66612 Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations

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

November 22, 2000.

Issued in Fort Worth, Texas, on October 30,

2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–28437 Filed 11–7–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–204–AD; Amendment

39–11956; AD 2000–22–10]

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

various inspections to detect

discrepancies of the elevator servo tab

and spring tab hinge fittings of the

horizontal stabilizer, and follow-on

corrective actions, if necessary. This

amendment clarifies certain fiberscopic

inspection and replacement procedures,

and corrective actions; revises the

applicability of the existing AD; and

adds an inspection procedure for the

servo tab center hinge fittings to detect

the presence of washers for both

attaching fasteners, and follow-on

corrective actions, if necessary. This

amendment also provides for optional

terminating action for the repetitive

inspections. The actions specified in

this AD are intended to prevent the

linkage of the elevator servo tab or

spring tab hinge fittings from separating

from the horizontal stabilizer, which

could result in loss of control of the

airplane.

DATES: Effective November 22, 2000.

The incorporation by reference of

Embraer Service Bulletin 145–55–0024,

dated May 25, 2000, as listed in the

regulations, is approved by the Director

of the Federal Register as of November

22, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

December 7, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

204–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. 2000–NM–204–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 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

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, 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:

Viswa Padmanabhan, Aerospace

Engineer, Airframe and Propulsion

Branch, ACE–117A, FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia 30337–2748;

telephone (770) 703–6049; fax (770)

703–6097.

SUPPLEMENTARY INFORMATION: On

February 15, 2000, the FAA issued AD

2000–04–09, amendment 39–11591 (65

FR 9217, February 24, 1000), applicable

to certain EMBRAER Model EMB–135

and EMB–145 series airplanes, to

require various inspections to detect

discrepancies of the elevator servo tab

and spring tab hinge fittings of the

horizontal stabilizer, and follow-on

corrective actions, if necessary. That

action was prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

required by that AD are intended to

prevent the linkage of the elevator servo

tab or spring tab hinge fittings from

separating from the horizontal stabilizer,

which could result in loss of control of

the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

Departmento de Aviacao Civil (DAC),

which is the airworthiness authority for

Brazil, has received new information

regarding the corrective action

necessary to address this unsafe

condition. As a result, the DAC has

issued the following Brazilian

airworthiness directives:

• 1999–09–01R2, dated May 1, 2000,

supersedes Brazilian airworthiness

directive 1999–09–01R1, dated October

25, 1999. This new revision was issued

to specify repetitive inspection intervals

and final rework of certain components.

Part III of this revision specifies that, for

certain Model EMB–135 and EMB–145

series airplanes, certain modifications of

the elevator mass balance assembly and

control column nose-up spring

modifications, in accordance with

Embraer Service Bulletin (S.B.) 145–27–

0034, must be completed before

accomplishment of the rework specified

in Part III of S.B. 145–55–0022, Change

01, dated January 25, 2000.

• 2000–05–01, dated May 25, 2000,

corrects any possible misinterpretation

of the replacement procedures included

in Brazilian airworthiness directive

1999–09–01R2, and in alert S.B. 145–

55–A022 and S.B. 145–55–0022.

Reports indicated that loose hinge

fittings were found, which was

attributed to the incorrect application of

the attachment fasteners to the tab

upper skin. It is considered that the loss

of fitting rigidity could cause damage to

the other fasteners in the tab spar.

Reports also indicated that some of the

fasteners (which attach the spring-tab

actuating arm to the tab upper skin and

the servo-tab actuating linkage hinge to

the tab lower skin) were not replaced

with fasteners having a washer, because

the collar conformation of those

fasteners was found to be correct. In

addition, maintenance records revealed

that such fasteners may not have been

replaced on certain airplanes. As a

result of these findings, the DAC issued

the previously referenced Brazilian

airworthiness directives to clarify that

all attachment fasteners must be

installed with a washer, and that the

fasteners must be replaced

independently of the installation

condition (even if the collar

conformation is found to be ‘‘correct’’).

