Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 63001

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:

2000–21–05 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

11937. Docket 2000–NM–123–AD.

Applicability: All BAe Model ATP

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 prevent separation of the top and

bottom torque links, and consequent loss of

directional control of the main landing gear

(MLG), accomplish the following:

Inspection

(a) Within 800 landings or 4 months after

the effective date of this AD, whichever

occurs first: Perform an inspection to detect

damage of the torque link apex joint of the

left- and right-hand MLG, in accordance with

British Aerospace Service Bulletin ATP–32–

99, dated February 21, 2000, and MessierDowty Service Bulletin 200–32–263,

including Appendix A, dated February 1,

2000. If any damage exceeds the limit

specified in the Messier-Dowty service

bulletin, prior to further flight, replace the

nut, bolt, and pin with new parts, as

applicable, in accordance with that service

bulletin. Repeat the inspection thereafter at

intervals not to exceed 1,000 landings.

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 actions shall be done in accordance

with British Aerospace Service

Bulletin ATP–32–99, dated February 21,

2000, and Messier-Dowty Service Bulletin

200–32–263, including Appendix A, dated

February 1, 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 American Support, 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 3: The subject of this AD is addressed

in British airworthiness directive 008–02–

2000.

Effective Date

(e) This amendment becomes effective on

November 6, 2000.

Issued in Renton, Washington, on October

12, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26710 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–379–AD; Amendment

39–11934; AD 2000–21–02]

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 certain Airbus Model

A330 and A340 series airplanes, that

requires revising the Airplane Flight

Manual to include new flight

operational procedures for the fuel

system; repetitive inspections of the

trim transfer fuel line in the vicinity of

the aft pressure bulkhead located

between frame (FR) 77 and FR86 to

detect any discrepancy; and corrective

actions, if necessary. This amendment

also requires modification of the air

release valve in the fuel trim tank

transfer system, which constitutes

terminating action for the requirements

of this AD. 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 damage to the fuel

trim transfer system, which could cause

rupture of the trim transfer fuel line due

to pressure build-up, and result in fuel

leakage from that fuel line. This action

is intended to address the identified

unsafe condition.

DATES: Effective November 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

63002 Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations

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 A330 and A340 series airplanes

was published in the Federal Register

on June 28, 2000 (65 FR 39825). That

action proposed to require revising the

Airplane Flight Manual (AFM) to

include new flight operational

procedures for the fuel system;

repetitive inspections of the trim

transfer fuel line in the vicinity of the

aft pressure bulkhead located between

frame (FR) 77 and FR86 to detect any

discrepancy; and corrective actions, if

necessary. That action also proposed to

require modification of the air release

valve in the fuel trim tank transfer

system, which would constitute

terminating action for the requirements

of this AD.

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 3 Airbus

Model A330 series airplanes of U.S.

Registry will be affected by this AD.

It will require approximately 1 work

hour to accomplish the revision to the

AFM, at an average labor rate of $60 per

work hour. Based on this figure, the cost

impact of the AFM revision required by

this AD action will be $180, or $60 per

airplane.

It will require approximately 2 work

hours to accomplish each inspection, at

an average labor rate of $60 per work

hour. Based on this figure, the cost

impact of each inspection required by

this AD action will be $360, or $120 per

airplane.

It will require approximately 3 work

hours to accomplish the installation of

the additional pressure relief valves in

the fuel trim tank, at an average labor

rate of $60 per work hour. Based on this

figure, the cost impact of the installation

required by this AD action will be $540,

or $180 per airplane.

The cost impact figures discussed

above are 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:

2000–21–02 Airbus Industrie: Amendment

39–11934. Docket 99–NM–379–AD.

Applicability: Model A330 and A340 series

airplanes, certificated in any category, except

those airplanes on which Airbus

Modification 47293 has been installed in

production, or on which the modification has

been accomplished in accordance with

Airbus Service Bulletin A330–28–3063 or

A340–28–4079, both dated October 6, 1999;

as applicable.

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 (d) 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 damage to the fuel trim transfer

system, which could cause rupture of the

trim transfer fuel line due to pressure buildup, and result in fuel leakage from that line;

accomplish the following:

Airplane Flight Manual Revision

(a) Within 10 days after the effective date

of this AD, revise the Limitations and Normal

Procedures section of the FAA-approved

Airplane Flight Manual (AFM) to include the

information specified in Airbus Temporary

Revision (TR) 4.03.00/09, TR 4.03.00/10, and

TR 4.03.00/12 (for Model A330 series

airplanes); or TR 4.03.00/20 (for Model A340

series airplanes); all dated July 23, 1999; as

applicable.

