39536 Federal Register / Vol. 65, No. 124 / Tuesday, June 27, 2000 / Rules and Regulations

have a significant economic impact on

a substantial number of small entities.

Executive Order 12372

This program/activity is listed in the

Catalog of Federal Domestic Assistance

under No. 10.025 and is subject to

Executive Order 12372, which requires

intergovernmental consultation with

State and local officials. (See 7 CFR part

3015, subpart V.)

Executive Order 12988

This final rule has been reviewed

under Executive Order 12988, Civil

Justice Reform. This rule: (1) Preempts

all State and local laws and regulations

that are in conflict with this rule; (2) has

no retroactive effect; and (3) does not

require administrative proceedings

before parties may file suit in court

challenging this rule.

Paperwork Reduction Act

This rule contains no new

information collection or recordkeeping

requirements under the Paperwork

Reduction Act of 1995 (44 U.S.C. 3501

et seq.).

List of Subjects

9 CFR Part 54

Animal diseases, Goats, Indemnity

payments, Scrapie, Sheep.

9 CFR Part 79

Animal diseases, Quarantine, Sheep,

Transportation.

Accordingly, we are amending 9 CFR

parts 54 and 79 as follows:

PART 54—CONTROL OF SCRAPIE

1. The authority citation for part 54

continues to read as follows:

Authority: 21 U.S.C. 111, 114, 114a, and

134a–134h; 7 CFR 2.22, 2.80, and 371.2(d).

2. In § 54.1, the following definition is

added in alphabetical order to read as

follows:

§ 54.1 Definitions.

* * * * *

Scrapie control pilot project. A pilot

project authorized by the Administrator

in writing, designed to test or improve

program procedures or to facilitate

research, in order to control and

eradicate scrapie. In addition to APHIS,

participants may include State animal

health agencies, flock owners, and other

parties as necessary.

* * * * *

3. A new § 54.14 is added to read as

follows:

§ 54.14 Waiver of requirements for scrapie

control pilot projects.

(a) The Administrator may waive the

following requirements of this part for

participants in a scrapie control pilot

project by recording the requirements

waived in the scrapie control pilot

project plan:

(1) The determination that an animal

is a high-risk animal, if the scrapie

control pilot project plan contains

testing or other procedures that indicate

that an animal, despite meeting the

definition of high-risk animal, is

unlikely to spread scrapie; and

(2) The requirement that high-risk

animals must be removed from a flock

if the scrapie control pilot project plan

contains alternative procedures to

prevent the further spread of scrapie

without removing high-risk animals

from the flock.

(b) [Reserved]

PART 79—SCRAPIE IN SHEEP AND

GOATS

1. The authority citation for part 79

continues to read as follows:

Authority: 21 U.S.C. 111–113, 115, 117,

120, 121, 123–126, 134b, and 134f; 7 CFR

2.22, 2.80, and 371.2(d).

2. In § 79.1, the following definition is

added in alphabetical order to read as

follows:

§ 79.1 Definitions.

* * * * *

Scrapie control pilot project. A pilot

project authorized by the Administrator

in writing, designed to test or improve

program procedures or to facilitate

research, in order to control and

eradicate scrapie. In addition to APHIS,

participants may include State animal

health agencies, flock owners, and other

parties as necessary.

* * * * *

3. A new § 79.4 is added to read as

follows:

§ 79.4 Waiver of requirements for scrapie

control pilot projects.

(a) The Administrator may waive the

following requirements of this part for

participants in a scrapie control pilot

project by recording the requirements

waived in the scrapie control pilot

project plan:

(1) The determination that an animal

is a high-risk animal, if the scrapie

control pilot project plan contains

testing or other procedures that indicate

that an animal, despite meeting the

definition of high-risk animal, is

unlikely to spread scrapie; and

(2) The requirement that high-risk

animals must be removed from a flock,

if the scrapie control pilot project plan

contains alternative procedures to

prevent the further spread of scrapie

without removing high-risk animals

from the flock.

(b) [Reserved]

Done in Washington, DC, this 21st day of

June 2000.

Bobby R. Acord,

Acting Administrator, Animal and Plant

Health Inspection Service.

[FR Doc. 00–16219 Filed 6–26–00; 8:45 am]

BILLING CODE 3410–34–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–45–AD; Amendment 39–

11786; AD 2000–12–08]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company Models CF6–

80C2A1/A2/A3/A5/A5F/A8/D1F

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 Company

(GE) Models CF6–80C2A1/A2/A3/A5/

A5F/A8/D1F turbofan engines. This AD

requires initial and repetitive visual

inspections of left hand and right hand

aft engine mount link assemblies for

separations, cracks and spherical

bearing race migration. Cracked or

separated parts must be replaced prior

to further flight. If spherical bearing race

migration is discovered, an additional

borescope inspection for cracks is also

required. If no cracks are discovered by

the additional borescope inspection,

assemblies have a 75-cycle grace period

for remaining in service before

replacement. Finally, installation of

improved aft engine mount link

assemblies constitutes terminating

action to the inspections of this AD.

This amendment is prompted by a

report of a fractured left hand aft engine

mount link discovered during a

scheduled removal of an engine of

similar design. The actions specified by

the AD are intended to prevent aft

engine mount link failure, which can

result in adverse redistribution of the aft

engine mount loads and possible aft

engine mount system failure.

DATES: Effective date August 28, 2000.

The incorporation by reference of

certain publications listed in the rule is

Federal Register / Vol. 65, No. 124 / Tuesday, June 27, 2000 / Rules and Regulations 39537

approved by the Director of the Federal

Register as of August 28, 2000.

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 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:

Karen Curtis, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7192,

fax (781) 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 Models CF6–80C2A1/A2/A3/

A5/A5F/A8/D1F turbofan engines was

published in the Federal Register on

February 23, 2000 (65 FR 8892). That

action proposed to require initial and

repetitive visual inspections of left hand

and right hand aft engine mount link

assemblies for separations, cracks and

spherical bearing race migration and

replacement of cracked or separated

parts prior to further flight.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Link Assembly Replacement Cost

Although one comment agrees with

the technical content of the AD, concern

was expressed because the economic

analysis within the NPRM indicates that

the cost to replace link assemblies is

approximately $7,000 per engine, while

the service bulletin indicates the cost is

$9,718 per engine. The comment

suggests that the FAA should change its

economic analysis to match the cost

quoted in the Service Bulletin. The FAA

does not agree. The FAA started with

the new part costs cited in the service

bulletin, but took into account that some

useful life had been realized from the

existing parts. The $7,000 per engine

cost to replace link assemblies quoted in

the NPRM represents the cost of the lost

life of existing, installed links.

Length of Grace Period

Another comment requests that the

length of the grace period permitted to

remove migrated links that are not

cracked, be tied to the extent of bearing

migration. The FAA does not agree.

Bearing migration results from a failed

or undersized bearing race swage lip.

There is no data available to quantify

the rate of migration once the retention

feature is overcome. Once migration

begins, there is no data to indicate that

it will not progress until contact is made

with the boss of the turbine rear frame

clevis. Therefore, the analysis assumed

the worst case condition (i.e. maximum

migration) for calculating the reduction

in useful life. The 75-cycle allowance

for replacement of migrated, but not

cracked links, is considered

conservative, but reasonable.

Replacement of Aft Engine Mount Link

Assemblies

One comment requests that the FAA

change the requirement to replace aft

engine mount link assemblies with

improved aft engine mount link

assemblies by deleting the requirement

that link assemblies be replaced prior to

the engine accumulating 29,000 cycles

since new. The comment stated that link

assemblies are sometimes installed new

on engines that have already

accumulated a considerable number of

cycles and that the link assemblies are

inspected themselves. Therefore,

replacement of link assemblies should

not be tied to engine cycles. The FAA

does not agree. Links are expected to be

replaced ‘‘at the next engine shop visit.’’

However, since the current link

assemblies are not life-limited and not

routinely tracked, the 29,000 cycles

since new (CSN) limit was added as an

absolute limit. Operators may apply for

an Alternate Method of Compliance

(AMOC) for link assemblies installed on

engines that will exceed the 29,000 CSN

limit prior to their next scheduled

engine shop visit provided sufficient

records of link assembly CSN data are

available to show that the links will not

exceed 29,000 CSN.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Economic Analysis

There are approximately 975 engines

of the affected design in the worldwide

fleet. The FAA estimates that 323

engines installed on aircraft of US

registry will be affected by this AD. The

cost to replace link assemblies is

approximately $7,000. The FAA

estimates that it will take approximately

0.5 work hours per engine to

accomplish each of an average of two

interim inspections prior to next engine

shop visit and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the AD

on US operators is estimated to be

$2,280,380.

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:

2000–12–08 General Electric Company:

Amendment 39–11786. Docket 99–NE–

45–AD.

Applicability: General Electric Company

(GE) Models CF6–80C2A1/A2/A3/A5/A5F/

39538 Federal Register / Vol. 65, No. 124 / Tuesday, June 27, 2000 / Rules and Regulations

A8/D1F turbofan engines, with left hand aft

engine mount link assemblies, part numbers

(P/Ns) 9348M79G01 or 9348M79G02

installed, or right hand aft engine mount link

assemblies, P/Ns 9348M84G01 or

9348M84G02 installed. These engines are

installed on but not limited to Airbus

Industrie A300 and A310 series, and

McDonnell Douglas MD–11 series 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 (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 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 aft engine mount link failure,

which can result in adverse redistribution of

the aft engine mount loads and possible aft

engine mount system failure, accomplish the

following:

Initial Inspection

(a) Visually inspect aft engine mount link

assemblies for separations, cracks, and

spherical bearing race migration. as follows:

Not Previously Inspected

(1) Within 400 cycles-in-service (CIS) after

the effective date of this AD, if not previously

inspected using GE CF6–80C2 Alert Service

Bulletin (ASB) 72–A0964, Revision 2, dated

January 24, 2000, Revision 1, dated

November 12, 1999, or Original, dated April

16, 1999, OR

Previously Inspected

(2) Within 400 cycles-since-last-inspection

(CSLI), if previously inspected using GE

CF6–80C2 Alert Service Bulletin (ASB) 72–

A0964, Revision 2, dated January 24, 2000,

Revision 1, dated November 12, 1999, or

Original, dated April 16, 1999,

(3) Inspect in accordance with the

Accomplishment Instructions of GE CF6–

80C2 ASB 72–A0964, Revision 2, dated

January 24, 2000.

Cracked or Separated Parts

(4) If a crack or separation is discovered,

prior to further flight:

(i) Remove the cracked or separated aft

engine mount link assembly and the

attaching hardware from service; AND

(ii) Replace with serviceable parts.

Removal of Aft Engine Mount Link

Assemblies with Spherical Bearing Race

Migration

(5) If an aft engine mount link assembly is

found with spherical bearing race migration,

but no cracks or separations, prior to further

flight, EITHER:

(i) Remove the aft engine mount link

assembly and the attaching hardware from

service and replace with serviceable parts;

OR

Additional Borescope Inspection of Aft

Engine Mount Link Assemblies with

Spherical Bearing Race Migration

(ii) Perform an additional borescope

inspection for cracks in accordance with

paragraph (3)(I) of the Accomplishment

Instructions of GE CF6–80C2 ASB 72–A0964,

Revision 2, dated January 24, 2000.

After Additional Borescope Inspection, If

Parts Are Cracked

(6) If a crack indication is discovered, prior

to further flight, remove the cracked aft

engine mount link assembly and the

attaching hardware from service, and replace

with serviceable parts.

After Additional Borescope Inspection, If

Parts Are Not Cracked (Grace Period)

(7) If crack indications are not discovered,

within 75 CIS after the inspection performed

in accordance with paragraph (a)(5)(ii) of this

AD, remove the aft engine mount link

assembly from service, and replace with

serviceable parts.

Attaching Hardware

(8) Attaching hardware may be returned to

service after inspection in accordance with

paragraph 3(I)(1)(d) or 3(I)(2)(d) of GE CF6–

80C2 ASB 72–A0964, Revision 2, dated

January 24, 2000, as applicable, only if visual

inspection of the removed link shows no

cracks or separations.

Note 2: Link attaching hardware includes

the nuts, bolts and washers that secure the

link.

Repetitive Inspections

(b) Thereafter, perform the actions required

by paragraph (a) and associated

subparagraphs at intervals not to exceed 400

CSLI.

Replacement with Improved Link

Assemblies

(c) Replace aft engine mount link

assemblies with improved aft engine mount

link assemblies at the next engine shop visit

(ESV), or before accumulating 29,000 engine

cycles since new (CSN), whichever occurs

first.

(1) Replace in accordance with the

Accomplishment Instructions of CF6–80C2

ASB 72–A0989, dated January 19, 2000.

Left Hand Aft Engine Mount Link

Assemblies

(2) Replace left-hand aft engine mount link

assemblies, P/Ns 9348M79G01 or

9348M79G02, with improved left-hand aft

engine mount link assemblies, P/N

1846M23G01.

Right Hand Aft Engine Mount Link

Assemblies

(3) Replace right hand aft engine mount

link assemblies, P/Ns 9348M84G01 or

9348M84G02, with improved right hand aft

engine mount link assemblies, P/N

9348M84G03.

Terminating Action

(d) Installation of improved aft engine

mount link assemblies in accordance with

paragraph (c) and its subparagraphs

constitutes terminating action to the

inspections required by paragraphs (a) and

(b) of this AD.

Alternative Methods of Compliance

(e) 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. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

Ferry Flights

(f) 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 inspection requirements

of this AD can be accomplished.

Incorporation By Reference

(g) The inspection shall be done in

accordance with the following GE Alert

Service Bulletins: (ASBs) CF6–80C2 72–

A0964, Revision 2, dated January 24, 2000;

Revision 1, dated November 12, 1999;

Original, dated April 16, 1999 and CF6–80C2

72–A0989, dated January 19, 2000. 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 General

Electric Company via Lockheed Martin

Technology Services, 10525 Chester Road,

Suite C, Cincinnati, Ohio 45215, telephone

(513) 672–8400, fax (513) 672–8422. Copies

may be inspected 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.

Effective Date

(h) This amendment becomes effective on

August 28, 2000.

Issued in Burlington, Massachusetts, on

June 8, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–16200 Filed 6–26–00; 8:45 am]

BILLING CODE 4910–13–U