37274 Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations

Inspection

(a) Perform a high frequency eddy current

(HFEC) inspection to detect fatigue cracks in

the frames and frame feet at fuselage frames

FR37 through FR41, adjacent to stringer 23,

at the time specified in paragraph (a)(1),

(a)(2), or (a)(3), as applicable; in accordance

with Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999.

(1) For Configuration 01 airplanes, as

identified in Airbus Service Bulletin A320–

53–1141: Within 3,500 flight cycles after the

effective date of this AD.

(2) For Configuration 02 airplanes, as

identified in Airbus Service Bulletin A320–

53–1141: Within 16,000 flight cycles after

accomplishment of Airbus Service Bulletin

A320–53–1025, Revision 1, dated November

24, 1994, or within 3,500 flight cycles after

the effective date of this AD, whichever

occurs later.

(3) For Configurations 03, 04, and 05

airplanes, as identified in Airbus Service

Bulletin A320–53–1141: Prior to the

accumulation of 20,000 total flight cycles, or

within 3,500 flight cycles after the effective

date of this AD, whichever occurs later.

Repetitive Inspections or Corrective

Action(s)

(b) For Configuration 01 airplanes: If no

crack is detected during the HFEC inspection

required by paragraph (a) of this AD,

accomplish the action specified in either

paragraph (b)(1) or (b)(2) of this AD.

(1) Repeat the HFEC inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 3,500 flight cycles

until accomplishment of paragraph (f) of this

AD. Or

(2) Prior to further flight, modify each

fastener hole of the outer frame flanges of left

and right fuselage frames FR37 through FR41,

adjacent to stringer 23, in accordance with

Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999. Within

16,000 flight cycles after accomplishment of

this modification, and thereafter at intervals

not to exceed 3,500 flight cycles, repeat the

HFEC inspection required by paragraph (a) of

this AD until accomplishment of paragraph

(f) of this AD.

Note 2: Airbus Service Bulletin A320–53–

1141, Revision 01, dated October 4, 1999,

references Airbus Service Bulletin A320–53–

1025, Revision 1, dated November 24, 1994,

as an additional source of information for

accomplishing the modification required by

paragraph (b)(2) of this AD.

Note 3: Accomplishment of the

modification in accordance with Airbus

Service Bulletin A320–53–1125, dated

August 5, 1994, prior to the effective date of

this AD, is considered acceptable for

compliance with the modification

requirements of paragraph (b)(2) of this AD.

(c) For Configurations 02, 03, 04, and 05

airplanes: If no crack is detected during the

inspection required by paragraph (a) of this

AD, repeat the HFEC inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 3,500 flight cycles

until accomplishment of paragraph (f) of this

AD.

(d) If any crack less than 0.20 inches (5.0

mm) in length is detected during any HFEC

inspection required by this AD, prior to

further flight, accomplish the actions

specified in either paragraph (d)(1) or (d)(2)

of this AD.

(1) Repair in accordance with Airbus

Service Bulletin A320–53–1141, Revision 01,

dated October 4, 1999. Repeat the HFEC

inspection required by paragraph (a) of this

AD thereafter at intervals not to exceed 3,500

flight cycles. Or

(2) Accomplish the actions specified in

paragraph (f) of this AD.

(e) If any crack is 0.20 inches (5.0 mm) or

greater in length, or if more than one crack

per frame side is detected during any HFEC

inspection required by this AD, prior to

further flight, simultaneously accomplish the

actions specified in paragraphs (e)(1) and

(e)(2) of this AD.

(1) Replace the frame segment and/or frame

foot with a new frame segment or frame foot

in accordance with Airbus Service Bulletin

A320–53–1141, Revision 01, dated October 4,

1999. And

(2) Accomplish the actions specified in

paragraph (f) of this AD.

Optional Terminating Action

(f) Modification of the frames and frame

feet area at fuselage frames FR37 through

FR41 (including the rotating probe eddy

current inspection to detect cracks, fastener

hole repair, installation of doublers on each

frame, cold working of specified fastener

holes, installation of new fasteners in the

cold-worked holes, and installation of new

modified system brackets), as applicable, in

accordance with Airbus Service Bulletin

A320–53–1128, Revision 01, including

Appendix 01, dated October 4, 1999,

constitutes terminating action for the

requirements of this AD.

Note 4: Accomplishment of the

modification in accordance with Airbus

Service Bulletin A320–53–1128, including

Appendix 01, dated October 3, 1997, prior to

the effective date of this AD, is considered

acceptable for compliance with the

modification requirements of paragraph (f) of

this AD.

