Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75589

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:

2000–24–20 Boeing: Amendment 39–12027.

Docket 99–NM–378–AD.

Applicability: All Model 707 and 720 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 (e) 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 fatigue cracking of certain

stringers, and around certain fastener holes of

the lower skin of the wings, which could

result in damage to adjacent structure and

consequent reduced structural integrity of the

airplane, accomplish the following:

Initial and Repetitive Inspections

(a) For Model 720 series airplanes: Within

500 flight cycles after the effective date of

this AD, perform an initial high frequency

eddy current (HFEC) inspection to detect

cracking, in accordance with Figure 1 of

Boeing Alert Service Bulletin A3395,

Revision 4, dated October 28, 1999.

(b) For Model 707 series airplanes having

fewer than 15,000 total flight cycles as of the

effective date of this AD: Prior to the

accumulation of 15,000 total flight cycles, or

within 150 flight cycles after the effective

date of this AD, whichever occurs later,

perform an initial HFEC inspection in

accordance with Figure 2; steps 1, 2, and 3;

of Boeing Alert Service Bulletin A3395,

Revision 4, dated October 28, 1999. Repeat

the inspection thereafter at intervals not to

exceed 1,300 flight cycles. Accomplishment

of the repetitive HFEC inspections terminates

the low frequency eddy current inspections

specified in AD 81–11–06 R1, amendment

39–4178.

(c) For Model 707 series airplanes having

15,000 total flight cycles or more as of the

effective date of this AD: Within 150 flight

cycles after the effective date of this AD,

perform an initial HFEC inspection in

accordance with Figure 2; steps 4, 5, and 6;

of Boeing Alert Service Bulletin A3395,

Revision 4, dated October 28, 1999, and

accomplish the requirements in paragraphs

(c)(1) and (c)(2) of this AD.

(1) Repeat the inspection thereafter at

intervals not to exceed 150 flight cycles until

accomplishment of the inspections required

by paragraph (c)(2) of this AD.

(2) Within 400 flight cycles after

accomplishment of the initial inspection

required by paragraph (c) of this AD,

accomplish the HFEC inspections required

by paragraph (b) of this AD. Accomplishment

of these inspections terminates the repetitive

inspections required by paragraph (c)(1) of

this AD.

Note 2: The actions required by AD 81–11–

06 R1, amendment 39–4178 [with the

exception of the LFEC inspections, as

specified in paragraph (b) of this AD] remain

in effect.

Inspect and Repair

(d) If any cracking is detected during any

inspection required by this AD, prior to

further flight, perform an internal inspection

in accordance with the Work Instructions

specified in Boeing Alert Service Bulletin

A3395, Revision 4, dated October 28, 1999;

and, prior to further flight, repair in

accordance with a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA; or in accordance with data

meeting the type certification basis of the

airplane approved by a Boeing Company

Designated Engineering Representative who

has been authorized by the Manager, Seattle

ACO, to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the Manager’s approval letter must

specifically reference this AD.

Alternative Methods of Compliance

(e) 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

ACO. 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permit

(f) 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

(g) Except as required by paragraph (d) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin A3395, Revision 4, dated October

28, 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 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.

Effective Date

(h) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 22, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30397 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–96–AD; Amendment

39–12025; AD 2000–24–18]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2 and B4 Series Airplanes, and

Model A300 B4–600, A300 B4–600R,

and A300 F4–600R (A300–600) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

75590 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300 B2 and B4 series airplanes, and

Model A300–600 series airplanes, that

requires repetitive inspections to detect

chafing and the existence of repairs of

the harness of the high-level sensor of

the fuel surge tanks, and to detect chafe

marks on the support canisters of the

magnetic level indicators; and follow-on

corrective actions, if necessary. This

amendment also requires modification

of the harness for the high-level sensor

of the outer wing fuel tanks, which

terminates certain repetitive

inspections. 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 chafing of the

harness of the high-level sensor, which

could result in a short circuit and

consequent fuel ignition source inside

the outer wing fuel tanks.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 8,

2001.

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 certain Airbus

Model A300 B2 and B4 series airplanes,

and Model A300 B4–600, A300 B4–

600R, and A300 F4–600R (A300–600)

series airplanes, was published in the

Federal Register on June 13, 2000 (65

FR 37084). That action proposed to

require repetitive inspections to detect

chafing and the existence of repairs of

the harness of the high-level sensor of

the fuel surge tanks, and to detect chafe

marks on the support canisters of the

magnetic level indicators; and follow-on

corrective actions, if necessary. That

action also proposed to require

modification of the harness for the highlevel sensor of the outer wing fuel tanks,

which would terminate certain

repetitive inspections.

Clarification of Model Designation

Since the issuance of the proposed

AD, the FAA has changed the manner

in which it identifies the airplane

models referred to as ‘‘Airbus Model

A300 and A300–600 series airplanes’’ to

reflect the model designation specified

on the type certificate data sheet. This

final rule has been revised to show the

appropriate model designations for

those airplanes.

Comments Received

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.

The commenter recommends that the

FAA only mandate the inspection

service bulletins, and not the

modification service bulletins. The

commenter is convinced that the

inspections alone are sufficient to

ensure safety.

