20894 Federal Register / Vol. 65, No. 76 / Wednesday, April 19, 2000 / Rules and Regulations

transmitted to Congress on November 9,

1999. Thirty legislative days expired in

the Senate and the House of

Representatives on April 3, 2000.

Announcement of Effective Date: New

11 CFR 9035.3 and amended 11 CFR

9007.1, 9034.4 and 9038.1, as published

at 64 FR 61777 (Nov. 15, 1999), are

effective as of April 19, 2000.

Dated: April 13, 2000.

Darryl R. Wold,

Chairman, Federal Election Commission.

[FR Doc. 00–9732 Filed 4–18–00; 8:45 am]

BILLING CODE 6715–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–14–AD; Amendment

39–11692; AD 2000–08–06]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA–366G1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

SA–366G1 helicopters, that requires

replacing certain electrical modules

with airworthy electrical modules. This

amendment is prompted by the

discovery of several defective electrical

modules. The actions specified by this

AD are intended to prevent loss of

electrical continuity, which could cause

loss of critical systems and subsequent

loss of control of the helicopter.

EFFECTIVE DATE: May 24, 2000.

FOR FURTHER INFORMATION CONTACT:

Robert McCallister, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, Fort Worth, Texas

76193–0110, telephone (817) 222–5121,

fax (817) 222–5961.

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 Eurocopter France

Model SA–366G1 helicopters was

published in the Federal Register on

January 10, 2000 (65 FR 1353). That

action proposed to require replacing

certain electrical modules with

airworthy electrical modules.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 94 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 100

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$2,969 for the maximum number of

modules replaced per helicopter, but the

manufacturer has stated that the parts

will be provided at no cost. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$564,000.

The regulations adopted herein will

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 final rule does not

have federalism implications under

Executive Order 13132.

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 Office of the Regional

Counsel, Southwest Region, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, 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 a new airworthiness directive to

read as follows:

AD 2000–08–06 Eurocopter France:

Amendment 39–11692. Docket No. 99–

SW–14–AD.

Applicability: Model 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

otherwise 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 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 within 400 hours

time-in-service or within 6 calendar months,

whichever occurs first, unless accomplished

previously.

To prevent loss of electrical continuity,

which could cause loss of required systems

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Replace each ‘‘CONNECTRAL’’ green

electrical module that does not have a white

dot on the face and that has a manufacturing

code of 95/16 through 96/21 with an

airworthy electrical module. Those

manufacturing codes identify modules

manufactured between the beginning of the

16th week of 1995 and the end of the 21st

week of 1996.

Note 2: Eurocopter France Service Bulletin

No. 01.25, dated May 28, 1998, pertains to

the subject of this AD.

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(d) This amendment becomes effective on

May 24, 2000.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

AD 98–251–022(A), dated July 1, 1998.

Federal Register / Vol. 65, No. 76 / Wednesday, April 19, 2000 / Rules and Regulations 20895

Issued in Fort Worth, Texas, on April 11,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–9820 Filed 3–18–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–70–AD; Amendment

39–11690; AD 2000–08–04]

RIN 2120–AA64

Airworthiness Directives; Robinson

Helicopter Company Model R44

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Robinson Helicopter

Company (RHC) Model R44 helicopters.

This action requires replacing certain

serial number (S/N) sprag clutches with

an airworthy sprag clutch as specified in

this AD. This amendment is prompted

by several reports of sprag clutch

failures. The actions specified by this

AD are intended to prevent a sprag

clutch failure, loss of main rotor RPM

during autorotation, and subsequent

loss of control of the helicopter.

DATES: Effective May 4, 2000. Comments

for inclusion in the Rules Docket must

be received on or before June 19, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 99–SW–70–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT:

Elizabeth Bumann, Aviation Safety

Engineer, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Blvd., Lakewood, California 90712–

4137, telephone (562) 627–5265; fax

(562) 627–5210.

SUPPLEMENTARY INFORMATION: On April

5, 1999, the FAA issued AD 99–07–18,

Amendment 39–11127 (64 FR 17964,

April 13, 1999), to require inserting a

Special Pilot Caution into the Rotorcraft

Flight Manual (RFM) to alert pilots of

the potential for the sprag clutch failing

to overrun during autorotation

maneuvers. The Special Pilot Caution

was an interim measure until permanent

corrective action was developed by the

manufacturer. The FAA now believes

that the affected sprag clutches need to

be replaced within 30 days or 50 hours

time-in-service (TIS), whichever occurs

first. Since the sprag clutch is such a

critical component of the rotor drive

system, this AD requires replacing sprag

clutch part number (P/N) C188–3, S/N

0003 through 0505, inclusive, with

sprag clutch, P/N C188–3, S/N 0506 and

higher. This amendment is prompted by

several reports of clutch assemblies,

including one from wreckage of an

accident, with cracked or fractured

sprag ends. The actions specified by this

AD are intended to prevent a sprag

clutch failure, loss of main rotor RPM

during autorotation, and subsequent

loss of control of the helicopter.

The FAA has reviewed RHC Service

Bulletin SB–36, dated November 5,

1999, which describes replacing the

sprag clutch, P/N C188–3, S/N 0453

through 0505, inclusive, with sprag

clutch, P/N C188–3, S/N 0506 and

subsequent. RHC Service Bulletin SB–

32, dated March 22, 1999, affected this

same P/N, S/N 0003 through 0452.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Robinson R44

helicopters of the same type design, this

AD is being issued to prevent a sprag

clutch failure, loss of main rotor RPM

during autorotation, and subsequent

loss of control of the helicopter. The

short compliance time involved is

required because the previously

described critical unsafe condition can

adversely affect the controllability of the

helicopter after an actual engine failure.

Therefore, replacing sprag clutch, P/N

C188–3, S/N 0003 through 0505,

inclusive, with sprag clutch, P/N C188–

3, S/N 0506 and higher, is required

within 30 calendar days or 50 hours

time-in-service after the effective date of

this AD, whichever occurs first, and this

AD must be issued immediately.

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.

The FAA estimates that 200

helicopters will be affected by this

proposed AD, that it will take

approximately 4 work hours to replace

a sprag clutch, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$3,600 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$768,000.

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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 99–SW–70–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft

and that it 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