Note 2: The AFM revision required by

paragraph (a) of this AD may be

accomplished by inserting a copy of the

applicable TR into the applicable section of

the AFM. When the temporary revisions

required by paragraph (a) of this AD have

been incorporated into the general revisions

of the AFM, the general revisions may be

inserted into the AFM, provided that the

information contained in the general

revisions is identical to that specified in the

temporary revisions.

Inspections

(b) Within 1,000 flight hours after the

effective date of this AD, perform a detailed

Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 63003

visual inspection of the trim transfer fuel line

in the vicinity of the aft pressure bulkhead

located between frame (FR) 77 and FR86 to

detect any discrepancy (including

deformation, dents, kinks, and broken rivets

of the fuel pipe and pipe clamp, support

bracket, and shroud) in accordance with the

Accomplishment Instructions of Airbus

Service Bulletin A330–28–3060, Revision 02

(for Model A330 series airplanes), or A340–

28–4077, Revision 02 (for Model A340 series

airplanes), both dated May 27, 1999, as

applicable. Repeat the inspection thereafter

at intervals not to exceed 1,000 flight hours

until the modification required by paragraph

(c) of this AD has been accomplished.

Note 3: Inspections accomplished prior to

the effective date of this AD in accordance

with Operator Information Telex/Flight

Operations Telex (OIT/FOT) 999.0142/98,

dated December 23, 1998, are considered

acceptable for compliance with the INITIAL

detailed visual inspection required by

paragraph (b) of this AD.

Corrective Actions

(1) If any discrepancy is detected during

any inspection required by paragraph (b) of

this AD, prior to further flight, accomplish

applicable corrective actions [including

replacement of any damaged components

and deactivation of the trim fuel pipe

isolation valve and auxiliary power unit

(APU) isolation valve] in accordance with the

Accomplishment Instructions and Figure 2 of

the applicable service bulletin.

Replacement of Pipe Shroud and Pipe

(2) If the isolation valves of the trim fuel

pipe and APU are deactivated in accordance

with the FAA-approved Master Minimum

Equipment List during accomplishment of

the corrective actions required by paragraph

(b)(1) of this AD: Within 10 days after

deactivation, replace the pipe shroud and

pipe, as applicable, and reactivate the valves,

in accordance with the applicable service

bulletin.

Terminating Action

(c) Within 18 months after the effective

date of this AD, modify the air release valve

(ARV) in the trim tank system (including

cleaning and lubricating certain components,

installing two additional pressure relief

valves, and installing the adapter and ARV)

in accordance with the Accomplishment

Instructions of Airbus Service Bulletin A330–

28–3063 or A340–28–4079, both dated

October 6, 1999, as applicable.

Accomplishment of such modification

constitutes terminating action for the AFM

revisions and the repetitive inspections

required by 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,

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

(e) 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

(f) The actions shall be done in accordance

with Airbus Temporary Revision 4.03.00/09,

dated July 23, 1999; Airbus Temporary

Revision 4.03.00/10, dated July 23, 1999;

Airbus Temporary Revision 4.03.00/12, dated

July 23, 1999; Airbus Temporary Revision

4.03.00/20, dated July 23, 1999; Airbus

Service Bulletin A330–28–3060, Revision 02,

including Appendix 01, dated May 27, 1999;

Airbus Service Bulletin A340–28–4077,

Revision 02, including Appendix 01, dated

May 27, 1999; Airbus Service Bulletin A330–

28–3063, dated October 6, 1999; and Airbus

Service Bulletin A340–28–4079, dated

October 6, 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 1999–

046–091(B), Revision 4 (for Model A330

series airplanes), and 1999–045–111(B),

Revision 4 (for Model A340 series airplanes),

both dated December 15, 1999.

Effective Date

(g) This amendment becomes effective on

November 24, 2000.

Issued in Renton, Washington, on October

12, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26709 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–10–AD; Amendment

39–11935; AD 2000–21–03]

RIN 2120–AA64

Airworthiness Directives; Israel

Aircraft Industries, Ltd., Model Astra

SPX and 1125 Westwind Astra Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Israel Aircraft

Industries, Ltd., Model Astra SPX and

1125 Westwind Astra series airplanes,

that requires a one-time inspection of

the position of the aileron autopilot

servo and attachment arm; follow-on

actions; and corrective actions, if

necessary; and installation of a stopper

angle on the servo bracket. This action

is necessary to prevent the control link

of the aileron autopilot servo from being

driven overcenter, which could result in

roll oscillations when the autopilot is

engaged. This action is intended to

address the identified unsafe condition.

DATES: Effective November 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Galaxy Aerospace Corporation,

One Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. 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 Israel

Aircraft Industries, Ltd., Model Astra

SPX and 1125 Westwind Astra series

airplanes was published in the Federal