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–

40554 Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules

82230 Wessling, Germany. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

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 99–NM–364–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.

99–NM–364–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, notified the FAA that an

unsafe condition may exist on all

Dornier Model 328–300 series airplanes.

The LBA advises that, after using the

parking brake during a taxiing test, the

pilot noticed that the brake did not

release completely. It was determined

that the parking brake may have been

used as a brake pressure metering

device while the airplane was moving.

Such improper use of the parking brake

could lead to a dragging brake, which

would not be detected by the takeoff

configuration warning in the airplane.

An undetected dragging parking brake,

if not corrected, could result in

decreased acceleration during the

takeoff roll, increased takeoff distance,

and possible runway overrun.

Explanation of Relevant Service

Information

Dornier has issued All Operators

Telefax AOT–328J–32–001, dated

September 9, 1999, which advises of a

revision to the Airplane Flight Manual

(AFM) to prohibit use of the parking

brake for braking, except in emergency

situations. The LBA classified the AOT

as mandatory and issued German

airworthiness directive 1999–352, dated

November 18, 1999, in order to assure

the continued airworthiness of these

airplanes in Germany.

FAA’s Conclusions

This airplane model is manufactured

in Germany and is 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 LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

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

revising the AFM to prohibit use of the

parking brake for braking, except in

emergency situations.

Difference Between Proposed AD and

the German Airworthiness Directive

Operators should note that, although

the LBA has mandated that the AFM be

revised prior to the next flight, the FAA

has determined that an interval of 10

days would address the identified

unsafe condition in a timely manner

while allowing operators sufficient time

to implement the AFM revision

proposed by this AD.

Cost Impact

The FAA estimates that 7 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per airplane

to accomplish the proposed AFM

revision, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$420, or $60 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Federal Register / Vol. 65, No. 127 / Friday, June 30, 2000 / Proposed Rules 40555

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:

Dornier Luftfahrt GMBH: Docket 99–NM–

364–AD.

Applicability: All Model 328–300 series

airplanes, certificated in any category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent an undetected dragging parking

brake, and consequent decreased acceleration

during the takeoff roll, increased takeoff

distance, and possible runway overrun,

accomplish the following:

AFM Revision

(a) Within 10 days after the effective date

of this AD: Revise the Limitations Section of

the FAA-approved Airplane Flight Manual

by inserting a copy of Dornier 328J All

Operators Telefax AOT–328J–32–001, dated

September 9, 1999.

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 Operations

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 1: 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 2: The subject of this AD is addressed

in German airworthiness directive 1999–352,

dated November 18, 1999.

Issued in Renton, Washington, on June 26,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–16644 Filed 6–29–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–21–AD]

RIN 2120–AA64

Airworthiness Directives; International

Aero Engines AG V2500–A5/D5 Series

Turbofan Engines

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 International Aero Engines (IAE)

V2500–A5/D5 series turbofan engines,

identified by serial number. This

proposal would require the removal of

engines assembled with an improper

High Pressure Turbine (HPT) module

configuration from service prior to

accumulating 5,100 or 7,600 cycles in

the improper configuration, or at the

next shop visit, depending on the type

of improper HPT configuration, and

restoration to type design. This

proposed amendment is prompted by

reports of engines that do not conform

to the engine type design, which could

cause a Low Cycle Fatigue (LCF) life

reduction of the HPT stage 1 disk. The

actions specified by the proposed AD

are intended to restore engines to type

design configuration and to prevent

possible LCF failure of the HPT stage 1

disk, which could result in an

uncontained engine failure and damage

to the airplane.

DATES: Comments must be received by

July 31, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–21–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

submitted to the Rules Docket by using

the following Internet address: ‘‘9-aneadcomment@faa.gov’’. Comments may

be inspected at this location between 8

a.m. and 4:30 p.m., Monday through

Friday, except Federal holidays. The

service information referenced in this

AD may be obtained from International

Aero Engines, 400 Main Street, East

Hartford, CT 06108; telephone (860)

565–5515; fax (860) 565–5510. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Diane Cook, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone 781–238–7133, fax

781–238–7199.

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

should identify the Rules Docket

number and be submitted 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.

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–NE–21–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–21–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports that during

recent shop visits at various overhaul

and repair facilities, 32 V2500–A5/D5

series engines have been assembled

with improper HPT module

configurations. The improper HPT

assemblies resulted from incorrect or

incomplete incorporation of several IAE

service bulletins (SB) required for

proper assembly of the high secondary

cooling airflow HPT stage 1 turbine

blades and cooling duct, which were