Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations 14301

Existing § 620.4(a) requires a System

institution to prepare and distribute to

its shareholders an annual report. While

the proposed rule did not include any

suggested changes to this section, the

FCC noted the FCA does not specify the

medium to be used by System

institutions for providing information to

their shareholders. The FCC stated that

‘‘delivery of information through an

electronic medium generally could

satisfy delivery or transmission

obligations under the Farm Credit Act

and Regulations.’’ While the FCC did

not specifically recommend that FCA

amend § 620.4(a) to allow both paper

and electronic distribution of

shareholder reports, the FCC suggested

that we should address this issue.

In this regard, the FCA has an internal

task force that is reviewing electronic

commerce issues. This task force will

present its findings and make

recommendations to the FCA Board that

may address this issue. Meanwhile,

existing § 620.4(a) requires System

institutions to ‘‘distribute’’ their annual

reports on paper until the issuance of

additional guidance in this area.

However, our regulations do not prevent

System institutions, if they so choose,

from making their annual reports

available on their Web sites.

List of Subjects in 12 CFR Part 620

Accounting, Agriculture, Banks,

banking, Reporting and recordkeeping

requirements, Rural areas.

For the reasons stated in the

preamble, we amend part 620 of chapter

VI, title 12 of the Code of Federal

Regulations to read as follows:

PART 620—DISCLOSURE TO

SHAREHOLDERS

1. The authority citation for part 620

continues to read as follows:

Authority: Secs. 5.17, 5.19, 8.11 of the

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

2279aa–11); secs. 424 of Pub. L. 100–233, 101

Stat. 1568, 1656.

Subpart A—General

2. Revise § 620.2(h)(1) and (2) to read

as follows:

§ 620.2 Preparing and filing the reports.

* * * * *

(h)(1) Each institution’s annual report

or notice must state, in a prominent

location within the report or notice:

(i) That the institution’s quarterly

reports are available free of charge on

request;

(ii) The approximate dates the

quarterly reports will be available; and

(iii) The telephone numbers and

addresses (including information on any

other distribution method the

institution makes available) where

shareholders can request or obtain

copies of the quarterly reports.

(2) Each association must state, in a

prominent location within each report:

(i) That the shareholders’ investment

in the association may be materially

affected by the financial condition and

results of operations of the related bank;

(ii) That (if not otherwise provided) a

copy of the bank’s financial reports to

shareholders will be made available free

of charge on request; and

(iii) The telephone numbers and

addresses (including information on any

other distribution method the

association makes available) where

shareholders can request or obtain

copies of the related bank’s financial

reports.

* * * * *

Subpart B—Annual Report to

Shareholders

3. Revise § 620.4(b) to read as follows:

§ 620.4 Preparing and distributing the

annual report.

* * * * *

(b)(1) A bank must distribute its

annual report to the shareholders of all

related associations if the bank

experiences a significant event that has

a material effect on those associations.

(2) Any bank that is required by

paragraph (b)(1) of this section to

distribute its annual report must

coordinate its distribution with its

related associations.

* * * * *

4. Add new § 620.5(a)(10) to read as

follows:

§ 620.5 Contents of the annual report to

shareholders.

(a) Description of business. ***

* * * * *

(10) For associations, in a separate

section of the annual report, discuss the

institution’s financial and supervisory

relationship with its funding bank. This

separate section may incorporate by

reference information from other

sections of the annual report. At a

minimum, the separate section must

include the statement required by

§ 620.2(h)(2)(i) and the following

information required elsewhere in this

section, if applicable:

(i) The association’s obligation to

borrow only from the bank unless the

bank gives the association approval to

borrow elsewhere;

(ii) The major terms of any capital

preservation, loss sharing, or financial

assistance agreements between the

association and the bank;

(iii) Any statutory or bank bylaw

provisions authorizing bank access to

the capital of the association;

(iv) The extent the bank assumed the

association’s exposure to interest rate

risk; and

(v) Any other material operational and

financial conditions that may affect the

interdependent relationship between

the association and the bank.

* * * * *

Dated: March 6, 2001.

