65832 Federal Register / Vol. 66, No. 246 / Friday, December 21, 2001 / Rules and Regulations

Actions Compliance Procedures

(3) For airplanes that incorporate an MSN in

the range of 321 through 331, 333, 335, 336,

338 through 341, 343, or 345, install a new

design FCWU (Pilatus part number FCWU

99–3) with a serial number of 100,001 or

higher, or FAA-approved equivalent part

number..

Within the next 50 hours TIS after January

25, 2002 (the effective date of this AD), unless already accomplished.

In accordance with the Accomplishment Instructions section of Pilatus PC–12 Service

Bulletin No. 27–008, pages 1, 2, and 11 at

the Revision 2 level, dated September 13,

2000; and pages 3 through 10 and 12

through 114 at the Revision 1 level, dated

June 26, 2000. Pilatus PC–12 Service Bulletin 27–012, dated September 13, 2000,

also relates to this subject.

(4) For airplanes that incorporate an MSN in

the range of 101 through 400, modify the flap

control wiring and install a flap power driveunit field control panel..

Within the next 50 hours TIS after January

25, 2002 (the effective date of this AD).

In accordance with the Accomplishment Instructions section of Pilatus PC–12 Service

Bulletin No. 27–011, Revision No. 1, dated

January 26, 2001.

(5) For all MSN airplanes, inspect the flap actuator internal gear system for correct end-play

and backlash measurements and make any

necessary corrective adjustments..

Inspect initially within the next 50 hours TIS

after January 25, 2002 (the effective date of

this AD) and thereafter at intervals not to

exceed 600 hours TIS. Accomplish corrective adjustments prior to further flight after

the inspection where deficiencies are detected.

In accordance with the instructions in Pilatus

PC–12 Maintenance Manual Temporary

Revision No. 27–14 (which superseded

Temporary Revision No. 27–13), dated December 4, 2000, or Pilatus PC–12 Aircraft

Maintenance Manual 27–50–03, pages 601

through 608, dated April 30, 2000, as applicable.

(6) For all MSN airplanes, do not install any

Pilatus part number FCWU 99–3 that has a

serial number of 100,000 or less..

As of January 25, 2002 (the effective date of

this AD).

Not Applicable.

Note 1: The FAA recommends that you

incorporate the most up-to-date Pilatus

reports and revisions pertaining to this

subject into the Pilatus PC–12 Pilot’s

Operating Handbook. The most up-to-date

documents as of the issue date of this AD are

Temporary Revision No. 15, Report No.

01973–001, Issued: April 3, 2000, Sections 3

and 7; and Temporary Revision No. 32,

Report No. 01973–001, Issued: January 8,

2001, Sections 2 and 3.

(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, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 2: 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 Doug Rudolph,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

(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 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

Pilatus PC–12 Service Bulletin No. 27–008,

pages 1, 2, and 11 at the Revision 2 level,

dated September 13, 2000, and pages 3

through 10 and 12 through 114 at the

Revision 1 level, dated June 26, 2000; Pilatus

PC–12 Service Bulletin 27–012, dated

September 13, 2000; Pilatus PC–12 Service

Bulletin No. 27–011, Revision No. 1, dated

January 26, 2001; Pilatus PC–12 Maintenance

Manual Temporary Revision No. 27–14

(which superseded Temporary Revision No.

27–13), dated December 4, 2000; and Pilatus

PC–12 Aircraft Maintenance Manual 27–50–

03, pages 601 through 608, dated April 30,

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 Pilatus Aircraft Ltd.,

Customer Liaison Manager, CH–6371 Stans,

Switzerland; telephone: +41 41 619 63 19;

facsimile: +41 41 619 6224; or from Pilatus

Business Aircraft Ltd., Product Support

Department, 11755 Airport Way, Broomfield,

Colorado 80021; telephone: (303) 465–9099;

facsimile: (303) 465–6040. 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 January 25, 2002.

Issued in Kansas City, Missouri, on

December 11, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–31102 Filed 12–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–28–AD; Amendment

39–12570; AD 2001–26–06]

RIN 2120–AA64

Airworthiness Directives; CFE

Company Model CFE738–1–1B

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to CFE Company model

CFE738–1–1B turbofan engines. This

action requires the removal of certain

fan rotor disks from service. This

amendment is prompted by a report

from a forging manufacturer, of a

metallurgical inclusion (contaminant)

found in a forging made from a certain

Federal Register / Vol. 66, No. 246 / Friday, December 21, 2001 / Rules and Regulations 65833

ingot of titanium. Fan rotor disks for

model CFE738–1–1B engines have been

manufactured from this same ingot and

are suspect for metallurgical inclusions.

The actions specified in this AD are

intended to remove from service

affected fan rotor disks, which if not

removed, could result in uncontained

engine failure and damage to the

airplane.

DATES: Effective January 7, 2002.

Comments for inclusion in the Rules

Docket must be received on or before

February 19, 2002.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2001–NE–

28–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may be inspected at this location, by

appointment, between 8 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays. Comments may also

be sent via the Internet using the

following address: ‘‘9-aneadcomment@faa.gov’’. Comments sent

via the Internet must contain the docket

number in the subject line. The service

information referenced in this AD may

be obtained from CFE Company, Data

Distribution, MS 64–03/2101–201, P.O.

Box 52170, Phoenix, AZ 85972–2170;

telephone (602) 365–2493, fax (602)

365–5577.

FOR FURTHER INFORMATION CONTACT:

Keith Mead, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7744,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: The FAA

was recently notified of a report from a

forging manufacturer of a metallurgical

inclusion (contaminant) found by

ultrasonic inspection in a certain forged

part. This part was made from a certain

ingot of titanium. The engine

manufacturer also reports that CFE738

fan rotor disks were manufactured from

this same ingot and are, therefore,

suspected of containing these

metallurgical inclusions. Metallurgical

inclusions are known to be crack

initiation sites in highly stressed

engines parts. Cracks that have initiated

from inclusions in disk material have

caused uncontained disk failures. The

FAA has therefore determined that these

suspect fan rotor disks could fail as a

result of having metallurgical

inclusions. This condition, if not

corrected, could result in uncontained

engine failure and damage to the

airplane.

Requirements of This AD

Since an unsafe condition has been

identified that is likely to exist or

develop on other CFE Company model

CFE738–1–1B turbofan engines of the

same type design, this AD is being

issued to remove from service affected

fan rotor disks, which if not removed,

could result in uncontained engine

failure and damage to the airplane. This

AD requires the removal from service of

certain fan rotor disks, either before

further flight or by an engine cycle

schedule, based on fan rotor disk serial

number.

Immediate Adoption of This AD

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 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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001-NE–28-AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Analysis

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it

would 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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this final rule.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and 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, 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:

2001–26–06 CFE Company: Amendment

39–12570. Docket 2001–NE–28–AD.

Applicability: This airworthiness directive

(AD) is applicable to CFE Company model

CFE738–1–1B turbofan engines that contain

fan rotor disks part number (P/N) 3050745–

2, serial numbers (SN’s) 000322903511

through 000322903536, and 000322903538

through 000322903541. These engines are

65834 Federal Register / Vol. 66, No. 246 / Friday, December 21, 2001 / Rules and Regulations

installed on, but not limited to Dassault

Aviation Falcon 2000 series airplanes.

Note 1: This AD applies to each engine

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

engines 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 (g) 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: Compliance with this AD is

required as indicated, unless already done.

To remove from service affected fan disks,

which if not removed, could result in

uncontained engine failure and damage to

the airplane, do the following:

(a) Remove from service before further

flight, the following serial number (SN) fan

rotor disks listed in Table 1:

TABLE 1. SN’S OF FAN ROTOR DISKS REQUIRING REMOVAL BEFORE FURTHER FLIGHT

000322903512 000322903520 000322903528 000322903535

000322903513 000322903521 000322903529 000322903536

000322903516 000322903523 000322903530 000322903538

000322903517 000322903524 000322903531 000322903539

000322903518 000322903525 000322903533 000322903540

000322903519 000322903527 000322903534 000322903541

(b) Remove from service within 10 engine

cycles-in-service after the effective date of

this AD, fan rotor disks SN’s 000322903511,

000322903515, and 000322903526.

(c) Remove from service within 70 engine

cycles-since-new (CSN), fan rotor disk SN

000322903514.

(d) Remove from service within 140 engine

CSN, fan rotor disks SN 000322903522 and

000322903532.

(e) The manufacturer’s records indicate

that fan rotor disks identified in paragraphs

(a) through (d) of this AD were installed in,

and may still be installed in the engines

listed by SN in the following Table 2. This

AD, however, applies to any engine with the

fan rotor disks installed, identified in

paragraphs (a) through (d) of this AD. Table

2 is provided for informational purposes only

to assist in locating engines that may be

affected. For information on replacing the

affected fan rotor disks in this AD, see CFE

Company Alert Service Bulletin CFE738-

A72–8053, dated July 24, 2001.

105430 105446 105455 105467

105432 105447 105456 105469

105434 105448 105457 105471

105438 105450 105459 105472

105441 105451 105461 105474

105443 105452 105462 105475

105444 105453 105463

105445 105454 105466

(f) After the effective date of this AD, do

not install any fan rotor disks P/N 3050745–

2, SN’s 000322903511 through

000322903536, and 000322903538 through

000322903541 onto any engine.

Alternative Methods of Compliance

(g) 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, Engine

Certification Office (ECO). Operators must

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(h) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the aircraft to a

location where the requirements of this AD

can be done.

Effective Date

(i) This amendment becomes effective on

January 7, 2002.

Issued in Burlington, Massachusetts, on

December 14, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–31326 Filed 12–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 01–AWP–27]

Establishment of a Class E Enroute

Domestic Airspace Area, Iron

Mountain, CA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule, requests for

comments.

SUMMARY: This action establishes a Class

E enroute domestic airspace area

beginning at 1,200 feet above ground

level (AGL) in the vicinity of Iron

Mountain, CA, to replace existing Class

G uncontrolled airspace.

DATES: Effective Date: 0901 UTC

February 21, 2002. Comment Date:

Comments for inclusion in the Rules

Docket must be received on or before

January 22, 2002.

ADDRESSES: Send comments on the

direct final rule in triplicate to: Federal

Aviation Administration, Attn:

Manager, Airspace Branch, AWP–520,

Docket No. 01–AWP–27, Air Traffic

Division, P.O. Box 92007, Los Angeles,

California 90009.

The official docket may be examined

in the Office of the Assistant Chief

Counsel, Western-Pacific Region,

Federal Aviation Administration, Room

6007, 15000 Aviation Boulevard,

Lawndale, California 90261.

An informal docket may also be

examined during normal business hours

at the Office of the Manager, Airspace

Branch, Air Traffic Division at the above

address.

FOR FURTHER INFORMATION CONTACT:

Debra Trindle, Air Traffic Division,

Airspace Specialist, AWP–520, WesternPacific Region, Federal Aviation

Administration, 15000 Aviation

Boulevard, Lawndale, California 90261,

telephone (301) 725–6613.