6046 Federal Register / Vol. 65, No. 26 / Tuesday, February 8, 2000 / Proposed Rules

Therefore, elimination of the flange

temperature requirement has no impact on

BWR flange integrity.’’

The Petitioner’s Conclusions

The petitioner has concluded that the

NRC requirements governing pressure

and temperature limits for the reactor

pressure vessel should be amended to

eliminate reactor vessel closure head

flange requirements. The petitioner has

also concluded that the elimination of

the flange requirement has no impact on

BWRs and could improve plant safety in

PWRs. The petitioner requests that the

reactor vessel closure head flange

requirement be eliminated from the

regulations at 10 CFR part 50, appendix

G, Table 1 as presented in its petition

for rulemaking.

Dated at Rockville, Maryland, this 1st day

of February, 2000.

For the Nuclear Regulatory Commission.

Annette Vietti-Cook,

Secretary of the Commission.

[FR Doc. 00–2833 Filed 2–7–00; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–358–AD]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

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

certain Fokker Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes.

This proposal would require a one-time

review of the maintenance records to

determine if tripping of the fuel boost

pump circuit breakers has been

recorded, repetitive inspections to

detect fuel leakage from the fuel boost

pump wiring conduits, and corrective

actions, if necessary. This proposal also

would require replacement of the three

single wires inside the metal conduit

sleeve of the fuel boost pumps with new

wires protected by a polyamide sleeve,

which would terminate the repetitive

inspections. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent the fuel boost

pump wiring from chafing, which could

result in electrical arcing and a possible

fuel tank ignition source.

DATES: Comments must be received by

March 9, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

358–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

Fokker Services B.V., P.O. Box 231,

2150 AE Nieuw-Vennep, the

Netherlands. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

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:

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–358–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–358–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Rijksluchtvaartdienst (RLD),

which is the airworthiness authority for

the Netherlands, notified the FAA that

an unsafe condition may exist on certain

Fokker Model F.28 Mark 1000, 2000,

3000, and 4000 series airplanes. On July

17, 1996, a Boeing Model 747 series

airplane was involved in an accident

shortly after takeoff from John F.

Kennedy International Airport in

Jamaica, New York. Subsequent to the

accident, the RLD advises that the

manufacturer has conducted a Fuel

System Safety Program (FSSP)

investigation. This investigation

revealed that, on an F.28 ‘‘Fellowship’’

series airplane, the wiring insulation

layers of the fuel boost pumps can be

damaged during removal and

installation of the wiring, or by chafing

within the conduits. Additionally, two

separate incidents of arcing have been

found in the metal conduits of the

wiring of the fuel boost pumps.

Circumferential cracks were found in

the insulation layering of the fuel boost

pump wiring. In some cases, the cracks

extended down to the conductor of the

wiring. This condition, if not corrected,

could result in electrical arcing and a

possible fuel tank ignition source.

Explanation of Relevant Service

Information

The manufacturer has issued Fokker

Service Bulletin SBF28/28–046, dated

September 1, 1999, which describes

procedures for the following:

• Part 1 of the Accomplishment

Instructions: A one-time review of the

maintenance records to determine if

tripping of the fuel boost pump circuit

breakers has been reported, and

repetitive visual inspections to detect

fuel leakage of the fuel boost pumps.

• Part 2, paragraph D., of the

Accomplishment Instructions:

Corrective actions for tripping of the

fuel boost pump circuit breakers. These

actions involve performing a resistance

check of the wiring, and, if necessary,

installing a new or serviceable fuel

boost pump and correcting any system

problems between the circuit breaker

and the main landing gear (MLG) wheel

bay connector, and repairing any fuel

Federal Register / Vol. 65, No. 26 / Tuesday, February 8, 2000 / Proposed Rules 6047

leak in the metal conduit of the fuel

boost pump. The corrective actions also

involve performing one-time

inspections (visual and boroscopic) to

detect discrepancies (i.e., arcing,

chafing, and cracking) of the insulation

layers of the wiring and wiring

conduits, and replacing the wiring and

repairing the wiring conduits.

