30536 Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations

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 internal overheating and arcing

of circuit breakers and airplane wiring due to

long-term use and breakdown of internal

components of the circuit breakers, which

could result in smoke and fire in the flight

compartment and main cabin, accomplish

the following:

Inspection and Replacement, if Necessary

(a) Within 24 months after effective date of

this AD: Perform a one-time general visual

inspection of circuit breakers to determine

the manufacturer of the circuit breaker in

accordance with McDonnell Douglas Alert

Service Bulletin DC10–24A161, dated

October 29, 1999.

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.’’

(1) If no Wood Electric Corporation or

Wood Electric Division of Potter Brumfield

Corporation circuit breaker is found, no

further action is required by this paragraph.

(2) If any Wood Electric Corporation or

Wood Electric Division of Potter Brumfield

Corporation circuit breaker is found, at the

next scheduled maintenance visit, but not

later than 24 months after the effective date

of this AD, replace the circuit breaker with

a new circuit breaker in accordance with the

service bulletin.

Spares

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

person shall install, on any airplane, a circuit

breaker, part number 104–205–104, 104–210–

104, 104–215–104, 104–220–104, 104–225–

104, 104–230–104, 104–235–104, 104–250–

104, 447–205–102, 448–205–102, 505–205–

102, 506–205–102, 447–507–102, 448–507–

102, 505–507–102, 506–507–102, 447–210–

102, 448–210–102, 505–210–102, 506–210–

102, 447–215–102, 448–215–102, 505–215–

102, 506–215–102, 447–220–102, 448–220–

102, 505–220–102, 506–220–102, 447–225–

102, 448–225–102, 505–225–102, 506–225–

102, 448–235–102, 505–235–102, 506–235–

102.

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, Los

Angeles 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, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles 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 McDonnell Douglas Alert Service

Bulletin DC10–24A161, dated October 29,

1999. 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 Aircraft Group,

Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

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

Transport Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 16, 2000.

Issued in Renton, Washington, on May 3,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11544 Filed 5–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–362–AD; Amendment

39–11719; AD 2000–09–10]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 series airplanes, that requires

modification of certain electrical looms

of the nose and main landing gear and

modification of the rotor shaft

attachment of the nose and main

landing gear tachometers. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent erratic operation of the wheel

tachometers, which could result in

degradation of the braking performance,

and possible increased landing roll.

DATES: Effective June 16, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 16,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: 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 certain Airbus

Model A300–600 series airplanes was

published in the Federal Register on

February 24, 2000 (65 FR 9223). That

action proposed to require modification

of certain electrical looms of the nose

and main landing gear and modification

of the rotor shaft attachment of the nose

and main landing gear tachometers.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Federal Register / Vol. 65, No. 93 / Friday, May 12, 2000 / Rules and Regulations 30537

Cost Impact

The FAA estimates that 79 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 7 work

hours per airplane to accomplish the

required modification of the electrical

looms, at an average labor rate of $60

per work hour. Required parts will cost

approximately $687 per airplane. Based

on these figures, the cost impact of the

modification of the electrical looms

required by this AD on U.S. operators is

estimated to be $87,453, or $1,107 per

airplane.

It will take approximately 13 work

hours per airplane to accomplish the

required modification of the rotor shaft

attachment, at an average labor rate of

$60 per work hour. Required parts will

cost approximately $169 per airplane.

Based on these figures, the cost impact

of the modification of the rotor shaft

attachment required by this AD on U.S.

operators is estimated to be $74,971, or

$949 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 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:

2000–09–10 Airbus Industrie: Amendment

39–11719. Docket 99–NM–362–AD.

Applicability: Model A300–600 series

airplanes, certificated in any category, except

those airplanes on which Airbus

Modifications 11661 and 11676 (Airbus

Service Bulletin A300–32–6069) and 12095

(Airbus Service Bulletin A300–32–6077)

have been installed.

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 (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 erratic operation of the wheel

tachometers, which could result in

degradation of the braking performance, and

possible increased landing roll, accomplish

the following:

Modifications

(a) Within 18 months after the effective

date of this AD, accomplish the requirements

of paragraphs (a)(1) and (a)(2) of this AD.

(1) Modify the electrical looms of the nose

and main landing gear, in accordance with

Airbus Service Bulletin A300–32–6069,

Revision 01, dated December 29, 1999; and

(2) Modify the rotor shaft attachment of the

nose and main landing gear tachometers, in

accordance with Airbus Service Bulletin

A300–32–6077, Revision 01, dated

September 25, 1999.

Note 2: Messier-Dowty Service Bulletins

470–32–779, dated April 14, 1997, and 470–

32–777, dated July 1, 1997, are referenced in

Airbus Service Bulletin A300–32–6069.

Messier-Bugatti Service Bulletin C20105–32–

782, dated October 17, 1996, is referenced in

Airbus Service Bulletin A300–32–6077. The

Messier-Dowty and Messier-Bugatti service

bulletins are additional sources of service

information for accomplishing the applicable

actions required by this AD.

Note 3: Accomplishment of the

modifications required by paragraph (a) of

this AD, prior to the effective date of this AD,

in accordance with Airbus Service Bulletin

A300–32–6069, dated June 13, 1997, or

A300–32–6077, dated May 28, 1999, is

considered acceptable for compliance with

the applicable requirements specified by this

AD.

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 4: 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.

Incorporation by Reference

(d) The modifications shall be done in

accordance with Airbus Service Bulletin

A300–32–6069, Revision 01, dated December

29, 1999; and Airbus Service Bulletin A300–

32–6077, Revision 01, dated September 25,

1999. 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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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.

Note 5: The subject of this AD is addressed

in French airworthiness directive 1999–428–

295(B), dated November 3, 1999.

(e) This amendment becomes effective on

June 16, 2000.

Issued in Renton, Washington, on May 3,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11548 Filed 5–11–00; 8:45 am]

BILLING CODE 4910–13–P