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

63004 Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations

Register on June 30, 2000 (65 FR 40551).

That action proposed to require require

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.

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 38 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$100 per airplane. Based on these

figures, the cost impact of the required

AD on U.S. operators is estimated to be

$8,360, or $220 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. 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:

2000–21–03 Israel Aircraft Industries, Ltd.:

Amendment 39–11935. Docket 2000–

NM–10–AD.

Applicability: Model Astra SPX and 1125

Westwind Astra series airplanes; certificated

in any category; serial numbers 030, and 042

through 086 inclusive.

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 the control link of the aileron

autopilot servo from being driven overcenter,

which could result in roll oscillations when

the autopilot is engaged, accomplish the

following:

Inspection and Corrective Actions

(a) Within 50 flight hours after the effective

date of this AD, perform a one-time general

visual inspection of the aileron autopilot

servo and attaching linkage to determine

whether the attachment arm on the servo is

in the correct position, in accordance with

Astra (Israel Aircraft Industries Ltd.) Alert

Service Bulletin 1125–27A–157, dated

September 14, 1999.

(1) If the attachment arm is in the correct

position, prior to further flight, install a

stopper angle on the servo bracket in

accordance with the alert service bulletin.

(2) If the attachment arm is in the incorrect

position, prior to further flight, perform a

general visual inspection to detect damage of

the bellcrank arm, control link, and

attachment arm, in accordance with the alert

service bulletin. Prior to further flight after

accomplishment of all applicable corrective

actions specified by this paragraph, install a

stopper angle on the servo bracket in

accordance with the alert service bulletin.

(i) If no damage is detected, prior to further

flight, reposition the attachment arm in

accordance with the alert service bulletin.

(ii) If any damage is detected and the

damage is within the limits specified by the

alert service bulletin, prior to further flight,

repair the damaged part in accordance with

the alert service bulletin.

(iii) If any damage is detected and the

damage exceeds the limits specified by the

alert service bulletin, prior to further flight,

replace the damaged part with a new part in

accordance with the alert 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.’’

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 3: 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 Astra (Israel Aircraft Industries Ltd.)

Alert Service Bulletin 1125–27A–157, dated

September 14, 1999. This incorporation by

Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 63005

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 Galaxy Aerospace Corporation,

One Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. 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.

Effective Date

(e) 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. 00–26708 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–91–AD; Amendment

39–11936; AD 2000–21–04]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires

installation of sleeving on the 90-minute

auxiliary power unit (APU) standby

power feeder cable at body station 1351.

This amendment is prompted by a

report of damage to the 90-minute APU

standby power feeder cable caused by

shifting of unrestrained cargo containers

during flight. The actions specified by

this AD are intended to prevent damage

to the 90-minute APU standby power

feeder cable, which could result in

arcing between the standby power

feeder cable and the shroud of the APU

fuel line, penetration of the fuel line

shroud, and a consequent fire in the

main deck floor above the aft cargo

compartment.

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 Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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:

Dennis Kammers, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2956; fax (425) 227–1181.

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 Boeing

Model 767 series airplanes was

published in the Federal Register on

May 12, 2000 (65 FR 30553). That action

proposed to require installation of

sleeving on the 90-minute auxiliary

power unit (APU) standby power feeder

cable at body station 1351.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Revise Paragraph (a) of the Proposal

The commenter notes that paragraph

(a) of the proposal states, ‘‘Within 6

months after the effective date of this

AD, install sleeving on the 90-minute

APU standby power feeder cable at body

station 1351 on the left side of the

airplane * * *’’ The commenter also

reiterates a portion of the Discussion

section that reads, ‘‘The cargo

containers damaged the 90-minute APU

standby power feeder cable and the

cabin floor support beam at body station

1351, on the right side of the airplane.

Investigation revealed evidence of

arcing between the cable and the beam.’’

The commenter inquires as to why there

is no proposed requirement for sleeving

of the cable on the right-hand side of the

airplane. The commenter further states

that even though the fuel line is not on

the right-hand side of the airplane, any

cable arcing may still become a

potential hazard and should be

addressed. Therefore, the commenter

requests that paragraph (a) of the

proposal be revised to read, ‘‘* * * on

the left and right sides of the airplane

* * *’’

The FAA does not concur with the

commenter’s request. Accomplishment

of the corrective action of the APU

standby power feeder cable, as required

by paragraph (a) of the final rule, is to

reduce the fire hazard associated with

an unrestrained cargo container

impacting the cable. Damaging the cable

in the region specified could cause

arcing against the APU fuel line shroud,

which could penetrate the fuel line and

result in a cabin fire. The arcing damage

between the APU standby power feeder

cable and the cargo floor beam, which

was reported in the initial investigation,

although serious in nature, was not

deemed an unsafe condition or a threat

to continued safe operation of the

airplane. Further investigation

determined that no structural or fire

concerns resulted from the incident.

Therefore, sleeving of the standby

power feeder cable is necessary only in

areas where damage to the cable may

cause arcing to the APU fuel line. No

change to paragraph (a) of the final rule

is necessary in this regard.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 151

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

14 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required action, 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 $840, or $60 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. 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