37922 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Proposed Rules

production can be increased by conditioning,

we may reduce the value of the production

after it has been conditioned by the cost of

conditioning but not lower than the value of

the production before conditioning. We may

obtain prices from any buyer of our choice.

If we obtain prices from one or more buyers

located outside your local market area, we

will reduce such prices by the additional

costs required to deliver the millet to those

buyers.

(iii) The value of the damaged or

conditioned production determined in

section 10(d)(4)ii) will be divided by the

local market price to determine the quality

adjustment factor;

(iv) The number of bushels remaining after

any reduction due to excessive moisture (the

moisture-adjusted gross bushel, if

appropriate) of the damaged or conditioned

production under section 10(d)(i) will then

be multiplied by the quality adjustment

factor from section 10(d)(4)(iii) to determine

the production to count.

(e) Any production harvested from plants

growing in the insured crop may be counted

as production of the insured crop on a weight

basis.

(f) If the insured crop is not swathed, the

amount of indemnity payable under section

10(b) will be reduced by 30 percent to reflect

those costs not incurred by you. If the

insured crop is swathed by not harvested, the

amount of indemnity payable under section

10(b) will be reduced by 15 percent to reflect

those costs incurred by you.

11. Late Planting

In lieu of the provisions contained in

section 16(a) of the Basic Provisions, the

production guarantee for each acre planted to

the insured crop during the late planting

period, unless otherwise specified in the

Special Provisions, will be reduced by:

(a) One percent for the first through the

tenth day; and

(b) Three percent for the eleventh through

the twentieth day.

12. Prevented Planting

Your prevented planting coverage will be

60 percent of your production guarantee for

timely planted acreage. If you have limited or

additional levels of coverage, as specified in

7 CFR part 400, subpart T, and pay an

additional premium, you may increase your

prevented planting coverage to a level

specified in the actuarial documents.

Signed in Washington, D.C., on June 5,

2000.

Kenneth D. Ackerman,

Manager, Federal Crop Insurance

Corporation.

[FR Doc. 00–15322 Filed 6–16–00; 8:45 am]

BILLING CODE 3410–08–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–376–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model DH.125, Model HS.125, Model

BH.125, Model BAe125 Series 800A

(Including Major Variants C–29A and

U1–25), Model Hawker 800, Model

Hawker 800XP, and Model Hawker 1000

Series Airplanes

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

certain Raytheon Model DH.125, Model

HS.125, Model BH.125, Model BAe.125

Series 800A, Model Hawker 800, Model

Hawker 800XP, and Model Hawker 1000

series airplanes. This proposal would

require leak checks and inspections for

corrosion of the pitot/static and stall

vent drain valves, and replacement of

certain components, if necessary. This

proposal is prompted by reports of

plugged or taped drain valves as well as

consequent corrosion of certain drain

valves. The actions specified by the

proposed AD are intended to prevent

erroneous altimeter and airspeed

indications due to plugged or taped

pitot/static and stall vent drain valves.

DATES: Comments must be received by

August 3, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

376–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays.

The service information referenced in

the proposed rule may be obtained from

Raytheon Aircraft Company, Manager

Service Engineering, Hawker Customer

Support Department, P. O. Box 85,

Wichita, Kansas 67201–0085. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Paul

DeVore, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Small Airplane Directorate,

Wichita, Kansas 672029; telephone

(316) 946–4142; fax (316) 946–4407.

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 shall

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 99–NM–376–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, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

99–NM–376–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

plugged or taped pitot/static and stall

vent drain valves. The reports indicate

that corrosion also was detected in some

valves. This condition, if not corrected,

could result in erroneous altimeter and

airspeed indications.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Aircraft Service Bulletin SB

34–3207, dated August 1999, which

describes procedures for performing

repetitive leak checks of the pitot/static

Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Proposed Rules 37923

and stall vent drain valves and

inspections for corrosion of the drain

valve system, and corrective actions,

such as replacement of certain

components of the drain valve system.

That service bulletin also references the

following two service bulletins as

additional sources of service

information.

