63912 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules

§ 50.68 Criticality accident requirements.

(a) Each holder of a construction

permit or operating license for a nuclear

power reactor issued under this part, or

a combined license for a nuclear power

reactor issued under part 52 of this

chapter shall comply with either 10 CFR

70.24 of this chapter or requirements in

paragraph (b).

(b) Each licensee shall comply with

the following requirements in lieu of

maintaining a monitoring system

capable of detecting a criticality as

described in 10 CFR 70.24:

(1) Plant procedures may not permit

handling and transportation at any one

time of more fuel assemblies than have

been determined to be safely subcritical

under the most adverse moderation

conditions feasible by unborated water.

(2) The estimated ratio of neutron

production to neutron absorption and

leakage (k-effective) of the fresh fuel in

the fresh fuel storage racks shall be

calculated assuming the racks are

loaded with fuel of the maximum

permissible U–235 enrichment and

flooded with pure water and must not

exceed 0.95, at a 95 percent probability,

95 percent confidence level.

(3) If optimum moderation of fresh

fuel in the fresh fuel storage racks

occurs when the racks are assumed to be

loaded with fuel of the maximum

permissible U–235 enrichment and

filled with low-density hydrogenous

fluid, the k-effective corresponding to

this optimum moderation must not

exceed 0.98, at a 95 percent probability,

95 percent confidence level.

(4) If no credit for soluble boron is

taken, the k-effective of the spent fuel

storage racks loaded with fuel of the

maximum permissible U–235

enrichment must not exceed 0.95, at a

95 percent probability, 95 percent

confidence level, if flooded with pure

water. If credit is taken for soluble

boron, the k-effective of the spent fuel

storage racks loaded with fuel of the

maximum permissible U–235

enrichment must not exceed 0.95, at a

95 percent probability, 95 percent

confidence level, if flooded with borated

water, and the k-effective must remain

below 1.0 (subcritical), at a 95 percent

probability, 95 percent confidence level,

if flooded with pure water.

(5) The quantity of SNM, other than

nuclear fuel stored on site, is less than

the quantity necessary for a critical

mass.

(6) Radiation monitors, as required by

GDC 63, are provided in storage and

associated handling areas when fuel is

present to detect excessive radiation

levels and to initiate appropriate safety

actions.

(7) The maximum nominal U–235

enrichment of the fresh fuel assemblies

is limited to no greater than five (5.0)

percent by weight.

PART 70—DOMESTIC LICENSING OF

SPECIAL NUCLEAR MATERIAL

1. The authority citation for 10 CFR

Part 70 continues to read as follows:

Authority: Secs. 51, 53, 161, 182, 183, 68

Stat. 929, 930, 948, 953, 954, as amended,

sec. 234, 83 Stat. 444, as amended, sec. 1701,

106 Stat. 2951, 2952, 2953 (42 U.S.C. 2071,

2073, 2201, 2232, 2233, 2282, 2297f); secs.

201, as amended, 202, 204, 206, 88 Stat.

1242, as amended, 1244, 1245, 1246, (42

U.S.C. 5841, 5842, 5845, 5846).

Sections 70.1(c) and 70.20a(b) also issued

under secs. 135, 141, Pub. L. 97–425, 96 Stat.

2232, 2241 (42 U.S.C. 10155, 10161). Section

70.7 also issued under Pub. L. 95–601, sec.

10, 92 Stat. 2951 (42 U.S.C. 5851). Section

70.21(g) also issued under sec. 122, 68 Stat.

939 (42 U.S.C. 2152). Section 70.31 also

issued under sec. 57d, Pub. L. 93–377, 88

Stat. 475 (42 U.S.C. 2077). Sections 70.36 and

70.44 also issued under sec. 184, 68 Stat. 954,

as amended (42 U.S.C. 2234).

Section 70.61 also issued under secs. 186,

187, 68 Stat. 955 (42 U.S.C. 2236, 2237).

Section 70.62 also issued under sec. 108, 68

Stat. 939, as amended (42 U.S.C. 2138).

