Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 18925 

(i) Repeat the detailed inspection of the 

cam latches and latch pins for damage, 

distress, or incorrect rigging. 

(ii) Repeat the HFEC or magnetic particle 

inspection of cam latch 1 and cam latch 2 for 

cracking. 

(k) Exceptions to Service Bulletin 

Specifications 

The following exceptions apply to this AD. 

(1) Where Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); specifies a compliance 

time relative to the issue date of that service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(2) Where Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); specifies to contact 

Boeing for appropriate action: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); repair in accordance 

with a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA. 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. 

(l) Concurrent Actions 

(1) For airplanes identified in Boeing 707 

Alert Service Bulletin A3536, dated February 

6, 2012: Before or concurrently with 

accomplishment of the detailed inspection 

specified in paragraph (g) of this AD, do a 

general visual inspection of the hinge fittings 

and the cam latches on the MCD, and 

perform related investigative and corrective 

actions as applicable, in accordance with the 

Accomplishment Instructions of Boeing 707/ 

720 Service Bulletin 3477, Revision 2, dated 

April 15, 1993. 

(2) For airplanes identified in Boeing Alert 

Service Bulletin 727–52A0150, dated January 

30, 2012: Before or concurrently with 

accomplishment of the detailed inspection 

specified in paragraph (g) of this AD, do a 

general visual inspection of the hinge fittings 

and the cam latches on the MCD, and 

perform related investigative and corrective 

actions if applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–52–0142, Revision 2, 

dated April 15, 1993. 

(m) Optional Terminating Action 

Accomplishment of the latch mechanism 

adjustment test and the MCD rigging, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes); terminates the 

repetitive inspections specified in paragraph 

(h) of this AD. Thereafter, do the MCD postrigging initial inspections and applicable 

related investigative and corrective actions 

specified in paragraph (i) of this AD, and the 

repetitive inspections specified in paragraph 

(j) of this AD. 

(n) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an alloy steel bolt as a 

cross bolt through any latch pin fitting 

assembly in the lower sill of the MCD on any 

airplane. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

(p) Related Information 

(1) For more information about this AD, 

contact Kimberly A. DeVoe, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6495; fax: 425–917–6590; 

email: kimberly.devoe@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 review copies of the 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 March 

21, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07213 Filed 3–27–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0212; Directorate 

Identifier 2012–NM–116–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 

Airbus Model A330–223F, –223, –321, 

–322, and –323 airplanes. This proposed 

AD was prompted by fatigue load 

analysis that determined that the 

inspection interval for certain pylon 

bolts must be reduced. This proposed 

AD would require a torque check of 

forward engine mount bolts, and 

replacement if necessary. We are 

proposing this AD to detect and correct 

loose or broken bolts, which could lead 

to engine detachment in-flight, and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 13, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. You may review 

copies of the 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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

18926 Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

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, WA 

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–2013–0212; Directorate Identifier 

2012–NM–116–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 2012–0094, 

dated May 31, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The forward mount engine pylon bolts, 

Part Number (P/N) 51U615, fitted on Airbus 

A330 aeroplanes with Pratt & Whitney (PW) 

PW4000 engines, are made from MP159 

material. 

The U.S. Federal Aviation Administration 

(FAA), as Engine Certification Authority, 

issued AD 2006–16–05 [Amendment 39– 

14705 (71 FR 44185, August 4, 2006)] to 

require (paragraph (g) of that AD) repetitive 

torque checks of MP159 material forward 

mount pylon bolts fitted on certain PW4000 

series engines. 

However, the engine mount system is 

considered to be part of aeroplane 

certification rather than the engine 

certification. Following further fatigue load 

analysis by Airbus of the A330 engine mount 

system, completed in February 2011 for both 

the freighter and passenger models of A330 

aeroplanes, it was determined that MP159 

material forward mount pylon bolts 

inspection interval must be reduced. 

This condition, if not detected and 

corrected, could ultimately lead to engine 

detachment from the aeroplane, possibly 

resulting in damage to the aeroplane and/or 

injury to person on the ground. 

