26906 Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 

comply with this proposed AD. The 

average labor rate is $85 per hour. 

Required parts cost about $750 per 

engine. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $1,360. 

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 above, 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. 

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): 

Turbomeca S.A.: Docket No. FAA–2014– 

0219; Directorate Identifier 2014–NE– 

04–AD. 

(a) Comments Due Date 

We must receive comments by July 11, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Turbomeca S.A. Makila 

2A and Makila 2A1 turboshaft engines with 

a high-pressure (HP) fuel pump, part number 

(P/N) 0 298 91 806 0 or P/N 0 298 91 805 

0, installed, that have not incorporated 

Turbomeca modification TU 59. 

(d) Reason 

This AD was prompted by failure of two 

HP fuel pumps that resulted in engine inflight shutdowns. We are proposing this AD 

to prevent failure of the HP fuel pump, which 

could lead to an in-flight shutdown, damage 

to the engine, and forced landing or accident. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 25 flight hours (FH) or 6 months 

after the effective date of this AD, whichever 

occurs earlier, clean and visually inspect the 

splines of the HP fuel pump/metering valve 

and the module M01 drive gear for wear, 

corrosion, scaling, pitting, and chafing. 

(2) Thereafter, reinspect every 100 FH 

since-last-inspection. 

(3) If the HP fuel pump/metering valve or 

the module M01 drive gear fail the inspection 

required by this AD, replace it with a part 

eligible for installation before further flight. 

(4) After the effective date of this AD, do 

not install any HP fuel pump, HP fuel pump 

drive shaft, module 01 drive gear, or module 

M01 77-tooth gear onto any engine, or install 

any engine onto any helicopter, unless the 

HP fuel pump/metering valve and the 

module M01 drive gear passed the inspection 

required by paragraph (e) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(g) Related Information 

(1) For more information about this AD, 

contact James E. Gray, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238–7199; 

email: James.E.Gray@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0059, dated March 

10, 2014, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2014–0219. 

(3) Turbomeca S.A. Mandatory Service 

Bulletin No. 298 73 2818, Version F, dated 

March 5, 2014, pertains to the subject of this 

AD and can be obtained from Turbomeca 

S.A., using the contact information in 

paragraph (g)(4) of this AD. 

(4) For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

telex: 570 042; fax: 33 (0)5 59 74 45 15. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

May 6, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–10782 Filed 5–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0913; Directorate 

Identifier 2012–NE–23–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. TPE331–5, 

–5A, –5AB, –5B, –10, –10R, –10U, 

–10UF, –10UG, –10UGR, and –10UR 

model turboprop engines. This 

proposed AD was prompted by engine 

propeller shaft coupling failures, 

leading to unexpected propeller pitch 

changes resulting in high aerodynamic 

and asymmetric drag on the airplanes 

using these engines. This proposed AD 

would require removing certain part 

number (P/N) propeller shaft couplings 

from service. This proposed AD would 

also require inserting a copy of 

Honeywell International Inc. Operating 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 26907 

Information Letter OI331–26, dated 

March 2, 2010, into the applicable 

Airplane Flight Manuals. We are 

proposing this AD to prevent loss of 

airplane control, leading to an accident. 

DATES: We must receive comments on 

this proposed AD by July 11, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Honeywell 

International Inc., 111 S. 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Web site: http://

portal.honeywell.com. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call 781– 

238–7125. 

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–2012– 

0913; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0913; Directorate Identifier 2012– 

NE–23–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 because of 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 

We have received numerous reports of 

propeller shaft couplings, P/Ns 

3107065–1 and 865888–3, failing. These 

propeller shaft couplings experience 

fatigue cracks at the corners of the 

lubrication slots that may result in 

separation and fragmentation of the 

propeller shaft coupling. That 

separation causes a sudden loss of drive 

torque from the engine’s power section 

to the propeller shaft (called drivetrain 

uncoupling). After a drivetrain 

uncoupling, the engine’s fuel pump 

continues to provide fuel to the power 

section, and with no propeller load and 

no engine control changes by the pilot, 

the engine power section will accelerate 

to the fuel control’s overspeed governor 

set point. Even though the propeller 

drive is uncoupled, the propeller blade 

pitch is still controlled by the propeller 

governor. During this overspeed 

condition, the propeller governor is 

designed to move the propeller blades 

toward higher pitch until full feather is 

reached with the propeller not rotating 

or rotating very slowly. Under certain 

conditions the power section will 

remain at about 104% RPM with the 

propeller blades in feather position and 

the propeller not rotating or rotating 

very slowly, until the engine is shut 

down by the pilot. 

