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

10356 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Rules and Regulations

Bell Helicopter Textron, Inc. (BHTI)

Model 204B helicopters that requires

replacing any main rotor mast assembly

(mast), part number (P/N) 204–011–

450–001, within 25 hours time-inservice (TIS). This amendment is

prompted by the crash of a restricted

category Model UH–1B helicopter due

to failure of a mast, P/N 204–011–450–

001. The same mast P/N is used on the

Model 204B helicopters. The actions

specified by this AD are intended to

prevent failure of the mast and

subsequent loss of control of the

helicopter.

EFFECTIVE DATE: March 22, 2001.

FOR FURTHER INFORMATION CONTACT:

Michael Kohner, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Certification Office, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5447, fax (817) 222–5783.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD for BHTI Model 204B

helicopters was published in the

Federal Register on October 2, 2000 (65

FR 58681). That action proposed

replacing any mast, P/N 204–011–450–

001, within 25 hours TIS.

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.

The FAA estimates that 15 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 10

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

$8,862 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$141,930.

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 FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, 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:

2001–02–11 Bell Helicopter Textron, Inc.:

Amendment 39–12096. Docket No. 2000-

SW–16-AD.

Applicability: Model 204B helicopters with

main rotor mast assembly, part number (P/N)

204–011–450–001, 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 (b) 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 within 25 hours

time-in-service, unless accomplished

previously.

To prevent failure of the main rotor mast

assembly (mast) and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Remove any mast, P/N 204–011–450–

001, from service and replace it with an

airworthy mast. Accomplishing the

requirement of this paragraph constitutes

terminating action for the requirements of

this AD. P/N 204–011–450–001 is not eligible

for installation on any helicopter.

(b) 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, Rotorcraft

Certification Office, 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, Rotorcraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(c) 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.

(d) This amendment becomes effective on

March 22, 2001.

Issued in Fort Worth, Texas, on January 19,

2001.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 01–3670 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–368–AD; Amendment

39–12110; AD 2001–03–06]

RIN 2120–AA64

Airworthiness Directives; Raytheon

(Beech) Model MU–300, MU–300–10,

400, and 400A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Raytheon (Beech) Model

MU–300, MU–300–10, 400, and 400A

series airplanes, that requires repetitive

inspections of the bleed air supply tube

assemblies for discrepancies; and

replacement of the bleed air tube

assembly with a new bleed air tube

assembly, if necessary. In lieu of

accomplishing the repetitive