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

63535

Vol. 65, No. 206

Tuesday, October 24, 2000

FEDERAL ELECTION COMMISSION

11 CFR Parts 100, 101, 102, 104, 109,

114, 9003, 9033

[Notice 2000–18]

Electronic Filing of Reports by Political

Committees

AGENCY: Federal Election Commission.

ACTION: Final rule; announcement of

effective date.

SUMMARY: On June 21, 2000, the

Commission published the text of

regulations making electronic filing

mandatory for certain political

committees and other persons. The

Commission announces that these rules

are effective as of January 1, 2001.

DATES: Effective January 1, 2001.

Applicability date: Reporting periods

beginning on or after January 1, 2001.

FOR FURTHER INFORMATION CONTACT: Ms.

Rosemary C. Smith, Assistant General

Counsel, or Ms. Cheryl A. Fowle,

Attorney, 999 E Street, NW.,

Washington, DC 20463, (202) 694–1650

or toll free (800) 424–9530.

SUPPLEMENTARY INFORMATION: The

Commission is announcing the effective

date of revisions to the regulations at 11

CFR 100.19, 101.1, 102.2, 104.5, 104.18,

109.2, 114.10, 9003.1 and 9033.1

making electronic filing mandatory for

certain political committees and other

persons. See Explanation and

Justification for Electronic Filing of

Reports by Political Committees, 65 FR

38415 (June 21, 2000). These rules

implement a 1999 amendment to the

Federal Election Campaign Act at 2

U.S.C. 434(a)(11) that requires the

Commission to make electronic filing

mandatory for political comittees and

other persons required to file with the

Commision who, in a calendar year,

have, or have reason to expect to have,

total contributions or total expenditures

exceeding a threshold amount to be set

by the Commission. Pub. L. No. 106–58,

106th Cong., section 639, 113 Stat. 430,

476–477 (1999). The new regulations set

that threshold amount at $50,000.

The statutory amendment specifically

covers reports and statements filed with

the Commission, i.e., all except those

filed by Senate candidates, their

authorized committees, and committees

that support or oppose them, which are

filed with the Secretary of the Senate.

Section 438(d) of Title 2, United

States Code and sections 9009(c) and

9039(c) of Title 26, United States Code,

require that any rules or regulations

prescribed by the Commission to carry

out the provisions of Titles 2 and 26 of

the United States Code be transmitted to

the Speaker of the House of

Representatives and the President of the

Senate thirty legislative days prior to

final promulgation. These rules were

transmitted to Congress on June 16,

2000. For the Title 2 rules, thirty

legislative days expired in the Senate on

September 12, 2000, and the House of

Representatives on September 20, 2000.

For the Title 26 regulations, thirty

legislative days expired in both Houses

on September 20, 2000.

Dated: October 19, 2000.

Darryl R. Wold,

Chairman, Federal Election Commission.

[FR Doc. 00–27233 Filed 10–23–00; 8:45 am]

BILLING CODE 6715–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–40–AD; Amendment

39–11942; AD 2000–21–10]

RIN 2120–AA64

Airworthiness Directives; CFE

Company CFE738–1–1B Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to CFE Company CFE738–1–

1B turbofan engines. This action

requires removing certain support

assemblies and replacing them with

support assemblies that have a new

design. This amendment is prompted by

a report of the loss of seal retention that

resulted in contact between the seal face

and the stage 2 high pressure turbine

(HPT) rotor disk, and subsequent wear

of the stage 2 HPT rotor disk. That

condition resulted in separation of the

stage 2 HPT wheel rim, and an

uncontained failure of the stage 2 HPT

rotor wheel. The actions specified in

this AD are intended to prevent the

static seal from moving forward, which

could result in contact between the seal

face and stage 2 HPT rotor, wear, and

the possibility of an uncontained failure

of the stage 2 HPT rotor.

DATES: Effective November 8, 2000. The

incorporation by reference of certain

publications listed in the rule is

approved by the Director of the Federal

Register as of November 8, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

December 26, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2000–NE–

40–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

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

via the Internet must contain the docket

number in the subject line.

The service information referenced in

this AD may be obtained from CFE

Company, Data Distribution, MS 64–03/

2101–201, P.O. Box 52170, Phoenix, AZ

85972–2170; telephone (602) 365–2493,

fax (602) 365–5577. This information

may be examined at the FAA, New

England Region, Office of the Regional

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Keith Mead, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7744,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: On June

27, 2000, the FAA was notified of an

uncontained engine failure of a

CFE738–1–1B turbofan engine. A

subsequent investigation determined

that the rivets that retain the seal to the

63536 Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations

No. 4 bearing support, part of the

support assembly, wore and allowed the

seal to migrate forward and contact the

stage 2 HPT rotor disk. That contact

caused a deep wear groove in the disk

web, and subsequent separation of

portions of the disk rim from the stage

2 HPT disk, resulting in an uncontained

failure of the engine. This condition, if

not corrected, could result in wear

damage to the stage 2 HPT rotor disk

that could result in fracture and a

possible uncontained failure of the disk.

Manufacturer’s Service Information

The FAA has reviewed and approved

the technical contents of the following

CFE Company service information:

• Alert Service Bulletin (ASB)

CFE738–A72–8042, Revision 1, dated

September 25, 2000. That ASB describes

procedures for replacing the support

assembly with a new design support

assembly, which has improved static

seal retention.

• SB CFE738–72–8043, dated October

2, 2000, that provides procedures for the

break-in of the engine support assembly

seal.

The FAA has also reviewed and

approved the technical contents of ASB

CFE738–A72–8041, dated August 21,

2000, that describes procedures for

borescope inspection of:

• The stage 2 HPT rotor disk for

contact rubs.

