54856 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation and Replacement 

Within 24 months after the effective date 

of this AD, install aft and forward drain 

tubes, relocate wire bundle routing, install a 

new drip shield and drip shield deflectors, 

and replace insulation blankets, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–25A3580, Revision 1, dated July 14, 

2011 (for Model 747–400F series airplanes); 

or Boeing Alert Service Bulletin 747– 

25A3581, Revision 1, dated June 30, 2011 (for 

Model 747–400 series airplanes). 

(h) Concurrent Actions 

For Group 1 airplanes as identified in 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 1, dated June 30, 2011: Prior to or 

concurrently with the actions required by 

paragraph (g) of this AD, seal the drain slot, 

install spuds, and install left- and right-side 

drain tubes, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–25A3526, Revision 1, 

dated February 20, 2009 (for Model 747–400 

series airplanes), except as specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Steps 1 through 5 of Figure 2 of Boeing 

Alert Service Bulletin 747–25A3526, 

Revision 1, dated February 20, 2009, are not 

required if work is being accomplished 

concurrently with the actions specified in 

Boeing Alert Service Bulletin 747–25A3581, 

Revision 1, dated June 30, 2011 (for Model 

747–400 series airplanes). 

(2) The portion of ‘‘More Data’’ in step 8 

of Figure 3 of Boeing Alert Service Bulletin 

747–25A3526, Revision 1, dated February 20, 

2009, which says ‘‘Attach drain tube and 

strap above bead on the spud,’’ is not 

required. 

(i) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-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. 

(j) Related Information 

(1) For more information about this AD, 

contact Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Control 

Systems, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; phone: 

425–917–6457; fax: 425–917–6590; email: 

francis.smith@faa.gov. 

(2) For service information identified in 

this 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; 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 98057– 

3356. For information on the availability of 

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

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21933 Filed 9–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0931; Directorate 

Identifier 2011–NM–128–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 The 

Boeing Company Model 727, 727C, 727– 

100, 727–100C, 727–200, and 727–200F 

series airplanes. This proposed AD was 

prompted by a structural re-evaluation 

by the manufacturer, which identified 

elements within the wing trailing edge 

flap area that qualify as structural 

significant items (SSI). This proposed 

AD would require revising the 

maintenance inspection program to 

include inspections that will give no 

less than the required damage tolerance 

rating for certain SSIs, and repairing 

cracked structure. We are proposing this 

AD to detect and correct fatigue 

cracking of the wing trailing edge 

structure, which could result in 

compromised structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 22, 2012. 

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 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; 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

Berhane.Alazar@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– 

2012–0931; Directorate Identifier 2011– 

NM–128–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:// 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54857 

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 

In the early 1980s, as part of its 

continuing work to maintain the 

structural integrity of older transport 

category airplanes, the FAA concluded 

that the incidence of fatigue cracking 

may increase as these airplanes reach or 

exceed their design service objective 

(DSO). In light of this, and as a result 

of increased utilization, and longer 

operational lives, we determined that a 

supplemental structural inspection 

program (SSIP) was necessary to 

maintain the continued structural 

integrity for all airplanes in the 

transport fleet. 

Since the establishment of the SSI 

Supplemental Structural Inspection 

Document (SSID) D6–48040–1, we have 

received information from the 

manufacturer, which identified 

elements within the wing trailing edge 

flap area, which qualified as SSI. An SSI 

is defined as a structural part or 

component that contributes significantly 

to carry flight, ground, pressure, or 

control loads, and whose failure could 

affect the structural integrity necessary 

for the safety of the airplane, and whose 

damage tolerance or safe-life 

characteristics it is necessary, therefore, 

to establish or confirm. Uncorrected 

fatigue cracks in these structural 

elements could result in compromised 

structural integrity of the airplane. 

Issuance of FAA Advisory Circular 

(AC) 

On March 7, 2008, we issued AC 91– 

56B, ‘‘Continuing Structural Integrity 

Program for Airplanes,’’ (http:// 

rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgAdvisoryCircular.nsf/list/AC%2091- 

56B/$FILE/AC%2091-56B.pdf). That AC 

provides guidance material to 

manufacturers and operators for use in 

developing a continuing structural 

integrity program to ensure safe 

operation of older airplanes throughout 

their operational lives. This guidance 

material applies to transport airplanes 

that were certified under the fail-safe 

requirements of part 4b (‘‘Airplane 

Airworthiness, Transport Categories’’) of 

the Civil Air Regulations or damage 

tolerance structural requirements of part 

25 (‘‘Airworthiness Standards: 

