Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Proposed Rules 21893

airworthiness directive 1–162, dated

November 30, 2000, in order to assure

the continued airworthiness of these

airplanes in Sweden.

FAA’s Conclusions

This airplane model is manufactured

in Sweden 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 LFV has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LFV,

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 3 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

testing, 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

$360, or $120 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 proposed AD were not adopted. The

cost impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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

adding the following new airworthiness

directive:

SAAB Aircraft AB: Docket 2001–NM–12–

AD.

Applicability: Model SAAB 2000 series

airplanes, certificated in any category, serial

numbers –004 through –063, 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 faulty activation of the

emergency pitch trim actuator (EPTA), which

could cause damage to the elevator front

spar, resulting in reduced structural integrity

of the elevator and a non-functioning

emergency pitch trim system (EPTS),

accomplish the following:

Testing and Corrective Actions

(a) Within 400 flight hours from the

effective date of this AD, perform a

functional test of the EPTS in accordance

with Saab Service Bulletin 2000–27–046,

dated November 30, 2000. If the left or right

EPTA is not working according to the

functional test, before further flight, check

the wiring and perform all applicable followon corrective actions, in accordance with

paragraph 2. C. of Saab Service Bulletin

2000–27–046, dated November 30, 2000.

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, Transport

Airplane Directorate, FAA. 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

(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 3: The subject of this AD is addressed

in Swedish airworthiness directive 1–162,

dated November 30, 2000.

Issued in Renton, Washington, on April 26,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10941 Filed 5–1–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–412–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2 and B4; A310; and A300 B4–

600, B4–600R, and F4–600R

(Collectively Called A300–600) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

21894 Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Proposed Rules

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A300 B2 and B4;

A310; and A300 B4–600, B4–600R, and

F4–600R (collectively called A300–600)

series airplanes. This proposal would

require modification of certain

components related to the fuel level

sensors. This action is necessary to

prevent the possibility of overheating of

the fuel level sensors, which could lead

to the risk of explosion in the fuel tank.

This action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

June 1, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

412–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-nprmcomment@faa.gov.

Comments sent via fax or the Internet

must contain ‘‘Docket No. 2000–NM–

412–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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1175;

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 action 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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–412–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–412–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for, notified the

FAA that an unsafe condition may exist

on certain Airbus Model A300 B2 and

B4; A310; and A300 B4–600, B4–600R,

and F4–600R (collectively called A300–

600) series airplanes. The DGAC advises

that investigations by the manufacturer

have revealed that, if a 115V alternating

current (AC) short circuit occurs outside

of the fuel tanks, in the wiring that is

routed with the fuel level sensor

harnesses, the sensing element in the

fuel level sensors could overheat. This

overheating of the sensors could cause

possible ignition of the fuel tank vapors,

resulting in an explosion inside of the

fuel tank.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A300–28–0078, dated September 27,

2000, which describes procedures for

installing new fused fuel level sensors

and new harness connectors in the wing

inner and outer fuel tanks and the

center fuel tank on Model A300 B2 and

B4 series airplanes. Airbus has also

issued Service Bulletins A310–28–2141,

including Appendix 01; and A300–28–

6063; both dated September 27, 2000;

which describe procedures for installing

fused adapters for the fuel level sensors

between the aircraft external wiring

harness and the in-tank wiring at the

fuel tank wall connectors in Model

A310 and A300–600 series airplanes.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directive 2000–481–

324(B), dated November 29, 2000, in

order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France 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 DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

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 bulletins described

previously.

Cost Impact

The FAA estimates that 157 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately the number of work

hours per airplane specified in the table

below to accomplish the proposed

modifications, and that the average

Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Proposed Rules 21895

labor rate is $60 per work hour.

Approximate required parts costs and

costs per airplane are listed in the table

below:

Approximate Cost per Airplane

Airplane model Work hours Parts cost

Approximate

cost per

airplane

A300 B2, Post Modification 03082S4068 .................................................................................... 8 $18,241 $18,721

A300 B2, Pre Modification 03082S4068 ..................................................................................... 8 16,690 17,170

A300 B4, Post Modification 01664S2368 .................................................................................... 16 24,512 25,472

A300 B4, Pre Modification 01664S2368 ..................................................................................... 16 22,811 23,771

A310–200 ..................................................................................................................................... 10 11,972 12,572

A310–300 ..................................................................................................................................... 12 16,125 16,845

A300–600 ..................................................................................................................................... 2 3,805 3,925

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 proposed AD were not adopted. The

cost impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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

adding the following new airworthiness

directive:

Airbus Industrie: Docket 2000–NM–412–

AD.

