Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations 33743

species had become widely distributed

in the United States. We did not receive

any information on the distribution of

any species of the genus Homeria, and,

therefore, could not select that

alternative.

This final rule contains no new

information collection or recordkeeping

requirements.

Executive Order 12372

This program/activity is listed in the

Catalog of Federal Domestic Assistance

under No. 10.025 and is subject to

Executive Order 12372, which requires

intergovernmental consultation with

State and local officials. (See 7 CFR part

3015, subpart V.)

Executive Order 12988

This final rule has been reviewed

under Executive Order 12988, Civil

Justice Reform. This rule: (1) Preempts

all State and local laws and regulations

that are inconsistent with this rule; (2)

has no retroactive effect; and (3) does

not require administrative proceedings

before parties may file suit in court

challenging this rule.

Paperwork Reduction Act

This final rule contains no new

information collection or recordkeeping

requirements under the Paperwork

Reduction Act of 1995 (44 U.S.C. 3501

et seq.).

List of Subjects

7 CFR Part 360

Imports, Plants (Agriculture),

Quarantine, Reporting and

recordkeeping requirements,

Transportation, Weeds.

7 CFR Part 361

Agricultural commodities, Imports,

Labeling, Quarantine, Reporting and

recordkeeping requirements, Seeds,

Vegetables, Weeds.

Accordingly, we are amending 7 CFR

parts 360 and 361 as follows:

PART 360—NOXIOUS WEED

REGULATIONS

1. The authority citation for part 360

continues to read as follows:

Authority: 7 U.S.C. 2803 and 2809; 7 CFR

2.22, 2.80, and 371.2(c).

§ 360.200 [Amended]

2. In § 360.200, paragraph (c) is

amended by adding, in alphabetical

order, an entry for ‘‘Homeria spp.’’.

PART 361—IMPORTATION OF SEED

AND SCREENINGS UNDER THE

FEDERAL SEED ACT

3. The authority citation for part 361

continues to read as follows:

Authority: 7 U.S.C. 1581–1610; 7 CFR 2.22,

2.80, and 371.2(c).

§ 361.6 [Amended]

4. In § 361.6, paragraph (a)(1) is

amended by adding, in alphabetical

order, an entry for ‘‘Homeria spp.’’.

Done in Washington, DC, this 19th day of

May 2000.

Craig A. Reed,

Administrator, Animal and Plant Health

Inspection Service.

[FR Doc. 00–13158 Filed 5–24–00; 8:45 am]

BILLING CODE 3410–34–U

FARM CREDIT ADMINISTRATION

12 CFR Part 614

RIN 3052–AB87

Loan Policies and Operations;

Participations; Effective Date

AGENCY: Farm Credit Administration.

ACTION: Notice of effective date.

SUMMARY: The Farm Credit

Administration (FCA) published a final

rule under part 614 on April 25, 2000

(65 FR 24101). This final rule deletes

requirements for a Farm Credit System

(Farm Credit or System) institution to

provide notice to or seek consent from

other System institutions when it buys

participation interests in loans

originated outside its chartered territory.

Repealing these notice and consent

requirements can help increase the flow

and availability of agricultural credit

and help diversify geographic and

industry concentrations in the loan

portfolios of Farm Credit banks and

associations. As a result of this rule, a

Farm Credit bank or association will no

longer need approval from other System

institutions when it buys participations

in loans from non-System lenders. In

accordance with 12 U.S.C. 2252, the

effective date of the final rule is 30 days

from the date of publication in the

Federal Register during which either or

both Houses of Congress are in session.

Based on the records of the sessions of

Congress, the effective date of the

regulations is May 25, 2000.

EFFECTIVE DATE: The regulation

amending 12 CFR part 614 published on

April 25, 2000 (65 FR 24101) is effective

May 25, 2000.

FOR FURTHER INFORMATION CONTACT:

S. Robert Coleman, Senior Policy

Analyst, Office of Policy and

Analysis, Farm Credit Administration,

McLean, VA 22102–5090, (703) 883–

4498; or

Richard A. Katz, Senior Attorney, Office

of General Counsel, Farm Credit

Administration, McLean, VA 22102–

5090, (703) 883–4020, TDD (703) 883–

4444.

(12 U.S.C. 2252(a)(9) and (10))

Dated: May 22, 2000.

Vivian L. Portis,

Secretary, Farm Credit Administration Board.

[FR Doc. 00–13191 Filed 5–24–00; 8:45 am]

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–04–AD; Amendment

39–11729; AD 2000–10–05]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SE.3160, SA.316B,

SA.316C, SA.319B, SA330F, SA330G,

SA330J, SA341G, and SA342J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Eurocopter France Model

SE.3160, SA.316B, SA.316C, SA.319B,

SA330F, SA330G, SA330J, SA341G, and

SA342J helicopters. This AD requires

inspecting each inflation head and

union nut on certain emergency

flotation gear nitrogen cylinders and

replacing each cracked inflation head

with an airworthy inflation head. This

amendment is prompted by the

discovery of cracked inflation heads

during routine maintenance inspections

of emergency flotation systems. The

actions specified by this AD are

intended to prevent an emergency

flotation gear nitrogen cylinder from

exploding with resultant high velocity

shrapnel, which could cause airframe

damage or personal injury and

subsequent loss of control of the

helicopter.

DATES: Effective June 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 29,

2000.

33744 Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Robert McCallister, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, 2601

Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5121, fax

(817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that applies to

Eurocopter France Model SE.3160,

SA.316B, SA.316C, SA.319B, SA330F,

SA330G, SA330J, SA341G, and SA342J

helicopters was published in the

Federal Register on December 10, 1999

(64 FR 69206). That action proposed to

require inspecting each inflation head

and union nut on certain emergency

flotation gear nitrogen cylinders and

replacing each cracked inflation head

with an airworthy inflation head.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial changes.

The FAA estimates that 114

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 4 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $2,138 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $271,092.

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 a new airworthiness directive to

read as follows:

AD 2000–10–05 Eurocopter France:

Amendment 39–11729. Docket No. 99–

SW–04–AD.

Applicability: Model SE.3160, SA.316B,

SA.316C, SA.319B, SA330F, SA330G,

SA330J, SA341G, and SA342J helicopters

with emergency flotation gear nitrogen

cylinder, P/N ARZ 74921, with inflation

head, part number (P/N) 74929, that has no

serial number (S/N), or with a S/N lower than

12000, or has a union nut, P/N 75441 or

75834, installed, certificated in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For helicopters 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 (d) 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

previously accomplished.

To prevent an emergency flotation gear

nitrogen cylinder from exploding with

resultant high velocity shrapnel, which could

cause airframe damage or personal injury and

subsequent loss of control of the helicopter,

accomplish the following:

(a) For Model SE.3160, SA.316B, SA.316C,

SA.319B, SA330F, SA330G, or SA330J

helicopters,

(1) At the next scheduled emergency

flotation gear maintenance inspection or 400

hours time-in-service (TIS), whichever occurs

first, accomplish the following:

(i) Discharge each emergency flotation gear

nitrogen cylinder (cylinder) in accordance

with the ‘‘Discharge Procedure for the

74921G Cylinder’’ in Eurocopter France

Service Bulletin 05.66, Revision 3, dated May

4, 1998 or Eurocopter France Service Bulletin

05.58, Revision 3, dated May 4, 1998.

(ii) Remove the inflation head and degrease

the assembly.

(iii) Perform a dye penetrant inspection of

each inflation head and union nut on each

emergency flotation gear nitrogen cylinder.

(2) Thereafter, conduct a dye penetrant

inspection of each inflation head and union

nut on each cylinder at each scheduled

emergency flotation gear maintenance

inspection or at intervals of not more than

400 hours TIS, whichever occurs first.

(b) For Model SA341G or SA342J

helicopters,

(1) At the next scheduled emergency

flotation gear maintenance inspection or 520

hours time-in-service, whichever occurs first,

accomplish the following:

(i) Discharge each emergency flotation gear

nitrogen cylinder in accordance with the

‘‘Discharge Procedure for the 74921G

Cylinder’’ in Eurocopter France Service

Bulletin 05.19, Revision 3, dated May 4,

1998.

(ii) Remove the inflation head and degrease

the assembly.

(iii) Perform a dye penetrant inspection of

each inflation head and union nut on each

cylinder.

(2) Thereafter, conduct a dye penetrant

inspection of each inflation head and union

nut on each cylinder at each scheduled

emergency flotation gear maintenance

inspection or at intervals of not more than

520 hours TIS, whichever occurs first.

(c) Before further flight, replace each

cracked inflation head, P/N 74929, with an

airworthy inflation head having S/N 12000 or

higher.

(d) 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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(e) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations 33745

(f) The discharge of each cylinder shall be

done in accordance with the ‘‘Discharge

Procedure for the 74921G Cylinder’’ in

Eurocopter France Service Bulletin 05.66,

Revision 3, dated May 4, 1998; Eurocopter

France Service Bulletin 05.58, Revision 3,

dated May 4, 1998; or Eurocopter France

Service Bulletin 05.19, Revision 3, dated May

4, 1998. 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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. Copies may be inspected at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

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

(g) This amendment becomes effective on

June 29, 2000.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

AD’s 80–062–041(A) R2, 80–063–030(A) R2,

and 80–061–028(A) R2, all dated July 15,

1998.

