Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75607

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

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:

2000–24–01 Bombardier, Inc. (Formerly

Canadair): Amendment 39–12008.

Docket 2000–NM–368–AD.

Applicability: The following airplanes,

certificated in any category:

Model Serial Nos.

CL–600–1A11 (CL–

600).

1004 though 1085 inclusive.

CL–600–2A12 (CL–

601).

3001 through 3066

inclusive.

CL–600–2B16 (CL–

601–3A and CL–

601–3R).

5001 through 5194

inclusive.

CL–600–2B16 (CL–

604).

5301 through 5392

inclusive.

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 water, ice, or slush

accumulation on the aileron quadrants and/

or control cable pulleys in the wheel bay of

the main landing gear (MLG) during ground

roll, which could subsequently freeze during

the climb to cruise altitude and cause

stiffness in the aileron controls and reduced

controllability of the airplane, accomplish

the following:

Installation of Protection Shields

(a) Within 45 days after the effective date

of this AD, install protection shields in the

wheel bay of the MLG, per the following

applicable Bombardier service bulletin:

Model Bombardier service bulletin Service bulletin date

CL–600–1A11 (CL–600) ............................................................. 600–0684 ................................ July 15, 1998

CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and

CL–601–3R).

601–0507 ................................ June 30, 1998

CL–600–2B16 (CL–604) ............................................................. 604–32–007 ............................ June 30, 1998

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 actions shall be done in accordance

with the following service bulletins, as

applicable:

Bombardier service bulletin Service

bulletin date

600–0684 .............................. July 15, 1998.

Bombardier service bulletin Service

bulletin date

601–0507 .............................. June 30,

1998.

604–32–007 .......................... June 30,

1998.

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 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; 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–

2000–30, dated September 12, 2000.

Effective Date

(e) This amendment becomes effective on

December 19, 2000.

Issued in Renton, Washington, on

November 17, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30020 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–42–AD; Amendment

39–11965; AD 2000–22–18]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Beech Model 58

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Beech Model 58

75608 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

airplanes. This AD requires you to

inspect the rudder bellcrank

interconnect tube for damage; replace or

refinish the interconnect tube, if

necessary; and modify the floorboard.

Four reports of damage to the

interconnect tube prompted this action.

The actions specified by this AD are

intended to correct the wrong use of

screws and consequent wear in the

pilot/copilot pedal interconnect tube,

which could result in loss of rudder

control.

DATES: This AD becomes effective on

December 29, 2000.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of December 29, 2000.

ADDRESSES: You may get the service

information referenced in this AD from

Raytheon Aircraft Company, P.O. Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 429–5372 or (316) 676–

3140; on the Internet at <http://

www.raytheon.com/rac/servinfo/27–

3013.pdf>. This file is in Adobe Portable

Document Format. The Acrobat Reader

is available at http://www.adobe.com/.

You may examine this information at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–CE–42–AD, 901

Locust, Room 506, Kansas City,

Missouri 64106; or at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul

C. DeVore, Aerospace Engineer, FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone: (316) 946–4142; facsimile:

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The FAA has received four reports of

grooves cut in the pilot/copilot rudder

interconnect tube. The grooves were

discovered during routine inspections.

What are the consequences if the

condition is not corrected? This

condition could result in jamming or

restricting rudder control.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to certain

Raytheon Beech Model 58 airplanes.

This proposal was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on September 7,

2000 (65 FR 54184). The NPRM

proposed to require you to inspect the

rudder bellcrank interconnect tube for

damage; if necessary, replace or refinish

the rudder bellcrank interconnect tube;

and plug the floorboard screw hole.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

The FAA’s Determination

What is FAA’s Final Determination on

this Issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. We determined

that these minor corrections:

—will not change the meaning of the

AD; and

—will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How many airplanes does this AD

impact? We estimate that this AD affects

491 airplanes in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

airplanes? We estimate the following

costs to accomplish the modification of

the floorboard and inspection of the

rudder bellcrank interconnect tube:

Labor cost Parts cost Total cost per airplane Total cost on U.S.

airplane operators

4 workhours × $60 per hour =

$240.

Parts are provided at no charge

under warranty.

$240 per airplane ......................... $240 × 491 = $117,840.

We estimate the following costs to accomplish the modification or replacement of the bellcrank interconnect tube:

Labor cost Parts cost Total cost per airplane Total cost on U.S.

airplane operators

1 workhour × $60 per hour = $60 Parts are provided at no charge

under warranty.

$60 per airplane ........................... $60 × 491 = $29,460.

Note: The manufacturer will allow

warranty credit for labor and parts to the

extent noted in the service bulletin.

Regulatory Impact

Does this AD impact various entities?

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.

Does this AD involve a significant rule

or regulatory action? 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 copy of the final

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, Incorporation by Reference,

Safety.

Adoption of the Amendment

Accordingly, under 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:

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75609

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. FAA amends § 39.13 by adding a

new AD to read as follows:

2000–22–18 Raytheon Aircraft Company:

Amendment 39–11965; Docket No.

2000–CE–42–AD.

(a) What airplanes are affected by this AD?

This AD affects Beech Model 58 airplanes;

serial numbers TH–1389, and TH–1396

through TH–1885, that are certificated in any

category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to correct the wrong use of screws and

consequent wear in the pilot/copilot pedal

interconnect tube, which could result in loss

of rudder control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must do the following actions:

Actions Compliance times Procedures

(1) Inspect the rudder bellcrank interconnect tube

for damage and ensure the floorboard panel

screws are 3⁄4 inch or less in length. Screws that

are longer than 3⁄4 inch in length can damage

parts installed immediately below the floorboards.

Inspect within the next 6 calendar

months after December 29, 2000

(the effective date of this AD).

Do this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph

of Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron Model

58 Shop Manual.

(2) If you find no damage to the rudder bellcrank

interconnect tube, discard any self-tapping

coarse thread screw installed in the flanges that

is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(3) If you find damage to the rudder bellcrank interconnect tube, and the damage has not worn into

the aluminum interconnect tube, refinish the

interconnect tube and discard any self-tapping

coarse thread screw installed in the flanges that

is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(4) If you find damage to the rudder bellcrank interconnect tube, and the damage has worn into the

aluminum interconnect tube, you must replace

the interconnect tube and discard any self-tapping coarse thread screw installed in the flanges

that is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(5) Plug the floorboard screw hole ........................... Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Wichita Aircraft

Certification Office (ACO), approves your

alternative. Send your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

of this AD. You should include in the request

an assessment of the effect of the

modification, alteration, or repair on the

unsafe condition addressed by this AD; and,

if you have not eliminated the unsafe

condition, specific actions you propose to

address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Paul C. DeVore,

Aerospace Engineer, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;

telephone: (316) 946–4142; facsimile: (316)

946–4407.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can do the requirements of this

AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from Raytheon

Aircraft Company, P.O. Box 85, Wichita,

Kansas 67201–0085; telephone: (800) 429–

5372 or (316) 676–3140; or on the Internet at

<http://www.raytheon.com/rac/ servinfo/27–

3013.pdf>. This file is in Adobe Portable

Document Format. The Acrobat Reader is

available at <http://www.adobe.com/>. You

can look at copies at the FAA, Central

Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on December 29, 2000.

Issued in Kansas City, Missouri, on

October 30, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–28438 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–28–AD; Amendment

39–12016; AD 2000–24–09]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.