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

42201

Vol. 63, No. 152

Friday, August 7, 1998

UNITED STATES ENRICHMENT

CORPORATION

10 CFR Part 1101

Removal of Obsolete Sunshine Act

Regulations

AGENCY: United States Enrichment

Corporation.

ACTION: Final rule.

SUMMARY: The United States Enrichment

Corporation (USEC) is removing from

the Code of Federal Regulations obsolete

regulations under the Government in

the Sunshine Act because the USEC is

being privatized and will become a state

chartered corporation under the USEC

Privatization Act.

EFFECTIVE DATE: July 28, 1998.

ADDRESSES: 2 Democracy Center, 6903

Rockledge Drive, Bethesda, Maryland

20817.

FOR FURTHER INFORMATION CONTACT:

Elizabeth Stuckle, (301) 564–3399.

SUPPLEMENTARY INFORMATION: Pursuant

to the authority of the Energy Policy Act

of 1992 (Pub. L. 102–486, 106 Stat.

2776, 42 U.S.C. 2297 et seq.) and the

USEC Privatization Act, (42 U.S.C.

2297h et seq.), the privatization of USEC

is to be completed on July 28, 1998 (the

‘‘Privatization Date’’). On the

Privatization Date, the assets and the

obligations of USEC are transferred to a

state chartered corporation and the

interest of the United States in USEC is

transferred to the private sector.

Pursuant to 42 U.S.C. 2297h–3(b), the

state chartered corporation that

succeeds to the interests of USEC as of

the Privatization Date is not an agency,

instrumentality or establishment of the

United States, as Government

corporation or a Government-controlled

corporation. Because the statutory basis

for the regulations at 10 CFR Part 1101

will be eliminated, we remove those

regulations effective as of the

privatization. Because the statutory

basis for the regulations ceases in its

entirety upon the privatization date of

USEC, it is for good cause shown that

this final rule be published without

notice and without publication of a

proposed rule.

List of Subjects in 10 CFR Part 1101

Sunshine Act.

Decided: July 28, 1998.

Robert J. Moore,

General Counsel.

PART 1101—REMOVED

For the reasons set forth in the

premable and under the authority of 42

U.S.C. 2297 et seq., title 10 of the Code

of Federal Regulations is amended by

removing Part 1101.

[FR Doc. 98–21020 Filed 8–6–98; 8:45 am]

BILLING CODE 8270–01–M

UNITED STATES ENRICHMENT

CORPORATION

10 CFR Chapter XI and Part 1102

Removal of Obsolete Freedom of

Information Act Regulations and CFR

Chapter

AGENCY: United States Enrichment

Corporation.

ACTION: Final rule.

SUMMARY: The United States Enrichment

Corporation (USEC) is removing from

the Code of Federal Regulations obsolete

regulations under the Freedom of

Information Act and vacating its CFR

chapter because the USEC is being

privatized and will become a state

chartered corporation under the USEC

Privatization Act.

EFFECTIVE DATE: July 28, 1998.

ADDRESSES: 2 Democracy Center, 6903

Rockledge Drive, Bethesda, Maryland

20817.

FOR FURTHER INFORMATION CONTACT:

Elizabeth Stuckle, (301) 564–3399.

SUPPLEMENTARY INFORMATION: Pursuant

to the authority of the Energy Policy Act

of 1992 (Pub. L. 102–486, 106 Stat.

2776, 42 U.S.C. 2297 et seq.) and the

USEC Privatization Act, (42 U.S.C.

2297h et seq.), the privatization of USEC

is to be completed on July 28, 1998 (the

‘‘Privatization Date’’). On the

Privatization Date, the assets and the

obligations of USEC are transferred to a

state chartered corporation and the

interest of the United States in USEC is

transferred to the private sector.

Pursuant to 42 U.S.C. 2297h–3(b), the

state chartered corporation that

succeeds to the interests of USEC as of

the Privatization Date is not an agency,

instrumentality or establishment of the

United States, a Government

corporation or a Government-controlled

corporation. Because the statutory basis

for the regulations at 10 C.F.R. Part 1102

will be eliminated, we remove those

regulations effective as of the

privatization. Because the statutory

basis for the regulations ceases in its

entirety upon the privatization date of

USEC, it is for good cause shown that

this final rule be published without

notice and without publication of a

proposed rule.

List of Subjects in 10 CFR Part 1102

Freedom of information.