For the reasons described above, this 

[EASA] AD requires accomplishment of 

repetitive torque checks of the forward 

mount pylon bolts installed on A330 

aeroplanes powered by PW4000 engines and, 

depending on findings, the replacement of all 

four bolts and associated nuts. 

Findings (discrepancies) include loose 

or broken bolts. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–71–3028, Revision 01, 

dated February 20, 2012. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

Compliance With AD 2006–16–05, 

Amendment 39–14705 (71 FR 44185, 

August 4, 2006) 

Doing the actions required by 

paragraph (g) of this AD constitutes 

compliance with the requirements 

specified in paragraph (g) of AD 2006– 

16–05, Amendment 39–14705 (71 FR 

44185, August 4, 2006). 

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 41 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours 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 

$6,970, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $6,747, for a cost of $6,832 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 18927 

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–2013–0212; 

Directorate Identifier 2012–NM–116–AD. 

(a) Comments Due Date 

We must receive comments by May 13, 

2013. 

(b) Affected ADs 

This AD affects AD 2006–16–05, 

Amendment 39–14705 (71 FR 44185, August 

4, 2006). 

(c) Applicability 

This AD applies to Airbus Model A330– 

223F, –223, –321, –322, and –323 airplanes, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by fatigue load 

analysis that determined that certain pylon 

bolts inspection interval must be reduced. 

We are issuing this AD to detect and correct 

loose or broken bolts, which could lead to 

engine detachment in-flight, and damage to 

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) Torque Check and Replacement 

(1) Within the compliance times specified 

in table 1, table 2, or table 3 to paragraph (g) 

of this AD, as applicable to airplane model 

and utilization, do a torque check to 

determine if there are any loose or broken 

forward engine mount bolts (4 positions/ 

engine) on both engines, and repeat that 

torque check at intervals not to exceed the 

values defined in table 1, table 2, or table 3 

to paragraph (g) of this AD, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–71– 

3028, Revision 01, dated February 20, 2012. 

For the purposes of table 1 and table 2 to 

paragraph (g) of this AD, the average flight 

time (AFT) is defined as a computation of the 

number of flight hours divided by the 

number of flight cycles accumulated since 

last torque check or since the airplane’s first 

flight, as applicable. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD: FOR MODEL A330–223, –321, –322 AND –323 AIRPLANES WITH AFT MORE

THAN 132 MINUTES

Flight cycles accumulated on the effective date 

of this AD since last torque check performed 

as specified in Pratt & Whitney Alert Service 

Bulletin PW4G–100–A71–32; or since airplane 

first flight, as applicable 

Compliance time Torque check interval (not to exceed) 

0–1,850 .............................................................. Within 2,350 flight cycles since the last torque 

check as specified in Pratt & Whitney Alert 

Service Bulletin PW4G–100–A71–32, or 

since airplane first flight, as applicable.

2,350 flight cycles or 24,320 flight hours, 

whichever occurs first. 

1,851–2,700 ....................................................... Within 500 flight cycles after the effective date 

of this AD without exceeding 2,700 flight cycles since last torque check as specified in 

Pratt & Whitney Alert Service Bulletin 

PW4G–100–A71–32, or since airplane first 

flight, as applicable; or within 3 months after 

the effective date of this AD; whichever occurs later.

2,350 flight cycles or 24,320 flight hours, 

whichever occurs first. 

TABLE 2 TO PARAGRAPH (g) OF THIS AD: FOR MODEL A330–321, –322, AND –323 AIRPLANES WITH AFT EQUAL OR

LESS THAN 132 MINUTES; AND FOR MODEL A330–321, –322, AND –323 AIRPLANES ON WHICH THE AFT IS NOT

CALCULATED ON A REGULAR BASIS

Flight cycles accumulated on the effective date 

of this AD since last torque check as 

performed as specified in Pratt & Whitney 

Alert Service Bulletin PW4G–100–A71–32; 

or since airplane first flight, as applicable 

Compliance time Torque check interval (not to exceed) 

0–1,450 .............................................................. Within 1,950 flight cycles since the last torque 

check performed as specified in Pratt & 

Whitney Alert Service Bulletin PW4G–100– 

A71–32, or since airplane first flight, as applicable.