The FAA does not concur with the

commenter’s request. The FAA is aware

that the Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France, did

not mandate the modification in the

French airworthiness directive that

addresses the identified unsafe

condition. However, as explained in the

proposal, the FAA has determined that

long-term continued operational safety

will be better assured by design changes

to remove the source of the problem,

rather than by repetitive inspections. No

additional data were submitted by the

commenter that would cause the FAA to

change its position in this regard. No

change to the final rule is necessary.

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 with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 37 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 inspections, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the inspections required by this AD

on U.S. operators is estimated to be

$2,220, or $60 per airplane, per

inspection cycle.

It will take approximately 1 work

hour per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be $2,220,

or $60 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.

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:

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75591

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:

2000–24–18 Airbus Industrie: Amendment

39–12025. Docket 2000–NM–96–AD.

Applicability: Model A300 B2 and B4

series airplanes, and Model A300 B4–600,

A300 B4–600R, and A300 F4–600R (A300–

600) series airplanes; certificated in any

category; except those airplanes on which

Airbus Modification 04489 has been installed

during production.

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 (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 chafing of the wire harnesses of

the high-level sensors, which could result in

a short circuit and consequent fuel ignition

source inside the outer wing fuel tanks,

accomplish the following:

Detailed Visual Inspection

(a) Within 500 flight hours after the

effective date of this AD, perform a detailed

visual inspection to detect chafing and the

existence of repairs of the harness (cable) of

the high-level sensor of the fuel surge tanks,

and to detect chafe marks on the support

canisters of the magnetic level indicators, in

accordance with Airbus Service Bulletin

A300–28–0077 (for Model A300 series

airplanes) or A300–28–6062 (for Model

A300–600 series airplanes), each dated July

19, 1999, as applicable.

(1) For airplanes on which modification of

the harness in accordance with Airbus

Service Bulletin A300–28–0058 (for Model

A300 series airplanes) or A300–28–6020 (for

Model A300–600 series airplanes), as

applicable, HAS NOT been accomplished:

Accomplish the requirements of paragraphs

(a)(1)(i) and (a)(1)(ii) of this AD.

(i) Repeat the detailed visual inspection

thereafter at intervals not to exceed 500 flight

hours until the requirements of paragraph

(a)(1)(ii) of this AD are accomplished. If any

wire chafing, chafe mark, or existing repair

is detected during any inspection, prior to

further flight, determine the appropriate

repair and/or condition of repair as specified

in Inspection Table 1 of the Accomplishment

Instructions of Airbus Service Bulletin A300–

28–0077 or A300–28–6062, as applicable. At

the times specified in Inspection Table I,

accomplish corrective actions (e.g.,

temporary or permanent repairs, and followon inspections and repairs) in accordance

with the applicable service bulletin. If any

discrepancy is found during any follow-on

inspection, prior to further flight, repair the

discrepancy in accordance with the

applicable service bulletin.

(ii) Within 18 months after the effective

date of this AD, modify the harness of the

high-level sensor in the outer wing fuel tanks

in accordance with Airbus Service Bulletin

A300–28–0058, Revision 02 (for Model A300

series airplanes), or A300–28–6020, Revision

01 (for Model A300–600 series airplanes),

each dated September 28, 1999.

Accomplishment of the modification

terminates the 500-flight-hour repetitive

inspection required by paragraph (a)(1) of

this AD. However, if a temporary repair is

installed, the 10,000-flight-hour detailed

visual inspection specified in the follow-on

corrective actions of Table 1 continues to be

required by this AD.

(2) For airplanes on which modification of

the harness in accordance with Airbus

Service Bulletin A300–28–0058 (for Model

A300 series airplanes) or A300–28–6020 (for

Model A300–600 series airplanes), as

applicable, HAS been accomplished:

Accomplish the requirements of paragraph

(a)(2)(i) or (a)(2)(ii), as applicable.

(i) If no wire chafing, chafe marks, or

existing repairs are detected, no further

action is required by this AD.

(ii) If any wire chafing, chafe mark, or

existing repair is detected, prior to further

flight, determine the appropriate repair and/

or condition of repair specified in Inspection

Table 2 of the Accomplishment Instructions

of Airbus Service Bulletin A300–28–0077 or

A300–28–6062, as applicable. At the times

specified in Inspection Table 2, accomplish

corrective actions (e.g., temporary or

permanent repairs and follow-on inspections)

in accordance with the applicable service

bulletin. If any discrepancy is found during

any follow-on inspection, prior to further

flight, repair the discrepancy in accordance

with the applicable service bulletin.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as

mirrors, magnifying lenses, etc., may be used.

Surface cleaning and elaborate access

procedures may be required.’’

Note 3: Modification accomplished prior to

the effective date of this AD in accordance

with Airbus Service Bulletin A300–28–0058,

dated December 15, 1988, or Revision 01,

dated October 1, 1991 (for Model A300 series

airplanes); or A300–28–6020, dated

December 15, 1988 (for Model A300–600

series airplanes); is considered acceptable for

compliance with the action specified in

paragraph (a)(1)(ii) of this AD.

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 Airbus Service Bulletin A300–28–0077,

dated July 19, 1999; Airbus Service Bulletin

A300–28–0058, Revision 02, dated

September 28, 1999; Airbus Service Bulletin

A300–28–6062, dated July 19, 1999; or

Airbus Service Bulletin A300–28–6020,

Revision 01, dated September 28, 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 directive 1999–404–

293(B), dated October 6, 1999.

Effective Date

(e) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 22, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30395 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–227–AD; Amendment

39–12015; AD 2000–24–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.