31824 Federal Register / Vol. 61, No. 121 / Friday, June 21, 1996 / Rules and Regulations

FEDERAL ELECTION COMMISSION

11 CFR Parts 100, 110 and 114

[Notice 1996–12]

Candidate Debates and News Stories

AGENCY: Federal Election Commission.

ACTION: Final rule: Announcement of

effective date.

SUMMARY: On April 24, 1996, the

Commission published the text of

revised regulations governing candidate

debates and news stories produced by

cable television organizations. 61 FR

18049. These regulations implement

portions of the Federal Election

Campaign Act of 1971, as amended. The

Commission announces that these rules

are effective as of June 21, 1996.

EFFECTIVE DATE: June 21, 1996.

FOR FURTHER INFORMATION CONTACT: Ms.

Susan E. Propper, Assistant General

Counsel, or Ms. Rosemary C. Smith,

Senior Attorney, 999 E Street, NW.,

Washington, DC 20463, (202) 219–3690

or toll free (800) 424–9530.

SUPPLEMENTARY INFORMATION: Today, the

Commission is announcing the effective

date of new regulations governing

candidate debates and news stories

produced by cable television

organizations. The new rules are being

incorporated into parts 100, 110 and 114

of the existing regulations.

Section 438(d) of Title 2, United

States Code, requires that any rule or

regulation prescribed by the

Commission to implement 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. The revisions to 11 CFR

100.7(b)(2), 100.8(b)(2), 110.13 and

114.4(f) were transmitted to Congress on

April 18, 1996. Thirty legislative days

expired in the Senate on June 7, 1996

and in the House of Representatives on

June 10, 1996.

Announcement of Effective Date

11 CFR 100.7(b)(2), 100.8(b)(2), 110.13

and 114.4(f), as published at 61 FR

18049 on April 24, 1996 are effective as

of June 21, 1996.

Dated: June 17, 1996.

Lee Ann Elliott,

Chairman, Federal Election Commission.

[FR Doc. 96–15792 Filed 6–20–96; 8:45 am]

BILLING CODE 6715–01–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–170–AD; Amendment

39–9673; AD 96–13–05]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Series Airplanes (Excluding

Model F28 Mark 0100 Series Airplanes)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F28

series airplanes, that requires a one-time

detailed visual inspection to detect

cracking of the elevator gust lock

housing and the gust lock support

structure, and repair or replacement of

cracked parts. This amendment is

prompted by a report of failure of an

elevator gust lock housing due to fatigue

cracking. The actions specified by this

AD are intended to prevent fatigue

cracking of the elevator gust lock

housing and the gust lock support

structure, which could result in loss of

the elevator and the support structure,

and possible consequent loss of primary

pitch control.

DATES: Effective July 26, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 26,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. 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:

Connie Beane, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2796; fax (206) 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 Fokker

Model F28 series airplanes was

published in the Federal Register on

April 1, 1996 (61 FR 14275). That action

proposed to require a one-time detailed

visual inspection to detect cracking of

the elevator gust lock housing and the

gust lock support structure, and repair

or replacement of cracked parts with

new or serviceable parts. For airplanes

on which cracking is found, that action

also prohibited use of the gust lock

system until cracked parts were

replaced.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Support for the Proposal

Both commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, 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 43 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.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $5,160, or $120 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 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 Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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
Federal Register / Vol. 61, No. 121 / Friday, June 21, 1996 / Rules and Regulations 31825

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:

96–13–05 Fokker: Amendment 39–9673.

Docket 95–NM–170–AD.

Applicability: Model F28 series airplanes;

serial numbers 11003 through 11241

inclusive, 11991, and 11992; certificated in

any category.

Note 1: Fokker Model F28 Mark 0100 series

airplanes are not subject to the requirements

of this AD.

Note 2: 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 (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 cracking of the elevator

gust lock housing and the gust lock support

structure, which could result in loss of the

elevator and the support structure, and

subsequent possible loss of primary pitch

control, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform a one-time detailed

visual inspection to detect cracking of the

elevator gust lock housing and the gust lock

support structure, in accordance with Fokker

Service Bulletin F28/55–30, Revision 1,

dated January 4, 1993.

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

flight, repair or replace the cracked elevator

gust lock housing or gust lock support

structure with a new or serviceable part in

accordance with Fokker Service Bulletin

F28/55–30, Revision 1, dated January 4,

1993. Use of the elevator gust lock system is

prohibited until cracked parts are replaced

with new or serviceable parts.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(d) 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.

(e) The inspection, repair, and replacement

shall be done in accordance with Fokker

Service Bulletin F28/55–30, Revision 1,

dated January 4, 1993, which contains the

following list of effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1–2 ............... 1 .............. Jan. 4, 1993.

3–5 ............... Original .... Aug. 24, 1992.

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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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.

(f) This amendment becomes effective on

July 26, 1996.

Issued in Renton, Washington, on June 13,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15603 Filed 6–20–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–151–AD; Amendment

39–9674; AD 96–13–06]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Series Airplanes (Excluding

Fokker Model F28 Mark 0100 Series

Airplanes)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F28

series airplanes, that requires

replacement of junction fittings of the

horizontal stabilizer with improved

fittings. For certain airplanes, this

amendment also requires replacement of

the drive-fitting bushings and bolts of

the horizontal stabilizer with improved

bushings and bolts. This amendment is

prompted by reports of stress corrosion

cracking in a junction fitting lug of the

horizontal stabilizer. The actions

specified by this AD are intended to

prevent such cracking, which could

result in failure of a lug and

uncommanded movement of the

horizontal stabilizer. This condition, if

not corrected, could result in reduced

controllability of the airplane.

DATES: Effective July 26, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 26,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. 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: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 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 Fokker

Model F28 series airplanes was

published in the Federal Register on