Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Proposed Rules 14359

section. A priority rating will be

assigned to each preapplication.

Preapplications selected for funding

will be based on the priority rating

assigned each preapplication and the

total funds available. All

preapplications submitted for funding

should contain sufficient information to

permit RBS to complete a thorough

priority rating.

§ 4284.541 Grant approval, fund

obligation, grant closing, and third-party

financial assistance.

The grantee will execute all

documents required by RBS to make a

grant under this subpart.

§§ 4284.542–4284.556 [Reserved].

§ 4284.557 Fund disbursement.

Grants will be disbursed as follows:

(a) A ‘‘Request for Advance or

Reimbursement’’ will be completed by

the applicant and submitted to Rural

Development not more frequently than

monthly. Payments will be made by

electronic funds transfer pursuant to the

Debt Collection Improvement Act of

1996 (Pub. L. 104–134).

(b) The grantee’s share in the cost of

the project will be disbursed in advance

of grant funds or on a pro-rata

distribution basis with grant funds

during the disbursement period. The

grantee may not provide its contribution

at the end of the grant period.

§ 4284.558 Reporting.

A ‘‘Financial Status Report’’ and a

project performance activity report will

be required of all grantees on a quarterly

calendar basis. A final project

performance report will be required

with the last Financial Status Report.

The final report may serve as the last

quarterly report. The final report must

include a final evaluation of the project.

Grantees must constantly monitor

performance to ensure that time

schedules are being met, projected work

by time periods is being accomplished,

and other performance objectives are

being achieved. Grantees are to submit

an original of each report to Rural

Development. The project performance

reports shall include, but not be limited

to, the following:

(a) A comparison of actual

accomplishments to the objectives

established for that period;

(b) Reasons why established

objectives (if any) were not met;

(c) Problems, delays, or adverse

conditions which will affect attainment

of overall project objectives, prevent

meeting time schedules or objectives, or

preclude the attainment of particular

project work elements during

established time periods. This

disclosure shall be accompanied by a

statement of the action taken or planned

to resolve the situation; and

(d) Objectives and timetable

established for the next reporting

period.

§§ 4284.559—4284.570 [Reserved]

§ 4284.571 Audit requirements.

The grantee will provide an audit

report in accordance with § 1942.17 of

this title. Audits must be prepared in

accordance with general accounting

principles and standards using the

publication, ‘‘Standards for Audit of

Governmental Organizations, Programs,

Activities and Functions.’’

§ 4284.572 Grant servicing.

Grants will be serviced in accordance

with part 1951, subpart E of this title.

§ 4284.573 Programmatic changes.

The grantee shall obtain prior

approval for any change to the scope or

objectives of the approved project.

Failure to obtain prior approval of

changes to the scope or budget can

result in suspension or termination of

grant funds.

§ 4284.574 Subsequent grants.

Subsequent grants will be processed

in accordance with the requirements set

forth in this subpart. Cooperative

development projects receiving

assistance under this program will be

evaluated one year after assistance is

received. If it is determined to be in the

best interests of the program, preference

may be given to a project or projects for

an additional grant in the immediately

succeeding year.

§ 4284.575 Grant suspension, termination,

and cancellation.

Grants may be canceled by RBS by

written notice. Grants may be

suspended or terminated for cause or

convenience in accordance with 7 CFR

parts 3015 and 3019, as applicable.

§§ 4284.576—4284.586 [Reserved]

§ 4284.587 Exception authority.

The Administrator may, in individual

cases, make an exception to any

requirement or provision of this subpart

if the Administrator determines that

application of the requirement or

provision would adversely affect U.S.

Department of Agriculture interest.

§§ 4284.588—4284.599 [Reserved]

§ 4284.600 OMB control number.

The information collection

requirements contained in this

regulation have been approved by the

Office of Management and Budget

(OMB) and have been assigned OMB

control number 0575–0006. You are not

required to respond to this collection of

information unless it displays a valid

OMB control number.

Dated: March 17, 1997.

Jill Long Thompson,

Under Secretary, Rural Development.

[FR Doc. 97–7743 Filed 3–25–97; 8:45 am]

BILLING CODE 3410–XY–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–51–AD]

RIN 2120–AA64

Airworthiness Directives; Mooney

Aircraft Corporation Models M20F,

M20J, and M20L Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to Mooney

Aircraft Corporation (Mooney) Models

M20F, M20J, and M20L airplanes. The

proposed action would require

removing the fuel cap retaining lanyard

from the fuel filler cap assemblies. A

report of lost engine power during flight

because of fuel starvation prompted the

proposed action. The investigation

revealed that the airplane fuel float

became trapped by the fuel cap

retaining lanyard, keeping the float from

following the fuel level. This condition

caused the pilot to get a false fuel

quantity reading. The actions specified

by the proposed AD are intended to

prevent loss of engine power and fuel

depletion during flight caused by a false

fuel gauge reading.

DATES: Comments must be received on

or before May 30, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–51–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Mooney Aircraft Corporation, Louis

Schreiner Field, Kerrville, Texas 78028.

This information also may be examined

at the Rules Docket at the address above.
14360 Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Proposed Rules

FOR FURTHER INFORMATION CONTACT: Ms.

Alma Ramirez-Hodge, Aerospace

Engineer, FAA, Fort Worth Airplane

Certification Office, 2601 Meacham

Boulevard, Fort Worth, Texas 76193–

0150; telephone (817) 222–5147;

facsimile (817) 222–5960.

