27116 Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Proposed Rules 

(e) Reason 

This AD was prompted by a report of 

chafed wires between electrical harnesses. 

We are issuing this AD to detect and correct 

damaged wiring and incorrect installation of 

the wiring harness and adjacent air ducts, 

which could lead to wire harness chafing and 

arcing, possibly resulting in an on-board fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within 500 flight hours after the effective 

date of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, Revision 

01, dated January 16, 2014; or Avions de 

Transport Re ́gional Service Bulletin ATR72– 

92–1032, Revision 01, dated January 16, 

2014; as applicable. 

(1) Do a general visual inspection for 

damage of the electrical wires of bundle 2M– 

2S–6M. 

(2) Do a general visual inspection for 

correct routing of electrical bundle 2M–2S– 

6M, and correct routing of the air duct. 

(h) Corrective Actions 

(1) If, during the inspection required by 

paragraph (g)(1) of this AD, any damage is 

found on the electrical wires: Before further 

flight, repair the wires, in accordance with 

the Accomplishment Instructions of Avions 

de Transport Re ́gional Service Bulletin 

ATR42–92–0024, Revision 01, dated January 

16, 2014; or Avions de Transport Re ́gional 

Service Bulletin ATR72–92–1032, Revision 

01, dated January 16, 2014; as applicable. 

(2) If, during the inspection required by 

paragraph (g)(2) of this AD, electrical bundle 

2M–2S–6M and/or an air duct is found to be 

incorrectly routed: Within 500 flight hours 

after the effective date of this AD, do a 

general visual inspection for correct 

positioning of the bracket, in accordance 

with the Accomplishment Instructions of 

Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, Revision 01, dated 

January 16, 2014; or Avions de Transport 

Re ́gional Service Bulletin ATR72–92–1032, 

Revision 01, dated January 16, 2014; as 

applicable. 

(i) If, during the inspection required by 

paragraph (h)(2) of this AD, the bracket is 

found to be correctly positioned: Within 500 

flight hours after the effective date of this AD, 

do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Re ́gional 

Service Bulletin ATR42–92–0024, Revision 

01, dated January 16, 2014; or Avions de 

Transport Re ́gional Service Bulletin ATR72– 

92–1032, Revision 01, dated January 16, 

2014; as applicable. 

(ii) If, during the inspection required by 

paragraph (h)(2) of this AD, the bracket is 

found to be missing or incorrectly positioned: 

Within 500 flight hours after the inspection 

required by paragraph (h)(2) of this AD, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

ATR–GIE Avions de Transport Re ́gional’s 

EASA Design Organization Approval (DOA). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by this AD, if those actions were 

performed before the effective date of this AD 

using Avions de Transport Re ́gional Service 

Bulletin ATR42–92–0024, dated June 6, 2013; 

or Avions de Transport Re ́gional Service 

Bulletin ATR72–92–1032, dated June 6, 2013; 

as applicable; which are not incorporated by 

reference in this AD. 

(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, Transport Airplane 

Directorate, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1137; 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0052R1, dated 

April 7, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–1280. 

(2) For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. You may 

view this 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 May 1, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11350 Filed 5–11–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1281; Directorate 

Identifier 2014–NM–241–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 777 airplanes. 

This proposed AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the lap 

splices of the aft pressure bulkhead 

webs are subject to widespread fatigue 

damage (WFD). This proposed AD 

would require repetitive inspections for 

any crack in the aft webs of the radial 

lap splices of the aft pressure bulkhead, 

and, if necessary, corrective actions. We 

are proposing this AD to detect and 

correct fatigue cracking in the aft webs 

of the radial lap splices of the aft 

pressure bulkhead, which could result 

in reduced structural integrity of the 

airplane and decompression of the 

cabin. 

DATES: We must receive comments on 

this proposed AD by June 26, 2015. 

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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Proposed Rules 27117 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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. It is also available 

on the Internet at http://regulations.gov 

by searching for and locating Docket No. 

FAA–2015–1281. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1281; 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: 

Haytham Alaidy, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6573; 

fax: 425–917–6590; email: 

Haytham.Alaidy@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– 

2015–1281; Directorate Identifier 2014– 

NM–241–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as WFD. As an 

airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Cracks in the aft webs of the radial lap 

splices of the aft pressure bulkhead can 

rapidly coalesce, and could result in 

reduced structural integrity of the 

airplane and decompression of the 

cabin. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 777–53A0078, dated December 

5, 2014. The service information 

describes procedures for inspecting the 

aft webs of the radial lap splices of the 

aft pressure bulkhead and repairing any 

crack. Refer to this service information 

for information on the procedures and 

compliance times. This service 

information is reasonably available at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

1281. Or see ADDRESSES for other ways 

to access this service information. 

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 

accomplishing the actions specified in 

the service information described 

previously except as discussed under 

‘‘Differences Between This Proposed AD 

and the Service Information.’’ 

The phrase ‘‘corrective actions’’ might 

be used in this proposed AD. 

‘‘Corrective actions’’ are actions that 

correct or address any condition found. 

