Federal Register / Vol. 66, No. 100 / Wednesday, May 23, 2001 / Rules and Regulations 28361

crop-year. In the future, AMS will

continue to review the program to

ensure that fees are adequate.

Accordingly, we believe that the impact

of this rule would not be significant on

the users of the inspection and

certification services.

Civil Justice Reform

This interim final rule has been

reviewed under Executive Order 12988,

Civil Justice Reform. This action is not

intended to have retroactive effect. This

rule will not preempt any State or local

laws, regulations, or policies, unless

they present an irreconcilable conflict

with this rule. There are no

administrative procedures which must

be exhausted prior to any judicial

challenge to the provisions of this rule.

Lists of Subjects in 7 CFR Part 29

Administrative practice and

procedure, Advisory committees,

Government publications, Imports,

Pesticides and pests, Reporting and

recordkeeping requirements, Tobacco.

For the reasons set forth in the

preamble, 7 CFR part 29 is amended as

follows:

PART 29—TOBACCO INSPECTION

Subpart B—Regulations

1. The authority citation for Part 29,

subpart B continues to read as follows:

Authority: 7 U.S.C. 511m and 511r.

2. In § 29.123, paragraph (b) is revised

to read as follows:

§ 29.123 Fees and charges.

* * * * *

(b) Domestic permissive inspection

and certification. (1) Fees and charges

for inspection at redrying plants shall

comprise the cost of salaries, travel, per

diem, and related expenses to cover the

cost of performing the service. Fees

shall be for the actual time required to

render the service calculated to the

nearest 30-minute period. The hourly

rate shall be $47.40 per hour. The

overtime rate for service performed

outside the inspector’s regularly

scheduled tour of duty shall be $53.70

per hour. The rate of $64.45 per hour

shall be charged for work performed on

Sundays and holidays. These same fees

shall be applicable for hogshead, bale,

cases or sample inspections. (2) Fees

and charges for inspection of tobacco

performed at receiving points is $.01 per

pound.

Subpart F—Policy Statement and

Regulations Governing the

Identification and Certification of

Nonquota Tobacco Produced and

Marketed in a Quota Area

3. The authority citation for subpart F

continues to read as follows:

Authority: Pub. L. 97–98. 95 Stat. 1266, as

amended (7 U.S.C. 1314f).

§ 29.9251 Fees and charges.

4. In § 29.9251 the words ‘‘$32.40’’,

‘‘$38.70’’ and ‘‘$48.45’’ are removed and

the words ‘‘$47.40’’ ‘‘$53.70’’ and

‘‘$64.45’’ are added in their place,

respectively.

Dated: May 17, 2001.

Kenneth C. Clayton,

Acting Administrator, Agricultural Marketing

Service.

[FR Doc. 01–12935 Filed 5–22–01; 8:45 am]

BILLING CODE 3410–02–P

FARM CREDIT ADMINISTRATION

12 CFR Part 650

RIN 3052–AB56

Federal Agricultural Mortgage

Corporation; Risk-Based Capital

Requirements; Effective Date

AGENCY: Farm Credit Administration.

ACTION: Notice of effective date.

SUMMARY: The Farm Credit

Administration (FCA) published a final

rule under part 650 on April 12, 2001

(66 FR 19048). In this final rule, we

amended our regulations, through the

Office of Secondary Market Oversight

(OSMO), by establishing risk-based

capital regulations for the Federal

Agricultural Mortgage Corporation

(Farmer Mac). The final rule in part 650

sets forth the risk-based capital

regulations for Farmer Mac, including

definitions, methods, parameters and

guidelines for developing and

implementing the risk-based capital

stress test; specifies capital calculation,

reporting, and compliance

requirements; and delineates our

monitoring, examination, supervisory,

and enforcement activities with respect

to Farmer Mac’s compliance with the

rule’s risk-based capital requirements;

and prescribes certain requirements for

business and capital planning. 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 23, 2001.

EFFECTIVE DATE: The regulation

amending 12 CFR part 650 published on

April 12, 2001 (66 FR 19048) is effective

May 23, 2001.

FOR FURTHER INFORMATION CONTACT:

Carl A. Clinefelter, Director, Office of

Secondary Market Oversight, Farm

Credit Administration, McLean, VA

22102–5090, (703) 883–4280, TDD

(703) 883–4444, or

Dennis K. Carpenter, Senior Policy

Analyst, Office of Policy and

Analysis, Farm Credit Administration,

McLean, VA 22102–5090, (703) 883–

4498, TDD (703) 883–4444, or

Joy Strickland, Senior Counsel, 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 18, 2001.