Kelly Mikel Williams,

Secretary, Farm Credit Administration Board.

[FR Doc. 01–5976 Filed 3–9–01; 8:45 am]

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–13–AD; Amendment

39–12132; AD 2001–04–13]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA.315B, SA.316B,

SA.316C, SE.3160, and SA.319B

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

for Eurocopter France (ECF) Model

SA.315B, SA.316B, SA.316C, SE.3160,

and SA.319B helicopters. That AD

requires initial and recurring

inspections of the main rotor blade

(blade) spar for cracks. This amendment

requires initial and recurring dye

penetrant or eddy current inspections

for a cracked blade spar at 100-hour

time-in-service (TIS) intervals or 600

cycles, whichever occurs first, rather

than the 25-hour TIS intervals currently

required. This amendment is prompted

by an accident in which an ECF Model

SA.315B helicopter blade failed due to

fatigue cracking. The actions specified

by this AD are intended to prevent

separation of a blade and subsequent

loss of control of the helicopter.

DATES: Effective April 16, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 16,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

14302 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. This information

may be examined at the FAA, Office of

the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room

663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5490, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–10–09,

Amendment 39–10725 (63 FR 46160,

August 31, 1998), which applies to ECF

Model SA.315B, SA.316B, SA.316C,

SE.3160, and SA.319B helicopters, was

published in the Federal Register on

December 1, 2000 (65 FR 75198). That

action proposed to require, within 25

hours TIS and thereafter at intervals not

to exceed 100 hours TIS or 600 cycles,

whichever occurs first, inspecting each

blade spar for a crack, using dye

penetrant or eddy current, and

inspecting each blade cuff to ensure an

adequate sealant bead. A ‘‘cycle’’ is any

landing, regardless of whether the main

rotor rotation is continued or stopped,

or any completion of an external load

operation; e.g. load release. If a crack is

found, the proposed AD would require

replacing the blade with an airworthy

blade before further flight.

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 but with one minor

editorial change. Notes 4 and 5 in the

proposal should have been Notes 3 and

4 respectively, and this AD corrects that

error. The FAA has determined that this

change will neither increase the

economic burden on an operator nor

increase the scope of the AD.

The FAA estimates that 93 helicopters

of U.S. registry will be affected by this

AD, that it would take approximately 4

hours to inspect and 4 hours to replace

a blade, if necessary, and that the

average labor rate is $60 per work hour.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $66,960, assuming three

inspections per year and no blade

replacement.

The regulations adopted herein will

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 final rule does not

have federalism implications under

Executive Order 13132.

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–10725 (63 FR

46160), and by adding a new

airworthiness directive (AD),

Amendment 39–12132, to read as

follows:

2001–04–13 Eurocopter France:

Amendment 39–12132. Docket No.

2000–SW–13–AD. Supersedes AD 98–

10–09, Amendment 39–10725, Docket

No. 98–SW–23–AD.

Applicability: Model SA.315B, SA.316B,

SA.316C, SE.3160, and SA.319B helicopters

with a main rotor blade (blade), with any of

the following part numbers (P/N): 3160S11–

10000 all dash numbers, 3160S11–30000 all

dash numbers, 3160S11–35000 all dash

numbers, 3160S11–40000 all dash numbers,

3160S11–45000 all dash numbers, 3160S11–

50000 all dash numbers, or 3160S11–55000

all dash numbers, installed, certificated in

any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For helicopters 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 a blade separation and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Within 25 hours time-in-service (TIS) or

before the next flight following the onset of

any one-per-rev vibration, whichever occurs

first, and thereafter at intervals not to exceed

100 hours TIS or 600 ‘‘cycles’’ (a ‘‘cycle’’ is

any landing, regardless of whether the main

rotor rotation is continued or stopped, or any

completion of an external load operation;

e.g., load release), whichever occurs first,

(1) Inspect each blade spar for a crack.

(i) Without removing the blade from the

helicopter, clean each blade root area using

‘‘Teepol’’ or an equivalent product.

(ii) Support the blade tip to eliminate blade

droop while inspecting the lower blade

surface.

