64884 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin Revision level Date 

A330–57–3085 .................................................................................................................................... 02 ............................. September 29, 2005. 

A330–57–3087 .................................................................................................................................... Original .................... February 15, 2005. 

A330–57–3087 .................................................................................................................................... 01 ............................. September 22, 2005. 

A330–57–3088, including Appendix 01 .............................................................................................. Original .................... September 21, 2005. 

A340–57–4093 .................................................................................................................................... 02 ............................. September 29, 2005. 

A340–57–4095 .................................................................................................................................... Original .................... February 15, 2005. 

A340–57–4095 .................................................................................................................................... 01 ............................. September 22, 2005. 

A340–57–4096, including Appendix 01 .............................................................................................. Original .................... September 21, 2005. 

Issued in Renton, Washington, on October 

25, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E6–18471 Filed 11–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23921; Directorate 

Identifier 2005–NM–205–AD; Amendment 

39–14812; AD 2006–22–15] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 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 all Boeing Model 747 

series airplanes. That AD currently 

requires repetitive inspections for 

cracking of the top and side panel webs 

and panel stiffeners of the nose wheel 

well (NWW), and corrective actions if 

necessary. This new AD reduces the 

interval for certain repetitive 

inspections and removes a certain 

optional inspection. This new AD also 

requires replacing the NWW side and 

top panels with new panels, which 

terminates the repetitive inspections. 

This AD results from the development 

of a new modification. We are issuing 

this AD to prevent fatigue cracks in the 

top and side panel webs and stiffeners 

of the NWW, which could compromise 

the structural integrity of the NWW and 

could lead to the rapid decompression 

of the airplane. 

DATES: This AD becomes effective 

December 11, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 11, 2006. 

On May 10, 2005 (70 FR 21141, April 

25, 2005), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Alert Service 

Bulletin 747–53A2465, Revision 4, 

dated February 24, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Nick 

Kusz, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6432; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–09–02, amendment 

39–14070 (70 FR 21141, April 25, 2005). 

[A correction of that AD was published 

in the Federal Register on May 25, 2005 

(70 FR 29940).] The existing AD applies 

to all Boeing Model 747 series airplanes. 

That NPRM was published in the 

Federal Register on February 15, 2006 

(71 FR 7883). That NPRM proposed to 

continue to require repetitive 

inspections for cracking of the top and 

side panel webs and panel stiffeners of 

the nose wheel well (NWW), and 

corrective actions if necessary. That 

NPRM also proposed to reduce the 

interval for certain repetitive 

inspections and remove a certain 

optional inspection. That NPRM also 

proposed to require replacing the NWW 

side and top panels with new panels, 

which would terminate the repetitive 

inspections. 

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. 

Support for the NPRM 

Boeing, the airplane manufacturer, 

agrees with the contents of the NPRM. 

Request To Remove Actions for Group 

2 Airplanes or Extend Compliance 

Time 

The Air Transport Association (ATA), 

on behalf of one of its members, 

Northwest Airlines (NWA), requests that 

either the proposed requirement for 

terminating action for Group 2 airplanes 

be removed from the NPRM or the 

compliance time for doing the 

termination action be extended from 

four years to six years. The ATA notes 

that there are no service instructions for 

the terminating action for Group 2 

airplanes. The ATA also states that 

extending the compliance time will 

allow the development of the service 

instructions and an assessment of the 

requirement’s impact. NWA adds that it 

has not experienced extensive cracking 

that would warrant serious 

consideration or justification to mandate 

the terminating action (replacement of 

the NWW side and top panels). NWA 

also states that it would be very difficult 

to accomplish the replacement without 

a service bulletin. 

We agree with the commenter’s 

concern regarding lack of availability of 

service instructions for Group 2 

airplanes; however, we do not consider 

that removing the terminating action or 

delaying this action until after the 


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Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations 64885 

manufacturer develops a service 

bulletin for the replacement of the 

NWW side and top panels for Group 2 

airplanes is warranted. 

We have coordinated with Boeing 

regarding the availability of service 

instructions. Boeing states that it will 

issue a revised service bulletin that 

includes procedures for Group 2 

airplanes by July 2007 and that there 

will parts available at that time. 

Therefore, we have revised the 

compliance time for Group 2 airplanes 

to allow adequate time to accomplish 

the actions specified in this final rule. 

We have extended the compliance 

time specified in paragraph (o) of the 

final rule from 48 months to 57 months. 

We have determined that extending the 

compliance time will not adversely 

affect safety. In addition, under the 

provisions of paragraph (p) of the final 

rule, we may approve requests for 

adjustments to the compliance time if 

data are submitted to substantiate that 

such an adjustment would provide an 

acceptable level of safety. 

Explanation of Change Made to NPRM 

For clarification, the FAA has revised 

the definition of a ‘‘detailed inspection’’

in Note 1 of this final rule. 

Typographical Errors 

The date of Revision 4 of Boeing Alert 

Service Bulletin 747–53A2465 was 

inadvertently specified as ‘‘February 

25’’ instead of ‘‘February 24’’ in 

paragraph (f) and Table 1 of the NPRM. 

We have revised this final rule 

accordingly. 

The Federal Register number and 

date of the existing AD was 

inadvertently specified as ‘‘70 FR 29940, 

May 25, 2005’’ in paragraph 2. of the 

NPRM. The existing AD was published 

April 25, 2005 (70 FR 21141). A 

correction of the existing AD was 

published May 25, 2005 (70 FR 29940). 

We have revised this final rule 

accordingly. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

There are about 1,127 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. Work hours are 

estimated at an average labor rate of $65 

per work hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Area 1 and 3 inspections (required by AD 2005–09–02).79 $0 $5,135, per inspection cycle 255 $1,309,425, per inspection 

cycle. 

Area 2 inspections (required 

by AD 2005–09–02).

8–18 0 $520–$1,170, per inspection 

cycle.

255 Up to $298,350, per inspection cycle. 

Replacement (new action) ..... 800 115,765 $167,765 ............................... 255 $42,780,075. 

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 39–14070 (70 

FR 21141, April 25, 2005), corrected at 

70 FR 29940, May 25, 2005, and by 

adding the following new airworthiness 

directive (AD): 

2006–22–15 Boeing: Amendment 39–14812. 

Docket No. FAA–2006–23921; 

Directorate Identifier 2005–NM–205–AD. 

Effective Date 

(a) This AD becomes effective December 

11, 2006. 

Affected ADs 

(b) This AD supersedes AD 2005–09–02. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 747–

200B, 747–200C, 747–200F, 747–300, 747–

400, 747–400D, 747–400F, 747SR, and 747SP 

series airplanes, certificated in any category. 


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64886 Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations 

Unsafe Condition 

(d) This AD results from the development 

of a new modification. We are issuing this 

AD to prevent fatigue cracks in the top and 

side panel webs and stiffeners of the nose 

wheel well (NWW), which could 

compromise the structural integrity of the 

NWW and lead to the rapid decompression 

of the airplane. 

Compliance 

(e) 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 2005–

09–02 With New Repetitive Interval and 

Service Information 

Initial and Repetitive Inspections of the Top 

and Side Panel Stiffeners 

(f) Prior to the accumulation of 16,000 total 

flight cycles, or within 1,000 flight cycles 

after January 27, 2005 (the effective date of 

AD 2004–25–23, amendment 39–13911), 

whichever is later, do internal detailed and 

surface high frequency eddy current (HFEC) 

inspections of the top and side panel 

stiffeners of the NWW (specified as Area 3 in 

the service bulletin) for cracks in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin (ASB) 747–

53A2465, Revision 4, dated February 24, 

2005. Repeat the inspections thereafter at the 

compliance times specified in paragraph 

(f)(1) or (f)(2) of this AD, as applicable. 

(1) For airplanes on which an inspection 

has not been done before the effective date 

of this AD in accordance with any service 

bulletin listed in Table 1 of this AD: Within 

1,500 flight cycles after doing the inspection 

specified in paragraph (f) of this AD, repeat 

the inspection. Repeat the inspection 

thereafter at intervals not to exceed 1,500 

flight cycles. 

(2) For airplanes on which an inspection 

has been done before the effective date of this 

AD in accordance with any service bulletin 

listed in Table 1 of this AD: Within 6,000 

flight cycles after doing the inspection 

specified in paragraph (f) of this AD or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs first, 

repeat the inspection. Repeat the inspection 

thereafter at intervals not to exceed 1,500 

flight cycles. 

TABLE 1.—BOEING SERVICE BULLETINS

Service bulletin Revision level Date 

Boeing ASB 747–53A2465 ................................................................................................................. Original .................... April 5, 2001. 

Boeing ASB 747–53A2465 ................................................................................................................. 2 ............................... November 11, 2004. 

Boeing ASB 747–53A2465 ................................................................................................................. 3 ............................... December 23, 2004. 

Boeing ASB 747–53A2465 ................................................................................................................. 4 ............................... February 24, 2005. 

