F2000EX EASY 02-30-00 ATA 30 – ICE AND RAIN PROTECTION

F2000EX EASY 02-30-00

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ATA 30 – ICE AND RAIN PROTECTION TABLE OF CONTENTS

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DASSAULT AVIATION Proprietary Data

02-30 ATA 30 – ICE AND RAIN PROTECTION

02-30-00 TABLE OF CONTENTS

02-30-05 GENERAL

Introduction Anti-icing protection sources Anti-ice system location overview

02-30-10 DESCRIPTION

Pneumatic anti-icing Electrical anti-icing

02-30-15 CONTROL AND INDICATION

Control Indication

02-30-20 SYSTEM PROTECTION

Introduction Circuit breakers

02-30-25 NORMAL OPERATION

Introduction IN-FLIGHT situations

02-30-30 ABNORMAL OPERATION

Introduction Airplane in flight in icing conditions with wings overheat CAS messages

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ATA 30 – ICE AND RAIN PROTECTION TABLE OF CONTENTS

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INTENTIONALLY LEFT BLANK

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ATA 30 – ICE AND RAIN PROTECTION GENERAL

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INTRODUCTION

The ice-protection system is intended to permit safe flight in intermittent or continuous maximum icing conditions.

The F2000EX EASy uses pneumatic and electrical power for its anti-icing and rain protection system.

An anti-fogging and demisting system is also provided for the cabin and flight deck windows.

Two electrically-operated windshield wipers are also provided.

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CAS windows

BLD synoptic

Anti-ice and raincircuit breakers

Anti-ice and rain controls

Bleed air controls

FIGURE 02-30-05-00 FLIGHT DECK OVERVIEW

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ANTI-ICING PROTECTION SOURCES

The Falcon 2000EX EASy is equipped with two anti-icing systems:

- one pneumatic system (LH and RH bleed air manifold),

- one electrical system using heating resistors.

PNEUMATIC SYSTEM SOURCES ELECTRICAL SYSTEM SOURCES

Engines No 1 and 2

BUS A1

BUS A2

BUS B1

BUS B2

BUS ESS

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.

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ANTI-ICE SYSTEM LOCATION OVERVIEW

FIGURE 02-30-05-01 ANTI-ICE AREA OVERVIEW

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ATA 30 – ICE AND RAIN PROTECTION DESCRIPTION

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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.

FIGURE 02-30-10-00 ENGINE BLEED AIR PORTS

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DISTRIBUTION

FIGURE 02-30-10-01 PNEUMATIC SYSTEM SIMPLIFIED DIAGRAM WITH WINGS ANTI-ICE ON

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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.

HEAT EXCHANGER RAM AIR INLET ANTI-ICE

Air is tapped downstream the wings anti-icing valve and supplies the intake duct of the air conditioning heat exchanger.

BRAKE HEATING (OPTION)

On each wing line, a pick-off in front of the main gear well supplies hot air to the brake unit.

ENGINE NACELLE INTAKE ANTI-ICE

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.

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ELECTRICAL ANTI-ICING

ELECTRICAL SYSTEM SCHEMATIC

FIGURE 02-30-10-02 ELECTRICAL SYSTEM SCHEMATIC

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WINDSHIELD AND SIDE WINDOWS

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 25°C (77°F) and 30°C (86°F).

Front windshield

Copilot windshield

RH lateral window

LH opening window

Pilot windshield

LH rear window RH rear window

FIGURE 02-30-10-03 WINDSHIELD AND SIDE WINDOWS

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.

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WATER WASTE DRAIN

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.

FIGURE 02-30-10-04 DRAIN MASTS LOCATION

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.

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ATA 30 – ICE AND RAIN PROTECTION CONTROL AND INDICATION

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CONTROL

OVERHEAD PANEL

FIGURE 02-30-15-00 OVERHEAD PANEL CONTROLS

AUTOMATIC SETTINGS

WINDSHIELD and PITOT functions

At airplane power-on, the overhead panel configuration is: WINDSHIELD PILOT, WINDSHIELD COPIL., PITOT NORMAL and PITOT ST-BY controls in OFF mode.