Raytheon Aircraft Service Bulletin SB

34–3223, dated August 1999, describes

the application of a temporary seal for

the pitot/static and stall vent drain

valves.

Raytheon Aircraft Service Bulletin SB

34–3282, dated August 1999, describes

the installation of a new insert for the

pitot/static and stall vent drain valves

that will provide a positive seal of the

valves. If accomplished on all drain

valves, the modification would

eliminate the need for the repetitive leak

checks described in SB 34–3207.

Explanation of Requirements of

Proposed Rule

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 leak checks of the pitot/static

and stall vent drain valve systems and

corrective actions, if necessary. The

proposed AD would provide an optional

action to apply a temporary seal of the

drain valve for certain drain valves that

are operative but that are leaking. The

actions would be required to be

accomplished in accordance with the

service bulletins described previously.

The proposed AD also would provide an

optional terminating action for the

proposed repetitive inspections that

involves installing a new insert for the

drain valve system.

Cost Impact

There are approximately 900

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

585 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 4 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$140,400, or $240 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Should an operator accomplish the

optional modification to the drain valve

system, it would take approximately 1

work hour per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the optional modification is

estimated to be $60 per airplane.

Regulatory Impact

The regulations proposed herein

would 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 proposal

would not have federalism implications

under Executive Order 13132.

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:

Raytheon Aircraft Co. (Formerly Beech):

Docket 99–NM–376–AD.

Applicability: Model DH.125, Model

HS.125, Model BH.125, Model BAe.125,

Model Hawker 800, Model Hawker 800XP,

and Model Hawker 1000 series airplanes; as

listed in Raytheon Aircraft Service Bulletin

SB 34–3207, dated August 1999; excluding

those airplanes on which all pitot/static drain

vent valves have been modified with an

insert in accordance with Raytheon Aircraft

Repair Design Office instructions; certificated

in any category.

Note 1: This AD applies to each airplane

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

airplanes that have been otherwise 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 (f) 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 erroneous altimeter and

airspeed indications due to plugged or taped

pitot/static and stall vent drain valves,

accomplish the following:

Leak Tests

(a) Within 300 hours time-in-service after

the effective date of this AD: Drain the pitot/

static and stall vent drain valves, and

perform a leak test of the systems, in

accordance with Raytheon Aircraft Service

Bulletin SB 34–3207, dated August 1999. If

all drain valves are operating correctly and

the leak test is passed successfully,

thereafter, repeat the leak test at intervals not

to exceed 300 hours time-in-service.

Drain Valves Operative

(b) If all drain valves are operative, but any

valve does not pass the leak test required by

paragraph (a) of this AD: Prior to further

flight, accomplish the actions specified in

paragraph (b)(1), (b)(2), or (b)(3) of this AD.

(1) Apply a temporary seal of the drain

valve(s) in accordance with Raytheon

Aircraft Service Bulletin SB 34–3223, dated

August 1999. Within 300 hours time-inservice after the accomplishment of the

temporary seal, accomplish the requirements

of paragraphs (b)(2) or (b)(3) of this AD.

(2) Replace the drain valve components

with new or serviceable drain valve

components in accordance with Raytheon

Aircraft Service Bulletin SB 34–3207, dated

August 1999, and perform the leak test

specified in paragraph (a) of this AD.

Thereafter, repeat the requirements of

paragraph (a) of this AD at intervals not to

exceed 300 hours time-in-service.

(3) Modify the drain valves in accordance

with Raytheon Aircraft Service Bulletin SB

34–3282, dated August 1999. Thereafter,

repeat the requirements of paragraph (a) of

this AD at intervals not to exceed 300 hours

time-in-service unless all the drain valves

have been modified. Accomplishment of the

modification on ALL drain valves

consititutes terminating action for the

requirement to perform repetitive leak tests.

