3566 Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2010–0042; Directorate Identifier 

2009–NM–010–AD. 

Comments Due Date 

(a) We must receive comments by March 7, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Saab AB, Saab 

Aerosystems airplanes, certificated in any 

category, identified in paragraphs (c)(1) and 

(c)(2) of this AD, that have been modified in 

accordance with Supplemental Type 

Certificate (STC) ST00224WI–D, 

ST00146WI–D, or SA984GL–D. 

(1) Model SAAB 340A (SAAB/SF340A) 

airplanes, serial numbers 004 through 159 

inclusive. 

(2) Model SAAB 340B airplanes, serial 

numbers 160 through 459 inclusive. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report of a crack 

found behind the external adapter plate of 

the antennae during inspection. Similar 

cracking was found on two additional 

airplanes, and extensive corrosion was found 

on one airplane. The Federal Aviation 

Administration is issuing this AD to detect 

and correct corrosion and cracking behind 

the external adapter plate of the antennae of 

certain damage-tolerant structure, which 

could result in reduced structural integrity 

and consequent rapid depressurization of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified. 

Inspection/Corrective Actions 

(g) Within 600 flight cycles after the 

effective date of this AD: Remove the external 

adapter plate of the antennae installation and 

do a general visual inspection of the fuselage 

surface for corrosion and cracking behind the 

external adapter plate of the antennae 

installation. If any corrosion or cracking is 

found, repair before further flight. If no 

corrosion or cracking is found, before further 

flight, ensure that proper corrosion 

protection has been applied before 

reinstalling the adapter plate. Do all the 

actions required by this paragraph in 

accordance with a method approved by the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Reporting Requirement 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD: Submit 

a report of the positive findings of the 

inspections required by paragraph (g) of this 

AD. Send the report to the Manager, Wichita 

ACO. The report must contain, at a 

minimum, the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

flight cycles and flight hours on the airplane 

since installation of the STC. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(3) A Federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave., SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

Special Flight Permit 

(i) 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), may be issued to operate the 

airplane to a location where the requirements 

of this AD can be accomplished, but 

concurrence by the Manager, Wichita ACO, 

FAA, is required prior to issuance of the 

special flight permit. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Wichita ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, Wichita 

ACO, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; 

telephone (316) 946–4116; fax (316) 946– 

4107. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

Issued in Renton, Washington on January 

12, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1118 Filed 1–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0026; Directorate 

Identifier 2010–NM–104–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200 and –300 

Series Airplanes Equipped With Pratt 

and Whitney 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 

Model 777–200 and –300 series 

airplanes. This proposed AD would 

require repetitive inspections for 


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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 3567 

hydraulic fluid contamination of the 

interior of the strut disconnect 

assembly; repetitive inspections for 

discrepancies of the interior of the strut 

disconnect assembly, if necessary; 

repetitive inspections of the exterior of 

the strut disconnect assembly for cracks, 

if necessary; and corrective action if 

necessary. This proposed AD also 

provides an optional terminating action 

for the inspections. This proposed AD 

results from reports of system 

disconnect boxes that have been 

contaminated with hydraulic fluid and, 

in one incident, led to subsequent 

cracking of titanium parts in the system 

disconnect assembly. We are proposing 

this AD to detect and correct hydraulic 

fluid contamination, which can cause 

cracking of titanium parts in the system 

disconnect assembly, resulting in 

compromise of the engine firewall. A 

cracked firewall can allow fire in the 

engine area to enter the strut and can 

lead to an uncontained engine strut fire 

if flammable fluid is present. Cracking 

of the disconnect box may also reduce 

the effectiveness of the fire 

extinguishing system in the engine 

compartment and could contribute to an 

uncontained engine fire. In addition, a 

cracked disconnect box can leak 

flammable fluids into the engine core, 

which can initiate an engine fire, and 

lead to one or both fire conditions 

discussed above. 

DATES: We must receive comments on 

this proposed AD by March 7, 2011. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; 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. 

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: 

Kevin Nguyen, Propulsion Branch, 

ANM–140S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6501; 

fax (425) 917–6590. 

