45550 Federal Register / Vol. 74, No. 170 / Thursday, September 3, 2009 / Rules and Regulations 

regarding lightning, § 25.1316, HIRF, 

§ 25.1317, and existing HIRF special 

conditions for the Boeing Model 737– 

600/–700/–700C/–800/–900 and 900ER 

series airplanes, SC–25–ANM–132, are 

incorporated by reference for the 

purpose of measuring lightning and 

HIRF protection. For the purposes of 

complying with HIRF requirements, the 

inflatable lapbelt system is considered a 

‘‘critical system’’ if its deployment 

could have a hazardous effect on the 

airplane; otherwise it is considered an 

‘‘essential’’ system. 

10. The inflatable lapbelt must 

function properly after loss of normal 

aircraft electrical power, and after a 

transverse separation of the fuselage at 

the most critical location. A separation 

at the location of the lapbelt does not 

have to be considered. 

11. It must be shown that the 

inflatable lapbelt will not release 

hazardous quantities of gas or 

particulate matter into the cabin. 

12. The inflatable lapbelt installation 

must be protected from the effects of fire 

such that no hazard to occupants will 

result. 

13. There must be a means for a 

crewmember to verify the integrity of 

the inflatable lapbelt activation system 

prior to each flight or it must be 

demonstrated to reliably operate 

between inspection intervals. 

14. The inflatable material may not 

have an average burn rate of greater than 

2.5 inches/minute when tested using the 

horizontal flammability test as defined 

in 14 CFR part 25, appendix F, part I, 

paragraph (b)(5). 

Issued in Renton, Washington, on August 

7, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–21299 Filed 9–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0781; Directorate 

Identifier 2009–NM–111–AD; Amendment 

39–16004; AD 2009–18–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes, 

Model A340–200 and –300 Series 

Airplanes, and Model A340–541 and 

–642 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–541 

and –642 airplanes. This AD requires 

replacing certain Thales Avionics pitot 

probes with certain other pitot probes. 

This AD results from reports of airspeed 

indication discrepancies while flying at 

high altitudes in inclement weather 

conditions. We are issuing this AD to 

prevent airspeed discrepancies, which 

could lead to disconnection of the 

autopilot and/or auto-thrust functions, 

and reversion to flight control alternate 

law and consequent increased pilot 

workload. Depending on the prevailing 

airplane altitude and weather, this 

condition, if not corrected, could result 

in reduced control of the airplane. 

DATES: This AD becomes effective 

September 8, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 8, 2009. 

We must receive comments on this 

AD by October 5, 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– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued a Notification of 

a Proposal to Issue an Airworthiness 

Directive (PAD), PAD 09–099, dated 

August 10, 2009 (referred to after this as 

‘‘the EASA PAD’’), to correct an unsafe 

condition for certain Airbus Model 

A330–200 and –300 series airplanes, 

Model A340–200 and –300 series 

airplanes, and Model A340–541 and 

–642 airplanes. The EASA PAD states 

that airspeed indication discrepancies 

have been reported on Model A330 and 

A340 airplanes while flying at high 

altitudes in inclement weather 

conditions. Investigation results 

indicate that these airplanes equipped 

with certain Thales Avionics pitot 

probes appear to have a greater 

susceptibility to adverse environmental 

conditions than certain other pitot 

probes. 

The EASA PAD also states that a new 

Thales Avionics pitot probe having part 

number (P/N) C16195BA has been 

designed, which improves the airspeed 

indication behavior in heavy rain 

conditions on Model A320 airplanes. 

This same pitot probe standard has been 

made available as an optional 

installation on Model A330 and A340 

airplanes, and although this has shown 

to be an improvement over the previous 

Thales Avionics pitot probe, P/N 

C16195AA standard, it has not yet 

demonstrated the same level of 

robustness to withstand high-altitude 

ice crystals as Goodrich pitot probes 

having P/N 0851HL. 

We are issuing this AD to prevent 

airspeed discrepancies, which could 

lead to disconnection of the autopilot 

and/or auto-thrust functions, and 

reversion to flight control alternate law 

and consequent increased pilot 

workload. Depending on the prevailing 

airplane altitude and weather, this 

condition, if not corrected, could result 

in reduced control of the airplane. 