Corrective actions in an AD could 

include, for example, repairs. 

Differences Between This Proposed AD 

and the Service Information 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

27118 Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Proposed Rules 

Explanation of ‘‘Required for 

Compliance’’ (RC) Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as RC 

(required for compliance) in any service 

information identified previously have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

Steps that are identified as RC in any 

service information must be done to 

comply with the proposed AD. 

However, steps that are not identified as 

RC are recommended. Those steps that 

are not identified as RC may be deviated 

from using accepted methods in 

accordance with the operator’s 

maintenance or inspection program 

without obtaining approval of an 

alternative method of compliance 

(AMOC), provided the steps identified 

as RC can be done and the airplane can 

be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 193 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................... 9 work-hours × $85 per hour = $765 per inspection cycle.$0 $765 per inspection 

cycle.

$147,645 per inspection 

cycle. 

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– 

2015–1281; Directorate Identifier 2014– 

NM–241–AD. 

(a) Comments Due Date 

We must receive comments by June 26, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 777–200, –200LR, –300, 

–300ER, and 777F series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the lap splices of the aft pressure 

bulkhead webs are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to detect and correct fatigue cracking in 

the aft webs of the radial lap splices of the 

aft pressure bulkhead, which could result in 

reduced structural integrity of the airplane 

and decompression of the cabin. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Lap Splice in the Web of the 

Aft Pressure Bulkhead 

Except as required by paragraph (h) of this 

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

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0078, dated December 5, 

2014, do a medium frequency eddy current 

inspection for any cracking in the aft webs 

of the radial lap splices of the aft pressure 

bulkhead, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0078, dated 

December 5, 2014. Repeat the inspection 

thereafter at intervals not to exceed 8,400 

flight cycles from the previous inspection. If 

any crack is found during any inspection 

required by this paragraph, do the applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0078, dated 

December 5, 2014. If a corrective action 

described in Boeing Alert Service Bulletin 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Proposed Rules 27119 

777–53A0078, dated December 5, 2014, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (i) of this 

AD. 

(h) Exception to Service Information 

Specifications 

Where Boeing Alert Service Bulletin 777– 

53A0078, dated December 5, 2014, 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. 

(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 

paragraph (j)(1) 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, and the 

approval must specifically refer to this AD. 

(4) If any service information contains 

steps that are identified as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

identified as RC are recommended. Those 

steps that are not identified as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the steps 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC require approval of an 

AMOC. 

(j) Related Information 

(1) For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

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

98057–3356; phone: 425–917–6573; fax: 425– 

917–6590; email: Haytham.Alaidy@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, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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 May 1, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11351 Filed 5–11–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–0368; Airspace 

Docket No. 14–ACE–9] 

Proposed Amendment of Class E 

Airspace for the Following Iowa 

Towns: Audubon, IA; Corning, IA; 

Cresco, IA; Eagle Grove, IA; Guthrie 

Center, IA; Hampton, IA; Harlan, IA; 

Iowa Falls, IA; Knoxville, IA; Oelwein, 

IA; and Red Oak, IA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Audubon 

County Airport, Audubon, IA; Corning 

Municipal Airport, Corning, IA; Ellen 

Church Field Airport, Cresco, IA; Eagle 

Grove Municipal Airport, Eagle Grove, 

IA; Guthrie County Regional Airport, 

Guthrie Center, IA; Hampton Municipal 

Airport, Hampton, IA; Harlan Municipal 

Airport, Harlan, IA; Iowa Falls 

Municipal Airport, Iowa Falls, IA; 

Knoxville Municipal Airport, Knoxville, 

IA; Oelwein Municipal Airport, 

Oelwein, IA; and Red Oak Municipal 

Airport, Red Oak, IA. Decommissioning 

of the non-directional radio beacons 

(NDB) and/or cancellation of NDB 

approaches due to advances in Global 

Positioning System (GPS) capabilities 

has made this action necessary for the 

safety and management of Instrument 

Flight Rules (IFR) operations at the 

above airports. 

DATES: 0901 UTC. Comments must be 

received on or before June 26, 2015. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. You must 

identify the docket number FAA–2015– 

0368/Airspace Docket No. 14–ACE–9, at 

the beginning of your comments. You 

may also submit comments 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 between 

9:00 a.m. and 5:00 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone 1–800– 

647–5527), is on the ground floor of the 

building at the above address. 

FAA Order 7400.9Y, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at http://www.faa.gov/air_traffic/ 

publications/. The Order is also 

available for inspection at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this proposed 

incorporation by reference material at 

NARA, call 202–741–6030, or go to 

http://www.archives.gov/federal_

register/code_of_federal-regulations/ibr_

locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. For further information, 

you can contact the Airspace Policy and 

Regulations Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: 202–267–8783. 

FOR FURTHER INFORMATION CONTACT: 

Roger Waite, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone: (817) 321– 

7652. 

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 and be submitted in 

triplicate to the address listed above. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2015–0368/Airspace 

mstockstill on DSK4VPTVN1PROD with PROPOSALS