Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Rules and Regulations 21859

Internal Inspection

(b) For Group 1 airplanes as listed in

Boeing Alert Service Bulletin 757–32A0135,

Revision 1, dated November 30, 2000: Within

8 years since the date of airplane delivery (for

MLG truck beams that have not been

overhauled), or since the date of installation

of new truck beams; or within 6 months after

the effective date of this AD; whichever

occurs latest: Perform an internal inspection

of the truck beam protective finish (plating

and primer) to detect discrepancies (flaked,

cracked, missing finish, or corrosion), as

illustrated in Figure 2 of the alert service

bulletin.

Corrective Action

(1) If no discrepancy is detected, prior to

further flight, apply corrosion preventive

compound in accordance with the

Accomplishment Instructions of the alert

service bulletin.

(2) If any discrepancy is detected, prior to

further flight, overhaul or replace the truck

beam, as applicable, in accordance with the

Accomplishment Instructions of the alert

service bulletin.

Note 3: Accomplishment of the internal

inspection and overhaul of the MLG truck

beam, as applicable, prior to the effective

date of this AD, in accordance with Boeing

Alert Service Bulletin 757–32A0135, dated

June 8, 2000, is considered acceptable for

compliance with the requirements 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 4: 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) The actions shall be done in accordance

with Boeing Alert Service Bulletin 757–

32A0135, Revision 1, dated November 30,

2000; or Boeing Alert Service Bulletin 757–

32A0138, Revision 1, dated November 30,

2000; as applicable. 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

June 6, 2001.

Issued in Renton, Washington, on April 20,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10466 Filed 5–1–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–200–AD; Amendment

39–12208; AD 2001–09–03]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 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 Model A330 series

airplanes. This action requires repetitive

inspections of the spars, rib, and

stringers in the vertical stabilizer spar

box for failure of the bonds to the skin,

and repair, if necessary. It also requires

modification of the vertical stabilizer

spar box by installation of fasteners to

reinforce the bonds to the skin, which

terminates the repetitive inspections.

This action is prompted by issuance of

mandatory continuing airworthiness

information. This action is necessary to

prevent failure of the bonds of the

vertical stabilizer spar box to the skin,

which could lead to reduced structural

integrity of the spar box. It is intended

to address the identified unsafe

condition.

DATES: Effective May 17, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 17,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 1, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket Number 2000–

NM–200–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

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–

anm–iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–200–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; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer, ANM–116,

International Branch, FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

certain Airbus Model A330 series

airplanes. The DGAC advises that there

have been findings of localized failure

of bonding of the spars, rib, and

stringers to the skin on several vertical

stabilizer spar boxes. This failure results

from contamination of the bonding

surface during the production process.

This condition, if not corrected, could

result in failure of the bonds of the

vertical stabilizer spar box to the skin,

which could lead to reduced structural

integrity of the spar box.

Explanation of Relevant Service

Information

Airbus has issued two service

bulletins pertinent to this unsafe

condition. Airbus Service Bulletin

A330–55A3025, Revision 01, dated

September 15, 2000, describes

procedures for initial and repetitive

ultrasonic inspections of the spars, rib,

and stringers of the vertical stabilizer

spar box for failure of the bonds to the

skin; and for repair of localized areas of

this debonding.

Airbus Service Bulletin A330–

55A3026, dated June 23, 2000, describes

procedures for installation of fasteners

21860 Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Rules and Regulations

to reinforce those areas which are

susceptible to failure of the bond

between the spars, rib, and stringers of

the vertical stabilizer spar box and the

skin. Accomplishment of the

installation eliminates the need for the

repetitive inspections.

Accomplishment of the actions

specified in these service bulletins is

intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directive 2000–427–

126(B), dated October 4, 2000, in order

to assure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

This airplane model is manufactured

in France 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,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, 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 the

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design that may be registered in the

United States at some time in the future,

this AD is being issued to prevent

failure of the bonds of the vertical

stabilizer spar box to the skin, resulting

in reduced structural integrity of the

spar box. This AD requires

accomplishment of the actions specified

in the service bulletins described

previously.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicability

of this rule currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this rule is

necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 2 to 70 work hours per

airplane, depending on its serial

number, to accomplish the required

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the inspection

is estimated to be between $120 and

$4,200 per airplane, per inspection

cycle.

In addition, it would take

approximately 20 to 822 work hours per

airplane, depending on its serial

number, to accomplish the required

terminating action at an average labor

rate of $60 per work hour. Required

parts would be provided by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the terminating action is estimated to

be between $1,200 to $49,320 per

airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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 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 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

summarizing each FAA-public contact

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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–2000–AD.’’

The postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted 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 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.

