31896 Federal Register / Vol. 74, No. 127 / Monday, July 6, 2009 / Proposed Rules 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Boeing: Docket No. FAA–2009–0608; 

Directorate Identifier 2008–NM–215–AD. 

Comments Due Date 

(a) We must receive comments by August 

20, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

747–200C and –200F series airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report from the 

manufacturer that the accomplishment of 

certain existing inspections, repairs, and 

modifications is not adequate to ensure the 

structural integrity of the affected 7075 series 

aluminum alloy upper deck floor beam upper 

chords on airplanes that have exceeded 

certain thresholds. We are issuing this AD to 

prevent cracking of the upper chords and 

straps (or angles) of the floor beams, which 

could lead to failure of the floor beams and 

consequent loss of controllability, rapid 

decompression, and loss of structural 

integrity of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Initial Inspection and Replacement 

(g) Before the accumulation of 21,000 total 

flight cycles, or within 1,500 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do an open hole high frequency 

eddy current (HFEC) inspection of all the 

fastener holes accessed for upper chord 

removal for cracks, and replace upper chords, 

straps (or angles), and radius fillers of the 

upper deck floor beams, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008. 

Repetitive Replacements and PostReplacement Inspections 

(h) Within 15,000 flight cycles after doing 

the replacement required by paragraph (g) of 

this AD, or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later: Do detailed and HFEC inspections for 

cracks of the modified upper deck floor 

beams, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2696, dated October 

16, 2008. Within 6,000 flight cycles after 

doing the detailed and HFEC inspections, do 

the replacement specified in paragraph (g) of 

this AD. Repeat the post-replacement 

inspections and replacement at the 

applicable times specified in paragraph 1.E. 

of Boeing Alert Service Bulletin 747– 

53A2696, dated October 16, 2008. 

Repair of Cracks 

(i) If any crack is found during any 

inspection required by this AD: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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: Ivan 

Li, Airframe Branch, ANM–120S, FAA, 

Seattle ACO, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. Or, email information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(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 on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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. 

Issued in Renton, Washington, on June 25, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15811 Filed 7–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0055; Directorate 

Identifier 2008–NM–194–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, A300 B2–203, A300 B2K– 

3C, A300 B4–103, A300 B4–203, and 

A300 B4–2C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

NPRM for the products listed above. 

This action revises the earlier NPRM by 

expanding the scope. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). * * * 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

* * * are required to conduct a design 

review against explosion risks. 

One of the consequences of the Airbus 

design review is the modification of the fuel 

pump wiring to provide protection against 

chafing of the fuel pump cables. This 

condition, if not corrected, could result in 

short circuits leading to fuel pump failure, 

arcing, and possible fuel tank explosion. 

[A previous AD] was issued to require 

* * * modification [of the fuel pump against 

short circuit] * * *. More recently, an 

additional modification of the electrical 

wiring of the outer fuel pump and the 

landing lights on the left (LH) and right (RH) 

sides has been introduced * * *. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 31, 2009. 

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– 


cprice-sewell on PROD1PC69 with PROPOSALS
Federal Register / Vol. 74, No. 127 / Monday, July 6, 2009 / Proposed Rules 31897 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@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, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221 or 425–227–1152. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

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–2009–0055; Directorate Identifier 

2008–NM–194–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 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

February 13, 2009 (72 FR 7202). That 

earlier NPRM proposed to supersede AD 

2007–18–02, amendment 39–15182 (74 

FR 49175, August 28, 2007), to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM was issued, Airbus 

has revised service information to 

introduce additional mechanical 

protection to prevent the fuel pump or 

landing light wiring from chafing. 

Airbus Mandatory Service Bulletin 

A300–24–0103, Revision 03, dated 

February 18, 2009, provides procedures 

for installing new splicing on the wires, 

a new cable type, shrink sleeve 

installation on the new wiring, and an 

additional braided conduit sleeve 

(Halar), as applicable, for the fuel 

pumps and landing lights. 

We referred to Airbus Service 

Bulletins A300–24–0103, Revision 01, 

dated January 11, 2007; and Revision 

02, dated April 4, 2008; as the 

appropriate sources of service 

information for doing the actions 

proposed in the original NPRM. More 

work is necessary for airplanes modified 

in accordance with either of those two 

service bulletins. We have revised 

paragraphs (c), (f), and (g) of this 

proposed AD to refer to Airbus 

Mandatory Service Bulletin A300–24– 

0103, Revision 03, dated February 18, 

2009. 

