79560 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / 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 AD: 

Airbus: Docket No. FAA–2012–1324; 

Directorate Identifier 2011–NM–104–AD. 

(a) Comments Due Date 

We must receive comments by February 6, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes; and Model A310–203, 

–204, –221, –222, –304, –322, –324, and –325 

airplanes; certificated in any category; all 

certificated models, all manufacturer serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52: Doors. 

(e) Reason 

This AD was prompted by a report of a 

crack in the forward cargo door selector valve 

pipe located in the avionics bay opposite to 

line replaceable unit racking. We are issuing 

this AD to prevent cracking in the forward 

cargo door selector valve pipe which could 

impact the 90 VU avionics line replaceable 

unit, and could result in multiple computer 

failures, affecting flight safety. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Replacement 

Except as provided by paragraph (h) of this 

AD: Within 30 months or 6,000 flight hours 

after the effective date of this AD, whichever 

occurs first, replace the aluminum high 

pressure pipe having part number (P/N) 

A5231006100300 with a new pipe made of 

corrosion resistant stainless steel having P/N 

A5231007000600, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–52–6065, 

Revision 01, dated July 5, 2010 (for Model 

A300 B4–600 series airplanes); or A310–52– 

2067, Revision 01, dated July 5, 2010 (for 

Model A310 series airplanes). 

(h) Exception 

Any airplane that has incorporated Airbus 

Modification 12464 in production has the 

new P/N A5231007000600 installed and is 

therefore compliant with the requirements of 

paragraph (g) of this AD. If the high pressure 

pipe has been replaced with P/N 

A5231006100300 in service after delivery of 

the airplane, replace the high pressure pipe 

in accordance with paragraph (g) of this AD 

within the times specified in paragraph (g) of 

this AD. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install an aluminum high 

pressure pipe having P/N A5231006100300, 

on any airplane. 

(j) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Replacements done before the effective 

date of this AD in accordance with Airbus 

Mandatory Service Bulletins A300–52–6065, 

dated July 9, 2002 (for Model A300–600 

series airplanes); and A310–52–2067, dated 

July 9, 2002 (for Model A310 series 

airplanes); are acceptable for compliance 

with the requirements of paragraph (g) of this 

AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0085, dated May 12, 2011 (corrected 

May 31, 2011); Airbus Mandatory Service 

Bulletin A300–52–6065, Revision 01, dated 

July 5, 2010; and Airbus Mandatory Service 

Bulletin A310–52–2067, Revision 01, dated 

July 5, 2010; for related information. 

Issued in Renton, Washington, on 

December 14, 2011. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–32844 Filed 12–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1323; Directorate 

Identifier 2010–NM–212–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Model A330–200 and –300 series 

airplanes; Model A330–223F and –243F 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. This 

proposed AD was prompted by a report 

that during the evaluation of specific 

engine failure cases at take-off on Airbus 

flight simulators. It has been shown that 

with flight control primary computer 

(FCPC)1 inoperative, in worst case 

scenario, when FCPC2 and FCPC3 resets 

occur during rotation at take off, a 

transient loss of elevator control 

associated with a temporary incorrect 

flight control law reconfiguration could 

occur. This proposed AD would require 

revising the Limitations section of the 

applicable airplane flight manual. We 

are proposing this AD to prevent 

movement of the elevators to zero 

position, which could result in inducing 

a pitch down movement instead of a 

pitch up movement needed for lift off, 

resulting in loss of controllability of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 6, 2012. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


jlentini on DSK4TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules 79561 

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 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

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–2011–1323; Directorate Identifier 

2010–NM–212–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0109, 

dated June 28, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

On A330/A340 aeroplanes, the Flight 

Control Primary Computer 2 (FCPC2) and 

FCPC3 are supplied with power from the 2PP 

bus bar. Electrical transients on the 2PP bus 

bar occur, in particular during engine n.2 

failure on A330 aeroplanes or engine n.3 

failure on A340 aeroplanes. Such electrical 

transients lead to a FCPC2 reset. FCPC3 reset 

does not occur thanks to the introduction of 

second electrical power supply to FCPC3 

from 1PP bus bar associated to the Electrical 

Contactor Management Unit (ECMU) 

standard 5. 

During the evaluation of specific engine 

failure cases at take-off on Airbus flight 

simulators, it has been evidenced that with 

FCPC1 inoperative, in the worst case, when 

FCPC2 and FCPC3 resets occur during 

rotation at take off, a transient loss of elevator 

control associated with a temporary incorrect 

flight control law reconfiguration could 

occur. This condition leads to a movement of 

the elevators to the zero position, which 

induces a pitch down movement instead of 

a pitch up movement needed to lift off. In 

addition, it leads to a limitation of the pilot 

control on pitch axis and limits the pilot 

capacity to counter the pitch down 

movement during this flight phase, which 

constitutes an unsafe condition. 

