22908 Federal Register / Vol. 66, No. 88 / Monday, May 7, 2001 / Rules and Regulations

§ 9.35 Duplication fees.

(a)(1) The charges by the duplicating

service contractor for the duplication of

records made available under § 9.21 at

the NRC Public Document Room (PDR),

One White Flint North, 11555 Rockville

Pike, Room O–1F23, Rockville, MD. are

as follows:

(i) Paper-to-paper reproduction is

$0.15 per page for standard size (up to

11′′ × 14′′). Pages 11′′ × 17′′ are $0.30 per

page. Pages larger than 11′′ × 17′′,

including engineering drawings, are

$2.50 per square foot.

(ii) Color drawings are $2.00 per 81⁄2′′

× 11′′ page. Pages larger than 81⁄2′′ × 11′′

are $12.00 per square foot.

(iii) Microfiche-to-paper reproduction

is $0.15 per page. Aperture cards are

$2.50 per square foot.

(iv) The charges for Electronic Full

Text (EFT) (ADAMS documents)

copying are as follows:

(A) Electronic Full Text (EFT) copying

of ADAMS documents to paper (applies

to images, OCR TIFF, and PDF text) is

$0.15 per page.

(B) Electronic Full Text (EFT) copying

of ADAMS documents to CD–ROM is

$10.00 for the first document on the

CD–ROM and $5.00 for each additional

document per accession number on the

same CD–ROM.

(C) CD–ROM-to-paper reproduction is

$0.15 per page.

(v) Priority rates (rush processing) are

as follows:

(A) The priority rate is offered for

standard size paper-to-paper

reproduction, microfiche-to-paper

reproduction, electronic full text (EFT)

copying of ADAMS documents to paper,

and CD–ROM-to-paper production at

$0.20 per page. The priority rate for

standard size color prints is $2.50 per

print. The priority rate for color

drawings larger than 81⁄2′′ × 11′′ is

$15.00 per square foot.

(B) The priority rate for aperture cards

is $3.50 per square foot. The priority

rate for electronic full text (EFT) to CD–

ROM is $15.00 for the first document on

the CD–ROM and $7.50 per each

additional document on the same CD–

ROM.

(vi) Facsimile charges are $0.30 per

page for local calls; $0.50 per page for

U.S. long distance calls, and $1.00 per

page for foreign long distance calls.

* * * * *

Dated in Rockville, Maryland, this 25th

day of April 2001.

For the Nuclear Regulatory Commission.

William D. Travers,

Executive Director for Operations.

[FR Doc. 01–11387 Filed 5–4–01; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–68–AD; Amendment

39–12210; AD 2001–09–05]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310–324, A310–325, and A300 B4–

622R Series Airplanes Equipped with

Pratt & Whitney PW4000 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 Airbus Model

A310–324, A310–325, and A300 B4–

622R series airplanes equipped with

Pratt & Whitney PW4000 series engines.

This action requires revising the

Airplane Flight Manuals (AFM) for the

Model A310 and Model A300–600

series airplanes. This action is necessary

to prevent acceleration and climb

performance less than that specified in

the AFM, which could result in runway

overruns or impact with obstacles or

terrain. This action is intended to

address the identified unsafe condition.

DATES: Effective May 22, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 22,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 6, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket Number 2001–

NM–68–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. 2001–NM–68–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 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: Tim

Backman, Aerospace Engineer, ANM–

116, International Branch, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2797;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA

has received reports that Pratt &

Whitney Model PW4000 series engines

with certain early-production fan blades

(Phase 0/1, FB2B or FB2T) installed on

Airbus Model A310–324, A310–325,

and A300 B4–622R series airplanes do

not produce the amount of thrust

indicated in the AFM. This thrust

shortfall is due to erosion of the fan

blade’s leading edge. The flight crew has

no indication of this shortfall in thrust.

This condition results in acceleration

and climb performance less than that

specified in the AFM, which, if not

corrected, could result in an overrun of

the runway or impact with an obstacle

or terrain.

Explanation of Relevant Service

Information

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France, has

requested that Airbus prepare revisions

to the AFM to take into account the

reduction in performance associated

with PW4000 series engines fitted with

early-production fan blades and to

incorporate the necessary adjustments

in performance. Those revisions are

expected to be available from Airbus in

mid-2001. Meanwhile, Airbus has

issued the following Temporary

Revisions (TR) to the AFM, each dated

January 22, 2001:

A310 Flight Manual TR 5.03.00/01 (for

Airbus Model A310–324 series airplanes);

A310 Flight Manual TR 5.03.00/02 (for

Airbus Model A310–325 series airplanes);

and

A300–600 Flight Manual TR 5.03.00/01 (for

Airbus Model A300 B4–622R series

airplanes).

These TR’s contain performance

adjustments for the AFM for Model

A310–324, A310–325, and A300 B4–

622R series airplanes equipped with one

or more Pratt & Whitney Model PW4000

series engine with early-production fan

blades. The DGAC classified these TR’s

as mandatory and issued French

airworthiness directive 2001–086(B),

Federal Register / Vol. 66, No. 88 / Monday, May 7, 2001 / Rules and Regulations 22909

dated March 7, 2001, in order to assure

the continued airworthiness of these

airplanes in France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of § 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 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, this AD is being issued to

prevent acceleration and climb

performance less than that specified in

the AFM, which could result in runway

overruns or impact with obstacles or

terrain. This AD requires revising the

Performance section of the FAAapproved AFM’s for Model A310–324,

A310–325, and 300 B4–622R series

airplanes to incorporate certain

adjustments in performance.