Drain Valves Inoperative

(c) If any drain valve is inoperative (e.g.,

plugged or taped), whether or not any leaking

is detected: Prior to further flight,

disassemble the valve and clean all

37924 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Proposed Rules

obstructions in accordance with Raytheon

Aircraft Service Bulletin SB 34–3207, dated

August 1999, and perform a general visual

inspection for corrosion of the drain valve.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or

droplight, and may require removal or

opening of access panels or doors. Stands,

ladders, or platforms may be required to gain

proximity to the area being checked.’’

(d) If no corrosion of the drain valves is

detected, prior to further flight, perform the

actions specified in either paragraph (d)(1) or

(d)(2) of this AD at the time specified.

(1) Perform the leak test specified in

paragraph (a) of this AD, and thereafter,

repeat the leak test requirements at intervals

not to exceed 300 hours time-in-service.

(2) Prior to further flight, modify any

inoperative valve in accordance with

Raytheon Aircraft Service Bulletin SB 34–

3282, dated August 1999. Thereafter, repeat

the leak test requirements of paragraph (a) of

this AD at intervals not to exceed 300 hours

time-in-service. Modification of ALL the

drain valves constitutes terminating action

for the requirement to perform repetitive leak

tests.

(e) If any drain valve is corroded, prior to

further flight: Inspect the connecting tubing

for corrosion and replace any corroded valve

or tubing with a new or serviceable valve or

tubing in accordance with Raytheon Aircraft

Service Bulletin SB 34–3207, dated August

1999. Accomplish the actions of paragraph

(e)(1) or (e)(2) of the AD at the time specified.

(1) Prior to further flight, perform the leak

test specified in paragraph (a) of this AD, and

thereafter, repeat the leak test requirements

of paragraph (a) of this AD at intervals not

to exceed 300 hours time-in-service.

(2) Prior to further flight, modify any

replaced drain valve in accordance with

Raytheon Aircraft Service Bulletin SB 34–

3282, dated August 1999. Thereafter, repeat

the leak test requirements of paragraph (a) of

this AD at intervals not to exceed 300 hours

time-in-service. Modification of ALL the

drain valves constitutes terminating action

for the requirement to perform repetitive leak

tests.

Alternative Methods of Compliance

(f) 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, Wichita

Aircraft Certification Office (ACO), ACE–

116W, FAA Small Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permit

(g) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on June 13,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15420 Filed 6–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–68–AD]

Airworthiness Directives; Eurocopter

Canada Ltd. Model BO 105 LS A–3

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to Eurocopter

Canada Ltd. Model BO 105 LS A–3

helicopters. That AD currently requires,

before further flight, creating a

component log card or equivalent

record, and determining the calendar

age and number of flights on each

tension-torsion (TT) strap, and

inspecting and removing, as necessary,

certain unairworthy TT straps. This

action would establish a life limit for

certain main rotor TT straps. This

proposal is prompted by an accident in

which a main rotor blade (blade)

separated from a Eurocopter

Deutschland GMBH (ECD) Model MBB–

BK 117 helicopter due to fatigue failure

of a TT strap. The same part-numbered

TT strap is used on the Model BO 105

LS A–3 helicopters. The actions

specified by this AD are intended to

prevent fatigue failure of a TT strap, loss

of a blade, and subsequent loss of

control of the helicopter.

DATES: Comments must be received on

or before August 18, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 99–SW–68–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. You may also

send comments electronically to the

Rules Docket at the following address:

9-asw-adcomments@faa.gov. Comments

may be inspected at the Office of the

Regional Counsel between 9 a.m. and 3

p.m., Monday through Friday, except

Federal holidays.

FOR FURTHER INFORMATION CONTACT:

Charles Harrison, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, Fort Worth,

Texas 76193–0110, telephone (817)

222–5128, fax (817) 222–5961

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 mailed

comments submitted in response to this

notice must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 99–SW–68–

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, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 99–SW–68–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

On October 4, 1999, the FAA issued

AD 99–20–13, Amendment 39–11371

(64 FR 56156, October 18, 1999),

applicable to Eurocopter Canada Ltd.

Model BO 105 LS A–3 helicopters. That

AD requires, before further flight,

creating a component log card or