Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations 31607

List of Subjects in 10 CFR Part 35

Byproduct material, Criminal

penalties, Drugs, Health facilities,

Health professions, Medical devices,

Nuclear materials, Occupational safety

and health, Radiation protection,

Reporting and recordkeeping

requirements.

For the reasons set out in the

preamble and under the authority of the

Atomic Energy Act of 1954, as amended,

the Energy Reorganization Act of 1974,

as amended, and 5 U.S.C. 552 and 553,

the NRC is adopting the following

amendment to 10 CFR part 35.

PART 35—MEDICAL USE OF

BYPRODUCT MATERIAL

1. The authority citation for part 35

continues to read as follows:

Authority: Secs. 81, 161, 182, 183, 68 Stat.

935, 948, 953, 954, as amended (42 U.S.C.

2111, 2201, 2232, 2233); sec. 201, 88 Stat.

1242, as amended (42 U.S.C. 5841).

2. The introductory text of § 35.18 is

revised to read as follows:

§ 35.18 License issuance.

The Commission shall issue a license

for the medical use of byproduct

material if:

* * * * *

Dated at Rockville, Md., this 20th day of

May 1998.

For the Nuclear Regulatory Commission.

L. Joseph Callan,

Executive Director for Operations.

[FR Doc. 98–15400 Filed 6–9–98; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–97–AD; Amendment

39–10582; AD 98–12–28]

RIN 2120–AA64

Airworthiness Directives; CASA Model

C–212 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all CASA Model C–212

series airplanes, that requires repetitive

inspections for cracking in the false spar

of the wing, and repair, if necessary.

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 detect and correct cracking

in the false spar, which could result in

reduced structural integrity of the wing.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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) to

include an airworthiness directive (AD)

that is applicable to all CASA Model C–

212 series airplanes was published in

the Federal Register on April 9, 1998

(63 FR 17341). That action proposed to

require repetitive inspections for

cracking in the false spar of the wing,

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

The FAA estimates that 41 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 30

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 inspection required by this AD on

U.S. operators is estimated to be

$73,800, or $1,800 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 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

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:

98–12–28 Construcciones Aeronauticas, S.A.

(CASA): Amendment 39–10582. Docket

98-NM–97-AD.

Applicability: All Model C–212 series

airplanes, 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
31608 Federal Register / Vol. 63, No. 111 /Wednesday, June 10, 1998 /Rules and Regulations

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 (b) 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 in the false

spar of the wing, which could result in

reduced structural integrity of the wing,

accomplish the following:

(a) Within 1,200 flight hours after the

effective date of this AD, perform a detailed

visual inspection for cracking in the false

spar of the wing, on the left and right sides

of the airplane, in accordance with CASA

Product Support Document COM 212–224,

dated November 28, 1990.

(1) If no cracking is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 1,200 flight hours.

(2) If any cracking is detected, prior to

further flight, repair in accordance with a

method approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Direccio ́n General de Aviacio ́n (DGAC),

which is the airworthiness authority for

Spain (or its delegated agent). Repeat the

detailed visual inspection thereafter at

intervals not to exceed 1,200 flight hours.

(b) 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 request 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.

(c) 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.

(d) The inspections shall be done in

accordance with CASA Product Support

Document COM 212–224, dated November

28, 1990. 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 Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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 Spanish airworthiness directive 02/96,

dated May 13, 1996.

(e) This amendment becomes effective on

July 15, 1998.

Issued in Renton, Washington, on June 3,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15254 Filed 6–9–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–53–AD; Amendment

39–10581; AD 98–12–27]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

BAe Model ATP airplanes, that requires

repetitive magnetic particle inspections

to detect cracking of the splined

operating shaft of the internal door

handle on the forward passenger door,

rear passenger door, and rear baggage

door; and corrective actions, if

necessary. 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 detect and correct cracking

of the splined operating shaft of the

internal door handle, which could result

in failure of the internal door handle,

inability to operate the door during an

emergency evacuation, and consequent

injury to airplane occupants.

DATES: Effective July 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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) to

include an airworthiness directive (AD)

that is applicable to certain British

Aerospace BAe Model ATP airplanes

was published in the Federal Register

on April 9, 1998 (63 FR 17342). That

action proposed to require repetitive

magnetic particle inspections to detect

cracking of the splined operating shaft

of the internal door handle on the

forward passenger door, rear passenger

door, and rear baggage door; and

corrective actions, 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

The FAA estimates that 10 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 18

work hours per airplane to accomplish

the required magnetic particle

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the magnetic

particle inspection required by this AD

on U.S. operators is estimated to be

$10,800, or $1,080 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 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