These controls are automatically set to NORMAL mode when: - one throttle lever is in TAKE-OFF position and one engine is on and with WOW

signal, or - without WOW signal.

They are automatically set to OFF mode when Flight / WOW transition occurs and IAS < 20 kt.

P1-T1 probe

The heating of the P1-T1 probe is effective when the ENG anti-ice control is set to ON.

Water waste drain masts

The drain masts and the heating elements of the lines are automatically activated as soon as the airplane is electrically powered.

Other anti-ice controls

All other overhead panel anti-ice controls are set to off mode when energizing the airplane systems (ANTI-ICE and WIPER functions).

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SYNTHETIC TABLE

ENG controls

TO ACTIVATE CONTROL FUNCTION

TO DE-ACTIVATE SYNOPTIC

Push ON

ON

controls hot air supply to air intake lips of No 1 and No 2 engines

Push off

Off

WINGS and BRAKE controls



Push AUTO

When in AUTO mode, the wings anti-ice valve is open and the BASC controls HP1 and HP2 valves to provide the required manifold pres-sure

CAUTION Never activate wings anti-ice on ground, except for test with

engines idle.

Push off

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TO ACTIVATE

CONTROL FUNCTION TO DE-ACTIVATE

SYNOPTIC

Push O’RIDE

Forces HP1 and HP2 valves to full open

When O'RIDE is de-activated, wings mode is automatically set to off

Push off

Push ON

Option

controls the power supply to the brake heating system,

the BRAKE anti-ice is effective only when WINGS is set to AUTO or O’RIDE modes (because the same duct is used).

Push off

NOTE

The brake anti-ice symbol is displayed only when the option is installed.

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WINDSHIELD controls



Automatic mode

Push MAX

allows three modes activated by pushing the pushbutton in the following logic:

- OFF,

- automatic,

- MAX,

- automatic,

- OFF.

PILOT in automatic mode: the following windshield pane heating circuits are supplied:

- LH half of front windshield pane,

- Pilot windshield pane,

- LH opening window,

- RH side window.

COPIL in automatic mode: the following windshield pane heating circuits are supplied:

- RH half of front windshield pane,

- Copilot windshield pane,

- LH rear window,

- RH rear window.

PILOT / COPIL in MAX mode: the corresponding windshield heating power is increased and the related half of front pane heating power is reduced.

Push OFF

No synoptic

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PITOT controls



Automatic mode

Controls automatic anti-icing of pitot, static, AOA probes and temperature sensors

Push OFF

No synoptic

Automatic mode

Controls automatic anti-icing of stand-by pitot probe

Push OFF

No synoptic

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WIPER controls



Off mode

Push SLOW

Allows three modes, activated by pushing the pushbutton in the following logic:

- off,

- SLOW,

- FAST,

- off.

PILOT and COPIL controls are indepen-dent.

Push FAST

No synoptic

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INDICATION

Anti-ice indication can be found on the BLEED synoptic:

Wing and brake anti-ice diagram

Engine air intake lip anti-ice diagram

FIGURE 02-30-15-01 BLEED SYNOPTIC WITH ANTI-ICE OFF

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ENGINE ANTI-ICE AND FLOW LINE

Anti-ice ON (no failure detected)

Anti-ice OFF (no failure detected)

Anti-ice ON

Low Pressure

Anti-ice ON

Over Pressure

Anti-ice OFF

Residual pressure

WINGS ANTI-ICE

Wings anti-ice on (no failure detected)

Wings anti-ice command off (no failure detected)

Wings anti-ice monitoring malfunction

Wings anti-ice on and low pressure

Wings anti-ice on and over pressure

Wings anti-ice command off with residual pressure

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BRAKE HEATING (OPTION)

Brake heating off Brake heating ON Brake heating failure

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ATA 30 – ICE AND RAIN PROTECTION SYSTEM PROTECTION

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INTRODUCTION

The circuit protection is provided with conventional trip-free circuit breakers located above the overhead panel.

CIRCUIT BREAKERS

FIGURE 02-30-20-00 ANTI-ICE CIRCUIT BREAKERS

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ATA 28 – FUEL SYSTEM TABLE OF CONTENTS

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ATA 30 – ICE AND RAIN PROTECTION NORMAL OPERATION

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INTRODUCTION

Icing conditions exist when the OAT on the ground and for take-off, or TAT in flight is 10°C 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 10°C 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.

AIRPLANE IN FLIGHT IN NON-ICING CONDITIONS

In this case, pitot, static, AOA probes and water waste masts are the only anti-iced systems.

FIGURE 02-30-25-00 OVERHEAD PANEL

FIGURE 02-30-25-01 BLEED SYNOPTIC WITHOUT ANTI-ICE

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ATA 30 – ICE AND RAIN PROTECTION NORMAL OPERATION

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AIRPLANE IN FLIGHT IN ICING CONDITIONS

In this case, pitot, static, AOA probes, water waste masts, engines and wings are anti-iced.


FIGURE 02-30-25-03 BLEED SYNOPTIC WITH ANTI-ICE ACTIVATED

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ATA 30 – ICE AND RAIN PROTECTION ABNORMAL OPERATION

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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.

AIRPLANE IN FLIGHT IN ICING CONDITIONS WITH WINGS OVERHEAT

ABNORMAL STATUS


FIGURE 02-30-30-01 BLEED SYNOPTIC WITH WINGS OVERHEAT

CONTEXT RESULT

Wings anti-ice excessive heating

A/I: WINGS OVHT CAS message is displayed

+ light on

- Wings symbol in amber

- OVER PRESSURE amber indication onBLEED synoptic

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AFTER PROCEDURE COMPLETE


FIGURE 02-30-30-03 BLEED SYNOPTIC WITH WINGS ANTI-ICE OFF

ACTION RESULT

WINGS pushbutton off Wings symbol in GRAY

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CAS MESSAGES

CAS MESSAGE DEFINITION

WHEEL XX OVHT Excessive temperature in (LH/RH) wheel compartment(option)

A/I CMPTR CONT FAULT CODE Parking only, a failure message that may affect dispatch has been recorded by the BASC

A/I CMPTR MONIT FAULT CODE Parking only, a failure message that may affect dispatch has been recorded by the BASC

A/I: ENG .. LO PRESS Low pressure in engine (1/2) inlet anti-ice system with anti-ice ON

A/I: ENG .. OVERPRESS Overpressure in engine (1/2) inlet anti-ice system with anti-ice ON

A/I: ENG .. UNWANTED OPS Pressure in engine (1/2) inlet anti-ice system while not activated

A/I: WINGS CMPTR FAIL Failure of wings anti-ice computer (BASC)

A/I: WINGS LO PRESS Low pressure in wings anti-ice system

A/I: WINGS OVHT Overpressure in wings anti-ice system

A/I: WINGS UNWANTED OPS Pressure in wings anti-ice system while not activated

AOA HEAT .. Angle-of-Attack probe (1/2) heating system failure

PITOT HEAT .. In-flight failure of Pitot (1/2) probe heating system

STATIC HEAT .. In-flight failure of static probe (1/2) heating system

ST-BY PITOT HEAT In-flight failure of stand-by Pitot and static probe heating system

WINDSHIELD XFR Pilot (copilot) windshield pane temperature control is transferred to copilot (pilot) temperature regulator unit

A/I: BRAKES MISCONFIG Brake anti-ice valves are not in the commanded position

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CAS MESSAGE DEFINITION

A/I CMPTR CONT FAULT CODE In flight, a failure message has been recorded by the BASC

A/I CMPTR MONIT FAULT CODE In flight, a failure message has been recorded by the BASC

ICE DETECTED Icing conditions detected (option)

ICE DETECTION FAIL Ice detection has failed (option)

PITOT ON On-ground indication that probes are heated

PROBE HEATING FAIL On-ground indication of probe heating system failure

WING A/I ON Wings anti-ice activated with airplane on ground (displayed with 1 min delay)

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F2000EX EASY 02-30-00 ATA 30 – ICE AND RAIN PROTECTION