To prevent such condition, [EASA] 

Emergency Airworthiness Directive (EAD) 

2008–0010–E was issued to prohibit 

aeroplanes dispatch with FCPC1 inoperative 

(from GO to NO–GO) for certain aeroplane 

configurations. For other configurations, 

dispatch is allowed when the integrity of the 

FCPC3 second electrical power supply is 

ensured. 

EASA AD 2008–0010R1 was issued to: 

—For A340–500/–600, alleviate the dispatch 

restriction on aeroplanes fitted with new 

FCPC Standard W11 (part number (P/N) 

LA2K2B100GA0000) 

and 

—For A330 and A340–200/–300, to take into 

account the possibility to embody in 

service a new FCPC3 second electrical 

power supply equivalent to the production 

one. 

This [EASA] AD, which supersedes EASA 

AD 2008–0010R1 retaining its requirements, 

is issued to extend the applicability to the 

newly certified models A330–223F and 

A330–243F. 

The FAA did not issue corresponding 

ADs for EASA Airworthiness Directive 

2008–0010–E and EASA Airworthiness 

Directive 2008–0010R1 since it was 

determined at that time that the FAA 

Master Minimum Equipment List 

(MMEL) was an acceptable method for 

controlling exposure of the U.S. fleet to 

the safety issue addressed in the EASA 

ADs. Since that decision was made, the 

FAA determined that an AD is needed 

to control dispatch restrictions. In 

addition, EASA Airworthiness Directive 

2010–0109 added two new Airbus 

models in the applicability and we are 

proceeding with this FAA AD in order 

to address the identified unsafe 

condition for the U.S. fleet. You may 

obtain further information by examining 

the MCAI in the AD docket. 

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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 55 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$4,675, or $85 per product. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 AD: 

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); and 

3. 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 


jlentini on DSK4TPTVN1PROD with PROPOSALS
79562 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules 

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: 

Airbus: Docket No. FAA–2011–1323; 

Directorate Identifier 2010–NM–212–AD. 

(a) Comments Due Date 

We must receive comments by February 6, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, –313, –541, and 

–642 airplanes; certificated in any category; 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by a report that 

during the evaluation of specific engine 

failure cases at take-off on Airbus flight 

simulators. It has been shown that with flight 

control primary computer (FCPC)1 

inoperative, in worst case scenario, when 

FCPC2 and FCPC3 resets occur during 

rotation at take off, a transient loss of elevator 

control associated with a temporary incorrect 

flight control law reconfiguration could 

occur. We are issuing this AD to prevent 

movement of the elevators to zero position, 

which could result in inducing a pitch down 

movement instead of a pitch up movement 

needed for lift off, resulting in loss of 

controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Airplane Flight Manual (AFM) Revision 

for Certain Airplanes 

For airplanes identified in paragraph (c) of 

this AD, except for airplanes identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Within 30 days after the effective date of this 

AD, revise the Limitations section of the 

applicable AFM to include the following 

statement. This may be done by inserting a 

copy of this AD into the AFM. 

‘‘Dispatch with the FCPC ‘‘PRIM 1’’ 

inoperative is prohibited.’’ 

(1) Model A330–223F and –243F airplanes. 

(2) Model A330–200 and –300 series 

airplanes, and Model A340–200 and –300 

series airplanes, on which Airbus 

modification 44385 has been embodied either 

in production or in service by Airbus Service 

Bulletin A330–27–3159 or Airbus Service 

Bulletin A340–27–4158; and on which 

Airbus modification 44431 has been 

embodied either in production or in service 

by Airbus Service Bulletin A330–24–3011 or 

Airbus Service Bulletin A340–24–4019. 

(3) Model A340–500 and –600 series 

airplanes on which Airbus modification 

57698 has been embodied either in 

production or in service by Airbus Service 

Bulletin A340–27–5046. 

Note 1: When a statement identical to that 

in paragraph (g) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

Note 2: This dispatch restriction applies 

notably to Model A330–200 and –300 series 

airplanes, and Model A340–200 and –300 

series airplanes, which have embodied 

Airbus Service Bulletin A330–27–3040 or 

Airbus Service Bulletin A340–27–4046 in 

service. 

(h) AFM Revision for Certain Other 

Airplanes 

For Model A330–200 and –300 series 

airplanes, and Model A340–200 and –300 

series airplanes, on which Airbus 

modification 44385 has been embodied either 

in production or in service by Airbus Service 

Bulletin A330–27–3159 or Airbus Service 

Bulletin A340–27–4158; and Airbus 

modification 44431 has been embodied either 

in production or in service by Airbus Service 

Bulletin A330–24–3011 or Airbus Service 

Bulletin A340–24–4019: Within 30 days after 

the effective date of this AD, revise the 

Limitations section of the applicable AFM to 

include the following statement. This may be 

done by inserting a copy of this AD into the 

AFM. 

‘‘Dispatch with the FCPC ‘‘PRIM 1’’ 

inoperative is allowed provided that the 

operational test of the FCPC3 second 

electrical power supply is successfully 

performed, in accordance with the 

instructions of Airbus AOT A330–27A3158, 

or AOT A340–27A4157, as applicable, before 

the first flight of the MMEL interval. 

