Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75605

AD prior to the effective date of this AD in

accordance with Airbus Service Bulletin

A320–27–1117, dated July 31, 1997, or

Revision 01, dated June 25, 1999, is

acceptable for compliance with that

paragraph.

Alternative Methods of Compliance

(g)(1) 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. Operators

shall submit requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

(2) Alternative methods of compliance,

approved previously in accordance with AD

99–17–11, amendment 39–11259, are

approved as alternative methods of

compliance with this AD.

Note 4: 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

(h) 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

(i) Except as required by paragraph (d) of

this AD, the actions shall be done in

accordance with Airbus Service Bulletin

A320–27–1108, Revision 01, dated July 15,

1997; Airbus Service Bulletin A320–27–1108,

Revision 02, dated April 17, 1998; Airbus

Service Bulletin A320–27–1108; Revision 03,

dated June 25, 1999; Airbus Service Bulletin

A320–27–1066, Revision 4, dated July 15,

1997; Airbus Service Bulletin A320–27–1097,

Revision 01, dated July 15, 1997; Airbus

Service Bulletin A320–27–1097, Revision 02,

dated June 25, 1999; Airbus Service Bulletin

A320–27–1108, Revision 04, dated November

22, 1999; Airbus Service Bulletin A320–27–

1066, Revision 5, dated June 25, 1999; and

Airbus Service Bulletin A320–27–1117,

Revision 02, dated January 18, 2000; as

applicable.

(1) The incorporation by reference of

Airbus Service Bulletin A320–27–1108,

Revision 04, dated November 22, 1999;

Airbus Service Bulletin A320–27–1066,

Revision 5, dated June 25, 1999; and Airbus

Service Bulletin A320–27–1117, Revision 02,

dated January 18, 2000, is approved by the

Director of the Federal Register in accordance

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

(2) The incorporation by reference of

Airbus Service Bulletin A320–27–1108,

Revision 01, dated July 15, 1997; Airbus

Service Bulletin A320–27–1108, Revision 02,

dated April 17, 1998; Airbus Service Bulletin

A320–27–1108; Revision 03, dated June 25,

1999; Airbus Service Bulletin A320–27–1066,

Revision 4, dated July 15, 1997; Airbus

Service Bulletin A320–27–1097, Revision 01,

dated July 15, 1997; and Airbus Service

Bulletin A320–27–1097, Revision 02, dated

June 25, 1999, was approved previously by

the Director of the Federal Register as of

September 27, 1999 (64 FR 45868, August 23,

1999).

(3) Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 5: The subject of this AD is addressed

in French airworthiness directive 1996–271–

092(B) R3, dated August 11, 1999.

Effective Date

(j) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 20, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30119 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–368–AD; Amendment

39–12008; AD 2000–24–01]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–1A11 (CL–600), CL–

600–2A12 (CL–601), and CL–600–2B16

(CL–601–3A, CL–601–3R, and CL–604)

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Bombardier Model

CL–600–1A11 (CL–600), CL–600–2A12

(CL–601), and CL–600–2B16 (CL–601–

3A, CL–601–3R, and CL–604) series

airplanes. This action requires

installation of protection shields in the

wheel bay of the main landing gear

(MLG). This action is necessary to

prevent water, ice or slush

accumulation on the aileron quadrants

and/or control cable pulleys in the

wheel bay of the MLG during ground

roll. Such water, ice or slush

accumulation could subsequently freeze

during the climb to cruise altitude and

cause stiffness in the aileron controls,

which could result in reduced

controllability of the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

19, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 3, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

368–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. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9–

anm-iarcomment@faa.gov. Comments

sent via the Internet must contain

‘‘Docket No. 2000–NM–368–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via fax or

the Internet as attached electronic files

must be formatted in Microsoft Word 97

for Windows or ASCII text.

The service information referenced in

this AD may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9,

Canada. This information may be

examined 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.

FOR FURTHER INFORMATION CONTACT: Dan

Parillo, Aerospace Engineer, Systems

and Flight Test Branch, ANE–172, FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York; telephone (516) 256–

7505; fax (516) 568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Civil Aviation, which is the

airworthiness authority for Canada,

notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–1A11 (CL–

600), CL–600–2A12 (CL–601), and CL–

600–2B16 (CL–601–3A, CL–601–3R, and

CL–604) series airplanes. TCCA advises

that it has received several reports of

stiffness in the aileron controls

following takeoff from a wet or snow/

slush covered runway. The cause of the

stiffness has been attributed apparently

to water, ice or slush accumulation on

75606 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

the aileron quadrants and/or control

cable pulleys in the wheel bay of the

main landing gear (MLG) during ground

roll, which subsequently froze during

the climb to cruise altitude. This

condition, if not corrected, could result

in stiffness in the aileron controls and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

Bombardier has issued the following

service bulletins:

Bombardier service bulletin Service bulletin date Model

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

601–0507 .................................. June 30, 1998 .................................................. CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A

and CL–601–3R)

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

The service bulletins describe

procedures for installation of protection

shields in the wheel bay of the MLG.

Accomplishment of the action specified

in the applicable service bulletin is

intended to adequately address the

identified unsafe condition. TCCA

classified these service bulletins as

mandatory and issued Canadian

airworthiness directive CF–2000–30,

dated September 12, 2000, in order to

assure the continued airworthiness of

these airplanes in Canada.

FAA’s Conclusions

These airplane models are

manufactured in Canada and are 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, TCCA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of TCCA,

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 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, this AD is being issued to

prevent water, ice or slush

accumulation on the aileron quadrants

and/or control cable pulleys in the

wheel bay of the MLG during ground

roll. Such water, ice or slush

accumulation could subsequently freeze

during the climb to cruise altitude and

cause stiffness in the aileron controls,

which could result in reduced

controllability of the airplane. This AD

requires accomplishment of the action

specified in the service bulletins

described previously.

Differences Between the AD and

Foreign Airworthiness Directive

The AD would differ from the parallel

Canadian airworthiness directive in that

it would require accomplishment of the

installation within 45 days after the

effective date of this AD. The parallel

Canadian airworthiness directive

recommends accomplishment of the

installation within 120 days after

October 25, 2000 (the effective date of

the Canadian airworthiness directive).

In developing an appropriate

compliance time for this AD, the FAA

considered not only TCCA’s

recommendation, but the onset of

inclement weather conditions, degree of

urgency associated with addressing the

subject unsafe condition, and average

utilization of the affected fleet. In light

of these factors, the FAA finds a 45-day

compliance time for initiating the

required installation to be warranted, in

that it represents an appropriate interval

of time allowable for affected airplanes

to continue to operate without

compromising safety.

Determination of Rule’s Effective Date

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 shall 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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 Number 2000–NM–368–AD.’’

The postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

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