27424 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

(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 Hawker Beechcraft 

Corporation, 9709 East Central, Wichita, 

Kansas 67201; telephone: (316) 676–5034; 

fax: (316) 676–6614; Internet: https:// 

www.hawkerbeechcraft.com/service_support/ 

pubs/. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on April 

30, 2010. 

Steven W. Thompson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–10717 Filed 5–14–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1066; Directorate 

Identifier 2009–NM–028–AD; Amendment 

39–16284; AD 2010–10–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–300, 

747SR, and 747SP Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747 

airplanes. That AD currently requires 

repetitive inspections to detect cracking 

in certain fuselage skin lap joints, and 

repair if necessary. This new AD 

expands the inspection area in the 

existing AD, adds a modification of 

certain lap joints, and adds certain postrepair inspections of the lap joints. 

Accomplishing the modification ends 

the repetitive inspections required by 

the existing AD for the length of lap 

joint that is modified. This AD results 

from a structural review of affected skin 

lap joints for widespread fatigue 

damage. We are issuing this AD to 

prevent fatigue cracking in certain lap 

joints, which could result in rapid 

depressurization of the airplane. 

DATES: This AD becomes effective June 

21, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 21, 2010. 

On July 13, 1994 (59 FR 30277, June 

13, 1994), the Director of the Federal 

Register approved the incorporation by 

reference of certain other publications 

listed in the AD. 

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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 94–12–04, Amendment 

39–8932 (59 FR 30277, June 13, 1994). 

The existing AD applies to certain 

Model 747 airplanes. That NPRM was 

published in the Federal Register on 

November 18, 2009 (74 FR 59488). That 

NPRM proposed to continue to require 

repetitive inspections to detect cracking 

in certain fuselage skin lap joints, and 

repair if necessary. That NPRM also 

proposed to expand the inspection area 

in the existing AD, add a modification 

of certain lap joints, and add certain 

post-repair inspections of the lap joints. 

That NPRM specified that 

accomplishing the modification would 

end the repetitive inspections required 

by the existing AD for the length of lap 

joint that is modified. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request for Certain Clarifications 

Boeing asks that we provide the 

following clarifications: 

• Include language in paragraph (c) of 

the NPRM which specifies that 

airplanes having line number 629, 635, 

637, 650, 666, 667, 673, 675, 683, 713, 

750, or 810 are Group 5 airplanes. 

Boeing states that after Boeing Service 

Bulletin 747–53A2367, Revision 3, 

dated January 15, 2009, was released, it 

was determined that these airplanes do 

not have a lower lobe air stair door and 

should have been included in Group 5, 

not Group 10. 

We agree with Boeing’s request for the 

reason provided. The airplane grouping 

is incorrect in Boeing Alert Service 

Bulletin 747–53A2367, Revision 2, 

dated October 30, 2008, and Boeing 

Service Bulletin 747–53A2367, Revision 

3, dated January 15, 2009. Therefore, we 

have added a new Note 1 after 

paragraph (c) of this AD to clarify the 

correct airplane grouping for airplanes 

having the identified line numbers. 

• Change the term ‘‘Delegation Option 

Authorization’’ (DOA) to ‘‘Organization 

Designation Authorization’’ (ODA) 

throughout the NPRM. 

We agree. Boeing Commercial 

Airplanes has received an Organization 

Designation Authorization (ODA), 

which replaces the previous designation 

as a Delegation Option Authorization 

(DOA) holder. We have changed 

paragraph (m)(3) of this AD to add 

delegation of authority to Boeing 

Commercial Airplanes ODA to approve 

an alternative method of compliance for 

any repair required by this AD. 

• Change the Discussion section of 

the NPRM to note that AD 2009–04–16, 

Amendment 39–15822 (74 FR 8737, 

February 26, 2009), supersedes AD 

2008–10–15, Amendment 39–15522 (73 

FR 29042, May 20, 2008). Although we 

agree that AD 2009–04–16 superseded 

AD 2008–10–15, the discussion section 

of the NPRM is not carried over to this 

final rule. Therefore, we have made no 

change to the AD in this regard. 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27425 

• Change the terminating action 

language specified in paragraph (j) of 

the NPRM to add the following at the 

end of the last sentence in that 

paragraph: ‘‘* * * for a period of 15,000 

flight cycles. Additional work is 

required for continued operation 

beyond 15,000 flight-cycles after the 

modification.’’ Boeing states that a postmodification inspection is specified in a 

note following Table 2 of paragraph 1.E. 

of Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 

2009. 

