69862 Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations

Applicability: Model 60 airplanes, serial

numbers 104 through 168 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 (c) 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 electrical arcing between the

oxygen tubing and an electrical source which

could result in an oxygen fire, accomplish

the following:

Inspection

(a) Within 60 days or 80 flight hours after

issuance of this AD, whichever occurs first,

perform a detailed visual inspection of the

oxygen tubing for adequate clamping and

adequate clearance from electrical wiring and

electrical contacts, in accordance with the

Accomplishment Instructions of Bombardier

Alert Service Bulletin (Learjet 60) SB A60–

35–2, dated November 4, 1999. If adequate

clamping and adequate clearance, as

specified in the service bulletin, are found,

no further action is required by this AD.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Adjustment

(b) If clamping or clearance of the oxygen

tubing from electrical wiring or contacts is

not adequate as specified in Bombardier

Alert Service Bulletin (Learjet 60) SB A60–

35–2, dated November 4, 1999, the clamping

or the clearance must be adjusted, in

accordance with the Accomplishment

Instructions of the service bulletin.

Alternative Methods of Compliance

(c) 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, Wichita

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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permits

(d) 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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Bombardier Alert Service Bulletin

(Learjet 60) SB A60–35–2, dated November 4,

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 Learjet, Inc., One Learjet Way, Wichita,

Kansas 67209–2942. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 101, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(f) This amendment becomes effective on

December 26, 2000.

Issued in Renton, Washington, on

November 9, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29374 Filed 11–20–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–329–AD; Amendment

39–11988; AD 2000–23–16]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Powered

By Pratt & Whitney JT9D–3 and –7

Series 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 certain Boeing Model 747

series airplanes. This action requires

repetitive inspections and torque checks

of the hanger fittings and strut forward

bulkhead of the forward engine mount

and adjacent support structure, and

corrective actions, if necessary. This

action also provides for optional

terminating action for the repetitive

inspections and checks. This action is

necessary to detect and correct loose

fasteners and associated damage to the

hanger fittings and bulkhead of the

forward engine mount, which could

result in separation of the engine from

the airplane.

DATES: Effective December 6, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

6, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 22, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

329–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-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–329–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

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

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:

Tamara Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports indicating the

detection of loose fasteners of the

hanger fittings and strut forward

bulkhead of the forward engine mount.

In one occurrence, damage to a hanger

fitting also was detected. Such damage

has been attributed to loose fasteners of

the front spar bulkhead of the strut. The

fasteners may not have been fully

torqued, or the nuts may have bottomed

out on the bolt threads prior to full

clamp-up during fastener torque.

Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations 69863

Certain tolerance build-up conditions

also could cause the nuts to shank

during installation. These conditions, if

not corrected, could result in loose

fasteners and associated damage to the

hanger fittings and bulkhead of the

forward engine mount, and consequent

separation of the engine from the

airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

54A2203, dated August 31, 2000, which

describes procedures for repetitive

detailed visual inspections and torque

checks of the hanger fittings and strut

forward bulkhead of the forward engine

mount and adjacent support structure to

detect loose fasteners, cracking, and/or

damage; and corrective actions, if

necessary. The corrective actions consist

of a torque check, before further flight,

if any loose fasteners are detected;

rework of loose hanger fittings, and

damaged or cracked fittings that are

within the allowable rework limits; and

replacement if damage or cracks are

detected that are outside the allowable

rework limits.

If certain damage of the strut forward

bulkhead; bulkhead chords; lower spar

web; or bulkhead channel is detected,

the alert service bulletin specifies

contacting Boeing for rework/

replacement instructions. The alert

service bulletin also describes

procedures for rework or replacement of

the fittings, which eliminates the need

for the repetitive inspections and

checks. The alert service bulletin

references Boeing Service Bulletin 747–

54A2159, dated November 3, 1994;

Revision 1, dated June 1, 1995; or

Revision 2, dated March 14, 1996; and

the 747 Structural Repair Manual,

Chapter 51–30–02, as additional sources

of service information for

accomplishment of the terminating

action.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

detect and correct loose fasteners and

associated damage to the hanger fittings

and bulkhead of the forward engine

mount, which could result in separation

of the engine from the airplane. This AD

requires repetitive inspections and

torque checks of the hanger fittings and

strut forward bulkhead of the forward

engine mount and adjacent support

structure to detect loose fasteners,

cracking, and/or damage; and corrective

actions, if necessary. This action also

provides for optional terminating action

for the repetitive inspections and

checks. The actions are required to be

accomplished in accordance with the

alert service bulletin described

previously, except as discussed below.

Interim Action

This is considered to be interim

action. At this time the FAA is

considering a separate rulemaking

action to mandate accomplishment of

the terminating action described in Part

6 of the alert service bulletin, which

would terminate the repetitive

inspections and checks required by this

AD action. The FAA also is considering

mandating the torque checks described

in Part 3 of the alert service bulletin,

which would extend the repetitive

inspection and check interval, until

accomplishment of the terminating

action. However, the planned

compliance time for these actions is

sufficiently long so that notice and

opportunity for prior public comment

will be practicable.

Differences Between Alert Service

Bulletin and This AD

Operators should note that, although

the effectivity section of the alert service

bulletin includes Boeing Model 747

series airplanes having serial numbers

21048 and 20887, these airplanes have

been modified and are now powered by

General Electric CF6–50 series engines,

and are not affected by the actions

required by this proposed rule.

Operators also should note that,

although the alert service bulletin

specifies that the manufacturer may be

contacted for certain rework and/or

replacement instructions, this AD

requires such rework and/or

replacement to be done in accordance

with a method approved by the FAA, or

in accordance with data meeting the

type certification basis of the airplane

approved by a Boeing Company

Designated Engineering Representative

who has been authorized by the FAA to

make such findings.

Determination of Rule’s Effective Date

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

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 shall 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.

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 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 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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–329–AD.’’

The postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

69864 Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations

correct an unsafe condition in aircraft,

and that it 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:

2000–23–16 Boeing: Amendment 39–11988.

Docket 2000-NM–329–AD.

Applicability: Model 747 series airplanes,

certificated in any category, as listed in

Boeing Alert Service Bulletin 747–54A2203,

dated August 31, 2000; except Model 747

series airplanes having serial numbers 21048

and 20887.

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 (c) 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 detect and correct loose fasteners and

associated damage to the hanger fittings and

strut forward bulkhead of the forward engine

mount, which could result in separation of

the engine from the airplane, accomplish the

following:

Repetitive Inspections/Checks

(a) Within 60 days after the effective date

of this AD: Perform a detailed visual

inspection and torque check as specified in

Part 2 of Boeing Alert Service Bulletin 747–

54A2203, dated August 31, 2000, to detect

loose fasteners and associated damage to the

hanger fittings and bulkhead of the forward

engine mount, in accordance with Figure 1

of the alert service bulletin. Repeat the

inspections/checks thereafter at the

applicable intervals specified in Figure 1 of

the alert service bulletin.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Corrective Actions

(1) If no loose fastener or associated

damage is detected, repeat the inspections/

checks thereafter at the applicable intervals

specified in Figure 1 of the alert service

bulletin until accomplishment of the

terminating action specified in paragraph (b)

of this AD.

Note 3: Where there are differences

between the AD and the alert service

bulletin, the AD prevails.

(2) If any loose fastener or associated

damage is detected, before further flight,

perform the applicable corrective actions

(torque check, rework or replacement of

fittings), as specified in Figure 1 of the alert

service bulletin. Repeat the inspections/

checks thereafter at the applicable intervals

specified in Figure 1 of the alert service

bulletin until accomplishment of the

terminating action specified in paragraph (b)

of this AD. Where the alert service bulletin

specifies that the manufacturer may be

contacted for disposition of certain corrective

actions (rework or replacement of fittings),

this AD requires such rework and/or

replacement to be done in accordance with

a method approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA; or

in accordance with data meeting the type

certification basis of the airplane approved

by a Boeing Company designated engineering

representative (DER) who has been

authorized by the Manager, Seattle ACO, to

make such findings. For a repair method to

be approved by the Manager, Seattle ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Optional Terminating Action

(b) Accomplishment of the terminating

action specified in Part 6 of Boeing Alert

Service Bulletin 747–54A2203, dated August

31, 2000, constitutes terminating action for

the repetitive inspections/checks required by

paragraph (a) of this AD.

Note 4: Installation of two BACW10BP*

auxiliary power unit washers on Group A

fasteners accomplished prior to the effective

date of this AD in accordance with Boeing

Service Bulletin 747–54A2159, dated

November 3, 1994, Revision 1, dated June 1,

1995, or Revision 2, dated March 14, 1996;

and pin or bolt protrusion as specified in the

747 Structural Repair Manual, Chapter 51–

30–02 (both referenced in Boeing Alert

Service Bulletin 747–54A2203, dated August

31, 2000); is considered acceptable for

compliance with the terminating action

specified in paragraph (b) of this AD.