Kelly Mikel Williams,

Secretary, Farm Credit Administration Board.

[FR Doc. 01–13071 Filed 5–22–01; 8:45 am]

BILLING CODE 6705–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–CE–08–AD; Amendment

39–12235; AD 2001–10–09]

RIN 2120–AA64

Airworthiness Directives; Honeywell

KC 225 Automatic FlightControl

Systems

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Honeywell KC 225

automatic flight control systems (AFCS)

that are installed on airplanes. This AD

requires you to inspect the KC 225

AFCS to determine the computer

modifications (Mods) that are

incorporated, deactivate any units with

only Mods 1 and/or 2 incorporated, and

fabricate and install an appropriate

placard if the unit is deactivated/

inoperative. The AD would provide, as

an alternative method of compliance,

the option of installing a unit that

incorporated MOD 3 or higher. This AD

is the result of several reports that the

AFCS is disconnecting without warning

28362 Federal Register / Vol. 66, No. 100 / Wednesday, May 23, 2001 / Rules and Regulations

in a gross mistrim configuration. The

actions specified by this AD are

intended to prevent an undesirable

autotrim command that the autopilot

cannot detect in the required time. The

airplane could then deviate from the

selected altitude or the autopilot could

disconnect without warning, which

could result in heavy loads at the

control column. Such loads in the pitch

axis could result in loss of control of the

airplane.

DATES: This AD becomes effective on

June 15, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulation as of June 15, 2001.

The Federal Aviation Administration

(FAA) must receive any comments on

this rule by August 10, 2001.

ADDRESSES: Send three copies of your

comments to FAA,Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2001–CE–

08–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106.

You may get the service information

referenced in this AD from Honeywell,

Product Support, One Technology

Center, 23500 W. 105th Street, Olathe,

Kansas 66061; telephone: (913) 712–

2613; facsimile: (913) 712–1306. You

may look at this information at FAA,

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

2001–CE–08–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:

Clyde Erwin, AerospaceEngineer, FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, Wichita,

Kansas 67209; telephone: (316) 946–

4149; facsimile: (329) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The FAA has received reports that the

Honeywell KC 225 automatic flight

control system (AFCS) is disconnecting

without warning during flight in a gross

mistrim configuration. The suspect

AFCS’s incorporate computer

modifications (Mods) 1 and/or 2.

Honeywell then conducted a factory

test, where it was noted that the pitch

trim ran when a malfunction of the trim

sense 1 monitor timer happened with

out-of-tolerance components in the trim

sense 2 monitor timer. The autopilot

then disconnected without warning

because of other monitors in the

autopilot.

What are the consequences if the

condition is not corrected? This

condition, if not corrected, could result

in an undesirable autotrim command

that the autopilot cannot detect in the

required time. The airplane could then

deviate from the selected altitude or the

autopilot could disconnect without

warning, which could result in heavy

loads at the control column. Such loads

in the pitch axis could result in loss of

control of the airplane.

Is there service information that

applies to this subject?Honeywell has

issued Installation Bulletin No. 472

Alert, Revision 1, dated January 2001.

This installation bulletin includes

procedures for:

—Inspecting to determine the currently

incorporated computer Mods, which

are indicated on the unit’s serial

number tag;

—Returning the unit to Honeywell for

modification; or

—Contacting Honeywell for a warranty

replacement unit.

The FAA’s Determination and an

Explanation of the Provisions of this AD

What has FAA decided? The FAA has

reviewed all available information,

including the service information

referenced above, and determined that:

—The unsafe condition referenced in

this document exists or could develop

on airplanes equipped with a certain

Honeywell KC 225 AFCS

configuration;

—Any airplane with one of these AFCS

units should have the actions

specified in the above service bulletin

incorporated; and

—The FAA should take AD action to

correct this unsafe condition.

What does this AD require? This AD

requires you to accomplish the actions

previously specified in Honeywell

Installation Bulletin No. 472 Alert,

Revision 1, dated January 2001.

Will I have the opportunity to

comment prior to the issuance of the

rule? Because the unsafe condition

described in this document could result

in potential loss of control of the

airplane, FAA finds that notice and

opportunity for public prior comment

are impracticable. Therefore, good cause

exists for making this amendment

effective in less than 30 days.

