Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37025

(1) Within 6,000 flight cycles, 14,000 flight

hours, or 5 years after the date of the first

inspection, whichever occurs earliest; or

(2) Within 4 years after the effective date

of this AD.

(c) For any auxiliary track assembly on

which any discrepancy is detected during

any detailed visual inspection required by

paragraph (a) of this AD: Repair the auxiliary

track assembly (replace the slider and liner

and install a retainer bar), or replace with a

new, improved assembly (including a new

liner and slider), as applicable, in accordance

with the Accomplishment Instructions of

Boeing Service Bulletin 747–78A2164,

Revision 2, dated December 3, 1998 (for

Model 747–400 series airplanes); or Boeing

Service Bulletin 767–78A0079, Revision 2,

dated December 3, 1998 (for Model 767 series

airplanes); as applicable; at the later of the

times specified in paragraphs (c)(1) and (c)(2)

of this AD. Such action constitutes

terminating action for the requirements of

this AD for that assembly.

(1) Within 4,500 flight cycles, 10,000 flight

hours, or 3 years after the date of the first

repair, whichever occurs earliest; or

(2) Within 2 years after the effective date

of this AD.

Note 4: Inspections and repairs

accomplished prior to the effective date of

this AD in accordance with Boeing Service

Bulletin 747–78A2164, Revision 1, or Boeing

Service Bulletin 767–78A0079, Revision 1,

both dated February 5, 1998; are considered

acceptable for compliance with the

applicable actions specified in this AD.

Alternative Methods of Compliance

(d) 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,

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, Seattle ACO.

Note 5: 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

(e) 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

(f) Except as provided by paragraph

(a)(3)(ii)(A) of this AD, the actions shall be

done in accordance with Boeing Service

Bulletin 747–78A2164, Revision 2, dated

December 3, 1998; or Boeing Service Bulletin

767–78A0079, Revision 2, dated December 3,

1998; 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 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.

(g) 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. 00–14436 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–230–AD; Amendment

39–11773; AD 2000–11–24]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

BAe Model ATP airplanes, that requires

repetitive inspections to detect

discrepancies of the downlock support

assembly and attachment of the nose

landing gear (NLG), and of the bulkhead

and adjacent structure in the NLG bay;

and corrective action, 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 damage of the NLG

downlock support, which could result

in collapse of the NLG and consequent

injury to passengers or flightcrew.

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 British Aerospace Regional

Aircraft, 13850 Mclearen Road,

Herndon, Virginia 20171. 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 British

Aerospace BAe Model ATP airplanes

was published in the Federal Register

on April 7, 2000 (65 FR 18260). That

action proposed to require repetitive

inspections to detect discrepancies of

the downlock support assembly and

attachment of the nose landing gear

(NLG), and of the bulkhead and adjacent

structure in the NLG bay; and corrective

action, 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

The FAA estimates that 10 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 4

work hours per airplane to accomplish

the required inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $2,400, or $240 per airplane, per

inspection cycle.

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

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