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

10353

Vol. 66, No. 32

Thursday, February 15, 2001

DEPARTMENT OF AGRICULTURE

Commodity Credit Corporation

7 CFR Part 1446

RIN 0560–AF56

Cleaning and Reinspection of Farmers

Stock Peanuts; Correction

AGENCY: Commodity Credit Corporation,

USDA.

ACTION: Correction to final regulations.

SUMMARY: This document corrects final

peanut price support regulations which

were published on Wednesday, January

10, 2001 (66 FR 1807).

DATES: Effective February 15, 2001.

FOR FURTHER INFORMATION CONTACT:

David Kincannon, (202) 720–7914.

SUPPLEMENTARY INFORMATION:

Background and Need for Correction

Amendments published on January

10, 2001, to the peanut price support

regulations contained in 7 CFR part

1446 related to Segregation 3 peanuts

and other aspects of the peanut support

program. However, one of those

amendments erroneously purported to

amend ‘‘1444.307’’ rather than

‘‘1446.307.’’ That error is hereby

corrected. 7 CFR 1446.307 was the

section which was the intended site of

the amendment; 7 CFR 1444.307 does

not exist.

Correction of Publication

Accordingly, the publication of

January 10, 2001 (66 FR 1807) of the

final regulations applicable to 7 CFR

part 1446 is corrected as follows:

On page 1810, in the first column, in

the heading and amendatory language of

the first sentence of the last paragraph

(item 4), the two references to

‘‘1444.307’’ are corrected to read

‘‘1446.307’’.

Signed at Washington, DC, on February 9,

2001.

James R. Little,

Acting Executive Vice President, Commodity

Credit Corporation.

[FR Doc. 01–3838 Filed 2–14–01; 8:45 am]

BILLING CODE 3410–05–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–11–AD; Amendment

39–12109; AD 2001–03–05]

RIN 2120–AA64

Airworthiness Directives; Learjet

Model 45 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 Learjet Model 45

airplanes. This action requires revising

the airplane flight manual (AFM) to

prohibit flight into known icing

conditions; inspecting the anti-ice

manifold assembly for missing material,

and performing corrective actions if

necessary; replacing the anti-ice

manifold assembly with a new

assembly, which terminates the AFM

revision requirement; and revising the

Learjet 45 maintenance program to

incorporate additional inspections and

maintenance practices for the anti-ice

manifold assembly. This action is

necessary to prevent metal fragments

from breaking off the anti-ice manifold

assembly due to fatigue, which could

block a duct in the anti-ice system and

result in an unannunciated loss of ice

protection. This action is intended to

address the identified unsafe condition.

DATES: Effective February 20, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

20, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

April 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

11–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

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-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2001–NM–11–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 Learjet,

Inc., One Learjet Way, Wichita, Kansas

67209–2942. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Robert Busto, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas 67209; telephone (316)

946–4157; fax (316) 946–4407.

SUPPLEMENTARY INFORMATION: The FAA

has been advised that a Learjet Model 45

airplane recently experienced anti-ice

system difficulties, generating a warning

to the flight crew of an overheat

condition of the horizontal stabilizer.

Subsequent inspection revealed a

fragment of metal from the system’s

bleed air manifold lodged in a section

of the system’s ducts. Inspection of

other airplanes revealed fatigue cracking

on the manifold splitter vanes.

The anti-ice system on Model 45

airplanes incorporates a bleed airflow

manifold to deliver air to the wing and

horizontal stabilizer piccolo tubes. The

manifold contains a set of internal

splitter vanes, which recent inspections

indicate are subject to premature fatigue

cracking. The vanes are inadequately

welded and subject to engine bleed

airflow at high temperatures.

10354 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Rules and Regulations

Consequently, the vanes are susceptible

to fatigue caused by turbulent airflow

traveling within the manifold. Metal

pieces of the vanes may break off and

become lodged in the anti-ice system

downstream of the leading edge skin

temperature sensors. This condition, if

not corrected, could result in an

unannunciated loss of ice protection.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Learjet 45 Temporary Flight Manual

Change TFM 2000–16, dated January 8,

2001, which prohibits flight into icing

conditions until the airplane’s anti-icing

system has been inspected and

modified, as described below.

The FAA has reviewed and approved

Bombardier (Learjet 45) Alert Service

Bulletin SB A45–30–2, dated December

18, 2000. The alert service bulletin

describes procedures for a one-time

inspection to detect missing pieces of

the manifold assembly splitter. If

fragments are missing from the splitter,

the service bulletin recommends

borescopic inspections to detect debris

in the anti-ice tube assemblies within

the wing and horizontal stabilizer antiice system, and removal of any splitter

debris. The alert service bulletin also

describes procedures for replacing the

anti-ice manifold assembly with a new

assembly.

The manufacturer has issued

Temporary Revisions (TR) 4–2, 5–2, and

30–1, all dated January 2, 2001, for the

Learjet 45 maintenance program

manual. TR’s 4–2 and 5–2 add

borescopic inspections of the anti-ice

manifold. TR 30–1 adds certain

maintenance practices for the removal,

installation, and inspection of the antiice manifold assembly. The TR’s are to

be incorporated into the Learjet

maintenance program manual to revise

the Learjet maintenance program.

Accomplishment of the actions

specified in the AFM revision, alert

service bulletin, and maintenance

program revisions is intended to

adequately address the identified unsafe

condition.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent metal fragments of the splitter

in the anti-ice system from breaking due

to fatigue, which could block a duct in

the anti-ice system and result in an

unannunciated loss of ice protection.