Other Relevant Rulemaking 

On February 4, 2004, we issued AD 

2004–03–33, Amendment 39–13477 (69 

FR 9936, March 3, 2004), for certain 

Airbus Model A300 B2 and B4 series 

airplanes; Model A300 B4–600, A300 

B4–600R, and A300 F4–600R series 

airplanes (collectively called A300– 

600); Model A310 series airplanes; 

Model A319, A320, and A321 series 


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Federal Register / Vol. 74, No. 170 / Thursday, September 3, 2009 / Rules and Regulations 45551 

airplanes; Model A330–301, –321, –322, 

–341, and –342 airplanes; and Model 

A340 series airplanes. Paragraphs (g)(1) 

and (h)(1) of that AD require, for some 

Model A330 and A340 airplanes, 

replacement of certain pitot probes with 

Goodrich pitot probes having P/N 

0851HL. For other Model A330 and 

A340 airplanes, paragraphs (g)(2) and 

(h)(2) of that AD require replacement of 

certain pitot probes with Thales 

Avionics pitot probe having P/N 

C16195AA. 

Relevant Service Information 

Airbus has issued the service 

bulletins listed in the following table: 

TABLE—SERVICE BULLETINS

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A330–34–3231 ........................................... Original ................................................ August 12, 2009. 

Airbus Mandatory Service Bulletin A340–34–4238 ........................................... Original ................................................ August 12, 2009. 

Airbus Mandatory Service Bulletin A340–34–5071 ........................................... Original ................................................ August 12, 2009. 

Airbus Service Bulletin A330–34–3206 ............................................................. 01 ........................................................ November 12, 2008. 

Airbus Service Bulletin A340–34–4200 ............................................................. 01 ........................................................ November 12, 2008. 

Airbus Service Bulletin A340–34–5068 ............................................................. Original ................................................ December 1, 2008. 

Airbus Service Bulletins A330–34– 

3206, A340–34–4200, and A340–34– 

5068 describe procedures for replacing 

Thales Avionics pitot probes, P/N 

C16195AA, in positions 1, 2, and 3 

(captain, first officer, and standby, 

respectively) with Thales Avionics pitot 

probes, P/N C16195BA in those 

positions. 

Airbus Mandatory Service Bulletins 

A330–34–3231, A340–34–4238, and 

A340–34–5071 describe procedures for 

replacing Thales Avionics pitot probes, 

P/N C16195BA, in positions 1 and 3 

(captain and standby, respectively) with 

a Goodrich pitot probe, P/N 0851HL, in 

those positions. 

FAA’s Determination and Requirements 

of This 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 

service information referenced above. 

We are issuing 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. 

We have reviewed the EASA PAD, 

which proposes to require replacing 

certain Thales Avionics pitot probes 

installed on certain Airbus Model A330 

and A340 airplanes. Additionally, we 

have reviewed the numerous airspeed 

anomalies recently reported on Model 

A330 and A340 airplanes. Based on our 

review, we have determined that an 

unsafe condition exists and immediate 

airworthiness action for the Model A330 

and A340 fleet is warranted. 

Therefore, we are issuing this AD to 

prevent airspeed discrepancies, which 

could lead to disconnection of the 

autopilot and/or auto-thrust functions, 

and reversion to flight control alternate 

law and consequent increased pilot 

workload. Depending on the prevailing 

airplane altitude and weather, this 

condition, if not corrected, could result 

in reduced control of the airplane. This 

AD requires replacing Thales Avionics 

pitot probes having P/N C16195AA and 

P/N C16195BA at positions 1 (captain) 

and 3 (standby) with Goodrich pitot 

probes having P/N 0851HL at positions 

1 and 3. This AD also requires replacing 

Thales Avionics pitot probes having 

P/N C16195AA at position 2 (first 

officer) with Thales Avionics pitot 

probes having P/N C16195BA at 

position 2. In addition, this AD provides 

for optional installation of Goodrich 

pitot probes having P/N 0851HL at 

position 2. 

