The Direction G n rale 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 designthat 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 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.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: