Federal Register / Vol. 66, No. 36 / Thursday, February 22, 2001 / Rules and Regulations 11105

Repetitive Inspections

(c) Repeat the detailed visual inspection

specified in paragraph (a) of this AD, at

intervals not to exceed 400 flight hours.

Terminating Action

(d) Within 2,000 flight hours from the

effective date of this AD, accomplish Part II,

III, or IV, as applicable, of the service

bulletin.

Alternative Methods of Compliance

(e) 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, Atlanta

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(f) 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

(g) The actions shall be done in accordance

with EMBRAER Service Bulletin 145–55–

0009, Change No. 02, dated May 19, 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 Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Boulevard, suite 450, Atlanta,

Georgia; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: A portion of the subject of this AD

is addressed in Brazilian airworthiness

directive No. 98–05–02, dated May 28, 1998.

Effective Date

(h) This amendment becomes effective on

March 29, 2001.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3849 Filed 2–21–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–142–AD; Amendment

39–12112; AD 2001–03–08]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Bombardier Model

CL–600–2B19 series airplanes, that

currently requires, among other actions,

certain revisions to the Airplane Flight

Manual; and removal of all elevator

flutter dampers. That AD also requires

installation of new elevator flutter

dampers, and replacement of shear pins

and shear links with new improved

shear pins and shear links. This

amendment adds airplanes to the

applicability of the existing AD; and

requires replacing certain shear pins

with new, improved shear pins; and, for

certain airplanes, inspection of the

maintenance records to determine

replacement status of the shear pins;

and corrective actions, if necessary. 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 premature failure of the shear

pins of the elevator damper, which may

increase the likelihood of jamming or

restricting movement of the elevator and

the resultant adverse effect on

controllability of the airplane.

DATES: Effective March 29, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of March 29,

2001.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of April 3, 1998 (63 FR 9928,

February 27, 1998).

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087 Station

Centre-ville, Montreal, Quebec H3C

3G9, Canada. 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 FAA, New York

Aircraft Certification Office, 10 Fifth

Street, Third Floor, Valley Stream, New

York; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

ANE–171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7512; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–04–45,

amendment 39–10356 (63 FR 9928,

February 27, 1998), which is applicable

to certain Bombardier Model CL–600–

2B19 series airplanes, was published in

the Federal Register on October 31,

2000 (65 FR 64898). The action

proposed to continue to require, among

other actions, certain revisions to the

Airplane Flight Manual (AFM); and

removal of all elevator flutter dampers.

The action also proposed to continue to

require installation of new elevator

flutter dampers, and replacement of

shear pins and shear links with new

improved shear pins and shear links.

The action also proposed to add

airplanes to the applicability of the

existing AD; and to require replacing

certain shear pins with new, improved

shear pins; and, for certain airplanes,

inspection of the maintenance records

to determine replacement status of the

shear pins; and corrective actions, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 214

Bombardier Model CL–600–2B19 series

11106 Federal Register / Vol. 66, No. 36 / Thursday, February 22, 2001 / Rules and Regulations

airplanes of U.S. registry that will be

affected by this AD.

The removal of the elevator dampers

and the AFM revision that are currently

required by AD 98–04–45, and retained

in this AD, take approximately 6 work

hours per airplane to accomplish, at an

average rate of $60 per work hour. The

FAA estimates that all affected U.S.

operators have previously accomplished

these requirements, therefore, the future

cost impact of these requirements is

minimal.

The inspections that are currently

required by AD 98–04–45, and retained

in this AD, take approximately 26 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the inspection requirements of AD

98–04–05 is estimated to be $1,560 per

airplane.

The installation of flutter dampers

that is currently required by AD 98–04–

45 takes approximately 12 work hours

per airplane to accomplish, at an

average labor rate of $60 per work hour.

Required parts will be provided at no

cost to the operators by the

manufacturer. Based on these figures,

the cost impact of the installation

currently required AD 98–04–45 is

estimated to be $720 per airplane.

