Federal Register / Vol. 65, No. 188 / Wednesday, September 27, 2000 / Proposed Rules 58011

in § 567.1 of this part (other than

purchased credit card relationships

described under paragraph (b)(2) of this

section and core deposit intangibles

described at paragraph (g)(3) of this

section), are deducted in computing

tangible and core capital.

(2) Purchase card relationships may

be included (that is not deducted) in

computing core capital subject to the

restrictions of this section, but must be

deducted in computing tangible capital.

(3) Mortgage servicing assets may be

included (that is not deducted) in

computing core capital subject to the

restrictions in this section, and may be

included in tangible capital in the same

amount.

(4) Nonmortgage servicing assets may

be included (that is not deducted) in

computing core capital subject to the

restrictions in this section. All

nonmortgage servicing assets must be

deducted in computing tangible capital.

(5) Residual interests may be included

(that is not deducted) in computing core

capital subject to the restrictions of this

section, and may be included in tangible

capital in the same amount.

* * * * *

(e) Core capital limitation. (1)

Aggregate limit. The maximum

aggregate amount of servicing assets,

purchased credit card relationships, and

residual interests that may be included

in core capital shall be limited to the

lesser of:

(i) 100 percent of the amount of core

capital computed before the deduction

of any disallowed servicing assets,

disallowed purchased credit card

relationships, and disallowed residual

interests; or

(ii) The amount of servicing assets

and purchased credit card relationships

determined in accordance with

paragraph (d) of this section plus the

amount of residual interests.

(2) Reduction by deferred tax liability.

Associations may elect to deduct

disallowed servicing assets and residual

interests on a basis that is net of any

associated deferred tax liability.

(3) Sublimit for purchased credit card

relationships, non mortgage-related

servicing assets, and residual interests.

In addition to the aggregate limitation in

paragraph (e)(1) of this section, a

sublimit shall apply to purchased credit

card relationships, non mortgage-related

servicing assets, and residual interests.

The maximum allowable amount of

these three types of assets combined

shall be limited to the lesser of:

(i) 25 percent of the amount of core

capital computed before the deduction

of any disallowed servicing assets,

purchased credit card relationships, and

residual interests; or

(ii) The amount of purchased credit

card relationships and non mortgagerelated servicing assets determined in

accordance with paragraph (d) of this

section plus the amount of residual

interests.

(f) [Reserved]

* * * * *

Dated: August 4, 2000.

By the Office of Thrift Supervision.

Ellen Seidman,

Director.

[FR Doc. 00–24203 Filed 9–26–00; 8:45 am]

BILLING CODES 4810–33–P, 6210–01–P, 6714–01–P,

6720–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–15–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–100, –200, and –300

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 Bombardier Model DHC–8–100,

–200, and –300 series airplanes. This

proposal would require inspecting the

endcaps of the main landing gear

selector valve for leaks of hydraulic oil

and, if leaks are detected, replacing the

leaking endcaps or the entire selector

valve. This proposal would also require

eventual replacement or rework of

certain selector valves, which would

terminate the repetitive inspections.

This action is prompted by a report of

the collapse of the main landing gear

due to an external leak of hydraulic oil

in the landing gear selector valve,

resulting from a fracture of the endcap.

This action is intended to prevent leaks

of hydraulic oil from the main landing

gear selector valve, which could result

in the collapse of the main landing gear.

DATES: Comments must be received by

October 27, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

15–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 am and 3:00 pm,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–15–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

the proposed rule may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington, or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York.

FOR FURTHER INFORMATION CONTACT:

James E. Delisio, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7521; fax

(516) 568–2716.

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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

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

58012 Federal Register / Vol. 65, No. 188 / Wednesday, September 27, 2000 / Proposed Rules

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. 2000–NM–15–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–114, Attention: Rules Docket No.

2000–NM–15–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, notified the FAA

that an unsafe condition may exist on

certain Bombardier Model DHC–8–100,

–200, and –300 series airplanes. TCCA

advises that an investigation of the

collapse of the main landing gear of a

model DHC–8 series airplane identified

the cause as an external hydraulic oil

leak in the landing gear selector valve

due to a fracture of the endcap. TCCA

further advises that main landing gear

selector valves that have not been

upgraded to part number (P/N) 57420–

5 configuration are more susceptible to

internal leaks and that excessive

internal leaks can also contribute to the

collapse of the main landing gear.

