15094 Federal Register / Vol. 62, No. 61 / Monday, March 31, 1997 / Rules and Regulations

days following the end of any

subsequent quarter at which the

institution’s permanent capital ratio

decreases by one half of 1 percent or

more from the level reported in the

notice.

Subpart E—Association Annual

Meeting Information Statement

9. Section 620.20 is amended by

removing paragraph (c) and revising

paragraph (b) to read as follows:

§ 620.20 Preparing and distributing the

information statement.

* * * * *

(b) The statement shall incorporate by

reference the annual report to

shareholders required by subpart B of

this part and contain the information

specified in § 620.21 and such other

material information as is necessary to

make the required statement, in light of

the circumstances under which it is

made, not misleading.

PART 630—DISCLOSURE TO

INVESTORS IN SYSTEMWIDE AND

CONSOLIDATED BANK DEBT

OBLIGATIONS OF THE FARM CREDIT

SYSTEM

10. The authority citation for part 630

is revised to read as follows:

Authority: Secs. 5.17, 5.19 of the Farm

Credit Act (12 U.S.C. 2252, 2254).

Subpart A—General

11. Section 630.3 is amended by

redesignating existing paragraphs (f) and

(g) as new paragraphs (g) and (h),

respectively, and adding new paragraph

(f) to read as follows:

§ 630.3 Publishing and filing the report to

investors.

* * * * *

(f) Information in documents prepared

for investors in connection with the

offering of debt securities issued

through the Federal Farm Credit Banks

Funding Corporation may be

incorporated by reference in the annual

and quarterly reports in answer or

partial answer to any item required in

the reports under this part. A complete

description of any offering documents

incorporated by reference must be

clearly identified in the report (e.g.,

Federal Farm Credit Banks

Consolidated Systemwide Bonds and

Discount Notes—Offering Circular

issued on [insert date]). Offering

documents incorporated by reference in

either an annual or quarterly report

prepared under this part must be filed

with the Chief Examiner, Farm Credit

Administration, McLean, Virginia

22102–5090, either prior to or at the

time of submission of the report under

paragraph (h) of this section. Any

offering document incorporated by

reference is subject to the delivery and

availability requirements set forth in

§ 630.4(a) (5) and (6).

* * * * *

Dated: March 20, 1997.

Jeanette Brinkley,

Acting Secretary, Farm Credit Administration

Board.

[FR Doc. 97–8000 Filed 3–28–97; 8:45 am]

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–34; Amendment 39–

9956; AD 97–05–12]

RIN 2120–AA64

Airworthiness Directives; General

Electric Aircraft Engines CT7 Series

Turboprop Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to General Electric Aircraft

Engines (GE) CT7 series turboprop

engines. This action requires eddy

current inspection of disk holes of stage

1 and 2 gas generator turbine (GGT)

disks for cracks, and, if necessary,

replacement with serviceable parts. This

amendment is prompted by a report of

a stage 2 GGT disk failure. The actions

specified in this AD are intended to

prevent a stage 1 or 2 GGT disk failure,

which could result in an uncontained

engine failure and damage to the

aircraft.

DATES: Effective April 15, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 15,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

May 30, 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.

96-ANE–34, 12 New England Executive

Park, Burlington, MA 01803-5299.

The service information referenced in

this AD may be obtained from GE

Aircraft Engines, 1000 Western Ave.,

Lynn, MA 01910; telephone (617) 594–

3140, fax (617) 594–4805. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dave Keenan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7139,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received a report of a General

Electric Aircraft Engines (GE) CT7 series

turboprop engine, installed on a SAABSCANIA SF340 aircraft, that

experienced an uncontained stage 2 gas

generator turbine (GGT) failure during

takeoff. The investigation revealed that

the failure was caused by a crack in a

disk cooling hole. The most likely cause

of the cracking was machining damage

to the disk cooling hole during

manufacturing. This condition, if not

corrected, could result in a stage 1 or 2

GGT disk failure, which could result in

an uncontained engine failure and

damage to the aircraft.

The FAA has reviewed and approved

the technical contents of GE (CT7-TP

Series) Alert Service Bulletin (SB) A72–

393, dated November 26, 1996, that lists

by serial number (S/N) affected stage 1

and 2 GGT disks, and (CT7-TP Series)

SB 72–390, Revision 1, dated December

11, 1996, that describes the procedures

for eddy current inspection (ECI) of disk

holes for cracks.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

prevent stage 1 or 2 GGT disk failure,

which could result in an uncontained

engine failure and damage to the

aircraft. This AD requires a one-time ECI

for cracks of disk holes of stage 1 and

2 GGT disks, and, if necessary,

replacement with serviceable parts. The

inspection compliance time is at the

next GGT module removal, or 9 months

after the effective date of this AD,

whichever occurs first. The actions are

required to be accomplished in

accordance with the SBs described

previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good
Federal Register / Vol. 62, No. 61 / Monday, March 31, 1997 / Rules and Regulations 15095

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 AD

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-ANE–34.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–05–12 General Electric Aircraft Engines:

Amendment 39–9956. Docket 96–ANE–

34.