Decided: July 28, 1998.

Robert J. Moore,

General Counsel.

CHAPTER XI— [REMOVED]

PART 1102—[REMOVED]

For the reasons set forth in the

preamble and under the authority of 42

U.S.C. 2297 et seq., title 10 of the Code

of Federal Regulations is amended by

removing part 1102 and vacating

chapter XI.

[FR Doc. 98–21021 Filed 8–6–98; 8:45 am]

BILLING CODE 8270–01–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–03–AD; Amendment 39–

10691; AD 98–16–15]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model B.121 Series 1, 2,

and 3 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain British Aerospace

Model B.121 Series 1, 2, and 3

airplanes. This AD requires installing an
42202 Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations

inspection opening in the area of the

main spar web, repetitively inspecting

the area at the main spar web for cracks,

and repairing or replacing any cracked

part. This AD also requires installing

nuts of improved design at the wing to

fuselage main-spar attachment fittings.

This AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for the United Kingdom. The

actions specified by this AD are

intended to prevent structural failure of

the main spar web area caused by

fatigue cracking or separation of the

wing caused by loose nuts at the wing

to fuselage main-spar attachment

fittings, which could result in loss of

control of the airplane.

DATES: Effective September 21, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

21, 1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

British Aerospace (Operations) Limited,

British Aerospace Regional Aircraft,

Prestwick International Airport,

Ayrshire, KA9 2RW, Scotland;

telephone: (01292) 479888; facsimile:

(01292) 479703. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–03–

AD, Room 1558, 601 E. 12th Street,

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: Mr.

Roger Chudy, Aerospace Engineer,

Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6932; facsimile:

(816) 426–2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain British Aerospace

Model B.121 Series 1, 2, and 3 airplanes

was published in the Federal Register

as a notice of proposed rulemaking

(NPRM) on March 16, 1998 (63 FR

12708). The NPRM proposed to require

installing an inspection opening in the

area of the main spar web, repetitively

inspecting the area at the main spar web

for cracks and the area of the wing to

fuselage attach bolt holes for corrosion,

and repairing or replacing any cracked

or corroded part. Accomplishment of

the proposed inspections as specified in

the NPRM would be required in

accordance with British Aerospace PUP

Mandatory Service Bulletin No. B121/

102, Revision No. 1, Issued April 16,

1997. If necessary, the proposed repair

or replacement would be required in

accordance with a scheme obtained

from the manufacturer through the FAA,

Small Airplane Directorate.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for the United

Kingdom.

After issuance of the NPRM, British

Aerospace developed additional service

information to that referenced in the

previous proposal to include the

installation of nuts of improved design

at the wing to fuselage main-spar

attachment fittings and the deletion of

the inspection at the area of the wing to

fuselage attach bolt holes for corrosion.

The improved design nuts provide

better torque retention than the ones

originally installed.

In addition, British Aerospace reexamined the service history and

evaluated reports from the field and

changed the compliance time (that is

referenced in the service information)

for the inspection opening installation

and the initial eddy current inspection

to upon the accumulation of 2,000

flying hours.

To incorporate the above changes,

British Aerospace issued the following

service bulletins, which supersede

British Aerospace PUP Mandatory

Service Bulletin No. B121/102, Revision

No. 1, Issued April 16, 1997:

—British Aerospace PUP Mandatory

Service Bulletin No. B121/106, dated

January 12, 1998, which specifies

procedures for replacing the nuts

(with improved design nuts) at the

wing to fuselage main-spar

attachment fittings; and

—British Aerospace PUP Mandatory

Service Bulletin No. B121/105, dated

January 12, 1998, which specifies

procedures for installing an

inspection opening in the area of the

main spar web, and inspecting the

area at the main spar web for cracks.

These procedures are basically the

same as contained in British

Aerospace PUP Mandatory Service

Bulletin No. B121/102, Revision No.

1, Issued April 16, 1997.

This prompted the FAA to issue a

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

certain British Aerospace Model B.121

Series 1, 2, and 3 airplanes. This

proposal was published in the Federal

Register as a supplemental NPRM on

May 29, 1998 (63 FR 29362). The

supplemental NPRM proposed to also

require installing nuts of improved

design at the wing to fuselage main-spar

attachment fittings and deleting the

inspection at the area of the wing to

fuselage attach bolt holes for corrosion.