Boeing Service Bulletin 747–53A2465 ................................................................................................ 1 ............................... October 16, 2003. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Initial Inspections of the Top and Sidewall 

Panel Webs 

(g) Do an external detailed inspection of 

the top and sidewall panel webs of the NWW 

(specified as Area 1 and Area 2 in the service 

bulletin) for cracks, in accordance with the 

Accomplishment Instructions of Boeing ASB 

747–53A2465, Revision 4, dated February 24, 

2005, at the earlier of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) At the later of the times specified in 

paragraph (g)(1)(i) and (g)(1)(ii) of this AD: 

(i) Before accumulating 20,000 total flight 

cycles. 

(ii) Within 100 flight cycles or 90 days after 

May 10, 2005 (the effective date of AD 2005–

09–02), whichever occurs first. 

(2) At the later of the times specified in 

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

(i) Before accumulating 16,000 total flight 

cycles. 

(ii) Within 1,000 flight cycles after May 10, 

2005. 

Repetitive Inspections of the Top and 

Sidewall Panel Webs 

(h) Repeat the inspection required by 

paragraph (g) of this AD at the intervals 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, as applicable. 

(1) For airplanes with fewer than 20,000 

total flight cycles as of May 10, 2005, repeat 

at intervals not to exceed 1,000 flight cycles 

until the first inspection after the airplane 

reaches 20,000 total flight cycles. 

(2) For airplanes with 20,000 total flight 

cycles or more, repeat at intervals not to 

exceed 500 flight cycles. 

Ultrasonic (UT) Inspections 

(i) Do an UT inspection of the top and 

sidewall panel webs for cracks, in accordance 

with Boeing ASB 747–53A2465, Revision 4, 

dated February 24, 2005, at the later of the 

times specified in paragraphs (i)(1) and (i)(2) 

of this AD. Repeat the inspections thereafter 

at intervals not to exceed 500 flight cycles. 

(1) Prior to the accumulation of 20,000 

total flight cycles. 

(2) Within 100 flight cycles or 90 days after 

May 10, 2005, whichever occurs first. 

Additional Inspections and Corrective 

Actions 

(j) Except as specified in paragraph (l) of 

this AD, if any crack is found during any 

inspection required by this AD, prior to 

further flight, do any applicable additional 

detailed inspections of stiffeners and beams 

and make repairs, in accordance with the 

Accomplishment Instructions of Boeing ASB 

747–53A2465, Revision 4, dated February 24, 

2005. 

Actions Accomplished per Previous Issues of 

Service Bulletin 

(k) The actions specified in paragraphs 

(k)(1), (k)(2), and (k)(3) of this AD are 

acceptable for compliance with the 

corresponding action specified in the 

applicable paragraph. 

(1) Inspections and corrective actions 

accomplished before January 27, 2005, in 

accordance with Boeing ASB 747–53A2465, 

dated April 5, 2001, are considered 

acceptable for compliance with the 

corresponding inspections specified in 

paragraph (f) of this AD. 

(2) Inspections accomplished before the 

effective date of this AD, in accordance with 

Boeing Service Bulletin 747–53A2465, 

Revision 1, dated October 16, 2003; Boeing 

ASB 747–53A2465, Revision 2, dated 

November 11, 2004; and Boeing ASB 747–

53A2465, Revision 3, dated December 23, 

2004; are considered acceptable for 

compliance with the corresponding 

inspections specified in paragraph (f) of this 

AD. 

Note 2: The detailed and surface HFEC 

inspections of the top and side panel 

stiffeners of the NWW specified in Boeing 

ASB 747–53A2465, dated April 5, 2001; and 

Boeing Service Bulletin 747–53A2465, 

Revision 1, dated October 16, 2003; are 

acceptable for compliance with the internal 

detailed and surface HFEC inspections 

specified in paragraph (f) of this AD. 

(3) Inspections and corrective actions 

accomplished before May 10, 2005, in 

accordance with Boeing Service Bulletin 

747–53A2465, Revision 1, dated October 16, 

2003; Boeing ASB 747–53A2465, Revision 2, 

dated November 11, 2004; and Boeing ASB 

747–53A2465, Revision 3, dated December 

23, 2004; are considered acceptable for 

compliance with the corresponding 

inspections specified in paragraphs (g) and 

(h) of this AD. 

Certain Other Corrective Actions 

(l) Where Boeing Service Bulletin and ASB 

747–53A2465 specify contacting the 

manufacturer if certain cracking is found, 

this AD requires, before further flight, 


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Federal Register / Vol. 71, No. 214 / Monday, November 6, 2006 / Rules and Regulations 64887 

repairing the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

No Reporting Requirement 

(m) Although Boeing Service Bulletin and 

ASB 747–53A2465 specify that operators 

should report inspection results to the 

manufacturer, this AD does not require those 

inspection results to be reported. 

