37026 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

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:

2000–11–24 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–11773.

Docket 99-NM–230-AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2002 through 2063

inclusive, 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 damage of the nose

landing gear (NLG) downlock support, which

could result in collapse of the NLG, and

consequent injury to passengers or

flightcrew, accomplish the following:

Repetitive Inspections and Corrective Action

(a) Within 6 months or 750 flight cycles

after the effective date of this AD, whichever

occurs first, perform a general visual

inspection to detect discrepancies (e.g.,

damage, or loose nuts or bolts) of the NLG

downlock support assembly, bulkhead,

attachment locations, and adjacent structure

in the NLG bay; in accordance with British

Aerospace Service Bulletin ATP–53–36,

Revision 1, dated February 21, 2000.

Thereafter, repeat the inspection at intervals

not to exceed 2 years or 3,000 flight cycles,

whichever occurs first.

(1) If any damage is found during any

inspection in accordance with paragraph (a)

of this AD, prior to further flight, repair in

accordance with the service bulletin.

(2) If any loose nut or bolt is found during

any inspection in accordance with paragraph

(a) of this AD, prior to further flight, torque

the affected nut or bolt to the limits specified

in the service bulletin, in accordance with

the service bulletin.

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.’’

Note 3: Inspections and corrective actions

accomplished prior to the effective date of

this AD in accordance with British Aerospace

Service Bulletin ATP–53–36, dated June 9,

1999, are considered acceptable for

compliance with the applicable actions

specified in this amendment.

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 actions shall be done in accordance

with British Aerospace Service Bulletin

ATP–53–36, Revision 1, dated February 21,

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 British Aerospace Regional Aircraft,

13850 Mclearen Road, Herndon, Virginia

20171. 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 British airworthiness directive 006–06–99.

(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. 00–14435 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–22–AD; Amendment

39–11774; AD 2000–11–25]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–232 and –233 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320–232 and –233 series airplanes,

that requires replacement of the fuel

metering units (FMU) of each engine

with modified FMU’s. 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 an inadvertent

increase in thrust, which could result in

reduced controllability of the airplane

during final approach.

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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37027

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 certain Airbus

Model A320–232 and –233 series

airplanes was published in the Federal

Register on March 27, 2000 (65 FR

16157). That action proposed to require

replacement of the fuel metering units

(FMU) of each engine with new FMU’s.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed rule.

Extension of Compliance Threshold

One commenter, an operator, requests

that the compliance threshold in the

proposed AD be revised to allow the

FMU replacements to be completed by

December 31, 2001, as recommended in

the related Airbus service bulletin. The

commenter states that the FMU

manufacturer has indicated that its

capacity for modification of existing

units and manufacture of new units will

not be sufficient to meet the 12-month

deadline that was specified in the

proposed AD.

The FAA concurs with this request.

Based on information received since

issuance of the proposed AD, the

available supply of FMU’s will be

inadequate to meet the replacement

requirements of the AD in the time

proposed. In light of this situation, the

FAA has determined that extending the

compliance time to ‘‘18 months after the

effective date of this AD’’ will

accommodate the time necessary for

affected operators to obtain replacement

parts without adversely affecting safety.

The FAA considers that this extension

will be approximately equivalent to the

calendar date suggested by the

commenter. The final rule has been

revised accordingly.

Reference to FMU Replacement Parts

The same commenter suggests that the

proposed AD be revised to refer to

replacement of FMU’s with ‘‘upgraded’’

or ‘‘modified’’ FMU’s. The commenter

states that, although the proposed AD

requires replacement of the FMU’s with

‘‘new’’ FMU’s, the existing (old)

configuration FMU’s also can be

modified, reidentified, and reinstalled.

The commenter states that rewording

the AD will avoid the possible

misinterpretation that only new (zero

total time) FMU’s are acceptable as

replacement parts.

The FAA acknowledges that

clarification of the requirements is

necessary. The FAA’s intent in the

proposal was to require replacement of

the FMU’s with FMU’s having a

different part number, as specified in

Airbus Service Bulletin A320–73–1067,

dated August 11, 1999. That service

bulletin is referenced in the proposed

AD as the appropriate source of service

information. Although the term ‘‘new’’

could be construed as installing a new

unit of the same part number, the FAA

notes that replacement with the same

part number is not specified in the

service bulletin. To avoid confusion, the

FAA has revised the final rule to specify

that FMU’s are to be replaced with

‘‘modified’’ FMU’s.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. 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

The FAA estimates that 77 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 14 work hours per

airplane (7 work hours per engine) to

accomplish the required replacements,

and that the average labor rate is $60 per

work hour. Required parts will be

provided by the manufacturer or vendor

at no cost to the operators. Based on

these figures, the cost impact of the AD

on U.S. operators is estimated to be

$64,680, or $840 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.

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:

2000–11–25 Airbus Industrie: Amendment

39–11774. Docket 2000–NM–22–AD.

Applicability: Model A320–232 and –233

series airplanes, certificated in any category,

except those airplanes on which Airbus

Modification 27146 or 28006 has been

installed, or on which Airbus Service

Bulletin A320–73–1067 has been

accomplished.

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,

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)