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Airworthiness Directives; Dassault Model Fan Jet Falcon Series Airplanes and Model Mystere-Falcon 20 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

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AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Fan Jet Falcon series airplanes and Model Mystere-Falcon 20 series airplanes, that requires inspecting and testing for fatigue cracking due to stress corrosion in the vertical posts of the window frames in the flight compartment. This action is necessary to prevent fatigue cracking of the window frames, which could result in rapid depressurization of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.

DATES:

Effective October 25, 2004.

ADDRESSES:

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 Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html.

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FOR FURTHER INFORMATION CONTACT:

Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1137; fax (425) 227-1149.

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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 Dassault Model Fan Jet Falcon series airplanes and Model Mystere-Falcon 20 series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on June 17, 2004 (69 FR 33872). That action proposed to require inspecting and testing for fatigue cracking due to stress corrosion in the vertical posts of the window frames in the flight compartment. That action also proposed to add airplanes to the applicability, to clarify which airplanes must do certain actions, and to specify which window frames to ultrasonically inspect.

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.

Explanation of Change Made to Final Rule

We have changed paragraphs (a)(1) and (a)(2) of this final rule to specify that the actions shall be done in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Direction Generale de l'Aviation Civile (or its delegated agent). In addition, Dassault Aviation Work Card 53-30-12, titled “Endoscopic Inspection of the Frames of Pilot, Co-Pilot, and Front Glass Panels (Aircraft Not Changed Per SB No. 701),” of the Dassault Aviation Fan Jet Falcon Maintenance Manual, is listed as one approved method for doing the detailed (endoscopic) inspection specified in paragraph (a)(1) of this final rule. Additionally, Dassault Aviation Work Card 53-30-07, titled “Non-Destructive Ultrasonic Testing of Vertical Posts on Screw-Mounted Windows,” of the Dassault Aviation Fan Jet Falcon Maintenance Manual, is listed as one approved method of doing the ultrasonic test specified in paragraph (a)(2) of this final rule.

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact

The FAA estimates that 220 airplanes of U.S. registry will be affected by this AD, that it will take approximately 4 work hours per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $57,200, or $260 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

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.

For the reasons discussed above, I certify that this action (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Start Printed Page 56161Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

Start List of Subjects

List of Subjects in 14 CFR Part 39

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Adoption of the Amendment

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Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

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PART 39—AIRWORTHINESS DIRECTIVES

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1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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

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2004-19-02 Dassault Aviation: Amendment 39-13796. Docket 2002-NM-227-AD.

Applicability: All Model Fan Jet Falcon series airplanes and Model Mystere-Falcon 20 series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue cracking of the window frames in the flight compartment, which could result in rapid depressurization of the fuselage and consequent reduced structural integrity of the airplane, accomplish the following:

Inspection and Test of Flight Compartment Window Frames

(a) Do an inspection and test for stress corrosion and cracking as specified in paragraphs (a)(1) and (a)(2) of this AD, at the applicable time specified in paragraph (b) of this AD.

(1) For airplanes that have not accomplished the actions specified in Dassault Service Bulletin FJF-701, dated March 25, 1986; or Revision 1 dated October 22, 1987: Do a detailed inspection (using an endoscope) to detect stress corrosion and cracking of the window frames in the flight compartment, including the pilot, co-pilot, and front windows. Do the inspection in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Generale de l'Aviation Civile (DGAC) (or its delegated agent). Dassault Aviation Work Card 53-30-12, titled “Endoscopic Inspection of the Frames of Pilot, Co-Pilot, and Front Glass Panels (Aircraft Not Changed Per SB No. 701),” of the Dassault Aviation Fan Jet Falcon Maintenance Manual is one approved method.

(2) For all airplanes: Do an ultrasonic test for cracking in the posts of window frames 2, 5, 7, 8, and 10. Do the test in accordance with a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent). Dassault Aviation Work Card 53-30-07, titled “Non-Destructive Ultrasonic Testing of Vertical Posts on Screw-Mounted Windows,” of the Dassault Aviation Fan Jet Falcon Maintenance Manual is one approved method.

Note 1:

For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”

(b) Do the inspection and test required by paragraph (a) of this AD, at the times specified in paragraph (b)(1) or (b)(2) of this AD, as applicable.

(1) For airplanes having 35 or more years since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first; or having accumulated 20,000 or more total flight cycles as of the effective date of this AD: Within 7 months after the effective date of this AD.

(2) For airplanes not identified in paragraph (b)(1) of this AD: Within 25 months or 2,500 flight cycles after the effective date of this AD, whichever is first.

Repair

(c) If any stress corrosion or cracking is found during any inspection or test required by paragraph (a) of this AD: Before further flight, repair per a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).

Reporting Requirement

(d) At the applicable time specified in paragraph (d)(1) or (d)(2) of this AD: Submit a report of the findings (positive and negative) of the inspection required by paragraph (a) of this AD to: Dassault Falcon Jet, Attn: Service Engineering/Falcon 20, fax: (201) 541-4706, at the applicable time specified in paragraph (d)(1) or (d)(2) of this AD. The report must include the airplane serial number, number of landings, number of flight hours, airplane age, and the number and length of any cracks found. Submission of the Charts of Records (part of French airworthiness directive 2001-600-028(B), dated December 12, 2001), is an acceptable method of complying with this requirement. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.

(1) If the inspection was done after the effective date of this AD: Submit the report within 5 days after the inspection.

(2) If the inspection was done prior to the effective date of this AD: Submit the report within 5 days after the effective date of this AD.

Alternative Methods of Compliance

(e) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.

Note 2:

The subject of this AD is addressed in French airworthiness directive 2001-600-028(B), dated December 12, 2001.

Effective Date

(f) This amendment becomes effective on October 25, 2004.

Start Signature

Issued in Renton, Washington, on September 9, 2004.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 04-21051 Filed 9-17-04; 8:45 am]

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