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–68–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:

2001–09–05 Airbus Industrie: Amendment

39–12210. Docket 2001–NM–68–AD.

Applicability: Model A310–324, A310–325,

and A300 B4–622R series airplanes;

certificated in any category; equipped with

Pratt & Whitney PW4000 series engines,

except for airplanes fitted with currentproduction FB2C fan blades (Phase 3 fan

blades) on both engines.

Note 1: Airbus Modification 10925 installs

Phase 3 engines, and these are equipped with

FB2C (Phase 3) fan blades. Therefore, this AD

is not applicable to airplanes with that

modification.

Compliance: Required as indicated, unless

accomplished previously.

To prevent acceleration and climb

performance less than that specified in the

Airplane Flight Manual (AFM), which could

result in runway overruns or impact with

obstacles or terrain, accomplish the

following:

AFM Revision

(a) For Model A310–324 and –325 series

airplanes: Within 30 days after the effective

date of this AD, revise the FAA-approved

AFM to incorporate specified adjustments in

performance by inserting the following

Airbus A310 Flight Manual Temporary

Revisions (TR), all dated January 22, 2001, as

applicable, into the Performance section of

the AFM: 5.03.00/01 (for Airbus Model

A310–324 series airplanes); or 5.03.00/02 (for

Airbus Model A310–325 series airplanes).

(b) For Model A300 B4–622R series

airplanes: Within 30 days after the effective

date of this AD, revise the FAA-approved

AFM to incorporate specified adjustments in

performance by inserting the following

A300–600 Flight Manual TR, dated January

22, 2001 into the Performance section of the

AFM: 5.03.00/01 (for Airbus Model A300 B4–

622R series airplanes).

(c) When the information in the TR’s

specified in paragraphs (a) and (b) of this AD,

has been incorporated into FAA-approved

general revisions of the applicable AFM’s,

22910 Federal Register / Vol. 66, No. 88 / Monday, May 7, 2001 / Rules and Regulations

the general revisions may be incorporated in

the applicable AFM, and the TR’s may be

removed from the AFM’s.

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 Operations Inspector, who

may add comments and then send it to the

Manager, International Branch.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with §§ 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 A310 Flight Manual Temporary

Revision 5.03.00/01, dated January 22, 2001;

Airbus A310 Flight Manual Temporary

Revision 5.03.00/02, dated January 22, 2001;

and Airbus A300–600 Flight Manual

Temporary Revision 5.03.00/01, dated

January 22, 2001; as applicable. (Note: Only

the first page to each of these Temporary

Revisions are date stamped; no other pages

of the Temporary Revisions contain the

revision date.) 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 3: The subject of this AD is addressed

in French airworthiness directive 2001–

086(B), dated March 7, 2001.

Effective Date

(g) This amendment becomes effective on

May 22, 2001.

Issued in Renton, Washington, on April 23,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10591 Filed 5–4–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–74–AD; Amendment

39–12219; AD 2001–09–12]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727–100, –100C, and –200 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 727–

100, –100C, and –200 series airplanes,

that, for certain airplanes, requires a

one-time inspection of certain fuselage

circumferential skin joints to determine

the type of fasteners installed, and

replacement of any aluminum fasteners

with steel fasteners, if necessary; or

modification of certain fuselage

circumferential skin joints; as

applicable. For certain other airplanes,

this amendment also requires repetitive

inspections to detect corrosion, sealant

deterioration, cracking, or disbonding;

repair, if necessary; and modification of

certain fuselage circumferential skin

joints. This amendment is prompted by

reports of corrosion between the body

skins and cold-bonded doublers at the

fuselage circumferential skin joints. The

actions specified by this AD are

intended to prevent delamination of the

cold-bonded doublers, which could

result in corrosion of the body skins and

doublers, and consequent reduced

structural capability of the fuselage

circumferential skin joints.

DATES: Effective June 11, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 11,

2001.

ADDRESSES: 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

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 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: Walt

Sippel, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2774;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 727–100, –100C, and –200 series

airplanes was published in the Federal

Register on December 6, 1999 (64 FR

68062). For certain airplanes, that action

proposed to require a one-time

inspection of certain fuselage

circumferential skin joints to determine

the type of fasteners installed, and

replacement of any aluminum fasteners

with steel fasteners, if necessary; or

modification of certain fuselage

circumferential skin joints; as

applicable. For certain other airplanes,

that action also proposed to require

repetitive inspections to detect

corrosion, sealant deterioration,

cracking, or disbonding; repair, if

necessary; and modification of certain

fuselage circumferential skin joints.

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.

Request To Delete Certain Sections of

Proposed AD

One commenter requests that Boeing

Model 727 series airplanes, line

numbers 153, 339, 416, and 540, be

deleted from the applicability section of

the proposed AD; and that paragraphs

(c) and (d) of the proposal, which apply

only to those airplanes, also be deleted.

The commenter states that the

manufacturer of those airplanes has

determined that they cannot be

repaired, and they were taken out-ofservice.

The FAA does not concur with the

commenter’s request; however, the FAA

agrees with the commenter’s intent. Part

39 of the Federal Aviation Regulations

(14 CFR part 39) states that, ‘‘No person

may operate a product to which an

airworthiness directive applies except

in accordance with the requirements of

that airworthiness directive.’’ The Part

39 regulation provides compliance relief

for airplanes that are not being operated,

because affected airplanes need only be

in compliance prior to return to

operation. In light of this fact, the

airplanes having the line numbers listed

above have been deleted from the Cost

Impact paragraph, below; however, the

applicability section and paragraphs (c)

and (d) will remain in the final rule