This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

27591

Vol. 66, No. 97

Friday, May 18, 2001

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–347–AD; Amendment

39–12231; AD 2001–10–05]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–100, –200, and –300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

DHC–8–100, –200, and –300 series

airplanes, that requires removing certain

foam filters from the cabin ducting

installation located below the dado

panels on the left- and right-hand sides

of the airplane. The actions specified by

this AD are intended to prevent an

increased risk of spreading a fire or

failure of the cabin to pressurize

adequately if certain foam filters are

installed. This action is intended to

address the identified unsafe condition.

DATES: Effective June 22, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 22,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Bombardier

Regional Aircraft Division, 123 Garratt

Boulevard, Downsview, Ontario M3K

1Y5, Canada. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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: Dan

Parrillo, Aerospace Engineer, Systems

and Flight Test Branch, ANE–172, FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York 11581; telephone

(516) 256–7505; fax (516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Bombardier

Model DHC–8–100, –200, and –300

series airplanes was published in the

Federal Register on February 14, 2001

(66 FR 10232). That action proposed to

require removing certain foam filters

from the cabin ducting installation

located below the dado panels on the

left-and right- hand sides of the

airplane.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 38

Bombardier Model DHC–8–100, –200,

and –300 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 8 work hours

per airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$18,240, or $480 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.

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

adding the following new airworthiness

directive:

2001–10–05 Bombardier, Inc. (Formerly de

Havilland, Inc.): Amendment 39–12231.

Docket 2000–NM–347–AD.

27592 Federal Register / Vol. 66, No. 97 / Friday, May 18, 2001 / Rules and Regulations

Applicability: Model DHC–8–100, –200,

and –300 series airplanes, certificated in any

category, having serial numbers 408, 413, 434

through 463 inclusive, 465 through 489

inclusive, 491 through 505 inclusive, and

507.

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 an increased risk of spreading

a fire, or failure of the cabin to pressurize

adequately if certain foam filters are

installed, accomplish the following:

Removal of Foam Filters

(a) Within 4 months after the effective date

of this AD, remove the foam filters from the

cabin ducting installation located below the

dado panels on the left- and right-hand sides

of the airplane (including verifying that the

foam filters are installed behind the grille

assemblies, inspecting the grille assemblies

on both the port and starboard sides and

along the entire length of the interior of the

airplane, removing all foam filters and

ensuring that no pieces remain, and

reinstalling the grille assemblies by locating

the fasteners and pressing each with a

quarter-turn), per Bombardier Aerospace

Repair Drawing RD8–21–23, Issue 2, dated

December 16, 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 §§ 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 Bombardier Aerospace Repair Drawing

RD8–21–23, Issue 2, dated December 16,

1999, which contains the following list of

effective pages:

Page No.

Revision

Level shown

on page

Date shown on

page

1 ............... 2 Dec. 16, 1999.

2 ............... 1 Dec. 18, 1998.

3 ............... 2 Dec. 16, 1999.

(Only page 1 contains the issue date of the

drawing; no other page contains this

information.) 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., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, 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–

2000–25, dated August 28, 2000.

Effective Date

(e) This amendment becomes effective on

June 22, 2001.

Issued in Renton, Washington, on May 8,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–12007 Filed 5–17–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–05–AD; Amendment

39–12233; AD 2001–10–07]

RIN 2120–AA64

Airworthiness Directives; General

Electric Co. CF6–80C2 Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), that is

applicable to General Electric Co. (GE)

CF6–80C2 turbofan engines with certain

stage 1 high pressure turbine (HPT)

rotor disks installed. This amendment

requires initial and repetitive

inspections of certain HPT rotor disks

for cracks in the bottom of the dovetail

slot. This amendment is prompted by a

report of an uncontained failure of an

engine during a high-power ground run

for maintenance. The actions specified

by this AD are intended to detect cracks

in the bottoms of the dovetail slots that

could propagate to failure of the disk

and cause an uncontained engine

failure.

DATES: Effective date June 18, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of June 18, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from General Electric Company via

Lockheed Martin Technology Services,

10525 Chester Road, Suite C, Cincinnati,

Ohio 45215, telephone (513) 672–8400,

fax (513) 672–8422. This information

may be examined at the Federal

Aviation Administration (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: Ann

Mollica, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone: (781) 238–7740, fax:

(781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to

General Electric Co. (GE) CF6–80C2

turbofan engines with certain stage 1

HPT rotor disks installed was published

in the Federal Register on March 12,

2001 (66 FR 14348). That action

proposed to detect cracks in the bottoms

of the dovetail slots that could

propagate to failure of the disk and

cause an uncontained engine failure.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Include Alert Service Bulletin Revision 1

One commenter states that Table 1

should reference GE Alert Service

Bulletin (ASB) CF6–80C2 72–A1024,

Revision 1, dated November 3, 2000, as

well as the original ASB issue.

The FAA agrees. The inspection

requirements in ASB Revision 1 are the

equivalent of the inspection

requirements of original issue ASB CF6–

80C2 72–A1024, dated October 13,

2000. Reference to ASB CF6–80C2 72–