34602 Federal Register / Vol. 65, No. 105 / Wednesday, May 31, 2000 / Proposed Rules

emergency core cooling system (ECCS)

that must be designed so that its

calculated cooling performance

following postulated loss-of-coolant

accidents conforms to the criteria set

forth in paragraph (b) of this section.

...

3. In Section 50.46, a new paragraph

(e) is added to read as follows:

(e) Approved cylindrical zirconiumbased alloys are those whose

performance has been evaluated and

determined by the NRC to conform to

the acceptance criteria of paragraphs

§ 50.46(b)(1) and (b)(2).

Dated at Rockville, Maryland this 24th day

of May, 2000.

For the Nuclear Regulatory Commission.

Annette L. Vietti-Cook,

Secretary of the Commission.

[FR Doc. 00–13515 Filed 5–30–00; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–15–AD]

RIN 2120–AA64

Airworthiness Directives; Turbomeca

Artouste II and Artouste III Series

Turboshaft Engines

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

Turbomeca Artouste II and Artouste III

series turboshaft engines. This proposal

would require installation of

modification TU 24, TU 167 or TU 164,

depending on the specific engine model.

These modifications would prevent

uncommanded partial closing or total

closing of the electrical fuel cock, which

would prevent uncommanded in-flight

engine shutdown. From the effective

date of this AD, and until the

modifications are installed, this

proposal would also limit the duration

of the engine operating cycle. This

proposal is prompted by reports of

unexpected power loss during test

flights. The actions specified by the

proposed AD are intended to prevent

unexpected power loss, which could

result in an uncommanded in-flight

engine shutdown, autorotation, and

forced landing.

DATES: Comments must be received by

July 31, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–15–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

submitted to the Rules Docket by using

the following Internet address: ‘‘9-aneadcomment@faa.gov’’. Comments may

be inspected at this location between

8:00 a.m. and 4:30 p.m., Monday

through Friday, except Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Turbomeca, 40220 Tarnos, France;

telephone 33 05 59 64 40 00, fax 33 05

59 64 60 80. This information may be

examined at the FAA, New England

Region, Office of the Regional Counsel,

12 New England Executive Park,

Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Glorianne Niebuhr, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299, telephone (781) 238–7132,

fax (781) 238–7199.

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 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 Number 2000–NE–15–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–15–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Director General de L’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the Federal Aviation

Administration (FAA) that an unsafe

condition may exist on Turbomeca

Artouste II and Artouste III series

turboshaft engines. The DGAC advises

that it has received reports of

unexpected power loss in service. This

power loss is due to closing of the

electrical fuel cock. This condition, if

not corrected, could result in

unexpected power loss, which could

result in an uncommanded in-flight

engine shutdown, autorotation, and

forced landing.

Service Information

Turbomeca has issued Artouste II

Service Bulletin (SB) No. 223 72 0070,

dated January 21, 1999, that specifies

procedures for installing modification

TU 24, which provides an equipped

relay inside the control unit. Turbomeca

has also issued Artouste III SB No. 218

80 0098, dated January 14, 1999 and SB

No. 218 80 0093, Revision 2, dated

January 14, 1999 which state similar

requirements and specify procedures for

installation of modifications TU 164 and

TU 167 respectively. The DGAC

classified these SB’s as mandatory and

issued Airworthiness Directive (AD)

1999–005(A), dated January 13, 1999,

and AD 1999–090(A), dated February

24, 1999, in order to ensure the

airworthiness of these engines in

France.

Bilateral Airworthiness Agreement

This engine 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.

Federal Register / Vol. 65, No. 105 / Wednesday, May 31, 2000 / Proposed Rules 34603

Proposed Actions

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines used on

helicopters of the same type design

registered in the United States, the

proposed AD would require installation

of modification TU 24, TU 164 or TU

167 at the earliest of the following:

• The next shop visit after the

effective date of this AD, or

• Within 30 days after the effective

date of this AD, or

• Within 120 cycles-in-service after

the effective date of this AD.

The actions would be required to be

accomplished in accordance with the

SB’s described previously. This

proposal will also limit the duration of

the engine operating cycle, from the

effective date of this AD, to a two-hour

cycle (engine start/stop) until the

modifications are installed.

Economic Analysis

There are approximately 3,102

engines of the affected design in the

worldwide fleet. The FAA estimates that

213 engines installed on aircraft of US

registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per engine

to accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Required parts would cost

approximately $630 per engine. Based

on these figures, the total cost impact of

the proposed AD on US operators is

estimated to be $159,750. The

manufacturer has advised the DGAC

that it may provide modifications TU

164 and TU 167 at no cost to the

operator, thereby substantially reducing

the cost impact of this proposed rule.

Regulatory Impact

This proposal does not have

federalism implications, as defined in

Executive Order 13132, because it

would 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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this proposal.

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:

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:

Turbomeca: Docket No. 2000–NE–15–AD.

