Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 39007 

(i) Additional Information 

(1) Bell Alert Service Bulletin No. 429–15– 

16, Revision B, dated June 15, 2016, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/ 

files/. You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

Transport Canada AD No. CF–2015–16R2, 

dated April 17, 2017. You may view the 

Transport Canada AD on the internet at 

http://www.regulations.gov in the AD Docket. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720 Tail Rotor Control System. 

Issued in Fort Worth, Texas, on July 23, 

2018. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16637 Filed 8–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0669; Product 

Identifier 2017–SW–041–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2016–25– 

19 for Airbus Helicopters (previously 

Eurocopter France) Model AS350B3 and 

EC130B4 helicopters. AD 2016–25–19 

requires inspecting the pilot’s and copilot’s throttle twist for proper 

operation. This proposed AD would 

retain the requirements of AD 2016–25– 

19 and add certain model helicopters to 

the applicability. The actions of this 

proposed AD are intended to address 

the unsafe condition on these 

helicopters. 

DATES: We must receive comments on 

this proposed AD by October 9, 2018. 

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 by searching for 

and locating Docket No. FAA–2018– 

0669; or in person at Docket Operations 

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 

Docket Operations (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 rule, contact Airbus 

Helicopters, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. You 

may review service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

george.schwab@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 

We issued AD 2016–25–19, 

Amendment 39–18745 (81 FR 95854, 

December 29, 2016) (AD 2016–25–19), 

for Airbus Helicopters Model AS350B3 

and EC130B4 helicopters with the 

ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine 

Control (FADEC) and with new twist 

grip modification (MOD) 073254 (for the 

Model AS350B3 helicopter) or MOD 

073773 (for the Model EC130B4 

helicopter). AD 2016–25–19 requires 

repetitively inspecting the wiring, 

performing an insulation test, inspecting 

the pilot and copilot throttle twist grip 

controls, and testing the pilot and 

copilot throttle twist grip controls for 

proper functioning. AD 2016–25–19 was 

prompted by AD No. 2013–0191–E, 

dated August 22, 2013 (EASA AD 2013– 

0191–E), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA advised 

that the switches in the engine ‘‘IDLE’’ 

or ‘‘FLIGHT’’ control system could be 

affected by the corrosive effects of a saltladen atmosphere, which could lead to 

engine power loss. EASA AD 2013– 

0191–E required repetitive inspections 

for corrosion, application of corrosion 

protection on the switches, and testing 

of the insulation and switches of the 

engine idle and flight control system. 

The actions required in AD 2016–25–19 

are intended to prevent unintended 

touchdown to the ground at a flight-idle 

power setting during a practice 

autorotation, damage to the helicopter, 

and injury to occupants. 

Actions Since AD 2016–25–19 Was 

Issued 

Since we issued AD 2016–25–19, 

EASA issued AD No. 2017–0052, dated 

March 24, 2017, which superseded 

EASA AD No. 2013–0191–E, dated 

August 22, 2013. EASA advised that 

Airbus Helicopters had added 


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39008 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 

clarifications to the operational 

procedure, introduced a modification to 

apply water-tight protection to the 

microswitch connectors, and extended 

the applicability to helicopters with a 

Turbomecca ARRIEL 2D engine 

installed. 

EASA subsequently issued AD No. 

2017–0059, dated April 6, 2017, which 

superseded EASA AD No. 2017–0052 to 

correct the applicability by including 

Model EC130T2 helicopters. 

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 Under 

1 CFR Part 51 

We reviewed one document that copublishes three Emergency Alert Service 

Bulletin (EASB) identification numbers: 

No. 05.00.61, Revision 3, dated June 15, 

2015, for Model AS350B3 helicopters; 

No. 05.00.41, Revision 2, dated June 15, 

2015, for the non-FAA type certificated 

Model AS550C3 helicopter; and No. 

05A009, Revision 3, dated June 15, 

2015, for Model EC130B4 helicopters. 

EASB Nos. 05.00.61 and 05A009 are 

incorporated by reference in AD 2016– 

25–19 and will be retained for the 

requirements of this proposed AD. 

