77782 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

(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.

(f) The inspections and modifications shall

be done in accordance with the

Accomplishment Instructions, paragraph A.,

of HR Textron Alert Service Bulletin No.

41000470–67A–05, Revision 1 or HR Textron

ASB No. 41105950–67A–01, Basic Issue, both

dated October 19, 2000, as applicable to the

affected actuator P/N. 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 HR Textron, 25200 W. Rye

Canyon Road, Santa Clarita, California

91355–1265, telephone (611) 294–6000, fax

(661) 259–9622. 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.

Note 4: BHTI ASB No.’s 205–00–79, 205B–

00–33, 212–00–109, 412–00–105, and

412CF–00–12, all dated October 19, 2000,

pertain to the subject of this AD and include

the applicable HR Textron Alert Service

Bulletins.

(g) This amendment becomes effective on

December 28, 2000.

Issued in Fort Worth, Texas, on November

30, 2000.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–31317 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–60–AD; Amendment

39–12038; AD 2000–25–04]

RIN 2120–AA64

Airworthiness Directives; Raytheon

(Beech) Model MU–300, MU–300–10,

400, 400A, and 400T Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon (Beech)

Model MU–300, MU–300–10, 400,

400A, and 400T series airplanes, that

requires a one-time inspection to detect

hydraulic fluid leakage from the B-nut

area, which attaches a hydraulic tube to

the anti-skid valve assembly, and

corrective actions, if necessary; and

installation of an additional support for

the hydraulic tube. This amendment is

intended to prevent an asymmetric

braking condition and a longer stopping

distance due to sudden loss of normal

braking to the left wheel. Such loss of

normal braking could result in the

airplane overrunning the runway

surface. This action is intended to

address the identified unsafe condition.

DATES: Effective January 17, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 17,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager Service Engineering, Beechjet/

Premier Technical Support Department,

P.O. Box 85, Wichita, Kansas 67201–

0085. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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: Paul

C. DeVore, 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) 946–4142; fax

(316) 946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Raytheon

(Beech) Model MU–300, MU–300–10,

400, 400A, and 400T series airplanes

was published in the Federal Register

on August 10, 2000 (65 FR 48945). That

action proposed to require a one-time

inspection to detect hydraulic fluid

leakage from the B-nut area, which

attaches a hydraulic tube to the antiskid valve assembly, and corrective

actions, if necessary; and installation of

an additional support for the hydraulic

tube.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 567 series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

522 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 2 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $31 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $78,822, or $151 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Additionally, the manufacturer has

indicated the warranty remedies may be

available to defer the cost of the

replacement parts also associated with

accomplishing this actions required by

this AD.

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.

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

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77783

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 the following new airworthiness

directive:

2000–25–04 Raytheon Aircraft Company

(Formerly Beech): Amendment 39–

12038. Docket 2000–NM–60–AD.

Applicability: Model MU–300, MU–300–

10, 400, 400A, and 400T series airplanes; as

listed in Raytheon Aircraft Service Bulletin

SB 32–3300, dated December 1999;

certificated in any category.

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 (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 as indicated, unless

accomplished previously.

To prevent an asymmetric braking

condition and a longer stopping distance due

to sudden loss of normal braking to the left

wheel, which could result in the airplane

overrunning the runway surface, accomplish

the following:

General Visual Inspection

(a) Within 200 flight hours after the

effective date of this AD, perform a one-time

general visual inspection to detect hydraulic

fluid leakage from the B-nut area, which

attaches a hydraulic tube to the anti-skid

valve assembly, in accordance with Raytheon

Aircraft Service Bulletin SB 32–3300, dated

December 1999.

Note 2: 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.’’

(1) If no leakage is found, prior to further

flight, install an additional support (i.e., new

nutplate, clamp, and screw) for the hydraulic

tube; in accordance with the service bulletin.

(2) If any leakage is found, prior to further

flight, replace the hydraulic tube with a new

or serviceable hydraulic tube, and install an

additional support (i.e., new nutplate, clamp,

and screw) for the hydraulic tube; in

accordance with the service bulletin.

Alternative Methods of Compliance

(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, 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permit

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The actions shall be done in accordance

with Raytheon Aircraft Service Bulletin SB

32–3300, dated December 1999. 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

Raytheon Aircraft Company, Manager Service

Engineering, Beechjet/Premier Technical

Support Department, P.O. Box 85, Wichita,

Kansas 67201–0085. 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, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

January 17, 2001.

Issued in Renton, Washington, on

December 4, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–31316 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–384–AD; Amendment

39–12039; AD 2000–25–05]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) Model EMB–135 and

EMB–145 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain EMBRAER Model

EMB–135 and EMB–145 series

airplanes, that currently requires a onetime inspection of the coupling hinge

and locking fastener of the Gamah

couplings of the fuel system tubing

located in the wing dry bay to detect

discrepancies, and follow-on corrective

actions. This amendment retains those

requirements and adds a requirement to

revise the applicability of the existing

AD to add certain airplanes. The actions

specified in this AD are intended to

prevent failure of the rivets of the

Gamah couplings and consequent

separation of a Gamah coupling, which

could result in fuel leakage and

consequent fire in or around the wing.

This action is intended to address the

unsafe condition.

DATES: Effective December 28, 2000.

The incorporation by reference of a

certain publication listed in the

regulations, was approved previously by

the Director of the Federal Register as of

October 3, 2000, (65 FR 56231,

September 18, 2000).

Comments for inclusion in the Rules

Docket must be received on or before

January 12, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

384–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this