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–2011–0026; Directorate Identifier 

2010–NM–104–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 reports of system 

disconnect boxes that have been 

contaminated with hydraulic fluid. One 

operator has found cracks in the system 

disconnect assembly bulkheads and 

lower skin panel. Subsequent analysis at 

Boeing found hydrogen enbrittlement of 

the system disconnect assembly 

bulkheads and lower skin panel. The 

system disconnect assembly is made 

from titanium and is located near the 

hot engine core of the engine where 

temperatures can exceed 270 degrees 

Fahrenheit. The presence of hydraulic 

fluid and temperature above 270 degrees 

Fahrenheit can result in hydrogen 

embrittlement of the titanium system 

disconnect assembly. Hydrogen 

embrittlement combined with a high 

sonic vibration environment can result 

in cracking of the system disconnect 

assembly. The system disconnect 

assembly is a box where hydraulic, fuel, 

and electrical connections are made 

between the engine and the strut. This 

box acts as a firewall between the 

engine compartment and the strut. The 

engine compartment has a fire 

extinguishing system while the strut 

does not. The strut is considered a 

flammable leakage zone where 

flammable fluids may be present. These 

fluids are subsequently drained from the 

strut and system disconnect box. A 

cracked firewall can allow fire in the 

engine area to enter the strut and can 

lead to an uncontained engine strut fire 

if flammable fluid is present. Cracking 

of the disconnect box may also reduce 

the effectiveness of the fire 

extinguishing system in the engine 

compartment and could contribute to an 

uncontained engine fire. In addition, a 

cracked disconnect box can leak 

flammable fluids into the engine core, 

which can initiate an engine fire, and 

lead to one or both fire conditions 

discussed above. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 777–54A0024, Revision 

1, dated November 4, 2010. This service 

bulletin describes procedures for doing 

repetitive general visual inspections for 

hydraulic fluid contamination of the 

interior of the strut disconnect 

assembly; repetitive detailed 

inspections for discrepancies (e.g., 

hydraulic fluid coking, heat 

discoloration, cracks, and etching or 

pitting) of the interior of the strut 

disconnect assembly, if certain 

conditions are found; repetitive detailed 

inspections of the exterior of the strut 

disconnect assembly for cracks; and 

corrective action, if certain conditions 

are found. The corrective action is 

replacing the titanium system 

disconnect assembly with an Inconel 

system disconnect assembly. If 

accomplished, the replacement will 

eliminate the potential for hydrogen 

embrittlement and subsequent cracking, 

and would eliminate the need for the 

inspections of the titanium strut 

disconnect assembly. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
3568 Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 

develop in other products of these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 53 airplanes of U.S. 

registry. We also estimate that it would 

take about 48 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$122,617 per product. Based on these 

figures, we estimate the cost of this 

proposed AD to the U.S. operators to be 

$6,714,941, or $122,697 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 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), 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2011–0026; Directorate Identifier 2010– 

NM–104–AD. 

Comments Due Date 

(a) We must receive comments by March 7, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 777–200 and –300 series 

airplanes, certificated in any category; 

equipped with Pratt and Whitney engines; as 

identified in Boeing Alert Service Bulletin 

777–54A0024, Revision 1, dated November 4, 

2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from reports of system 

disconnect boxes that have been 

contaminated with hydraulic fluid, in which 

one case a crack was found. The Federal 

Aviation Administration is issuing this AD to 

detect and correct hydraulic fluid 

contamination, which can cause cracking of 

titanium parts in the system disconnect 

assembly, resulting in compromise of the 

engine firewall. A cracked firewall can allow 

fire in the engine area to enter the strut and 

can lead to an uncontained engine strut fire 

if flammable fluid is present. Cracking of the 

disconnect box may also reduce the 

effectiveness of the fire extinguishing system 

in the engine compartment and could 

contribute to an uncontained engine fire. In 

addition, a cracked disconnect box can leak 

flammable fluids into the engine core, which 

can initiate an engine fire and lead to one or 

both fire conditions discussed above. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspections and Corrective Actions 

(g) Within 12 months after the effective 

date of this AD: Do a general visual 

inspection for hydraulic fluid contamination 

of the interior of the strut disconnect 

assembly, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010. 

