13424 Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations

reference was approved 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 Sikorsky Aircraft Corporation,

Attn: Manager, Commercial Tech Support,

6900 Main Street, Stratford, Connecticut

06614, phone (203) 386–3001, fax (203) 386–

5983. 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.

(g) This amendment becomes effective on

March 21, 2001, to all persons except those

persons to whom it was made immediately

effective by Emergency AD 2001–03–51,

issued January 30, 2001, which contained the

requirements of this amendment.

Issued in Fort Worth, Texas, on February

20, 2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–5165 Filed 3–5–01; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–01–AD; Amendment

39–12141; AD 2001–05–05]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

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 detailed visual inspections to

find discrepancies of the installation of

the midspar fuse pins of the inboard and

outboard struts, and follow-on actions,

if necessary. This action also provides

for an optional terminating modification

for the repetitive inspections. This

action is necessary to find and fix

discrepancies of the installation of the

midspar fuse pins, which could result in

loss of the secondary retention

capability of the fuse pins, migration of

the fuse pins, and consequent loss of the

strut and engine from the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective March 21, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 21,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

May 7, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

01–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. 2001–NM–01–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 several reports indicating

that, during routine maintenance, loose

primary retention nuts of the midspar

fuse pins of the inboard and outboard

struts were found on certain Boeing

Model 747 series airplanes. One report

indicated that the primary retention nut

migrated into the secondary retention

washer. The cause of these

discrepancies was determined to be

inadequate run-on torque of the primary

retention nut. Such conditions, if not

fixed, could result in the loss of

secondary retention capabilities of the

fuse pins, migration of the fuse pins,

reduction of the joint capability of the

midspar fittings to carry the design

loads, and consequent loss of the strut

and engine from the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 747–54A2206,

Revision 1, dated February 22, 2001,

which describes procedures for

repetitive detailed visual inspections to

find discrepancies (incorrect thread

protrusion, which is less than two

threads protruding from the nut

between the nut and the secondary

retention washer; incorrect gap between

the fuse pin primary nut and secondary

retention washer; cracked or broken

torque stripe) of the installation of the

midspar fuse pins of the inboard and

outboard struts, and follow-on actions,

if necessary.

If the primary nut has backed off and

is contacting the secondary retention

washer; the follow-on actions include,

but are not limited to:

• Inspection of the fuse pin threads for

damage,

• Installation of a new primary nut,

• Replacement of damaged fuse pins

with new pins, and

• Installation of a torque stripe.

If the primary nut has backed off and

is not contacting the secondary

retention washer, follow-on actions

consist of repeating the inspection of the

fuse pin installation at a reduced

inspection interval.

The service bulletin also provides for

an optional terminating modification

which consists of replacement of the

primary nut of the midspar fuse pin

with a new nut and installation of the

torque stripe, a detailed visual

inspection of the fuse pin threads for

damage, and replacement of the fuse

pin, if necessary, Doing these actions

ends the repetitive inspections.

Other Relevant Rulemaking

This AD is related to AD 95–10–16,

amendment 39–9233 (60 FR 27008, May

22, 1995); AD 95–13–05, amendment

39–9285 (60 FR 33333, June 28, 1995);

AD 95–13–06, amendment 39–9286 (60

FR 33338, June 28, 1995); AD 95–13–07,

amendment 39–9287 (60 FR 33336, June

28, 1995), and AD 99–10–10,

amendment 39–11163 (64 FR 25197,

May 11, 1999). The replacement of fuse

pins in the upper link, midspar fittings,

and diagonal brace of the nacelle strut

with new corrosion-resistant pins is

required by those AD’s as part of the

modification of the nacelle strut/wing

structure for earlier Model 747 series

airplanes. The actions required by this

AD are to be done if any of the AD’s

specified above, or the production

equivalent, has been accomplished.

Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations 13425

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, this AD requires

accomplishment of the actions specified

in the service bulletin described

previously.

Interim Action

This is considered to be interim

action. The FAA is currently

considering requiring the optional

terminating modification, which will

constitute terminating action for the

repetitive inspections required by this

AD action. However, the planned

compliance time for the installation of

the modification is sufficiently long so

that notice and opportunity for prior

public comment will be practicable.

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 2001–NM–01–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

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:

2001–05–05 Boeing: Amendment 39–12141.

Docket 2001–NM–01–AD.

Applicability: Model 747 series airplanes,

as listed in Boeing Service Bulletin 747–

54A2206, Revision 1, dated February 22,

2001, 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 per

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 find and fix discrepancies of the

installation of the midspar fuse pins of the

inboard and outboard strut, which could

result in loss of the secondary retention

capability of the fuse pins, migration of the

fuse pins, and consequent loss of the strut

and engine from the airplane; accomplish the

following:

Inspections/Follow-On Actions

(a) At the latest of the times specified in

paragraphs (a)(1) and (a)(2) of this AD, as

applicable: Do a detailed visual inspection to

find discrepancies (incorrect thread

protrusion, which is less than two threads

protruding from the nut between the nut and

the secondary retention washer; incorrect gap

between the fuse pin primary nut and

secondary retention washer; cracked or

broken torque stripe) of the installation of the

midspar fuse pins of the inboard and

outboard struts, per Figure 2 of Boeing

Service Bulletin 747–54A2206, Revision 1,

dated February 22, 2001.

(1) For airplanes not modified per one of

the AD’s listed in Table 1 of this AD: Do the

inspection at the later of the times specified

in paragraphs (a)(1)(i) and (a)(1)(ii) of this

AD:

(i) Before the accumulation of 8,000 total

flight hours, or within 24 months since

manufacture of the airplane, whichever

occurs first.

(ii) Within 90 days after the effective date

of this AD.

(2) For airplanes modified per one of the

AD’s listed in Table 1 of this AD: Do the

inspection at the later of the times specified

13426 Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations

in paragraphs (a)(2)(i) and (a)(2)(ii) of this

AD. Table 1 follows:

TABLE 1

AD No. Amendment

No.

AD 95–16–16 ............................ 39–9233

AD 95–13–05 ............................ 39–9285

AD 95–13–06 ............................ 39–9286

AD 95–07 .................................. 39–9287

AD 99–10–10 ............................ 39–11163

(i) Within 8,000 flight hours, or within 24

months since doing the modification,

whichever occurs first.

(ii) Within 90 days after the effective date

of this AD.

Note 2: Where there are differences

between the AD and the service bulletin, the

AD prevails.

Note 3: 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.’’

(A) If no discrepancy is found: Repeat the

inspection at intervals not to exceed 8,000

flight hours or 24 months, whichever is first,

until you do the terminating modification

specified in paragraph (b) of this AD.

(B) If any discrepancy is found, and the

primary nut has backed off and contacts the

secondary retention washer: Before further

flight, do the terminating modification

specified in paragraph (b) of this AD.

(C) If any discrepancy is found, and the

primary nut does not contact the secondary

retention washer: Repeat the inspection at

intervals not to exceed 90 days. Within 18

months after the initial finding, or the

effective date of this AD, whichever occurs

later, do the terminating modification

specified in paragraph (b) of this AD.

Note 4: Inspections accomplished prior to

the effective date of this AD per Boeing Alert

Service Bulletin 747–54A2206, dated October

19, 2000, are acceptable for compliance with

the inspections required by paragraph (a) of

this AD.

Optional Terminating Action

(b) Doing the terminating modification

(replacement of the primary nut of the

midspar fuse pin with a new nut, installation

of torque stripe, a detailed visual inspection

of the fuse pin threads for damage, and

replacement, if necessary) per Figure 3 of

Boeing Service Bulletin 747–54A2206,

Revision 1, dated February 22, 2001, ends the

repetitive inspections required by this AD.

Note 5: Accomplishment of the terminating

action specified in Boeing Alert Service

Bulletin 747–54A2206, dated October 19,

2000, is 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

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, Seattle ACO.

Note 6: 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 per

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 per Boeing

Service Bulletin 747–54A2206, Revision 1,

dated February 22, 2001. This incorporation

by reference was approved by the Director of

the Federal Register per 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

March 21, 2001.

Issued in Renton, Washington, on February

26, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–5168 Filed 3–5–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF HEALTH AND

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 510

New Animal Drugs; Change of Sponsor

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 for three approved

new animal drug applications (NADA’s)

from PM Ag Products, Inc., to Sweetlix,

LLC.

DATES: This rule is effective March 6,

2001.

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: PM Ag

Products, Inc., 1055 West 175th St.,

Homewood, IL 60430, has informed

FDA that it has transferred ownership

of, and all rights and interests in NADA

033–773 for Sweetlix Bloat Guard Block,

NADA 109–471 for Staley Sweetlix with

Rumensin, and NADA 136–214 for

Enproal Bloat Blox to Sweetlix, LLC,

175 South Main St., suite 150, Salt Lake

City, UT 84111. Accordingly, the agency

is amending the regulations in 21 CFR

510.600(c)(1) and (c)(2) to reflect the

transfer of ownership. The agency is

removing the sponsor name for PM Ag

Products, Inc., because the firm no

longer is the holder of any approved

NADA’s, and the drug labeler code

assigned to PM Ag Products, Inc., is

being retained as the drug labeler code

for Sweetlix, LLC.

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 removing

the entry for ‘‘PM Ag Products, Inc.’’

and by alphabetically adding an entry

for ‘‘Sweetlix, LLC ’’ and in the table in

paragraph (c)(2) by revising the entry for

‘‘036904 ’’ to read as follows:

§ 510.600 Names, addresses, and drug

labeler codes of sponsors of approved

applications.

* * * * *

(c) * * *

(1) * * *