33164 Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations

4. Electronic communication. A dividend

rate may be stated only if it is provided in

conjunction with, but not more

conspicuously than, the annual percentage

yield to which it relates. In an advertisement

using electronic communication, the member

must be able to view both rates

simultaneously. This requirement is not

satisfied if the member can view the annual

percentage yield only by use of a link that

connects the member to information

appearing at another location.

* * * * *

(e)(1) Certain Media

(e)(1)(i)

2. Internet advertisements. The exemption

for advertisements made through broadcast

or electronic media does not extend to

advertisements made by electronic

communication, such as advertisements

posted on the Internet or sent by e-mail.

* * * * *

Section 707.10—Electronic Communication

(b) General Rule

1. Relationship to the E-Sign Act. The ESign Act authorizes the use of electronic

disclosures. It does not affect any

requirement imposed under this part other

than a provision that requires disclosures to

be in paper form, and it does not affect the

content or timing of disclosures. Electronic

disclosures are subject to the regulation’s

format, timing, and retainability rules and the

clear and conspicuous standard. For

example, to satisfy the clear and conspicuous

standard for disclosures, electronic

disclosures must use visual text.

2. Clear and conspicuous standard. A

credit union must provide electronic

disclosures using a clear and conspicuous

format. Also, in accordance with the ESignAct:

i. The credit union must disclose the

requirements for accessing and retaining

disclosures in that format;

ii. The member must demonstrate the

ability to access the information

electronically and affirmatively consent to

electronic delivery; and

iii. The credit union must provide the

disclosures in accordance with the specified

requirements.

3. Timing and effective delivery.

i. When a member opens an account online. When a member opens an account online, the member must be required to access

the disclosures required under § 707.4 before

the account is opened or a service is

provided, whichever is earlier. A link to the

disclosures satisfies the timing rule if the

member cannot bypass the disclosures before

opening the account. Or the disclosures in

this example must automatically appear on

the screen, even if multiple screens are

required to view the entire disclosure. The

credit union is not required to confirm that

the member has read the disclosure.

ii. For disclosures provided periodically.

Disclosures provided by mail are timely

based on when the disclosures are sent.

Disclosures posted at an Internet web site,

such as periodic statements or change-interms and other notices, are timely when the

credit union has both made the disclosures

available and sent a notice alerting the

member that the disclosures have been

posted. For example, under § 707.5, credit

unions must give advance notice to affected

members at least 30 calendar days in advance

of certain changes. For a change in terms

notice posted on the Internet, a credit union

must both post the notice and notify

members of its availability at least 30 days in

advance of the change.

4. Retainability of disclosures. Credit

unions satisfy the requirement that

disclosures be in a form that the member may

keep if electronic disclosures are delivered in

a format that is capable of being retained

(such as by printing or storing electronically).

The format must also be consistent with the

information required to be provided under

Section 101(c)(1)(C)(i) of the E-Sign Act, 15

U.S.C. 7001(c)(1)(C)(i)), about the hardware

and software requirements for accessing and

retaining electronic disclosures.

5. Disclosures provided on credit union’s

equipment. A credit union that controls the

equipment providing electronic disclosures

to members (for example, a computer

terminal located in a credit union’s lobby or

at a public kiosk) must ensure that the

equipment satisfies the regulation’s

requirements to provide timely disclosures in

a clear and conspicuous format and in a form

that the member may keep. For example, if

disclosures are required at the time of an online transaction, the disclosures must be sent

to the member’s e-mail address or must be

posted at another location such as the credit

union’s Internet web site, unless the credit

union provides a printer that automatically

prints the disclosures.

(d) Address Or Location To Receive

Electronic Communication

(d)(1)

1. Electronic address. A member’s

electronic address is an e-mail address that

is not limited to receiving communications

transmitted solely by the credit union.

(d)(2)

1. Identifying account involved. A credit

union may identify a specific account in a

variety of ways and is not required to identify

an account by reference to the account

number. For example, where the member has

only one share account, and no confusion

would result, the credit union may refer to

‘‘your share account.’’ If the member has two

accounts, the credit union may, for example,

differentiate accounts by using terms such as

‘‘primary account’’ and ‘‘secondary account’’

or by using a truncated account number.

2. 90-day rule. The actual disclosures

provided to a member must be available for

at least 90 days, but the credit union has

discretion to determine whether they should

be available at the same location for the

entire period.

(e) Redelivery

1. E-mail returned as undeliverable. If an

e-mail to the member (containing an alert

notice or other disclosure) is returned as

undeliverable, the redelivery requirement is

satisfied if, for example, the credit union

sends the disclosure to a different e-mail

address or postal address that the credit

union has on file for the member. Sending

the disclosures a second time to the same

electronic address is not sufficient if the

credit union has a different address for the

member on file.