(1) For airplanes on which no hydraulic 

fluid contamination is found (Condition 1): 

Repeat the general visual inspection required 

by paragraph (g) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(2) For airplanes on which hydraulic fluid 

contamination is found (Condition 2): Before 

further flight, do a detailed inspection for 

discrepancies (e.g., hydraulic fluid coking, 

heat discoloration, cracks, and etching or 

pitting) of the interior of the strut disconnect 

assembly, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010. 

(i) For airplanes on which no discrepancy 

is found during the inspection required by 

paragraph (g)(2) of this AD (Condition 2A): 

Repeat the detailed inspection required by 

paragraph (g)(2) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(ii) For airplanes on which hydraulic fluid 

coking or heat discoloration is found but no 

cracking, etching, or pitting is found during 

the inspection required by paragraph (g)(2) of 

this AD (Condition 2B): Do the actions 

required by paragraph (g)(2)(ii)(A) and 

(g)(2)(ii)(B) of this AD. 

(A) Within 300 flight cycles after doing the 

inspection required by paragraph (g)(2) of 

this AD: Do a detailed inspection of the 

exterior of the strut disconnect assembly for 

cracks, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; and repeat the 

detailed inspection thereafter at intervals not 

to exceed 300 flight cycles. 

(B) Within 6,000 flight cycles or 750 days 

after hydraulic fluid coking and/or heat 

discoloration was found during the 

inspection required by paragraph (g)(2) of 

this AD, whichever occurs first: Replace the 

titanium system disconnect assembly with an 

Inconel system, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–54A0024, 

Revision 1, dated November 4, 2010. 

(h) For airplanes on which any crack, 

etching, or pitting is found during any 

inspection required by paragraph (g)(2) or 

(g)(2)(ii)(A) of this AD (Condition 3): Before 

further flight, replace the titanium system 

disconnect assembly with an Inconel system, 

in accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010. 

Optional Terminating Action 

(i) Replacing the titanium system 

disconnect assembly with an Inconel system 


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Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules 3569 

disconnect assembly in accordance with Part 

4 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–54A0024, 

Revision 1, dated November 4, 2010, 

terminates the actions required by this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin 777–54A0024, dated 

April 1, 2010, are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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. Send information to ATTN: Kevin 

Nguyen, Propulsion Branch, ANM–140S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6501; fax (425) 917–6590. Information 

may be e-mailed to: 9–ANM–Seattle-ACO– 

AMOC–Requests@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. 

Issued in Renton, Washington, on January 

12, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1119 Filed 1–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–1209; Airspace 

Docket No. 10–ANM–10] 

Proposed Amendment of Class E 

Airspace; West Yellowstone, MT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify Class E airspace at Yellowstone 

Airport, West Yellowstone, MT, to 

accommodate aircraft using the 

Instrument Landing System (ILS) 

Localizer (LOC) standard instrument 

approach procedures at Yellowstone 

Airport, West Yellowstone, MT. The 

FAA is proposing this action to enhance 

the safety and management of aircraft 

operations at Yellowstone Airport. 

DATES: Comments must be received on 

or before March 7, 2011. 

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–2010–1209; Airspace 

Docket No. 10–ANM–10, 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 

2010–1209 and Airspace Docket No. 10– 

ANM–10) 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–2010–1209 and 

Airspace Docket No. 10–ANM–10’’. 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_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 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 modifying Class E 

airspace extending upward from 700 

feet above the surface at Yellowstone 

Airport, West Yellowstone, MT, to 

accommodate new ILS LOC standard 

instrument approach procedures at 

Yellowstone Airport, West Yellowstone, 

MT. This action would enhance the 

safety and management of aircraft 

operations at Yellowstone Airport. 

Class E airspace designations are 

published in paragraph 6005, of FAA 

Order 7400.9U, dated August 18, 2010, 

and effective September 15, 2010, which 

is incorporated by reference in 14 CFR 

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 


emcdonald on DSK2BSOYB1PROD with PROPOSALS