21072 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

Cost Impact

There are approximately 159 Model

767–200 and –300 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 18 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 1 work

hour per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$482 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $9,756,

or $542 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this 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 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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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

adding the following new airworthiness

directive:

2001–08–22 Boeing: Amendment 39–12199.

Docket 2000–NM–296–AD.

Applicability: Model 767–200 and -300

series airplanes, as listed in Boeing Alert

Service Bulletin 767–38A0057, dated July 13,

2000; equipped with a potable water system;

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 fracture of a clamshell coupling

on the potable water fill line, which could

cause a large amount of water to flow into the

aft cargo compartment, and result in large

shifts in the airplane’s center of gravity and

consequent reduced controllability of the

airplane, accomplish the following:

Replacement

(a) Within 12 months after the effective

date of this AD, replace the existing potable

water fill line tube with a new flexible hose,

in accordance with Boeing Alert Service

Bulletin 767–38A0057, dated July 13, 2000.

Spares

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

person shall install a potable water fill line

tube, part number 417T2021–179, on any

airplane.

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.

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 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.

Incorporation by Reference

(e) The replacement shall be done in

accordance with Boeing Alert Service

Bulletin 767–38A0057, dated July 13, 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Effective Date

(f) This amendment becomes effective on

June 1, 2001.

Issued in Renton, Washington, on April 18,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10175 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–41–AD; Amendment

39–12198; AD 2001–08–21]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Lockheed Model L–

1011–385 series airplanes, that requires

a visual inspection of the fuel level

control switch, the fuel level control

switch wiring harness, and the wiring

harness conduit for damage, wear or

chafing, broken or missing O-rings, or

indications of electrical arcing. This

amendment also requires replacement of

a certain conduit in the fuel level

control switch wiring harness,

installation of electrical sleeving over

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21073

the fuel level control switch wiring

harness, and installation of the fuel

level control switch which has been so

modified. The actions specified by this

AD are intended to prevent chafing of

the fuel level control switch wiring

harness, which could cause arcing and

result in a fire in the fuel tank.

DATES: Effective June 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Lockheed Martin Aircraft &

Logistics Center, 120 Orion Street,

Greenville, South Carolina 29605. 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: Tom

Peters, Program Manager, ACE–116A,

FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; telephone (770) 703–6063; 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 all Lockheed Model

L–1011–385 series airplanes was

published in the Federal Register on

October 19, 2000 (65 FR 62651). That

action proposed to require a visual

inspection of the fuel level control

switch, the fuel level control switch

wiring harness, and the wiring harness

conduit for damage, wear or chafing,

broken or missing O-rings, or

indications of electrical arcing. This

amendment also requires replacement of

a certain conduit in the fuel level

control switch wiring harness,

installation of electrical sleeving over

the fuel level control switch wiring

harness, and installation of the fuel

level control switch which has been so

modified. Those actions are intended to

prevent chafing of the fuel level control

switch wiring harness, which could

cause arcing and result in a fire in the

fuel tank.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

One commenter requests that the

compliance time for the actions

specified by the proposed AD be revised

from ‘‘within 12 months after the

effective date of this AD,’’ to ‘‘within 18

months after the effective date of this

AD.’’ The commenter advises that

special equipment to drain and vent the

tanks and a specially trained crew are

necessary to perform the actions

specified in the proposed AD. The

commenter advises further that the

special equipment and trained crew are

only available at a maintenance base.

The commenter makes the case that by

extending the compliance time to

coordinate with the scheduled C-check

(at 18-month intervals) the number of

required fuel tank entries will be

minimized, and therefore, the risk of

damage to the tanks and the associated

internal and external components will

also be minimized.

The FAA agrees with the commenter

for the reasons stated by the commenter

and has revised the final rule

accordingly. We consider that such a 6-

month extension of the compliance time

will not have an adverse effect of the

safety of the fleet.

This same commenter also requests

that requirements of paragraph (a) of the

proposed rule be revised to clarify that

not all conduits should be replaced with

part number (P/N) 97590–121 conduits.

The commenter points out that not all

conduits can be replaced with a -121

conduit, as shapes and bends vary from

conduit to conduit. The commenter

notes that Lockheed Service Bulletin

093–28–094 (referenced in the NPRM as

the appropriate service information)

describes procedures for replacing only

conduit having P/N 97590–103 with

-121 conduit.

The FAA agrees with the request for

the reasons stated by the commenter.

We have revised the final rule by adding

a new paragraph (b) to clarify that only

conduit having P/N 97590–103 need to

be replaced with the -121 conduit.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 235 Model

L–1011–385 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 117 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 19 work

hours per airplane to accomplish the

required inspection, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$200 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$156,780, or $1,340 per airplane. hour.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this 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 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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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

21074 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

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

adding the following new airworthiness

directive:

2001–08–21 Lockheed: Amendment 39–

12198. Docket 2000–NM–41–AD.

Applicability: All Model L–1011–385

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 chafing of the fuel level control

switch wiring harness, which could cause

arcing and result in a fire in the fuel tank,

accomplish the following:

Inspection, Replacement, and Installation

(a) Within 18 months after the effective

date of this AD: Verify the part number (P/

N) of the wiring harness conduit and perform

a general visual inspection of the fuel level

control switch, the fuel level control switch

wiring harness, and the wiring harness

conduit to detect any visible damage, any

wear or chafing, broken or missing O-rings,

or indications of electrical arcing, in

accordance with the Accomplishment

Instructions in Lockheed Service Bulletin

093–28–094, dated March 3, 2000.

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.’’

(b) Prior to further flight after

accomplishment of the requirements in

paragraph (a) of this AD, accomplish the

actions specified in paragraphs (b)(1) and

(b)(2), as applicable; in accordance with the

Accomplishment Instructions in Lockheed

Service Bulletin 093–28–094, dated March 3,

2000.

(1) Install sleeving over each fuel level

control switch wiring harness and install the

modified fuel level control switch.

(2) If a conduit with P/N 97590–103 is

installed, replace the conduit with one

having P/N 97590–121, install sleeving over

each fuel level control switch wiring harness,

and install the modified fuel level control

switch.

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, 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.

Note 3: 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

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Lockheed Service Bulletin 093–28–094,

dated March 3, 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 Lockheed Martin Aircraft &

Logistics Center, 120 Orion Street,

Greenville, South Carolina 29605. Copies

may be inspected 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.

Effective Date

(f) This amendment becomes effective on

June 1, 2001.

Issued in Renton, Washington, on April 18,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10174 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–182–AD; Amendment

39–12202; AD 2001–08–25]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330–301, –321, –322, and –342 Series

Airplanes and Airbus Model A340

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A330–301, –321, –322, and –342 series

airplanes and certain Airbus Model

A340 series airplanes. This action

requires reinforcement of the wing

structure at the inboard pylon rear

pickup area. This action is necessary to

prevent fatigue cracking of the bottom

skin and reinforcing plate of the wing

due to bending, which could lead to

reduced structural integrity of the

airplane wing. This action is intended to

address the identified unsafe condition.

DATES: Effective May 14, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 14,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

May 29, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

182–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–182–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 Airbus

Industrie, 1 Rond Point Maurice