2. In § 70.24, paragraph (d) is revised

to read as follows:

§ 70.24 Criticality accident requirements.

* * * * *

(d) The requirements in paragraph (a)

through (c) of this section do not apply

to holders of a construction permit or

operating license for a nuclear power

reactor issued pursuant to part 50 of this

chapter, or combined licenses issued

under part 52 of this chapter, if the

holders comply with the requirements

of paragraph (b) of 10 CFR 50.68 of this

chapter.

Dated at Rockville, Maryland this 14th day

of November, 1997.

For the Nuclear Regulatory Commission.

L. Joseph Callan,

Executive Director for Operations.

[FR Doc. 97–31732 Filed 12–2–97; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–22–AD]

Airworthiness Directives; Eurocopter

France (Formerly Aerospatiale, Society

Nationale Industrielle, Sud Aviation)

Model SA–365N, SA–365N1, AS–365N2,

and SA–366G1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

Eurocopter France (formerly

Aerospatiale, Society Nationale

Industrielle, Sud Aviation) Model SA–

365N, SA–365N1, AS-365N2, and SA–

366G1 helicopters. This proposal would

require an inspection of the

transmission deck for cracks; repair of

any cracked transmission decks; and

replacement of the transmission deck

support beams (support beams) with

redesigned support beams. This

proposal is prompted by several reports

of cracks in the transmission deck and

support beams. The actions specified by

the proposed AD are intended to detect

cracks that reduce the strength of the

main gearbox strut attachment and

could result in failure of the main

gearbox mounting, and subsequent loss

of control of the helicopter.

DATES: Comments must be received by

February 2, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 96–SW–22–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays.

The service information referenced in

the proposed rule may be obtained from

American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr.

Mike Mathias, Aerospace Engineer,

FAA, Rotorcraft Directorate, ASW–111,

2601 Meacham Blvd., Fort Worth, Texas
Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules 63913

76137, telephone (817) 222–5123, fax

(817) 222–5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 96–SW–22–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 96–SW–22–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

The Direction Generale De L’Aviation

Civile (DGAC), which is the

airworthiness authority for France

recently notified the FAA that an unsafe

condition may exist on Eurocopter

France SA–365N, SA–365N1, AS–

365N2, and SA–366G1 helicopters. The

DGAC advises that cracks were

discovered in one of the two support

beams under the transmission deck and

in the transmission deck itself.

Eurocopter France has issued Telex

Service No. 10011, dated February 24,

1995, which specifies checks for cracks

in the transmission deck and

transmission deck support beams, to be

accomplished within 50 hours following

receipt of the Telex Service. The Telex

Service applies to affected aircraft that

have 4,000 or more flying hours. The

DGAC classified this service bulletin as

mandatory and issued AD 95–067–

038(B), and AD 95–068–017(B), both

dated April 12, 1995, in order to assure

the continued airworthiness of these

helicopters in France.

Subsequently, Eurocopter France

issued Eurocopter Service Bulletin

05.00.36 on November 14, 1995.

Eurocopter Service Bulletin 05.00.36

recommends replacement of the current

transmission support beams, part

numbers (P/N) 365A21–3365–49 and

365A21–3365–CY with redesigned

support beams P/N 365A21–3365–JE–01

and 365A21–3365–JF–01, at major

maintenance intervals specified by the

service bulletin.

This helicopter model is

manufactured in France and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Eurocopter France

Model SA–365N, SA–365N1, AS–

365N2, and SA–366G1 helicopters of

the same type design registered in the

United States, the proposed AD would

require inspections of the transmission

deck, repair of any cracks that are

found, and replacement of the support

beams, P/N 365A21–3365–49 and

365A21–3365–CY, with redesigned

support beams, P/N 365A21–3365–JE–

01 and 365A21–3365–JF–01. For Model

AS–365N2 helicopters, the inspections

must be accomplished before or upon

the accumulation of 2,000 hours timein-service (TIS), or within 50 hours TIS

after the effective date of this AD,

whichever occurs later. For Model SA–

365N, SA–365N1, and SA–366G1

helicopters, the inspections must be

accomplished upon the accumulation of

4,000 hours TIS, or within 50 hours TIS

after the effective date of this AD,

whichever occurs later. The support

beams must be replaced with reinforced

beams whether or not cracks are found

in the transmission deck or the

currently installed support beams. If

cracks are found in the transmission

deck; the repairs must be accomplished.

