This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

36053

Vol. 65, No. 110

Wednesday, June 7, 2000

FEDERAL ELECTION COMMISSION

11 CFR Part 108

[Notice 2000–12]

Filing Copies of Campaign Finance

Reports and Statements With State

Officers

AGENCY: Federal Election Commission.

ACTION: Final rule; announcement of

effective date.

SUMMARY: On March 22, 2000 at 65 FR

15221, the Commission published the

text of revised regulations governing

filing of campaign finance reports with

State officers and the duties of State

officers concerning the reports. The

Commission announces that these rules

are effective as of June 7, 2000.

EFFECTIVE DATE: The amendment to 11

CFR 108.1, 108.2, 108.3, 108.4, and

108.6 as publiched at 65 FR 15221

(March 22, 2000), are effective as of June

7, 2000.

FOR FURTHER INFORMATION CONTACT: Ms.

Rosemary C. Smith, Assistant General

Counsel, or Ms. Rita A. Reimer,

Attorney, 999 E Street, NW.,

Washington, DC 20463, (202) 694–1650

or toll free (800) 424–9530.

SUPPLEMENTARY INFORMATION: The

Commission is announcing the effective

date of revised regulations at 11 CFR

Part 108, governing filing copies of

campaign finance reports and

statements with State officers. These

rules implement a 1995 amendment to

the Federal Election Campaign Act at 2

U.S.C. 439(c) that exempts States

meeting certain criteria from receipt and

maintenance requirements for reports

filed in connection with federal

elections.

The statutory amendment specifically

covers reports and statements filed with

the Commission, i.e., all except those

filed by Senate candidates, their

authorized committees, and committees

that support or oppose them, which are

filed with the Secretary of the Senate.

The new rules also exempt from State

receipt and maintenance requirements

reports filed with the Secretary of the

Senate that can be accessed

electronically from the Commission’s

Web site, www.fec.gov.

Section 438(d) of Title 2, United

States Code, requires that any rules or

regulations prescribed by the

Commission to carry out the provisions

of Title 2 of the United States Code be

transmitted to the Speaker of the House

of Representatives and the President of

the Senate thirty legislative days prior to

final promulgation. These rules were

transmitted to Congress on March 17,

2000. Thirty legislative days expired in

the Senate on May 16, 2000, and the

House of Representatives on May 23,

2000.

Darryl R. Wold,

Chairman, Federal Election Commission.

[FR Doc. 00–14241 Filed 6–6–00; 8:45 am]

BILLING CODE 6715–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–311–AD; Amendment

39–11744; AD 2000–10–20]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Lockheed Model L–

1011–385 series airplanes, that requires

repetitive inspections to detect cracking

of the fuselage skin in the areas of the

left- and right-hand stringerless sidewall

window belts, and repair, if necessary.

This amendment is prompted by reports

of fatigue cracks found in the fuselage

skin where the skin thickness steps from

0.40 to 0.23 inch. The actions specified

by this AD are intended to detect and

correct cracking of the fuselage skin,

which could result in reduced structural

integrity of the airplane.

DATES: Effective July 12, 2000. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of July 12, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Lockheed Martin Aircraft &

Logistics Center, 120 Orion Street,

Greenville, South Carolina 29605.

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 FAA,

Small Airplane Directorate, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; telephone (770) 703–6063; fax

(770) 703–6097.

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 all Lockheed Model

L–1011–385 series airplanes was

published in the Federal Register on

February 16, 2000 (65 FR 7801). That

action proposed to require require

repetitive inspections to detect cracking

of the fuselage skin in the areas of the

left- and right-hand stringerless sidewall

window belts, and repair, if necessary.

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 235

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

117 airplanes of U.S. registry will be

36054 Federal Register / Vol. 65, No. 110 / Wednesday, June 7, 2000 / Rules and Regulations

affected by this AD, that it will take

approximately 48 work hours per

airplane to accomplish the required

inspection, 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

$336,960, or $2,880 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.

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:

2000–10–20 Lockheed: Amendment 39–

11744. Docket 98–NM–311–AD.

Applicability: All Model L–1011–385

series airplanes, as listed in Lockheed

Service Bulletin 093–53–279, dated May 6,

1998; 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 (f) 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 and correct cracking of the

fuselage skin, which could result in reduced

structural integrity of the airplane,

accomplish the following:

(a) Perform an ultrasonic inspection on the

fuselage skin in the area of the stringerless

sidewall window belts, at the radii on both

the forward and aft sides of the machined

cutout where the fuselage skin steps from

0.40 to 0.23 inch, to detect cracking in the

base of the radii. Accomplish the inspection

in accordance with Lockheed Service

Bulletin 093–53–279, dated May 6, 1998, at

each of the 6 specific inspection zones

identified in the service bulletin at the later

of the times specified in paragraphs (a)(1)

and (a)(2) of this AD.

