Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34085

the aircraft due to accretion of ice on the

airplane, accomplish the following:

Airplane Flight Manual

(a) Within 20 flight hours after the effective

date of this AD: Revise the Limitations and

Normal Procedures Sections of the FAAapproved Airplane Flight Manual (AFM) to

include the following procedures, as

specified in paragraphs (a)(1), (a)(2), (a)(3),

and (a)(4) of this AD. This may be

accomplished by inserting a copy of this AD

in the AFM.

(1) In the Limitations section under the

existing title ‘‘Operation in Icing

Conditions,’’ insert the following:

‘‘Autopilot use is prohibited when

atmospheric icing conditions exist, at the

first sign of icing accretion anywhere on the

airplane, or after the illumination of the Ice

Condition light, whichever occurs first.

Leading edge deicers switch must be

operated in the Heavy mode only.’’

(2) In the Normal Procedures section under

the existing title, ‘‘Operation in Icing

Conditions,’’ delete the following:

‘‘Leading edge deicers switch.......ON

Select ‘Heavy’ or ‘Light’ mode (1 or 3 minutes

cycle), based on the flight crew’s judgement

and evaluation of the severity of the ice

encounter and rate of accretion.’’

(3) In the Normal Procedures section under

the existing title, ‘‘Operation in Icing

Conditions,’’ insert the following:

‘‘Leading edge deicers switch.......On

(TIMER 1 or TIMER 2) Select ‘Heavy’ mode

if Light/Heavy switch is still installed.’’

(4) In the Normal Procedures section insert

the following warning:

‘‘WARNING: If large or frequent changes in

longitudinal trim, and/or excessive

performance degradation occur (identified by

large increases in power required to maintain

airspeed and altitude), immediately request

priority handling from air traffic control to

exit icing conditions.’’

Placard Installation

(b) Within 400 flight hours after the

effective date of this AD, install a placard to

activate the deicing boots and disengage the

autopilot, whenever ice is detected by visual

cues or ice detector illumination, to the left

of the pilot’s airspeed indicator and one

placard to the right of the co-pilot’s altimeter,

per EMBRAER Service Bulletin 120–25–

0258, dated May 14, 2001.

(c) Within 400 flight hours after the

effective date of this AD, remove the ‘‘LightHeavy’’ inflation switch of the leading edge

deicing boots, per EMBRAER Service

Bulletin 120–30–0032, Change No. 01, dated

June 13, 2001.

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, Atlanta

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, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

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) Except for the actions specified in

paragraph (a) of this AD, the actions shall be

done in accordance with EMBRAER Service

Bulletin 120–25–0258, dated May 14, 2001;

and EMBRAER Service Bulletin 120–30–

0032, Change No. 01, dated June 13, 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 Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Boulevard, suite 450, Atlanta,

Georgia; 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 Brazilian airworthiness directive 2001–05–

02, dated June 6, 2001.

Effective Date

(g) This amendment becomes effective on

July 12, 2001.

Issued in Renton, Washington, on June 20,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16047 Filed 6–22–01; 10:10 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–191–AD; Amendment

39–12291; AD 2001–13–11]

RIN 2120–AA64

Airworthiness Directives; Dassault

Model Falcon 10 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 Dassault Model Falcon

10 series airplanes. This action requires

an inspection to verify proper

installation of the pins in the dual nonreturn valves of the fire extinguishing

system for the engines, and replacement

of any defective valve with a new valve.

This action is necessary to prevent

failure of a fire extinguisher bottle to

discharge, which could result in the

inability to extinguish a fire in an

engine. This action is intended to

address the identified unsafe condition.

DATES: Effective July 12, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 12,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

July 27, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

191–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 the Internet must contain ‘‘Docket

No. 2001–NM–191–AD’’ in the subject

line and need not be submitted in

triplicate. Comments sent via fax or 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 Dassault

Falcon Jet, P.O. Box 2000, South

Hackensack, New Jersey 07606. 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,

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: The

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France recently notified

the FAA that an unsafe condition may

exist on all Dassault Model Falcon 10

series airplanes. The DGAC advises that,

during routine maintenance, when

removing a fire extinguishing bottle that

had accidentally discharged, it was

34086 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

found that the charge from the bottle

had been trapped in the discharge line.

Investigation revealed that a pin had not

been correctly installed in the nonreturn valve during manufacture. The

pin is normally located across the valve

body to prevent the shuttle-ball from

blocking the outlet to the engine. If the

pin is located too close to the edge of

the valve body, the shuttle-ball may

block the discharge outlet and prevent

the charge from releasing into the

engine during an engine fire. Such

conditions, if not corrected, could result

in the inability to extinguish a fire in an

engine.

Explanation of Relevant Service

Information

Dassault has issued Service Bulletin

F10–A291, dated June 1, 2001, which

describes procedures for an inspection

to verify proper installation of the pins

in the dual non-return valves of the fire

extinguishing system for the engines,

and replacement of any defective valve

with a new valve. A defective valve is

described as any valve with a pin found

outside the identified tolerance range.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directive T2001–219–

025(B), dated June 1, 2001, 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 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 failure of a fire extinguisher

bottle to discharge, which could result

in the inability to extinguish a fire in an

engine. This AD requires an inspection

to verify proper installation of the pins

in the dual non-return valves of the fire

extinguishing system for the engines,

and replacement of any defective valve

with a new valve. The actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Difference Between This AD, Service

Bulletin, and Foreign Airworthiness

Directive

This AD differs from the service

bulletin and the parallel French

airworthiness directive in that it

requires accomplishment of the

inspection within 10 days after the

effective date of this AD. In developing

an appropriate compliance time for this

AD, the FAA considered not only the

DGAC’s recommendation, but the

degree of urgency associated with

addressing the subject unsafe condition,

the average utilization of the affected

fleet, and the time necessary to perform

the inspection (one hour). In light of all

of these factors, the FAA finds a 10-day

compliance time for completing the

required actions to be warranted, in that

it represents an appropriate interval of

time allowable for affected airplanes to

continue to operate without

compromising safety.

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–191–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.

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.