After any cracks that are found in the

transmission deck have been repaired

and after replacing the support beams,

clean, prime, and paint the affected

areas of the transmission deck and the

replacement support beams in

accordance with the referenced service

information.

The FAA estimates that 137

helicopters of U.S. registry would be

affected by this proposed AD, that it

would take approximately 50 work

hours per helicopter to accomplish the

proposed actions, and that the average

labor rate is $60 per work hour.

Required parts would cost

approximately $5,000 per helicopter.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $1,096,000.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:
63914 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

Eurocopter France (Formerly Aerospatiale,

Society Nationale Industrielle, Sud

Aviation): Docket No. 96–SW–22–AD.

Applicability: Model SA–365N, SA–365N1,

AS–365N2, and SA–366G1 helicopters,

certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To detect cracks that reduce the strength of

the main gearbox strut attachment and could

result in failure of the main gearbox

mounting, and subsequent loss of control of

the helicopter, accomplish the following:

(a) For Model SA–365N, SA–365N1, and

SA–366G1 helicopters, on or before attaining

4,000 hours time-in-service (TIS), or within

50 hours TIS after the effective date of this

AD, whichever occurs later; and for Model

SA–365N2 helicopters, on or before attaining

2,000 hour TIS, or within 50 hours TIS after

the effective date of this AD, whichever

occurs later; perform the following:

(1) Inspect the transmission deck for cracks

using a dye-penetrant inspection method, in

accordance with paragraph BB of Eurocopter

France Telex Service No. 10011, dated

February 24, 1995. If a crack is found in the

transmission deck, repair prior to further

flight.

Note 2: A FAA-approved repair solution

can be initiated by contacting the American

Eurocopter Technical Support Department,

ATTN: Manager, telephone: 972–641–3460,

fax: 972–641–3527.

(2) Replace the currently installed

transmission deck support beams, part

numbers (P/N) 365A21–3365–49 and

365A21–3365–CY, with reinforced

transmission deck support beams, P/N

365A21–3365–JE–01 and 365A21–3365–JF–

01, in accordance with the Accomplishment

Instructions in Eurocopter France Service

Bulletin No. 05.00.36, Rev. 1, dated

December 16, 1996.

(b) After completion of paragraphs (a)(1)

and (a)(2) of this AD, clean, prime and paint

the affected areas of the transmission deck

and the reinforced support beams in

accordance with paragraph BB 2A of

Eurocopter France Telex Service No. 10011,

dated February 24, 1995.

(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, Rotorcraft

Standards Staff, FAA, Rotorcraft Directorate.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Rotorcraft Certification

Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 95–068–017(B) and AD 95–067–

038(B), both dated April 12, 1995.

Issued in Fort Worth, Texas, on November

24, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–31614 Filed 12–2–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–72–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Models B200,

B200C, and B200T Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Raytheon Aircraft Company (Raytheon)

Models B200, B200C, and B200T

airplanes (formerly referred to as Beech

Models B200, B200C, and B200T

airplanes). The proposed AD would

require replacing the wiring for the

engine fire detector system with fire

resistant wiring. The proposed AD is the

result of the discovery during aircraft

production of the potential for the

existing engine fire detector system

wiring on the affected airplanes to fail

because of high heat and/or fire. The

actions specified by the proposed AD

are intended to prevent failure of the

engine fire detector system if high heat

and/or fire stopped an electrical signal

between the engine fire detectors and

the engine fire warning annunciator

lights located in the cockpit, which

could result in passenger injury in the

event of an airplane fire.

DATES: Comments must be received on

or before February 4, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–72–

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

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from the

Raytheon Aircraft Company, P.O. Box

85, Wichita, Kansas 67201–0085. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Randy Griffith, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4145; facsimile

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following