Federal Register / Vol. 60, No. 71 / Thursday, April 13, 1995 / Rules and Regulations 18729

amendments we are making to the rule

as a result of the comments.

Executive Order 12866 and Regulatory

Flexibility Act

This interim rule has been reviewed

under Executive Order 12866.

For this action, the Office of

Management and Budget has waived its

review process required by Executive

Order 12866.

There are approximately 31,200 cattle

herds in North Carolina. An estimated

95 percent of the herds are owned by

small businesses. Changing the status of

North Carolina may enhance the

marketability of cattle and bison from

the State, since some prospective cattle

and bison buyers prefer to buy cattle

and bison from accredited-free States.

This may result in some beneficial

economic impact on some small

entities. However, based on our

experience in similar designations of

other States, the impact should not be

significant.

Under these circumstances, the

Administrator of the Animal and Plant

Health Inspection Service has

determined that this action will not

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 12778

This rule has been reviewed under

Executive Order 12778, 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 document contains no

information collection or recordkeeping

requirements under the Paperwork

Reduction Act of 1980 (44 U.S.C. 3501

et seq.).

List of Subjects in 9 CFR Part 77

Animal diseases, Bison, Cattle,

Reporting and recordkeeping

requirements, Transportation,

Tuberculosis.

Accordingly, 9 CFR part 77 is

amended as follows:

PART 77—TUBERCULOSIS

1. The authority citation for part 77

continues to read as follows:

Authority: 21 U.S.C. 111, 114, 114a, 115–

117, 120, 121, 134b, and 134f; 7 CFR 2.17,

2.51, and 371.2(d).

§ 77.1 [Amended]

2. In § 77.1, in the definition for

Modified accredited state, paragraph (2)

is amended by removing ‘‘North

Carolina,’’.

3. In § 77.1, in the definition for

Accredited-free state, paragraph (2) is

amended by adding ‘‘North Carolina,’’

immediately after ‘‘New York,’’.

Done in Washington, DC, this 7th day of

April 1995.

Terry L. Medley,

Acting Administrator, Animal and Plant

Health Inspection Service.

[FR Doc. 95–9161 Filed 4–12–95; 8:45 am]

BILLING CODE 3410–34–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 90–ANE–25; Amendment 39–

9186; AD 91–10–03 R1]

Airworthiness Directives; General

Electric Company (GE) CF6–45 and

CF6–50 Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to General Electric Company

(GE) CF6–45 and CF6–50 series turbofan

engines, that currently requires

repetitive inspections of high pressure

compressor (HPC) rear shafts, and also

requires installation of a certain rear

shaft flange bolt configuration . This

amendment clarifies that engines with a

Parts Manufacturer Approval (PMA)

bolt part number (P/N) installed must

accomplish the inspection requirements

of the AD, and allow the installation of

the PMA bolt in lieu of the GE bolt. This

amendment is prompted by the

omission of the PMA bolt P/N from the

current AD requirements. The actions

specified by this AD are intended to

prevent an HPC rear shaft fracture,

which could result in an inflight engine

shutdown and an uncontained engine

failure.

DATES: Effective April 28, 1995.

The incorporation by reference of

certain publications listed in the

regulations was approved by the

Director of the Federal Register as of

June 17, 1991.

Comments for inclusion in the Rules

Docket must be received on or before

June 12, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

90–ANE–25, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from General

Electric Company, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief 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:

Robert Ganley, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7138,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: On March

18, 1991, the Federal Aviation

Administration (FAA) issued AD 91–

10–03, Amendment 39–6956 (56 FR

19920, May 1, 1991), applicable to

General Electric Company (GE) CF6–45

and CF6–50 series turbofan engines, to

require repetitive inspections of high

pressure compressor (HPC) rear shafts,

and installation of a certain rear shaft

flange bolt configuration. That action

was prompted by reports of 35 HPC rear

shafts found cracked in the bolt hole

area. That condition, if not corrected,

could result in an HPC rear shaft

fracture, which could result in an

inflight engine shutdown and an

uncontained engine failure.

Since the issuance of that AD, the

FAA has determined that Parts

Manufacturer Approval (PMA)

Production Approval Listing,

Supplement No. 27, authorizes the use

of Valley-Todeco (VT) bolt, Part Number

(P/N) VCD0016, in lieu of GE bolt, P/N

1375M69P01. Since VT bolt, P/N

VCD0016, and GE bolt, P/N

1375M69P01, are identical in design,

paragraphs (a)(1)(v), (a)(2), and (a)(2)(v)

of AD 91–10–03 should also apply to

HPC rear shafts that are installed with

VT bolt, P/N VCD0016.

The FAA has reviewed and approved

the technical contents of GE Service

Bulletin (SB) No. 72–958, Revision 1,

dated October 18, 1990, that describes
18730 Federal Register / Vol. 60, No. 71 / Thursday, April 13, 1995 / Rules and Regulations

procedures for inspection of HPC rear

shafts.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD revises AD 91–10–

03 to continue the inspection

requirements of the current AD, but

adds HPC rear shafts that are installed

with VT bolt, P/N VCD0016, to

paragraphs (a)(1)(v), (a)(2), and (a)(2)(v).

The actions are required to be

accomplished in accordance with the

service bulletin described previously.

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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 90–ANE–25.’’ The

postcard will be date stamped and

returned to the commenter.

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.

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, 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–6956 (56 FR

19920, May 1, 1991) and by adding a

new airworthiness directive,

Amendment 39–9186, to read as

follows:

91–10–03 R1 General Electric Company:

Amendment 39–9186. Docket 90–ANE–

25. Revises AD 91–10–03, Amendment

39–6956.

Applicability: General Electric Company

(GE) CF6–45 and CF6–50 series turbofan

engines installed on, but not limited to,

McDonnell Douglas DC–10 series, Boeing 747

series, and Airbus A300 series aircraft.

Note: 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 use the authority

provided in paragraph (e) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any engine from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a high pressure compressor

(HPC) rear shaft fracture, which could result

in an inflight engine shutdown and an

uncontained engine failure, accomplish the

following:

(a) Fluorescent penetrant inspect HPC rear

shafts, Part Numbers (P/N) 9127M58P03,

9079M63P12, 9079M63P15, 9079M63P16,

9079M63P17, 9079M63P18, and

9079M63P19, in accordance with the

Accomplishment Instructions of GE Service

Bulletin (SB) No. 72–958, Revision 1, dated

October 18, 1990, as follows:

(1) For HPC rear shafts currently installed

with hook bolts, P/N 9012M99G10,

9114M95G07, and 9114M95G10, inspect in

accordance with the following schedule:

(i) For shafts which have not been

previously inspected and have 10,000 cycles

since new (CSN) or greater on the effective

date of this airworthiness directive (AD),

inspect within the next 1,500 cycles in

service (CIS) after the effective date of this

AD.

(ii) For shafts which have not been

previously inspected and have less than

10,000 CSN on the effective date of this AD,

inspect within the next 2,500 CIS from the

effective date of this AD, or before

accumulating 7,500 CSN, whichever occurs

later. However, no shaft may exceed 11,500

CSN prior to inspection.

(iii) For shafts that have been previously

inspected and have 3,000 cycles since last

inspection (CSLI) or less on the effective date

of this AD, reinspect within 4,500 CSLI, or

before accumulating 7,500 CSN, whichever

occurs later.

(iv) For shafts that have been previously

inspected and have greater than 3,000 CSLI

on the effective date of this AD, reinspect

within the next 1,500 CIS from the effective

date of this AD, or before accumulating 7,500

CSN, whichever occurs later.

(v) Remove from service, HPC rear shaft

hook bolts identified in (a)(1) of this AD, after

any inspection performed in accordance with

paragraph (a)(1) of this AD, and replace with

new tapered turn-around bolts, P/N

1375M69P01 or VCD0016.

(2) For HPC rear shafts installed with turnaround bolts, P/N 9249M54P01, or tapered

turn-around bolts, P/N 1375M69P01 or
Federal Register / Vol. 60, No. 71 / Thursday, April 13, 1995 / Rules and Regulations 18731

VCD0016, inspect in accordance with the

following schedule:

(i) For shafts which have not been

previously inspected and have 6,500 CSN or

greater on the effective date of this AD,

inspect within the next 2,500 CIS after the

effective date of this AD.

(ii) For shafts which have not been

previously inspected and have less than

6,500 CSN on the effective date of this AD,

inspect prior to accumulating 9,000 CSN.

(iii) For shafts that have been previously

inspected and have 3,500 CSLI or less on the

effective date of this AD, reinspect within

6,000 CSLI, or before accumulating 9,000

CSN, whichever occurs later.

(iv) For shafts that have been previously

inspected and have greater than 3,500 CSLI

on the effective date of this AD, reinspect

within the next 2,500 CIS from the effective

date of this AD, or before accumulating 9,000

CSN, whichever occurs later.

(v) Remove from service, HPC rear shaft

turn-around bolts identified in paragraph

(a)(2) of this AD, after any inspection

performed in accordance with paragraph

(a)(2) of this AD, and replace with new

tapered turn-around bolts, P/N 1375M69P01

or VCD0016.

Note: Information concerning the tapered

turn-around bolt noted in paragraph (a) of

this AD can be found in GE SB No. 72–877.

(b) Remove from service, prior to further

flight, any shafts found cracked at inspection.

(c) Thereafter, for shafts which have been

inspected in accordance with paragraph (a) of

this AD, reinspect in accordance with the

Accomplishment Instructions of GE SB No.

72–958, Revision 1, dated October 18, 1990,

at intervals not to exceed 6,000 CSLI.

(d) Compliance with paragraph (a) of AD

91–10–03 satisfies the corresponding

requirements of paragraph (a) of this AD.

(e) An alternative method of compliance or

adjustment of the initial 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: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(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 requirements of this AD

can be accomplished.

(g) The actions required by this AD shall

be done in accordance with the following

service document:

Document No. Pages Revision Date

GE SB No. 72–958 ...................................................................................................................................... 1–2 1 ............. Oct. 18, 1990.

3–6 Original .. Aug. 15, 1990.

Total pages: 6.

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 as of June 17, 1991. Copies

may be obtained from General Electric

Company, Technical Publications

Department, 1 Neumann Way, Cincinnati,

OH 45215. Copies may be inspected at the

FAA, New England Region, Office of the

Assistant Chief 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.

(h) This amendment becomes effective on

April 28, 1995.

Issued in Burlington, Massachusetts, on

April 4, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–9133 Filed 4–11–95; 11:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Parts 771 and 779

[Docket No. 950407090–5090–01]

RIN 0694–AB18

Establishment of New General License

G–BETA for Exports of Certain Beta

Test Software

AGENCY: Bureau of Export

Administration, Commerce.

ACTION: Interim rule.

SUMMARY: This rule amends the Export

Administration Regulations (EAR) by

establishing a new General License G–

BETA for certain exports of beta test

software under the jurisdiction of the

Department of Commerce. Under the

provisions of this new General License,

beta test software programs may be

exported to all destinations except

Country Groups S and Z, Iran, Iraq,

Sudan, and Syria. Exporters are advised

that certain restrictions apply, and

should consult the EAR before using

General License G–BETA.

This new General License eligibility

will greatly reduce the number of

validated license applications for

certain software intended for massmarket distribution.

DATES: This rule is effective April 13,

1995. Comments must be received by

May 30, 1995.

ADDRESSES: Written comments (six

copies) should be sent to Nancy Crowe,

Bureau of Export Administration,

Department of Commerce, P.O. Box 273,

Washington, DC 20044.

FOR FURTHER INFORMATION CONTACT:

Nancy Crowe, Regulatory Policy

Division, Office of Exporter Services,

Bureau of Export Administration,

Telephone: (202) 482–2440.

SUPPLEMENTARY INFORMATION: This rule

amends Part 771 of the Export

Administration Regulations (EAR) by

establishing a new General License G–

BETA for certain exports of beta test

software. This change will allow

exports, under certain conditions, of

software controlled by the Department

of Commerce on the Commerce Control

List (Supplement No. 1 to Part 799.1 of

the EAR), and under Commerce

licensing jurisdiction, which would

otherwise require a validated license to

all destinations except Country Groups

S and Z, Iran, Iraq, Sudan, and Syria.

This rule will allow shipment under

General License G–BETA of beta test

software programs that: (a) Are intended

for export and reexport under the

provisions of the General Software Note

(Supplement No. 2 to Part 799.1 of the

EAR) after completion of testing; (b) are

provided free-of-charge or at a price that

does not exceed the cost of reproduction

and distribution; and (c) are designed

for user-installation. In addition, the

exporter must obtain a statement from

each testing consignee prior to shipment

certifying that the beta test software will

only be used for beta testing purposes,

and will not be rented, leased, sold,

sublicensed, assigned, or otherwise

transferred. Further, the statement must

certify that the testing consignee will

not transfer or export any product,

process, or service that is the direct

product of the beta test software.

Software shipped under General License

G–BETA must be destroyed abroad or

returned to the exporter within 30 days

of the end of the beta test period as

defined by the software producer or, if

the software producer does not define a

test period, within 30 days of

completion of the consignee’s role in the

test.

The following is a brief description of

the development of this rule. In the Fall