Transport Category Airplanes’’) of the 

Federal Aviation Regulations (FARs) (14 

CFR part 25), and that have a maximum 

gross weight greater than 75,000 

pounds. The procedures set forth in that 

AC are applicable to transport category 

airplanes operated under subpart D 

(‘‘Special Flight Operations’’) of part 91 

(‘‘General Operating and Flight Rules’’) 

of the FARs (14 CFR part 91); part 121 

(‘‘Operating Requirements: Domestic, 

Flag, and Supplemental Operations’’) of 

the FARs (14 CFR part 121); part 125 

(‘‘Certification and Operations: 

Airplanes Having a Seating Capacity of 

20 or More Passengers or a Maximum 

Payload of 6,000 Pounds or More and 

Rules Governing Persons Onboard Such 

Aircraft’’) of the FARs (14 CFR part 

125); and part 135 (‘‘Operating 

Requirements: Commuter and OnDemand Operations and Rules 

Governing Persons On Board Such 

Aircraft’’) of the FARs (14 CFR part 

135). The objective of the SSIP was to 

establish inspection programs to ensure 

timely detection of fatigue cracking. 

Development of the SSIP 

In order to evaluate the effect of 

increased fatigue cracking with respect 

to maintaining fail-safe design and 

damage tolerance of the structure of The 

Boeing Company Model 727, 727C, 727– 

100, 727–100C, 727–200, and 727–200F 

series airplanes, Boeing conducted a 

structural reassessment of those 

airplanes, using damage tolerance 

evaluation techniques. Boeing 

accomplished this reassessment using 

the criteria contained in FAA AC 91– 

56B, dated March 7, 2008, (http:// 

rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgAdvisoryCircular.nsf/list/AC%2091- 

56B/$FILE/AC%2091-56B.pdf), as well 

as Amendment 25–45, effective 

December 1, 1978, of section 25.571 

(‘‘Damage-tolerance and fatigue 

evaluation of structure’’) of the FARs (14 

CFR 25.571). During the reassessment, 

members of the airline industry 

participated with Boeing in working 

group sessions and developed the SSIP 

for Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes. Engineers and maintenance 

specialists from the FAA also supported 

these sessions. Subsequently, based on 

the working group’s recommendations, 

Boeing developed the Supplemental 

Structural Inspection Document (SSID) 

D6–48040–1. 

Other Related Rulemaking 

On May 12, 1998, the FAA issued AD 

98–11–03, Amendment 39–10530 (63 

FR 27455, May 19, 1999), which is 

applicable to all The Boeing Company 

Model 727 series airplanes. On 

December 30, 1998, the FAA issued AD 

98–11–03 R1, Amendment 39–10983 (64 

FR 989, January 7, 1999), to revise the 

maintenance inspection program to 

include inspections that will give no 

less than the required damage tolerance 

rating for each SSI, and repair of 

cracked structure. AD 98–11–03 R1 

requires that the maintenance 

inspection program be revised to 

include inspections that will give no 

less than the required damage tolerance 

rating for each SSI, and repair of 

cracked structure. That action was 

prompted by a structural re-evaluation 

by the manufacturer that identified 

additional structural elements for 

which, if damage were to occur, 

supplemental inspections may be 

required for timely crack detection. The 

actions required by that AD are 

intended to ensure the continued 

structural integrity of The Boeing 

Company Model 727 fleet. 

Relevant Service Information 

We reviewed Boeing Document D6– 

48040–2, Supplemental Structural 

Inspection Document For Model 727 

Airplanes, Appendix A, dated December 

2010, which identifies SSIs within the 

wing trailing edge flap area that need 

inspection to ensure timely detection of 

fatigue damage. The inspection 

requirements identified in Boeing 

Document D6–48040–2, Appendix A, 

Supplemental Structural Inspection 

Document For Model 727 Airplanes, 

dated December 2010, are intended to 

be accomplished in conjunction with, 

not as a replacement for, the existing 

approved structural inspection program. 

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. 

Proposed AD Requirements 

This proposed AD would require 

revising the maintenance inspection 

program to include inspections that will 

give no less than the required damage 

tolerance rating for each SSI, repetitive 

inspections to detect cracks in SSIs, and 

repair of any cracked structure. Before 

any airplane that is subject to this 

proposed AD can be added to an air 

carrier’s operations specifications, a 

program for doing the inspections 

required by this proposed AD must be 

established. 

Costs of Compliance 

We estimate that this proposed AD 

affects 206 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 


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54858 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revise maintenance program ......................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $17,510 

Compliance with this proposed AD 

would be a method of compliance with 

the FAA aging airplane safety final rule 

(AASFR) (70 FR 5518, February 2, 2005) 

for certain baseline structure of Model 

727, 727C, 727–100, 727–100C, 727– 

200, and 727–200F series airplanes. The 

AASFR final rule requires certain 

operators to incorporate damage 

tolerance inspections into their 

maintenance inspection programs. 