We have determined that doing the 

actions in this new AD terminates the 

requirements of paragraphs (g)(2) and 

(h)(2) of AD 2004–03–33, and also is 

acceptable for compliance with 

paragraphs (g)(1) and (h)(1) of AD 2004– 

03–33. We might consider further 

rulemaking to revise AD 2004–03–33. 

This AD corresponds to the EASA 

PAD, which addresses the identified 

unsafe condition on Model A330 and 

A340 airplanes. AD 2004–03–33 is 

applicable to Model A330 and A340 

airplanes and other Airbus airplane 

models. We might consider further 

rulemaking to address other Airbus 

models. 

FAA’s Justification and Determination 

of the Effective Date 

Airspeed discrepancies could lead to 

disconnection of the autopilot and/or 

auto-thrust functions, and reversion to 

flight control alternate law and 

consequent increased pilot workload. 

Depending on the prevailing airplane 

altitude and weather, this condition, if 

not corrected, could result in reduced 

control of the airplane. Because of our 

requirement to promote safe flight of 

civil aircraft and thus, the critical need 

to assure the proper functioning of the 

pitot probes, and the short compliance 

time involved with this action, this AD 

must be issued immediately. 

The required compliance time of 120 

days is usually sufficient to allow for a 

brief comment period before adoption of 

a final rule. In this AD, however, the 

compliance time of 120 days was 

selected because of a short-term 

problem with the availability of 

sufficient replacement parts; a shorter 

compliance time might have resulted in 

the unnecessary removal of airplanes 

from service pending delivery of 

replacement parts. Nevertheless, we 

have determined that immediate 

adoption of this AD is necessary in this 

case because of the importance of 

initiating the required replacements as 

soon as possible. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–0781; Directorate Identifier 2009– 

NM–111–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 


jlentini on DSKJ8SOYB1PROD with RULES
45552 Federal Register / Vol. 74, No. 170 / Thursday, September 3, 2009 / Rules and Regulations 

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 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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 that the 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2009–18–08 Airbus: Amendment 39–16004. 

Docket No. FAA–2009–0781; Directorate 

Identifier 2009–NM–111–AD. 

Effective Date 

(a) This AD becomes effective September 8, 

2009. 

Affected ADs 

(b) This AD affects AD 2004–03–33, 

Amendment 39–13477. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

equipped with Thales Avionics pitot probes 

having part number (P/N) C16195AA or 

C16195BA. 

(1) Airbus Model A330–201, A330–202, 

A330–203, A330–223, A330–243, A330–301, 

A330–302, A330–303, A330–321, A330–322, 

A330–323, A330–341, A330–342, and A330– 

343 series airplanes. 

(2) Airbus Model A340–211, A340–212, 

A340–213, A340–311, A340–312, and A340– 

313 series airplanes. 

(3) Airbus Model A340–541 and A340–642 

airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 34: Navigation. 

Unsafe Condition 

(e) This AD results from reports of airspeed 

indication discrepancies while flying at high 

altitudes in inclement weather conditions. 

We are issuing this AD to prevent airspeed 

discrepancies, which could lead to 

disconnection of the autopilot and/or autothrust functions, and reversion to flight 

control alternate law and consequent 

increased pilot workload. Depending on the 

prevailing airplane altitude and weather, this 

condition, if not corrected, could result in 

reduced control of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Replacement 

(g) Within 120 days after the effective date 

of this AD, accomplish the applicable 

replacements required by paragraphs (g)(1) 

and (g)(2) of this AD. 

(1) For airplanes equipped with Thales 

Avionics pitot probes, P/N C16195AA, in 

position 2 (first officer): Replace the P/N 

C16195AA pitot probe with a Thales 

Avionics pitot probe having P/N C16195BA, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. 

TABLE 1—SERVICE BULLETINS FOR REPLACEMENTS SPECIFIED IN PARAGRAPH (g)(1) OF THIS AD 

For model— Use Airbus Service 

Bulletin— Revision— Dated— 

A330–201, –202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 series airplanes.

A330–34–3206 ..................... 01 ......................................... November 12, 2008. 

