DASSAULT AVIATION Proprietary Data

Transcription

1 F900EX EASY CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS TABLE OF CONTENTS GENERAL Introduction Anti-icing protection sources Anti-ice system location overview DESCRIPTION Pneumatic anti-icing Electrical anti-icing CONTROL AND INDICATION Control Indication SYSTEM PROTECTION Introduction Circuit breakers NORMAL OPERATION Introduction In-flight situation ABNORMAL OPERATION Introduction Airplane in-flight in icing conditions with wings overheat CAS messages

2 F900EX EASY PAGE 2 / 2 CODDE 1 TABLE OF CONTENTS INTENTIONALLY LEFT BLANK

3 F900EX EASY CODDE 1 PAGE 1 / 4 GENERAL INTRODUCTION The ice-protection system is intended to permit safe flight into and through intermittent or continuous maximum icing conditions. The F900EX 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.

4 F900EX EASY PAGE 2 / 4 CODDE 1 GENERAL FIGURE FLIGHT DECK OVERVIEW

5 F900EX EASY CODDE 1 PAGE 3 / 4 GENERAL ANTI-ICING PROTECTION SOURCES The Falcon 900EX 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 Engine 1,2,3 and APU bleed air ELECTRICAL SYSTEM SOURCES BUS A1 BUS A2 BUS B1 BUS B2 The pneumatic system, using hot bleed air from the engines, protects the following structural parts and equipment: - inboard / outboard slats, - the fixed leading edge sections on the inboard side of each wing panel, - engines air intake, - engine No 2 S-duct, - brakes (optional), - ECU heat exchanger ram-air inlet. HP air is used for anti-ice protection of engine air intake lips. 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 (TAT) probe, - Angle Of Attack (AOA) sensors, - stand-by pitot pressure probe, - Pt2 Tt2 sensors (one per engine), - cockpit windshields and windows, - water drains.

6 F900EX EASY PAGE 4 / 4 CODDE 1 GENERAL ANTI-ICE SYSTEM LOCATION OVERVIEW FIGURE ANTI-ICE AREAS OVERVIEW

7 F900EX EASY CODDE 1 PAGE 1 / 8 DESCRIPTION PNEUMATIC ANTI-ICING INTRODUCTION Each engine is fitted with LP and HP bleed air ports located respectively at the LP compressor final stage and HP compressor outlets. The LP and HP air is extracted from the engines through main and auxiliary ports. The main LP bleed ports permanently supply air to the interconnection manifold, named the distribution line to which the main system 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. Ice protection of engine air intakes is provided by HP air extracted from the corresponding engine through the auxiliary HP bleed air port. An isolation electric valve (crossbleed valve) can split the distribution assembly into two independent circuits. FIGURE ENGINE BLEED AIR PORTS

8 F900EX EASY PAGE 2 / 8 CODDE 1 DESCRIPTION DISTRIBUTION FIGURE PNEUMATIC SYSTEM SIMPLIFIED DIAGRAM WITH ANTI-ICE ON The pneumatic system relies on LP and HP bleed air drawn from the three engines. Anti-icing is provided by circulation of LP hot air bled from the last stage of each engine LP compressor. The HP engine bleed air valve located on each engine air bleed regulates the hot air system. A minimum N1 depending on altitude and True Air Temperature (TAT) is necessary to ensure proper anti-icing. When the feeder isolation (crossbleed) valve is closed: - No 2 engine is the only anti-icing supply source for the S-duct, - No 1 and No 3 engines are the only anti-icing supply source for wings.

9 F900EX EASY CODDE 1 PAGE 3 / 8 DESCRIPTION ENGINE NACELLE INTAKES The air intake anti-ice systems of all three engines are fully independent. They are supplied with dedicated HP bleed air from the corresponding engine. The HP valve modulates the supply of HP bleed air to maintain a constant pressure in the anti-icing line and limits that pressure. The No 1 engine anti-ice system also provides anti-icing for heat exchanger air intake (engine 1 pylon). No 2 ENGINE S-DUCT Normally, the air supply for the S-duct anti-icing is an HP / LP mix from the bleed-air manifold interconnecting all three engines. However, if the ISOLATION switch on the BLEED AIR panel is closed (stripe vertical), the No 2 engine continues to supply air directly to the bleed air manifold, providing for S-duct anti-icing and cabin air conditioning operation, while engines 1 and 3 supply bleed air for wing anti-icing and cockpit air conditioning. Engine No 2 S-duct FIGURE S-DUCT

