Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules 40551

power and responsibilities among the

various levels of government. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation: (1)

Is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 39–11020 (64 FR

5588, February 4, 1999), and by adding

a new airworthiness directive (AD), to

read as follows:

Short Brothers, Plc: Docket 2000–NM–202–

AD. Supersedes AD 99–03–06,

Amendment 39–11020.

Applicability: All Model SD3–60 SHERPA

series airplanes, 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.

To prevent breakage of the power control

cable assemblies due to the inflexible

construction of the cable, which could result

in loss of engine power and consequent

reduced controllability of the airplane,

accomplish the following:

Inspection and Corrective Actions

(a) At the next scheduled heavy

maintenance inspection, but no later than

1,200 flight hours after the effective date of

this AD: Perform a one-time inspection to

determine the part number (P/N) of the

power control cable assemblies and pulleys

of the engine controls, in accordance with

Part A of the Accomplishment Instructions of

Shorts Service Bulletin SD3–60 SHERPA–76–

1, Revision 2, dated March 21, 2000.

(1) If any power control cable assembly

having P/N SD3–47–1091 or SD3–47–1094 is

found, prior to further flight, replace the

power control cable assembly with a new

power control cable assembly in accordance

with Part B of the Accomplishment

Instructions of the service bulletin.

(2) If any pulley having P/N C181605 is

found, prior to further flight, replace the

pulley with a new pulley in accordance with

Part C of the Accomplishment Instructions of

the service bulletin.

Spares

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

person shall install on the engine controls of

any airplane a cable assembly having P/N

SD3–47–1091 or SD3–47–1094, or any pulley

having P/N C181605.

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,

International Branch, ANM–116, FAA,

Transport 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, International

Branch, ANM–116.

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.

Issued in Renton, Washington, on June 26,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–16646 Filed 6–29–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–10–AD]

RIN 2120–AA64

Airworthiness Directives; Israel

Aircraft Industries, Ltd., Model Astra

SPX and 1125 Westwind Astra Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive

(AD) that is applicable to certain

Israel Aircraft Industries, Ltd., Model

Astra SPX and 1125 Westwind Astra

series airplanes. This proposal would

require a one-time inspection of the

position of the aileron autopilot servo

and attachment arm; follow-on actions;

and corrective actions, if necessary; and

installation of a stopper angle on the

servo bracket. This action is necessary

to prevent the control link of the aileron

autopilot servo from being driven

overcenter, which could result in roll

oscillations when the autopilot is

engaged. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

July 31, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

10–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may also be sent

via the Internet using the following

address: 9-anm-nprmcomment@faa.gov.

Comments sent via the Internet must

contain ‘‘Docket No. 2000-NM–10–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

the proposed rule may be obtained from

Galaxy Aerospace Corporation, One

Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

40552 Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

• 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 proposed 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 proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–10–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–10–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Administration of

Israel (CAAI), which is the

airworthiness authority for Israel,

notified the FAA that an unsafe

condition may exist on certain Israel

Aircraft Industries, Ltd., Model Astra

SPX and 1125 Westwind Astra series

airplanes. The CAAI advises that a tooshort attachment arm on an aileron

autopilot servo actuator can allow the

servo control link to be driven

overcenter. This condition, if not

corrected, could result in roll

oscillations when the autopilot is

engaged.

Explanation of Relevant Service

Information

The manufacturer has issued Astra

(Israel Aircraft Industries) Alert Service

Bulletin 1125–27A–157, dated

September 14, 1999. The service

bulletin describes procedures for a onetime inspection of the aileron autopilot

servo and attaching linkage to determine

whether the attachment arm on the

autopilot servo is in the correct position.

For any attachment arm that is not in

the correct position, the service bulletin

describes procedures for a one-time

inspection to detect damage (including

gouges and scratches) of the bellcrank

arm, control link, and servo attachment

arm; follow-on actions; and corrective

actions, if necessary. The follow-on and

corrective actions include repositioning

the servo attachment arm to the correct

position, and repairing or replacing

damaged parts with new parts

depending on the extent of damage

found. The service bulletin also

describes procedures for installing a

stopper angle on the servo bracket.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The CAAI

classified this service bulletin as

mandatory and issued Israeli

airworthiness directive 27–99–10–06R1,

dated November 17, 1999, in order to

assure the continued airworthiness of

these airplanes in Israel.

FAA’s Conclusions

These airplane models are

manufactured in Israel and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the CAAI has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAAI,

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 Requirements of

Proposed 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, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 38 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $100 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $8,360, or

$220 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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 proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules 40553

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Israel Aircraft Industries, Ltd.: Docket 2000–

NM–10–AD

Applicability: Model Astra SPX and

1125 Westwind Astra series airplanes;

certificated in any category; serial

numbers 030, and 042 through 086

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 (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 the control link of the aileron

autopilot servo from being driven overcenter,

which could result in roll oscillations when

the autopilot is engaged, accomplish the

following:

Inspection and Corrective Actions

(a) Within 50 flight hours after the effective

date of this AD, perform a one-time general

visual inspection of the aileron autopilot

servo and attaching linkage to determine

whether the attachment arm on the servo is

in the correct position, in accordance with

Astra (Israel Aircraft Industries) Alert Service

Bulletin 1125–27A–157, dated September 14,

1999.

(1) If the attachment arm is in the correct

position, prior to further flight, install a

stopper angle on the servo bracket in

accordance with the alert service bulletin.

(2) If the attachment arm is in the incorrect

position, prior to further flight, perform a

general visual inspection to detect damage of

the bellcrank arm, control link, and

attachment arm, in accordance with the alert

service bulletin. Prior to further flight after

accomplishment of all applicable corrective

actions specified by this paragraph, install a

stopper angle on the servo bracket in

accordance with the alert service bulletin.

(i) If no damage is detected, prior to further

flight, reposition the attachment arm in

accordance with the alert service bulletin.

(ii) If any damage is detected and the

damage is within the limits specified by the

alert service bulletin, prior to further flight,

repair the damaged part in accordance with

the alert service bulletin.

(iii) If any damage is detected and the

damage exceeds the limits specified by the

alert service bulletin, prior to further flight,

replace the damaged part with a new part in

accordance with the alert service bulletin.

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.’’

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,

International Branch, ANM–116, FAA,

Transport 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

Note 4: The subject of this AD is addressed

in Israeli airworthiness directive 27–99–10–

06R1, dated November 17, 1999.

Issued in Renton, Washington, on June 26,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–16645 Filed 6–29–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–364–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–300 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Dornier Model 328–300 series airplanes.

This proposal would require revising

the Airplane Flight Manual. This action

is necessary to prevent an undetected

dragging parking brake, and consequent

decreased acceleration during the

takeoff roll, increased takeoff distance,

and possible runway overrun. This

action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

July 31, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

364–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may also be sent

via the Internet using the following

address: 9-anm-nprmcomment@faa.gov.

Comments sent via the Internet must

contain ‘‘Docket No. 99–NM–364–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

the proposed rule may be obtained from

FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–