This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

68065

Vol. 65, No. 220

Tuesday, November 14, 2000

DEPARTMENT OF AGRICULTURE

Animal and Plant Health Inspection

Service

9 CFR Part 78

[Docket No. 99–052–2]

Brucellosis in Cattle; State and Area

Classifications; Louisiana

AGENCY: Animal and Plant Health

Inspection Service, USDA.

ACTION: Affirmation of interim rule as

final rule.

SUMMARY: We are adopting as a final

rule, without change, an interim rule

that amended the regulations

concerning the interstate movement of

cattle by changing the classification of

Louisiana from Class A to Class Free.

We have determined that Louisiana

meets the standards for Class Free

status. The interim rule relieved certain

restrictions on the interstate movement

of cattle from Louisiana.

EFFECTIVE DATE: The interim rule

became effective on July 27, 2000.

FOR FURTHER INFORMATION CONTACT: Dr.

Valerie Ragan, Senior Staff Veterinarian,

National Animal Health Programs, VS,

APHIS, 4700 River Road Unit 43,

Riverdale, MD 20737–1231; (301) 734–

7708.

SUPPLEMENTARY INFORMATION:

Background

In an interim rule effective July 27,

2000, and published in the Federal

Register on August 3, 2000 (65 FR

47653–47654, Docket No. 99–052–1), we

amended the brucellosis regulations in

9 CFR part 78 by removing Louisiana

from the list of Class A States in

§ 78.41(b) and adding it to the list of

Class Free States in § 78.41(a). That

action relieved certain restrictions on

the interstate movement of cattle from

Louisiana.

Comments on the interim rule were

required to be received on or before

October 2, 2000. We did not receive any

comments. Therefore, for the reasons

given in the interim rule, we are

adopting the interim rule as a final rule.

This action also affirms the

information contained in the interim

rule concerning Executive Order 12866

and the Regulatory Flexibility Act,

Executive Orders 12372 and 12988, and

the Paperwork Reduction Act.

Further, for this action, the Office of

Management and Budget has waived the

review process required by Executive

Order 12866.

List of Subjects in 9 CFR Part 78

Animal diseases, Bison, Cattle, Hogs,

Quarantine, Reporting and

recordkeeping requirements,

Transportation.

PART 78—BRUCELLOSIS

Accordingly, we are adopting as a

final rule, without change, the interim

rule that amended 9 CFR part 78 and

that was published at 65 FR 47653–

47654 on August 3, 2000.

Authority: 21 U.S.C. 111–114a–1, 114g,

115, 117, 120, 121, 123–126, 134b, and 134f;

7 CFR 2.22, 2.80, and 371.4.

Done in Washington, DC, this 6th day of

November 2000 .

Bobby R. Acord,

Acting Administrator, Animal and Plant

Health Inspection Service.

[FR Doc. 00–29025 Filed 11–13–00; 8:45 am]

BILLING CODE 3410–34–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–34–AD; Amendment

39–11964; AD 2000–22–17]

RIN 2120–AA64

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Models MS

880B, MS 885, MS 892A–150, MS 892E–

150, MS 893A, MS 893E, MS 894A, MS

894E, Rallye 100S, Rallye 150T, Rallye

150ST, Rallye 235C, and Rallye 235E

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all SOCATA—Groupe

AEROSPATIALE (Socata) Models MS

880B, MS 885, MS 892A–150, MS 892E–

150, MS 893A, MS 893E, MS 894A, MS

894E, Rallye 100S, Rallye 150T, Rallye

150ST, Rallye 235C, and Rallye 235E

airplanes. This AD requires you to

repetitively inspect, and, if necessary,

replace elevator clevis and rudder

governor control clevis that are too thin.

This AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for France. The actions

specified in this AD are intended to

correct rudder and elevator control

clevis that are too thin because of

abnormal wear, with consequent failure

of the rudder and elevator clevis. Such

failure could lead to loss of directional

or pitch control.

DATES: This AD becomes effective on

December 29, 2000.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of December 29, 2000.

ADDRESSES: You may get the service

information referenced in this AD from

SOCATA Groupe AEROSPATIALE,

Customer Support, Aerodrome TarbesOssun-Lourdes, BP 930—F65009 Tarbes

Cedex, France; telephone: (33)

(0)5.62.41.73.00; facsimile: (33)

(0)5.62.41.76.54; or the Product Support

Manager, SOCATA—Groupe

AEROSPATIALE, North Perry Airport,

7501 Pembroke Road, Pembroke Pines,

Florida 33023; telephone: (954) 894-

1160; facsimile: (954) 964–4191. You

may examine this information at the

Federal Aviation Administration (FAA),

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

2000–CE–34–AD, 901 Locust, Room

506, Kansas City, Missouri 64106; or at

the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64106;

telephone: (816) 329–4146; facsimile:

(816) 329–4090.

SUPPLEMENTARY INFORMATION:

68066 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

Discussion

What Events Have Caused This AD?

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on all Socata

Models MS 880B, MS 885, MS 892A–

150, MS 892E–150, MS 893A, MS 893E,

MS 894A, MS 894E, Rallye 100S, Rallye

150T, Rallye 150ST, Rallye 235C, and

Rallye 235E airplanes. The DGAC

reports one failure of the rudder clevis

in a Rallye airplane in flight. Abnormal

wear of the part resulted in the failure.

