14288 Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Rules and Regulations

There are approximately 440 engines

of the affected design in the worldwide

fleet. The FAA estimates that 150

engines installed on aircraft of U.S.

registry will be affected by this AD, and

that it will take approximately zero

additional work hours per engine to

accomplish the required actions.

Required parts will cost approximately

$7,667 per engine, based on the

estimated current part cost, prorated

downward by a factor equal to the

quotient of the difference between the

original cyclic life limit (9,000 cycles)

and the revised cyclic life limit (6,000

cycles) divided by the original cyclic

life limit. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $1,150,000.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–06–15 General Electric Company:

Amendment 39–9972. Docket 95–ANE–

41.

Applicability: General Electric Company

(GE) Models CF34–1A, –3A, and –3A2

turbofan engines, with high pressure

compressor (HPC) stage 1 rotor disks, part

number 6040T79G01, installed. These

engines are installed on but not limited to

Canadair Limited Model CL–600–2A12 and

CL–600–2B16 aircraft.

Note 1: This airworthiness directive (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 (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 HPC stage 1 rotor disk rupture,

engine failure, and damage to the aircraft,

accomplish the following:

(a) Remove from service HPC stage 1 rotor

disks prior to accumulating 6,000 cycles in

service since new, and replace with a

serviceable part.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(c) This amendment becomes effective on

May 27, 1997.

Issued in Burlington, Massachusetts, on

March 14, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–7597 Filed 3–25–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–19; Amendment 39–

9971; AD 97–06–14]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF34 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to General Electric Company

CF34 series turbofan engines, that

reduces the allowable operating cyclic

life limit for affected fan disks. This

amendment is prompted by an updated

stress and life analysis. The actions

specified by this AD are intended to

prevent fan disk rupture, engine failure,

and damage to the aircraft.

DATES: Effective May 27, 1997.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.

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 General Electric

Company (GE) CF34 series turbofan

engines was published in the Federal

Register on March 25, 1996 (61 FR

12050). That action proposed to reduce

the allowable operating cyclic life limit

for affected fan disks.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

There are approximately 440 engines

of the affected design in the worldwide

fleet. The FAA estimates that 150

engines installed on aircraft of U.S.

registry will be affected by this AD, that

it will take approximately zero

additional work hours per engine to

accomplish the required actions.

Required parts will cost approximately

$106,320 per engine, based on the

estimated current part cost, prorated

downward by a factor equal to the

quotient of the difference between the

original cyclic life limit (38,280 cycles)

and the revised cyclic life limit (9,000

cycles) divided by the original cyclic
Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Rules and Regulations 14289

life limit. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $15,950,000.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–06–14 General Electric Company:

Amendment 39–9971. Docket 95–ANE–

19.

Applicability: General Electric Company

(GE) Model CF34–1A, –3A, and –3A2

turbofan engines, with fan disk part numbers

(P/N’s) 6020T62G04, 6020T62G05,

6078T00G01, or 5921T54G01 installed. These

engines are installed on but not limited to

Canadair Limited Model CL–600–2A12 and

CL-600–2B16 aircraft.

Note 1: This airworthiness directive (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 (d)

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 fan disk rupture, engine failure,

and damage to the aircraft, accomplish the

following:

(a) Remove from service fan disks, P/N’s

6020T62G04, 6020T62G05, 6078T00G01, and

5921T54G01, prior to accumulating 9,000

cycles in service (CIS) since new, and replace

with a serviceable part.

(b) For the purpose of this AD, a

serviceable part is defined as a fan disk with

less than 9,000 CIS.

(c) This AD defines a new life limit of

9,000 CIS for fan disks, P/N’s 6020T62G04,

6020T62G05, 6078T00G01, and 5921T54G01.

(d) 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. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(e) 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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) This amendment becomes effective on

May 27, 1997.

Issued in Burlington, Massachusetts, on

March 11, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–7596 Filed 3–25–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–ASW–15]

Establishment of Class D Airspace;

McKinney, TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action establishes the

Class D airspace extending upward from

the surface to and including 2,900 feet

mean sea level (MSL) at McKinney, TX.

An air traffic control tower has begun

providing air traffic control services for

pilots operating at McKinney Municipal

Airport. This action is intended to

provide adequate controlled airspace for

aircraft operating at McKinney

Municipal Airport, McKinney, TX.

EFFECTIVE DATE: 0901 UTC, May 22,

1997.

FOR FURTHER INFORMATION CONTACT:

Donald J. Day, Airspace Branch, Air

Traffic Division, Southwest Region,

Federal Aviation Administration, Fort

Worth, TX 76193–0530, telephone 817–

222–5593.

SUPPLEMENTARY INFORMATION:

History

On June 19, 1996, a proposal to

amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to establish

the Class D airspace at McKinney, TX,

was published in the Federal Register

(61 FR 31063). A municipal contracted

air traffic control tower has begun

providing air traffic control services for

pilots operating at McKinney Municipal

Airport. The proposal was to establish

adequate controlled airspace extending

upward from the surface to and

including 2,900 feet MSL within a 4-

mile radius of the airport. The proposal

was intended to provide controlled

airspace at McKinney Municipal

Airport.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments to the proposal were

received. The rule is therefore adopted

as proposed.

The coordinates for this airspace

docket are based on North American

Datum 83. Class D airspace designations

for airspace areas are published in

Paragraph 5000 of FAA Order 7400.9D

dated September 4, 1996, and effective

September 16, 1996, which is

incorporated by reference in 14 CFR

71.1. The Class D airspace designation

listed in this document will be

published subsequently in the Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) establishes the Class D airspace

located at McKinney Municipal Airport,

McKinney, TX, to provide controlled

airspace for aircraft operating with the

services of the air traffic control tower.

The FAA has determined that this

regulation only involves an established