34800 Federal Register / Vol. 66, No. 127 / Monday, July 2, 2001 / Rules and Regulations

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 4: 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

(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 modification shall be done in

accordance with Airbus Service Bulletin

A300–29–6048, Revision 01, dated July 12,

2000; or Airbus Service Bulletin A310–29–

2086, Revision 01, dated July 12, 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 5: The subject of this AD is addressed

in French airworthiness directive 2000–284–

317(B), dated July 12, 2000.

Effective Date

(f) This amendment becomes effective on

August 6, 2001.

Issued in Renton, Washington, on June 21,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16201 Filed 6–29–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–194–AD; Amendment

39–12299; AD 2001–13–17]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2 and A300 B4; A300 B4–600,

B4–600R, and F4–600R (Collectively

Called A300–600); and A310 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 all Airbus Model A300 B2

and A300 B4; A300 B4–600, B4–600R,

and F4–600R (collectively called A300–

600); and A310 series airplanes. This

action requires revising the Airplane

Flight Manual to advise the flight crew

of appropriate procedures to follow in

the event of lost or erroneous airspeed

indications. This action is necessary to

prevent inadvertent excursions outside

the normal flight envelope. This action

is intended to address the identified

unsafe condition.

DATES: Effective July 17, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 17,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

August 1, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

194–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–194–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:

Tamra Elkins, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2669;

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

all Airbus Model A300 B2 and A300 B4;

A300 B4–600, B4–600R, and F4–600R

(collectively called A300–600); and

A310 series airplanes. The DGAC

advises that. Lost or erroneous airspeed

indications could result in lack of

sufficient information for the flight crew

to safely operate the airplane, and

consequent inadvertent excursions

outside the normal flight fenvelope.

Explanation of Relevant Service

Information

Airbus has issued the following

Temporary Revisions (TRs) to the FAAapproved A300, A300–600, and A310

Airplane Flight Manuals (AFMs). The

TRs provide updated procedures for the

flight crew to follow in the event of lost

or erroneous airspeed indications. The

TRs are listed in the following table:

Model/series Engine TR No. Date

A300 .......................................... GE CF6–50C 4.02.00/08 April 25, 2001.

A300 .......................................... GE CF6–50C2/C2R 4.02.00/09 April 26, 2001.

A300–600 .................................. GE CF6–80C2 4.02.00/11 March 21, 2000.

A300–600 .................................. PW 4000 4.02.00/13 March 28, 2000.

A310 .......................................... GE CF6–80A3 4.02.00/11 March 21, 2000.

A310 .......................................... GE CF6–80C2 4.02.00/12 March 22, 2000.

A310 .......................................... PW JT9D–7R4 4.02.00/13 March 23, 2000.

A310 .......................................... PW 4000 4.02.00/14 March 24, 2000.

Federal Register / Vol. 66, No. 127 / Monday, July 2, 2001 / Rules and Regulations 34801

The DGAC classified these TRs as

mandatory and issued French

airworthiness directive 2001–129(B),

dated April 4, 2001, to ensure 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 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 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 inadvertent excursions outside

the normal flight envelope in the event

of lost or erroneous airspeed

indications. This AD requires revising

the applicable FAA-approved AFMs to

advise the flight crew of appropriate

procedures to follow in the event of lost

or erroneous airspeed indications.

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 2001–NM–194–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:

2001–13–17 Airbus Industrie: Amendment

39–12299. Docket 2001–NM–194–AD.

Applicability: All Model A300 B2 and

A300 B4; A300 B4–600, B4–600R, and F4–

600R (collectively called A300–600); and

A310 series airplanes; certificated in any

category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent inadvertent excursions outside

the normal flight envelope in the event of lost

or erroneous airspeed indications,

accomplish the following:

Revision to Airplane Flight Manual (AFM)

(a) For Model A300 B2–1A series airplanes

equipped with General Electric CF6–50A

engines, and for Model A300 B4–600 series

airplanes equipped with Pratt & Whitney

JT9D–7R4H1 engines: Within 10 days after

the effective date of this AD, revise the

‘‘Procedures Following Failure’’ Section of

the FAA-approved AFM, in accordance with

a method approved by the Manager,

International Branch, ANM–116, Transport

Airplane Directorate, FAA.

