Applicability: Falcon 2000EX aircraft with M1691 (EASy Aircraft) which have not incorporated Service Bulletin SB-F2000EX-80 (or modification M2675).

Requirement:

1. Unless previously accomplished, add temporary change TC 17 to the AFM performance section (This can be achieved by inserting a copy of this AD in the AFM performance section).
Adjacent to page 5-150-2: Take off Field length limits
Field length determined from balanced field length charts has to be increased by 27%. Conversely, the field length limited take-off weight is reached when the field length determined from the charts is equal to the field length available multiplied by 0.78.
Maximum take-off weight on wet runway must never be higher than maximum take-off weight on the same runway in dry conditions. Then in case of take-off weight limited by balanced field length on wet runway, this weight has to be compared to the maximum take-off weight on dry runway.
Adjacent to page 5-150-3: Landing Field length limit
Landing distance or landing field length as determined from the chart has to be increased by 25%. Conversely, the field length limited landing weight is reached when the field length or the landing distance, as required by operating regulations is equal to the runway length actually available multiplied by 0.80. The landing weight normally anticipated at the destination or alternate airport must not be greater than the maximum landing weight.

2. Incorporate SB F2000EX-80 and cancel the TC-17 from the AFM. The incorporation of the SB F2000EX-80 is the terminating action for this AD which allows removal of the runway length penalties for take-off and landing from requirement 1.
Note: DGAC AD UF-2005-140 EASA approval No. 2005-61 10 dated 26 July 2005 refers.

Compliance:

1. Before the next flight following the effective date of this AD.
2. Before 31 December 2006.

This Airworthiness Directive becomes effective on 31 January 2006.

Background: Two types of events have been observed in service:

1. Temporary loss of braking efficiency at landing which was recovered after fully
   releasing the brakes and reapplying braking force.
2. Display shortly after take off of a red “BOTH BRAKE SYSTEM” CAS message associated with “BRAKE COMPTR#1 FAULT CODE” and “BRAKE COMPTR#2 FAULT CODE” CAS message.

Both types of events have been linked to incorrect data being transmitted between the IRS and the Brake System Control Unit. This results in a failure of the BSCU to provide accurate use of the anti skid system and a reduction in braking efficiency. Loss of efficiency in braking may jeopardize the certificated take off and landing performances.

This AD proposes to add runway length penalties at take off and landing to the AFM of the affected aircraft until a wiring modification is incorporated to directly link the IRS to the BSCU.

FMI: www.casa.gov.au