Potential Unsafe Failure Scenarios 

After a propeller shaft drivetrain 

uncoupling, the speed of the engine’s 

power section may be reduced: (1) From 

full power, by the pilot retarding the 

power lever to flight idle, which reduces 

fuel to the power section; (2) at flight 

idle, because the fuel control reduces 

the fuel supply to the power section 

and/or; (3) by fragmentation of the 

propeller shaft coupling and secondary 

damage to the gears in the gearbox. If 

the resulting speed of the power section 

falls below the propeller governor set 

point (set by the pilot-controlled 

condition lever), the propeller governor 

will move the propeller out of feather to 

a low-pitch, high-drag position. 

Also, after a propeller shaft drivetrain 

uncoupling, a pilot reacting to the 

overspeed of the power section may 

inadvertently retard the power lever to 

flight idle. Doing so will cause the 

propeller governor to move the 

feathered propeller to a low-pitch, highdrag condition. 

Several reports during maintenance 

test flights and in-service operations of 

twin-engine airplanes have shown that 

inadvertent movement of the propeller 

blade pitch to a low blade angle create 

a high aerodynamic and asymmetric 

drag with resultant uncommanded yaw 

and roll response on the airplane. 

Following this unexpected yaw and roll 

response, stabilization and control of 

the airplane may range from unusually 

difficult to catastrophic, and pilots may 

lack sufficient time to properly assess 

the engine problem, initiate an engine 

emergency shutdown, and activate the 

feather valve. 

The drivetrain uncoupling events 

described previously lead to loss of 

thrust, cause the propeller blade pitch to 

go to a low-blade angle, and create a 

high aerodynamic and asymmetric drag 

on the airplane. The low-blade angle 

may result in loss of airplane control, 

leading to an accident. After a review of 

about 40 years of National 

Transportation Safety Board fatal 

accident reports of multi-engine 

airplanes with TPE331 engines, we 

determined that certain airplanes are 

more at risk by engine-failure events 

than others. Therefore, we are proposing 

compliance times in this AD that 

address the risk by airplane after a 

propeller shaft coupling failure. 

Relevant Service Information 

Allied-Signal Aerospace Company, 

Garrett Engine Division Service Bulletin 

No. TPE331–72–0873, Revision 1, dated 

May 20, 1993, describes procedures for 

replacing the affected P/Ns of propeller 

shaft couplings with a defined 

redesigned propeller shaft coupling. 

Honeywell International Inc. 

Operating Information Letter OI331–26, 

dated March 2, 2010, describes 

emergency procedures for aircrew if a 

propeller shaft coupling fails. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
26908 Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 

Proposed AD Requirements 

This proposed AD would require 

removing propeller shaft couplings, P/

Ns 3107065–1, 865888–3, 865888–6, 

and 865888–8, from service. 

This proposed AD would also require 

inserting a copy of Honeywell 

International Inc. Operating Information 

Letter OI331–26, dated March 2, 2010, 

into the applicable Airplane Flight 

Manual, Pilot Operating Handbook, or 

Manufacturer’s Operating Manual. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 485 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about one 

hour per engine to perform the actions 

required by this proposed AD, if done 

at next turbine hot section scheduled 

inspection, and 40 hours per engine if 

done at an unscheduled access of the 

propeller shaft coupling. We also 

estimate that 400 engines would have 

the replacement actions done at a 

scheduled time of next turbine hot 

section inspection, and 85 engines 

would have the replacement actions 

done at an unscheduled access of the 

propeller shaft coupling. We also 

estimate that the average labor rate is 

$85 per hour. Required parts would cost 

about $12,000 per engine. Based on 

these figures, we estimate the total cost 

of the proposed AD to U.S. operators to 

be $6,143,000. 

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 above, 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. 

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): 

Honeywell International Inc. (Type 

Certificate Previously Held by 

AlliedSignal Inc., Garrett Engine 

Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona): 

Docket No. FAA–2012–0913; Directorate 

Identifier 2012–NE–23–AD. 

(a) Comments Due Date 

We must receive comments by July 11, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell 

International Inc. TPE331–5, –5A, –5AB, 

–5B, –10, –10R, –10U, –10UF, –10UG, 

–10UGR, and –10UR model turboprop 

engines, with a propeller shaft coupling, part 

number (P/N) 3107065–1, 865888–3, 865888– 

6, or 865888–8, installed. 

(d) Unsafe Condition 

This AD was prompted by engine propeller 

shaft coupling failures leading to unexpected 

propeller pitch changes resulting in high 

aerodynamic and asymmetric drag on the 

airplanes using these engines. We are issuing 

this AD to prevent loss of airplane control, 

leading to an accident. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Engines Installed In Mitsubishi MU–2B 

Series (MU–2 Series) Airplanes: Remove from 

service the affected propeller shaft coupling 

at the earliest of the following: 

(i) Next piece-part exposure; or 

(ii) Next turbine (hot) section inspection 

(HSI); or 

(iii) Before accumulating an additional 

1,200 cycles after the effective date of this 

AD. 

(2) Engines Installed In Construcciones 

Aeronauticas, S.A. (CASA) C–212 Series, and 

Twin Commander 690 and 695 Series 

(Jetprop Commander) Airplanes: Remove 

from service the affected propeller shaft 

coupling at the earliest of the following: 

(i) Next piece-part exposure; or 

(ii) Next turbine HSI; or 

(iii) Before accumulating an additional 

2,400 cycles after the effective date of this 

AD. 

(3) Engines Installed In British Aerospace 

Jetstream 3101 Series, Dornier Luftfahrt 

Dornier 228 Series, and M7 (formerly 

Fairchild, Swearingen) SA226 and SA227 

Series Airplanes, and All Other Airplanes 

Not Listed in this AD Using Affected Engines: 

Remove from service the affected propeller 

shaft coupling at the earliest of the following: 

(i) Next piece-part exposure; or 

(ii) Next turbine HSI; or 

(iii) Before accumulating an additional 

3,600 cycles after the effective date of this 

AD. 

(4) Inserting a Copy of Honeywell 

International Inc. Operating Information 

Letter into the FAA-Approved Flight Manual: 

Within 60 days after the effective date of 

this AD, for airplanes with engine propeller 

shaft coupling, P/N 3107065–1, 865888–3, 

865888–6, or 865888–8, installed, insert a 

copy of Honeywell International Inc. 

Operating Information Letter OI331–26, 

dated March 2, 2010, into the Emergency 

Procedures Section of the applicable 

Airplane Flight Manual, Pilot Operating 

Handbook, or Manufacturer’s Operating 

Manual. 

(f) Definition 

For the purpose of this AD, next piece-part 

exposure is when the nose cone assembly is 

removed from the engine. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any propeller shaft coupling, P/N 

3107065–1, 865888–3, 865888–6, or 865888– 

8, into any engine. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 26909 

(i) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(2) Allied-Signal Aerospace Company 

Service Bulletin No. TPE331–72–0873, 

Revision 1, dated May 20, 1993, addresses 

acceptable replacement parts, and other 

information pertaining to the subject of this 

AD. 

(3) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; phone: 800–601–3099; Web site: 

http://portal.honeywell.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

May 6, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–10783 Filed 5–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R06–OAR–2014–0214; FRL–9910–77– 

Region 6] 

Approval and Promulgation of 

Implementation Plans; New Mexico; 

Regional Haze and Interstate Transport 

Affecting Visibility State 

Implementation Plan Revisions; 

Withdrawal of Federal Implementation 

Plan for the San Juan Generating 

Station 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is proposing to approve 

revisions to the New Mexico Regional 

Haze State Implementation Plan that 

address the Best Available Retrofit 

Technology (BART) requirement for 

oxides of nitrogen (NOX) for the Public 

Service of New Mexico (PNM) San Juan 

Generating Station (SJGS) in San Juan 

County, New Mexico and the New 

Mexico Visibility Transport SIP that 

address impacts of emissions from the 

SJGS, as required by the Federal Clean 

Air Act (CAA) mandate to ensure that 

emissions from sources in New Mexico 

do not interfere with programs in other 

states to protect visibility. In 

conjunction with these proposed 

approvals, we propose to withdraw the 

federal implementation plan (FIP) that 

addresses the NOX BART and visibility 

transport requirements for the SJGS. The 

EPA is taking this action under the 

CAA. 

DATES: Comments must be received on 

or before June 11, 2014. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R06– 

OAR–2014–0214 by one of the following 

methods: 

• Federal e-Rulemaking Portal: 

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

online instructions. 

• Email: feldman.michael@epa.gov. 

• Mail or delivery: Mr. Guy 

Donaldson, Chief, Air Planning Section 

(6PD–L), Environmental Protection 

Agency, 1445 Ross Avenue, Suite 1200, 

Dallas, Texas 75202–2733. 

Instructions: Direct your comments to 

Docket No. EPA–R06–OAR–2014–0214. 

Our policy is that all comments received 

will be included in the public docket 

without change and may be made 

available online at www.regulations.gov, 

including any personal information 

provided, unless the comment includes 

information claimed to be Confidential 

Business Information (CBI) or other 

information whose disclosure is 

restricted by statute. The 

www.regulations.gov Web site is an 

‘‘anonymous access’’ system, which 

means we will not know your identity 

or contact information unless you 

provide it in the body of your comment. 

If you send an email comment directly 

to us without going through 

www.regulations.gov your email address 

will be automatically captured and 

included as part of the comment that is 

placed in the public docket and made 

available on the Internet. If you submit 

an electronic comment, we recommend 

that you include your name and other 

contact information in the body of your 

comment and with any disk or CD–ROM 

you submit. If we cannot read your 

comment due to technical difficulties 

and cannot contact you for clarification, 

we may not be able to consider your 

comment. Electronic files should avoid 

the use of special characters, any form 

of encryption, and be free of any defects 

or viruses. 

Do not submit information that you 

consider to be CBI or otherwise 

protected through www.regulations.gov 

or email. Clearly mark the part or all of 

the information that you claim as CBI. 

For CBI information in a disk or CD 

ROM that you mail to EPA, mark the 

outside of the disk or CD ROM as CBI 

and identify electronically within the 

disk or CD ROM the specific 

information that is claimed as CBI. In 

addition to one complete version of the 

comment that includes information 

claimed as CBI, you must submit a copy 

of the comment that does not contain 

the information claimed as CBI for 

inclusion in the public docket. We will 

not disclose information so marked 

except in accordance with procedures 

set forth in 40 CFR part 2. 

Docket: The index to the docket for 

this action is available electronically at 

www.regulations.gov and in hard copy 

at EPA Region 6, 1445 Ross Avenue, 

Suite 700, Dallas, Texas. While all 

documents in the docket are listed in 

the index, some information may be 

publicly available only at the hard copy 

location (e.g., copyrighted material), and 

some may not be publicly available at 

either location (e.g., CBI). To inspect the 

hard copy materials, please schedule an 

appointment with the person listed in 

the FOR FURTHER INFORMATION CONTACT

paragraph below or Mr. Bill Deese at 

214–665–7253. 

FOR FURTHER INFORMATION CONTACT: 

Michael Feldman, 214–665–9793; 

feldman.michael@epa.gov. 

SUPPLEMENTARY INFORMATION: 

Definitions 

For the purpose of this document, we 

are giving meaning to certain words or 

initials as follows: 

i. The words or initials Act or CAA 

mean or refer to the Clean Air Act, 

unless the context indicates otherwise. 

ii. The words EPA, we, us or our mean 

or refer to the United States 

Environmental Protection Agency. 

iii. The initials SIP mean or refer to 

State Implementation Plan. 

iv. The initials FIP mean or refer to 

Federal Implementation Plan. 

v. The initials RH and RHR mean or 

refer to Regional Haze and the Regional 

Haze Rule. 

vi. The initials NMED mean the New 

Mexico Environmental Department. 

vii. The initials BART mean or refer 

to Best Available Retrofit Technology. 

viii. The initials EGUs mean or refer 

to Electric Generating Units. 

ix. The initials NOX mean or refer to 

nitrogen oxides. 

x. The initials SO2 mean or refer to 

sulfur dioxide. 

xi. The initials H2SO4 mean or refer to 

sulfuric acid. 

xii. The initials PM2.5 mean or refer to 

particulate matter with an aerodynamic 

of less than 2.5 micrometers. 

xiii. The initials NAAQS mean or 

refer to the National Ambient Air 

Quality Standards. 

xiv. The initials RPOs mean or refer 

to regional planning organizations. 


tkelley on DSK3SPTVN1PROD with PROPOSALS