Accomplishment of the proposed action

as specified in the supplemental NPRM

would be in accordance with the service

information previously referenced.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 2 airplanes in

the U.S. registry will be affected by this

AD; that it will take approximately 37

workhours per airplane to accomplish

the initial inspection, inspection

opening installation, and improved

design nut installations; that the average

labor rate is approximately $60 an hour.

There is no cost for the parts to

accomplish the replacements. Based on

these figures, the total cost impact of

this AD on U.S. operators is estimated

to be $4,440, or $2,220 per airplane.

These figures only take into account the

cost of the initial inspections,

inspection opening installation, and

improved design nut installations; and

do not take into account the cost of

repetitive inspections. The FAA has no

way of determining the number of

repetitive inspections each owner/

operator of the affected airplanes will

incur.

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
Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations 42203

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

under the criteria of the Regulatory

Flexibility Act. A copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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 a new airworthiness directive

(AD) to read as follows:

98–16–15 British Aerospace (Operations)

Limited: Amendment 39–10691; Docket

No. 98–CE–03–AD.

Applicability: Model B.121 Series 1, 2, and

3 airplanes, all serial numbers, 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 in the

body of this AD, unless already

accomplished.

To prevent structural failure of the main

spar web area caused by fatigue cracking or

separation of the wing caused by loose nuts

at the wing to fuselage main-spar attachment

fittings, which could result in loss of control

of the airplane, accomplish the following:

(a) Within the next 100 hours time-inservice (TIS) after the effective date of this

AD, replace the nuts (with improved design

nuts) at the wing to fuselage main-spar

attachment fittings in accordance with

British Aerospace PUP Mandatory Service

Bulletin No. B121/106, dated January 12,

1998.

(b) Upon accumulating 2,000 hours TIS on

the main spar or within the next 50 hours TIS

after the effective date of this AD, whichever

occurs later, install an inspection opening

and inspect, using eddy current methods, the

area at the main spar web for cracks in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of British Aerospace

PUP Mandatory Service Bulletin No. B121/

105, dated January 12, 1998.

Note 2: Accomplishing the installation

inspection opening and initial eddy current

inspection required by this AD in accordance

with British Aerospace PUP Mandatory

Service Bulletin No. B121/102, Revision No.

1, Issued April 16, 1997, is considered

‘‘already accomplished’’ for the requirements

of paragraph (b) of this AD.

(c) Within 800 hours TIS after the initial

inspection required by paragraph (b) of this

AD, and thereafter at intervals not to exceed

800 hours TIS, reinspect the area of the main

spar web as specified in paragraph (b) of this

AD.

(d) If any cracks are found during any

inspection required by this AD, prior to

further flight, accomplish the following:

(1) Obtain a repair or replacement scheme

from the manufacturer through the FAA,

Small Airplane Directorate, at the address

specified in paragraph (f) of this AD; and

(2) Incorporate this scheme and continue to

repetitively inspect as required by paragraph

(c) of this AD, unless specified differently in

the instructions to the repair or replacement

scheme.

(e) 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.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(g) Questions or technical information

related to British Aerospace PUP Mandatory

Service Bulletin No. B121/106, dated January

12, 1998, and British Aerospace PUP

Mandatory Service Bulletin No. B121/105,

dated January 12, 1998, should be directed to

British Aerospace (Operations) Limited,

British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland; telephone: (01292)

479888; facsimile: (01292) 479703. This

service information may be examined at the

FAA, Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri.

(h) The replacements, installation, and

inspections required by this AD shall be done

in accordance with British Aerospace PUP

Mandatory Service Bulletin No. B121/106,

dated January 12, 1998, and British

Aerospace PUP Mandatory Service Bulletin

No. B121/105, dated January 12, 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 British

Aerospace (Operations) Limited, British

Aerospace Regional Aircraft, Prestwick

International Airport, Ayrshire, KA9 2RW,

Scotland. Copies may be inspected at the

FAA, Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri, 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 British AD 005–01–98, not dated.

(i) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 28,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–20840 Filed 8–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–30–AD; Amendment 39–

10692; AD 98–16–16]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Model PC–7 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Pilatus Aircraft Ltd.

Model PC–7 airplanes. This AD requires

replacing the seal unit on both main

landing gear (MLG) legs and the nose

landing gear (NLG) leg. This AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

Switzerland. The actions specified by