We do not agree with Boeing’s 

request. The note following Table 2 of 

paragraph 1.E. of the service bulletin 

specifies that additional work is 

required for continued operation 

beyond 15,000 flight cycles after the 

modification, and that Boeing must be 

contacted for instructions. Considering 

the compliance time of 30,000 total 

flight cycles for the modification, and 

the compliance time for additional 

work, we have determined that 

rulemaking on the undefined additional 

work is not necessary at this time. We 

will consider future rulemaking once 

the additional work is defined. We have 

made no change to the AD in this 

regard. 

• Add a new paragraph (j)(1) to the 

NPRM to state that at all lap joint areas 

not covered by the modification 

required by paragraph (j) of this AD, a 

lap joint modification must be installed 

at 35,000 total flight cycles. Boeing 

states that the NPRM should reflect the 

structural modification point (SMP) for 

all lap splices not modified by Boeing 

Service Bulletin 747–53A2367, Revision 

3, dated January 15, 2009, as stated on 

page 26, section 1.D., Note 7, of that 

service bulletin. 

We do not agree with Boeing’s 

request. Notes in the Description section 

of a service bulletin are considered 

informational only. In addition, the 

subject note specifies modification of all 

lap joints not covered by the 

modification specified in Boeing Service 

Bulletin 747–53A2367. The compliance 

time specified in that note in Boeing 

Service Bulletin 747–53A2367, Revision 

3, dated January 15, 2009, is 35,000 total 

flight cycles, and Boeing is not planning 

to provide engineering drawings for that 

modification. Modification of those lap 

joints is not included in this AD. We 

will consider future rulemaking when 

modification procedures are available. 

We have made no change to the AD in 

this regard. 

Explanation of Change Made to This 

AD 

We have changed this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

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. 

Explanation of Change to Costs of 

Compliance 

After the NPRM was issued, we 

reviewed the figures we have used over 

the past several years to calculate AD 

costs to operators. To account for 

various inflationary costs in the airline 

industry, we find it necessary to 

increase the labor rate used in these 

calculations from $80 per work hour to 

$85 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly rate. 

Costs of Compliance 

There are 209 airplanes of the affected 

design in the worldwide fleet. This AD 

affects about 69 airplanes of U.S. 

registry. 

The actions that are required by AD 

94–12–04 and retained in this AD take 

about 14 work hours per airplane, at an 

average labor rate of $85 per work hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$1,190 per airplane, per inspection 

cycle. 

The new Area 2 inspections take up 

to 477 work hours per airplane, 

depending on airplane configuration, at 

an average labor rate of $85 per work 

hour. Based on these figures, the 

estimated cost of the new inspections 

specified in this AD for U.S. operators 

is up to $2,797,605, or up to $40,545 per 

airplane, per inspection cycle. 

The new modification takes about 171 

work hours per airplane, at an average 

labor rate of $85 per work hour. 

Required parts cost per airplane will be 

minimal. Based on these figures, the 

estimated cost of the new actions 

specified in this AD for U.S. operators 

is $1,002,915, or $14,535, per airplane. 

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 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. 

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 removing Amendment 39–8932 (59 

FR 30277, June 13, 1994) and by adding 

the following new airworthiness 

directive (AD): 


srobinson on DSKHWCL6B1PROD with RULES
27426 Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 

2010–10–05 The Boeing Company: 

Amendment 39–16284. Docket No. 

FAA–2009–1066; Directorate Identifier 

2009–NM–028–AD. 

Effective Date 

(a) This AD becomes effective June 21, 

2010. 