New Requirements of This AD 

Terminating Action 

(n) For Group 1 and 3 airplanes identified 

in Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005: Before 

accumulating 22,000 total flight cycles or 

within 48 months after the effective date of 

this AD, whichever occurs later, replace the 

NWW side and top panels with new panels 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747–

53A2562, Revision 1, dated July 28, 2005. 

Doing the replacement terminates the 

requirements of this AD. 

(o) For Group 2 airplanes identified in 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005, and Model 

747 airplanes not identified in the service 

bulletin: Before accumulating 22,000 total 

flight cycles or within 57 months after the 

effective date of this AD, whichever occurs 

later, replace the NWW side and top panels 

using a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA. Doing the replacement terminates the 

requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(p)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by 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. 

(4) AMOCs approved previously according 

to AD 2005–09–02 are approved as AMOCs 

for the corresponding provisions of 

paragraphs (f) through (j) and (l) of this AD. 

(5) AMOCs approved previously according 

to AD 2004–25–23 are approved as AMOCs 

for the corresponding provisions of 

paragraph (f) of this AD. 

Material Incorporated by Reference 

(q) You must use Boeing Alert Service 

Bulletin 747–53A2465, Revision 4, dated 

February 24, 2005; and Boeing Service 

Bulletin 747–53A2562, Revision 1, dated July 

28, 2005; as applicable, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005, in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On May 10, 2005 (70 FR 21141, April 

25, 2005), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–53A2465, 

Revision 4, dated February 24, 2005. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, WA 98124–2207, for 

a copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., Room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the 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 October 

25, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E6–18465 Filed 11–3–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2006–25501; Airspace 

Docket No. 06–ACE–9] 

Establishment of Class D Airspace; 

Ft. Riley, KS 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This notice amends Part 71 of 

the Federal Aviation Regulations (14 

CFR part 71) by establishing a Class D 

airspace area extending upward from 

the surface to and including 3,600 feet 

above sea level within a 3.7-mile radius 

of Fort Riley, Marshall Army Airfield, 

KS. The establishment of an air traffic 

control tower has made this action 

necessary. 

DATES: Effective Date: 0901 UTC, 

November 23, 2006. 

FOR FURTHER INFORMATION CONTACT: 

Grant Nichols, System Support, DOT 

Regional Headquarters Building, Federal 

Aviation Administration, 901 Locust, 

Kansas, City, MO 64106; telephone: 

(816) 329–2522. 

SUPPLEMENTARY INFORMATION: 

History 

On Friday, August 11, 2006, the FAA 

proposed to amend Part 71 of the 

Federal Aviation Regulations (14 CFR 

part 71) to establish Class D airspace at 

Ft. Riley, KS (71 FR 46130). The 

proposal was to establish a Class D 

airspace area to provide controlled 

airspace for flight operations due to the 

establishment of an air traffic control 

tower. Interested parties were invited to 

participate in this rulemaking 

proceeding by submitting written 

comments on the proposal to the FAA. 

A comment was received regarding the 

size of Class D airspace area. The size 

of the Class D airspace area is 

determined by FAA Order 7400.2F 

Procedures for Handling Airspace 

Matters, Chapter 17, Section 2. Class D 

Airspace Standards. 

The Rule 

This notice amends Part 71 of the 

Federal Aviation Regulations (14 CFR 

part 71) by establishing a Class D 

airspace area extending upward from 

the surface to and including 3,600 feet 

above sea level within a 3.7-mile radius 

of Fort Riley, Marshall Army Airfield, 

KS. The establishment of an air traffic 

control tower has made this action 

necessary. The intended effect of this 

action is to provide controlled airspace 

for flight operations at Fort Riley, 

Marshall Army Airfield, KS. The are 

will be depicted on appropriate 

aeronautical charts. 

Class D airspace areas extending 

upward from the surface of the earth are 

published in Paragraph 5000 of FAA 

Order 7400.9P, Airspace Designations 

and Reporting Points, dated September 

1, 2006, and effective September 16, 

2006, which is incorporated by 

reference in 14 CFR 71.1. of the same 

Order. The Class D airspace designation 

listed in this document will be 

published subsequently in the Order. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation—(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) 

does not warrant preparation of a 

Regulatory Evaluation as the anticipated 

impact is so minimal. Since this a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule, when 

promulgated, will not have a significant 

economic impact on a substantial 


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