Alternative Methods of Compliance

(g) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(h) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(i) The actions shall be done in accordance

with Airbus Service Bulletin A320–53–1141,

Revision 01, dated October 4, 1999. 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 Airbus

Industrie, 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 Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 6: The subject of this AD is addressed

in French airworthiness directive 98–509–

123(B), dated December 16, 1998.

(j) This amendment becomes effective on

July 19, 2000.

Issued in Renton, Washington, on June 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14791 Filed 6–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–06–AD; Amendment

39–11778; AD 2000–11–29]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 050, 100, 200, 300, 400,

500, 600, and 700 Series Airplanes; and

Model F28 Mark 0070, 0100, 1000, 2000,

3000, and 4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F27

Mark 050, 100, 200, 300, 400, 500, 600,

and 700 series airplanes, and Model F28

Mark 0070, 0100, 1000, 2000, 3000, and

4000 series airplanes, that requires a

one-time functional test to verify correct

installation of the shoulder harnesses of

the pilot’s and co-pilot’s seats and, if

necessary, replacement of the shoulder

harness assembly with a new or

serviceable shoulder harness assembly.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent failure of the

shoulder harness, which could result in

injury to the flight crew during

Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations 37275

extremely turbulent flight conditions or

during emergency landing or stopping

conditions.

DATES: Effective July 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 19,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., P.O. Box

231, 2150 AE Nieuw-Vennep, the

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Fokker

Model F27 Mark 050, 100, 200, 300,

400, 500, 600, and 700 series airplanes,

and Model F28 Mark 0070, 0100, 1000,

2000, 3000, and 4000 series airplanes

was published in the Federal Register

on February 17, 2000 (65 FR 8075). That

action proposed to require a one-time

functional test to verify correct

installation of the shoulder harnesses of

the pilot’s and co-pilot’s seats and

replacement of an incorrectly installed

shoulder harness assembly with a new

or serviceable shoulder harness

assembly.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

No Objection to the Proposal

One commenter, an operator, states

that it has already accomplished the

proposed testing, and therefore has no

comments regarding the proposed rule.

Request for Revision to Applicability

One commenter, an operator, requests

that the proposed AD be revised to limit

the applicability to shoulder harnesses

that have been repaired by agencies

other than the original equipment

manufacturer (OEM) of the harness. The

commenter states that the failure

described in the proposed AD was a

one-time, isolated occurrence, and that

the harness is used on multiple fleets,

all of which have been operating

without report from any operator of

such malfunctions. The commenter also

states that Pacific Scientific, the OEM,

has assured the commenter that all new

and repaired or remanufactured

harnesses cannot disengage from the

reel ‘‘without a catastrophic failure of

the webbing.’’ Since the commenter

receives all harnesses in sealed bags in

new condition, any tampering prior to

installation that could cause failure of

the harness would be detectable.

The FAA does not concur. The FAA

acknowledges that the investigations

that prompted the proposed AD

revealed improper repairs of the

shoulder harness assemblies

accomplished by a maintenance

company rather than the shoulder

harness OEM. Further discussions with

the Rijksluchtvaartdienst (RLD), which

is the airworthiness authority for the

Netherlands, have revealed that only

one maintenance company was

involved, and that the faulty shoulder

harnesses, of the 0108900 series, had

been installed only on Fokker Model

F27 and F28 series airplanes. However,

the RLD also advises that it was not

possible to trace all harness assemblies

that had been repaired in the past by the

maintenance company; therefore, it

cannot be determined with any certainty

how many other airplanes have these

faulty harness assemblies installed.

The FAA notes that even if it could

be determined definitively whether the

installed shoulder harnesses have ever

been repaired in the past by someone

other than the shoulder harness OEM,

which would require a review of

complete maintenance records for each

shoulder harness, such records may not

be available for airplanes transferred

from another operator. Additionally, the

FAA considers that the time required for

such a review would likely be greater

than that for the one-time functional test

of the harnesses specified in the

proposed AD. No change is made to the

final rule. However, under the

provisions of paragraph (b) of the AD,

the FAA may approve requests for an

alternative method of compliance if

substantiating data (such as verification

that the shoulder harness maintenance

records show that only OEM repairs

were made) are submitted to justify use

of that method.

Statement of Unsafe Condition

One commenter notes that the

statement of the unsafe condition in the

Summary, Discussion, and Compliance

sections of the proposed AD deviates

from the description provided in Dutch

airworthiness directive BLA 1999–

139(A), dated October 29, 1999. The

commenter suggests that the statement

should be revised as follows: ‘‘* * *

which could result in injury to the flight

crew during extremely turbulent flight

conditions or during emergency

landing/stop conditions.’’ The

commenter states that this wording

gives a better defined description of the

situations in which separation of the

shoulder harness from the seat could

occur.

