8196 Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules

§ 650.65 Appointment of a conservator.

(a) The Farm Credit Administration

Board may in its discretion appoint, ex

parte and without prior notice, a

conservator for the Corporation

provided that one or more of the

grounds for appointment as set forth in

§ 650.50 of this subpart exist;

(b) Upon the appointment of a

conservator, the Chairman of the Farm

Credit Administration shall

immediately notify the Corporation and

shall publish a notice of the

appointment in the Federal Register.

(c) As soon as practicable after the

conservator takes possession of the

Corporation, the conservator shall

notify, by first class mail, each holder of

stock in the Corporation of the

establishment of the conservatorship

and shall describe the effect of the

conservatorship on the Corporation’s

operations and equity holdings.

(d) Upon the issuance of the order

placing the Corporation in

conservatorship, all rights, privileges,

and powers of the members, board of

directors, officers, and employees of the

Corporation are vested exclusively in

the conservator.

(e) The Farm Credit Administration

Board may, at any time, terminate the

conservatorship and direct the

conservator to turn over the

Corporation’s operations to such

management as the Farm Credit

Administration Board may designate, in

which event the provisions of this

subpart shall no longer apply.

§ 650.66 Powers and duties of the

conservator.

(a) The conservator shall direct the

Corporation’s further operation until the

Farm Credit Administration Board

decides that the Corporation can operate

without the conservatorship or places

the Corporation into receivership. Upon

correction or resolution of the problem

or condition that provided the basis for

the appointment, the Farm Credit

Administration Board may turn the

Corporation over to such management

as the Farm Credit Administration

Board may direct.

(b) The conservator shall exercise all

powers necessary to continue the

ongoing operations of the Corporation,

to conserve and preserve the

Corporation’s assets and property, and

otherwise protect the interests of the

Corporation, its stockholders, and

creditors as provided in this subpart.

(c) The conservator serves as the

trustee of the Corporation and conducts

its operations for the benefit of the

creditors and stockholders of the

Corporation.

(d) The conservator may exercise the

powers that a receiver of the

Corporation may exercise under any of

the provisions of § 650.56(b) of this

subpart, except paragraphs (b)(2) and

(b)(16). In interpreting the applicable

paragraphs for purposes of this section,

the terms ‘‘conservator’’ and

‘‘conservatorship’’ shall be read for

‘‘receiver’’ and ‘‘receivership’’.

(e) The conservator may also take any

other action the conservator considers

appropriate or expedient to the

continuing operation of the Corporation.

§ 650.67 Inventory, examination, and

reports to stockholders.

(a) As soon as practicable after taking

possession of the Corporation, the

conservator shall take an inventory of

the assets and liabilities of the

Corporation as of the date possession

was taken. One copy of the inventory

shall be filed with the Farm Credit

Administration.

(b) The conservatorship shall be

examined by the Farm Credit

Administration in accordance with

section 8.11 of the Act.

(c) The conservatorship shall prepare

and file financial reports and other

documents in accordance with the

requirements of § 620.40 and part 621 of

this chapter. The conservator of the

Corporation shall provide the

certification required in § 621.14 of this

chapter.

§ 650.68 Final discharge and release of the

conservator.

At such time as the conservator shall

be relieved of its conservatorship duties,

the conservator shall file a report on the

conservator’s activities with the Farm

Credit Administration. The conservator

shall thereupon be completely and

finally released.

Dated: February 19, 1997.

Floyd Fithian,

Secretary, Farm Credit Administration Board.

[FR Doc. 97–4475 Filed 2–21–97; 8:45 am]

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–56–AD]

RIN 2120–AA64

Airworthiness Directives; I. A. M.

Rinaldo Piaggio Model P180 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 certain I. A. M.

Rinaldo Piaggio (Piaggio) Model P180

airplanes. The proposed action would

require repetitively inspecting for cracks

around the vertical pin and the torque

tube bottom flange of the rudder and the

fasteners that connect the torque tube to

the bottom flange. If cracks are evident,

the proposed action would require

modifying the rudder torque tube

bottom flange assembly by replacing the

cracked part with a part of improved

design which would terminate the

repetitive inspection. The proposed AD

is the result of several reports of fatigue

cracks around the pin that vertically

supports the rudder axle. The actions

specified by the proposed AD are

intended to prevent fatigue cracks in the

rudder torque tube bottom flange which

could result in loss of rudder control

and possible loss of the airplane.