(1) Prior to the accumulation of 20,000

total flight cycles; or

(2) Within 600 flight cycles or 6 months

after the effective date of this AD, whichever

occurs first.

(b) For readings of less than 20 percent

obtained at all 6 inspection zones during the

ultrasonic inspection required by paragraph

(a) of this AD: Repeat the ultrasonic

inspection thereafter at intervals not to

exceed 1,500 flight cycles.

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

this AD: For any reading of 20 percent or

greater and less than or equal to 50 percent

obtained at any inspection zone during the

ultrasonic inspection required by paragraph

(a) of this AD, prior to further flight, perform

a low frequency eddy current (LFEC)

inspection to measure the depth of the

cracking, in accordance with Lockheed

Service Bulletin 093–53–279, dated May 6,

1998.

(1) If the results of the LFEC inspection are

outside the reject zone, as defined in the

service bulletin: Within 1,500 flight cycles,

repeat both the ultrasonic and LFEC

inspections specified by paragraphs (a) and

(c), respectively, of this AD.

(i) If the results of the LFEC inspection

specified by paragraph (c)(1) of this AD are

outside the reject zone: Within 1,800 flight

cycles after the initial crack finding, as

detected during the ultrasonic inspection

specified in paragraph (a) of this AD, repair

any affected inspection zone in accordance

with Part II of the Accomplishment

Instructions of the service bulletin. Such

repair constitutes terminating action for the

repetitive inspection requirements of this AD

for the repaired inspection zone only.

(ii) If the results of the LFEC inspection

specified by paragraph (c)(1) of this AD are

within the reject zone: Prior to further flight,

repair any affected inspection zone in

accordance with Part II of the

Accomplishment Instructions of the service

bulletin. Such repair constitutes terminating

action for the repetitive inspection

requirements of this AD for the repaired

inspection zone only.

(2) If the results of the LFEC inspection are

within the reject zone, as defined in the

service bulletin: Prior to further flight, repair

any affected inspection zone in accordance

with Part II of the Accomplishment

Instructions of the service bulletin. Such

repair constitutes terminating action for the

repetitive inspection requirements of this AD

for the repaired inspection zone only.

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

this AD: For any reading of 50 percent or

greater obtained at any inspection zone

during the ultrasonic inspection required by

paragraph (a) of this AD, prior to further

flight, perform a LFEC inspection to measure

the depth of the cracking, in accordance with

Lockheed Service Bulletin 093–53–279,

dated May 6, 1998.

(1) If the results of the LFEC inspection are

outside the reject zone, as defined in the

service bulletin: Within 300 flight cycles,

repeat both the ultrasonic and LFEC

inspections specified in paragraphs (a) and

(c), respectively, of this AD.

(i) If the results of the LFEC inspection

specified by paragraph (d)(1) of this AD are

outside the reject zone: Within 600 flight

cycles after the initial crack finding, as

detected during the ultrasonic inspection

specified in paragraph (a) of this AD, repair

any affected inspection zone in accordance

with Part II of the Accomplishment

Instructions of the service bulletin. Such

repair constitutes terminating action for the

repetitive inspection requirements of this AD

for the repaired inspection zone only.

(ii) If the results of the LFEC inspection

specified by paragraph (d)(1) of this AD are

within the reject zone: Prior to further flight,

repair any affected inspection zone in

accordance with Part II of the

Accomplishment Instructions of the service

bulletin. Such repair constitutes terminating

action for the repetitive inspection

requirements of this AD for the repaired

inspection zone only.

(2) If the results from the LFEC inspection

are within the reject zone, as defined in the

service bulletin: Prior to further flight, repair

any affected inspection zone in accordance

with Part II of the Accomplishment

Instructions of the service bulletin. Such

repair constitutes terminating action for the

repetitive inspection requirements of this AD

for the repaired inspection zone only.

(e) For any inspection results that require

repair in two adjacent zones: Prior to further

flight, repair in accordance with a method

approved by the Manager, Atlanta Aircraft

Certification Office (ACO), FAA, Small

Airplane Directorate.

