Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68779

Incorporation by Reference 

(e) The actions shall be done in accordance 

with McDonnell Douglas Alert Service 

Bulletin MD80–24A105, Revision 02, dated 

January 24, 2000. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024). Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California; 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/code_of_

federal_regulations/ibr_locations.html.

Effective Date 

(f) This amendment becomes effective on 

January 3, 2005.

Issued in Renton, Washington, on 

November 10, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25786 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18593; Directorate 

Identifier 2004–NM–21–AD; Amendment 39–

13875; AD 2004–23–20] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A300 B2, A300 B4, A300 B4–600, and 

A300 B4–600R Series Airplanes; and 

Model A300 C4–605R Variant F and 

A300 F4–605R Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A300 

B4–601, A300 B4–603, A300 B4–620, 

A300 B4–605R, A300 B4–622R, and 

A300 F4–605R airplanes. That AD 

currently requires repetitive inspections 

for cracking in the area surrounding 

certain fuselage attachment holes, 

installation of new fasteners for certain 

airplanes, and certain follow-on 

corrective actions if necessary. This new 

AD requires modifying certain fuselage 

frames, which would terminate certain 

repetitive inspections. This AD also 

adds airplanes to the applicability. This 

AD is prompted by the development of 

a modification intended to prevent 

cracking of the center section of the 

fuselage, which could result in a 

ruptured frame foot and reduced 

structural integrity of the airplane.

DATES: This AD becomes effective 

January 3, 2005. 

The incorporation by reference of 

Airbus Service Bulletin A300–53–0271, 

Revision 03, dated June 13, 2003; and 

Airbus Service Bulletin A300–53–6125, 

Revision 01, dated June 13, 2003; as 

listed in the AD, is approved by the 

Director of the Federal Register as of 

January 3, 2005. 

On May 7, 2001 (66 FR 17490, April 

2, 2001), the Director of the Federal 

Register approved the incorporation by 

reference of Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000.

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. You can 

examine this information 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.

You can examine the contents of this 

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., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Dan Rodina, 

Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056; 

telephone (425) 227–2125; fax (425) 

227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can examine the 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 DOT street address stated in the 

ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

2001–06–10, amendment 39–12157 (66 

FR 17490, April 2, 2001). The existing 

AD applies to all Airbus Model A300 

B4–601, A300 B4–603, A300 B4–620, 

A300 B4–605R, A300 B4–622R, and 

A300 F4–605R airplanes. The proposed 

AD, published in the Federal Register

on July 16, 2004 (69 FR 42612), would 

require modifying certain fuselage 

frames, which would terminate certain 

repetitive inspections, and add 

airplanes to the applicability. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been submitted on the proposed AD. 

Request To Clarify Grace Period 

One commenter requests that we 

clarify the grace period specified in 

paragraph (i) of the proposed AD, 

specifically regarding the following 

sentence:

For airplanes that have exceeded the 

specified threshold, this AD requires 

compliance within the earlier of the 

flight-cycle and flight-hour grace 

periods specified in the service bulletin.

The commenter states that this 

language could be confusing. In Note 

(01), paragraph 1.E.(2)(b) 

(‘‘COMPLIANCE’’), of Airbus Service 

Bulletins A300–53–0271 and A300–53–

6125, the grace period is described in 

terms of flight hours and flight cycles 

only for airplanes that have exceeded 

their ‘‘design service goal’’ (DSG). For 

airplanes that have exceeded the 

‘‘threshold’’ but not their DSG, the 

service bulletins (in Note (02)) describe 

the grace period as the earlier of 

accomplishment of two service bulletins 

required by related AD 96–13–11, 

amendment 39–9679 (61 FR 35122, July 

5, 1996).

We partially agree. For airplanes 

above their DSG, NOTE (01) specifies 

the imprecise grace period ‘‘3,300FC/

3700FH for B2, 2900FC/3900FH for B4–

100 and 2,200FC/4500FH for B4–200.’’

We added the sentence quoted by the 

commenter only to specify that the grace 

period must be determined by the 

earlier of the flight-hour and flight-cycle 

values. While ‘‘design service goal’’

might have been more precise than 

‘‘threshold’’ in this context, we referred 

to these two terms collectively as ‘‘the 

specified threshold’’ to clarify the 

compliance-time conditions of the 

service bulletins. We have revised 

68780 Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 

paragraph (i) of this final rule to clarify 

the method for determining the 

appropriate grace period. 

Request To Add Service Bulletin 

Reference 

One commenter requests that we 

revise Table 1 of the proposed AD to 

add Airbus Service Bulletin A300–53–

6122. The commenter provides no 

further explanation. 

We find that clarification of Table 1 

is necessary. Table 1 identifies the 

service bulletin references for the 

requirements of paragraph (i) of this AD. 

Service Bulletin A300–53–6122 is the 

reference for the requirements of 

paragraphs (f) and (g) of this AD. That 

service bulletin does not provide 

information relevant to Table 1. We 

have not changed the final rule 

regarding this issue. 

Request To Approve Future Service 

Information 

One commenter requests that we 

revise the proposed AD to indicate that 

any approved revisions of the identified 

service bulletins are acceptable, as 

stated in the parallel French 

airworthiness directives F–224–001 and 

F–224–002, both dated January 7, 2004. 

We cannot accept as-yet unpublished 

service documents for compliance with 

the requirements of an AD. Referring to 

an unavailable service bulletin in an AD 

violates Office of the Federal Register 

regulations for approving materials that 

are incorporated by reference. We have 

not changed the final rule regarding this 

issue. However, under the provisions of 

paragraph (k)(1) of this final rule, 

affected operators may request approval 

to use a later revision of the referenced 

service bulletin as an alternative method 

of compliance (AMOC). 

Request To Clarify Repair Approval 

One commenter requests that we 

revise paragraphs (j) and (k) of the 

proposed AD to clarify the acceptability 

of DGAC-or Airbus-approved repairs. 

The commenter points out that such 

explicit approval would eliminate the 

processing time and work duplication 

for requests for AMOCs if an approval 

by DGAC or its agent is available. We 

infer that the commenter is requesting 

that paragraph (k) of this AD provide 

explicit approval of repairs done in 

accordance with a method approved by 

the DGAC, as specified in paragraph (j) 

of this AD. 

We do not agree. We cannot allow 

operators to contact the manufacturer 

for repair instructions; to do so would 

be delegating our rulemaking authority 

to the manufacturer. Furthermore, we 

do not agree that clarification is 

necessary regarding approvals for 

repairs specified in paragraph (j) of this 

AD, which specifically allows repair 

approval by the DGAC or its delegated 

agent. Concerning paragraph (k) of this 

AD, AMOCs must be approved by the 

FAA. 

Request To Approve Alternative 

Materials 

One commenter reports that the 

oversize fasteners (specified in Airbus 

Service Bulletins A300–53–0271 and 

A300–53–6125) may be difficult to 

obtain. The commenter therefore 

requests that we revise the proposed AD 

to approve use of the alternative 

substitute fasteners listed in the Airbus 

Structural Repair Manual (SRM) or the 

Airbus Process and Materials 

Specification Manual. 

We do not find it necessary to revise 

the AD regarding this issue. Because the 

service bulletins refer to the appropriate 

sections of the applicable Airbus SRM, 

the specific substitute parts listed in the 

SRM are considered acceptable for any 

repair or modification required by this 

AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, 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 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD:

ESTIMATED COSTS

Action Model Work 

hours 

Labor 

rate per 

hour 

Parts cost Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection ................. A300–600 6 $65 None required $390, per inspection ... 106 $41,340, per inspection. 

Modification ............... A300 90 65 2,000 .............. 7,850 ........................... 24 188,400. 

Modification ............... A300–600 56 65 4,000 .............. 7,640 ........................... 106 809,840. 

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. 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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68781

2004–23–20 Airbus: Amendment 39–13875. 

Docket No. FAA–2004–18593; 

Directorate Identifier 2004–NM–21–AD. 

Effective Date 

(a) This AD becomes effective January 3, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2001–06–10, 

amendment 39–12157. Paragraph (i) of this 

AD terminates certain requirements of AD 

96–13–11, amendment 39–9679. 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B2, A300 B4, A300 B4–600, and A300 

B4–600R series airplanes; and all Airbus 

Model A300 C4–605R Variant F and A300 

F4–605R airplanes; certificated in any 

category; except those airplanes modified by 

Airbus Modification 12168. 

Unsafe Condition 

(d) This AD was prompted by the 

development of a modification intended to 

prevent cracking of the center section of the 

fuselage, which could result in a ruptured 

frame foot and reduced structural integrity 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 Certain Requirements of AD 

2001–06–10

Inspections 

(f) For Model A300 B4–600 and A300 B4–

600R series airplanes, and Model A300 C4–

605R Variant F and A300 F4–605R airplanes: 

Perform a high-frequency eddy-current or 

rototest inspection to detect cracking in the 

area surrounding the frame feet attachment 

holes between fuselage frames (FR) 41 and 

FR46 from stringers 24 to 28, left- and righthand sides, in accordance with Airbus 

Service Bulletin A300–53–6122, dated 

February 9, 2000, at the time specified in 

paragraph (f)(1) or (f)(2), as applicable. 

(1) For airplanes on which Task 53–15–54 

in Maintenance Review Board Document 

(MRBD), Revision 3, dated April 1998, has 

not been accomplished as of May 7, 2001 (the 

effective date of AD 2001–06–10): Perform 

the inspection at the later of the times 

specified in paragraphs (f)(1)(i) and (f)(1)(ii) 

of this AD.

(i) Prior to the accumulation of the total 

flight-cycle or flight-hour threshold, 

whichever occurs first, specified in 

paragraph 1.E. (‘‘Compliance’’) of the service 

bulletin; or 

(ii) Within the applicable grace period 

specified in paragraph 1.E. (‘‘Compliance’’) of 

the service bulletin. 

(2) For airplanes on which Task 53–15–54 

in the MRBD, Revision 3, dated April 1998, 

has been accomplished as of May 7, 2001: 

Perform the next repetitive inspection at the 

later of the times specified in paragraphs 

(f)(2)(i) and (f)(2)(ii) of this AD. 

(i) Within the flight-cycle or flight-hour 

interval, whichever occurs first, specified in 

paragraph 1.E. (‘‘Compliance’’) of the service 

bulletin, following the latest inspection 

accomplished in accordance with the MRBD; 

or 

(ii) Within the grace period specified in 

paragraph 1.E. (‘‘Compliance’’) of the service 

bulletin. 

(g) For airplanes on which no cracking is 

detected during the inspection required by 

paragraph (f) of this AD, prior to further 

flight, install new fasteners as applicable, in 

accordance with Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000; and 

repeat the inspection required by paragraph 

(f) of this AD thereafter at intervals not to 

exceed the applicable intervals specified in 

paragraph 1.E. (‘‘Compliance’’) of the service 

bulletin, until the actions required by 

paragraph (i) of this AD have been done. 

Corrective Actions 

(h) For airplanes on which cracking is 

detected during any inspection required by 

paragraph (f) of this AD: Prior to further 

flight, except as required by paragraph (j) of 

this AD, accomplish corrective actions (e.g., 

performing rotating probe inspections, 

reaming out cracks, cold working fastener 

holes, and installing oversized fasteners) in 

accordance with Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000. 

Repeat the inspection required by paragraph 

(f) of this AD thereafter at intervals not to 

exceed the applicable intervals specified in 

paragraph 1.E. (‘‘Compliance’’) of the service 

bulletin, until the actions required by 

paragraph (i) of this AD have been done. 

New Requirements of This AD 

Modification: All Airplanes 

(i) For all airplanes: Within the compliance 

times specified in paragraph 1.E. of the 

applicable service bulletin listed in Table 1 

of this AD, modify the fuselage frames in 

accordance with the Accomplishment 

Instructions of the applicable service 

bulletin. For airplanes that have exceeded 

their design service goal, as specified in 

NOTE (01) of paragraph 1.E. of the service 

bulletin, this AD requires compliance within 

the earlier of the flight-cycle and flight-hour 

grace periods specified in the service 

bulletin.

TABLE 1.—SERVICE INFORMATION

Airplane model Airbus service bulletin Required revision level 

Revision level(s) also acceptable for 

compliance if done before the effective 

date of this AD 

A300 B2 and A300 B4 series airplanes A300–53–0271 Revision 03, dated June 13, 2003 ........ Original, dated September 10, 1991. 

Revision 01, dated February 16, 1993. 

Revision 02, dated July 13, 2000. 

A300 B4–600 and A300 B4–600R series airplanes, and A300 C4–605 Variant F and A300 F4–605R airplanes.A300–53–6125 Revision 01, dated June 13, 2003 ........ Original, dated November 8, 2000. 

(1) For the affected Model A300 B4–600 

series airplanes: Accomplishment of the 

modification terminates the requirements of 

this AD.

(2) For Model A300 B2 and A300 B4 series 

airplanes: Accomplishment of the 

modification terminates certain repetitive 

inspections required by AD 96–13–11, i.e., 

inspections of the frame feet holes for frames 

41 to 46 (as specified in Airbus Service 

Bulletin A300–53–0345) and frames 48 to 54 

(as specified in Airbus Service Bulletin 

A300–53–238). However, the repetitive 

inspections of the frame foot angle radius (as 

specified in Service Bulletin A300–53–238), 

which are required by AD 96–13–11, must 

continue. 

Exceptions to Service Bulletin Procedures 

(j) During any inspection required by this 

AD, if the applicable service bulletin 

specifies to contact the manufacturer for 

appropriate instructions: Before further 

flight, perform applicable corrective action in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Direction Generale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

Alternative Methods of Compliance 

(k)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

alternative methods of compliance (AMOCs) 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) AMOCs approved previously in 

accordance with AD 2001–06–10, 

amendment 39–12157, are approved as 

AMOCs with the corresponding requirements 

of this AD. 

Related Information 

(l) French airworthiness directives F–

2004–001 and F–2004–002, both dated 

January 7, 2004, also address the subject of 

this AD. 

Material Incorporated by Reference 

(m) Unless the AD specifies otherwise, you 

must use the service information that is

68782 Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 

specified in Table 2 of this AD to perform the actions that are required by this AD, as 

applicable.

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision level Date 

Airbus Service Bulletin A300–53–0271 .................................................................................. 03 ................................... June 13, 2003. 

Airbus Service Bulletin A300–53–6122 .................................................................................. Original ........................... February 9, 2000. 

Airbus Service Bulletin A300–53–6125 .................................................................................. 01 ................................... June 13, 2003. 

(1) The incorporation by reference of 

Airbus Service Bulletin A300–53–0271, 

Revision 03, dated June 13, 2003; and Airbus 

Service Bulletin A300–53–6125, Revision 01, 

dated June 13, 2003; is approved by the 

Director of the Federal Register in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) On May 7, 2001 (66 FR 17490, April 2, 

2001), the Director of the Federal Register 

approved the incorporation by reference of 

Airbus Service Bulletin A300–53–6122, 

dated February 9, 2000. 

(3) For copies of the service information, 

contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; 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/

code_of_federal_regulations/

ibr_locations.html.

Issued in Renton, Washington, on 

November 10, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25785 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–18824; Airspace 

Docket No. 04–ACE–50] 

Modification of Class D Airspace; and 

Modification of Class E Airspace; 

Joplin, MO

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Direct final rule; confirmation of 

effective date. 

SUMMARY: This document confirms the 

effective date of the direct final rule 

which revises Class D and Class E 

airspace at Joplin, MO.

EFFECTIVE DATE: 0901 UTC, January 20, 

2005.

FOR FURTHER INFORMATION CONTACT:

Brenda Mumper, Air Traffic Division, 

Airspace Branch, ACE–520A, DOT 

Regional Headquarters Building, Federal 

Aviation Administration, 901 Locust, 

Kansas City, MO 64106; telephone: 

(816) 329–2524.

SUPPLEMENTARY INFORMATION: The FAA 

published this direct final rule with a 

request for comments in the Federal 

Register on September 29, 2004 (69 FR 

58047). The FAA uses the direct final 

rulemaking procedure for a noncontroversial rule where the FAA 

believes that there will be no adverse 

public comment. This direct final rule 

advised the public that no adverse 

comments were anticipated, and that 

unless a written adverse comment, or a 

written notice of intent to submit such 

an adverse comment, were received 

within the comment period, the 

regulation would become effective on 

January 20, 2005. No adverse comments 

were received, and thus this notice 

confirms that this direct final rule will 

become effective on that date.

Issued in Kansas City, MO on November 8, 

2004. 

Anthony D. Roetzel, 

Acting Area Director, Western Flight Services 

Operations.

[FR Doc. 04–26101 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–18820; Airspace 

Docket No. 04–ACE–46] 

Modification of Class E Airspace; 

Kennett, MO

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Direct final rule; request for 

comments; correction. 

SUMMARY: This action corrects a direct 

final rule; request for comments that 

was published in the Federal Register

on Tuesday, September 28, 2004, (69 FR 

57839) [FR Doc. 04–21736]. It corrects 

an error in the legal description of the 

Class E airspace area extending upward 

from 700 feet above the surface at 

Kennett, MO.

DATES: This direct final rule is effective 

on 0901 UTC, January 20, 2005.

FOR FURTHER INFORMATION CONTACT:

Brenda Mumper, Air Traffic Division, 

Airspace Branch, ACE–520A, DOT 

Regional Headquarters Building, Federal 

Aviation Administration, 901 Locust, 

Kansas City, MO 64106; telephone: 

(816) 329–2524.

SUPPLEMENTARY INFORMATION:

History 

Federal Register Document 04–21736, 

published on Tuesday, September 28, 

2004, (69 FR 57839) modified the Class 

E airspace area extending upward from 

700 feet above the surface at Kennett, 

MO. The modification expanded the 

airspace area to protect for diverse 

departures, redefined the extension to 

the Class E airspace area in terms of the 

003° bearing from the Kennett 

nondirectional radio beacon (NDB), 

decreased the length and width of the 

extension, corrected the location of the 

NDB in the legal description and 

corrected the Kennett Memorial Airport 

reference point (ARP) used in the legal 

description. However, publication of a 

revised Kennett Memorial Airport ARP 

in the National Flight Data Digest on 

November 8, 2004, requires a further 

revision to the Kennett, MO Class E 

airspace areas.

■ Accordingly, pursuant to the authority 

delegated to me, the legal description of 

the Class E airspace area extending 

upward from 700 feet above the surface 

at Kennett, MO, as published in the 

Federal Register on Tuesday, September 

28, 2004, (69 FR 57839) [FR Doc. 04–

21736] is corrected as follows:

§ 71.1 [Corrected]

■ On page 57840, Column 2, last 

paragraph, third line, change ‘‘(Lat. 

36°13′49′′ N., long. 90°02′04′′ W.)’’ to 

read: ‘‘(Lat. 36°13′33′′ N., long. 90°02′12′′

W.)’’