Issued in Fort Worth, Texas, on May 5,

2000.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–12351 Filed 5–24–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–112–AD; Amendment

39–11747; AD 99–15–04 R1]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc., Models PA–46–

310P and PA–46–350P Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 99–15–04,

which currently requires you to

calibrate, inspect, and repair or replace

portions of the turbine inlet temperature

system on all The New Piper Aircraft,

Inc. (New Piper) Models PA–46–310P

and PA–46–350P airplanes (different

actions for different airplane models).

Information reveals that the AD should

not apply to airplanes where the factory

installed turbine inlet temperature

gauge and associated probe have been

replaced through supplemental type

certificate (STC). This AD retains the

actions of AD 99–15–04, and restricts

the applicability accordingly. The

actions specified by this AD are

intended to prevent improper engine

operation caused by improperly

calibrated turbine inlet temperature

indicators or defective turbine inlet

temperature probes, which could result

in engine damage/failure with

consequent loss of control of the

airplane.

EFFECTIVE DATE: This AD becomes

effective on July 28, 2000.

ADDRESSES: You may examine

information related to this AD at FAA,

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

98–CE–112–AD, 901 Locust, Room 506,

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Donald J. Young, Aerospace Engineer,

FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30349; telephone: (770) 703–6079;

facsimile: (770) 703–6097; e-mail

address: ‘‘Donald.Young@faa.gov’’.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

Has FAA taken any action to this

point? Field reports that indicated

service accuracy problems with the

existing turbine inlet temperature

system on certain New Piper Models

PA–46–310P and PA–46–350P airplanes

caused FAA to issue AD 99–15–04,

Amendment 39–11223. This AD

currently requires you to accomplish the

following:

1. Calibrate the turbine inlet

temperature system to assure the

accuracy of the existing turbine inlet

temperature indicator and wiring on all

airplanes;

2. Repair or replace any turbine inlet

temperature system that fails the

calibration test on all airplanes;

3. Repetitively replace the turbine

inlet temperature probe on the Model

PA–46–350P airplanes; and

4. Insert a copy of the AD into the

Pilot’s Operating Handbook (POH) of

certain airplanes.

Since issuing AD 99–15–04, we have

received information to show that the

AD should not apply on airplanes where

the factory installed turbine inlet

temperature gauge and associated probe

were replaced through supplemental

type certificate (STC).

To address this issue, we issued a

notice of proposed rulemaking (NPRM)

to revise AD 99–15–04. This NPRM was

published in the Federal Register on

November 5, 1999 (64 FR 60383). The

NPRM proposed to continue to require

you to accomplish all the actions that

AD 99–15–04 currently requires. Those

airplanes that do not have a Lewis or

Transicoil Turbine Inlet Temperature

Gauge and associated probe installed,

and where this system was replaced in

accordance with an STC, would be

excluded from the AD. Relief from the

AD is available only if the gauge and

probe are replaced through STC and not

if a second turbine inlet temperature

gauge was installed while retaining the

Lewis or Transicoil gauge and probe.

Was the public invited to comment on

the NPRM? The FAA invited interested

persons to participate in the making of

the amendment. A summary of the

comments and FAA’s responses follows:

Comment Issue No. 1: Provide

Justification for Indefinite Life of

Probes Installed Through STC

What is the commenter’s concern?

One commenter requests an explanation

on how FAA determined that the

turbine inlet temperature gauge and

associated probe would last indefinitely

if installed through STC.

What is FAA’s response to the

concern? Our intent of this AD is not to

life limit the turbine inlet temperature

system. We are issuing the AD to assure

that the system is calibrated correctly

and assure that certain parts of this

system are checked and replaced

accordingly. We have not received any

service history or other evidence of

problems with those systems installed

in accordance with an STC. We also

have not received any evidence of

inadequate maintenance instructions for

any system installed in accordance with

an STC. If an unsafe condition develops

on airplanes with these systems

installed per STC, we will issue an AD

against airplanes with that specific

configuration.

We are not changing the AD as a

result of this comment.

Comment Issue No. 2: Provide Specific

STC Numbers and Holders

What are the commenter’s concerns?

One commenter requests that FAA

include a list of STC numbers and

holders of those STC’s that provide

relief from this AD. This commenter

also points out that relief should also be

given if New Piper (the manufacturer)

develops a new turbine temperature

inlet system since we are allowing relief

for any STC, whether currentlyapproved or approved in the future.

What is FAA’s response to the

concerns? We have elected not to

provide a list of STC’s that provide

relief because the FAA having to revise

the AD every time a new STC was

developed and certificated would make

tracking of this AD action confusing and

impractical. We acknowledge that New