The FAA acknowledges that the

wording suggested by the commenter

provides a slightly more precise

description of the unsafe condition

intended to be addressed by this AD.

The Discussion section of the AD is not

repeated in the final rule, but the FAA

has revised the Summary and

Compliance sections of the AD

accordingly.

Type Certificate Holder

The same commenter requests that the

Explanation of Relevant Service

Information section of the AD be revised

to refer to Fokker Services B.V., rather

than the now defunct airplane

manufacturer, as the current type

certificate holder. The commenter

advises that Fokker Services B.V is the

issuer of the relevant service

information. The FAA acknowledges the

accuracy of this information; however,

since this section is not repeated in the

final rule, no change is made to the AD.

Other Change to the AD

Since issuance of the proposed AD,

Fokker Services B.V. has issued Service

Bulletin SBF27/25–65, Revision 1, dated

March 1, 2000. The original issue of this

service bulletin, dated October 14, 1999,

is referenced in the proposed AD as the

appropriate source of service

information for Model F27 Mark 100,

200, 300, 400, 500, 600, and 700 series

airplanes. The procedures in Revision 1

are essentially the same as those in the

original, with certain information

contained in the maintenance manual

for accomplishment of the functional

test added to the service bulletin.

Paragraph (a)(2) of the AD has been

revised to reference Revision 1 of the

service bulletin, and a ‘‘NOTE’’ has been

added to the AD to give credit to

operators that may have accomplished

the required actions in accordance with

the original issue of the service bulletin.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

37276 Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 191 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required functional test, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $11,460, or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (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. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–11–29 Fokker Services B.V.:

Amendment 39–11778. Docket 2000–

NM–06–AD.

Applicability: Model F27 Mark 050, 100,

200, 300, 400, 500, 600, and 700 series

airplanes; and Model F28 Mark 0070, 0100,

1000, 2000, 3000, and 4000 series airplanes;

certificated in any category; on which any

Pacific Scientific Model 0108900 series flight

crew shoulder harness assembly is installed.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the shoulder harness,

which could result in injury to the flight

crew during extremely turbulent flight

conditions or during emergency landing or

stopping conditions, accomplish the

following:

Functional Test

(a) Within 6 months after the effective date

of this AD, perform a one-time functional test

to verify correct installation of the shoulder

harnesses of the pilot’s and co-pilot’s seats,

in accordance with paragraph (a)(1), (a)(2),

(a)(3), or (a)(4) of this AD, as applicable. If

any shoulder harness is incorrectly installed,

prior to further flight, replace the shoulder

harness assembly with a new or serviceable

shoulder harness assembly, in accordance

with paragraph (a)(1), (a)(2), (a)(3), or (a)(4)

of this AD, as applicable.

(1) For Model F27 Mark 050 series

airplanes: Accomplish the actions in

accordance with Fokker Service Bulletin

SBF50–25–051, dated October 14, 1999.

(2) For Model F27 Mark 100, 200, 300, 400,

500, 600, and 700 series airplanes:

Accomplish the actions in accordance with

Fokker Service Bulletin SBF27/25–65,

Revision 1, dated March 1, 2000.

(3) For Model F28 Mark 0070 and 0100

series airplanes: Accomplish the actions in

accordance with Fokker Service Bulletin

SBF100–25–088, dated October 14, 1999.

(4) For Model F28 Mark 1000, 2000, 3000,

and 4000 series airplanes: Accomplish the

actions in accordance with Fokker Service

Bulletin SBF28/25–103, dated October 14,

1999.

Note 2: Accomplishment of the actions in

accordance with Fokker Service Bulletin

SBF27/25–65, dated October 14, 1999, is

acceptable for compliance with the

requirements of paragraph (a)(2) of the AD.

Alternative Methods of Compliance

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International

Branch,ANM–116.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The actions shall be done in accordance

with Fokker Service Bulletin SBF50–25–051,

dated October 14, 1999; Fokker Service

Bulletin SBF27/25–65, Revision 1, dated

March 1, 2000; Fokker Service Bulletin

SBF100–25–088, dated October 14, 1999; or

Fokker Service Bulletin SBF28/25–103, dated

October 14, 1999; as applicable. Fokker

Service Bulletin SBF27/25–65, Revision 1,

dated March 1, 2000, contains the following

list of effective pages:

Page number

Revision level

shown on

page

Date shown

on page

1, 4–6 ........... 1 ................... March 1,

2000.

