298 Filed 12–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1068; Directorate 

Identifier 2013–NM–196–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This proposed AD was 

prompted by reports of failure of the 

high pressure shutoff valves (HPSOVs) 

causing the timer and monitor unit 

(TMU) to become inoperative since the 

HPSOV and the TMU are on the same 

circuit breaker. This proposed AD 

would require a wiring modification to 

segregate the HPSOV power supply 

from the TMU. We are proposing this 

AD to prevent an inoperative TMU, 

which could result in the loss of the 

automatic de-icing mode, and lead to an 

increased workload for the flight crew 

and loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by February 18, 2014. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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 MCAI, 

the regulatory 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 FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–1068; Directorate Identifier 

2013–NM–196–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

mstockstill on DSK4VPTVN1PROD with PROPOSALS