• The rivets that attach the static seal

to the bearing frame support to ensure

there are no anomalies.

• The bearing frame support and

static seal to determine if there is a gap

between them.

• The static seal to determine if there

is any distortion or waviness.

Requirements of This AD

Since an unsafe condition has been

identified that is likely to exist or

develop on other CFE Company

CFE738–1–1B turbofan engines of the

same type design, this AD is being

issued to require replacing existing

support assemblies, part numbers (P/

N’s) 3050860–2, –3, and –5 through –9

inclusive, with new support assemblies,

P/N 3050860–10, –11, P/N 3057005–1

through –5 inclusive, or P/N 3057006–

1, –2. The replacement of the support

assembly must be done in accordance

with ASB CFE738–A72–8042, Revision

1, dated September 25, 2000. Break-in of

the support assembly seal must be done

in accordance with SB CFE738–72–

8043, Revision 1, dated October 2, 2000.

For engines that have not been

borescope inspected using ASB

CFE738–A72–8041, dated August 21,

2000, the support assembly must be

replaced or borescope inspected within

the specified replacement interval for

that group. The borescope inspection

must be done in accordance with ASB

CFE738–A72–8041, dated August 21,

2000.

Immediate Adoption of This AD

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 AD

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–40–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This proposed rule does not have

federalism implications, as defined in

Executive Order No. 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 proposed rule.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–21–10 CFE Company: Amendment 39–

11942. Docket 2000–NE–40–AD.

Applicability: This AD is applicable to CFE

Company CFE738–1–1B turbofan engines

with support assembly, part numbers (P/N’s)

3050860–2, –3, and –5 through –9 inclusive,

installed. These engines are installed on, but

not limited to, Dassault Aviation Falcon 2000

series airplanes.

Note 1: This airworthiness directive (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 (d)

Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations 63537

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: Compliance with this AD is

required as indicated, unless already done.

To prevent the static seal from moving

forward, which could result in contact

between the seal face and stage 2 HPT rotor,

wear, and the possibility of an uncontained

failure of the stage 2 HPT rotor, do the

following:

(a) Remove support assembly, P/N

3050860–2, –3, –5 through –9, and replace it

with a serviceable seal assembly in

accordance with the Accomplishment

instructions 2.A.(3) through 2.A.(8)(d) and

2.B.(1) through 2.B.(3) of ASB CFE738 A72–

8042, Revision 1, dated September 25, 2000,

as follows:

Engines That Have Already Been Inspected

(1) For engines that have been inspected

using CFE Company alert service bulletin

(ASB) ASB CFE738 A72–8041, dated August

21, 2000, replace the support assembly as

follows:

Operating hours time-since new (TSN) on the effective

date of this AD Replace by the earlier of—

Fewer than 500 hours TSN ............................................... 150 hours time-in-service (TIS) or 90 days after the effective date of this AD.

500 hours to 1,000 hours TSN .......................................... 250 hours TIS or 150 days after the effective date of this AD.

More than 1,000 hours TSN .............................................. 400 hours TIS or 240 days after the effective date of this AD.

Engines That Have Not Been Inspected

(2) For engines that have not been

inspected using CFE Company alert service

bulletin (ASB) ASB CFE738 A72–8041, dated

August 21, 2000, do EITHER of the following

within the earlier of 50 hours TIS or 30 days

after the effective date of this AD:

(i) Replace the support assembly with a

serviceable support assembly in accordance

with the Accomplishment instructions

2.A.(3) through 2.A.(8)(d) and 2.B.(1) through

2.B.(3) of ASB CFE738 A72–8042, and 2.A.

or 2.B. of SB CFE738–72–8043, Revision 1,

dated October 2, 2000;

(ii) Inspect the engine in accordance with

the Accomplishment Instructions 2.A.

through 2.B.(6) of ASB CFE738–A72–8041,

dated August 21, 2000, and then replace the

support assembly in accordance with the

replacement schedule in paragraph (a)(1) of

this AD.

Support Assembly Seal Break-In

(b) After the seal has been replaced, do the

support assembly seal break-in procedure in

accordance 2.A. (test cell) or 2.B. (on wing)

of SB CFE738–72–8043, Revision 1, dated

October 2, 2000.

Definition of a Serviceable Part

(c) For the purposes of this AD, a

serviceable support assembly is defined as a

support assembly with P/N 3050860–10, or

–11, P/N 3057005–1 through –5 inclusive, or

P/N 3057006–1, or –2.

Alternative Methods of Compliance

(d) 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 (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(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.

Documents That Have Been Incorporated by

Reference

(f) The actions specified in this AD must

be done in accordance with the following

CFE Company service bulletins:

Document No. Pages Revision Date

ASB CFE738–A72–8041 ...................................................................... All ............................... Original ....................... August 21, 2000.

Total pages: 26.

ASB CFE738–A72–8042 ...................................................................... All ............................... 1 ................................. September 25, 2000.

Total pages: 22.

SB CFE738–72–8043 ........................................................................... All ............................... 1 ................................. October 2, 2000.

Total pages: 28.

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 CFE Company, Data Distribution, MS

64–03/2101–201, P.O. Box 52170, Phoenix,

AZ 85972–2170; telephone (602) 365–2493,

fax (602) 365–5577. Copies may be inspected

at the FAA, New England Region, Office of

the Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700, Washington,

DC.

Effective Date of This AD

(g) This amendment becomes effective on

November 8, 2000.

Issued in Burlington, Massachusetts, on

October 16, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–26972 Filed 10–23–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–48–AD; Amendment

39–11940; AD 2000–21–08]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Pratt & Whitney

JT8D series turbofan engines, that