DATES: Comments must be received on

or before April 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–56–

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 I. A.

M. Rinaldo Piaggio, S.p.A., Via Cibrario,

4 16154 Genoa, Italy. This information

also may be examined at the Rules

Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Tom Rodriguez, Program Officer,

Brussels Aircraft Certification Division,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

508.2715; facsimile (322) 230.6899; or

Mr. Roman T. Gabrys, Project Officer,

Small Airplane Directorate, Aircraft

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

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
Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules 8197

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–56–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–56–AD, Room

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

Missouri 64106.

Discussion

The Registro Aeronautico Italiano

(RAI), which is the airworthiness

authority for Italy, recently notified the

FAA that an unsafe condition may exist

on certain Piaggio P180 airplanes. The

RAI reports that fatigue cracks are

appearing in the area of the vertical pin

support and around the torque tube

bottom flange of the rudder. These

cracks were discovered during routine

inspections on high flight hour Piaggio

P180 airplanes. This condition, if not

detected and corrected, could result in

loss of rudder control and possible loss

of the airplane.

Relevant Service Information

Piaggio has issued Service Bulletin

80–0076, ORIGINAL ISSUE: May 30,

1995 which specifies procedures for

inspecting for cracks and modifying the

torque tube bottom flange and fasteners,

if cracks are found.

The RAI classified this service

bulletin as mandatory and issued AD

No. 95–183, Issued July 3, 1995, in order

to assure the continued airworthiness of

these airplanes in Italy.

The FAA’s Determination

This airplane model is manufactured

in Italy and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the RAI has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the RAI,

reviewed all available information

including the service information

referenced above, and determined that

AD action is necessary for products of

this type design that are certificated for

operation in the United States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Piaggio P180 airplanes

of the same type design registered in the

United States, the proposed AD would

require inspecting for cracks around the

torque tube bottom flange, the fasteners,

and vertical support pin of the rudder;

and, if cracks are found, modifying the

rudder torque tube bottom flange

assembly by replacing the cracked part

with a part of improved design. If no

cracks are found, the proposed action

would require repetitively inspecting

the area until cracks appear and then

modifying the rudder torque tube

bottom flange by replacing the cracked

part with a part of improved design.

Accomplishment of the proposed

modification would be in accordance

with Piaggio Service Bulletin 80–0076,

ORIGINAL ISSUE: May 30, 1995.

Differences Between the Proposed AD,

Service Bulletin, and RAI AD

I.A.M. Rinaldo Piaggio SB 80–0076,

Original Issue May 30, 1995, and the

RAI AD No. 95–183, dated July 3, 1995,

specify repetitively inspecting every 500

hours time-in-service (TIS) using a dye

penetrant method, and if the crack

lengths are greater than 6 mm, the part

must be replaced prior to further flight.

If the crack lengths are greater than 3

mm, but less than 6 mm, the part must

be replaced within the next 50 hours

TIS; and, if the cracks are less than 3

mm, then the parts must be replaced

within the next 100 hours TIS. The

proposed AD, if adopted, would not

allow any continued flight with any

crack found. FAA policy is to disallow

airplane operation when known cracks

exist in primary structure (the rudder is

considered primary structure).

Cost Impact

The FAA estimates that 4 airplanes in

the U.S. registry would be affected by

the proposed AD, that it would take

approximately 6 workhours per airplane

to accomplish the proposed initial

inspection and that the average labor

rate is approximately $60 an hour. Parts

are not accounted for in this cost

analysis because, on some airplanes,

cracks may never be discovered during

one of these inspections. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $1,440 ($360 per

airplane). The FAA is not taking into

account the cost for the repetitive

inspections because there is no way to

determine the number of repetitive

inspections that might be incurred over

the life of the airplane.

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:
8198 Federal Register / Vol. 62, No. 36 / Monday, February 24, 1997 / Proposed Rules

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:

I.A.M. Rinaldo Piaggio: Docket No. 96–CE–

56–AD.

