39072 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

significantly or uniquely affect small

governments. Therefore, no actions were

deemed necessary under the provisions

of the Unfunded Mandates Reform Act

of 1995.

Small Business Regulatory Enforcement

Fairness Act of 1996

This rule is not a major rule as

defined by section 804 of the Small

Business Regulatory Enforcement Act of

1996. This rule will not result in an

annual effect on the economy of $100

million or more; a major increase in

costs or prices; or significant adverse

effects on competition, employment,

investment, productivity, innovation, or

on the ability of United States-based

companies to compete with foreignbased companies in domestic and

export markets.

Executive Order 12866

This rule is not considered by the

Department of Justice, Immigration and

Naturalization Service, to be a

‘‘significant regulatory action’’ under

Executive Order 12866, section 3(f),

Regulatory Planning and Review, and

the Office of Management and Budget

has waived its review process under

section 6(a)(3)(A).

Executive Order 13132

This rule will not have substantial

direct effects 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, in

accordance with section 6 of Executive

Order 13132, it is determined that this

rule does not have sufficient federalism

implications to warrant the preparation

of a federalism summary impact

statement.

Executive Order 12988 Civil Justice

Reform

This rule meets the applicable

standards set forth in sections 3(a) and

3(b)(2) of Executive Order 12988.

List of Subjects in 8 CFR Part 100

Organization and functions

(Government agencies).

Accordingly, part 100 of chapter I of

title 8 of the Code of Federal

Regulations is amended as follows:

PART 100—STATEMENT OF

ORGANIZATION

1. The authority citation for part 100

continues to read as follows:

Authority: 8 U.S.C. 1103; 8 CFR part 2.

2. In § 100.4, paragraphs (f)(7) and

(f)(8) are revised to read as follows:

§ 100.4 Field offices.

* * * * *

(f) * * *

(7) Los Angeles, California. The

Asylum Office in Los Angeles has

jurisdiction over the States of Arizona,

the southern portion of California as

listed in § 100.4(b)(16) and

§ 100.4(b)(39), Hawaii, the southern

portion of Nevada currently within the

jurisdiction of the Las Vegas Suboffice,

and the Territory of Guam.

(8) San Francisco, California. The

Asylum Office in San Francisco has

jurisdiction over the northern part of

California as listed in § 100.4(b)(13), the

portion of Nevada currently under the

jurisdiction of the Reno Suboffice, and

the States of Alaska, Oregon, and

Washington.

* * * * *

Dated: June 6, 2000.

Doris Meissner,

Commissioner, Immigration and

Naturalization Service.

[FR Doc. 00–15925 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–10–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–240–AD; Amendment

39–11790; AD 2000–12–12]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A300, A300–600, and

A310 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, A300–600, and A310 series

airplanes, that currently requires

inspections to detect cracks in the lower

spar axis of the nacelle pylon between

ribs 9 and 10, and repair, if necessary.

The existing AD also provides for

optional modification of the pylon,

which terminates the inspections for

Model A300 and A310 series airplanes

and increases the threshold and

repetitive interval of the inspections for

Model A300–600 series airplanes. This

amendment reduces the inspection

threshold and requires repetitive

inspections following accomplishment

of the optional modification for Model

A310 series airplanes. 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 cracking,

which could result in reduced structural

integrity of the lower spar of the pylon.

DATES: Effective July 28, 2000.

The incorporation by reference of

Airbus Industrie Service Bulletins

A310–54–2016, Revision 02, dated June

11, 1999, and A310–54–2022, Revision

1, dated March 16, 1999 is approved by

the Director of the Federal Register as of

July 28, 2000.

The incorporation by reference of the

remaining Airbus Industrie publications

was approved previously by the Director

of the Federal Register as of June 12,

1995 (60 FR 25604, May 12, 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 95–10–03,

amendment 39–9220 (60 FR 25604, May

12, 1995), which is applicable to certain

Airbus Model A300, A300–600, and

A310 series airplanes, was published in

the Federal Register on April 20, 2000

(65 FR 21154). The action proposed to

continue to require inspections to detect

cracks in the lower spar axis of the

nacelle pylon between ribs 9 and 10,

and repair, if necessary. The action also

proposed to continue to provide for

optional modification of the pylon,

which terminates the inspections for

Model A300 and A310 series airplanes

and increases the threshold and

repetitive interval of the inspections for

Model A300–600 series airplanes. The

action also proposed to reduce the

inspection threshold and require

repetitive inspections following

accomplishment of the optional

modification for Model A310 series

airplanes.

Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations 39073

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 140 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 4 work

hours per airplane to accomplish the

inspection that was previously required

by AD 95–10–03, and retained in this

AD, at an average labor rate of $60 per

work hour. Based on these figures, the

cost impact of the inspection on U.S.

operators is estimated to be $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

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

removing amendment 39–9220 (60 FR

25604, May 12, 1995), and by adding a

new airworthiness directive (AD),

amendment 39–11790, to read as

follows:

2000–12–12 Airbus Industrie: Amendment

39–11790. Docket 99–NM–240–AD.

Supersedes AD 95–10–03, Amendment

39–9220.

Applicability: The following airplanes,

certificated in any category:

—Model A300 series airplanes, as listed in

Airbus Service Bulletin A300–54–071,

Revision 1, dated October 15, 1993.

—Model A300–600 series airplanes, as listed

in Airbus Service Bulletin A300–54–6011,

Revision 1, dated October 15, 1993.

—Model A310 series airplanes, as listed in

Airbus Service Bulletin A310–54–2016,

Revision 02, dated June 11, 1999.

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 prevent fatigue cracking, which could

result in reduced structural integrity of the

lower spar of the pylon, accomplish the

following:

Restatement of Certain Requirements of AD

95–10–03

Model A300 Series Airplanes

(a) For Model A300 B4–2C, B2K–3C, B2–

203, B4–103, and B4–203 series airplanes:

Prior to the accumulation of 9,000 total

landings, or within 500 landings after June

12, 1995 (the effective date of AD 95–10–03,

amendment 39–9220), whichever occurs

later, perform an internal eddy current

inspection to detect cracks in the lower spar

axis of the pylon between ribs 9 and 10, in

accordance with Airbus Industrie Service

Bulletin A300–54–071, dated November 12,

1991; or Revision 1, dated October 15, 1993.

(1) If no crack is found, repeat the

inspection thereafter at intervals not to

exceed 2,500 landings.

(2) If any crack is found that is less than

or equal to 30 mm: Perform subsequent

inspections and repair in accordance with

the methods and times specified in the

service bulletin.

(3) If any crack is found that is greater than

30 mm, but less than 100 mm: Prior to the

accumulation of 250 landings after crack

discovery, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC) (or its delegated agent).

(4) If any crack is found that is greater than

or equal to 100 mm: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent).

(5) Accomplishment of the modification

specified in Airbus Industrie Service Bulletin

A300–54–0079, dated October 15, 1993,

constitutes terminating action for the

inspections required by paragraph (a) of this

AD.

Model A300–600 Series Airplanes

(b) For Model A300–600 B4–620, C4–620,

B4–622R, and B4–622 series airplanes:

Except as provided by paragraph (b)(5) of this

AD, prior to the accumulation of 4,000 total

landings, or within 500 landings after June

12, 1995 (the effective date of AD 95–10–03),

whichever occurs later, perform an internal

eddy current inspection to detect cracks in

the lower spar axis of the pylon between ribs

9 and 10, in accordance with Airbus

Industrie Service Bulletin A300–54–6011,

dated November 12, 1991, as amended by

Service Bulletin Change Notice O.A., dated

July 10, 1992; or Revision 1, dated October

15, 1993.

(1) If no crack is found, repeat the

inspection thereafter at intervals not to

exceed 2,500 landings.

(2) If any crack is found that is less than

or equal to 30 mm: Perform subsequent

inspections and repair in accordance with

the methods and times specified in the

service bulletin.

(3) If any crack is found that is greater than

30 mm, but less than 100 mm: Prior to the

accumulation of 250 landings after crack

discovery, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116; or the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC) (or its delegated agent).

(4) If any crack is found that is greater than

or equal to 100 mm: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent).

(5) Accomplishment of the modification

specified in Airbus Industrie Service Bulletin

A300–54–6019, dated October 15, 1993,

increases the threshold and repetitive

interval of the inspections required by

paragraph (b) of this AD to the threshold and

39074 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

interval specified in paragraph 2.D. of the

Accomplishment Instructions of Airbus

Industrie Service Bulletin A300–54–6011,

Revision 1, dated October 15, 1993.