10 F900EX EASY PAGE 4 / 8 CODDE 1 DESCRIPTION WINGS Downstream from anti-icing valve, the hot air system is divided into two lines: - one for RH wing, - one for LH wing. On each wing, the line first supplies the fixed leading edge sections and after the inboard and the outboard slat box structures, through two telescopic tubes. Wings anti-ice protection is mainly ensured by bleed air supplied by No 1 and No 3 engines. The No 2 engine bleed air supply is also available, unless the isolation (crossbleed) valve is closed. The Bleed Air Supply Computer controls and monitors the wings and No 2 engine S-duct anti-ice systems. In AUTO position, the Bleed Air Supply Computer (BASC) controls HP bleed valves to provide correct air pressure in the RH bleed air manifold. BRAKES (option) On each wing line, a pick off in front of the main gear well supplies hot air for the brake unit heating. DEFOGGING AND DEMISTING Air picked off the cockpit air conditioning system helps to remove mist from: - front windshield panel, - pilot panel, - copilot panel, - LH opening window, - LH and RH side windows.

11 F900EX EASY CODDE 1 PAGE 5 / 8 DESCRIPTION ELECTRICAL ANTI-ICING DISTRIBUTION FIGURE ELECTRICAL SYSTEM SCHEMATIC

12 F900EX EASY PAGE 6 / 8 CODDE 1 DESCRIPTION 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 panes are fitted with dual heat regulating sensors, one active and one in stand-by. The heating temperature is automatically regulated between 25 C (77 F) and 30 C (86 F). Pilot windshield Front windshield LH opening window Copilot windshield RH lateral window LH rear window RH rear window FIGURE WINDSHIELD AND SIDE WINDOWS PROBES The pitot pressure probes, static pressure probe, AOA sensors and Outside Air Temperature probe are heated by resistors controlled by switches. 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. Resistors controlled by the PITOT ST-BY pushbutton heats the stand-by pitot pressure probe.

13 F900EX EASY CODDE 1 PAGE 7 / 8 DESCRIPTION WATER WASTE DRAIN Drain masts of the water system (one for the forward galley, one for the rear wash basin) 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. Drain mast Drain mast FIGURE 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. Maximum speed for wipers operation is 215 kt.

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15 F900EX EASY CODDE 1 PAGE 1 / 12 CONTROL AND INDICATION CONTROL OVERHEAD PANEL FIGURE OVERHEAD PANEL CONTROL AUTOMATIC SETTINGS PILOT, COPIL., NORMAL and ST-BY controls At airplane power on, the overhead panel configuration is: PILOT, COPIL., NORMAL and ST-BY controls in OFF mode. These controls are automatically set to NORMAL mode when: - one throttle lever is in take off position, one engine is on and with WOW signal, - without WOW signal. They are automatically set to OFF mode when Flight / WOW transition occurs and IAS < 60 kt. Pt2-Tt2 probe The Pt2-Tt2 probes, located in each engine air intake, provide information about the airflow to the DEEC. Their heating is effective when the anti-ice ENG 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.

16 F900EX EASY PAGE 2 / 12 CODDE 1 CONTROL AND INDICATION SYNTHETIC TABLE CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC status light Controls hot air supply to No 1 and No 3 engine air intake lips. Push On commands air-intake anti-icing On pushbutton Engines air intake lips are directly anti-iced by HP air of the corresponding engine Push Off commands air-intake anti-ice valve closing Off status light Controls hot air supply to No 2 engine air intake lip and S-duct. Engine air intake lip is directly anti-iced by HP air of No 2 engine. Push On commands No 2 engine intake and S-duct antiicing On On pushbutton Engine No 2 S-duct is anti-iced by bleed air from LH bleed air manifold. In AUTO mode, the BASC opens the S-duct anti-ice valve and controls HP valves to provide the correct air pressure in the RH bleed air manifold Push Off commands anti-ice valve closing Off Off

17 F900EX EASY CODDE 1 PAGE 3 / 12 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC status light Push On overrides the system Forces HP2 bleed valve to full open pushbutton Push Off returns to AUTO mode Override mode status light When in AUTO mode: - the BASC opens the wings anti-ice valve and controls HP valves to provide air pressure in the RH bleed air manifold Push On: system in regulation when AUTO is selected pushbutton CAUTION Never engage wings anti-ice on ground. Push Off

18 F900EX EASY PAGE 4 / 12 CODDE 1 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC status light pushbutton Forces HP1 and HP3 valves to full open (thus providing the maximum bleed air heating power) Push On overrides the system Push Off returns to AUTO mode Override mode Option: status light - controls the power supply to the brake heating system Push ON - landing gear and brakes are anti-iced by the same duct used for wings antiicing (RH bleed air manifold) pushbutton - the brake anti-ice selection is effective only when wings is set to AUTO or O RIDE modes Push Off

19 F900EX EASY CODDE 1 PAGE 5 / 12 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC Allows three modes activated by pushing the button in the following logic: - OFF - automatic Automatic mode - MAX status light - automatic - OFF PILOT in automatic mode: the following windshield panes heating circuits are supplied: - LH half of front windshield pane MAX mode - pilot windshield pane pushbutton - LH opening window No synoptic status light - RH side window COPIL in automatic mode: the following windshield panes heating circuits are supplied: - RH half of front windshield pane - copilot windshield pane - LH rear window - RH rear window Push OFF PILOT / COPIL in MAX position: the corresponding windshield heating power is increased and the related half front pane heating power is reduced

20 F900EX EASY PAGE 6 / 12 CODDE 1 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC pushbutton Automatic mode Overrides pitot, static and AOA heat automatic function No synoptic status light Push OFF pushbutton Automatic mode Overrides stand-by pitot automatic function No synoptic Push Off status light

21 F900EX EASY CODDE 1 PAGE 7 / 12 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC status light Off mode Allows three modes activated by pushing the button in the following logic: - off pushbutton - SLOW - FAST SLOW mode No synoptic status light - off PILOT and COPIL controls are independent FAST mode

22 F900EX EASY PAGE 8 / 12 CODDE 1 CONTROL AND INDICATION INDICATION Anti-ice indication can be found on the BLEED synoptic. Engine 2 S-duct anti-ice diagram Wings and brake anti-ice diagram Engine air intake lips anti-ice diagram APU Crossbleed valve FIGURE BLEED SYNOPTIC WITH ANTI ICE ON NOTE The brake anti-ice symbol is only displayed when the option is installed.

23 F900EX EASY CODDE 1 PAGE 9 / 12 CONTROL AND INDICATION CROSSFEED VALVE Crossfeed valve open Crossfeed valve closed ENGINE N 1 AND N 2 ANTI-ICE AND FLOW LINE Engine anti-ice command ON Engine anti-ice command OFF Engine stopped Engine anti-ice command ON and low pressure. Engine anti-ice command ON and over pressure. Engine anti-ice command OFF and residual pressure.

24 F900EX EASY PAGE 10 / 12 CODDE 1 CONTROL AND INDICATION No 2 ENGINE S-DUCT Engine anti-ice command AUTO Engine anti-ice command OFF Engine anti-ice command AUTO with failure Engine anti-ice activated with low pressure Engine anti-ice activated with overpressure Engine anti-ice command OFF with residual pressure Engine anti-ice command O'RIDE Engine anti-ice command O'RIDE with failure

25 F900EX EASY CODDE 1 PAGE 11 / 12 CONTROL AND INDICATION WING ANTI-ICE Wing anti-ice command AUTO (wing anti-iced) Wing anti-ice command OFF Wing anti-ice command AUTO with failure Wing anti-ice command AUTO and low pressure Wing anti-ice command AUTO and overpressure Wing anti-ice command OFF with residual pressure Wing anti-ice command O'RIDE Engine anti-ice command O'RIDE with failure

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27 F900EX EASY CODDE 1 PAGE 1 / 2 SYSTEM PROTECTION INTRODUCTION The circuit protection is provided by conventional trip-free circuit breakers located above the overhead panel. CIRCUIT BREAKERS FIGURE ANTI-ICE CIRCUIT BREAKERS

28 F900EX EASY PAGE 2 / 2 CODDE 1 SYSTEM PROTECTION INTENTIONALLY LEFT BLANK

29 F900EX EASY CODDE 1 PAGE 1 / 4 NORMAL OPERATION 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 SITUATION 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.