This AD requires accomplishment of the

actions specified in the AFM revision,

alert service bulletin, and maintenance

program revisions described previously,

except as discussed below.

Difference Between AD and Alert

Service Bulletin

This AD requires replacement of the

anti-ice manifold assembly within 100

flight hours, whereas the alert service

bulletin recommends replacement

within 25 flight hours. At the time the

alert service bulletin was developed, the

shorter compliance time was

recommended because of the urgency of

the unsafe condition and the lack of

available interim procedures developed

to prohibit flight into known icing

conditions until the manifold is

replaced. In developing an appropriate

compliance time for this AD, the FAA

considered the safety implications as

well as subsequent recommendations

from the manufacturer. The FAA finds

that 100 flight hours represents an

appropriate interval of time allowable

for affected airplanes to continue to

operate without compromising safety.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket 2001–NM–11–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it 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.

A copy of it, if filed, 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 Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Rules and Regulations 10355

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:

2001–03–05 Learjet: Amendment 39–12109.

Docket 2001–NM–11–AD.

Applicability: Model 45 airplanes,

certificated in any category, serial numbers

45–002 through 45–004 inclusive, 45–006

through 45–121 inclusive, and 45–124

through 45–129 inclusive.

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 (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 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 metal fragments from breaking

off the anti-ice manifold assembly due to

fatigue, which could block a duct in the antiice system and result in an unannunciated

loss of ice protection, accomplish the

following:

Revision of Airplane Flight Manual (AFM)

(a) Within 24 hours after the effective date,

and until accomplishment of the

requirements of paragraph (b) of this AD:

Revise the Limitations section of the FAAapproved AFM by replacing the existing

information in the TYPE OF OPERATION

section with the following. This may be

accomplished by inserting a copy of this AD

into the AFM.

‘‘This airplane is approved for:

• VFR (Visual)

• IFR (Instrument)

• Day

• Night

Flight into icing conditions is prohibited.

If icing conditions are encountered, comply

with the Inadvertent Icing Encounter

procedure, Section IV. Fly out of icing

conditions as soon as possible.

Icing conditions exist when outside air

temperature (OAT) on the ground and for

takeoff is 10°C (50°F) or below, or the static

air temperature (SAT) in flight is 10°C (50°F)

to ¥40°C (¥40°F), and visible moisture in

any form is present (such as clouds, fog with

visibility of one mile or less, rain, snow,

sleet, or ice crystals).

Icing conditions also exist when the OAT

on the ground and for takeoff is 10°C (50°F)

or below when operating on ramps, taxiways,

or runways where surface snow, ice, standing

water, or slush may be ingested by the

engines, or freeze on engines, nacelles, or

engine sensor probes.’’

Note 2: Insertion into the AFM of a copy

of Learjet 45 Temporary Flight Manual

Change (TFM) TFM 2000–16, dated January

8, 2001, is also acceptable for compliance

with the requirements of paragraph (a) of this

AD.

Anti-Ice Manifold Assembly Replacement

(b) Within 100 flight hours after the

effective date of this AD: Perform a general

visual inspection to detect missing pieces

from the splitter vanes of the manifold

assembly, perform all applicable corrective

actions (including borescopic inspections to

detect debris and removal of debris), and

replace the anti-ice manifold assembly with

a new assembly. Do the actions in accordance

with Bombardier (Learjet 45) Alert Service

Bulletin SB A45–30–2, dated December 18,

2000. When the manifold assembly has been

replaced, the TFM required by paragraph (a)

of this AD may be removed from the AFM.

Note 3: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Maintenance Program Revision

(c) Concurrently with the accomplishment

of the requirements of paragraph (b) of this

AD, revise the Learjet maintenance program

by incorporating the procedures for removal,

installation, and inspection of the anti-ice

manifold assembly specified in Learjet Model

45 Maintenance Manual Temporary

Revisions 4–2, 5–2, and 30–1; all dated

January 2, 2001.

(d) When the temporary revisions required

by paragraph (c) of this AD have been

incorporated into the general revisions of the

maintenance program, the general revisions

may be incorporated into the maintenance

program, provided that the information

contained in the general revisions is identical

to that specified in the temporary revisions.

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, Wichita

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, Wichita ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita 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, provided the airplane

is restricted from flight into known icing

conditions.

Incorporation by Reference

(g) Except as required by paragraph (a) of

this AD: The actions shall be done in

accordance with Bombardier (Learjet 45)

Alert Service Bulletin SB A45–30–2, dated

December 18, 2000; Learjet 45 Maintenance

Manual Temporary Revision 4–2, dated

January 2, 2001; Learjet 45 Maintenance

Manual Temporary Revision 5–2, dated

January 2, 2001; and Learjet 45 Maintenance

Manual Temporary Revision 30–1, dated

January 2, 2001; as applicable. The actions

required by paragraph (a) of this AD may also

be done in accordance with Learjet 45

Temporary Flight Manual Change TFM

2000–16, dated January 8, 2001. 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 Learjet,

Inc., One Learjet Way, Wichita, Kansas

67209–2942. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Effective Date

(h) This amendment becomes effective on

February 20, 2001.

Issued in Renton, Washington, on February

7, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3671 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–16–AD; Amendment

39–12096; AD 2001–02–11]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 204B

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for