Applicability: Model P180 airplanes (all

serial numbers), 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 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 within the next 100

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

date of this AD, and thereafter as indicated

in the body of this AD, unless already

accomplished.

To prevent fatigue cracks in the rudder

torque tube bottom flange which could result

in loss of rudder control and possible loss of

the airplane, accomplish the following:

(a) Inspect the area around the torque tube,

bottom flange, and vertical support pin of the

rudder for cracks (using a dye penetrant

method) and visually inspect for cracks in

the fasteners that connect the torque tube to

the bottom flange.

Note 2: The inspection in Part A of the

Compliance section of Piaggio Service

Bulletin (SB) 80–0076, ORIGINAL ISSUE:

May 30, 1995, uses different criteria than the

inspection required in paragraph (a) of this

AD. This AD takes precedence over Piaggio

SB 80–0076.

(b) If cracks are found, prior to further

flight, modify the rudder torque tube bottom

flange by replacing any cracked part with a

part of improved design in accordance with

Part B and Attachment #1 of the

ACCOMPLISHMENT INSTRUCTIONS of

Piaggio SB 80–0076, ORIGINAL ISSUE: May

30, 1995.

(c) If no cracks are found, continue to

inspect at intervals not to exceed 100 hours

TIS thereafter until cracks appear. If cracks

appear during any inspection required by

this AD, prior to further flight, modify the

rudder torque tube bottom flange by the

replacing cracked part with a part of

improved design in accordance with Part B

and Attachment #1 of the

ACCOMPLISHMENT INSTRUCTIONS of

Piaggio SB 80–0076, ORIGINAL ISSUE: May

30, 1995.

(d) Modifying the rudder torque tube flange

by replacing a cracked torque tube bottom

flange, part number (P/N) 80–373108–103,

with an improved torque tube bottom flange

(P/N 80–373201–001) is considered a

terminating action for the repetitive

inspections required in paragraph (c) of this

AD.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Brussels Aircraft Certification

Division, FAA, Europe, Africa, and Middle

East Office, c/o American Embassy, B–1000

Brussels, Belgium; or the Manager, Small

Airplane Directorate, Aircraft Certification

Service, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels Aircraft Certification Division or

Manager, Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Division or the Small Airplane

Directorate.

(g) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to I. A. M. Rinaldo

Piaggio, S.p.A., Via Cibrario, 4 16154 Genoa,

Italy; or may examine these documents 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

February 14, 1997.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–4371 Filed 2–21–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 97–ANE–08]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D–200 Series Turbofan

Engines

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 Pratt &

Whitney JT8D–200 series turbofan

engines, that currently requires for front

compressor front hubs (fan hubs),

cleaning; initial and repetitive eddy

current (ECI) and fluorescent penetrant

inspections (FPI) of tierod and

counterweight holes for cracks; removal

of bushings; the cleaning and ECI and

FPI of bushed holes for cracks; and, if

necessary, replacement with serviceable

parts. In addition, the current AD

requires reporting the findings of

cracked fan hubs. This action will not

change the current AD’s inspection

procedures, or the effectivity date that

starts the cycle count for the initial

inspection schedules. This AD will,

however, add an additional inspection

schedule that requires the initial

inspection of certain fan hubs with

standard drilled holes and coolant

channel drilled (CCD) holes to occur

earlier than the existing AD requires.

This proposal is prompted by additional

investigation since publication of the

current AD that reveals that certain fan

hubs with standard drilled holes and

CCD holes may be more susceptible to

cracking. This proposal also requires

reporting the results of the initial fan

hub inspections. The actions specified

by the proposed AD are intended to

prevent fan hub failure due to tierod,

counterweight, or bushed hole cracking,

which could result in an uncontained

engine failure and damage to the

aircraft.

DATES: Comments must be received by

April 25, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal

Aviation Administration (FAA), New

England Region, Office of the Assistant

Chief Counsel, Attention: Rules Docket

No. 97–ANE–08, 12 New England

Executive Park, Burlington, MA 01803-

–5299. Comments may also be sent via

the Internet using the following address:

‘‘9-ad-engineprop@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.

The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860)

565–6600, fax (860) 565–4503. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Diane Cook, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–