Comments Invited

How do I comment on this AD?

Although this action is in the form of a

final rule and was not preceded by

notice and opportunity for public

comment, we invite your comments on

the rule. You may send whatever

written data, views, or arguments you

choose. You need to include the rule’s

docket number and send three copies of

your comments to the address specified

under the caption ADDRESSES. We will

consider all comments received by the

closing date specified above. We may

change this rule in light of comments

received. Factual information that

supports your ideas and suggestions is

extremely helpful in evaluating the

effectiveness of the AD action and

determining whether we need to take

additional rulemaking action.

Are there any specific portions of the

AD I should pay attention to? The FAA

specifically invites comments on the

overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. You may read all

comments we receive before and after

the closing date of the rule in the Rules

Docket. We will file a report in the

Rules Docket that summarizes each FAA

contact with the public that concerns

the substantive parts of this AD.

We are reviewing the writing style we

currently use in regulatory documents,

in response to the Presidential

memorandum of June 1, 1998. That

memorandum requires federal agencies

to communicate more clearly with the

public. We are interested in your

comments on whether the style of this

document is clear, and any other

suggestions you might have to improve

the clarity of FAA communications that

affect you. You can get more

information about the Presidential

memorandum and the plain language

initiative at http://

www.plainlanguage.gov.

How can I be sure FAA receives my

comment? If you want us to

acknowledge the receipt of your

comments, you must include a selfaddressed, stamped postcard. On the

postcard, write ‘‘Comments to Docket

No. 2001–CE–08–AD.’’ We will date

stamp and mail the postcard back to

you.

Regulatory Impact

Does this AD impact various entities?

These regulations 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, FAA

has determined that this final rule does

not have federalism implications under

Executive Order 13132.

Does this AD involve a significant rule

or regulatory action? The FAA has

determined that this regulation is an

emergency regulation that must be

issued immediately to correct an unsafe

Federal Register / Vol. 66, No. 100 / Wednesday, May 23, 2001 / Rules and Regulations 28363

condition in aircraft, and is not a

significant regulatory action under

Executive Order 12866. It has been

determined further that this action

involves an emergency regulation under

DOT Regulatory Policies and Procedures

(44 FR 11034, February 26, 1979). If it

is determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.

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 airworthiness directive (AD) to

read as follows:

2001–10–09 Honeywell: Amendment 39–

12235; Docket No. 2001–CE–08–AD.

(a) What airplanes are affected by this AD?

This AD affects the following Honeywell

automatic flight control systems (AFCS) that

are installed in, but not limited to, the

airplanes listed below:

(1) Affected KC 225 AFCS:

Unit Part No.

Applicable

to Serial

No.

KC–225 065–00183–0101 All units

065–00183–0201

065–00183–0301

065–00183–0401

065–00183–0501

065–00183–0601

065–00183–2501

065–00183–2601

065–00183–2701

065–00183–2801

065–00183–2901

065–00183–3001

(2) List of airplanes where the affected AFCS could be installed. This is not a comprehensive list and airplanes not on this

list that have an affected AFCS installed through field approval or other methods are still affected by this AD:

Manufacturer Airplane models

Aerostar Aircraft Corporation .................................................................... PA–60–700P.

The Cessna Aircraft Company ................................................................. 208 and 208B.

Commander Aircraft Corporation ............................................................. 114B and 114TC.

Mooney Aircraft Corporation .................................................................... M20M and M20R.

The New Piper Aircraft, Inc. ..................................................................... PA–34–220T and PA–46–350P.

Raytheon Aircraft Company (Beech) ....................................................... 58, 95–55, 95–C55, A36, B36TC, D55, and E55.

SOCATA—Groupe Aerospatiale .............................................................. TB20 and TB21.

(b) Who must comply with this AD?

Anyone who wishes to operate any airplane

that incorporates one of the

affectedHoneywell automatic flight control

systems must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent an undesirable autotrim command

that the autopilot cannot detect in the

required time. The airplane could then

deviate from the selected altitude or the

autopilot could disconnect without warning,

which could result in heavy loads at the

control column. Such loads in the pitch axis

could result in loss of control of the airplane.

