Federal Register of Legislation - Australian Government

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AD/AMD 50/40 Airworthiness Directives/Pt 105 — Aircraft as made
Software Integrity Check and Enhanced Avionics System Upgrade
Administered by: Infrastructure, Transport, Cities and Regional Development
Exempt from sunsetting by the Legislation (Exemptions and Other Matters) Regulation 2015 s12 item 15
Registered 21 Mar 2007
Tabling HistoryDate
Tabled Senate26-Mar-2007
Tabled HR26-Mar-2007

 

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.

AMD Falcon 50 and 900 Series Aeroplanes

AD/AMD 50/40

Software Integrity Check and Enhanced Avionics System Upgrade

4/2007

 

Applicability:

Falcon 900EX aeroplanes, serial numbers (S/N) 97, 120 to 170 inclusive and Falcon 900EX (version F900DX) aeroplanes S/N 601 to 607 inclusive.

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 F900EX-298 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 F900EX-304 (modification M5255) dated 8 February 2007 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 1 and 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.

 

 

This Airworthiness Directive becomes effective on 12 April 2007.

Background:

EASA has advised that during an internal review, it was discovered that some software integrity checks were not fully implemented in modules of the Honeywell EPIC avionics, as used in Falcon EASy aircraft.

 

Consequently, the continuing integrity of the modules’ software cannot be demonstrated, as required by software requirements.  Software corruption may then potentially occur during any upload of the operational software and also as random effects under normal conditions.

 

This Directive mandates the use of the FLICK tool on a regular basis pending a software correction.  The software load implementing the terminating actions also includes a software correction for the untimely inhibition of the "flap asymmetry” detection below 200ft.  This is mandated to correct a situation that may not conform to EASA CS 25.671 (c) (1).


David Punshon
Delegate of the Civil Aviation Safety Authority

26 February 2007