The new actions (i.e., replacement of

the shear pins, check of maintenance

records, and AFM revision) that are

required in this AD will take

approximately 21 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts are estimated to cost

$801. Based on these figures, the cost

impact of these new requirements of

this AD on U.S. operators is estimated

to be $441,054, or $2,061 per airplane.

The cost impact figures discussed

above are 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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

removing amendment 39–10356 (63 FR

9928, February 27, 1998), and by adding

a new airworthiness directive (AD),

amendment 39–12112, to read as

follows:

2001–03–08 Bombardier, Inc. (Formerly

Canadair): Amendment 39–12112.

Docket 2000–NM–142–AD. Supersedes

AD 98–04–45, Amendment 39–10356.

Applicability: Model CL–600–2B19 series

airplanes, having serial numbers 7003

through 7357 inclusive, certificated in any

category.

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 (i) 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 premature failure of the shear

pins of the elevator damper, which may

increase the likelihood of jamming or

restricting movement of the elevator and the

resultant adverse effect on controllability of

the airplane, accomplish the following:

Restatement of Actions Required by AD 98–

04–45:

Airplane Flight Manual (AFM) Revision

Required by AD 98–04–45

(a) For airplanes having serial numbers

7003 through 7054 inclusive: Within 30 days

after January 26, 1994 (the effective date of

AD 94–01–09, amendment 39–8791), revise

the Limitations Section of the FAA-approved

AFM to include the following restrictions of

altitude and airspeed operations under

conditions of single or double hydraulic

system failure; and advise the flight crew of

these revised limits. Revision of the AFM

may be accomplished by inserting a copy of

this AD or AFM Revision 34, dated June 12,

1995, in the AFM. Restrictions of altitude

and airspeed operations under conditions of

single or double hydraulic system failure are

listed in the following tables.

TABLE 1.—SINGLE HYDRAULIC SYSTEM

FAILURE

Altitude limit

(maximum)

Airspeed limit

(maximum)

31,000 feet ................ 0.55 Mach

(199 KIAS)

30,000 feet ................ 0.55 Mach

(204 KIAS)

28,000 feet ................ 0.55 Mach

(213 KIAS)

26,000 feet ................ 0.55 Mach

(222 KIAS)

24,000 feet ................ 0.55 Mach

(232 KIAS)

22,000 feet ................ 0.55 Mach

(241 KIAS)

20,000 feet and

below.

252 KIAS

TABLE 2.—DOUBLE HYDRAULIC

SYSTEM FAILURE

Altitude limit

(maximum)

Airspeed limit

(maximum)

10,000 feet ................ 200 KIAS

Note 2: The restrictions described in the

AFM Temporary Revision (TR) RJ/30, dated

December 16, 1993, meet the requirements of

this paragraph. Therefore, inserting a copy of

TR RJ/30 in lieu of this AD in the AFM is

considered an acceptable means of

compliance with this paragraph.

(b) Within 7 days after December 14, 1994

(the effective date of AD 94–24–02,

amendment 39–9075), accomplish the

Federal Register / Vol. 66, No. 36 / Thursday, February 22, 2001 / Rules and Regulations 11107

requirements of paragraphs (b)(1) and (b)(2)

of this AD.

(1) Remove the elevator dampers in

accordance with Canadair Regional Jet Alert

Service Bulletin S.B. A601R–27–041, dated

October 28, 1994.

(2) Revise the Limitations Section of the

FAA-approved AFM to include the

following, which advises the flight crew of

daily checks to verify proper operation of the

elevator control system. Revision of the AFM

may be accomplished by inserting a copy of

this AD or AFM Revision 32, dated March 30,

1995, in the AFM.

Note 3: The daily check described in the

AFM TR RJ/40, dated October 28, 1994,

meets the requirements of this paragraph.

Therefore, inserting a copy of TR RJ/40 into

the AFM in lieu of this AD is considered an

acceptable means of compliance with this

paragraph.

‘‘Elevator, Before Engine Start (First Flight of

Day)

(1) Elevator—Check: Travel range (to

approximately 1⁄2 travel) using each

hydraulic system in turn, with the other

hydraulic systems depressurized.’’

Inspections Required by AD 98–04–45

(c) For airplanes having serial numbers

7003 through 7049 inclusive: Within 12

months after April 3, 1998 (the effective date

of AD 98–04–45, amendment 39–10356),

perform the actions required in paragraphs

(c)(1), (c)(2), and (c)(3) of this AD, as

applicable, in accordance with Section 2.B.,

Part A, of Canadair Regional Jet Service

Bulletin S.B. 601R–27–040, Revision ‘‘B,’’

dated September 11, 1995.

(1) Remove the shear pins and shear links

of the flutter dampers and perform a visual

inspection to detect any deformation or

discrepancy of the flutter damper hinge

fitting and lug of the horizontal stabilizer.

Prior to further flight, replace any deformed

or discrepant part with a serviceable part in

accordance with the service bulletin.

(2) Perform a visual inspection to detect

any deformation or discrepancy of the

elevator hinge/damper fitting and shear pin

lugs. Prior to further flight, replace any

discrepant part with a serviceable part in

accordance with the service bulletin.

(3) Perform a fluorescent penetrant

inspection and a dimensional inspection to

detect any deformation or discrepancy of the

shear pin lugs. If any deformation or

discrepancy is found on the lugs, prior to

further flight, replace the elevator with a new

or serviceable elevator in accordance with

the service bulletin.

Note 4: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(d) For airplanes having serial numbers

7003 through 7054: Within 12 months after

April 3, 1998 (the effective date of AD 98–

04–45, amendment 39–10356), install new

elevator flutter dampers (P/N 601R75142–7)

in accordance with Section 2.B., Part B, of

Canadair Regional Jet Service Bulletin S.B.

601R–27–040, Revision ‘‘B,’’ dated

September 11, 1995.

New Requirements of This AD:

Installation of Shear Pins

(e) For airplanes having serial numbers

7003 through 7142 inclusive, and 7144:

Within 12 months after the effective date of

this AD, install new shear pins (part number

(P/N) 601R24063–31/S) in accordance with

Part A of the Accomplishment Instructions of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘‘A,’’ dated March 10,

2000. After accomplishment of the

installation of new shear pins, Canadair

Regional Jet TR RJ/68–1, dated February 15,

2000, may be removed from the AFM.

Inspection of Maintenance Records

(f) For airplanes having serial numbers

7143, and 7145 through 7357 inclusive:

Within 14 days after the effective date of this

AD, perform a one-time inspection of the

maintenance records to determine the

replacement status of the shear pins of the

elevator flutter dampers, in accordance with

Part B of the Accomplishment Instructions of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘‘A,’’ dated March 10,

2000.

(1) If the maintenance records indicate that

all shear pins were NOT replaced after

delivery of the airplane, or if all shear pins

were replaced with shear pins having P/N

601R24063–31/S: No further action is

required by this AD.

(2) If the maintenance records indicate that

any shear pin was replaced after delivery of

the airplane with a shear pin having P/N

601R24063–31 or 601R24063–953, or if the

maintenance records do not verify that all

shear pins having P/N 601R24063–31/S are

installed: Accomplish the requirements of

paragraph (g) of this AD at the times

specified in that paragraph.

AFM Revision and Replacement

(g) For airplanes on which any shear pin

of the elevator flutter dampers of the

elevators was replaced after delivery of the

airplane with a shear pin having P/N

601R24063–31 or 601R24063–953, or for

airplanes on which verification of shear pins

having P/N 601R24063–31/S is not possible:

Accomplish the requirements of paragraphs

(g)(1) and (g)(2) of this AD at the times

specified in those paragraphs.

(1) Within 30 days after the effective date

of this AD, revise the Normal Procedures

Section of the AFM by inserting Canadair

Regional Jet TR RJ/68–1, dated February 15,

2000, in the AFM, which advises the flight

crew of an additional first-flight-of-the-day

check of the elevator control system.

(2) Within 12 months after the effective

date of this AD, replace the shear pins with

new, improved shear pins having P/N

601R24063–31/S, in accordance with Part C

of the Accomplishment Instructions of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘‘A,’’ dated March 10,

2000. After accomplishment of the

installation of new shear pins, the temporary

revision required by paragraph (g)(1) of this

AD may be removed from the AFM.

Spares

(h) As of the effective date of this AD, no

person shall install a shear pin of the elevator

flutter dampers having P/N 601R24063–31 or

601R24063–953 on any airplane.

Alternative Methods of Compliance

(i) 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, New York

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(j) 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

(k) Except as required by paragraphs (a)

and (b)(2) of this AD, the actions shall be

done in accordance with Canadair Regional

Jet Alert Service Bulletin S.B. A601R–27–

041, dated October 28, 1994; Canadair

Regional Jet Service Bulletin S.B. 601R–27–

040, Revision ‘‘B,’’ dated September 11, 1995;

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘‘A,’’ dated March 10,

2000; and Canadair Regional Jet Airplane

Flight Manual Temporary Revision RJ/68–1,

dated February 15, 2000; as applicable.

(1) The incorporation by reference of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘‘A,’’ dated March 10,

2000; and Canadair Regional Jet Airplane

Flight Manual Temporary Revision RJ/68–1,

dated February 15, 2000; is approved by the

Director of the Federal Register in accordance

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

(2) The incorporation by reference of

Canadair Regional Jet Alert Service Bulletin

S.B. A601R–27–041, dated October 28, 1994;

and Canadair Regional Jet Service Bulletin

S.B. 601R–27–040, Revision ‘‘B,’’ dated

September 11, 1995; was approved

previously by the Director of the Federal

Register as of April 3, 1998 (63 FR 9928,

February 27, 1998).

(3) Copies may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087 Station Centre-ville,

11108 Federal Register / Vol. 66, No. 36 / Thursday, February 22, 2001 / Rules and Regulations

Montreal, Quebec H3C 3G9, Canada. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

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

New York Aircraft Certification Office, 10

Fifth Street, Third Floor, Valley Stream, New

York; 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 Canadian airworthiness directive CF–

2000–10, dated March 23, 2000.

Effective Date

(l) This amendment becomes effective on

March 29, 2001.

Issued in Renton, Washington, on February

8, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3697 Filed 2–21–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF THE TREASURY

Internal Revenue Service

26 CFR Part 26

[TD 8912]

RIN 1545–AX08

Generation-Skipping Transfer Issues;

Correction

AGENCY: Internal Revenue Service (IRS),

Treasury.

ACTION: Correction to final regulations.

SUMMARY: This document contains a

correction to final regulations that were

published in the Federal Register on

Wednesday, December 20, 2000 (65 FR

79735) relating to the generationskipping transfer (GST) tax imposed

under chapter 13 of the Internal

Revenue Code.

DATES: This correction is effective

December 20, 2000.

FOR FURTHER INFORMATION CONTACT:

James F. Hogan (202) 622–3090 (not a

toll-free number).

SUPPLEMENTARY INFORMATION:

Background

The final regulations that are the

subject of this correction are under

section 2601 of the Internal Revenue

Code.

Need for Correction

As published, the final regulations

contain an error that may prove to be

misleading and is in need of

clarification.

Correction of Publication

Accordingly, the publication of the

final regulations (TD 8912), that were

the subject of FR Doc. 00–31757, is

corrected as follows:

§ 26.2601–1 [Corrected]

On page 79740, column 2, § 26.2601–

1, paragraph (b)(4)(i)(E), Example 9.,

line 6, the language ‘‘is to pass to the A’s

issue, per stirpes. Under’’ is corrected to

read ‘‘is to pass to A’s issue, per stirpes.

