12724 Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations

Note: Warranty credit will be allowed on

all affected airplanes to the extent specified

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:

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:

2001–04–05 Raytheon Aircraft Company:

Amendment 39-12123; Docket No. 2000-

CE–10–AD.

(a) What airplanes are affected by this AD?

This AD affects Beech Model 1900D

airplanes, serial numbers UE–156 through

UE–299, that are:

(1) Certificated in any category; and

(2) Equipped with a KLN–90B Global

Positioning System (GPS) incorporated in

accordance with AlliedSignal Supplemental

Type Certificate (STC) SA00245WI–D.

(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 assure that the copilot’s NAV ‘‘FLAG’’

displays are based on the copilot’s selected

NAV source. Inconsistent NAV ‘‘FLAG’’

displays could cause the copilot to make

decisions based on an invalid GPS source

without knowing it was invalid.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

Rewire the KLN–90B Global Positioning System to eliminate the possibility of inconsistent

NAV ‘‘FLAG’’ displays.

Within the next 400 hours time-in-service

(TIS) after April 9, 2001 (the effective date

of this AD), unless already accomplished.

In accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Raytheon Mandatory Service Bulletin SB 34–3222, Issued:

January, 2000.

(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. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note 1: 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. 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 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 Todd Dixon, Aerospace

Engineer, Wichita Aircraft Certification

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

telephone: (316) 946–4152; 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

§§ 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 accomplish 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 34–

3222, Issued: January, 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 the Raytheon Aircraft Company, PO Box

85, Wichita, Kansas 67201–0085. 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 April 9, 2001.

Issued in Kansas City, Missouri, on

February 8, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–4049 Filed 2–27–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–27–AD; Amendment

39–12125; AD 2001–03–52]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B16 (CL–604) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting airworthiness directive (AD)

2001–03–52 that was sent previously to

all known U.S. owners and operators of

Bombardier Model CL–600–2B16 (CL–

604) series airplanes by individual

notices. This AD requires revising the

airplane flight manual to provide the

flight crew with revised aft center of

gravity (CG) limits. This action is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign airworthiness authority. The

Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations 12725

actions specified by this AD are

intended to prevent fuel migration

under conditions of acceleration and/or

climb, which could result in the

airplane exceeding the aft center of

gravity limit, and consequent loss of

control of the airplane.

DATES: Effective March 5, 2001, to all

persons except those persons to whom

it was made immediately effective by

emergency AD 2001–03–52, issued

February 2, 2001, which contained the

requirements of this amendment.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 5,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

March 30, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

27–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 fax or the Internet must contain

‘‘Docket No. 2001–NM–27–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The applicable service information

may be obtained from Bombardier, Inc.,

Canadair, Aerospace Group, P.O. Box

6087, Station Centre-ville, 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; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

James E. Delisio, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York;

telephone (516) 256–7521; fax (516)

568–2716.

SUPPLEMENTARY INFORMATION: On

February 2, 2001, the FAA issued

emergency AD 2001–03–52, which is

applicable to certain Bombardier Model

CL–600–2B16 (CL–604) series airplanes.

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, recently notified

the FAA that an unsafe condition may

exist on certain Bombardier Model CL–

600–2B16 (CL–604) series airplanes.

The TCCA reported a recent incident

that occurred during a flight test in

which, during the initial takeoff

rotation, an airplane pitched up at a

significantly high rate resulting in a

natural stall. After the initial pushover

from the stall, the airplane stalled again

when the pilot attempted to raise the

nose a second time.

Investigation revealed that fuel

migration in the center fuel tank caused

a center of gravity shift. The fuel tanks

are not baffled, which allows fuel to

migrate when the airplane pitches up.

Such fuel migration under conditions of

acceleration and/or climb, if not

corrected, could result in the airplane

exceeding the aft center of gravity limit,

and consequent loss of control of the

airplane.

Correction of Typographical Error

The FAA has revised paragraph (a) of

this AD to correct a typographical error

that appeared in the emergency AD. The

typographical error referenced Canadair

Challenger CL–604 Airplane Flight

Manual (AFM) PSP–606–1, which does

not exist, and has been changed to

Canadair Challenger CL–604 Airplane

Flight Manual (AFM) PSP–604–1 in the

Federal Register version of the final

rule.

FAA’s Conclusions

This airplane model is manufactured

in Canada and is type certificated for

operation in the United States under the

provisions of § 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 the 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 the Requirements of the

Rule

Since the unsafe condition described

is likely to exist or develop on other

airplanes of the same type design

registered in the United States, the FAA

issued emergency AD 2001–03–52 to

prevent fuel migration under conditions

of acceleration and/or climb, which

could result in the airplane exceeding

the aft center of gravity limit, and

consequent loss of control of the

airplane. The AD requires revising the

FAA-approved Airplane Flight Manual

to provide the flight crew with revised

aft center of gravity (CG) limits that

prevent fuel migration from resulting in

a rearward shift of the CG to the degree

that will result in controllability

problems.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

notices issued on February 2, 2001, to

all known U.S. owners and operators of

Bombardier Model CL–600–2B16 (CL–

604) series airplanes. These conditions

still exist, and the AD is hereby

published in the Federal Register as an

amendment to section 39.13 of the

Federal Aviation Regulations (14 CFR

39.13) to make it effective as to all

persons.

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.

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

12726 Federal Register / Vol. 66, No. 40 / Wednesday, February 28, 2001 / Rules and Regulations

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NM–27–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,

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:

2001–03–52 Bombardier Inc. (Formerly

Canadair): Amendment 39–12125.

Docket 2001–NM–27–AD.

Applicability: Model CL–600–2B16 (CL–

604) series airplanes, serial numbers 5301

through 5489 inclusive; certificated in any

category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fuel migration under conditions

of acceleration and/or climb, which could

result in the airplane exceeding the aft center

of gravity limit, and consequent loss of

control of the airplane, accomplish the

following:

Airplane Flight Manual Revision

(a) Within 5 days after the effective date of

this AD, revise the Limitations and Abnormal

Procedures Sections of the Canadair

Challenger CL–604 Airplane Flight Manual

(AFM) PSP–604–1, by inserting a copy of

Canadair Challenger Temporary Revision

(TR) No. 604/13, dated February 1, 2001, into

the AFM.

(b) When the information in TR No. 604/

13, dated February 1, 2001, has been

incorporated into the FAA-approved general

revisions of the AFM, the general revisions

may be inserted in the AFM, and the TR may

be removed from the AFM.

Alternative Methods of Compliance

(c) 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). 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 1: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Note 2: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2001–07, dated February 2, 2001.

Incorporation by Reference

(d) The AFM revision shall be done in

accordance with Canadair Challenger

Temporary Revision No. 604/13, dated

February 1, 2001. 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.

Effective Date

(e) This amendment becomes effective on

March 5, 2001, to all persons except those

persons to whom it was made immediately

effective by emergency AD 2001–03–52,

issued February 2, 2001, which contained the

requirements of this amendment.

Issued in Renton, Washington, on February

13, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4217 Filed 2–27–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–57–AD; Amendment

39–12124; AD 2001–04–06]

RIN 2120–AA64

Airworthiness Directives; CFM

International, S.A. CFM56–3, –3B, and

–3C Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to CFM International, S.A.

CFM56–3, –3B, and –3C series turbofan

engines. This amendment requires that

use of certain lubricants no longer on

the manufacturer’s approved list be

discontinued. In addition, this

amendment requires a one-time fan disk

dovetail wear measurement, and if wear

exceeds certain limits, requires an

ultrasonic inspection for cracks in the

fan disk, and, if necessary, removal from

service of fan disks and replacement

with serviceable parts. This amendment

is prompted by reports of fan disk heavy

wear and cracks. The actions specified

by this amendment are intended to

prevent fan disk failure, which could

result in an uncontained engine failure

and damage to the aircraft.

DATES: Effective date April 4, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of April 4, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFM International, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2800, fax (513) 552–2816.

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:

Glorianne Niebuhr, Aerospace Engineer,

Engine Certification Office, FAA, Engine