37028 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

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 an inadvertent increase in

thrust, which could result in reduced

controllability of the airplane during final

approach, accomplish the following:

Replacement

(a) Within 18 months after the effective

date of this AD, replace the fuel metering

units (FMU) of each engine with modified

FMU’s, in accordance with Airbus Service

Bulletin A320–73–1067, dated August 11,

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 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 §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 replacement shall be done in

accordance with Airbus Service Bulletin

A320–73–1067, dated August 11, 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 3: The subject of this AD is addressed

in French airworthiness directive 2000–005–

143(B), dated January 12, 2000.

(e) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 2,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14434 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–53–AD; Amendment

39–11775; AD 2000–11–26]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A330

and A340 series airplanes, that requires

repetitive ultrasonic inspections to

detect corrosion of the retraction links

of the main landing gear (MLG), and

replacement of the retraction link with

a new retraction link, if necessary. 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

detect and correct corrosion of the

retraction link of the MLG, which could

result in reduced structural integrity

and possible collapse of the MLG.

DATES: Effective July 18, 2000. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of July 18, 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,

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 all Airbus Model

A330 and A340 series airplanes was

published in the Federal Register on

April 7, 2000 (65 FR 18258). That action

proposed to require repetitive ultrasonic

inspections to detect corrosion of the

retraction links of the main landing gear

(MLG), and replacement of the

retraction link with a new retraction

link, if necessary.

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.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicablity of

this rule currently are operated by nonU.S. operators under foreign registry;

therefore, they are not directly affected

by this AD action. However, the FAA

considers that this rule is necessary to

ensure that the unsafe condition is

addressed in the event that any of these

subject airplanes are imported and

placed on the U.S. Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 1 work hour to

accomplish the required inspection, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of this AD would be $60 per

airplane, per inspection cycle.

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)

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37029

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:

2000–11–26 Airbus Industrie: Amendment

39–11775. Docket 2000–NM–53–AD.

Applicability: All Model A330 and A340

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 (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 detect and correct corrosion of the

retraction links of the main landing gear

(MLG), which could result in reduced

structural integrity and possible collapse of

the MLG, accomplish the following:

Repetitive Ultrasonic Inspections

(a) Within 36 months time-in-service on

any new retraction link, or within 2 months

after the effective date of this AD, whichever

occurs later, perform an ultrasonic inspection

to detect corrosion of the retraction links leftand right-hand of the MLG, in accordance

with Airbus Service Bulletin A330–32–3105,

Revision 01, dated December 14, 1999 (for

Model A330 series airplanes), or Airbus

Service Bulletin A340–32–4148, Revision 01,

dated December 14, 1999 (for Model A340

series airplanes), as applicable.

(1) If no corrosion is detected, or if

corrosion is detected that is within the limits

specified in the applicable service bulletin,

repeat the inspection thereafter at intervals

not to exceed 6 months.

(2) If any corrosion is detected that is

outside the limits specified in the applicable

service bulletin, replace the affected

retraction link with a new retraction link at

the time specified and in accordance with the

procedures specified in the applicable

service bulletin. Thereafter, repeat the

inspection specified in paragraph (a) on any

new retraction links, at the time specified in

paragraph (a) of this AD.

Note 2: The Airbus service bulletins

reference Messier-Dowty Service Bulletins

A33/34–32–151, Revision 3, including

Appendix A, and A33/34–32–152, Revision

3, including Appendix A, each dated January

11, 2000, as additional sources of service

information for accomplishing the repetitive

inspections.

Note 3: Although the inspection schedule

of this AD applies to both left-and right-hand

retraction links of the MLG, replacement of

a retraction link, prior to scheduled

replacement, would result in subsequent

staggered inspections for the remainder of the

retraction links.

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 §§ 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 actions shall be done in accordance

with Airbus Service Bulletin A330–32–3105,

Revision 01, dated December 14, 1999; or

Airbus Service Bulletin A340–32–4148,

Revision 01, dated December 14, 1999; as

applicable. 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 directives 2000–

013–107(B) R1, dated February 9, 2000, and

2000–015–132(B), dated January 12, 2000.

(e) This amendment becomes effective on

July 18, 2000.

Issued in Renton, Washington, on June 2,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14433 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–139–AD; Amendment

39–11776; AD 2000–11–27]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 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

A319, A320, and A321 series airplanes.

This action requires a one-time

ultrasonic inspection to detect

disbonding of the skin attachments at

the stringers and spars of the vertical

stabilizer, and repair, if necessary. This

action is necessary to detect and correct

disbonding of the vertical stabilizer

structure, which could result in reduced

structural integrity of the spar boxes of

the vertical stabilizer.

DATES: Effective June 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 28,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 13, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

139–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this