Applicability: Model A300 B2 and B4

series airplanes; Model A310 series airplanes,

except those on which Airbus Modification

12201 has been embodied in production; and

Model A300 B4–600, B4–600R, and F4–600R

(collectively called A300–600) series

airplanes, except those on which Airbus

Modification 12202 has been embodied in

production; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 the possibility of overheating of

the fuel level sensors, which could lead to

the risk of explosion in the fuel tank,

accomplish the following:

Modification

(a) Within 18 months after the effective

date of this AD, modify the electrical

connectors to the fuel sensors by the

installation of new connectors and new

sensors, or fused adapters for the sensors, as

applicable, in accordance with the applicable

service bulletin listed in the following table:

TABLE 1.—APPLICABLE SERVICE BULLETINS

Airbus model series airplane Airbus service bulletin

No. Service bulletin date

(1) A300 B2 and B4 ................................................................................................................ A300–28–0078 ............... September 27, 2000.

(2) A310 .................................................................................................................................. A310–28–2141 ............... September 27, 2000.

(3) A300–600 .......................................................................................................................... A300–28–6063 ............... September 27, 2000.

Spare Parts

(b) As of the effective date of this AD, no person shall install on any airplane a part with any of the identifying numbers

listed in the following table:

21896 Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Proposed Rules

TABLE 2.—PROHIBITED SPARE PARTS

Airbus model series airplane Part Part No.

(1) A300 B2 and B4 ................................................................ Sensor ................................................................................... 718–054–1

(2) A300 B2 and B4 ................................................................ Sensor ................................................................................... 718–557

(3) A300 B2 and B4 ................................................................ Sensor ................................................................................... 718–055–1

(4) A300 B2 and B4 ................................................................ Connector .............................................................................. 852510R8T33SN02

(5) A310 .................................................................................. Connector .............................................................................. E0052R10B6SNE

(6) A310 .................................................................................. Connector .............................................................................. E0052R12B10SNE

(7) A310 .................................................................................. Connector .............................................................................. E0052R14B19SNE

(8) A300–600 .......................................................................... Connector .............................................................................. E0052R14B19SNE

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, Transport

Airplane Directorate, FAA. 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 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 3: The subject of this AD is addressed

in French airworthiness directive 2000–481–

324(B), dated November 29, 2000.

Issued in Renton, Washington, on April 25,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10940 Filed 5–1–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–53–AD]

RIN 2120–AA64

Airworthiness Directives; Honeywell

International Inc. TFE731–2, –3, and –4

Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: The Federal Aviation

Administration (FAA) proposes to

supersede two existing airworthiness

directives (ADs), applicable to

Honeywell International Inc. (formerly

AlliedSignal Inc. and Garrett Turbine

Engine Co.) TFE731–2, –3, and –4 series

turbofan engines. Those AD’s currently

require removing certain fan rotor discs

from service in accordance with a

drawdown schedule, and establishing

new fan rotor disc life limits. This

proposal would require stricter life

limits for certain fan rotor discs. This

proposal is prompted by the availability

of an improved fan rotor disc and by a

reduction in the probability of fan rotor

disc failure by terminating the life of the

older, high-stressed, fan rotor disc. The

actions specified in the proposed AD are

intended to prevent failure of the fan

disc due to fatigue cracking in the

dovetail slots, which could result in inflight engine shutdown, uncontained

engine failure, and damage to the

airplane.

DATES: Comments must be received by

July 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2000–NE–

53–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

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

via the Internet must contain the docket

number in the subject line. 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

the proposed rule may be obtained from

Honeywell Engines and Systems

(formerly AlliedSignal Inc. and Garrett

Turbine Engine Co.) Technical

Publications and Distribution, M/S

2101–201, P.O. Box 52170, Phoenix, AZ

85072–2170; telephone: (602) 365–2493

(General Aviation), (602) 365–5535

(Commercial Aviation), fax: (602) 365–

5577 (General Aviation), (602) 365–2832

(Commercial Aviation). 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:

Joseph Costa, Aerospace Engineer, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood CA

90712–4137; telephone: (562) 627–5246;

fax: (562) 627–5210.

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 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 action 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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NE–53–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRM’s

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–53–AD, 12 New