Wed, Jan 25, 2006
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:
- Before the next flight following the effective date of this
AD.
- Before 31 December 2006.
This Airworthiness Directive becomes effective on 31 January
2006.
Background:
Two types of events have been observed in service:
- Temporary loss of braking efficiency at landing which was
recovered after fully
releasing the brakes and reapplying braking force.
- 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.
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