A340–211, –212, –213, –311, –312, and –313 series airplanes.A340–34–4200 ..................... 01 ......................................... November 12, 2008. 

A340–541 and –642 airplanes ............................................. A340–34–5068 ..................... Original ................................. December 1, 2008. 

(2) For airplanes equipped with Thales 

Avionics pitot probes, P/N C16195AA or 

P/N C16195BA, in position 1 (captain) or 3 

(standby): Replace P/N C16195AA and P/N 

C16195BA pitot probes with Goodrich pitot 

probes having P/N 0851HL, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin listed in Table 2 

of this AD. 


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Federal Register / Vol. 74, No. 170 / Thursday, September 3, 2009 / Rules and Regulations 45553 

TABLE 2—SERVICE BULLETINS FOR REPLACEMENTS SPECIFIED IN PARAGRAPH (g)(2) OF THIS AD 

For model— Use Airbus Mandatory 

Service Bulletin— Revision— Dated— 

A330–201, –202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 series airplanes.

A330–34–3231 ...................... Original .................................. August 12, 2009. 

A340–211, –212, –213, –311, –312, and –313 series airplanes.A340–34–4238 ...................... Original .................................. August 12, 2009. 

A340–541 and –642 airplanes ............................................... A340–34–5071 ...................... Original .................................. August 12, 2009. 

Optional Replacement 

(h) Installing Goodrich pitot probes having 

P/N 0851HL in position 2 (first officer), in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent); is 

acceptable for compliance with the 

requirements of paragraph (g)(1) of this AD. 

Credit for Actions Done in Accordance With 

Previous Issues of Service Bulletins 

(i) Accomplishing the replacement 

required by paragraph (g)(1) of this AD before 

the effective date of this AD, in accordance 

with Airbus Service Bulletin A330–34–3206, 

dated September 14, 2007; or Airbus Service 

Bulletin A340–34–4200, dated September 14, 

2007; as applicable, is acceptable for 

compliance with the corresponding action 

required by paragraph (g)(1) of this AD. 

Related AD 2004–03–33 

(j) Doing the applicable replacements 

required by this AD terminates the 

replacements required by paragraphs (g)(2) 

and (h)(2) of AD 2004–03–33. 

(k) Doing the applicable replacements 

required by this AD is acceptable for 

compliance with the replacements required 

by paragraphs (g)(1) and (h)(1) of AD 2004– 

03–33. 

Alternative Methods of Compliance 

(AMOCs) 

(l) 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: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1138; 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. 

Related Information 

(m) None. 

Material Incorporated by Reference 

(n) You must use the applicable service 

information contained in Table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For 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, e-mail: 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A330–34–3231 ............................................... Original .................................................. August 12, 2009. 

Airbus Mandatory Service Bulletin A340–34–4238 ............................................... Original .................................................. August 12, 2009. 

Airbus Mandatory Service Bulletin A340–34–5071 ............................................... Original .................................................. August 12, 2009. 

Airbus Service Bulletin A330–34–3206 ................................................................. 01 .......................................................... November 12, 2008. 

Airbus Service Bulletin A340–34–4200 ................................................................. 01 .......................................................... November 12, 2008. 

Airbus Service Bulletin A340–34–5068 ................................................................. Original .................................................. December 1, 2008. 

Issued in Renton, Washington, on August 

24, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21368 Filed 9–2–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2008–0763; Airspace 

Docket No. 08–AAL–22] 

Establishment of Class E Airspace; 

Quinhagak, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace at Quinhagak, AK to provide 

adequate controlled airspace to contain 

aircraft executing Standard Instrument 

Approach Procedures (SIAPs). Two 

Standard Instrument Approach 

Procedures (SIAPs) are being developed 

for the Quinhagak Airport at Quinhagak, 

AK. Additionally, one textual Obstacle 

Departure Procedure (ODP) is being 

developed. Also, this action makes a 

minor correction to the geographic 

coordinates for the airport. This action 

establishes Class E airspace upward 

from 700 feet (ft.) above the surface at 

Quinhagak Airport, Quinhagak, AK. 

DATES: Effective Date: 0901 UTC, 

October 22, 2009. The Director of the 

Federal Register approves this 


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