Applicability: This airworthiness

directive (AD) applies to Turbomeca

Artouste II and Artouste III B, B1 and D

series turboshaft engines. These engines

are installed on, but not limited to,

Alouette II SE 3130, Alouette II SE 313

B, Eurocopter SA 315 LAMA and SA

316 Alouette III series helicopters.

Note 1: This AD applies to each engine

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

engines 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 (h) 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 unexpected power loss,

which could result in an uncommanded

in-flight engine shutdown, autorotation,

and forced landing, accomplish the

following:

For Artouste II Engines

(a) As of the effective date of this AD,

the duration of the operating cycle

(start-up to shutdown) is limited to two

hours total until modification TU 24 is

installed in accordance with Turbomeca

Artouste II Service Bulletin 218 80 0070,

Section 2, dated January 21, 1999.

(b) At the next shop visit, within 30

days, or within 120 cycles after the

effective date of this AD, whichever

occurs first, install modification TU 24

in accordance with Turbomeca Artouste

II Service Bulletin 218 80 0070, Section

2, dated January 21, 1999.

For Artouste III B and Artouste III B1

Engines

(c) As of the effective date of this AD,

the duration of the operating cycle

(start-up to shutdown) is limited to two

hours total until modification TU 167 is

installed in accordance with Turbomeca

Artouste III Service Bulletin 218 80

0093, Revision 2, Section 2, dated

January 14, 1999.

(d) At the next shop visit, within 30

days, or within 120 cycles after the

effective date of this AD, whichever

occurs first, install modification TU 167

in accordance with Turbomeca Artouste

III Service Bulletin 218 80 0093,

Revision 2, Section 2, dated January 14,

1999.

For Artouste III D Engines

(e) As of the effective date of this AD,

the duration of the operating cycle

(start-up to shutdown) is limited to two

hours total until modification TU 164 is

installed in accordance with Turbomeca

Artouste III Service Bulletin 218 80

0098, Section 2, dated January 14, 1999.

(f) At the next shop visit, within 30

days, or within 120 cycles after the

effective date of this AD, whichever

occurs first, install modification TU 164

in accordance with Turbomeca Artouste

III Service Bulletin 218 80 0098, Section

2, dated January 14, 1999.

Definition

(g) For the purpose of this AD, a shop

visit is defined as any time when the

engine is removed from the helicopter

for maintenance.

Alternative Methods of Compliance

(h) 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, Engine

Certification Office. Operators shall

submit their request through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and

then send it to the Manager, Engine

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

34604 Federal Register / Vol. 65, No. 105 / Wednesday, May 31, 2000 / Proposed Rules

if any, may be obtained from the Engine

Certification Office.

Special Flight Permits

(i) 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.

Issued in Burlington, Massachusetts,

on May 23, 2000.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–13567 Filed 5–30–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–206–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, Ø200, Ø300, Ø400,

and 747SR Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Boeing

Model 747 series airplanes, that would

have required a one-time inspection to

determine whether H–11 steel bolts are

installed as attach and support bolts at

the trailing edge flap transmissions, and

replacement of any H–11 steel bolt with

an Inconel bolt. That proposal was

prompted by reports of fracturing or

cracking of H–11 steel bolts at the flap

transmissions. This new action revises

the proposed rule by expanding the

applicability to include additional

airplanes. The actions specified by this

new proposed AD are intended to

prevent loss of a flap transmission,

which could reduce lateral

controllability of the airplane.

DATES: Comments must be received by

July 5, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

206–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Barbara Mudrovich, Aerospace

Engineer, Systems and Equipment

Branch, ANM–130S, FAA, Transport

Airplane Directorate, Seattle Aircraft

Certification Office, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056;

telephone (425) 227–2983; fax (425)

227–1181.

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 shall

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 Number 99–NM–206–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, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

99–NM–206–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Boeing Model 747 series airplanes, was

published as a notice of proposed

rulemaking (NPRM) in the Federal

Register on December 28, 1999 (64 FR

72582). That NPRM would have

required a one-time inspection to

determine whether H–11 steel bolts are

installed as attach and support bolts at

the trailing edge flap transmissions, and

replacement of any H–11 steel bolt with

an Inconel bolt. That NPRM was

prompted by reports of fracturing or

cracking of H–11 steel bolts at the flap

transmissions. That condition, if not

corrected, could result in loss of a flap

transmission, which could reduce

lateral controllability of the airplane.

Comments

Due consideration has been given to

the comments received in response to

the NPRM. Certain comments have

resulted in changes to the NPRM.

Request To Expand Applicability

One commenter, an operator, requests

that the FAA expand the applicability of

the proposed rule to include all Model

747 series airplanes. The commenter

points out that, though only Model 747

series airplanes having line numbers 1

through 871 inclusive were delivered

with the affected bolts, the affected bolts

may have been installed as spares on

Model 747 series airplanes after line

number 871. The commenter states that

it found the subject bolts installed on

airplanes in its fleet that are not

included in the applicability of the

proposed rule. The FAA concurs with

the commenter’s request and has revised

the applicability statement of this

supplemental NPRM to include all

Model 747–100, –100B, –100B SUD,

–200B, –200C, –200F, –300, –400,

–400D, –400F, and 747SR series

airplanes.

Request To Revise ‘‘Cost Impact’’

Section

Several commenters request that the

FAA revise the cost impact information

provided in the preamble of the NPRM.

One commenter states that the cost

information in the NPRM is not

consistent with the service bulletin, and

requests that the cost impact

information be revised to reflect the

estimates in the service bulletin.

Another commenter states that it does

not understand the estimate of 6 work

hours per airplane and estimates a total

of 24 work hours will be necessary to

accomplish both the inspection and