[Federal Register Volume 63, Number 83 (Thursday, April 30, 1998)]
[Rules and Regulations]
[Pages 23659-23662]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11315]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-130-AD; Amendment 39-10507; AD 98-09-26]
RIN 2120-AA64


Airworthiness Directives; Dassault Model Falcon 2000 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Dassault Model Falcon 2000 series airplanes. 
This action requires revising the Airplane Flight Manual (AFM) to 
provide the flightcrew with procedures for monitoring and properly 
setting the fuel booster pump pressure; and repetitive visual 
inspections of the fuel lines to detect fatigue cracking and fuel 
leakage. This action also requires a one-time inspection of the fuel 
lines to detect cracking, replacement of any discrepant part with a new 
part, and installation of new brackets between the pressure

[[Page 23660]]

switch and the fuel pump of the numbers 1 and 2 engines, which 
constitutes terminating action for the repetitive inspections and the 
AFM revision. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified in this AD are intended to prevent 
fatigue cracking of the fuel line at the pressure switch pickoff point, 
which could result in fuel leakage and potential engine fire.

DATES: Effective May 15, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 15, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 1, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-130-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Dassault Model Falcon 
2000 series airplanes. The DGAC advises that it has received several 
reports of leakage of fuel from the engine fuel pressure switch line on 
the number 1 engine. The cause of the leaking was determined to be 
fatigue cracks caused by excessive vibrations of the pressure switch. 
Such fatigue cracking, if not corrected, could result in fuel leakage 
and potential engine fire.

Explanation of Relevant Service Information

    Dassault Aviation has issued Service Bulletin F2000-123 (F2000-28-
7), dated November 14, 1997, which describes procedures for a one-time 
dye penetrant inspection for fatigue cracking in the fuel lines; 
replacement of discrepant parts with new parts; and installation of new 
brackets between the pressure switch and the fuel pump of the numbers 1 
and 2 engines. Installation of new brackets, when accomplished, 
eliminates the need for the AFM revision. Accomplishment of the actions 
specified in the service bulletin is intended to adequately address the 
identified unsafe condition.
    The DGAC classified this service information as mandatory and 
issued French airworthiness directive 98-020-005(B), dated January 28, 
1998, 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 fatigue 
cracking of the fuel line at the pressure switch pickoff point, which 
could result in fuel leakage and potential engine fire. This AD 
requires:

--Revising the Limitations and Abnormal Procedures Sections of the AFM 
to provide the flightcrew with procedures for monitoring and properly 
setting the fuel booster pump pressure;
--Repetitive visual inspections of the fuel lines to detect fatigue 
cracking and fuel leakage, in accordance with the airplane maintenance 
manual; and
--a one-time dye penetrant inspection of the fuel lines to detect 
cracking; replacement of the fuel lines, if necessary; and installation 
of new brackets between the pressure switch and the fuel pump of the 
number 1 and 2 engines; in accordance with the service bulletin 
described previously. Accomplishment of the installation terminates the 
AFM revision and repetitive inspections.

Differences Between the Rule, Service Bulletin, and French 
Airworthiness Directive

    Operators should note that the service bulletin recommends 
accomplishing the one-time dye penetrant inspection and the 
installation ``at the first opportunity.'' The French airworthiness 
directive requires revising the AFM prior to further flight, and the 
one-time inspection and installation of brackets within 60 days. 
However, this AD differs from the service bulletin and French 
airworthiness directive in that it requires revising the AFM within 5 
days, and accomplishing the one-time inspection and installation within 
45 days.
    In developing appropriate compliance times for this AD, the FAA 
considered not only the recommendations of the manufacturer and the 
DGAC, 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 AFM revision, dye penetrant 
inspection, and installation. In light of all of these factors, the FAA 
finds a 5-day compliance time for accomplishing the AFM revision, and a 
45-day compliance time for initiating the required dye penetrant 
inspection and installation of new brackets to be warranted, in that 
those times represent appropriate intervals 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

[[Page 23661]]

suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    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 98-NM-130-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

98-09-26  Dassault Aviation: Amendment 39-10507. Docket 98-NM-130-
AD.

    Applicability: Model Falcon 2000 series airplanes; serial 
numbers 2 through 49 inclusive, and 51; 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 (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 fatigue cracking of the fuel line at the pressure 
switch pickoff point, which could result in fuel leakage and 
potential engine fire, accomplish the following:
    (a) Within 5 days after the effective date of this AD, revise 
the Limitations and Abnormal Procedures Sections of the FAA-approved 
Airplane Flight Manual (AFM) to include the following procedures, 
which will enable the flightcrew to monitor and properly set the 
fuel booster pump pressure. This may be accomplished by inserting a 
copy of this AD in the AFM.

``FILING INSTRUCTIONS

    Insert this page adjacent to page 3-160-1.

FUEL--LOW BOOSTER PUMP PRESSURE

    Until compliance with SB F2000-123, the paragraph ``If FUEL.. 
light remains on:'' is modified as follows:

________ If FUEL.. light remains on:                                    
   X-BP rotary switch..............  Closed                     
   X-BP light......................  Out-Checked                
   Associated fuel quantity          Monitored                  
   indicator.                                                           
   ESS/RH bus tie rotary switch....  Tied                       
   Associated engine power lever...  IDLE detent                
   Associated engine FUEL ENG        OFF                        
   switch.                                                              
   Associated engine FUEL SHUT-OFF   Actuated                   
   switch.                                                              
   Associated ENG ANTI-ICE switch..  Off                        
   Associated GEN switch...........  Off                        
________ If engine 2 is shutdown, complete                              
 the above procedure with:                                              
   HYDR 2 ISOL switch..............  OPEN''                     
                                                                        

    Note 2: The revision of the AFM required by this paragraph may 
be accomplished by inserting a copy of Falcon 2000 AFM Temporary 
Change No. 65 in the AFM. When this temporary change has been 
incorporated into general revisions of the AFM, the general 
revisions may be inserted in the AFM, provided the information 
contained in the general revision is identical to that specified in 
Falcon 2000 AFM Temporary Change No. 65.
    (b) Within 5 days after the effective date of this AD, perform a 
visual inspection of the fuel lines to detect fatigue cracking and 
fuel leakage, in accordance with Procedure 05.100 of Chapter 5.40 of 
Revision 4 of the Dassault Aviation Falcon 2000 Airplane Maintenance 
Manual.
    (1) If no discrepancy is detected, repeat the visual inspection 
daily thereafter until the requirements of paragraph (c) of this AD 
have been accomplished.
    (2) If any discrepancy is detected, prior to further flight, 
accomplish the requirements of paragraph (c) of this AD.
    (c) Within 45 days after the effective date of this AD, 
accomplish the actions specified in paragraphs (c)(1) and (c)(2) of 
this AD, in accordance with Dassault Aviation Service Bulletin 
F2000-123 (F2000-28-7), dated November 14, 1997.
    (1) Perform a one-time dye penetrant inspection of the fuel 
lines to detect cracking. If any cracking is detected, prior to 
further flight, replace the discrepant part with a new part, in 
accordance with the service bulletin. And
    (2) Install new brackets between the pressure switch and the 
fuel pump of each engine in accordance with the service bulletin. 
Accomplishment of this installation constitutes terminating action 
for the requirements of paragraphs (a) and (b) of this AD. Following 
accomplishment of paragraph (c) of this AD, the AFM revision 
required by paragraph (a) may be removed from the AFM.
    (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, 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR

[[Page 23662]]

21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.
    (f) Except as required by paragraph (b) of this AD, the actions 
shall be done in accordance with Dassault Aviation Service Bulletin 
F2000-123 (F2000-28-7), dated November 14, 1997. 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 4: The subject of this AD is addressed in French 
airworthiness directive 98-020-005(B), dated January 28, 1998.

    (g) This amendment becomes effective on May 15, 1998.

    Issued in Renton, Washington, on April 22, 1998.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11315 Filed 4-29-98; 8:45 am]
BILLING CODE 4910-13-U