Affected AD 

(b) This AD supersedes AD 94–12–04, 

Amendment 39–8932. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–300, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Service 

Bulletin 747–53A2367, Revision 3, dated 

January 15, 2009. 

Note 1: Airplanes having line number 629, 

635, 637, 650, 666, 667, 673, 675, 683, 713, 

750, or 810 are Group 5 airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a structural review 

of affected skin lap joints for widespread 

fatigue damage. The Federal Aviation 

Administration is issuing this AD to prevent 

fatigue cracking in certain lap joints, which 

could result in rapid depressurization 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. 

Restatement of Requirements of AD 94–12– 

04, With Revised Service Information 

Repetitive Inspections 

(g) For airplanes identified in Boeing 

Service Bulletin 747–53–2367, dated 

December 18, 1991: Prior to the accumulation 

of 22,000 full pressure flight cycles (or, if the 

external skin panel of an affected lap joint 

has been replaced, prior to the accumulation 

of 22,000 full pressure flight cycles since skin 

replacement), or within 1,000 landings after 

July 13, 1994 (the effective date of AD 94– 

12–04), whichever occurs later, perform an 

external surface high frequency eddy current 

(HFEC) inspection of the skin around the 

upper row of fasteners, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–53–2367, dated 

December 18, 1991; Boeing Service Bulletin 

747–53–2367, Revision 1, dated January 27, 

1994; Boeing Alert Service Bulletin 747– 

53A2367, Revision 2, dated October 30, 2008; 

or Boeing Service Bulletin 747–53A2367, 

Revision 3, dated January 15, 2009. As of the 

effective date of this AD, only Revision 3 may 

be used. 

(1) If no crack is found, repeat the 

inspection thereafter at intervals not to 

exceed 3,000 full pressure flight cycles until 

the inspections required by paragraph (h) of 

this AD are done. 

(2) If any crack is found, accomplish 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Prior to further flight, perform an open 

hole HFEC inspection to detect cracking in 

the upper row fastener holes between the 

adjacent frames, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53–2367, dated 

December 18, 1991; Boeing Service Bulletin 

747–53–2367, Revision 1, dated January 27, 

1994; Boeing Alert Service Bulletin 747– 

53A2367, Revision 2, dated October 30, 2008; 

or Boeing Service Bulletin 747–53A2367, 

Revision 3, dated January 15, 2009. Prior to 

further flight, repair any crack found, in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. 

Note 2: Guidance on repairing cracking can 

be found in Chapter 53–30–03 of the Boeing 

747 Structural Repair Manual. 

(ii) Repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 3,000 full pressure 

flight cycles until the inspections required by 

paragraph (h) of this AD are done. 

New Requirements of This AD 

Repetitive Inspections/Investigative and 

Corrective Actions 

(h) For all airplanes: Do initial and 

repetitive HFEC inspections for cracks of lap 

joints in Sections 41, 42, 44, and 46, by doing 

all the actions, including all applicable 

related investigative and corrective actions, 

specified in the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 2009, 

except as provided by paragraph (l) of this 

AD. Do the inspections at the applicable 

times specified in paragraph 1.E. of Boeing 

Service Bulletin 747–53A2367, Revision 3, 

dated January 15, 2009, except as required by 

paragraph (k) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. Accomplishing the 

inspections required by this paragraph ends 

the repetitive inspections required by 

paragraph (g) of this AD. Do the actions 

required by paragraph (h) of this AD until the 

modification required by paragraph (j) of this 

AD is done. 

(i) For areas on which a lap joint repair was 

installed and the repair doubler is greater 

than or equal to 40 inches long: Do initial 

and repetitive internal HFEC inspections for 

cracks, as required by paragraph (h) of this 

AD, by doing all the applicable actions, 

including applicable corrective actions, 

specified in the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 2009, 

except as provided by paragraph (l) of this 

AD. Do the inspection and corrective actions 

at the times specified in paragraph 1.E. of 

Boeing Service Bulletin 747–53A2367, 

Revision 3, dated January 15, 2009, except as 

required by paragraph (k) of this AD. 