• Part 2, paragraph E., of the

Accomplishment Instructions:

Corrective actions in the event that fuel

leakage is detected from the fuel boost

pump wiring conduits. The corrective

actions involve inspecting the pressure

bung for serviceability, and, if

necessary, installing a new or

serviceable pressure bung. Additionally,

the corrective actions involve inspecting

(visual and boroscopic) to detect

discrepancies (i.e., arcing, chafing, and

cracking) of the insulation layers of the

wiring and wiring conduits, and

replacing the wiring and repairing the

wiring conduits.

• Part 3 of the Accomplishment

Instructions: Replacement of the three

single wires inside the metal conduit

sleeve of the fuel boost pump with new

wires protected by a polyamide sleeve.

The replacement also involves

performing a visual inspection, and, if

necessary, a boroscopic inspection of

the boost pump wiring to detect

discrepancies (i.e., arcing, chafing, and

cracking) of the insulation layers of the

wiring and wiring conduits, and

replacing the wiring and repairing the

wiring conduits. Accomplishment of the

replacement eliminates the need for the

repetitive inspections.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The RLD

classified this service bulletin as

mandatory and issued Dutch

airworthiness directive BLA 1999–114,

dated September 13, 1999, in order to

assure the continued airworthiness of

these airplanes in the Netherlands.

FAA’s Conclusions

This airplane model is manufactured

in the Netherlands 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 RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

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.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 22 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per airplane

to accomplish the proposed review of

the maintenance records, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the review proposed by this AD on

U.S. operators is estimated to be $1,320,

or $60 per airplane.

It would take approximately 3 work

hours per airplane to accomplish the

proposed repetitive inspection, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the proposed inspection by this AD

on U.S. operators is estimated to be

$3,960, or $180 per airplane, per

inspection cycle.

It would take approximately 33 work

hours per airplane to accomplish the

proposed modification, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $1,355 per airplane.

Based on these figures, the cost impact

of the proposed modification by this AD

on U.S. operators is estimated to be

$73,370, or $3,335 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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:

Fokker Services B.V: Docket 99–NM–358–

AD.

Applicability: Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes having

serial numbers 11003 through 11241

inclusive and 11991 through 11994 inclusive,

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, unless

accomplished previously.

To prevent the fuel boost pump wiring

from chafing, which could result in electrical

arcing and a possible fuel tank ignition

source, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform a one-time inspection of

the maintenance records of the airplane to

determine if tripping of the fuel boost pump

6048 Federal Register / Vol. 65, No. 26 / Tuesday, February 8, 2000 / Proposed Rules

circuit breakers has been reported within the

last 30 days, in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF28/28–046, dated

September 1, 1999.

(b) If resettable or unresettable tripping of

the circuit breaker of the fuel boost pump is

reported during the inspection required by

paragraph (a) of this AD, or if such tripping

is reported at any time subsequent to that

inspection: Within 10 days after the date of

the inspection or any occurrence, accomplish

the applicable repair (including a resistance

check and inspections of the wire and

conduit for discrepancies), in accordance

with Part 2 of the Accomplishment

Instructions of Fokker Service Bulletin

SBF28/28–046, dated September 1, 1999. If

any discrepancy is detected during any

inspection performed during the repair, prior

to further flight, repair in accordance with

the service bulletin.

(c) In the event of any resettable or

unresettable tripping of the circuit breakers

of the fuel boost pump as indicated in

paragraph (b) of this AD, the airplane may be

operated for a period not to exceed 10 days

after the occurrence, provided the circuit

breaker of the fuel boost pump and fuel boost

pump switch have been properly deactivated

and placarded for flightcrew awareness, in

accordance with the FAA-approved Master

Minimum Equipment List (MMEL).