FAA’s Conclusions

These airplane models are

manufactured in Brazil and are type

certificated for operation in the United

States under the provisions of section

Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations 66613

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Relevant Service

Information

Embraer has issued the following

service information:

• Service Bulletin 145–55–0022,

Change 02, dated May 4, 2000, adds a

fiberscopic inspection in Part II of the

Accomplishment Instructions to detect

the presence of a washer; and

installation of a washer, if necessary.

Part III of this service bulletin revises

certain rework procedures (including

rework and installation of the elevator

servo and spring tabs; and

reidentification, static balancing, and

installation of the elevator). This rework

procedure also specifies that, for certain

airplanes, the modification specified by

Embraer S.B. 145–27–0034 must be

accomplished before Part III of S.B. 145–

55–0022, Change 02, is accomplished.

Accomplishment of the actions

specified in Part III of S.B. 145–55–

0022, Change 02, eliminates the need for

the repetitive inspections.

• Service Bulletin 145–55–0024, dated

May 25, 2000, adds a fiberscopic

inspection of the attachment of the

servo tab center hinge fitting to the tab

skin in Part II of the Accomplishment

Instructions of this service bulletin. This

inspection specifies detecting the

presence of washers under the collar

bases of both attaching fasteners, in the

inner side of the tab skin; and corrective

actions, if necessary. Procedures include

additional action to clarify certain

replacement procedures that were

specified in alert S.B. 145–55–A022,

Change 01, dated October 7, 1999, and

Change 02, dated October 8, 1999. Such

action specifies that any discrepant

fastener must be replaced with a new

fastener having a washer, and that the

action if required to be accomplished

independently of the installation

condition. In addition, S.B. 145–55–

0024 specifies that operators report any

discrepancy found during inspections of

elevator spring tab and servo tab hinge

fittings that are specified in Part I of the

Accomplishment Instructions of the

service bulletin.

• Service Bulletin 145–27–0034,

Change 01, dated August 5, 1998,

revises procedures for replacing the

elevator mass-balance weight assembly

and nose-up spring. Procedures also

revise static balancing and weight and

balance, add new mass-balance weight

and its attachment bolt, and delete the

instruction for checking the backlash.

The DAC mandated compliance with

the preceding service bulletins, and

issued previously referenced Brazilian

airworthiness directive 1999–09–01R2

in order to assure the continued

airworthiness of these airplanes in

Brazil.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD supersedes AD 2000–04–

09 to continue to require various

inspections to detect discrepancies of

the elevator servo tab and spring tab

hinge fittings of the horizontal

stabilizer, and follow-on corrective

actions, if necessary. This amendment

clarifies certain fiberscopic inspection

and replacement procedures, and

corrective actions; revises the

applicability of the existing AD; and

adds an inspection procedure for the

servo tab center hinge fittings to detect

the presence of washers for both

attaching fasteners, and follow-on

corrective actions. This amendment also

provides for optional terminating action

for the repetitive inspections. In

addition, this amendment requires that

operators report to the manufacturer any

discrepancy found during any detailed

visual inspection accomplished in

accordance with S.B. 145–55–0024,

dated May 25, 2000. This AD requires

accomplishment of actions specified in

the service bulletin described

previously, except as discussed below.

Differences Between This AD, Brazilian

Airworthiness Directives, and Related

Service Information

Operators should note that, although

the previously referenced Brazilian

airworthiness directives and Embraer

service information specify that certain

rework actions are required, this AD

provides those actions as optional. The

FAA has determined that such action

may be required in subsequent

rulemaking action to provide sufficient

time for public comment.

Explanation of Changes to the

Applicability of AD 2000–04–09

The applicability of AD 2000–04–09

included all of the serial numbers for

Model EMB–135 and EMB–145 series

airplanes, as listed in alert S.B. 145–55–

A022, Change 02, dated October 8, 1999.

