Dassault Falcon 000dx-Ex-Ice and Rain Protection
Dassault Falcon 000dx-Ex-Ice and Rain Protection
Dassault Falcon 000dx-Ex-Ice and Rain Protection
02-30-05 GENERAL
Introduction
Anti-icing protection sources
Anti-ice system location overview
02-30-10 DESCRIPTION
Pneumatic anti-icing
Electrical anti-icing
INTRODUCTION
CAS windows
BLD synoptic
BUS A1
BUS A2
The pneumatic system, using hot bleed air from the engines, protects the following structural
parts and equipment:
- wing inboard leading edge,
- outboard slats,
- air conditioning heat exchanger ventilation air intake,
- engine air intake lips,
- wheel brakes (optional).
The electrical anti-ice system protects the following probes, parts and equipment:
- LH and RH pitot pressure probes,
- LH and RH static pressure probes,
- Total Air Temperature probe,
- Angle-of-Attack sensors,
- stand-by pitot pressure probe,
- P1-T1 sensors (one per engine),
- cockpit windshields and windows,
- water drains.
In addition, wipers are provided for the main windshields.
PNEUMATIC ANTI-ICING
GENERAL
Each engine is fitted with LP and HP bleed air ports located on the compressor HP spool.
The main LP bleed ports supply air to the interconnection manifold, named the distribution
line to which the main systems are connected.
When the LP air pressure is not high enough to achieve correct anti-icing or defogging, HP
air, extracted through the main HP bleed ports, is injected into the LP bleed air through an
electric valve. The Bleed Air System Computer (BASC) controls the electric valve opening
and closing.
The BASC monitors the wings anti-ice system and displays the corresponding CAS
message(s).
Ice protection of engine air intakes is provided by HP air extracted from the corresponding
engine through the auxiliary HP bleed air port.
DISTRIBUTION
WINGS ANTI-ICE
The wings anti-icing system protects the wing inboard leading edges, the outboard slats
(through telescopic tubes) and the air-conditioning heat exchanger ventilation air intake.
Wings anti-icing is provided by circulation of mixed LP and HP hot air.
A minimum N1 value depending on altitude and Total Air Temperature (TAT) is necessary to
ensure proper anti-icing.
When the system is in AUTO mode, the wings anti-icing valve is commanded to open.
- if one of the throttle levers is set to MAX CLIMB position or further, the valve partially
opens, in order to reduce the amount of air bled from the engine.
- if both throttle levers are below MAX CLIMB, the valve fully opens.
When the feeder isolation valve is closed, No 2 engine is the only anti-icing supply source
for this system.
Air is tapped downstream the wings anti-icing valve and supplies the intake duct of the air
conditioning heat exchanger.
On each wing line, a pick-off in front of the main gear well supplies hot air to the brake unit.
The No 1 and 2 air intake anti-icing systems are fully independent. They are supplied with
dedicated HP bleed air from the corresponding engine.
The pneumatic A/I valve controls the bleed air supply to maintain a constant pressure in the
anti-icing line. In case of duct rupture, a venturi limits the airflow of the HP compressor.
WINDOW DEMISTING
The cockpit air conditioning system helps to remove mist, especially from:
- front windshield,
- pilot windshield,
- copilot windshield.
ELECTRICAL ANTI-ICING
The cockpit windows are electrically heated by a network of heating elements incorporated
into the transparent panes.
The electrical anti-icing system of the windshields is composed of two identical circuits:
- one pilot circuit,
- one copilot circuit.
The pilot and copilot circuits are fitted with dual heat regulating sensors, one active and one
stand-by.
The heating temperature is automatically regulated between 25C (77F) and 30C (86F).
Copilot windshield
LH opening window
RH lateral window
PROBES
The pitot pressure probes, static pressure probes, AOA sensors and Outside Air
Temperature probe are heated by resistors controlled by pushbuttons.
Resistors controlled by the PITOT NORMAL pushbutton heat the following probes and
sensors:
- LH and RH pitot pressure probes,
- LH and RH static pressure probes,
- LH and RH Angle Of Attack sensors,
- Outside Air Temperature probe.
Resistor controlled by the PITOT ST-BY pushbutton heats the stand-by pitot pressure probe.
Drain masts of the water system (one for the front galley, one for the rear washbasin) are
electrically anti-iced.
The water drain hoses between rear mast and pressurized area include an electrical resistor
which surrounds end fittings.
The drain masts and the heating elements of the lines are supplied from the DRAINS HEAT
circuit breakers.
WIPERS
Pilot and copilot windshield panes are both equipped with a wiper arm powered by an
electrical motor-converter and designed to keep the field of view clear during taxi, take-off,
approach and landing phases when raining or snowing.
When the wipers are not used, they are stowed in a recess located at the bottom of each
windshield.
Each wiper is powered and controlled independently of the other by a pushbutton on the LH
and RH side of the overhead panel.
CONTROL
OVERHEAD PANEL
AUTOMATIC SETTINGS
P1-T1 probe
The heating of the P1-T1 probe is effective when the ENG anti-ice control is set to ON.
The drain masts and the heating elements of the lines are automatically activated as
soon as the airplane is electrically powered.
All other overhead panel anti-ice controls are set to off mode when energizing the
airplane systems (ANTI-ICE and WIPER functions).
SYNTHETIC TABLE
ENG controls
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
Push ON ON
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
Push ORIDE
Push off
Option
Push ON
controls the power
supply to the brake
heating system,
the BRAKE anti-ice is
effective only when
WINGS is set to AUTO
or ORIDE modes
(because the same duct Push off
is used).
NOTE
The brake anti-ice symbol is displayed only when the option is installed.
WINDSHIELD controls
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
PITOT controls
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
Automatic
mode
Controls automatic anti-icing
of pitot, static, AOA probes No synoptic
and temperature sensors
Push OFF
Automatic
mode
Push OFF
WIPER controls
TO ACTIVATE
CONTROL FUNCTION SYNOPTIC
TO DE-ACTIVATE
Off mode
- off.
INDICATION
WINGS ANTI-ICE
INTRODUCTION
The circuit protection is provided with conventional trip-free circuit breakers located above the
overhead panel.
CIRCUIT BREAKERS
INTRODUCTION
Icing conditions exist when the OAT on the ground and for take-off, or TAT in flight is 10C or
below, and visible moisture in any form is present (such as clouds, fog with visibility of one
mile or less, rain, snow, sleet or ice crystals).
Icing conditions also exist when the OAT on the ground and for take-off is 10C or below
when operating on ramps, taxiways or runways where surface snow, ice, standing water, or
slush may be ingested by the engines or freeze on engines, nacelles or engine sensor
probes.
IN-FLIGHT SITUATIONS
In the following, typical in-flight situations have been selected to help the crew to understand
the symbols provided in the various panels and displays.
In this case, pitot, static, AOA probes and water waste masts are the only anti-iced systems.
In this case, pitot, static, AOA probes, water waste masts, engines and wings are anti-iced.
INTRODUCTION
In the following, one abnormal operation has been selected to help the crew to understand the
symbols provided in the various panels and displays.
ABNORMAL STATUS
CONTEXT RESULT
ACTION RESULT
CAS MESSAGES
A/I: WINGS UNWANTED OPS Pressure in wings anti-ice system while not activated