[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