However, this AD revises the

applicability of this AD to those

airplanes listed in S.B. 145–55–0022,

Change 02, dated May 4, 2000, or S.B.

145–55–0024, dated May 25, 2000, and

those airplanes on which the elevator

servo tabs and spring tabs have been

replaced in accordance with alert S.B.

145–55–A022, Change 02, dated October

8, 1999, or S.B. 145–55–0022, Change

01, dated January 25, 2000.

Interim Action

This AD is considered to be interim

action. The FAA is currently

considering requiring the rework of all

elevator servo and spring tabs, which

will constitute terminating action for the

repetitive inspections required by this

AD action. However, such action will be

proposed in a separate rulemaking

action since the compliance time for the

rework is sufficiently long so that notice

and opportunity for prior public

comment will be practicable.

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.

66614 Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations

• 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 Number 2000–NM–204–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 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

removing amendment 39–11591 (65 FR

9217, February 24, 2000), and by adding

a new airworthiness directive (AD),

amendment 39–11956, to read as

follows:

2000–22–10 Empresa Brasileira de

Aeronautica S.A. (EMBRAER):

Amendment 39–11956. Docket 2000–

NM–204–AD. Supersedes AD 2000–04–

09, Amendment 39–11591.

Applicability: Model EMB–135 and EMB–

145 series airplanes, certificated in any

category, as listed in Embraer Service

Bulletin 145–55–0022, Change 02, dated May

4, 2000, or Embraer Service Bulletin 145–55–

0024, dated May 25, 2000; and those

airplanes on which the elevator servo tabs

and spring tabs have been replaced in

accordance with Embraer Alert Service

Bulletin 145–55–A022, Change 02, dated

October 8, 1999, or Embraer Service Bulletin

145–55–0022, dated October 20, 1999.

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)(1) 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 disconnection of the elevator

spring tab or servo tab hinge from their

attachments, which could result in loss of

elevator control and reduced controllability

of the airplane, accomplish the following:

Detailed Visual Inspection

(a) Within 20 flight hours after the effective

date of this AD, perform a detailed visual

inspection of the hinge fittings of the left and

right elevator spring tabs and servo tabs to

detect any discrepancy (including incorrect

attachment of the hinge fittings; signs of

scratches on painted surfaces of the tab spar;

detachment of hinge fitting from the tab; and

relative movement and gap between hinge

fittings and tab spars, and between the spring

tab spar or skin) in accordance with Part I of

the Accomplishment Instructions of Embraer

Service Bulletin (S.B.) 145–55–0024, dated

May 25, 2000.

Note 2: Inspections accomplished prior to

the effective date of this amendment, in

accordance with Part I of the

Accomplishment Instructions of S.B. 145–

55–0022, dated October 20, 1999, or Change

01, dated January 25, 2000, or alert S.B. 145–

55–A022, Change 02, dated October 8, 1999,

are considered acceptable for compliance

with the requirements of paragraph (a) of this

AD.

(1) If no discrepancy is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 100 flight hours until

accomplishment of either paragraph (b) or (c)

of this AD.

(2) If any discrepancy is detected, prior to

further flight, accomplish the action specified

by either paragraph (a)(2)(i) or (a)(2)(ii) of this

AD.

(i) Replace any discrepant elevator tab with

a new tab in accordance with the service

bulletin, and repeat the detailed visual

inspection thereafter at intervals not to

exceed 100 flight hours until

accomplishment of either the actions

required by paragraph (b) or the optional

terminating action specified by paragraph (c)

of this AD.

Note 3: The inspection and fastener

replacement actions required by paragraph

(b) of this AD do not constitute terminating

action for the requirements of this AD, but

only extend the inspection intervals from 100

to 400 flight hours.

(ii) Perform the optional terminating action

specified by paragraph (c) of this AD.

