[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] ----------------------------------------------------------------------- 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. ----------------------------------------------------------------------- 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