1,950 flight cycles or 20,210 flight hours, 

whichever occurs first. 

1,451–2,700 ....................................................... Within 500 flight cycles after the effective date 

of this AD without exceeding 2,700 flight cycles since last torque check performed as 

specified in Pratt & Whitney Alert Service 

Bulletin PW4G–100–A71–32, or since airplane first flight, as applicable; or within 3 

months after the effective date of this AD; 

whichever occurs later.

1,950 flight cycles or 20,210 flight hours, 

whichever occurs first. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

18928 Federal Register / Vol. 78, No. 60 / Thursday, March 28, 2013 / Proposed Rules 

TABLE 3 TO PARAGRAPH (g) OF THIS AD: FOR MODEL A330–223F AIRPLANES

Compliance time Torque check interval (not to exceed) 

Within 2,140 flight cycles or 6,600 flight hours, whichever occurs first 

since the last torque check performed as specified in Pratt & Whitney 

Alert Service Bulletin PW4G–100–A71–32, or since airplane first 

flight, as applicable.

2,140 flight cycles or 6,600 flight hours, whichever occurs first. 

(2) If any loose or broken bolt is detected 

during the check required by paragraph (g)(1) 

of this AD, before further flight, replace all 

four forward engine mount bolts and 

associated nuts, on the engine where the 

loose or broken bolt was detected, with new 

bolts and nuts, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–71–3028, 

Revision 01, dated February 20, 2012. 

(3) Replacement of bolts and nuts as 

required by paragraph (g)(2) of this AD is not 

terminating action for the repetitive torque 

checks required by paragraph (g)(1) of this 

AD. 

(h) Compliance with AD 2006–16–05, 

Amendment 39–14705 (71 FR 44185, August 

4, 2006) 

Doing the actions required by paragraph (g) 

of this AD constitutes compliance with the 

requirements specified in paragraph (g) of AD 

2006–16–05, Amendment 39–14705 (71 FR 

44185, August 4, 2006). 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any INCO718 material, 

forward mount pylon bolt having Pratt & 

Whitney P/N 54T670 on any airplane. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Mandatory Service Bulletin 

A330–71–3028, dated December 16, 2011, 

which is not incorporated by reference in 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, 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, WA 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. 

(l) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0094, dated May 31, 2012; and Airbus 

Mandatory Service Bulletin A330–71–3028, 

Revision 01, dated February 20, 2012. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. You may review copies of 

the 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 March 

20, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07203 Filed 3–27–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0158; Airspace 

Docket No. 13–ASO–5] 

Proposed Amendment of Class E 

Airspace; Tuskegee, AL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E Airspace at Tuskegee, 

AL, as the Tuskegee VOR/DME has been 

decommissioned and airspace 

reconfiguration is necessary for the 

safety and airspace management of 

Instrument Flight Rules (IFR) operations 

at Moten Field Municipal Airport. This 

action also would amend the airport’s 

name. 

DATES: Comments must be received on 

or before May 13, 2013. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey SE., Washington, DC 20590– 

0001; Telephone: 1–800–647–5527; Fax: 

202–493–2251. You must identify the 

Docket Number FAA–2013–0158; 

Airspace Docket No. 13–ASO–5, at the 

beginning of your comments. You may 

also submit and review received 

comments through the Internet at 

http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rule by submitting 

such written data, views, or arguments, 

as they may desire. Comments that 

provide the factual basis supporting the 

views and suggestions presented are 

particularly helpful in developing 

reasoned regulatory decisions on the 

proposal. Comments are specifically 

invited on the overall regulatory, 

aeronautical, economic, environmental, 

and energy-related aspects of the 

proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2013–0158; Airspace Docket No. 13– 

ASO–5) and be submitted in triplicate to 

the Docket Management System (see 

‘‘ADDRESSES’’ section for address and 

phone number). You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

Persons wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2013–0158; Airspace 

Docket No. 13–ASO–5.’’ The postcard 

mstockstill on DSK4VPTVN1PROD with PROPOSALS