Note 4: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc. may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Inspection and Fastener Replacement

(b) Within 400 flight hours after the

effective date of this AD, perform a one-time

detailed visual inspection, using a fiberscope,

of the servo tab center hinge fitting to the tab

skin to detect any discrepancy (including the

absence of washers under the collar bases of

both attaching fasteners, and incorrect

fastener connection) in accordance with Part

II of the Accomplishment Instructions of S.B.

145–55–0024, dated May 25, 2000.

(1) If no discrepancy is detected, repeat the

inspection required by paragraph (a) of this

AD thereafter at intervals not to exceed 400

flight hours until accomplishment of the

optional terminating action specified by

paragraph (c) of this AD.

Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations 66615

(2) If any discrepancy is detected, prior to

further flight, replace, one at a time, each

affected fastener with a new fastener having

a washer, in accordance with the service

bulletin. Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 400 flight hours until

accomplishment of the optional terminating

action specified by paragraph (c) of this AD.

Note 5: Replacement of the attaching

fasteners one at a time will avoid the loss of

the servo tab or spring tab hinge fittings

position.

Optional Terminating Action

(c) Rework (including installation of the

elevator servo and spring tabs; and

reidentification, static balancing, and

installation of the elevator) of all elevator

servo and spring tabs in accordance with Part

III of the Accomplishment Instructions of

S.B. 145–055–0022, Change 02, dated May 4,

2000, constitutes terminating action for the

repetitive inspections required by this AD.

Model EMB–135 and EMB–145 series

airplanes having serial numbers 145004

through 145043, must accomplish the

modifications specified by S.B. 145–27–0034,

Change 01, dated August 5, 1998, prior to the

rework specified by this paragraph.

Note 6: Modifications of certain airplanes

specified in paragraph (c) of this AD,

accomplished before the effective date of this

amendment, in accordance with S.B. 145–

27–0034, dated April 3, 1998, are considered

acceptable for compliance with the

modification requirement in paragraph (c) of

this AD.

Reporting Requirement

(d) Submit a report of inspection findings

for any discrepancy detected during any

inspection required by paragraph (a) of this

AD to Empresa Brasileira de Aeronautica

S.A. (EMBRAER), P.O. Box 343—CEP 12.225,

Sao Jose dos Campos—SP, Brazil; at the

applicable time specified in paragraph (d)(1)

or (d)(2) of this AD. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(1) For airplanes on which any inspection

is accomplished after the effective date of

this AD: Submit the report within 10 days

after performing any detailed visual

inspection required by paragraph (a) of this

AD.

(2) For airplanes on which any inspection

has been accomplished prior to the effective

date of this AD: Submit the report within 10

days after the effective date of this AD.

Alternative Methods of Compliance

(e)(1) 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, Atlanta

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, Atlanta ACO.

(2) Alternative methods of compliance,

approved previously in accordance with AD

2000–04–09, amendment 39–11591, are

approved as alternative methods of

compliance with this AD.

Note 7: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta 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.

Incorporation by Reference

(g) The inspections shall be done in

accordance with Embraer Service Bulletin

145–55–0024, dated May 25, 2000. 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

Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA, 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.

Note 8: The subject of this AD is addressed

in Brazilian airworthiness directives 1999–

09–01R2, dated May 1, 2000, and 2000–05–

01, dated May 25, 2000.

Effective Date of This AD

(h) This amendment becomes effective on

November 22, 2000.

Issued in Renton, Washington, on October

27, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28087 Filed 11–6–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–121–AD; Amendment

39–11958; AD 2000–22–12]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) Model EMB–120 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain EMBRAER Model

EMB–120 series airplanes, that requires

replacement of the existing wire

between certain circuit breakers with an

improved wire. The actions specified by

this AD are intended to prevent

overheating of the wire between certain

circuit breakers, which could result in

smoke emissions in the cockpit. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 12, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

12, 2000.

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, 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:

Carla Worthey, Program Manager,

Program Management & Services

Branch, ACE–118A, FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia 30349; telephone

(770) 703–6062; fax (770) 703–6097.

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 EMBRAER

Model EMB–120 series airplanes, was

published in the Federal Register on