We have revised the Costs of 

Compliance paragraph of this 

supplemental NPRM to specify the costs 

of the requirements that are retained 

from the existing AD and the costs of 

the new requirements of this 

supplemental NPRM. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0188, 

dated October 10, 2008 (referred to after 

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

condition for the specified products. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–24–0103, Revision 03, 

dated February 18, 2009. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

The additional actions in the revised 

service information described above 

expand the scope of the earlier NPRM. 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this proposed AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 13 products of U.S. registry. 

The actions that are required by AD 

2007–18–02 and retained in this 

proposed AD take about 72 work-hours 

per product, at an average labor rate of 

$80 per work hour. Required parts 

would cost about $5,050 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these costs. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, the estimated 

cost of the currently required actions is 

$140,530, or $10,810 per product. 

We estimate that it would take about 

42 work-hours per product to comply 

with the new basic requirements of this 


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proposed AD. The average labor rate is 

$80 per work-hour. Required parts 

would cost about $4,100 per product. 

Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these costs. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $96,980, or $7,460 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it 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 

removing Amendment 39–15182 (72 FR 

49175, August 28, 2007) and adding the 

following new AD: 

Airbus: Docket No. FAA–2009–0055; 

Directorate Identifier 2008–NM–194–AD. 

Comments Due Date 

(a) We must receive comments by July 31, 

2009. 

Affected ADs 

(b) The proposed AD supersedes AD 2007– 

18–02, Amendment 39–15182. 

Applicability 

(c) This AD applies to Airbus Model A300 

B2–1C, A300 B2–203, A300 B2K–3C, A300 

B4–103, A300 B4–203, and A300 B4–2C 

airplanes, certificated in any category, as 

identified in Airbus Mandatory Service 

Bulletin A300–24–0103, Revision 03, dated 

February 18, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

[T]he FAA has published SFAR 88 (Special 

Federal Aviation Regulation 88). 

Subsequently, the Joint Aviation Authorities 

(JAA) recommended the application of a 

similar regulation to the National Aviation 

Authorities (NAA) of its member countries. 

Under this regulation, all holders of type 

certificates for passenger transport aircraft 

with either a passenger capacity of 30 or 

more, or a payload capacity of 3,402 kg 

(7,500 lbs) or more, which have received 

their certification since 01 January 1958, are 

required to conduct a design review against 

explosion. 

One of the consequences of the Airbus 

design review is the modification of the fuel 

pump wiring to provide protection against 

chafing of the fuel pump cables. This 

condition, if not corrected, could result in 

short circuits leading to fuel pump failure, 

arcing, and possible fuel tank explosion. 

EASA (European Aviation Safety Agency) 

AD 2007–0066 [which corresponds to FAA 

AD 2007–18–02] was issued to require this 

modification in accordance with Airbus SB 

[service bulletin] A300–24–0103, Revision 

01. More recently, an additional modification 

of the electrical wiring of the outer fuel pump 

and the landing lights on the left (LH) and 

right (RH) side has been introduced in 

Revision 02 of Airbus SB A300–24–0103. For 

the reason described above, this new AD 

retains the requirements of EASA AD 2007– 

0066, which is superseded, and requires 

additional work. 

The additional modification will provide 

additional protection from chafing and will 

prevent intermittent operation of the fuel 

pump and landing lights, as well as the 

failure of the power supply. The modification 

of the wiring of the outer fuel pump and the 

landing light on the LH side route 1P harness 

and RH side route 2P harness includes 

additional mechanical protection that 

includes procedures for installing new 

splicing on the wires, a new cable type, 

shrink sleeve installation on the new wiring, 

and an additional braided conduit sleeve 

(Halar), as applicable, for the fuel pumps and 

the landing lights. 

Restatement of Requirements of AD 2007– 

18–02 With New Service Bulletin 

(f) Within 31 months after October 2, 2007 

(the effective date of AD 2007–18–02), unless 

already done, modify the inner and outer fuel 

pump wiring, route 1P and 2P harnesses in 

the LH (left-hand) wing and in the RH (righthand) wing, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–24–0103, Revision 01, 

dated January 11, 2007; or Airbus Mandatory 

Service Bulletin A300–24–0103, Revision 03, 

dated February 18, 2009. As of the effective 

date of this AD, Airbus Mandatory Service 

Bulletin A300–24–0103, Revision 03, dated 

February 18, 2009, must be used for the 

actions required by this paragraph. Actions 

done before October 2, 2007, in accordance 

with Airbus Service Bulletin A300–24–0103, 

dated March 15, 2006, for airplanes under 

configuration 01 as defined in Airbus Service 

Bulletin A300–24–0103, Revision 01, dated 

January 11, 2007; Revision 02, dated April 4, 

2008; or Revision 03, dated February 18, 

2009; are acceptable for compliance with the 

requirements of this paragraph. 

