Federal Register / Vol. 74, No. 196 / Tuesday, October 13, 2009 / Rules and Regulations 52395 

Accomplishment Instructions paragraph 3.B. 

or paragraph 3.C. of RR MSB RB.211–72– 

7775, Revision 3, dated April 9, 1999, and 

the following compliance schedules: 

(1) For cases with 1,500 or fewer cyclessince-new (CSN) on the effective date of this 

AD, inspect before accumulating 1,500 CSN. 

(2) For cases with more than 1,500 CSN on 

the effective date of this AD, inspect within 

50 cycles-in-service (CIS) after the effective 

date of this AD. 

(3) If you detect any cracks of 1.5 inches 

or more in length, replace the case before 

further flight. 

Repetitive Inspections 

(g) Thereafter, inspect cases at the 

following intervals. Use the Accomplishment 

Instructions paragraph 3.B. or paragraph 3.C. 

of RR MSB RB.211–72–7775, Revision 3, 

dated April 9, 1999. 

(1) Inspect within 500 cycles-since-last 

inspection (CSLI) if you detected no cracks 

during the last inspection. 

(2) Inspect within 100 CSLI if you detected 

cracks less than or equal to 0.5 inch in length 

during the last inspection. 

(3) Inspect within 50 CSLI if you detected 

cracks greater than 0.5 inch but less than 1.5 

inches in length. 

Credit for Previous Inspections 

(h) Cases inspected before the effective 

date of this AD using RB.211–72–7775, 

Revision 2, dated February 27, 1998, or 

earlier issue, meet the requirements of this 

AD for the initial or repetitive inspections 

specified in paragraphs (f) through (f)(3) and 

(g) through (g)(3) of this AD. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) Civil Aviation Authority airworthiness 

directive 008–07–85, dated June 19, 1985, 

also addresses the subject of this AD. 

(k) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: ian.dargin@faa.gov; telephone (781) 

238–7178; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(l) You must use Rolls-Royce plc 

Mandatory Service Bulletin RB.211–72–7775, 

Revision 3, dated April 9, 1999 to perform 

the inspections required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact Rolls-Royce plc, 

P.O. Box 31, Derby, DE24 8BJ, United 

Kingdom; telephone: 44 (0) 1332–242424; 

fax: 44 (0) 1332–249936, for a copy of this 

service information. You may review copies 

at the FAA, New England Region, 12 New 

England Executive Park, Burlington, MA; or 

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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 22, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–23661 Filed 10–9–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0429; Directorate 

Identifier 2007–NM–059–AD; Amendment 

39–16038; AD 2009–21–01] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300 and 737–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–300 and 737–400 

series airplanes. This AD requires 

repetitive inspections to detect cracking 

of the aft fuselage skin, and related 

investigative/corrective actions if 

necessary. This AD results from reports 

of cracks in the aft fuselage skin on both 

sides of the airplane. We are issuing this 

AD to detect and correct cracking in the 

aft fuselage skin along the longitudinal 

edges of the bonded skin doubler, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD is effective November 

17, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 17, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6447; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 737–300 and 737– 

400 series airplanes. That NPRM was 

published in the Federal Register on 

May 7, 2009 (74 FR 21278). That NPRM 

proposed to require repetitive 

inspections to detect cracking of the aft 

fuselage skin, and related investigative/ 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the three commenters. 

Support for the AD 

Boeing concurs with the content of 

the NPRM. 

Request To Allow Use of Previous 

Service Information 

Southwest Airlines requests that skin 

panel replacements accomplished in 

accordance with Part 3 of Boeing 

Service Bulletin 737–53–1168, Revision 

1, dated August 17, 1995; and Revision 

2, dated November 27, 1996; also be 

considered as terminating action for the 

inspections specified in paragraph (g) of 

the NPRM. (We referred to Boeing 

Service Bulletin 737–53–1168, Revision 

3, dated November 28, 2006, as the 

appropriate source of service 

information for accomplishing the 

actions specified in paragraph (g) of the 

NPRM for Model 737–300 series 

airplanes.) 

We agree. We have reviewed the 

following service bulletins and have 

determined that these documents are 

also acceptable for terminating the 

inspections specified in paragraph (g) of 

this AD. Therefore, we have revised 

paragraph (j) of this AD to include these 

additional documents. Also, for easier 


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52396 Federal Register / Vol. 74, No. 196 / Tuesday, October 13, 2009 / Rules and Regulations 

readability, we have added a table in paragraph (j) of this AD to specify the 

acceptable service documents. 

TABLE—ACCEPTABLE SERVICE INFORMATION FOR OPTIONAL TERMINATING ACTION

Model Document 

Model 737–300 series airplanes.Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, dated March 16, 1995. 

Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, Revision 1, dated August 17, 

1995. 

Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, Revision 2, dated November 

27, 1996. 

Model 737–400 series airplanes.Part III of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1187, dated November 2, 1995. 

Part III of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1187, Revision 1, dated January 

16, 1997. 

Request To Publish Effectivity and 

Compliance Information 

The Aviation Group requests that 

paragraphs 1.E., ‘‘Compliance,’’ and 

1.A., ‘‘Effectivity,’’ of Boeing Service 

Bulletin 737–53–1168, Revision 3, dated 

November 28, 2006; and Boeing Service 

Bulletin 737–53–1187, Revision 2, dated 

May 9, 2007; be added to the NPRM, 

either within the body of the AD or as 

an incorporated attachment. The 

commenter asserts that many owners, 

lessors, or their respective 

representatives, are routinely denied 

access to the manufacturer’s Web site 

where the referenced service 

information is archived, making it very 

difficult or impossible to evaluate and 

schedule compliance with this AD. 

We do not agree to add the 

compliance and effectivity sections of 

Boeing Service Bulletin 737–53–1168, 

Revision 3, dated November 28, 2006; 

and Boeing Service Bulletin 737–53– 

1187, Revision 2, dated May 9, 2007; to 

this AD. Due to the length and 

complexity of the applicability and 

compliance times required in this AD, 

we referred directly to the service 

information to ensure the accuracy of 

those sections in this AD. We also gave 

notice for the compliance times in the 

‘‘Relevant Service Information’’ section 

of the NPRM. Operators should note 

that type certificate holders are required 

under the Federal Aviation Regulations 

to make available the service 

information necessary for 

accomplishing AD requirements to 

affected operators. All service 

information that we incorporate by 

reference in our AD is available to those 

who operate the product that is the 

subject of the AD. The necessary service 

information has also been incorporated 

by reference in this AD; therefore, this 

information is also available for review 

at the FAA or the Office of the Federal 

Register, as specified in the ADDRESSES

section and paragraph (n) of this AD. 

We have made no change to this AD in 

this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects about 

516 airplanes of U.S. registry. The 

following table provides the estimated 

costs for U.S. operators to comply with 

this AD. The average labor rate is $80 

per work hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection to determine inspection zones 1 .................................... $0 $80 ................................ 516 $41,280. 

Repetitive inspections—Option 1 ............ 64 .................................. 0 $5,120, per inspection 

cycle.

516 Up to $2,641,920. 

Repetitive inspections—Option 2 ............ 62 .................................. 0 $4,960, per inspection 

cycle.

516 Up to $2,559,360. 

Internal inspection ................................... 5, per inspection zone 

(3 zones).

0 $1,200 ........................... 516 $619,200. 

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 

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 


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Federal Register / Vol. 74, No. 196 / Tuesday, October 13, 2009 / Rules and Regulations 52397 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2009–21–01 Boeing: Amendment 39–16038. 

Docket No. FAA–2009–0429; Directorate 

Identifier 2007–NM–059–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 17, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

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

this AD, certificated in any category. 

(1) Boeing Model 737–300 series airplanes 

as identified in Boeing Service Bulletin 737– 

53–1168, Revision 3, dated November 28, 

2006. 

(2) Boeing Model 737–400 series airplanes 

as identified in Boeing Service Bulletin 737– 

53–1187, Revision 2, dated May 9, 2007. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracks 

in the aft fuselage skin on both sides of the 

airplane. We are issuing this AD to detect 

and correct cracking in the aft fuselage skin 

along the longitudinal edges of the bonded 

skin doubler, which could result in reduced 

structural integrity of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections, Related Investigative and 

Corrective Actions 

(g) At the applicable times specified in 

Tables 1 and 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1168, Revision 3, dated November 

28, 2006 (for Model 737–300 series 

airplanes); or Table 1 of paragraph 1.E., of 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007 (for Model 

737–400 series airplanes); except as provided 

by paragraph (k) of this AD: Do the 

applicable inspections and related 

investigative actions to detect cracks in the 

aft fuselage skin panels, by accomplishing all 

of the applicable actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1168, Revision 3, 

dated November 28, 2006; or Boeing Service 

Bulletin 737–53–1187, Revision 2, dated May 

9, 2007; as applicable; including Note (f) of 

Table 1 of paragraph 1.E. And, do the 

applicable corrective actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1168, Revision 3, 

dated November 28, 2006; or Boeing Service 

Bulletin 737–53–1187, Revision 2, dated May 

9, 2007; as applicable; except as provided by 

paragraphs (h), (i), and (l) of this AD. Repeat 

the applicable inspections and related 

investigative actions thereafter at the 

applicable intervals specified in Tables 1 and 

2 of paragraph 1.E. of Boeing Service Bulletin 

737–53–1168, Revision 3, dated November 

28, 2006; or Table 1 of paragraph 1.E. of 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007; as applicable. 

(h) If any crack is found during any 

inspection or corrective action required by 

this AD, before further flight, repair in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1168, Revision 3, dated November 28, 

2006 (for Model 737–300 series airplanes); or 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007 (for Model 

737–400 series airplanes); except, where 

Boeing Service Bulletin 737–53–1168, 

Revision 3, dated November 28, 2006; or 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007; as applicable; 

specifies to contact Boeing, before further 

flight, repair according to a method approved 

in accordance with the procedures specified 

in paragraph (m) of this AD. 