[FR Doc. 01–15471 Filed 6–20–01; 8:45 am]

BILLING CODE 7535–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–15–AD; Amendment

39–12275; AD 2001–12–19]

RIN 2120–AA64

Airworthiness Directives; Turbomeca

S.A. Artouste II and Artouste III Series

Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), that is

applicable to Turbomeca S.A. Artouste

II and Artouste III series turboshaft

engines. This amendment requires

installation of modification TU 24, TU

167, or TU 164, depending on the

specific engine series. These

modifications will prevent

uncommanded partial closing or total

closing of the electrical fuel cock, which

will prevent uncommanded in-flight

engine shutdown. From the effective

date of this AD, and until the

modification is installed, this

amendment will also limit the duration

of the engine operating cycle. This

amendment is prompted by reports of

unexpected power loss during test

flights. The actions specified by this AD

are intended to prevent unexpected

power loss, which could result in an

uncommanded in-flight engine

shutdown, autorotation, and forced

landing.

DATES: Effective date July 26, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of July 26, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Turbomeca S.A, Turbomeca

S.A.64511 Bordes Cedex, France;

telephone 33 05 59 64 40 00, fax 33 05

59 64 60 80. This information may be

examined at the FAA, New England

Region, Office of the Regional 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.

Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations 33165

FOR FURTHER INFORMATION CONTACT:

Glorianne Niebuhr, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7132;

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to

Turbomeca Artouste II and Artouste III

series turboshaft engines was published

in the Federal Register on May 31, 2000

(65 FR 34602). That action proposed to

require installation of modification TU

24, TU 167, or TU 164, depending on

the specific engine series, in accordance

with Turbomeca Artouste II Service

Bulletin (SB) No. 223 72 0070, dated

January 21, 1999; Turbomeca Artouste

III SB No. 218 80 0098, dated January

14, 1999; or Turbomeca Artouste III SB

No. 218 80 0093, Revision 2, dated

January 14, 1999.

Comments

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.

There are approximately 3,102

Turbomeca S.A. Artouste II and

Artouste III series turboshaft engines of

the affected design in the worldwide

fleet. The FAA estimates that 213

engines installed on helicopters of US

registry would be affected by this

proposed AD, that it would take

approximately two work hours per

engine to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $630 per

engine. Based on these figures, the total

cost impact of the proposed AD on US

operators is estimated to be $159,750.

The manufacturer has advised the

Direction Generale de L’Aviation Civile

(DGAC), which is the airworthiness

authority for France, that it may provide

modification TU 24, TU 164, or TU 167

at no cost to the operator, thereby

substantially reducing the cost impact of

this proposed rule.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it

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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this final rule.

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 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 final evaluation has

been prepared for this action and it 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, 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 a new airworthiness directive to

read as follows:

2001–12–19 Turbomeca S.A.: Amendment

39–12275. Docket No. 2000–NE–15–AD.

Applicability

This airworthiness directive (AD) is

applicable to Turbomeca S.A. Artouste II and

Artouste III series turboshaft engines. These

engines are installed on, but not limited to,

Alouette II SE 3130, Alouette II SE 313 B,

Eurocopter SA 315 LAMA, and SA 316

Alouette III series helicopters.

Note 1: This 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 (h) 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 unexpected power loss, which

could result in an uncommanded in-flight

engine shutdown, autorotation, and forced

landing, accomplish the following:

For Artouste II Engines

(a) As of the effective date of this AD, the

duration of the operating cycle (start-up to

shutdown) is limited to two hours total until

modification TU 24 is installed in accordance

with Turbomeca Artouste II Service Bulletin

(SB) 218 80 0070, Section 2, dated January

21, 1999.

(b) At the next shop visit, within 30 days,

or within 120 cycles after the effective date

of this AD, whichever occurs first, install

modification TU 24 in accordance with

Turbomeca Artouste II SB 218 80 0070,

Section 2, dated January 21, 1999.

For Artouste III B and Artouste III B1

Engines

(c) As of the effective date of this AD, the

duration of the operating cycle (start-up to

shutdown) is limited to two hours total until

modification TU 167 is installed in

accordance with Turbomeca Artouste III SB

218 80 0093, Revision 2, Section 2, dated

January 14, 1999.

(d) At the next shop visit, within 30 days,

or within 120 cycles after the effective date

of this AD, whichever occurs first, install

modification TU 167 in accordance with

Turbomeca Artouste III Service Bulletin 218

80 0093, Revision 2, Section 2, dated January

14, 1999.

For Artouste III D Engines

(e) As of the effective date of this AD, the

duration of the operating cycle (start-up to

shutdown) is limited to two hours total until

modification TU 164 is installed in

accordance with Turbomeca Artouste III

Service Bulletin 218 80 0098, Section 2,

dated January 14, 1999.