EASB No. 05.00.41 is not incorporated 

by reference in AD 2016–25–19 and will 

not be incorporated by reference in this 

proposed AD. This service information 

applies to helicopters with an Arriel 

2B1 engine installed and describes 

procedures for a functional check and 

installation of protection for microcontacts (microswitches) 53Ka, 53Kb, 

and 65K (IDLE/FLIGHT mode). 

We also reviewed one document that 

co-publishes three EASB identification 

numbers: No. 05.00.77, Revision 1, 

dated June 15, 2015, for Model AS350B3 

helicopters; No. 05.00.52, Revision 1, 

dated June 15, 2015, for the non-FAA 

type certificated Model AS550C3 

helicopter; and No. 05A014, Revision 1, 

dated June 15, 2015, for Model EC130T2 

helicopters. EASB Nos. 05.00.77 and 

05A014 will be incorporated by 

reference in this proposed AD. EASB 

No. 05.00.52 will not be incorporated by 

reference in this proposed AD. This 

service information applies to 

helicopters with an Arriel 2D engine 

installed and describes procedures for a 

check of the protection for microcontacts (microswitches) 53Ka, 53Kb, 

and 65K (IDLE/FLIGHT mode). 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Proposed AD Requirements 

This proposed AD would retain the 

inspection requirements of AD 2016– 

25–19 but would add Model AS350B3 

helicopters with an Arriel 2D engine 

installed and Model EC130T2 

helicopters. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD requires the initial 

inspections within 10 flight hours or 7 

days; this proposed AD requires 

compliance before the next autorotation 

training flight or before 100 hours timein-service, whichever occurs earlier, as 

the unsafe condition only occurs when 

transitioning the throttle in flight from 

flight to idle and back to flight, such as 

during a practice autorotation. 

Additionally, the EASA AD requires 

installing Airbus Helicopters 

modification 074263; this proposed AD 

does not as it does not correct the unsafe 

condition. 

Interim Action 

We consider this proposed AD to be 

an interim action. If final action is later 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 692 helicopters of U.S. 

Registry. 

We estimate that operators will incur 

the following costs in order to comply 

with this proposed AD. At an average 

labor rate of $85 per work hour, it 

would take about 4 work hours for the 

inspections and any necessary 

maintenance, for a total cost of $340 per 

helicopter and $235,280 for the U.S. 

fleet per inspection cycle. 

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 

removing Airworthiness Directive (AD) 

2016–25–19, Amendment 39–18745 (81 

FR 95854, December 29, 2016), and 

adding the following new AD: 


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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 39009 

Airbus Helicopters (Previously Eurocopter 

France): Docket No. FAA–2018–0669; 

Product Identifier 2017–SW–041–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Model AS350B3 helicopters with an 

ARRIEL 2B1 engine with the two-channel 

Full Authority Digital Engine Control 

(FADEC) and with new twist grip 

modification (MOD) 073254 or with an 

ARRIEL 2D engine installed; 

(2) Model EC130B4 helicopters with an 

ARRIEL 2B1 engine with the two-channel 

FADEC and with new twist grip MOD 073773 

installed; and 

(3) Model EC130T2 helicopters with an 

ARRIEL 2D engine installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of one of the two contactors, 53Ka or 

53Kb, which can prevent switching from 

‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during 

autorotation training making it impossible to 

recover from a practice autorotation and 

compelling the pilot to continue the 

autorotation to the ground. This condition 

could result in unintended touchdown to the 

ground at a flight-idle power setting during 

a practice autorotation, damage to the 

helicopter, and injury to occupants. 

(c) Affected ADs 

This AD replaces AD 2016–25–19, 

Amendment 39–18745 (81 FR 95854, 

December 29, 2016). 

(d) Comments Due Date 

We must receive comments by October 9, 

2018. 

(e) 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. 

(f) Required Actions 

(1) Before the next practice autorotation or 

within 100 hours time-in-service (TIS), 

whichever occurs first, inspect the wiring, 

perform an insulation test, inspect the pilot 

and copilot throttle twist grip controls, and 

test the pilot and copilot throttle twist grip 

controls for proper functioning by following 

the Accomplishment Instructions, paragraph 

3.B.1 through 3.B.6, of Airbus Helicopters 

Emergency Alert Service Bulletin (EASB) No. 