Alternative Methods of Compliance

(c) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) 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.

Incorporation by Reference

(e) Except as provided by paragraph (a)(2)

of this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–54A2203, dated August 31,

2000. 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected 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.

Effective Date

(f) This amendment becomes effective on

December 6, 2000.

Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations 69865

Issued in Renton, Washington, on

November 8, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29215 Filed 11–20–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF HEALTH AND

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 510

New Animal Drugs; Change of

Sponsor’s Address

AGENCY: Food and Drug Administration,

HHS.

ACTION: Final rule.

SUMMARY: The Food and Drug

Administration (FDA) is amending the

animal drug regulations to reflect a

change of sponsor’s address for Novartis

Animal Health US, Inc.

DATES: This rule is effective November

21, 2000.

FOR FURTHER INFORMATION CONTACT:

Norman J. Turner, Center for Veterinary

Medicine (HFV–102), Food and Drug

Administration, 7500 Standish Pl.,

Rockville, MD 20855, 301–827–0214.

SUPPLEMENTARY INFORMATION: Novartis

Animal Health US, Inc., P.O. Box 18300,

Greensboro, NC 27419–8300, has

informed FDA of a change of sponsor’s

address to 3200 Northline Ave., suite

300, Greensboro, NC 27408.

Accordingly, the agency is amending

the regulations in 21 CFR 510.600(c)(1)

and (c)(2) to reflect the change of

sponsor’s address.

This rule does not meet the definition

of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because

it is a rule of ‘‘particular applicability.’’

Therefore, it is not subject to the

congressional review requirements in 5

U.S.C. 801–808.

List of Subjects in 21 CFR Part 510

Administrative practice and

procedure, Animal drugs, Labeling,

Reporting and recordkeeping

requirements.

Therefore, under the Federal Food,

Drug, and Cosmetic Act and under

authority delegated to the Commissioner

of Food and Drugs and redelegated to

the Center for Veterinary Medicine, 21

CFR part 510 is amended as follows:

PART 510—NEW ANIMAL DRUGS

1. The authority citation for 21 CFR

part 510 continues to read as follows:

Authority: 21 U.S.C. 321, 331, 351, 352,

353, 360b, 371, 379e.

2. Section 510.600 is amended in the

table in paragraph (c)(1) by revising the

entry for ‘‘Novartis Animal Health US,

Inc.’’ and in the table in paragraph (c)(2)

by revising the entry for ‘‘058198’’ to

read as follows:

§ 510.600 Names, addresses, and drug

labeler codes of sponsors of approved

applications.

* * * * *

(c) * * *

(1) * * *

Firm name and address Drug labeler code

*******

Novartis Animal Health US, Inc., 3200 Northline Ave., suite 300,

Greensboro, NC 27408

058198

*******

(2) * * *

Drug labeler code Firm name and address

*******

058198 Novartis Animal Health US, Inc., 3200 Northline Ave., suite 300,

Greensboro, NC 27408

*******

Dated: November 6, 2000.

Claire M. Lathers,

Director, Office of New Animal Drug

Evaluation, Center for Veterinary Medicine.

[FR Doc. 00–29764 Filed 11–20–00; 8:45 am]

BILLING CODE 4160–01–F

DEPARTMENT OF THE TREASURY

31 CFR Part 1

Departmental Offices; Privacy Act of

1974; Implementation

AGENCY: Department of the Treasury.

ACTION: Final Rule.

SUMMARY: The Department of the

Treasury is amending its Privacy Act

exemption rules that were first

published on October 2, 1975, to

consolidate the regulations issued

pursuant to 5 U.S.C. 552a(j) and (k)

which exempt one or more systems of

records established on behalf of each

bureau by the Department.

EFFECTIVE DATE: November 21, 2000.

ADDRESSES: Inquiries may be addressed

to Department of the Treasury,

Disclosure Services, Washington, DC

22020.

FOR FURTHER INFORMATION CONTACT: Dale

Underwood, Deputy Assistant Director,

Disclosure Services, (202) 622–0930.

SUPPLEMENTARY INFORMATION: The

Privacy Act of 1974, as amended, 5

U.S.C. 552a, authorizes the head of the

agency to promulgate rules in

accordance with the Administrative

Procedure Act to exempt Privacy Act

systems of records from certain

provisions of the Privacy Act, if the

system of records contains records

which fall within 5 U.S.C. 552a(j) and/

or (k).

The Department is amending this part

to consolidate the regulations issued