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:

Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Rules and Regulations 21861

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:

2001–09–03 Airbus Industrie: Amendment

39–12208. Docket 2000–NM–200–AD.

Applicability: Model A330 series airplanes,

certificated in any category; with serial

numbers as listed in Airbus Service Bulletin

A330–55A3026, dated June 23, 2000, or

A330–55A3025, Revision 01, dated

September 15, 2000.

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

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the bonds of the

spars, the rib, and the stringers of the vertical

stabilizer spar box to the skin, which could

lead to reduction in the structural integrity of

the spar box, accomplish the following:

Inspections

(a) Within 650 flight cycles from the

previous inspection performed prior to the

effective date of this AD, in accordance with

Airbus All Operators Telex (AOT) A330–

55A3025, dated April 19, 2000, or 60 days

after the effective date of this AD, whichever

occurs later: Perform an ultrasonic inspection

of the spars, the rib, and the stringers of the

vertical stabilizer spar box for failure of the

bonds to the skin, in accordance with Airbus

Service Bulletin A330–55A3025, Revision 01,

dated September 15, 2000. Repeat the

ultrasonic inspection at intervals not to

exceed 650 flight cycles until the

accomplishment of paragraph (c) of this AD.

Note 2: The ultrasonic inspection need not

include those areas of the spars, the rib, and

the stringers of the vertical stabilizer spar box

which have previously been repaired or

modified.

Repairs

(b) Perform applicable repairs, as shown in

Table 1, as follows:

TABLE 1.—REPAIRS

If, during any inspection required by

paragraph (a)—

Then—

(1) No failure of the

bonds is detected.

No repair is required.

TABLE 1.—REPAIRS—Continued

If, during any inspection required by

paragraph (a)—

Then—

(2) A single area of

failed bonding is

detected, and it is

smaller than 300

mm 2.

No repair is required.

(3) A single area of

failed bonding is

detected, and it is

at least 300 mm 2

but less than 2,000

mm 2.

Prior to further flight,

perform a local repair per Airbus

Service Bulletin

A330–55A3025,

Revision 01, dated

September 15,

2000.

(4) A single area of

failed bonding is

detected, and it is

at least 2,000 mm 2,

or multiple areas of

failed bonding are

detected at one

specific component.

Prior to further flight,

perform a repair

per Airbus Service

Bulletin A330–

55A3025, Revision

01, dated September 15, 2000.

Terminating Action

(c) Within 5 years of the date of

manufacture of the airplane: Install fasteners

to the spars, the rib, and the stringers of the

vertical stabilizer spar box, in accordance

with Airbus Service Bulletin A330–55A3026,

dated June 23, 2000. Accomplishment of the

installation terminates the repetitive

inspection required by paragraph (a) of this

AD.

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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, International

Branch, ANM–116.

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.

Incorporation by Reference

(f) The actions shall be done in accordance

with Airbus Service Bulletin A330–55A3025,

Revision 01, dated September 15, 2000, and

Airbus Service Bulletin A330–55A3026,

dated June 23, 2000; as applicable. 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 Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. 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.

Note 4: The subject of this AD is addressed

in French airworthiness directive 2000–427–

126(B), dated October 4, 2000.

Effective Date

(g) This amendment becomes effective on

May 17, 2001.

Issued in Renton, Washington, on April 20,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10464 Filed 5–1–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF HEALTH AND

HUMAN SERVICES

Food and Drug Administration

21 CFR Part 558

New Animal Drugs for Use in Animal

Feeds; Monensin, Sulfadimethoxine,

and Ormetoprim; Technical

Amendment

AGENCY: Food and Drug Administration,

HHS.

ACTION: Final rule; technical

amendment.

SUMMARY: The Food and Drug

Administration (FDA) is updating the

animal drug regulations for medicated

feeds to correctly reflect previously

approved assay limits for Type A

medicated articles containing monensin,

or sulfadimethoxine and ormetoprim in

combination. This action is being taken

to improve the accuracy of the agency’s

regulations.

DATES: This rule is effective May 2,

2001.

FOR FURTHER INFORMATION CONTACT:

Mary G. Leadbetter, Center for

Veterinary Medicine (HFV–143), Food

and Drug Administration, 7500 Standish

Pl., Rockville, MD 20855, 301–827–

6964.

SUPPLEMENTARY INFORMATION: FDA has

found that the April 1, 2000, edition of

Title 21, Parts 500 to 599 of the Code of

Federal Regulations (CFR) does not

reflect revised assay limits for Type A

medicated articles containing monensin,

or sulfadimethoxine and ormetoprim in

combination, that were approved in the

new animal drug applications for these

drugs. At this time, FDA is amending

the regulations to correct these errors in

21 CFR 558.4.