30538 Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–372–AD; Amendment

39–11721; AD 2000–09–12]

RIN 2120–AA64

Airworthiness Directives; Raytheon

(Beech) Model 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 400A and 400T series airplanes,

that requires replacement of

temperature switch assemblies of the

wing ice protection system with new,

improved parts. This amendment is

prompted by reports of electrical

continuity problems with solder joints

on the temperature switches of the wing

ice protection system. The actions

specified by this AD are intended to

prevent detachment or breakage of wires

in the temperature switch assemblies of

the wing ice protection system. Such

detachment or breakage of wires could

result in the flightcrew not being

advised of an over-temperature situation

on the leading edge of the wing, which

could result in structural damage to the

wing.

DATES: Effective June 16, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 16,

2000.

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, Small

Airplane Directorate, 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:

Philip Petty, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4139; 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 400A and 400T series

airplanes was published in the Federal

Register on January 12, 2000 (65 FR

1836). That action proposed to require

replacement of temperature switch

assemblies of the wing ice protection

system with new, improved parts.

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 404

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

366 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 30 work hours per

airplane to accomplish the required

replacement, and that the average labor

rate is $60 per work hour. Required

parts will be provided by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $658,800, or $1,800 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.

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

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:

2000–09–12 Raytheon Aircraft Company

(Formerly Beech): Amendment 39–11721.

Docket 99–NM–372–AD.

Applicability: Model 400A series airplanes,

having serial numbers RK–01 through RK–

188 inclusive; Model 400T (T–1A) series

airplanes, having serial numbers TT–01

through TT–180 inclusive; and Model 400T

(TX) series airplanes, having serial numbers

TX–01 through TX–09 inclusive; 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 (c) 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.

Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations 30539

To prevent detachment or breakage of

wires in the temperature switch assemblies of

the wing ice protection system, which could

result in the flightcrew not being advised of

an over-temperature situation on the leading

edge of the wing, and consequent structural

damage to the wing, accomplish the

following:

Replacement

(a) At the next scheduled inspection, but

no later than 200 flight hours after the

effective date of this AD, replace temperature

switch assemblies of the wing ice protection

system with new, improved temperature

switch assemblies, in accordance with

Raytheon Service Bulletin 30–3008, Revision

1, dated August 1999.

Note 2: Replacements accomplished prior

to the effective date of this AD in accordance

with Raytheon Service Bulletin 30–3008,

dated March 1999, are considered acceptable

for compliance with the applicable action

specified in this AD.

Spares

(b) As of the effective date of this AD, no

person shall install, on any airplane, a

temperature switch assembly having a part

number listed in the ‘‘Old Part Number’’

column of the table in 2.D. of Raytheon

Service Bulletin 30–3008, Revision 1, dated

August 1999.

Alternative Methods of Compliance

(c) 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,

Small Airplane Directorate. 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 Permits

(d) 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

(e) The replacement shall be done in

accordance with Raytheon Service Bulletin

30–3008, Revision 1, dated August 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, Small Airplane

Directorate, 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.

(f) This amendment becomes effective on

June 16, 2000.

Issued in Renton, Washington, on May 3,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11549 Filed 5–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–305–AD; Amendment

39–11718; AD 2000–09–09]

RIN 2120–AA64

Airworthiness Directives; EMBRAER

Model EMB–145 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain EMBRAER Model

EMB–145 series airplanes, that currently

requires revisions to the Airplane Flight

Manual (AFM) to provide the flight

crew with updated procedures for

prohibiting use of the autopilot below

1,500 feet above ground level,

emergency procedures for pitch trim

runaway, and abnormal procedures for

autopilot trim failure and stabilizer out

of trim. That AD also requires

installation of certain warning placards.

This amendment requires replacement

of a certain integrated computer with a

new integrated computer; installation of

an upgraded integrated computers

checklist; and removal of certain

placards and certain limitations in the

AFM. This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent failure of the pitch

trim system, which could cause

undetected autopilot trim runaway, and

consequent reduced controllability of

the airplane, uncommanded autopilot

disconnect, and excessive altitude loss.

DATES: Effective June 16, 2000.

The incorporation by reference of

EMBRAER Service Bulletin S.B. 145–

31–0010, dated March 18, 1999, as

listed in the regulations, is approved by

the Director of the Federal Register as of

June 16, 2000.

The incorporation by reference of

EMBRAER Alert Service Bulletin, S.B.

145–31–A010, dated December 15,

1998, as listed in the regulations, was

previously approved by the Director of

the Federal Register as of February 2,

1999 (64 FR 4521, January 29, 1999).

ADDRESSES: The service information

referenced in this AD may be obtained

from Empresa Brasileira de Aeronautica

S.A. (EMBRAER), P.O. Box 343—CEP

12.225, Sao Jose dos Campos—SP,

Brazil. 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, Small

Airplane Directorate, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Rob

Capezzuto, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; telephone (770) 703–6071; fax

(770) 703–6097.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–01–12,

amendment 39–11015 (64 FR 4521,

January 29, 1999), which is applicable

to certain EMBRAER Model EMB–145

series airplanes, was published in the

Federal Register on December 29, 1999

(64 FR 72964). The action proposed to

require revisions to the Airplane Flight

Manual to provide the flight crew with

updated procedures for prohibiting use

of the autopilot below 1,500 feet above

ground level, emergency procedures for

pitch trim runaway, and abnormal

procedures for autopilot trim failure and

stabilizer out of trim. That AD also

requires installation of certain warning

placards. This amendment requires

replacement of a certain integrated