Federal Register / Vol. 65, No. 110 / Wednesday, June 7, 2000 / Rules and Regulations 36055

Alternative Methods of Compliance

(f) 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, Atlanta

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(g) 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

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

this AD, the actions shall be done in

accordance with Lockheed Service Bulletin

093–53–279, dated May 6, 1998. 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

Lockheed Martin Aircraft & Logistics Center,

120 Orion Street, Greenville, South Carolina

29605. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

FAA, Small Airplane Directorate, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(i) This amendment becomes effective on

July 12, 2000.

Issued in Renton, Washington, on May 17,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14018 Filed 6–6–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–56–AD; Amendment 39–

11764; AD 2000–11–16]

RIN 2120–AA64

Airworthiness Directives; Ayres

Corporation S2R Series and Model 600

S2D Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 97–17–03,

which currently requires you to

accomplish the following on Ayres

Corporation (Ayres) S2R Series and

Model 600 S2D airplanes: inspect the

1⁄4-inch and 5⁄16-inch bolt hole areas on

the lower spar caps for fatigue cracking;

replace any lower spar cap where

fatigue cracking is found; and report any

fatigue cracking. This AD retains the

inspection and replacement (if

necessary) requirements of the lower

spar caps that are currently required in

AD 97–17–03. This AD also makes these

inspections repetitive, adds additional

airplanes to the Applicability of the AD,

changes the initial compliance time for

all airplanes, and arranges the affected

airplanes into groups (six) based on

usage and configurations. The existing

AD was the result of an accident of an

Ayres S2R series airplane where the

wing separated from the airplane in

flight. The actions specified by this AD

are intended to detect and correct

fatigue cracking of the lower spar caps,

which could result in the wing

separating from the airplane with

consequent loss of control of the

airplane.

DATES: This AD becomes effective on

July 25, 2000.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of July 25, 2000.

ADDRESSES: You may get the service

information referenced in this AD from

the Ayres Corporation, P.O. Box 3090,

One Rockwell Avenue, Albany, Georgia

31706–3090. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–56–

AD, 901 Locust, Room 506, Kansas City,

Missouri 64106; or at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Satish Lall, Aerospace Engineer, FAA,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30349; telephone: (770) 7036082;

facsimile: (770) 703–6097.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

Has FAA taken any action to this

point? An accident on an Ayres S2R

series airplane where the wing

separated from the airplane in flight

caused FAA to issue AD 9717–03,

Amendment 39–10195 (62 FR 43296,

August 18, 1997). AD 97–17–03

currently requires you to accomplish the

following:

• Inspect the 1/4-inch and 5/16-inch

bolt hole areas on the lower spar caps

for fatigue cracking;

• Replace any lower spar cap where

fatigue cracking is found; and

• Report any fatigue cracking to FAA.

Investigation of all resources available

to FAA at the time of the accident

showed nine occurrences of fatigue

cracking in the lower spar caps of Ayres

S2R airplanes, specifically emanating

from the 1⁄4-inch and 5⁄16-inch bolt

holes. Investigation of the abovereferenced accident revealed that the

cause can be attributed to fatigue cracks

emanating from the 1⁄2-inch and 5⁄16-

inch bolt holes in the lower spar caps.

Because the Ayres Model 600 S2D

airplanes have a similar type design to

that of the S2R series airplanes, they

were included in the Applicability of

AD 97–17–03.

Data indicates that the fatigue cracks

on these Ayres S2R series airplanes

become detectable at different times

based upon the type of engines and

design of the airplane. With this in

mind, FAA categorized these airplanes

into three groups for the Applicability of

AD 97–17–03.

Since issuing AD 97–17–03, we

received data specifying 29 additional

occurrences of fatigue cracks found in

the lower spar caps of Ayres S2R and

Model 600 S2D airplanes. The data from

these occurrences indicate the

following:

• Several of these occurrences

involved airplanes that had not

accumulated enough hours to require

the initial inspection of AD 97–17–03;

• Detectable cracks could still

develop after the initial inspection on

the affected airplanes; and

• Ayres has manufactured additional

airplanes that have a similar type design

to that of the airplanes affected by AD

97–17–03. The existing AD should also

cover these airplanes.

To address the above areas, FAA

issued a notice of proposed rulemaking

(NPRM) to supersede AD 97–17–03.

This NPRM was published in the

Federal Register on January 13, 1999

(64 FR 2157). The NPRM proposed to

supersede AD 97–17–03 with a new AD

that would:

• Retain the inspection and

replacement (if necessary) requirements

of the lower spar caps that are currently

required in AD 97–17–03;

• Make these inspections repetitive;

• Add additional airplanes to the

Applicability of the AD;

• Change the initial compliance time

for all airplanes; and

• Arrange the affected airplanes into

four groups instead of three based on

usage and configurations.