(i) If any cracking of a repaired area is 

found during any inspection required by this 

AD, and Boeing Service Bulletin 737–53– 

1168, Revision 3, dated November 28, 2006 

(for Model 737–300 series airplanes); or 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007 (for Model 

737–400 series airplanes); specifies 

contacting Boeing for appropriate action: 

Before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

Optional Terminating Action 

(j) Doing the skin panel replacement before 

the effective date of this AD, in accordance 

with the service information specified in 

Table 1 of this AD, as applicable, terminates 

the inspection requirements of paragraph (g) 

of this AD for that skin panel only. As of the 

effective date of this AD, doing the skin panel 

replacement, in accordance with Boeing 

Service Bulletin 737–53–1168, Revision 3, 

dated November 28, 2006; or Boeing Service 

Bulletin 737–53–1187, Revision 2, dated May 

9, 2007; as applicable; terminates the 

inspection requirements of paragraph (g) of 

this AD for that skin panel only. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR OPTIONAL TERMINATING ACTION

Model Document 

Model 737–300 series airplanes.Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, dated March 16, 1995. 

Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, Revision 1, dated August 17, 

1995. 

Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, Revision 2, dated November 

27, 1996. 

Part 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1168, Revision 3, dated November 

28, 2006. 

Model 737–400 series airplanes.Part III of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1187, dated November 2, 1995. 

Part III of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1187, Revision 1, dated January 

16, 1997. 


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52398 Federal Register / Vol. 74, No. 196 / Tuesday, October 13, 2009 / Rules and Regulations 

TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR OPTIONAL TERMINATING ACTION—Continued 

Model Document 

Part III of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1187, Revision 2, dated May 9, 

2007. 

Exception to Service Bulletins 

(k) Where Boeing Service Bulletin 737–53– 

1168, Revision 3, dated November 28, 2006 

(for Model 737–300 series airplanes); or 

Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007 (for Model 

737–400 series airplanes); specifies 

compliance times after the release date of 

those service bulletins, this AD requires that 

the specified actions be done within the 

specified compliance times after the effective 

date of this AD. 

No Reporting Required 

(l) Although Boeing Service Bulletin 737– 

53–1168, Revision 3, dated November 28, 

2006 (for Model 737–300 series airplanes); 

and Boeing Service Bulletin 737–53–1187, 

Revision 2, dated May 9, 2007 (for Model 

737–400 series airplanes); specify to submit 

information to the manufacturer, this AD 

does not include such a requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6447; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-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. 

Material Incorporated by Reference 

(n) You must use Boeing Service Bulletin 

737–53–1168, Revision 3, dated November 

28, 2006; or Boeing Service Bulletin 737–53– 

1187, Revision 2, dated May 9, 2007; as 

applicable; to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

do the optional terminating action specified 

in this AD, you must use the service 

information specified in Table 2 of this AD, 

as applicable, to do the optional terminating 

action, unless the AD specifies otherwise. 

TABLE 2—SERVICE INFORMATION FOR OPTIONAL TERMINATING ACTION

Boeing Service Bulletin— Revision— Dated— 

737–53–1168 ........................................................................ Original ................................................................................. March 16, 1995. 

737–53–1168 ........................................................................ 1 ........................................................................................... August 17, 1995. 

737–53–1168 ........................................................................ 2 ........................................................................................... November 27, 1996. 

737–53–1168 ........................................................................ 3 ........................................................................................... November 28, 2006. 

737–53–1187 ........................................................................ Original ................................................................................. November 2, 1995. 

737–53–1187 ........................................................................ 1 ........................................................................................... January 16, 1997. 

737–53–1187 ........................................................................ 2 ........................................................................................... May 9, 2007. 

(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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

September 25, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–23877 Filed 10–9–09; 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] 

Establishment of Class E Airspace; 

Chuathbaluk, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final Rule. 

SUMMARY: This action establishes Class 

E airspace at Chuathbaluk, AK to 

provide adequate controlled airspace to 

contain aircraft executing Standard 

Instrument Approach Procedures 

(SIAPs). One Standard Instrument 

Approach Procedure (SIAP) is being 

developed for the Chuathbaluk Airport 

at Chuathbaluk, AK. Also, this action 

makes a minor correction to the 

geographic coordinates and text 

description for the airport. This action 

establishes Class E airspace upward 

from 700 feet (ft.) above the surface at 

Chuathbaluk Airport, Chuathbaluk, AK. 

DATES: Effective Date: 0901 UTC, 

December 17, 2009. The Director of the 

Federal Register approves this 

incorporation by reference action under 

title 1, Code of Federal Regulations, part 

51, subject to the annual revision of 

FAA Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: Gary 

Rolf, AAL–538G, Federal Aviation 

Administration, 222 West 7th Avenue, 

Box 14, Anchorage, AK 99513–7587; 


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