Federal Register / Vol. 65, No. 113 / Monday, June 12, 2000 / Proposed Rules 36803

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

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 39–11522 (65 FR

3799, January 25, 2000), and by adding

a new airworthiness directive (AD), to

read as follows:

Airbus Industrie: Docket 2000–NM–104–AD.

Supersedes AD 2000–02–04, Amendment

39–11522.

Applicability: Model A300 B2–203 and

B4–203 series airplanes in a forward facing

cockpit version, as listed in Airbus Service

Bulletin A300–22A0115, Revision 02, dated

March 7, 2000; and all Model A300–600 and

A310 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 a sudden change in pitch due

to an out-of-trim condition combined with an

autopilot disconnect, which could result in

reduced controllability of the airplane,

accomplish the following:

Repetitive Inspections

(a) At the applicable time specified by

paragraph (a)(1) or (a)(2) of this AD: Perform

an inspection of the autotrim function by

testing the flight control computer (FCC)/

flight augmentation computer (FAC) integrity

in logic activation of the autotrim, in

accordance with Airbus Service Bulletin

A300–22A6042, Revision 01 (for Model

A300–600 series airplanes); A300–22A0115,

Revision 02 (for Model A300 series

airplanes); or A310–22A2053, Revision 01

(for Model A310 series airplanes); all dated

March 7, 2000; as applicable. If any

discrepancy is found, prior to further flight,

perform all applicable corrective actions

(including trouble-shooting, replacing the

FCC and/or FAC, retesting, checking the

wires between certain FCC and FAC pins,

and repairing damaged wires) in accordance

with the applicable service bulletin. Repeat

the inspection thereafter at intervals not to

exceed 500 flight hours.

(1) For airplanes on which the pitch trim

system test has been performed in

accordance with the requirements of AD

2000–02–04, amendment 39–11522: Inspect

within 500 flight hours after accomplishment

of the test required by that AD, or within 20

days after the effective date of this AD,

whichever occurs later.

(2) For all other airplanes: Inspect within

20 days after the effective date of this AD.

Reporting Requirement

(b) For all inspections required by

paragraph (a) of this AD: At the applicable

time specified by paragraph (b)(1) or (b)(2) of

this AD, submit a report of the inspection

results (both positive and negative findings)

to AI/SE-D32 Technical Data and

Documentation Services, Airbus Industrie

Customer Services Directorate, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex

France; fax (+33) 5 61 93 28 06.

(1) For inspections accomplished after the

effective date of this AD: Submit the report

within 10 days after performing the

inspection.

(2) For inspections 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

(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 International Branch,

ANM–116.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with §§ 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 3: The subject of this AD is addressed

in French airworthiness directive 2000–115–

304(B) R1, dated May 3, 2000.

Issued in Renton, Washington, on June 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14794 Filed 6–9–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–107–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–300, –400, and –500 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

Boeing Model 737–300, –400, and –500

series airplanes. This proposal would

require replacement of the existing

autothrottle computer with a new,

improved autothrottle computer. This

proposal is prompted by reports of

asymmetric thrust conditions during

flight caused by irregular autothrottle

operation in which the thrust levers

slowly move apart causing the airplane

36804 Federal Register / Vol. 65, No. 113 / Monday, June 12, 2000 / Proposed Rules

to bank excessively and go into a roll.

The actions specified by the proposed

AD are intended to prevent such

conditions, which could result in loss of

control of the airplane.

DATES: Comments must be received by

July 27, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

107–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.

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Thanh Truong, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2552; fax (425) 227–1181.

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.

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–107–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–107–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports on

certain Boeing Model 737–300, –400,

and –500 series airplanes indicating an

asymmetric thrust condition caused by

irregular autothrottle operation, in

which the thrust levers slowly move

apart causing the airplane to bank and

roll. This thrust condition exceeds the

autopilot roll authority and results in a

bank angle of more than 30 degrees. In

one incident, the airplane rolled more

than 46 degrees without crew

recognition. Without pilot intervention,

an airplane that has asymmetric thrust

can bank excessively and go into a roll.

Such conditions, if not corrected, could

result in loss of control of the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 737–

22A1130, dated September 24, 1998,

which describes procedures for

replacement of the existing autothrottle

computer with a new, improved

autothrottle computer. The improved

autothrottle computer disengages the

autothrottle if an asymmetric thrust

condition is detected, and prevents the

airplane from rolling to an excessive

bank angle.

Accomplishment of the actions

specified in the alert service bulletin is

intended to adequately address the

unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require accomplishment of the actions

specified in the alert service bulletin

described previously, except as

discussed below.