New Requirements of This AD: Actions and 

Compliance 

(g) Unless already done, within 12 months 

after the effective date of this AD, modify the 

wiring of the outer fuel pump and the 

landing light on the LH side route 1P harness 

and RH side route 2P harness, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–24– 

0103, Revision 03, dated February 18, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI specifies doing a modification in 

accordance with Airbus Mandatory Service 

Bulletin A300–24–0103, Revision 02, dated 

April 4, 2008. However, this AD requires 

doing additional actions that are specified in 

Airbus Mandatory Service Bulletin A300–24– 

0103, Revision 03, dated February 18, 2009. 

The MCAI has not yet been revised to require 


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the additional actions. We have coordinated 

this difference with EASA. 

Other FAA AD Provisions 

(h) 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. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2008–0188, dated October 10, 2008; 

Airbus Service Bulletin A300–24–0103, 

Revision 01, dated January 11, 2007; and 

Airbus Mandatory Service Bulletin A300–24– 

0103, Revision 03, dated February 18, 2009; 

for related information. 

Issued in Renton, Washington, on June 25, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15812 Filed 7–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0231; Airspace 

Docket No. 09–AAL–6] 

Proposed Establishment of Class E 

Airspace; Chuathbaluk, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This action proposes to 

establish Class E airspace at 

Chuathbaluk, AK. One Standard 

Instrument Approach Procedure (SIAP) 

is being developed for the Chuathbaluk 

Airport at Chuathbaluk, AK. Adoption 

of this proposal would result in creating 

Class E airspace upward from 700 feet 

(ft.) above the surface at the 

Chuathbaluk Airport, Chuathbaluk, AK. 

DATES: Comments must be received on 

or before August 20, 2009. 

ADDRESSES: Send comments on the 

proposal to the Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. You must identify the 

docket number FAA–2009–0231/ 

Airspace Docket No. 09–AAL–6, at the 

beginning of your comments. You may 

also submit comments on 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 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket Office 

(telephone 1–800–647–5527) is on the 

plaza level of the Department of 

Transportation NASSIF Building at the 

above address. 

An informal docket may also be 

examined during normal business hours 

at the office of the Manager, Safety, 

Alaska Flight Service Operations, 

Federal Aviation Administration, 222 

West 7th Avenue, Box 14, Anchorage, 

AK 99513–7587. 

FOR FURTHER INFORMATION CONTACT: Gary 

Rolf, Federal Aviation Administration, 

222 West 7th Avenue, Box 14, 

Anchorage, AK 99513–7587; telephone 

number (907) 271–5898; fax: (907) 271– 

2850; e-mail: gary.ctr.rolf@faa.gov. 

Internet address: http://www.faa.gov/ 

about/office_org/headquarters_offices/ 

ato/service_units/systemops/fs/alaskan/ 

rulemaking/. 

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–2009–0231/Airspace 

Docket No. 08–AAL–6.’’ 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 notice 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 Notice of Proposed 

Rulemakings (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 or the Superintendent of 

Document’s Web page at http:// 

www.access.gpo.gov/nara/index.html. 

Additionally, any person may obtain 

a copy of this notice by submitting a 

request to the Federal Aviation 

Administration, Office of Air Traffic 

Airspace Management, ATA–400, 800 

Independence Avenue, SW., 

Washington, DC 20591 or by calling 

(202) 267–8783. Communications must 

identify both docket numbers for this 

notice. Persons interested in being 

placed on a mailing list for future 

NPRMs should contact the FAA’s Office 

of Rulemaking, (202) 267–9677, to 

request a copy of Advisory Circular No. 

11–2A, Notice of Proposed Rulemaking 

Distribution System, which describes 

the application procedure. 

The Proposal 

The FAA is considering an 

amendment to the Code of Federal 

Regulations (14 CFR part 71), which 

would establish Class E airspace at the 

Chuathbaluk Airport, in Chuathbaluk, 

AK. The intended effect of this proposal 

is to create Class E airspace upward 

from 700 ft. above the surface to contain 

Instrument Flight Rules (IFR) operations 

at the Chuathbaluk Airport, 

Chuathbaluk, AK. 


cprice-sewell on PROD1PC69 with PROPOSALS