Applicability: General Electric Aircraft

Engines (GE) Models CT7–5A2, –7A, –9B,

–9C turboprop engines, installed on but not

limited to Construcciones Aeronauticas, SA

(CASA) CN–235 series and SAAB-SCANIA

SF340 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 (l)

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 a stage 1 or 2 gas generator

turbine (GGT) disk failure, which could

result in an uncontained engine failure and

damage to the aircraft, accomplish the

following:

(a) For all stage 1 GGT disks, Part Number

(P/N) 6064T06P01, identified in Table 1 of

GE (CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

7,000 or more cycles since new (CSN) on the

effective date of this AD, perform a one time

eddy current inspection (ECI) for cracks in

accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, or not to

exceed 9 months after the effective date of

this AD, whichever occurs first.

(b) For all stage 1 GGT disks, P/N

6064T06P01, identified in Table 1 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

less than 7,000 CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7-TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, but not to

exceed 9,000 CSN.

(c) For all stage 1 GGT disks, P/N

6064T06P01, identified in Table 2 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

10,000 or more CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, or not to

exceed 9 months after the effective date of

this AD, whichever occurs first.

(d) For all stage 1 GGT disks, P/N

6064T06P01, identified in Table 2 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

less than 10,000 CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, but not to

exceed 12,000 CSN.

(e) For all stage 2 GGT disks, P/N

6064T12P01, identified in Table 3 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

7,000 or more CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, or not to

exceed 9 months after the effective date of

this AD, whichever occurs first.

(f) For all stage 2 GGT disks, P/N

6064T12P01, identified in Table 3 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

less than 7,000 CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, but not to

exceed 9,000 CSN.

(g) For all stage 2 GGT disks, P/N

6064T12P01, identified in Table 4 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

10,000 or more CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–
15096 Federal Register / Vol. 62, No. 61 / Monday, March 31, 1997 / Rules and Regulations

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, or not to

exceed 9 months after the effective date of

this AD, whichever occurs first.

(h) For all stage 2 GGT disks, P/N

6064T12P01, identified in Table 4 of GE

(CT7–TP Series) SB A72–393, dated

November 26, 1996, that have accumulated

less than 10,000 CSN on the effective date of

this AD, perform a one time ECI for cracks

in accordance with the Accomplishment

Instructions of GE (CT7–TP Series) SB 72–

390, Revision 1, dated December 11, 1996, at

the next GGT module removal, but not to

exceed 12,000 CSN.

(i) For all stage 1 GGT disks, P/N

6064T06P01, and all stage 2 GGT disks, P/N

6064T12P01, not identified in Tables 1

through 4 of GE (CT7–TP Series) SB A72–

393, dated November 26, 1996, that have

accumulated 7,000 or more CSN on the

effective date of this AD, perform a one time

ECI for cracks in accordance with the

Accomplishment Instructions of GE (CT7–TP

Series) SB 72–390, Revision 1, dated

December 11, 1996, at the next GGT module

removal, or not to exceed 9 months after the

effective date of this AD, whichever occurs

first.

(j) For all stage 1 GGT disks, P/N

6064T06P01, and all stage 2 GGT disks, P/N

6064T12P01, not identified in Tables 1

through 4 of GE (CT7–TP Series) SB A72–

393, dated November 26, 1996, that have

accumulated less than 7,000 CSN on the

effective date of this AD, perform a one time

ECI for cracks in accordance with the

Accomplishment Instructions of GE (CT7–TP

Series) SB 72–390, Revision 1, dated

December 11, 1996, at the next GGT module

removal, but not to exceed 9,000 CSN.

(k) Prior to further flight, remove from

service cracked disks, and replace with

serviceable parts.

(l) 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.

(m) 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.

(n) The actions required by this AD shall

be done in accordance with the following GE

(CT7–TP Series) SBs:

Document No. Pages Revision Date

A72–393 ................................................. 1–16 Original ................................................. November 26, 1996.

Total ................................................ 16

72–390 ................................................... 1–6 1 ........................................................... December 11, 1996.

Total ................................................ 6

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from GE Aircraft Engines, 1000 Western Ave.,

Lynn, MA 01910; telephone (617) 594–3140,

fax (617) 594–4805. Copies may be inspected

at the FAA, New England Region, Office of

the Assistant Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(o) This amendment becomes effective on

April 15, 1997.

Issued in Burlington, Massachusetts, on

February 24, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–7595 Filed 3–28–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 97–NM–22–AD; Amendment

39–9974; AD 97–07–01]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires the deactivation of the

avionics ground refrigeration unit (GRU)

of the air conditioning system until a

modification of avionics ventilation

circuit and the GRU is accomplished.

This amendment is prompted by reports

of water accumulation found in the Air

Data/Inertial Reference Unit (ADIRU)

trays of the avionics rack; the

accumulation is the result of operation

of the GRU in high ambient humidity.

The actions specified in this AD are

intended to prevent water accumulating

in this area, which could result in the

failure of the ADIRU and consequent

loss of air data and navigational

information to the flightcrew.

DATES: Effective April 15, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 15,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

May 30, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

22–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD 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; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2589; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, recently notified

the FAA that an unsafe condition may

exist on certain Airbus Model A330 and

A340 series airplanes. The DGAC

advises that there have been reports of

water accumulation found in the Air

Data/Inertial Reference Unit (ADIRU)

trays of the avionics racks on in-service

airplanes. All of the airplanes on which

this phenomenon occurred were

equipped with a ground cooling system,

identified as Airbus Modification No.

40063S10052. (This is an optional

modification available to Model A330

and A340 series airplanes.)

Investigation revealed that water

droplets can accumulate on the

evaporator cores of the ground

refrigeration unit (GRU) as a result of