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 that

summarizes 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 No. 96–CE–51–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, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–51–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Events Leading to the Proposed Action

The FAA received a report of an

incident where a Mooney Model M20J

airplane lost engine power during flight

because of fuel starvation. The pilot

noted that the fuel gauge indicated the

tank was half full before the engine quit.

The pilot switched fuel tanks, re-started

the engine, and the airplane landed

without further incident. Subsequent

investigation of the incident revealed

that after fueling the airplane, the fuel

cap retaining lanyard trapped the

outboard float, preventing the float from

following the fuel level downward. As

a result, the fuel gauge showed the tank

as half full of fuel when the tank was

actually empty. The fuel cap lanyard

and tank float design is the same for all

Mooney Models M20F, M20J, and M20L

airplanes.

Related Service Information

Mooney Aircraft has issued service

bulletin M20–259, Issue Date:

September 1, 1996, which specifies

removing the lanyard from the fuel cap

assembly.

Explanation of the Provisions of the

Proposed Action

After examining the circumstances

and reviewing all available information

related to the incident described above,

the FAA has determined that AD action

should be taken to prevent loss of

engine power and fuel depletion during

flight caused by a false fuel gauge

reading.

Since an unsafe condition has been

identified that is likely to exist or

develop in other Mooney Models M20F,

M20J, and M20L airplanes of the same

type design, the proposed AD would

require removing the lanyard (nylon

type material) from the fuel cap

assembly.

Cost Impact

The FAA estimates that 2,526

airplanes in the U.S. registry would be

affected by the proposed AD, that it

would take approximately 1 workhour

per airplane to accomplish the proposed

action, and that the average labor rate is

approximately $60 an hour. There are

no parts to include in this cost estimate.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $151,560 or

$60 per airplane. The FAA has no way

to determine how many owners/

operators have accomplished this

action, and would assume that no

operator has accomplished this action.

Regulatory Impact

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 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) 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 has been placed 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

Mooney Aircraft Corporation: Docket No.

96–CE–51–AD.

Applicability: The following Models and

serial numbered airplanes, certificated in any

category.

Models Serial numbers

M20F ........... All serial numbers.

M20J ........... 24–0001 through 24–3381.

M20L ........... 26–0001 through 26–0041.

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 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 (c) 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.
Federal Register / Vol. 62, No. 58 / Wednesday, March 26, 1997 / Proposed Rules 14361

Compliance: Required within the next 50

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent loss of engine power and fuel

depletion during flight caused by a false fuel

gauge reading, accomplish the following:

(a) Remove the lanyard (nylon type

material) from the left-hand (LH) and righthand (RH) fuel filler cap assembly in

accordance with the INSTRUCTIONS section

of Mooney Aircraft Corporation Service

Bulletin M20–259, Issue Date: September 1,

1996.

(b) 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 airplane to

a location where the requirements of this AD

can be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Fort Worth

Airplane Certification Office, 2601 Meacham

Boulevard, Fort Worth, Texas 76193–0150.

The request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Fort Worth Airplane

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth Airplane

Certification Office.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to Mooney Aircraft

Corporation, Louis Schreiner Field, Kerrville,

Texas, 78028; or may examine this document

at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on March

20, 1997.

Larry E. Werth,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–7679 Filed 3–25–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–182–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A300–600 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 Airbus Industrie Model A300–

600 series airplanes. This proposal

would require repetitive eddy current

inspections to detect cracks of the outer

skin of the fuselage at certain frames,

and repair or reinforcement of the

structure at the frames, if necessary.

This proposal also would require

eventual reinforcement of the structure

at certain frames, which, when

accomplished, terminates the repetitive

inspections. This proposal is prompted

by a report indicating that fatigue cracks

were found in the area of certain frames.

The actions specified by the proposed

AD are intended to prevent such fatigue

cracking, which could reduce the

structural integrity of the airframe and

result in rapid decompression of the

airplane.

DATES: Comments must be received by

May 5, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

182–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 96–NM–182–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–103, Attention: Rules Docket No.

96–NM–182–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Generale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on certain Model

A300–600 series airplanes. The DGAC

advises that, during inspection of inservice Model A300 series airplanes,

fatigue cracks were found after 18,000

flight cycles in the area of frames 28A

and 30A, at left and right-hand stringer

30. Fatigue cracking in this area of the

fuselage could reduce the structural

integrity of the airframe and result in

rapid decompression of the airplane.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A300–53–6045, dated March 21, 1995,

as revised by Change Notice No. O.A.,

dated June 1, 1995, which describes

procedures for repetitive eddy current

inspections to detect cracks of the outer

skin of the fuselage at frames 28A and

30A above stringer 30, and repair or

reinforcement of the structure of the

frames, if necessary.

Airbus also has issued Service

Bulletin A300–53–6037, dated March

21, 1995, which describes procedures

for reinforcement of the structure at

frames 28 and 29, and frames 30 and 31,

between stringers 29 and 30.

Accomplishment of the reinforcement

will limit the risk of cracking in these

areas. Such reinforcement eliminates

the need for the repetitive inspections.

The DGAC classified Airbus Service

Bulletin A300–53–6045 as mandatory

and issued French airworthiness

directive (C/N) 95–244–191(B), dated

December 6, 1995, in order to assure the

continued airworthiness of these

airplanes in France. The DGAC