(d) What must I do to address this

problem? To address this problem, you must

do the following actions, unless already

done:

Action Compliance time Procedures

(1) Inspect the KC 225 automatic flight control

system (AFCS) (Part Number 065–00183–

0101, –0201, –0301, –0401, –0501, –0601,

–2501, –2601, –2701, –2801, –2901, or

–3001) to determine the currently installed

computer modifications (Mods). These modifications are indicated on the AFCS serial

number tag.

Within the next 10 hours time-in-service (TIS)

after June 15, 2001 (the effective date of

this AD).

Do this following the Honeywell Installation

Bulletin No. 472 Alert, Revision 1, dated

January 2001.

(2) If only Mods 1 and/or 2 are incorporated,

accomplish the following:

Prior to further flight after the inspection required by paragraph (d)(1) of this AD.Accomplish the deactivation in accordance

with Honeywell Installation Bulletin No. 472

Alert, Revision 1, dated January 2001. The

owner/operator holding at least a private

pilot certificate as authorized by section

43.7 of the Federal Aviation Regulations

(14 CFR 43.7) may accomplish the placard

requirements of paragraph (d)(2)(ii) of this

AD. Make an entry into the aircraft records

showing compliance with this portion of the

AD in accordance with section 43.9 of the

Federal Aviation Regulations (14 CFR

43.9).

(i) Deactivate the KC 225 AFCS by pulling and

banding the autopilot circuit breaker(s) to prevent operation of the KC 225 AFCS in flight;

and.

28364 Federal Register / Vol. 66, No. 100 / Wednesday, May 23, 2001 / Rules and Regulations

Action Compliance time Procedures

(ii) Fabricate a placard that indicates the KC

225 AFCS is inoperative, and install this

placard on the instrument panel within the pilot’s clear view. The placard should use letters of at least 0.10-inch in height and contain the following words: ‘‘KC 225 AFCS INOPERATIVE.’’.

(3) As an alternative method of compliance to

paragraphs (d)(2)(i) and (d)(2)(ii) of this AD

for the KC 225 AFCS with only Mods 1 and/

or 2 installed, accomplish either of the following to return the KC 225 AFCS to operation.

At any time as terminatinig action for all other

requirements of this AD.

Do this following the Honeywell Installation

Bulletin No. 472 Alert, Revision 1, dated

January 2001.

(i) Return the AFCS to the Honeywell Service

Center for modification to install Mod 1, 2,

and 3 (or higher) levels and then incorporate

thisAFCS on the airplane; or.

(ii) Contact Honeywell Product Support for a

warranty replacement KC 225 AFCS that

contains Mod 1, 2, and 3 (or higher) levels

and then incorporate this AFCS on the airplane.

(4) If no Mods are installed or at least Mods 1,

2, and 3 are installed, ensure that the aircraft

records identify Mod status. No further action

is required by this AD.

Prior to further flight after the inspection required by paragraph (d)(1) of this AD.Do this following the Honeywell Installation

Bulletin No. 472 Alert, Revision 1, dated

January 2001.

(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, Wichita Aircraft

Certification Office approves your

alternative. Send your request through an

FAAPrincipal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note: This AD applies to each airplane

with a Honeywell automatic flight control

computer 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.

You should include in the request 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? Contact Clyde Erwin, Aerospace

Engineer, FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Wichita, Kansas 67209; telephone: (316) 946–

4149; facsimile: (329)946–4407.

(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

§§ 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

Honeywell Installation Bulletin No. 472

Alert, Revision 1, dated January 2001. 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 Honeywell, Business & General

Aviation, One Technology Center, 23500 W.

105th Street, Olathe, Kansas 66061. You can

look at copies at 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 June 15, 2001.

Issued in Kansas City, Missouri, on May

14, 2001.

Melvin D. Taylor,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–12634 Filed 5–22–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–58–AD; Amendment 39–

12238; AD 2001–10–12]

RIN 2120–AA64

Airworthiness Directives; GE Aircraft

Engines CJ610 Series Turbojet and

CF700 Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that is applicable to GE Aircraft Engines

(GEAE) CJ610 series turbojet and CF700

series turbofan engines that currently

requires removal of certain unapproved

parts before further flight. This

amendment requires removal of

additional unapproved parts. This

amendment is prompted by the

discovery by the FAA of additional

unapproved parts not listed in the

original AD that have been introduced

into the field and might be installed on

the affected engines. The actions

specified in this AD are intended to

prevent the use of unapproved parts

which could lead to an uncontained