These requirements are described in 

paragraph (c)(1) of section 121.1109 of 

the FARs (14 CFR 121.1109 (c)(1)) and 

paragraph (b)(1) of section 129.109 of 

the FARs (14 CFR 129.109(b)(1)). 

Accomplishment of the actions required 

by this proposed AD will meet the 

requirements of these CFR sections for 

certain baseline structure. The costs for 

accomplishing the inspection portion of 

this proposed AD were accounted for in 

the regulatory evaluation of the AASFR 

final rule. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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, 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): 

The Boeing Company: Docket No. FAA– 

2012–0931; Directorate Identifier 2011– 

NM–128–AD. 

(a) Comments Due Date 

We must receive comments by October 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections, methods, and 

compliance times.) Compliance with these 

actions is required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the areas 

addressed by these inspections, the operator 

may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (j) of this AD. The 

request should include a description of 

changes to the required actions that will 

ensure the continued operational safety of 

the airplane. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a structural reevaluation by the manufacturer, which 

identified elements within the wing trailing 

edge flap area that qualify as structural 

significant items (SSI). We are issuing this 

AD to detect and correct fatigue cracking of 

the wing trailing edge structure, which could 

result in compromised structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revise Maintenance Program 

(1) Before the accumulation of 55,000 total 

flight cycles, or within 12 months after the 

effective date of this AD, whichever occurs 

later: Revise the maintenance program to 

incorporate inspections that provide no less 

than the required damage tolerance rating 

(DTR) for each SSI listed in Boeing Document 

D6–48040–2, Supplemental Structural 

Inspection Document For Model 727 

Airplanes, Appendix A, dated December 

2010. The required DTR value for each SSI 

is identified in Boeing Document D6–48040– 

2, Supplemental Structural Inspection 

Document For Model 727 Airplanes, 

Appendix A, dated December 2010. The 

revision to the maintenance inspection 

program must include and must be 

implemented in accordance with the 

procedures in Section 3.0 of Boeing 

Document D6–48040–2, Supplemental 

Structural Inspection Document For Model 

727 Airplanes, Appendix A, dated December 

2010; and in accordance with the procedures 

in Section 5.0, ‘‘Damage Tolerance Rating 

(DTR) System Application,’’ and Section 6.0, 

‘‘SSI Discrepancy Reporting,’’ of Boeing 

Document D6–48040–1, Supplemental 

Structural Inspection Document (SSID), 

Volume 1, Revision H, dated June 1994. 

(2) The initial compliance time for the 

inspections is before the accumulation of 

55,000 total flight cycles, or within 3,000 

flight cycles after 12 months from the 


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Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54859 

effective date of this AD, whichever occurs 

later. 

(h) Repair 

If any cracked structure is found during 

any inspection specified in Boeing Document 

D6–48040–2, Supplemental Structural 

Inspection Document For Model 727 

Airplanes, Appendix A, dated December 

2010, before further flight, repair the cracked 

structure using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used other than those specified in Boeing 

Document D6–48040–2, Supplemental 

Structural Inspection Document For Model 

727 Airplanes, Appendix A, dated December 

2010, unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-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. 

(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, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: Berhane.Alazar@faa.gov. 

(2) For service information identified in 

this 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; 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 August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21944 Filed 9–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0750; Airspace 

Docket No. 11–AWP–4] 

RIN 2120–AA66 

Proposed Establishment of VOR 

Federal Airway V–629; Las Vegas, NV 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish a new VHF Omnidirectional 

Range (VOR) Federal airway near Las 

Vegas, NV, to supplement the existing 

route structure for aircraft navigating in 

an area of marginal radar coverage. This 

would enhance the efficiency of the 

National Airspace System (NAS). 

DATES: Comments must be received on 

or before October 22, 2012. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, 1200 New Jersey Avenue SE., West 

Building Ground Floor, Room W12–140, 

Washington, DC 20590–0001; telephone: 

(202) 366–9826. You must identify FAA 

Docket No. FAA–2012–0750 and 

Airspace Docket No. 11–AWP–4 at the 

beginning of your comments. You may 

also submit comments through the 

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

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace, Regulations and ATC 

Procedures Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

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– 

2012–0750 and Airspace Docket No. 11– 

AWP–4) and be submitted in triplicate 

to the Docket Management Facility (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–2012–0750 and 

Airspace Docket No. 11–AWP–4.’’ 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. 

You may review the public docket 

containing the proposal, any comments 

received and any final disposition in 

person in the Dockets Office (see 

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 during 

normal business hours at the office of 

the Western Service Center, Operations 

Support Group, Federal Aviation 

Administration, 1601 Lind Ave. 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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS