Federal Register / Vol. 63, No. 94 / Friday, May 15, 1998 / Proposed Rules 27001

insignificant impact on the IdahoEastern Oregon onion industry.

This action would decrease the

assessment obligation imposed on

handlers. While assessments impose

some additional costs on handlers, the

costs are minimal and uniform on all

handlers. Some of the additional costs

may be passed on to producers.

However, these costs would be offset by

the benefits derived by the operation of

the order. In addition, the Committee’s

meeting was widely publicized

throughout the Idaho-Eastern Oregon

onion industry and all interested

persons were invited to attend the

meeting and participate in Committee

deliberations on all issues. Like all

Committee meetings, the April 2, 1998,

meeting was a public meeting and all

entities, both large and small, were able

to express views on this issue. Finally,

interested persons are invited to submit

information on the regulatory and

informational impacts of this action on

small businesses.

This proposed rule would impose no

additional reporting or recordkeeping

requirements on either small or large

onion handlers. As with all Federal

marketing order programs, reports and

forms are periodically reviewed to

reduce information requirements and

duplication by industry and public

sector agencies.

The Department has not identified

any relevant Federal rules that

duplicate, overlap, or conflict with this

rule.

A 15-day comment period is provided

to allow interested persons the

opportunity to respond to this request

for information and comments. Fifteen

days is deemed appropriate because: (1)

The Committee needs to have sufficient

funds to pay its expenses which are

incurred on a continuous basis; (2) the

1998–99 fiscal period begins on July 1,

1998, and the order requires that the

rate of assessment for each fiscal period

apply to all assessable onions handled

during such fiscal period; and (3)

handlers are aware of this action which

was recommended by the Committee at

a public meeting and is similar to other

assessment rate actions issued in past

years.

List of Subjects in 7 CFR Part 958

Marketing agreements, Onions,

Reporting and recordkeeping

requirements.

For the reasons set forth in the

preamble, 7 CFR part 958 is proposed to

be amended as follows:

PART 958—ONIONS GROWN IN

CERTAIN DESIGNATED COUNTIES IN

IDAHO, AND MALHEUR COUNTY,

OREGON

1. The authority citation for 7 CFR

part 958 continues to read as follows:

Authority: 7 U.S.C. 601–674.

2. Section 958.240 is proposed to be

revised to read as follows:

§ 958.240 Assessment rate.

On and after July 1, 1998, an

assessment rate of $0.09 per

hundredweight is established for IdahoEastern Oregon onions.

Dated: May 11, 1998.

Robert C. Keeney,

Deputy Administrator, Fruit and Vegetable

Programs.

[FR Doc. 98–13005 Filed 5–14–98; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–18–AD]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF6–6 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

General Electric Company (GE) CF6–6

series turbofan engines. This proposal

would require removal from service of

affected low pressure turbine (LPT)

stage 4 disks prior to reaching new,

reduced cyclic life limits, and

replacement with serviceable parts. This

proposal is prompted by reports of LPT

stage 4 disk cracking in the blade

dovetail slot bottom area. The actions

specified by the proposed AD are

intended to prevent LPT stage 4 disk

cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

DATES: Comments must be received by

June 15, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

18–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal 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 98–ANE–18–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–ANE–18–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports of low
27002 Federal Register / Vol. 63, No. 94 / Friday, May 15, 1998 / Proposed Rules

pressure turbine (LPT) stage 4 disk

cracking on General Electric Company

(GE) CF6–6 series turbofan engines. The

investigation revealed that the dovetail

slot bottoms of the LPT stage 4 disks,

part numbers (P/Ns) 9010M40P01,

9010M40P02, 9010M40P07,

9010M40P09, and 9010M40P12, have

higher than predicted levels of stress

during engine operation. In addition,

the low cycle fatigue (LCF) material

properties have been found to be lower

than the original design intent. The disk

cracks were found by inspection during

engine shop visits. Extensive material

testing, and stress and life analyses

revealed a minimum calculated LCF

cyclic life lower than the published LCF

cyclic retirement life for the stage 4 LPT

disks. This condition, if not corrected,

could result in LPT stage 4 disk

cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require removal from service of affected

LPT stage 4 disks prior to reaching new,

reduced cyclic life limits, and

replacement with serviceable parts .

There are approximately 257 engines

of the affected design in the worldwide

fleet. The FAA estimates that 242

engines installed on aircraft of U.S.

registry would be affected by this

proposed AD, and that required parts,

on a prorated basis, would cost

approximately $22,432 per engine.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $5,428,544.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

General Electric Company: Docket No. 98–

ANE–18–AD.

Applicability: General Electric Company

(GE) CF6–6 series turbofan engines, installed

on but not limited to McDonnell Douglas

DC–10–10 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 (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 low pressure turbine (LPT)

stage 4 disk cracking, which could result in

an uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) Remove from service LPT stage 4 disks,

part numbers (P/Ns) 9010M40P01,

9010M40P02, 9010M40P07, 9010M40P09,

and 9010M40P12, and replace with

serviceable parts, in accordance with the

following schedule:

(1) For disks with 12,300 or more cycles

since new (CSN) but less than 24,000 CSN on

the effective date of this AD, remove from

service affected disks at the earliest of the

following:

(i) The next piece-part exposure after the

effective date of this AD; or

(ii) The next engine shop visit after

accumulating 16,500 CSN; or

(iii) Within 4,200 cycles in service (CIS)

after the effective date of this AD; or

(iv) Prior to exceeding 24,000 CSN.

(2) For disks with 5,000 or more CSN, but

less than 12,300 CSN, on the effective date

of this AD, remove from service affected

disks at the earlier of the following:

(i) Prior to exceeding 16,500 CSN; or

(ii) Within 7,300 CIS after the effective date

of this AD.

(3) For disks with less than 5,000 CSN on

the effective date of this, remove from service

affected disks prior to exceeding 12,300 CSN.

(b) This AD establishes a new cyclic

retirement life limit for LPT stage 4 disks of

12,300 CSN. Thereafter, except as provided

in paragraph (d) of this AD, no alternative

cyclic retirement life limits may be approved

for LPT stage 4 disks.

(c) For the purpose of this AD, the

following definitions apply:

(1) An engine shop visit is defined as

separation of a major, static flange.

(2) Piece-part exposure is when the

affected part is completely disassembled in

accordance with the disassembly instructions

in the engine manual or section of the

Instructions for Continued Airworthiness

(ICA).

(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. 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 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.

Issued in Burlington, Massachusetts, on

May 7, 1998.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–12915 Filed 5–14–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–45–AD]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.