Differences Between Proposed Rule and

Alert Service Bulletin

Operators should note that this

proposed AD would require

replacement of the autothrottle

computer to be accomplished within

one year after the effective date of this

AD. The alert service bulletin

recommends that this replacement

should be accomplished ‘‘as soon as

manpower and materials are available.’’

However, in developing an appropriate

compliance time for the proposed

replacement, the FAA considered not

only the degree of urgency associated

with addressing the subject unsafe

condition, but also the number of

proposed requirements and the

availability of required parts. The FAA

has determined that one year represents

an appropriate interval of time

allowable wherein all of these actions

can be accomplished during scheduled

airplane maintenance and an ample

number of required parts will be

available for modification of the U.S.

fleet within the proposed compliance

period. The FAA also finds that such a

compliance time will not adversely

affect the safety of the affected

airplanes.

Cost Impact

There are approximately 1,974

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

799 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

replacement, and that the average labor

rate is $60 per work hour. Required

parts would cost between $1,400 and

$4,200 per airplane. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

between $1,460 and $4,260 per airplane.

The cost impact figures discussed

above are 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

Federal Register / Vol. 65, No. 113 / Monday, June 12, 2000 / Proposed Rules 36805

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

adding the following new airworthiness

directive:

Boeing: Docket 2000–NM–107–AD.

Applicability: All Model 737–300, –400,

and –500 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 a severe asymmetric thrust

condition during flight which could result in

loss of control of the airplane, accomplish the

following:

Replacement

(a) Within 1 year after the effective date of

this AD: Replace the existing autothrottle

computer with a new, improved autothrottle

computer in accordance with Boeing Alert

Service Bulletin 737–22A1130, dated

September 24, 1998.

Spares

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

person shall install on any airplane, an

autothrottle computer having part number

10–62017–1, –2, –3, –4, –5, –11, –21, –23,

–25, or –27.

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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permit

(d) Special flight permits may be issued in

accordance with §§ 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 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14793 Filed 6–9–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ASW–6]

Proposed Modification of Federal

Airways in the Vicinity of Dallas/Fort

Worth; TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This action proposes to

amend fourteen Federal airways in the

vicinity of Dallas/Fort Worth, TX. The

FAA is proposing this action to simplify

the airway structure, thereby, enhancing

the management of aircraft operations in

the area.

DATES: Comments must be received on

or before July 28, 2000.

ADDRESSES: Send comments on this

proposal in triplicate to: Manager, Air

Traffic Division, ASW–500, Docket No.

00–ASW–6, Federal Aviation

Administration, 2601 Meacham Blvd;

Fort Worth, TX 76193–0500. The official

docket may be examined in the Rules

Docket, Office of the Chief Counsel,

Room 916, 800 Independence Avenue,

SW., Washington, DC, weekdays, except

Federal holidays, between 8:30 a.m. and

5 p.m.

An informal docket may also be

examined during normal business hours

at the office of the Regional Air Traffic

Division, Federal Aviation

Administration, 2601 Meacham Blvd;

Fort Worth, TX 76193–0500.

FOR FURTHER INFORMATION CONTACT: Bil

Nelson, Airspace and Rules Division,

ATA–400, Office of Air Traffic Airspace

Management, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone: (202) 267–8783.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested parties are invited to

participate in this proposed rulemaking

by submitting such written data, views,

or arguments as they may desire.

Comments that provide the factual basis

supporting the views and suggestions

presented are particularly helpful in

developing reasoned regulatory

decisions on the proposal. Comments

are specifically invited on the overall

regulatory, aeronautical, economic,

environmental, and energy-related

aspects of the proposal.

Communications should identify the

airspace docket number and be

submitted in triplicate to the address

listed above. Commenters wishing the

FAA to acknowledge receipt of their

comments on this action must submit

with those comments a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Airspace Docket No. 00–

ASW–6.’’ The postcard will be date/

time stamped and returned to the

commenter. All communications

received on or before the specified

closing date for comments will be

considered before taking action on the

proposed rule. The proposal contained

in this action may be changed in light

of comments received. All comments

submitted will be available for

examination in the Rules Docket both

before and after the closing date for

comments. A report summarizing each

substantive public contact with FAA

personnel concerned with this

rulemaking will be filed in the docket.

Availability of NPRM

An electronic copy of this document

may be downloaded using a modem and

suitable communications software from

the FAA regulations section of the

Fedworld electronic bulletin board

service (telephone: 703–321–3339) or

the Government Printing Office’s

electronic bulletin board service

(telephone: 202–512–1661).

Internet users may reach the FAA’s

web page at http://www.faa.gov or the