What Happens if You Do Not Correct

the Condition?

This condition, if not corrected, could

result in failure of the rudder and

elevator clevis and consequent loss of

directional or pitch control.

Has FAA Taken Any Action to This

Point?

We issued a proposal to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) to include an AD that

would apply to all Socata Models MS

880B, MS 885, MS 892A–150, MS 892E–

150, MS 893A, MS 893E, MS 894A, MS

894E, Rallye 100S, Rallye 150T, Rallye

150ST, Rallye 235C, and Rallye 235E

airplanes. This proposal was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

September 11, 2000 (65 FR 54820). The

NPRM proposed to require you to

repetitively inspect the elevator and

rudder governor control clevis, and, if

necessary, replace any clevis that is too

thin.

Was the Public Invited To Comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

The FAA’s Determination

What Is FAA’s Final Determination on

This Issue?

After careful review of all available

information related to the subject

presented above, we have determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. We determined that these

minor corrections:

—Will not change the meaning of the

AD; and

—Will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How Many Airplanes Does This AD

Impact?

We estimate that this AD affects 81

airplanes in the U.S. registry.

What Is the Cost Impact of This AD on

Owners/Operators of the Affected

Airplanes?

We estimate the following costs to

accomplish each inspection and

possible replacement and lubrication:

Labor cost Parts cost Total cost per airplane Total cost on U.S.

airplane operators

4 workhours $60 per hour = $240 .. $24 per airplane if clevis replacement is necessary.$264 per airplane ......................... $264 × 81 = $21,384.

These actions are repetitive. We have

no way of determining how many of

these repetitive actions each owner/

operator may incur over the life of each

airplane.

Regulatory Impact

Does This AD Impact Various Entities?

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.

Does This AD Involve a Significant Rule

or Regulatory Action?

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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, under 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. FAA amends § 39.13 by adding a

new AD to read as follows:

2000–22–17 Socata—Groupe Aerospatiale:

Amendment 39–11964; Docket No.

2000–CE–34–AD.

(a) What airplanes are affected by this AD?

This AD affects the following airplane

models, all serial numbers, certificated in any

category:

MS 880B

MS 892E–150

MS 894A

Rallye 150T

Rallye 235E

MS 885

MS 893A

MS 894E

Rallye 150ST

MS 892A–150

MS 893E

Rallye 100S

Rallye 235C

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to correct rudder clevis and elevator control

clevis that are too thin because of abnormal

wear, and the consequent failure of the

rudder and elevator clevis. Such failure

could lead to loss of directional or pitch

control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following

actions:

Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68067

Actions Compliance times Procedures

(1) Inspect the elevator and rudder control clevis for abnormal wear. Measure clevis thickness. The thickness at the bent section

should be at least 0.043 inch (in)/1.1 millimeter (mm).

Within the next 100 hours time-in-service

(TIS) after December 29, 2000 (the effective date of this AD), and thereafter at intervals not to exceed 600 hours TIS.

Do this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(2) If, during inspection, the elevator or rudder

control clevis measures a thickness less than

0.043 in/1.1 mm, replace the clevis.

Before further flight after the inspection where

abnormal wear was found.

Do this section in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(3) Lubricate the clevis ....................................... Within the next 100 hours TIS after December

29, 2000 (the effective date with the of this

AD), and thereafter at intervals not to exceed 100 hours TIS.

Do this action in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? You can contact Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64016;

telephone: (816) 329–4146; facsimile: (816)

329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Socata Mandatory Service Bulletin SB 155–

27, dated April, 2000. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from SOCATA

Groupe AEROSPATIALE, Customer Support,

Aerodrome Tarbes-Ossun-Lourdes, BP 930—

F65009 Tarbes Cedex, France; telephone: (33)

(0)5.62.41.73.00. You can look at copies at

the FAA, Central Region, Office of the

Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on December 29, 2000.

Note 2: The subject of this AD is addressed

in French AD number 2000–174(A), dated

May 3, 2000.

Issued in Kansas City, Missouri, on

October 30, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–28439 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–344–AD; Amendment

39–11968; AD 2000–22–20]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–10, –9–20, –9–30,

–9–40, and –9–50 Series Airplanes and

C–9 (Military) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain McDonnell

Douglas Model DC–9–10, –9–20, –9–30,

–9–40, and –9–50 series airplanes and

C–9 (military) airplanes. This action

requires, among other actions,

measuring the diameter of the hole

counterbore of the outboard idler hinge

fitting of the left and right wing flap;

performing repetitive high frequency

eddy current inspections (HFEC) to

detect cracks at the flap idler hinge

fitting, if necessary; and replacing the

flap idler hinge fitting with a new like

part, if any crack is detected. This action

is necessary to prevent failure of the

outboard flap idler hinge fitting due to

fatigue cracking, which could result in

a deflected flap that may cause an

asymmetric lift and consequent reduced

controllability and structural integrity of

the airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective November 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

29, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

344–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–344–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Boeing

Commercial Aircraft Group, Long

Beach Division, 3855 Lakewood

Boulevard, Long Beach, California

90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). This information

may be examined 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