2–3 ............... Original ........ October 14,

1999.

Federal Register / Vol. 65, No. 115 / Wednesday, June 14, 2000 / Rules and Regulations 37277

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 Fokker Services B.V., P.O. Box 231,

2150 AE Nieuw-Vennep, the Netherlands.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 4: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1999–

139 (A), dated October 29, 1999.

(e) This amendment becomes effective on

July 19, 2000.

Issued in Renton, Washington, on June 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14792 Filed 6–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 99–AAL–18]

Revision of Class E Airspace;

Unalaska, AK; Correction

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule, correction.

SUMMARY: This action corrects the error

in the geographic description of a final

rule that was published in the Federal

Register on April 24, 2000 (65 FR

21644), Airspace Docket 99–AAL–18.

The final rule revised the class E

airspace at Unalaska, AK.

EFFECTIVE DATE: 0901 UTC, June 15,

2000.

FOR FURTHER INFORMATION CONTACT:

Robert Durand, Operations Branch,

AAL–531, Federal Aviation

Administration, 222 West 7th Avenue,

Box 14, Anchorage, AK 99513–7587;

telephone number (907) 271–5898; fax:

(907) 271–2850; email:

Bob.Durand@faa.gov. Internet address:

http://www.alaska.faa.gov/at.

SUPPLEMENTARY INFORMATION:

History

Federal Register Document 00–10015,

Airspace Docket 99–AAL–18, published

on April 24, 2000 (65 FR 21644), revised

the Class E airspace area at Unalaska,

AK. The coordinates for the Unalaska

Airport are in error. The coordinates for

the Unalaska Airport should read: lat.

53° 54′ 01′′ N., long. 166° 32′ 37′′ W.

This action corrects this error.

Correction to Final Rule

Accordingly, pursuant to the

authority delegated to me, the error for

the Class E airspace, Unalaska, AK, as

published in the Federal Register April

24, 2000 (FR Document 00–10015), is

corrected as follows:

1. On page 21645, Column 1, in the

airspace description for Unalaska

Airport, line 2, correct the coordinates

to read ‘‘[lat. 53° 54′ 01′′ N., long. 166°

32′ 37′′ W.]’’.

Issued in Anchorage, AK, on June 6, 2000.

Willis C. Nelson,

Manager, Air Traffic Division, Alaskan

Region.

[FR Doc. 00–14863 Filed 6–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 99–ASW–33]

Realignment of Jet Route; TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action realigns Jet Route

25 (J–25) in the vicinity of San Antonio,

TX. Specifically, this action realigns J–

25 between the Corpus Christi Very

High Frequency Omnidirectional Range/

Tactical Air Navigation (VORTAC) and

the San Antonio VORTAC. The FAA is

taking this action to enhance the

management of air traffic operations and

allow for better utilization of navigable

airspace in the San Antonio, TX, area.

Additionally, this action corrects the

legal description of J–25 by changing the

originating point of the jet route and an

incorrect radial.

EFFECTIVE DATE: 0901 UTC, August 10,

2000.

FOR FURTHER INFORMATION CONTACT: Bil

Nelson, Airspace and Rules Division,

ATA–400, Office of Air Traffic Airspace

Management, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone: (202) 267–8783.

SUPPLEMENTARY INFORMATION:

Background

As a result of a recent airspace review,

the FAA has determined that a segment

of J–25, between the Corpus Christi

VORTAC and the San Antonio

VORTAC, requires realignment to allow

for better utilization of the navigable

airspace in the San Antonio, TX, area.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments were received. Except for

editorial changes, and the correction to

the originating point of J–25 from

‘‘Matamoras, Mexico’’ to the ‘‘INT of the

United States/Mexican Border and

Brownsville, TX, 221° radial’’ and the

‘‘San Antonio, TX, 174° radials’’ to the

‘‘San Antonio, TX, 166° radials,’’ this

amendment is the same as that proposed

in the notice.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) realigns J–25 in the vicinity of

San Antonio, TX. This action realigns

the affected jet route between the

Corpus Christi VORTAC and the San

Antonio VORTAC. The FAA is taking

this action to enhance the management

of air traffic operations and allow for

better utilization of navigable airspace

in the San Antonio, TX, area.

Additionally, this action corrects the

legal description of J–25 by changing the

originating point of the jet route and an

incorrect radial.

Jet routes are published in Paragraph

2004 of FAA Order 7400.9G dated

September 1, 1999, and effective

September 16, 1999, which is

incorporated by reference in 14 CFR

71.1. The jet route 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. It, therefore (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under Department of

Transportation (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 is 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

number of small entities under the

criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).