AD 99-14-07

This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000 series airplanes; and certain Dassault Model 900EX, and Mystere Falcon 900 series airplanes, that requires repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new jackscrews; repetitive measurement of the screw/nut play to detect discrepancies; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent jamming of the flap jackscrews, which could result in the inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane.

Final rule

99-14-07 DASSAULT AVIATION [Formerly Avions Marcel Dassault-Breguet Aviation (AMD/BA)]: Amendment 39-11218. Docket 99-NM-63-AD.
Applicability: All Model Falcon 2000 series airplanes; Falcon 900EX series airplanes, serial numbers 04 and subsequent; and Mystere Falcon 900 series airplanes, serial numbers 161 and subsequent; 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 jamming of the flap jackscrews, which could result in inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane, accomplish the following:

Repetitive Operational Test
(a) Within 5 flight cycles after the effective date of this AD: Perform an operational test of the flap asymmetry detection system to ensure that the system is functioning correctly, in accordance with the procedures specified in Falcon 2000 Airplane Maintenance Manual (AMM) 27-502, dated November 1995; Falcon 900 AMM 27-502, dated January 1995; or Falcon 900EX AMM 27-502, dated September 1996, as applicable. Prior to further flight, repair any discrepancy detected in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (or its delegated agent). Repeat the operational test thereafter at intervals not to exceed 330 flight hours or 7 months, whichever occurs first.

Repetitive Replacement
(b) Prior to the accumulation of 1,000 total flight cycles on the inboard flap jackscrews, or within 25 flight cycles after the effective date of this AD, whichever occurs later: Replace the inboard flap jackscrews with new jackscrews in accordance with the procedures specified in Falcon 2000 AMM 27-510, dated November 1995; Falcon 900 AMM 27-521, dated December 1998; or Falcon 900EX AMM 27-510, dated September 1996, as applicable. Repeat the replacement thereafter at intervals not to exceed 1,000 flight cycles.

Repetitive Inspection
(c) Prior to the accumulation of 1,000 total flight cycles on the outboard and center flap jackscrews, or within 25 flight cycles after the effective date of this AD, whichever occurs later: Measure the screw/nut play of the outboard and center flap jackscrews to detect discrepancies, in accordance with the procedures specified in Falcon 2000 AMM, Temporary Revision (TR) 27-504, dated October 1998; Falcon 900 AMM, TR 27-514, dated February 1999; or Falcon 900EX AMM, TR 27-514, dated February 1999, as applicable.

NOTE 2: The AMM revisions required by paragraph (c) of this AD may be accomplished by inserting a copy of the TR's into the applicable AMM. When these TR's have been incorporated into the general revisions of the AMM, the general revisions may be inserted into the AMM, provided that the information contained in the general revisions is identical to that specified in the TR's.

(1) If the measurement is greater than 0.014 inch, prior to further flight, replace the discrepant flap jackscrew with a new jackscrew in accordance with the procedures specified in Falcon 2000 AMM 27-510, dated November 1995; Falcon 900 AMM 27-521, dated December 1998; or Falcon 900EX AMM 27-510, dated September 1996, as applicable. Repeat the inspection thereafter at intervals not to exceed 330 flight hours or 7 months, whichever occurs first.

(2) If the measurement is less than or equal to 0.014 inch, repeat the measurement thereafter at intervals not to exceed 330 flight hours or 7 months, whichever occurs first.

Alternative Methods of Compliance
(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. 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.

Special Flight Permits
(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

NOTE 4: The subject of this AD is addressed in French airworthiness directives 1999-038- 008(B), dated January 27, 1999 (for Falcon 2000 series airplanes); and 1999-082-024(B) dated February 24, 1999 (for Falcon 900 and Mystere Falcon 900EX series airplanes).

(f) This amendment becomes effective on August 11, 1999.

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 all Dassault Model Falcon 2000 series airplanes; and certain Dassault Model 900EX, and Mystere Falcon 900 series airplanes was published in the Federal Register on May 3, 1999 (64 FR 23552). That action proposed to require repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new jackscrews; repetitive measurement of the screw/nut play to detect discrepancies; and corrective action, if necessary.

Explanation of Changes Made to this Final Rule
In the applicability paragraph of the proposed rule, the FAA inadvertently transposed the serial numbers for Falcon 900EX and Mystere Falcon 900 series airplanes. Therefore, the applicability paragraph of the final rule has been revised toread, "All Model Falcon 2000 series airplanes; Falcon 900EX series airplanes, serial numbers 04 and subsequent; and Mystere Falcon 900 series airplanes, serial numbers 161 and subsequent; certificated in any category."

For clarification purposes, the FAA also has revised "NOTE 2" of the final rule by changing all references to the "Airplane Flight Manual (AFM)" to correctly reference the "Airplane Maintenance Manual (AMM)."

Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule with the changes described previously. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Interim Action
This is considered to be interim action. The manufacturer has advised that it currently is developing a modification that will positively address the unsafe condition addressed by this AD. Once this modification is developed, approved, and available, the FAA mayconsider additional rulemaking.

Cost Impact
The FAA estimates that 159 airplanes of U.S. registry will be affected by this AD. It will take approximately 1 work hour per airplane to accomplish the required operational test, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the operational test required by this AD on U.S. operators is estimated to be $9,540, or $60 per airplane, per test cycle.

It will take approximately 8 work hours per airplane to accomplish the required flap jackscrew replacement, at an average labor rate of $60 per work hour. Required parts will cost approximately $21,200 per airplane. Based on these figures, the cost impact of the replacement required by this AD on U.S. operators is estimated to be $3,447,120, or $21,680 per airplane, per replacement cycle.

It will take approximately 8 work hours per airplane to accomplish the required measurement, at an average labor rate of $60 per work hour. Based onthese figures, the cost impact of the measurement required by this AD on U.S. operators is estimated to be $76,320, or $480 per airplane, per measurement cycle.

The cost impact figures discussed above are 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.

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.

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 Flexibility 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."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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: