AD/F2000/24 - Software Integrity Check and Enhanced Avionics System Upgrade (Cth)

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/F2000/24 Software Integrity Check and Enhanced Avionics System Upgrade 4/2007 DM

Applicability: Falcon 2000EX aeroplanes, serial numbers 06, 28 to 86 inclusive, and 88; without Dassault Aviation Falcon Service Bulletin (SB) F2000EX-100 dated 30 August 2006 or later Revision approved by the European Aviation Safety Agency (EASA) implemented (ie still in EASy Step 2 configuration). Requirement: 1. Perform a software check using a dedicated software tool named "Flash Integrity Check" (FLICK) in accordance with the accomplishment instructions of Dassault Aviation Falcon SB F2000EX-120 dated 7 September 2006 or later Revision approved by the EASA. 2. Make a temporary amendment to Chapter 5-40 of the Aircraft Maintenance Manual (AMM) to indicate that the MP 45-403 "Software modules integrity check" is to be accomplished at 40 day intervals. Note 1: To record the temporary inspection schedule, a copy of this Directive may be included in of the AMM as a temporary change. 3. Modify the aircraft in accordance with the accomplishment instructions of SB F2000EX-100 (modification M2656) or later Revision approved by the EASA. This is considered to be a terminating action for the temporary repetitive inspection requirements introduced by the Requirement 2 AMM amendment and the temporary amendment to the AMM may be removed. 4. For aircraft with advanced graphics module (AGM) and enhanced ground proximity warning module (EGPWM) modules with a part number (P/N) prior to 7026545-1904 (AGM) and 7028419-1904 (EGPWM), perform a check with the FLICK tool in accordance with the AMM MP 45-401. Note 2: EASA AD 2007-0032 refers. Compliance: For Requirement 1and 2 - No later than 40 days after the effective date of this Directive. For Requirement 3- Within 12 months after the effective date of this Directive. For Requirement 4 - After each operational software loading.