Explanation of Relevant Service

Information

Bombardier has issued Alert Service

Bulletin A8–32–145, Revision ‘A’, dated

December 3, 1999, which describes

procedures for inspection of the

endcaps of the main landing gear

selector valve for leaks of hydraulic oil

and replacement of either the endcaps

or the complete main landing gear

selector valve, if necessary. The service

bulletin also describes procedures for

replacement or rework of certain

selector valves, which will eliminate the

need for the repetitive inspections.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. TCCA

classified this service bulletin as

mandatory and issued Canadian

airworthiness directive CF–99–22, dated

August 30, 1999, in order to assure the

continued airworthiness of these

airplanes in Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada 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,

TCCA has kept the FAA informed of the

situation described above. The FAA has

examined the findings of TCCA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 235 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take 9 work

hours per airplane to accomplish the

proposed inspection and replacement of

the main landing gear selector valve (if

a leak of hydraulic oil is detected at the

first inspection), and that the average

labor rate is $60 per work hour. If the

operator chooses to replace the endcaps

and do repetitive inspections prior to

replacing the main landing gear selector

valve, the number of work hours will be

greater. Required parts would be

provided at no charge to operators.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be $126,900, or $540 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this proposed AD were not adopted. The

cost impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (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 copy of the draft

regulatory evaluation prepared for this

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

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Bombardier: Docket 2000–NM–15–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes, serial numbers 003

through 182 inclusive and 184 through 531

inclusive; 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 (d) 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

Federal Register / Vol. 65, No. 188 / Wednesday, September 27, 2000 / Proposed Rules 58013

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the collapse of the main

landing gear due to leaks of hydraulic oil

from the main landing gear selector valve,

accomplish the following:

Inspection

(a) Within 100 flight cycles after the

effective date of this AD, perform a general

visual inspection of the endcaps of the main

landing gear selector valve for the presence

of hydraulic oil, in accordance with the

Accomplishment Instructions of Bombardier

Alert Service Bulletin A8–32–145, Revision

‘A’, dated December 3, 1999. Repeat the

inspection thereafter at intervals not to

exceed 400 flight hours until the

requirements of paragraph (c) are

accomplished.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Replacement or Modification

(b) If any hydraulic oil is detected on either

endcap during any inspection required by

paragraph (a) of this AD: Prior to further

flight, perform the actions specified in either

paragraph (b)(1) or (b)(2) of this AD.

(1) Replace the existing aluminum

endcaps, part number (P/N) 34629, with new

stainless steel endcaps having P/N 52982, in

accordance with the Accomplishment

Instructions of Bombardier Alert Service

Bulletin S.B. A8–32–145, Revision ‘A’, dated

December 3, 1999. Repeat the inspections

required by paragraph (a) at intervals not to

exceed 400 flight hours until the

requirements of paragraph (c) are met.

(2) Replace the main landing gear selector

valve with a valve having P/N 57420–5A, in

accordance with the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A8–32–145, Revision ‘A’, dated

December 3, 1999. This action terminates the

inspections required by paragraph (a) of this

AD.

Note 3: Use care when removing the

endcaps, so that the internal components do

not fall on the ground and get damaged.

(c) Within 12 months after the effective

date of this AD: Perform the actions specified

in either paragraph (c)(1) or (c)(2) of this AD

as applicable, in accordance with the

Accomplishment Instructions of Bombardier

Alert Service Bulletin A8–32–145, Revision

‘A’, dated December 3, 1999.

Accomplishment of either paragraph (c)(1) or

(c)(2) terminates the repetitive inspection

requirements of this AD.

(1) If a main landing gear selector valve

having P/N 57420, P/N 57420–1, or P/N

57420–3 is installed, remove it and replace

it with a valve having P/N 57420–5A.

(2) If a main landing gear selector valve

having P/N 57420–5 is installed, remove it

and replace it with a valve having P/N

57420–5A or modify the valve to the P/N

57420–5A configuration (ModSum

8Q100802).

Alternative Methods of Compliance

(d) 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, New York

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(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.

Note 5: The subject of this AD is addressed

in Canadian airworthiness directive CF–99–

22, dated August 30, 1999.

Issued in Renton, Washington, on

September 21, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–24752 Filed 9–26–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–79–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 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 Model A330 and A340

series airplanes. This proposal would

require modification of the rib 1/wing

center spar attachment. This action is

necessary to prevent fatigue cracking at

the rib 1/center spar angle and bottom

corner fitting, which could result in

reduced structural capability of the

wing. This action is intended to address

the identified unsafe condition.

DATES: Comments must be received by

October 27, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

79–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–79–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2110; fax (425) 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,