Under’’.

Cynthia E. Grigsby,

Chief, Regulations Unit, Office of Special

Counsel (Modernization and Strategic

Planning).

[FR Doc. 01–4292 Filed 2–21–01; 8:45 am]

BILLING CODE 4830–01–P

DEPARTMENT OF TRANSPORTATION

Coast Guard

33 CFR Part 117

[CGD07–01–011]

Drawbridge Operation Regulations:

Stickney Point Bridge (SR 72),

Sarasota, Sarasota County, FL

AGENCY: Coast Guard, DOT.

ACTION: Notice of temporary deviation

from regulations.

SUMMARY: The Commander, Seventh

Coast Guard District, has approved a

temporary deviation from the

regulations governing the operation of

the Stickney Point Drawbridge (SR 72)

across the Gulf Intracoastal Waterway,

mile 68.6, Sarasota, Sarasota County,

Florida. This deviation allows the

drawbridge owner or operator to only

open a single leaf from February 26,

2001 to February 28, 2001 from 8 a.m.

until 5 p.m., daily. This temporary

deviation is requred to allow the bridge

owner to safely complete maintenance

to the drawbridge.

DATES: This deviation is effective from

February 26, 2001 to February 28, 2001.

FOR FURTHER INFORMATION CONTACT: Mr.

Barry Dragon, Chief, Operations Section,

Seventh Coast Guard District, Bridge

Section at (305) 415–6743.

SUPPLEMENTARY INFORMATION: The

Stickney Point Drawbridge (SR 72)

across the Gulf Intracoastal Waterway at

Sarasota, FL is a double leaf bridge with

a vertical clearance of 18 feet above

mean high water (MHW) measured at

the center in the closed position. On

January 24, 2001 the owner requested a

deviation from the current operating

regulation in 33 CFR 117.35 which

requires the drawbridge to open

promptly and fully when a request to

open is given. This temporary deviation

was requested to allow necessary

maintenance to the drawbridge in a

critical time sensitive manner.

The District Commander has granted

a temporary deviation from the

operating requirements listed in 33 CFR

117.35 for the purpose of maintenance

of the drawbridge. Under this deviation,

the Stickney Point Drawbridge (SR 72)

need only open one leaf from February

26, 2001 to February 28, 2001 from 8

a.m. until 5 p.m., daily.

Dated: February 13, 2001.

G. E. Shapley,

Chief, Bridge Administration, Seventh Coast

Guard District.

[FR Doc. 01–4329 Filed 2–21–01; 8:45 am]

BILLING CODE 4910–15–U

DEPARTMENT OF TRANSPORTATION

Coast Guard

33 CFR Part 117

[CGD08–00–005]

RIN 2115–AE47

Drawbridge Operation Regulation;

Chef Menteur Pass, LA

AGENCY: Coast Guard, DOT.

ACTION: Final rule.

SUMMARY: The Coast Guard is changing

the regulation governing the operation

of the U.S. Highway 90 bridge across

Chef Menteur Pass, mile 2.8 at Lake

Catherine, Orleans Parish, Louisiana.

The rule provides that the draw shall

open on signal; except that, from 5:30

a.m. to 7:30 a.m., Monday through

Friday except Federal holidays, the

draw need open only on the hour and

on the half-hour for the passage of

vessels. The draw shall open at any time

for a vessel in distress. This change will

accommodate the navigation needs of

commercial fishing vessels while

providing the uninterrupted flow of

vehicular traffic for commuters en route

to work during this period.

DATES: This rule becomes effective on

March 26, 2001.

ADDRESSES: Comments and material

received from the public, as well as

documents indicated in this preamble as

being available in the docket, are part of

docket CGD08–00–005 and are available

for inspection or copying at the Bridge

Administration Branch, Eighth Coast

Guard District, 501 Magazine Street,

New Orleans, Louisiana between 7 a.m.

and 3 p.m., Monday through Friday,

except Federal holidays.