Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations 37853

Incorporation by Reference

(e) Except as provided by paragraph (b) of

this AD, the actions shall be done in

accordance with Saab Service Bulletin 340–

92–027, dated December 10, 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 Saab

Aircraft AB, SAAB Aircraft Product Support,

S–581.88, Linko ̈ping, Sweden. 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 4: The subject of this AD is addressed

in Swedish airworthiness directive 1–149,

dated December 10, 1999.

(f) This amendment becomes effective on

July 24, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15184 Filed 6–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–164–AD; Amendment

39–11789; AD 2000–12–11]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 series airplanes, that

currently requires repetitive ultrasonic

inspections to detect cracks in the bolt

holes inboard and outboard of rib 9 on

the bottom booms of the front and rear

wing spars, and repair, if necessary.

This amendment requires revising the

compliance thresholds for the

inspection and requires that the

inspections be repeated at reduced

intervals. 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 fatigue cracks in the

bolt holes of the wing spars, which

could result in reduced structural

integrity of a wing spar.

DATES: Effective July 24, 2000.

The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

Revision 1, dated August 31, 1995, as

listed in the regulations, is approved by

the Director of the Federal Register as of

July 24, 2000.

The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

dated August 1, 1994, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

May 10, 1995 (60 FR 17990, April 10,

1995).

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, 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)

by superseding AD 95–07–05,

amendment 39–9187 (60 FR 17990,

April 10, 1995), which is applicable to

certain Airbus Model A300–600 series

airplanes, was published in the Federal

Register on April 20, 2000 (65 FR

21157). The action proposed to continue

to require repetitive ultrasonic

inspections to detect cracks in the bolt

holes inboard and outboard of rib 9 on

the bottom booms of the front and rear

wing spars, and repair, if necessary. The

action also proposed to revise the

compliance thresholds for the

inspection and require that the

inspections be repeated at reduced

intervals.

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

There are approximately 75 airplanes

of U.S. registry that will be affected by

this AD.

The inspection that is currently

required by AD 95–07–05, and retained

in this AD, takes approximately 1 work

hour per airplane to accomplish

(excluding 10 work hours for access and

close-up), at an average labor rate of $60

per work hour. Based on this figure, the

cost impact of the currently required

inspection on U.S. operators is

estimated to be $4,500, or $60 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

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:

37854 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations

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

removing amendment 39–9187 (60 FR

17990, April 10, 1995), and by adding

a new airworthiness directive (AD),

amendment 39–11789, to read as

follows:

2000–12–11 Airbus Industrie: Amendment

39–11789. Docket 98–NM–164–AD.

Supersedes AD 95–07–05, Amendment

39–9187.

Applicability: Model A300–600 series

airplanes, certificated in any category, on

which Airbus Modification 10161 has not

been installed in 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 (c) 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 fatigue cracks in the bolt holes

of the wing spars, which could result in

reduced structural integrity of a wing spar,

accomplish the following:

Ultrasonic Inspections

(a) Perform an ultrasonic inspection to

detect fatigue cracking of the bolt holes

inboard and outboard of rib 9 on the bottom

booms of the front and rear wing spars, in

accordance with Airbus Service Bulletin

A300–57–6037, dated August 1, 1994, or

Revision 1, dated August 31, 1995, at the

applicable time specified in paragraph (a)(1)

or (a)(2) of this AD. Repeat the inspection

thereafter at intervals not to exceed 4,800

flight cycles or 11,000 flight hours,

whichever occurs first.

(1) For airplanes on which Airbus

Modification 8842 (reference Airbus Service

Bulletin A300–57–6039) has not been

installed: Inspect at the earlier of the times

specified by paragraphs (a)(1)(i) and (a)(1)(ii)

of this AD.

(i) Prior to the accumulation of 17,000 total

flight cycles, or within 2,000 flight cycles

after May 10, 1995 (the effective date of AD

95–07–05, amendment 39–9187), whichever

occurs later.

(ii) Prior to the accumulation of 39,000

total flight hours.

(2) For airplanes on which Airbus

Modification 8842 has been installed: Inspect

at the earlier of the times specified by

paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.

(i) Within 17,000 flight cycles after

accomplishment of Airbus Modification

8842, or within 2,000 flight cycles after May

10, 1995, whichever occurs later.

(ii) Within 39,000 flight hours after

accomplishment of Airbus Modification

8842.

Corrective Action

(b) If any crack is found, prior to further

flight, repair in accordance with Airbus

Service Bulletin A300–57–6037, dated

August 1, 1994, or Revision 1, dated August

31, 1995. Thereafter, perform the repetitive

inspections required by paragraph (a) of this

AD.

Alternative Methods of Compliance

(c) 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

(d) 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

(e) The actions shall be done in accordance

with Airbus Service Bulletin A300–57–6037,

dated August 1, 1994; or Airbus Service

Bulletin A300–57–6037, Revision 1, dated

August 31, 1995, as applicable. Airbus

Service Bulletin A300–57–6037, Revision 1,

dated August 31, 1995, contains the

following list of effective pages:

Page No.

Revision

level shown

on page

Date shown on

page

1, 2, 4–6 1 .................. August 31, 1995.

3, 7–17 Original ........ August 1, 1994.

(1) The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

Revision 1, dated August 31, 1995, is

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51.

(2) The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

dated August 1, 1994, was approved

previously by the Director of the Federal

Register as of May 10, 1995 (60 FR 17990,

April 10, 1995).

(3) 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 94–208–

169(B)R2, dated October 8, 1997.

(f) This amendment becomes effective on

July 24, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15186 Filed 6–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Coast Guard

33 CFR Parts 100, 110, and 165

[CGD01–99–191]

RIN 2115–AA97, AA98, AE46

Temporary Regulations: Sail Boston

2000, Port of Boston, MA.

AGENCY: Coast Guard, DOT.

ACTION: Temporary final rule.

SUMMARY: The Coast Guard is

establishing temporary regulations,

including regulated areas, safety and

security zones, and spectator anchorages

before, during, and after Sail Boston

2000 events in the Port of Boston,

Massachusetts, between July 10–16,

2000. These regulations are necessary to

promote the safe navigation of vessels

and the safety of life and property

during the heavy volume of vessel

traffic expected during the events.

DATES: This rule is effective from July

10, 2000 until July 16, 2000.

ADDRESSES: Comments and material

received from the public, as well as

documents, indicated in this preamble

as being available in the docket, are part

of docket CGD01–99–191 and are

available for inspection and copying at

the Coast Guard Marine Safety Office

Boston, 455 Commercial Street, Boston,

MA 02109 between 7:30 a.m. and 4 p.m.

Monday through Friday, except Federal

holidays.

FOR FURTHER INFORMATION CONTACT:

Lieutenant Brian J. Downey, Marine

Safety Office Boston, Waterways

Management Division, (617) 223–3006.

SUPPLEMENTARY INFORMATION:

Regulatory Information

On March 15, 2000, the Coast Guard

published a notice of proposed