(f) At the next shop visit, within 30 days,

or within 120 cycles after the effective date

of this AD, whichever occurs first, install

modification TU 164 in accordance with

Turbomeca Artouste III Service Bulletin 218

80 0098, Section 2, dated January 14, 1999.

Definition

(g) For the purpose of this AD, a shop visit

is defined as any time when the engine is

removed from the helicopter for

maintenance.

Alternative Methods of Compliance

(h) 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. Operators shall submit

their request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

33166 Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations

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.

Special Flight Permits

(i) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

Documents That Have Been Incorporated by

Reference

(j) The inspection shall be done in

accordance with the following Turbomeca

service bulletins (SBs):

Document No. Pages Revision Date

SB Artouste II SB 223 72 0070; Total pages: 16 ........................................ All .................................. Original ......................... Jan. 21, 1999.

SB Artouste III SB 218 80 0093; Total pages: 18 ....................................... All .................................. 2 .................................... Jan. 14, 1999.

SB Artouste III SB 218 80 0098; Total pages: 10 ....................................... All .................................. Original ......................... Jan. 14, 1999.

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 Turbomeca S.A., 40220 Tarnos, France;

telephone 33 05 59 64 40 00, fax 33 05 59

64 60 80. Copies may be inspected at the

FAA, New England Region, Office of the

Regional 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.

Note 3: The subject of this AD is addressed

in Direction Generale de L’Aviation Civile

(DGAC) Airworthiness Directive (AD) 1999–

005(A), dated January 13, 1999, and AD

1999–090(A), dated February 24, 1999.

Effective Date

(k) This amendment becomes effective on

July 26, 2001.

Issued in Burlington, Massachusetts, on

June 11, 2001.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 01–15392 Filed 6–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–30–AD; Amendment

39–12276; AD 2001–12–20]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company (GE) CF6–50

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to General Electric Company

(GE) CF6–50 turbofan engines. This

amendment requires removal of old

high pressure compressor (HPC) air

ducts and mating hardware and

replacement with newly designed air

ducts and reworked mating hardware.

This amendment also requires the

repetitive inspection of certain

reworked mating hardware. This

amendment is prompted by reports of

an uncontained low pressure turbine

(LPT) disk failure that resulted from an

air duct failure that caused a fan mid

shaft (FMS) separation. The actions

specified by this AD are intended to

prevent HPC air duct failures that could

result in FMS failures, that in turn could

result in rejected takeoffs or

uncontained LPT events, and to prevent

HPC rear shaft failures that could result

in uncontained engine failures.

DATES: Effective date July 26, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of July 26, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from General Electric Company via

Lockheed Martin Technology Services,

10525 Chester Road, Suite C, Cincinnati,

Ohio 45215, telephone: (513) 672–8400;

fax: (513) 672–8422. You may examine

the AD docket (including any comments

and service information) at the FAA,

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA

between 8:00 a.m. and 4:30 p.m.,

Monday through Friday, except Federal

holidays. You may also examine the

service information at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Karen Curtis, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington MA

01803–5299; telephone: (781) 238–7192;

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to GE

CF6–50 turbofan engines was published

in the Federal Register on November 24,

2000 (65 FR 70533). That action

proposed to require removal of old high

pressure compressor (HPC) air ducts

and mating hardware and replacement

with newly designed air ducts and

reworked mating hardware in

accordance with GE Aircraft Engines

(GEAE) Service Bulletin (SB) CF6–50

72–1200, dated May 8, 2000; GEAE

Alert Service Bulletin (ASB) CF6–50

72–A1200, Revision 1, dated July 20,

2000; or GEAE ASB CF6–50 72–A1200,

Revision 2, dated November 2,

2000.Those bulletins describe

procedures for removal of the HPC air

duct assembly, part numbers (P/N’s):

9128M36G03 / G04 / G05 / G06 / G08

/ G20 / G21 or 1644M16G03 and mating

hardware (rear shaft or stage 11–14

spool shaft) and replacement with the

new design air duct and reworked

mating hardware.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Typographical Error

One commenter notes that there is a

typographical error in paragraph (a) of

the proposed rule. The error is in the

P/N for the air duct assembly. There is

no P/N 99128M36G03. The FAA agrees,

and has changed the P/N reference from

99128M36G03 to 9128M36G03.

Cost of 3–9 Spool Inspections

One commenter requests that the cost

of the stage 3–9 spool inspections

required by other AD’s be included in

the cost analysis for this rule as well.

The FAA does not agree. The costs of

the stage 3–9 spool inspections required

by other AD’s were accounted for in the

rule making process for those rules. This

AD does not require additional stage 3–

9 spool inspections.

Shop Visit Definition

Two commenters request that the

definition of shop visit for this rule be

modified or clarified because they

believe that the shop visit definition in

the proposed rule will force