Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Rules and Regulations 14287

intact, and provide sufficient care for,

representative samples of the crop in

locations acceptable to us (The amount of

production to count for such acreage will be

based on the harvested production or

appraisals from the samples at the time

harvest should have occurred. If you do not

leave the required samples intact, or fail to

provide sufficient care for the samples, our

appraisal made prior to giving you consent to

put the acreage to another use will be used

to determine the amount of production to

count); or

(B) You elect to continue to care for the

crop, the amount of production to count for

the acreage will be the harvested production,

or our reappraisal if additional damage

occurs and the crop is not harvested; and

(2) All harvested production from the

insurable acreage.

(d) When forage is harvested as other than

air-dry forage, the production to count will

be adjusted to the equivalent of air-dry

forage.

(e) Any harvested production from plants

growing in the forage will be counted as

forage on a weight basis.

(f) In addition to the provisions of section

15 (Production Included in Determining

Indemnities) of the Basic Provisions (§ 457.8),

we may determine the amount of production

of any unharvested forage on the basis of our

field appraisals conducted after the normal

time for each cutting for the area.

12. Written Agreements.

Designated terms of this policy may be

altered by written agreement in accordance

with the following:

(a) You must apply in writing for each

written agreement no later than the sales

closing date, except as provided in section

12(e);

(b) The application for a written agreement

must contain all variable terms of the

contract between you and us that will be in

effect if the written agreement is not

approved;

(c) If approved, the written agreement will

include all variable terms of the contract,

including, but not limited to, crop type or

variety, the guarantee, premium rate, and

price election;

(d) Each written agreement will only be

valid for one year (If the written agreement

is not specifically renewed the following

year, insurance coverage for subsequent crop

years will be in accordance with the printed

policy); and

(e) An application for a written agreement

submitted after the sales closing date may be

approved if, after a physical inspection of the

acreage, it is determined that no loss has

occurred and the crop is insurable in

accordance with the policy and written

agreement provisions.

* * * * *

§ 457.127 Forage Production Winter

Coverage Endorsement.

The provisions of the Forage

Production Winter Coverage

Endorsement for the 1998 and

succeeding crop years are as follows:

Department of Agriculture

Federal Crop Insurance Corporation

Forage Production Winter Coverage

Endorsement

In return for payment of the additional

premium designated in the actuarial table,

the Common Crop Insurance Policy Basic

Provisions (§ 457.8) and the Forage

Production Crop Insurance Provisions

(§ 457.117) are amended to incorporate the

following terms and conditions:

(a) For this Endorsement to be effective,

you must have the Common Crop Insurance

Policy Basic Provisions (§ 457.8) and the

Forage Production Crop Insurance Provisions

(§ 457.117) in force and you must comply

with all terms and conditions contained

therein.

(b) This Endorsement is not available for

forage crops insured under a Catastrophic

Risk Protection Endorsement.

(c) You must elect this Endorsement on

your application or on a form approved by

us, for coverage under this Endorsement, on

or before the sales closing date specified in

the Special Provisions for the crop year in

which you wish to insure your forage under

this Endorsement.

(d) This Endorsement is available for the

following acreage in all counties for which

the actuarial table designates forage

production premium rates:

(1) Fall planted acreage, for the first and

subsequent crop years following the year of

establishment; and

(2) Spring planted acreage, for the second

and subsequent crop years following the year

of establishment.

(e) Under this Endorsement, the insurance

period will be as follows:

(1) Insurance will attach on acreage with

an adequate stand on the later of the date we

accept your application or the applicable

calendar dates following the end of the

insurance period for the previous crop year

as listed below:

(i) For all states except California—October

16;

(ii) For California—January 1;

(2) Insurance will end on the earliest of:

(i) Total destruction of the forage crop;

(ii) Removal from the windrow or the field

for each cutting;

(iii) Final adjustment of the loss;

(iv) Abandonment of the forage crop;

(v) The date grazing commences on the

forage crop; or

(vi) The following dates of the crop year:

(A) All states except California—October

15;

(B) California—December 31.

(f) This is a continuous Endorsement and

it will remain in effect for as long as your

forage production policy remains in effect or

you cancel this coverage in accordance with

paragraph (g).

(g) This Endorsement may be canceled by

either you or us for any succeeding crop year

by giving written notice on or before the

cancellation date preceding the crop year for

which the cancellation of this Endorsement

is to be effective.

Signed in Washington, D.C., on March 19,

1997.

Kenneth D. Ackerman,

Manager, Federal Crop Insurance

Corporation.

[FR Doc. 97–7655 Filed 3–25–97; 8:45 am]

BILLING CODE 3410–FA–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–41; Amendment 39–

9972; AD 97–06–15]

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 high pressure

compressor (HPC) stage 1 rotor disks.

This amendment is prompted by an

updated stress and life analysis. The

actions specified by this AD are

intended to prevent HPC stage 1 rotor

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 December 18, 1995, (60 FR

65035). That action proposed to reduce

the allowable operating cyclic life limit

for affected high pressure compressor

(HPC) stage 1 rotor 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.
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