05.00.61, Revision 3, dated June 15, 2015, for 

Model AS350B3 helicopters with an ARRIEL 

2B1 engine; EASB No. 05.00.77, Revision 1, 

dated June 15, 2015, for Model AS350B3 

helicopters with an ARRIEL 2D engine; EASB 

No. 05A009, Revision 3, dated June 15, 2015, 

for Model EC130B4 helicopters; or EASB No. 

05A014, Revision 1, dated June 15, 2015, for 

Model EC130T2 helicopters, as appropriate 

for your model helicopter. 

(2) Repeat the inspections in paragraph 

(f)(1) of this AD at intervals not to exceed the 

following compliance times. For purposes of 

this AD, salt laden conditions exist when a 

helicopter performs a flight from a takeoff 

and landing area, heliport, or airport less 

than 0.5 statute mile from salt water or 

performs a flight within 0.5 statute mile from 

salt water below an altitude of 1,000 ft. above 

ground or sea level. 

(i) For helicopters that have operated in 

salt laden conditions since the previous 

inspection required by this AD, at intervals 

not to exceed 330 hours TIS. 

(ii) For helicopters that have not operated 

in salt laden conditions since the previous 

inspection required by this AD, at intervals 

not to exceed 660 hours TIS. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, Rotorcraft Standards Branch, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, 10101 Hillwood 

Parkway, Fort Worth, Texas 76177; telephone 

(817) 222–5110; email 9-ASW-FTW-AMOCRequests@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2017–0059, dated April 6, 2017. You may 

view the EASA AD on the internet at http:// 

www.regulations.gov in the AD Docket. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7697 Engine Control System Wiring. 

Issued in Fort Worth, Texas, on July 11, 

2018. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16494 Filed 8–7–18; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R03–OAR–2018–0153; FRL–9981– 

76—Region 3] 

Approval and Promulgation of Air 

Quality Implementation Plans; 

Maryland; Amendment to Control of 

Emissions of Volatile Organic 

Compounds From Consumer Products 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is proposing to approve a 

state implementation plan (SIP) revision 

submitted by the State of Maryland. 

This revision pertains to Code of 

Maryland Regulations (COMAR) 

26.11.32—Control of Emissions of 

Volatile Organic Compounds (VOCs) 

from Consumer Products. This action is 

being taken under the Clean Air Act 

(CAA). 

DATES: Written comments must be 

received on or before September 7, 

2018. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R03– 

OAR–2018–0153 at http://

www.regulations.gov, or via email to 

Susan Spielberger, Associate Director, 

Office of Air Planning and Programs, 

Spielberger.Susan@epa.gov. For 

comments submitted at Regulations.gov, 

follow the online instructions for 

submitting comments. Once submitted, 

comments cannot be edited or removed 

from Regulations.gov. For either manner 

of submission, EPA may publish any 

comment received to its public docket. 

Do not submit electronically any 

information you consider to be 

confidential business information (CBI) 

or other information whose disclosure is 

restricted by statute. Multimedia 

submissions (audio, video, etc.) must be 

accompanied by a written comment. 

The written comment is considered the 

official comment and should include 

discussion of all points you wish to 

make. EPA will generally not consider 

comments or comment contents located 

outside of the primary submission (i.e. 

on the web, cloud, or other file sharing 

system). For additional submission 

methods, please contact the person 

identified in the FOR FURTHER

INFORMATION CONTACT section. For the 

full EPA public comment policy, 

information about CBI or multimedia 

submissions, and general guidance on 

making effective comments, please visit 

http://www2.epa.gov/dockets/ 

commenting-epa-dockets. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Becoat (215) 814–2036, or by 

email at becoat.gregory@epa.gov. 

SUPPLEMENTARY INFORMATION: On 

November 16, 2017, the Maryland 

Department of Environment (MDE) 

submitted a revision to its SIP for 

COMAR 26.11.32—Control of Emissions 

of Volatile Organic Compounds from 

Consumer Products. The amendment is 

part of Maryland’s strategy to achieve 

and maintain the 8-hour ozone national 

ambient air quality standards (NAAQS) 

throughout the State. 

I. Background 

EPA has designated certain areas 

within Maryland as nonattainment for 

the 2008 ozone NAAQS. See 40 CFR 


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