New Requirements of This AD

Model A310 Series Airplanes

(c) For Model A310–221, –222, –322, –324,

and –325 series airplanes: Perform an

internal eddy current inspection to detect

cracks in the lower spar axis of the pylon

between ribs 9 and 10, in accordance with

Airbus Industrie Service Bulletin A310–54–

2016, dated November 12, 1991; or Revision

1, dated October 15, 1993; or Revision 02,

dated June 11, 1999; at the time specified in

paragraph (d) of this AD.

(1) If no crack is found, repeat the

inspection thereafter at intervals not to

exceed 2,500 landings.

(2) If any crack is found that is less than

or equal to 30 mm: Perform subsequent

inspections and repair in accordance with

the methods and times specified in the

service bulletin.

(3) If any crack is found that is greater than

30 mm, but less than 100 mm: Prior to the

accumulation of 250 landings after crack

discovery, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116; or the

DGAC (or its delegated agent).

(4) If any crack is found that is greater than

or equal to 100 mm: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent).

(5) Accomplishment of the modification

specified in Airbus Industrie Service Bulletin

A310–54–2022, dated October 15, 1993; or

Revision 01, dated March 16, 1999; increases

the threshold and repetitive interval of the

inspections required by paragraph (c) of this

AD to the threshold and interval specified in

paragraph 2.D. of the Accomplishment

Instructions of Airbus Industrie Service

Bulletin A310–54–2016, Revision 02, dated

June 11, 1999.

(d) Perform the initial inspection required

by paragraph (c) of this AD at the earlier of

the times specified by paragraphs (d)(1) and

(d)(2) of this AD.

(1) Prior to the accumulation of 25,000

total landings, or within 500 landings after

June 12, 1995, whichever occurs later.

(2) At the applicable time specified by

paragraph (d)(2)(i), (d)(2)(ii), or (d)(2)(iii) of

this AD.

(i) For airplanes that have accumulated

fewer than 10,000 landings as of the effective

date of this AD: Perform the inspection prior

to the accumulation of 3,800 total landings,

or within 1,500 landings after the effective

date of this AD, whichever occurs later.

(ii) For airplanes that have accumulated

10,000 total landings or more, but fewer than

20,000 total landings, as of the effective date

of this AD: Perform the inspection within

1,000 landings after the effective date of this

AD.

(iii) For airplanes that have accumulated

20,000 total landings or more as of the

effective date of this AD: Perform the

inspection within 500 landings after the

effective date of 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,

International Branch, ANM–116. 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

(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 provided by paragraphs (a)(3),

(a)(4), (b)(3), (b)(4), (c)(3), and (c)(4) of this

AD, the actions shall be done in accordance

with the following Airbus Industrie service

bulletins, as applicable.

Airbus Industrie Service

Bulletin No.

Revision

Level

Service Bulletin

Date

A300–54–071 ......................................................................... Original .................................................................................. November 12, 1991.

A300–54–071 ......................................................................... 1 ............................................................................................ October 15, 1993.

A300–54–0079 ....................................................................... Original .................................................................................. October 15, 1993.

A300–54–6011 ....................................................................... Original .................................................................................. November 12, 1991.

Change Notice O.A. A300–54–6011 ..................................... Original .................................................................................. July 10, 1992.

A300–54–6011 ....................................................................... 1 ............................................................................................ October 15, 1993.

A300–54–6019 ....................................................................... Original .................................................................................. October 15, 1993.

A310–54–2016 ....................................................................... Original .................................................................................. November 12, 1991.

A310–54–2016 ....................................................................... 1 ............................................................................................ October 15, 1993.

A310–54–2022 ....................................................................... Original .................................................................................. October 15, 1993.

A310–54–2022 ....................................................................... 01 .......................................................................................... March 16, 1999.

A310–54–2016 ....................................................................... 02 .......................................................................................... June 11, 1999.

(1) The incorporation by reference of

Airbus Industrie Service Bulletin

A310–54–2016, Revision 02, dated June 11,

1999; and A310–54–2022, Revision 1, dated

March 16, 1999, 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 the

remaining Airbus Industrie publications was

approved previously by the Director of the

Federal Register as of June 12, 1995 (60 FR

25604, May 12, 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 1999–237–

285(B), dated June 2, 1999.

(h) This amendment becomes effective on

July 28, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15185 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–37–AD; Amendment

39–11787; AD 2000–12–09]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Aircraft Corporation (Sikorsky) Model

S–76A Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for