30 F900EX EASY PAGE 2 / 4 CODDE 1 NORMAL OPERATION AIRPLANE IN FLIGHT IN NON ICING CONDITION In this case, pitot, static, AOA and water waste are the only anti-iced systems. FIGURE ANTI-ICE OVERHEAD PANEL FIGURE BLD SYNOPTIC

31 F900EX EASY CODDE 1 PAGE 3 / 4 NORMAL OPERATION AIRPLANE IN FLIGHT IN ICING CONDITIONS: In this case, PITOT, STATIC, AOA, water waste, engines and wings are anti-iced. FIGURE ANTI-ICE OVERHEAD PANEL FIGURE BLD SYNOPTIC

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33 F900EX EASY CODDE 1 PAGE 1 / 4 ABNORMAL OPERATION INTRODUCTION In the following, abnormal operation has been selected to help the crew to understand the symbols provided in the various panels and displays.

34 F900EX EASY PAGE 2 / 4 CODDE 1 ABNORMAL OPERATION AIRPLANE IN-FLIGHT IN ICING CONDITIONS WITH WINGS OVERHEAT ABNORMAL STATUS FIGURE ANTI-ICE OVERHEAD PANEL FIGURE BLD SYNOPTIC CONTEXT RESULT A/I: WINGS OVHT CAS message is displayed Abnormal wings and anti-ice protection + MASTER CAUTION light on Wings anti-ice overheat - Wings symbol in amber OVERPRESSURE indication in amber on BLD synoptic

35 F900EX EASY CODDE 1 PAGE 3 / 4 ABNORMAL OPERATION AFTER PROCEDURE COMPLETE FIGURE ANTI-ICE OVERHEAD PANEL FIGURE BLD SYNOPTIC ACTION WINGS pushbuttons off RESULT Wings symbol in gray

36 F900EX EASY PAGE 4 / 4 CODDE 1 ABNORMAL OPERATION CAS MESSAGES CAS MESSAGE A/I: BRAKE MISCONFIG A/I: ENG 2 A/I CMPTR FAIL A/I: ENG2 OVHT A/I: ENG.. LO PRESS A/I: ENG.. OVERPRESS A/I: ENG.. UNWANTED OPS A/I: WINGS CMPTR FAIL A/I: WINGS LO PRESS A/I: WINGS OVHT A/I: WINGS UNWANTED OPS AOA HEAT.. DEFINITION Brake A/I (optional) functioning problem Failure of engine 2 anti-ice computer Overheating of engine 2 anti-ice system Low pressure of engine (1/2/3) anti-ice system with A/I selected Over pressure of engine (1/3) anti-ice system with A/I selected Engine (1/2/3) anti-ice system is off and a residual pressure is detected Failure of wings anti-ice computer Low pressure of wing anti-ice bleed air Overheating of wing anti-ice system Anti-ice systems are off and a residual pressure is detected on wings Angle Of Attack probe (1/2) heating system failure FAULT CODE Refer to CODDE1 / Chapter 02 / ATA PITOT HEAT.. STATIC HEAT.. ST-BY PITOT HEAT WINSHIELD XFR Failure of pitot (1/2) probe heating system In flight, failure of static probe (1/2) heating system In flight, failure of stand-by Pitot heating system One of the two temperature regulators has failed FAULT CODE Refer to CODDE1 / Chapter 02 / ATA ICE DETECTED ICE DETECTION FAIL PITOT ON PROBE HEATING FAIL WING A/I ON Icing conditions detected Ice detection has failed On ground indication that Pitot probes are heated On ground and all engines off, indication of failure of probe heating system Wing anti-ice selected with airplane on ground