Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34087

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:

2001–13–11 Dassault Aviation [Formerly

Avions Marcel Dassault-Breguet Aviation

(AMD/BA)]: Amendment 39–12291.

Docket 2001–NM–191–AD.

Applicability: All Model Falcon 10 series

airplanes, 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 failure of a fire extinguisher

bottle to discharge, which could result in the

inability to extinguish a fire in an engine,

accomplish the following:

Inspection/Replacement

(a) Within 10 days after the effective date

of this AD: Do an inspection to verify proper

installation of the pins in the dual non-return

valves of the fire extinguishing system for the

engines, per the Accomplishment

Instructions of Dassault Service Bulletin

F10–A291, dated June 1, 2001. Before further

flight, replace any defective valve (pin

outside the identified tolerance range) with a

new valve per the service bulletin.

Spares

(b) As of the effective date of this AD, no

person shall install a dual non-return valve,

part number 39299500, on any airplane,

unless it has been inspected per paragraph (a)

of this AD; the pin is within the specified

tolerance range; and the valve is marked with

a ‘‘C,’’ per Figure 1 of the Accomplishment

Instructions of Dassault Service Bulletin

F10–A291, dated June 1, 2001.

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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. 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 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

(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 inspection and replacement shall

be done in accordance with Dassault Service

Bulletin F10–A291, dated June 1, 2001. 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

Dassault Falcon Jet, P.O. Box 2000, South

Hackensack, New Jersey 07606. 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 T2001–

219–025(B), dated June 1, 2001.

Effective Date

(f) This amendment becomes effective on

July 12, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15938 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–12–AD; Amendment

39–12290; AD 2001–13–10]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

2000 series airplanes, that requires

testing of certain components of the

emergency pitch trim system (EPTS),

and corrective action, if necessary. The

actions specified by this AD are

intended to prevent faulty activation of

the emergency pitch trim actuator

(EPTA), which could cause damage to

the elevator front spar, resulting in

reduced structural integrity of the

elevator and a non-functioning EPTS.

This action is intended to address the

identified unsafe condition.

DATES: Effective August 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈aping,

Sweden. 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: Dan

Rodina, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

fax (425) 227–1149.

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 Saab Model

SAAB 2000 series airplanes was

published in the Federal Register on

May 2, 2001 (66 FR 21892). That action

proposed to require testing of certain

components of the emergency pitch trim

system (EPTS), and corrective action, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

34088 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

Cost Impact

The FAA estimates that 3 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 2 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$360, or $120 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.

For the reasons discussed above, I

certify that this action (1) Is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 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:

2001–13–10 Saab Aircraft AB: Amendment

39–12290. Docket 2001–NM–12–AD.

Applicability: Model SAAB 2000 series

airplanes, certificated in any category, serial

numbers –004 through –063, inclusive.

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 (b) 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 faulty activation of the

emergency pitch trim actuator (EPTA), which

could cause damage to the elevator front

spar, resulting in reduced structural integrity

of the elevator and a non-functioning

emergency pitch trim system (EPTS),

accomplish the following:

Testing and Corrective Actions

(a) Within 400 flight hours from the

effective date of this AD, perform a

functional test of the EPTS in accordance

with Saab Service Bulletin 2000–27–046,

dated November 30, 2000. If the left or right

EPTA is not working according to the

functional test, before further flight, check

the wiring and perform all applicable followon corrective actions, in accordance with

paragraph 2. C. of Saab Service Bulletin

2000–27–046, dated November 30, 2000.

Alternative Methods of Compliance

(b) 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 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

(c) 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

(d) The actions shall be done in accordance

with Saab Service Bulletin 2000–27–046,

dated November 30, 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 Saab Aircraft AB, SAAB

Aircraft Product Support, S–581.88,

Linko ̈aping, Sweden. 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 Swedish airworthiness directive 1–162,

dated November 30, 2000.

Effective Date

(e) This amendment becomes effective on

August 1, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15937 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–374–AD; Amendment

39–12289; AD 2001–13–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2–1C, B2–203, B2K–3C, B4–2C,

B4–103, and B4–203 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300

B2–1C, B2–203, B2K–3C, B4–2C, B4–

103, and B4–203 series airplanes, that

requires a one-time inspection of the

space between the fuel quantity

indication (FQI) probes and any

adjacent structures for minimum

clearance, and corrective action, if

necessary. The actions specified by this

AD are intended to prevent the

possibility of electrical arcing to the fuel

tank if the airplane should be struck by