If the test is not successful, repair in 

accordance with the instructions of Airbus 

AOT A330–27A3158 or AOT A340–27A4157, 

as applicable, before dispatch with FCPC 

‘‘PRIM 1’’ inoperative.’’ 

Note 3: Model A330–223F and –243F 

airplanes are not affected by paragraph (h) of 

this AD. 

Note 4: When a statement identical to that 

in paragraph (h) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

(i) AFM Revision for Model A330–223F and 

A330–243F Airplanes 

For Model A330–223F and A330–243F 

airplanes: Within 30 days after the effective 

date of this AD, revise the Limitations section 

of the AFM to include the following 

statement. This may be done by inserting a 

copy of this AD into the AFM. 

‘‘Dispatch with the FCPC ‘‘PRIM 1’’ 

inoperative is allowed provided that the 

operational test of the FCPC3 second 

electrical power supply is successfully 

performed in accordance with the 

instructions of Airbus AOT A330–27A3158, 

before the first flight of the MMEL interval. 

If the test is not successful, repair in 

accordance with the instructions of Airbus 

AOT A330–27A3158, before dispatch with 

FCPC ‘‘PRIM 1’’ inoperative.’’ 

Note 5: When a statement identical to that 

in paragraph (i) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0109, 

dated June 28, 2010, for related information. 


jlentini on DSK4TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules 79563 

Issued in Renton, Washington, on 

December 14, 2011. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–32845 Filed 12–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–1192; Airspace 

Docket No. 11–ANM–22] 

Proposed Amendment of Class E 

Airspace; Sheridan, WY 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Sheridan 

County Airport, Sheridan, WY. 

Decommissioning of the Sheridan 

Tactical Air Navigation System 

(TACAN) has made this action 

necessary for the safety and 

management of Instrument Flight Rules 

(IFR) operations at the airport. 

DATES: Comments must be received on 

or before February 6, 2012. 

ADDRESSES: Send comments on this 

proposal 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; 

telephone (202) 366–9826. You must 

identify FAA Docket No. FAA–2011– 

1192; Airspace Docket No. 11–ANM–22, 

at the beginning of your comments. You 

may also submit comments through the 

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

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed 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 

2011–1192 and Airspace Docket No. 11– 

ANM–22) 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. 

Commenters 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 FAA 

Docket No. FAA–2011–1192 and 

Airspace Docket No. 11–ANM–22’’. The 

postcard will be date/time stamped and 

returned to the commenter. 

All communications received on or 

before the specified closing date for 

comments will be considered before 

taking action on the proposed rule. The 

proposal contained in this action may 

be changed in light of comments 

received. All comments submitted will 

be available for examination in the 

public docket both before and after the 

closing date for comments. 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 through the 

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

Recently published rulemaking 

documents can also be accessed through 

the FAA’s Web page at http:// 

www.faa.gov/airports_air_traffic/ 

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 the address and 

phone number) between 9 a.m. and 

5 p.m., Monday through Friday, except 

federal holidays. An informal docket 

may also be examined during normal 

business hours at the Northwest 

Mountain Regional Office of the Federal 

Aviation Administration, Air Traffic 

Organization, Western Service Center, 

Operations Support Group, 1601 Lind 

Avenue SW., Renton, WA 98057. 

Persons interested in being placed on 

a mailing list for future NPRMs should 

contact the FAA’s Office of Rulemaking, 

(202) 267–9677, for a copy of Advisory 

Circular No. 11–2A, Notice of Proposed 

Rulemaking Distribution System, which 

describes the application procedure. 

The Proposal 

The FAA is proposing an amendment 

to Title 14 Code of Federal Regulations 

(14 CFR) Part 71 by amending Class E 

surface airspace at Sheridan County 

Airport, Sheridan, WY. Airspace 

reconfiguration is necessary due to the 

decommissioning of the Sheridan 

TACAN. Controlled airspace is 

necessary for the safety and 

management of IFR operations at the 

airport. 

Class E airspace designations are 

published in paragraph 6002, of FAA 

Order 7400.9V, dated August 9, 2011, 

and effective September 15, 2011, which 

is incorporated by reference in 14 CFR 

Part 71.1. The Class E airspace 

designation listed in this document will 

be published subsequently in this 

Order. 

The FAA has determined this 

proposed regulation only involves an 

established body of technical 

regulations for which frequent and 

routine amendments are necessary to 

keep them operationally current. 

Therefore, this proposed regulation; (1) 

Is not a ‘‘significant regulatory action’’ 

under Executive Order 12866; (2) is not 

a ‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 

FR 11034; February 26, 1979); and (3) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified this proposed rule, when 

promulgated, would not have a 

significant economic impact on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the U.S. Code. Subtitle 1, 

Section 106, describes the authority for 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the agency’s 

authority. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of the airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it would 

amend this proposal for controlled 

airspace at Sheridan County Airport, 

Sheridan, WY. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (air). 


jlentini on DSK4TPTVN1PROD with PROPOSALS