Document ID: chunk:federal_register_of_legislation:F2008L00395:body:0
Version: federal_register_of_legislation:F2008L00395
Segment Type: other
Provision Reference: 
Character Range: 0–2498

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Dassault Aviation Falcon 2000 Series Aeroplanes
AD/F2000/29  Generator Control Unit Wiring  3/2008

Applicability:  Falcon 2000EX aircraft from serial number 1 to 107 inclusive, which have not been modified by Dassault Aviation Falcon Service Bulletin (SB) F2000EX-141 dated
                16 February 2007 or Revision 1 dated 26 November 2007.
Requirement:    Modify the Generator Control Units (GCU) electrical wiring as instructed in the accomplishment instructions of SB F2000EX-141 or later EASA approved revision.
                Note:  EASA AD 2007-0290 refers.
Compliance:     Within the next 13 months after the effective date of this Directive.
                This Airworthiness Directive becomes effective on 13 March 2008.
Background:     The European Aviation Safety Agency has advised that during an approach, a Falcon 2000EX operator experienced a temporary loss of the four Electronic Flight Instrumentation System (EFIS) display units followed by a consecutive restart of the avionics.  During initial investigation, a loose connection on the DC load distribution system was discovered and determined to be the root cause of this event.

                However, further analysis indicated that large electrical transients on the essential bus bar may possibly cause simultaneous and temporary power shortage on both sides of the electrical system.

                This Directive requires a wiring modification of the GCUs to increase the electrical system robustness.  This action is necessary to prevent a momentary loss of data on the EFIS screens, which could lead to the pilot's loss of situational awareness during initial climb or approach/landing and could possibly result in reduced control of the aeroplane.

Charles Lenarcic
Delegate of the Civil Aviation Safety Authority

23 January 2008