73462 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2013–0978; Directorate Identifier 2013– 

NM–120–AD. 

(a) Comments Due Date 

We must receive comments by January 21, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–400ER series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

767–29–0113, dated May 29, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 29, Hydraulic Power. 

(e) Unsafe Condition 

This AD was prompted by reports of 

turbine wheel bursts in the air driven pump 

(ADP) turbine gearbox assembly (TGA), 

which resulted in the release of high energy 

fragments. We are issuing this AD to prevent 

fragments from an uncontained turbine 

wheel burst penetrating the fuselage and 

striking passengers, or penetrating the wingto-body fairing and striking ground handling 

or maintenance personnel, causing serious 

injury. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Turbine Gearbox 

Assembly 

Except as required by paragraph (i) of this 

AD: At the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 767–29–0113, dated May 29, 

2013, replace the existing ADP TGA having 

part number N012000000 or N012000000–1 

with an improved ADP TGA having part 

number N012000000–2 or N012000000–3, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 767–29–0113, dated May 29, 

2013. 

Note 1 to paragraph (g) of this AD: 

Guidance on modifying an existing ADP TGA 

so it can be re-identified as part number 

N012000000–2 or N012000000–3 can be 

found in Fairchild Controls Service Bulletin 

N012000000–29–03, Revision 2, dated 

January 29, 2013. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an ADP TGA having part 

number N012000000 or N012000000–1 on 

any airplane. 

(i) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 767–29–0113, dated May 29, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(k) Related Information 

(1) For more information about this AD, 

contact Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6468; fax: 425–917– 

6190; email: kenneth.frey@faa.gov. 

(2) For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, 

MC2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; Internet https://

www.myboeingfleet.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 26, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–29136 Filed 12–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1024; Directorate 

Identifier 2013–NM–140–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–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD was 

prompted by reports of a fractured wingto-fuselage strut attachment joint bolt. 

This proposed AD would require doing 

a torque check of all wing-to-fuselage 

strut attachment joint bolts, and 

repairing or replacing if necessary. For 

certain airplanes this proposed AD 

would require a detailed inspection for 

corrosion, damage, and wear of each 

wing-to-fuselage strut attachment joint 

bolt and associated hardware, and 

replacing if necessary; and a borescope 

inspection for corrosion and damage of 

the bore hole and barrel nut threads, 

and repairing or replacing if necessary. 

We are proposing this AD to detect and 

correct fractured bolts, which could 

result in reduced structural integrity of 

the wing-to-fuselage strut attachment 

joint and subsequent loss of the wing. 

DATES: We must receive comments on 

this proposed AD by January 21, 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 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 73463 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

You may view this 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 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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7306; 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–2013–1024; Directorate Identifier 

2013–NM–140–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 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–17R1, 

dated June 27, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

There have been two in-service reports of 

a wing-to-fuselage strut attachment joint bolt 

found fractured during routine maintenance. 

Laboratory examination of one fractured bolt 

revealed that the fracture was attributed to 

stress corrosion cracking. 

Failure of the bolts could compromise the 

structural integrity of the wing-to-fuselage 

strut attachment joint and could lead to a 

subsequent loss of the wing. 

This [Canadian] AD mandates the 

inspection and rectification, as required, of 

the wing-to-fuselage strut attachment joint 

bolts and associated hardware. 

* * * * * 

Required actions include doing a torque 

check of wing-to-fuselage strut 

attachment joint bolts, and repairing or 

replacing if necessary. For certain 

airplanes, required actions include a 

detailed inspection for corrosion, 

damage (including but not limited to 

scratching, cracking, pitting, cross 

threads, etc.), and wear of each wing-tofuselage strut attachment joint bolt and 

associated hardware, and replacement if 

necessary; and a borescope inspection 

for corrosion and damage of the bore 

hole and barrel nut threads, and repair 

or replacement if necessary. 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– 

2013–1024. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 8–57–47, Revision A, dated 

May 29, 2013. The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, this 

proposed AD would require that the 

repair approval specifically refer to the 

FAA AD. This change is intended to 

clarify the method of compliance and to 

provide operators with better visibility 

of repairs that are specifically developed 

and approved to correct the unsafe 

condition. In addition, we use the 

phrase ‘‘its delegated agent, or by the 

DAH with State of Design Authority 

design organization approval, as 

applicable’’ in this proposed AD to refer 

to a DAH authorized to approve 

required repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 94 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD. 

We also estimate that it would take 

about 107 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $5,476 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $1,369,674, or 

$14,571 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the repairs or replacements 

specified in this proposed AD. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
73464 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 

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 proposed 

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; 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 AD: 

Bombardier, Inc.: Docket No. FAA–2013– 

1024; Directorate Identifier 2013–NM– 

140–AD. 

(a) Comments Due Date 

We must receive comments by January 21, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes; certificated in any 

category; serial numbers 003 through 672 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of a 

fractured wing-to-fuselage strut attachment 

joint bolt. We are issuing this AD to detect 

and correct fractured bolts, which could 

result in reduced structural integrity of the 

wing-to-fuselage strut attachment joint and 

subsequent loss of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Torque Check 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a 

torque check of the wing-to-fuselage strut 

attachment joint bolts, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013. 

(1) For airplanes that have accumulated 

fewer than 40,000 total flight cycles, and 

have less than 15 years in service since new, 

as of the effective date of this AD: Do the 

torque check before the accumulation of 

42,000 total flight cycles, or within 16 years 

in service since new, whichever occurs first. 

(2) For airplanes that have accumulated 

40,000 total flight cycles or more, or have 15 

years or more in service since new, as of the 

effective date of this AD: Do the torque check 

within 2,000 flight cycles or 12 months after 

the effective date of this AD, whichever 

occurs first. 

(h) Inspection and Corrective Actions 

(1) If only one bolt fails the torque check, 

before further flight, replace the bolt, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–57–47, Revision A, dated May 29, 2013; 

and before further flight do the actions 

specified in paragraphs (h)(3)(i) and (h)(3)(ii) 

of this AD. 

(2) If more than one bolt fails the torque 

check, before further flight, repair, using a 

method approved by the Manager, New York 

Aircraft Certification Office (ACO), FAA; or 

Transport Canada Civil Aviation (TCCA) (or 

its delegated agent or by the Design Approval 

Holder with the TCCA design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. 

(3) If all bolts pass the torque check, before 

further flight, do the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, 

as applicable. 

(i) Do a detailed inspection for corrosion, 

damage (including but not limited to 

scratching, cracking, pitting, and cross 

threads, etc.), and wear, of each wing-tofuselage strut attachment joint bolt and 

associated hardware, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013. If any bolt or hardware has 

corrosion, damage, or wear, before further 

flight, replace the affected part, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013. 

(ii) Do a borescope inspection for corrosion 

and damage (including but not limited to 

scratching, cracking, pitting, and cross 

threads, etc.) of the bore hole and barrel nut 

threads, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013, except as provided by 

paragraph (i) of this AD. 

(A) If any corrosion or damage is found in 

the barrel nut threads, before further flight, 

replace the barrel nut, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013, except as provided by 

paragraph (i) of this AD. 

(B) If any corrosion or damage is found in 

the bore of the hole, before further flight, 

repair, using a method approved by the 

Manager, New York ACO, FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent or by the Design Approval 

Holder with the TCCA design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. 

(i) Exception to Service Information 

Where Bombardier Service Bulletin 8–57– 

47, Revision A, dated May 29, 2013, specifies 

to contact the manufacturer for repair 

information, this AD requires repairing 

before further flight using a method approved 

by the Manager, New York ACO, FAA; or 

TCCA (or its delegated agent, or by the 

Design Approval Holder with TCCA design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 8–57–47, dated March 16, 

2012. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 73465 

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 ACO, 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 Design 

Approval Holder 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. 

(l) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–17R1, 

dated June 27, 2013, for related information, 

which can be found in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2013–1024. 

(2) For service information identified in 

this 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 view this 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. 

Issued in Renton, Washington, on 

November 29, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–29134 Filed 12–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0683; Airspace 

Docket No. 13–ANE–1] 

Proposed Amendment of Class E 

Airspace; Morrisville, VT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E Airspace at Morrisville, 

VT, as the Morrisville-Stowe NonDirectional Beacon (NDB) has been 

decommissioned, requiring airspace 

redesign at Morrisville-Stowe State 

Airport. This action would enhance the 

safety and airspace management of 

Instrument Flight Rules (IFR) operations 

at the airport. This action also would 

update the geographic coordinates of the 

airport. 

DATES: Comments must be received on 

or before January 21, 2014. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey, SE., Washington, DC 

20590–0001; Telephone: 1–800–647– 

5527; Fax: 202–493–2251. You must 

identify the Docket Number FAA–2013– 

0683; Airspace Docket No. 13–ANE–1, 

at the beginning of your comments. You 

may also submit and review received 

comments through the Internet at 

http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rulemaking by 

submitting such written data, views, or 

arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2013–0683; Airspace Docket No. 13– 

ANE–1) and be submitted in triplicate to 

the Docket Management System (see 

ADDRESSES section for address and 

phone number). You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

Persons wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2013–0683; Airspace 

Docket No. 13–ANE–1.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

All communications received before 

the specified closing date for comments 

will be considered before taking action 

on the proposed rule. The proposal 

contained in this notice may be changed 

in light of the comments received. A 

report summarizing each substantive 

public contact with FAA personnel 

concerned with this rulemaking will be 

filed in the docket. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded from and 

comments submitted through http://

www.regulations.gov. Recently 

published rulemaking documents can 

also be accessed through the FAA’s Web 

page at http://www.faa.gov/airports_

airtraffic/air_traffic/publications/

airspace_amendments/. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office (see the 

ADDRESSES section for address and 

phone number) between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except Federal Holidays. An informal 

docket may also be examined between 

8:00 a.m. and 4:30 p.m., Monday 

through Friday, except Federal Holidays 

at the office of the Eastern Service 

Center, Federal Aviation 

Administration, Room 350, 1701 

Columbia Avenue, College Park, Georgia 

30337. 

Persons interested in being placed on 

a mailing list for future NPRM’s should 

contact the FAA’s Office of Rulemaking, 

(202) 267–9677, to request a copy of 

Advisory circular No. 11–2A, Notice of 

Proposed Rulemaking distribution 

System, which describes the application 

procedure. 

The Proposal 

The FAA is considering an 

amendment to Title 14, Code of Federal 

Regulations (14 CFR) part 71 to amend 

Class E airspace extending upward from 

700 feet above the surface at MorrisvilleStowe State Airport, Morrisville, VT. 


emcdonald on DSK67QTVN1PROD with PROPOSALS