Terminating Action 

(j) Before the accumulation of 30,000 total 

flight cycles or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later: Modify the applicable lap joints 

in Sections 41 and 42 by doing all the actions 

specified in the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 2009, 

except as required by paragraph (l) of this 

AD. Accomplishing this modification 

terminates the repetitive inspection 

requirements of this AD for the length of lap 

joint that is modified. 

Exceptions to Boeing Service Bulletin 747– 

53A2367, Revision 3, Dated January 15, 2009 

(k) Where Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 2009, 

specifies compliance times ‘‘from the date on 

the original issue of this service bulletin [12/ 

18/91],’’ this AD requires compliance within 

the specified compliance time after July 13, 

1994 (the effective date of AD 94–12–04). 

Where Boeing Service Bulletin 747–53A2367, 

Revision 3, dated January 15, 2009, specifies 

compliance times ‘‘after the date on Revision 

2 of this service bulletin [10/30/08],’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(l) Where Boeing Service Bulletin 747– 

53A2367, Revision 3, dated January 15, 2009, 

specifies to contact Boeing for repair or 

modification instructions: Before further 

flight, repair or modify using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle ACO, 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, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; 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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 94–12–04 are approved 

as alternative methods of compliance with 

the corresponding requirements of this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

specified in Table 1 of this AD, as applicable, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 


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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations 27427 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Alert Service Bulletin 747–53A2367 ................................................................................... 2 ................................ October 30, 2008. 

Boeing Service Bulletin 747–53–2367 ............................................................................................ Original ...................... December 18, 1991. 

Boeing Service Bulletin 747–53–2367 ............................................................................................ 1 ................................ January 27, 1994. 

Boeing Service Bulletin 747–53A2367 ............................................................................................ 3 ................................ January 15, 2009. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the Boeing service information specified in 

Table 2 of this AD under 5 U.S.C. 552(a) and 

1 CFR part 51. 

TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Alert Service Bulletin 747–53A2367 ................................................................................................... 2 October 30, 2008. 

Boeing Service Bulletin 747–53A2367 ............................................................................................................ 3 January 15, 2009. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the Boeing service information 

contained in Table 3 of this AD on July 13, 

1994 (59 FR 30277, June 13, 1994). 

TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Service Bulletin 747–53–2367 ............................................................................................ Original ...................... December 18, 1991. 

Boeing Service Bulletin 747–53–2367 ............................................................................................ 1 ................................ January 27, 1994. 

(3) 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. 

(4) 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. 

(5) 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 April 27, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–10875 Filed 5–14–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0007; Airspace 

Docket No. 09–AAL–20] 

Amendment of Jet Route J–120; 

Alaska 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Jet Route 

J–120, in Alaska. The FAA is taking this 

action in preparation of the eventual 

decommissioning of the Barter Island 

(BTI) Non-directional Beacon (NDB) at 

the Village of Kaktovik, Alaska. This 

action ensures the safe and efficient use 

of the airspace within the National 

Airspace System (NAS). 

DATES: Effective date 0901 UTC, July 29, 

2010. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: Ken 

McElroy, Airspace and Rules Group, 

Office of System Operations Airspace 

and AIM, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On February 9, 2010, the FAA 

published in the Federal Register a 

notice of proposed rulemaking to amend 

Jet Route J–120, in Alaska (75 FR 6320). 

The Barter Island NDB is scheduled for 

decommissioning, and will make the 

northern end (from Fort Yukon 

VORTAC to BTI) of this route unusable. 

Two Area Navigation T Routes (T–228, 

T–273) have been added to the NAS to 

service the Barter Island area. Interested 

parties were invited to participate in 

this rulemaking proceeding by 

submitting written comments on the 

proposal. No comments were received. 

The amendment is adopted as proposed. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

amending Jet Route J–120, Alaska. The 

segment from the Fort Yukon VORTAC 

to the BTI NDB will be removed due to 

decommissioning of the BTI NDB. 

Jet routes are published in paragraph 

2004 of FAA Order 7400.9T signed 

August 27, 2009, and effective 

September 15, 2009, which is 

incorporated by reference in 14 CFR 

71.1. The Jet route listed in this 


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