Federal Register / Vol. 65, No. 200 / Monday, October 16, 2000 / Rules and Regulations 61085

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

removing amendment 39–11914 (65 FR

57944, September 27, 2000), and by

adding a new airworthiness directive

(AD), amendment 39–11928, to read as

follows:

2000–20–03 R1 Bombardier, Inc. (Formerly

Canadair): Amendment 39–11928.

Docket 2000–NM–312–AD. Revises AD

2000–20–03, Amendment 39–11914.

Applicability: Model CL–600–2B19 series

airplanes, serial numbers 7003 through 7323

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 (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 as indicated, unless

accomplished previously.

To prevent reduced controllability of the

airplane due to an accumulation of water,

ice, and slush on the aileron quadrants and

control cable pulleys in the wheel bay of the

main landing gear (MLG); accomplish the

following:

Installation

(a) Within 45 days after October 2, 2000

(the effective date of AD 2000–20–03), install

splash shields in the wheel bay of the MLG

in accordance with Bombardier Service

Bulletin 601R–27–104, dated October 15,

1999.

Alternative Methods of Compliance

(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, New York

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The installation shall be done in

accordance with Bombardier Service Bulletin

601R–27–104, dated October 15, 1999. This

incorporation by reference was approved

previously by the Director of the Federal

Register as of October 2, 2000 (65 FR 57944,

September 27, 2000). Copies may be obtained

from Bombardier Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station Centre-ville,

Montreal, Quebec H3C 3G9, Canada. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

New York Aircraft Certification Office, 10

Fifth Street, Third Floor, Valley Stream, New

York 11581; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 3: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–28, dated August 28, 2000.

Effective Date

(e) This amendment becomes effective on

October 2, 2000.

Issued in Renton, Washington, on October

4, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26092 Filed 10–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–25–AD; Amendment

39–11931; AD 2000–20–19]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model AS–350B, BA, B1, B2,

B3, C, D, and D1, and AS–355E, F, F1,

F2 and N Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

for Eurocopter France Model AS–350B,

BA, B1, B2, C, D, and D1, and AS–355E,

F, F1, and F2 helicopters. That AD

currently requires inspections of the

main rotor head components, the main

gearbox (MGB) suspension bars, and the

ground resonance prevention system

components. This amendment requires

those same inspections, but would also

apply to Model AS–350B3 and AS–

355N helicopters. This amendment is

prompted by the inadvertent omission

of those model helicopters from the

previous AD. The actions specified by

this AD are intended to prevent ground

resonance due to reduced structural

stiffness, which could lead to failure of

a main rotor head or MGB suspension

component and subsequent loss of

control of the helicopter.

DATES: Effective November 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

May 23, 2000 (65 FR 20721, April 18,

2000).

ADDRESSES: The service information

referenced in this AD 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; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5490, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

61086 Federal Register / Vol. 65, No. 200 / Monday, October 16, 2000 / Rules and Regulations

Aviation Regulations (14 CFR part 39)

by superseding AD 86–15–10 R2,

Amendment 39–11681 (65 FR 20721),

which applies to Eurocopter France

Model AS–350B, BA, B1, B2, B3, C, D,

and D1, and AS–355E, F, F1, F2 and N

helicopters was published in the

Federal Register on July 20, 2000 (65 FR

44995). That action proposed to require

an initial inspection within 10 hours

time-in-service (TIS) and thereafter,

repetitive inspections of the main rotor

head components, the MGB suspension

bars, and the ground resonance

prevention system components at

intervals not to exceed 500 hours TIS.

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 586

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 8 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$480 per helicopter, or $281,280 for the

entire fleet.

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 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

removing Amendment 39–11681 (65 FR

20721, April 18, 2000), Amendment 39–

6515 (55 FR 5833, February 20, 1990)

and Amendment 39–5517 (52 FR 13233,

April 22, 1987) and by adding a new

airworthiness directive (AD),

Amendment 39–11931, to read as

follows:

2000–20–19 Eurocopter France:

Amendment 39–11931. Docket No. 2000-

SW–25–AD. Supersedes AD 86–15–10

R2, Amendment 39–11681, Docket No.

98–SW–82–AD; AD 86–15–10R1,

Amendment 39–6515, Docket No. 86–

ASW–22; and AD 86–15–10,

Amendment 39–5517, Docket No. 86–

ASW–22.

Applicability: Model AS–350B, BA, B1, B2,

B3, C, D, and D1, and AS–355E, F, F1, F2 and

N 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 (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 ground resonance due to

reduced structural stiffness, which could

lead to failure of a main rotor head or main

gearbox (MGB) suspension component and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Within 10 hours time-in-service (TIS):

(1) For Model AS–350B, BA, B1, B2, B3, C,

D, and D1 helicopters, inspect the main rotor

head components, the MGB suspension bars

(struts), and the landing gear ground

resonance prevention components (aft spring

blades and hydraulic shock absorbers) in

accordance with paragraph CC.3 of

Aerospatiale Service Bulletin (SB) No. 01.17a

(not dated).

(2) For Model AS–355E, F, F1, F2, and N

helicopters, inspect the main rotor head

components, the MGB suspension bars

(struts), and the landing gear ground

resonance prevention components (aft spring

blades and hydraulic shock absorbers) in

accordance with paragraph CC.3 of SB No.

01.14a (not dated).

(b) Rework or replace damaged

components in accordance with SB No.

01.17a or SB No. 01.14a, as applicable.

(c) Repeat the inspections and rework

required by paragraphs (a) and (b) of this AD

at intervals not to exceed 500 hours TIS.

(d) If the helicopter is subjected to a hard

landing or to high surface winds when

parked without effective tiedown straps

installed, repeat the inspections required by

paragraph (a) of this AD for the main rotor

head star arms and the MGB suspension bars

(struts) before further flight.

(e) After a landing with abnormal selfsustained dynamic vibrations (ground

resonance type vibrations), repeat all the

inspections required by paragraph (a) of this

AD.

(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, 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(h) The inspections shall be done in

accordance with paragraph CC.3 of

Aerospatiale Service Bulletin No. 01.17a (not

dated) or No. 01.14a (not dated), as

applicable. The rework or replacement, if

necessary, shall be done in accordance with

Aerospatiale Service Bulletin No. 01.17a or

No. 01.14a (neither is dated), as applicable.

The incorporation by reference of those

documents was previously approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51 as of

May 23, 2000 (65 FR 20721, April 18, 2000).

Copies may be obtained from American

Eurocopter Corporation, 2701 Forum Drive,

Grand Prairie, Texas 75053–4005, telephone

(972) 641–3460, fax (972) 641–3527. Copies

may be inspected at the FAA, Office of the

Regional Counsel, Southwest Region, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(i) This amendment becomes effective on

November 20, 2000.

Federal Register / Vol. 65, No. 200 / Monday, October 16, 2000 / Rules and Regulations 61087

Issued in Fort Worth, Texas, on September

29, 2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–26234 Filed 10–13–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ACE–22]

Amendment to Class E Airspace;

Elkhart, KS

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This document confirms the

effective date of a direct final rule which

revises Class E airspace at Elkhart, KS.

DATES: The direct final rule published at

65 FR 45707 is effective on 0901 UTC,

November 30, 2000.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Division,

Airspace Branch, ACE–520C, DOT

Regional Headquarters Building, Federal

Aviation Administration, 901 Locust,

Kansas City, MO 64106; telephone:

(816) 329–2525.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on July 25, 2000 (65 FR 45707).

The FAA uses the direct final

rulemaking procedure for a noncontroversial rule where the FAA

believes that there will be no adverse

public comment. This direct final rule

advised the public that no adverse

comments were anticipated, and that

unless a written adverse comment, or a

written notice of intent to submit such

an adverse comment, were received

within the comment period, the

regulation would become effective on

November 30, 2000. No adverse

comments were received, and thus this

document confirms that this direct final

rule will become effective on that date.

Issued in Kansas City, MO on September

28, 2000.

Herman J. Lyons, Jr.,

Manager, Air Traffic Division, Central Region.

[FR Doc. 00–26525 Filed 10–13–00; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ACE–21]

Amendment to Class E Airspace;

Columbia, MO

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This document confirms the

effective date of a direct final rule which

revises Class E airspace at Columbia,

MO.

DATES: The direct final rule published at

65 FR 43686 is effective on 0901 UTC,

November 30, 2000.

FOR FURTHER INFORMATION CONTACT:

Brenda Mumper, Air Traffic Division,

Airspace Branch, ACE–520A, DOT

Regional Headquarters Building, Federal

Aviation Administration, 901 Locust,

Kansas City, MO 64106; telephone:

(816) 329–2524.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on July 14, 2000 (65 FR 43686).

The FAA uses the direct final

rulemaking procedure for a noncontroversial rule where the FAA

believes that there will be no adverse

public comment. This direct final rule

advised the public that no adverse

comments were anticipated, and that

unless a written adverse comment, or a

written notice of intent to submit such

an adverse comment, were received

within the comment period, the

regulation would become effective on

November 30, 2000. No adverse

comments were received, and thus this

document confirms that this direct final

rule will become effective on that date.

Issued in Kansas City, MO on September

28, 2000.

Herman J. Lyons, Jr.,

Manager, Air Traffic Division, Central Region.

[FR Doc. 00–26526 Filed 10–13–00; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ASW–6]

Amendment of Federal Airways in the

Vicinity of Dallas/Fort Worth; TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action amends thirteen

Federal airways in the vicinity of

Dallas/Fort Worth, TX. In the NPRM for

this action, the FAA proposed to modify

14 airways. However, after considering

aircraft routing through the Shreveport,

LA, Approach Control terminal airspace

and retention of transition fixes for the

Shreveport Regional Airport and

Barksdale Air Force Base (AFB), the

FAA has decided not to make the

proposed modification of

V–566. The FAA is taking this action to

simplify the airway structure, thereby,

enhancing the management of aircraft

operations in the area.

EFFECTIVE DATE: 0901 UTC, November

30, 2000.

FOR FURTHER INFORMATION CONTACT: Bil

Nelson, Airspace and Rules Division,

ATA–400, Office of Air Traffic Airspace

Management, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone: (202) 267–8783.

SUPPLEMENTARY INFORMATION:

Background

As a result of a recent airspace review,

the FAA has determined that airways in

the vicinity of Dallas/Fort Worth, TX,

should be amended to improve

management of the aircraft operations.

On June 12, 2000, the FAA published in

the Federal Register (65 FR 36805) a

proposal to amend fourteen Federal

airways. However, after considering

aircraft routing through the Shreveport,

LA, Approach Control terminal airspace

and retention of transition fixes for the

Shreveport Regional Airport and

Barksdale AFB, the FAA decided not to

make the proposed modification of V–

566.

Interested parties were invited to

participate in this proposed rulemaking

by submitting such written data, views,

or arguments as they may desire. No

comments were received. Except for

editorial changes, and the decision not

to amend V–566, this amendment is the

same as that proposed in the NPRM.