(d) Within 30 days after the effective date

of this AD, perform a general visual

inspection to detect signs of fuel leakage from

the wiring conduits of the fuel boost pumps,

in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F28/28–046, dated

September 1, 1999. If any fuel leakage is

detected during the inspection, prior to

further flight, isolate the fuel leak, and repair

in accordance with Part 2 of the

Accomplishment Instructions of the service

bulletin. Thereafter, repeat the inspection at

intervals not to exceed 90 days.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

(e) Replace the existing three single wires

(including inspections) inside the metal

conduits of the fuel boost pumps with three

twisted wires protected by a polyamide

braided wire sleeve, in accordance with Part

3 of the Accomplishment Instructions of

Fokker Service Bulletin F28/28–046, dated

September 1, 1999, at the time specified in

paragraph (e)(1) or (e)(2) of this AD, as

applicable. If any discrepancy is detected

during any inspection required by this

paragraph, prior to further flight, repair in

accordance with the service bulletin.

Accomplishment of the actions required by

this paragraph constitutes terminating action

for the actions required by this AD.

(1) For airplanes that have accumulated

less than 40,000 total flight hours as of the

effective date of this AD: Within 2 years after

the effective date of this AD.

(2) For airplanes that have accumulated

40,000 or more total flight hours as of the

effective date of this AD: Within 1 year after

the effective date of this AD.

Alternative Methods of Compliance

(f) 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, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(g) 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.

Note 4: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1999–

114, dated September 13, 1999.

Issued in Renton, Washington, on February

2, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–2830 Filed 2–7–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF ENERGY

Federal Energy Regulatory

Commission

18 CFR Parts 270, 375 and 381

[Docket No. RM00–6–000]

Well Category Determinations

January 27, 2000.

AGENCY: Federal Energy Regulatory

Commission.

ACTION: Notice of proposed rulemaking.

SUMMARY: The Federal Energy

Regulatory Commission (Commission)

proposes to amend its regulations to

reinstate certain regulations involving

well category determinations for

Internal Revenue Code Section 29 tax

credits, but limited to certain well

recompletions commenced after January

1,1993. These regulations were deleted

by the Commission in Order No. 567.

DATES: Comments on the proposed

rulemaking are due on or before April

10, 2000.

ADDRESSES: File comments on the notice

of proposed rulemaking with the Office

of the Secretary, Federal Energy

Regulatory Commission, 888 First

Street, NE, Washington, DC 20426.

Comments should reference Docket No.

RM00–6–000.

FOR FURTHER INFORMATION CONTACT:

Marilyn Rand (Technical Information),

Office of Pipeline Regulation, 888

First Street, NE, Washington, DC

20426, (202) 208–0444

Jacob Silverman (Advisory Attorney),

Office of the General Counsel, 888

First Street, NE, Washington, DC

20426, (202) 208–2078

SUPPLEMENTARY INFORMATION: In

addition to publishing the full text of

this document in the Federal Register,

the Commission provides all interested

persons an opportunity to view and/or

print the contents of this document via

the Internet through FERC’s Home Page

(http://www.ferc.fed.us) and in FERC’s

Public Reference Room during normal

business hours (8:30 a.m. to 5:00 p.m.

Eastern time) at 888 First Street, NE,

Room 2A, Washington, DC 20426.

From FERC’s Home Page on the

Internet, this information is available in

both the Commission Issuance Posting

System (CIPS) and the Records and

Information Management System

(RIMS).

—CIPS provides access to the texts of

formal documents issued by the

Commission since November 14,

1994.

—CIPS can be access using the CIPS

link or the Energy Information Online

icon. The full text of this document

will be available on CIPS in ASCII

and WordPerfect 8.0 format for

viewing, printing, and/or

downloading.

—RIMS contains images of documents

submitted to and issued by the

Commission after November 16, 1981.

Documents from November 1995 to

the present can be viewed and printed

from FERC’s Home Page using the

RIMS link or the Energy Information

Online icon. Descriptions of

documents back to November 16,

1981, are also available from RIMSon-the-Web; requests for copies of

these and other older documents

should be submitted to the Public

Reference Room.

User assistance is available for RIMS,

CIPS, and the Website during normal

business hours from our Help line at

(202) 208–2222 (E-Mail to

WebMaster@ferc.fed.us) or the Public