(b) For all airplanes not identified in

paragraph (a) of this AD: Within 10 days after

the effective date of this AD, revise the

‘‘Procedures Following Failure’’ Section of

the applicable AFM by inserting into the

AFM a copy of the applicable Temporary

Revision (TR) listed in the following table:

34802 Federal Register / Vol. 66, No. 127 / Monday, July 2, 2001 / Rules and Regulations

TABLE 1.—TEMPORARY REVISIONS

Model/series Engine TR No. Date

A300 .......................................... GE CF6–50C 4.02.00/08 April 25, 2001.

A300 .......................................... GE CF6–50C2/C2R 4.02.00/09 April 26, 2001.

A300–600 .................................. GE CF6–80C2 4.02.00/11 March 21, 2000.

A300–600 .................................. PW 4000 4.02.00/13 March 28, 2000.

A310 .......................................... GE CF6–80A3 4.02.00/11 March 21, 2000.

A310 .......................................... GE CF6–80C2 4.02.00/12 March 22, 2000.

A310 .......................................... PW JT9D–7R4 4.02.00/13 March 23, 2000.

A310 .......................................... PW 4000 4.02.00/14 March 24, 2000.

(c) When the information in the applicable

TR listed in Table 1 of this AD has been

incorporated into the FAA-approved general

revisions of the AFM, the general revisions

may be incorporated into the AFM, and the

TR may be removed from the AFM.

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. 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,

ANM–116.

Note 1: 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 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 AFM revision required by

paragraph (b) of this AD shall be done in

accordance with A300 Flight Manual

Temporary Revision 4.02.00/08, dated April

25, 2001; A300 Flight Manual Temporary

Revision 4.02.00/09, dated April 26, 2001;

A300–600 Flight Manual Temporary

Revision 4.02.00/11, dated March 21, 2000;

A300–600 Flight Manual Temporary

Revision 4.02.00/13, dated March 28, 2000;

A310 Flight Manual Temporary Revision

4.02.00/11, dated March 21, 2000; A310

Flight Manual Temporary Revision 4.02.00/

12, dated March 22, 2000; A310 Flight

Manual Temporary Revision 4.02.00/13,

dated March 23, 2000; and A310 Flight

Manual Temporary Revision 4.02.00/14,

dated March 24, 2000; as applicable. (Only

page 2 of each Temporary Revision contains

the document date; no other page of these

documents contains this information.) 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 2: The subject of this AD is addressed

in French airworthiness directive 2001–

129(B), dated April 4, 2001.

Effective Date

(g) This amendment becomes effective on

July 17, 2001.

Issued in Renton, Washington, on June 21,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16199 Filed 6–29–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–09–AD; Amendment

39–12300; AD 2001–13–18]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Beech Models 45

(YT–34), A45 (T–34A, B–45), and D45

(T–34B) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This document supersedes

Airworthiness Directive (AD) 99–12–02,

which currently requires flight and

operating limitations on Raytheon

Aircraft Corporation (Raytheon) Beech

Models 45 (YT–34), A45 (T–34A, B–45),

and D45 (T–34B) airplanes. AD 99–12–

02 resulted from a report of an in-flight

separation of the right wing on a

Raytheon Beech Model A45 (T–34A)

airplane. The AD was issued as an

interim action until the development of

FAA-approved inspection procedures.

Raytheon has developed procedures to

inspect the wing spar assemblies of the

above-referenced airplanes. This AD

requires repetitive inspections of the

wing spar assembly for cracks with

replacement of any wing spar assembly

found cracked (unless the spar assembly

has a crack indication in the filler strip

where the direction of the crack is

toward the outside edge of the filler

strip). This AD also includes a reporting

requirement of the results of the initial

inspection and maintains the flight and

operating restrictions required by AD

99–12–02 until accomplishment of the

initial inspection. The actions specified

by this AD are intended to prevent wing

spar failure caused by fatigue cracks in

the wing spar assemblies and ensure the

operational safety of the abovereferenced airplanes.

DATES: This AD becomes effective on

August 16, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of August 16, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

Raytheon Aircraft Company, P.O. Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 625–7043 or (316) 676–

4556. You may examine this

information at FAA, Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

09–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul

Nguyen, Aerospace Engineer, FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone: (316) 946–4125; facsimile:

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

Has FAA taken any action to this

point? In-flight separation of the right

wing on a Raytheon Beech Model A45

(T34A) airplane caused FAA to issue

AD 99–12–02, Amendment 39–11193

(64 FR 31689, June 14, 1999). This AD

requires:

—Incorporating flight and operating

limitations that restrict the airplanes