(iii) By either a dye penetrant or eddy

current method, inspect each blade along the

hatched area indicated in Figure 1, beginning

on the blade lower surface, then on the flat

section of the trailing edge (B), on the blade

upper surface, and then on the flat section of

the leading edge (A).

Note 2: Eurocopter France Service

Bulletins (SB) SA 315 No. 05.39 and SA 316/

319 No. 05.98, dated November 12, 1999,

pertain to the subject of this AD.

(iv) If a crack is found, replace the blade

with an airworthy blade before further flight.

BILLING CODE 4910–13–P

Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations 14303

BILLING CODE 4910–13–C

14304 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations

(2) Ensure that there is a sealant bead (1)

around the edge of each blade cuff. If no

sealant bead exists or if a sealant bead shows

excessive wear, before further flight, apply a

sealant bead in accordance with paragraph

2.2 of the Accomplishment Instructions of

Eurocopter France SB 65.137 R1, dated

November 17, 1993.

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(c) Special flight permits will not be

issued.

(d) The modification shall be done in

accordance with paragraph 2.2 of the

Accomplishment Instructions of Eurocopter

France SB 65.137 R1, dated November 17,

1993. 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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. Copies may be inspected at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

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

(e) This amendment becomes effective on

April 16, 2001.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 1998–171–039(A)R2 and 1998–

170–056(A)R2, both dated January 12, 2000.

Issued in Fort Worth, Texas, on February

20, 2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–5164 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–CE–89–AD; Amendment 39–

12137; AD 2001–05–01]

RIN 2120–AA64

Airworthiness Directives; DG

Flugzeugbau GmbH Model DG–500MB

Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain DG Flugzeugbau

GmbH (DG Flugzeugbau) Model DG–

500MB sailplanes equipped with a

SOLO 2625 02 engine. This AD requires

you to install additional access holes in

the propeller mount and modify the

engine. This AD also requires you to do

a ground test run and replace the digital

engine indicator circuit breaker. This

AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for the Federal Republic of

Germany. The actions specified by this

AD are intended to correct an

inadequate circuit breaker and

unsatisfactory drive belt tension that

could cause damage to the engine

crankshaft. Such damage could lead to

engine failure and loss of control of the

sailplane.

DATES: This AD becomes effective on

April 27, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of April 27, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

DG Flugzeugbau GmbH, Postbox 41 20,

D–76646 Bruchsal, Federal Republic of

Germany; telephone: +49 7257–890;

facsimile: +49 7257–8922. You may

examine this information at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 99–CE–89–

AD, 901 Locust, Room 506, Kansas City,

Missouri 64106; or at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Mike Kiesov, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64106;

telephone: (816) 329–4144; facsimile:

(816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Luftfahrt-Bundesamt (LBA), which

is the airworthiness authority for the

Federal Republic of Germany, notified

FAA that an unsafe condition may exist

on all DG Flugzeugbau Model DG–

500MB sailplanes equipped with a

SOLO 2625 02 engine. The LBA reports

that the service history for the SOLO

2625 02 engine shows a need to modify

the front crank shaft bearing.

Additionally, the digital engine

indicator circuit breaker amperage is too

low for use and needs replacement.

What are the consequences if the

condition is not corrected? The actions

specified by this AD are intended to

correct an inadequate circuit breaker

and unsatisfactory drive belt tension

that could cause damage to the engine

crankshaft. Such damage could lead to

engine failure and loss of control of the

sailplane.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to certain DG

Flugzeugbau Model DG–500MB

sailplanes equipped with a SOLO 2625

02 engine. This proposal was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

December 27, 2000 (65 FR 81782). The

NPRM proposed to require you install

additional access holes in the propeller

mount and modify the engine. The

NPRM also proposed to require you to

do a ground test run and replace the

digital engine indicator circuit breaker.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

FAA’s Determination

What is FAA’s final determination on

this issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. We determined

that these minor corrections:

—Will not change the meaning of the

AD; and

—Will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How many sailplanes does this AD

impact? We estimate that this AD affects

1 sailplane in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

sailplanes? We estimate the following

costs to accomplish the modification: