F2000EX EASY 02-36-00 ATA 36 – PNEUMATIC CODDE 1 PAGE 1 … · 2012. 6. 27. · ATA 36 –PNEUMATIC DESCRIPTION DGT94085 DASSAULT AVIATION Proprietary Data HPBLEED AIR The main

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DGT94085

ATA 36 – PNEUMATIC TABLE OF CONTENTS

ISSUE 3

DASSAULT AVIATION Proprietary Data

02-36 ATA 36 – PNEUMATIC

02-36-00 TABLE OF CONTENTS

02-36-05 GENERAL

Introduction Sources

02-36-10 DESCRIPTION

Introduction Main sub-systems Distribution

02-36-15 CONTROL AND INDICATION

Control Indication

02-36-20 SYSTEM PROTECTION

Introduction Circuit breakers Main protections

02-36-25 NORMAL OPERATION

Introduction IN-FLIGHT operation without anti-ice

02-36-30 ABNORMAL OPERATION

Introduction BLEED 1 overheat CAS messages

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ATA 36 – PNEUMATIC TABLE OF CONTENTS

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INTENTIONALLY LEFT BLANK

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ATA 36 – PNEUMATIC GENERAL

ISSUE 3


INTRODUCTION

The pneumatic system on the Falcon 2000EX EASy uses engine and APU bleed air as a high and low pressure energy source for the engine start, air-conditioning, fuel tanks, hydraulic reservoirs, potable water tank pressurization and ice and rain protection system. A pneumatic Ground Power Unit (GPU) may be connected to the system when necessary.

Bleed air circuit breakers

Bleed air controls

BLD synoptic

CAS windows

FIGURE 02-36-05-00 FLIGHT DECK OVERVIEW

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ATA 36 – PNEUMATIC GENERAL

DGT94085


SOURCES

ON GROUND IN-FLIGHT

Bleed air from APU compressor discharge

Low and high pressure bleed air supplied from engines No 1 and 2 if running

- LP supplied from the last axial stage of HP compressor section

- HP supplied from HP compressor discharge

Pressurized air from a ground power unit

Low and high pressure bleed air supplied from engines No 1 and 2

- LP supplied from the last axial stage of HP compressor section

- HP supplied from HP compressor discharge

Bleed air from APU compressor discharge

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ATA 36 – PNEUMATIC DESCRIPTION

ISSUE 3


INTRODUCTION

The bleed air is divided into two categories, engine and APU bleed air. The engine bleed air is supplied from the LP and HP compressors of both engines. The bleed air from the APU is supplied on the ground or in flight from a plenum surrounding the combustor.

FIGURE 02-36-10-00 ENGINE BLEED AIR PORTS

MAIN SUB-SYSTEMS

LP BLEED AIR

The main bleed air sources for LP air are located on the inboard side of No 1 and No 2 engines. An auxiliary outboard bleed port on both engines provides pressurized air for fuel tank and hydraulic reservoirs pressurization. The LP bleed air also supplies continuously the jet pump of cabin pressurization system.

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HP BLEED AIR

The main source for HP bleed air is through manifold-equipped bleed ports on each engine. The auxiliary bleed-air sources are single bleed ports located on the upper centerline of each engine. They provide the air intake anti-ice system with hot air. The HP bleed air also supplies the water tank pressurization system.

BLEED-AIR SYSTEM CONTROL

Both engine HP bleed-air valves are identical. They consist of electrical driven butterfly valves, controlled by the BASC (Bleed-Air System Computer) in the automatic mode. This computer, which is redundantly powered on the monitoring side, receives inputs from temperature and pressure sensors located throughout the pneumatic system, valve position indicators, air data system, ground-flight relay system, wing anti-ice and HP valve pushbutton position. Using the inputs provided, the BASC regulates the HP valve position and controls warnings associated with bleed-air system malfunctions. The BASC also gives an order to close to the corresponding HP valve for each engine start. Valve position is modulated to supply a required pressure throughout the pneumatic system, ensuring that the bleed-air requirements of the air-conditioning, pressurization, and wing anti-ice systems are satisfied. In case of air conditioning requirements without anti-ice, the BASC opens the valves to 70% max. For air conditioning requirements with anti-ice, the BASC can open the valves up to 100%. If the wing anti-ice pushbutton is selected to the override position, the BASC automatic control of HP1 and HP 2 is overridden and the valves fully open. The override position of the anti-ice pushbutton is used only in case of anti-ice system failure.

ENGINE LP + HP BLEED-AIR MIXING

At the outlet of each engine, airflows from the main LP and HP ports are mixed by venturi-action. The resulting pressure is greater than LP bleed-air pressure. The mixed airflow supplies a common feeder duct through a Pressure Reducing Valve (PRV). In normal position, the PRV regulates the bleed air pressure delivered in the common feeder duct. The valve opens for a minimal upstream pressure of 0.7 bar (10 psi), it automatically closes if the APU starts with APU selector in AUTO position. It automatically fully opens when the wing anti-icing system is in operation. In OFF position, the PRV is closed and fully isolates the bleed air of the corresponding side. The HP bleed valve located on the same side is automatically closed. Bleed air back flow from an operating engine to an inoperative engine, or to an engine with a lower power setting, or injection of HP bleed air into the LP bleed air port is prevented by check valves.

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APU BLEED AIR

The bleed air from the APU can supply the LH common feeder duct and be used to operate the air conditioning system. APU bleed air also supplies the pressurization jet pump controlling the cabin outflow valves and water tank pressurization.

GROUND AIR CONNECTOR

The ground air connector supplies the RH common feeder duct through an integrated check valve. The recommanded air kart pressure is 30 psi (max 50 psi) for a 82 lb/sec minimum air flow and 249°C (480°F) max temperature. It is located at the rear of the aircraft, on the RH side.

FIGURE 02-36-10-01 GROUND AIR CONNECTOR

COMMON FEEDER DUCT

The common feeder duct supplies a mixture of HP and LP air to the pilot and passenger air conditioning system as well as to the wing anti-icing system. The common feeder duct can be divided into two separate sub-systems by means of an electrically motor-operated cross bleed valve. One side of the cross bleed valve is connected to the No 1 engine and APU and supplies compressed air to the passenger air conditioning system, No 1 engine pneumatic starter and jet pump. The other side is connected to the No 2 engine or GPU and supplies the cockpit air conditioning system, the wing anti-icing system and No 2 engine pneumatic starter.

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CROSS BLEED VALVE

An XBLEED pushbutton located on the BLEED AIR panel controls the electrical cross bleed valve. When the cross bleed valve is closed, the two systems are separated. In AUTO mode, the cross bleed valve is normally closed except if one engine is inoperative or the wing anti-icing system is operative or the heat exchanger ventilation jet pump valve is open. The ISOL and OPEN positions override the valve position.

APU BLEED VALVE

The APU bleed valve is controlled by an APU pushbutton located on the BLEED AIR panel. When it is open, APU bleed air supplies the pneumatic system. If the APU pushbutton is AUTO, the APU bleed air valve is open except when:

- the APU is not in operation, - the wing anti-ice system is in operation, - a Pressure Reducing Valve (PRV) is not fully closed within 4 sec following its closing

command. In AUTO mode, APU bleed valve is fully open as long as the Exhaust Gas Temperature (EGT) limit is not reached. The O’RIDE and OFF positions override the automatic mode.

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DISTRIBUTION

FIGURE 02-36-10-02 BLEED AIR SYSTEM GENERAL

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ATA 36 – PNEUMATIC CONTROL AND INDICATION

ISSUE 3


CONTROL

The BLEED AIR panel located within the overhead panel controls engines and APU bleed valves, Pressure Reducing Valves (PRV) and the CABIN or COCKPIT supply valves. An XBLEED pushbutton can also control the bleed air common feeder duct cross bleed valve.

FIGURE 02-36-15-00 OVERHEAD BLEED AIR CONTROL PANEL

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SYNTHETIC TABLE

TO ACTIVATE CONTROL FUNCTION

TO DE-ACTIVATE SYNOPTIC

Automatic mode

Automatic mode wing

ANTI-ICE O'RIDE

When pushed, overrides the BASC automatic control and closes the corresponding HP valve.

Push OFF

Automatic mode

valve not closed

The normal position is automatic mode, PRV regulates the bleed air pressure in the common feeder duct. In OFF position, the PRV is closed.

Push OFF

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TO ACTIVATE

CONTROL FUNCTION TO DE-ACTIVATE

SYNOPTIC

Automatic mode

Push OFF

Activates the automatic operation of the APU bleed valve when the APU is in operation. The valve position is also controlled by the APU computer. In O’RIDE position, the valve is open, it is closed in OFF position.

Push O'RIDE

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TO ACTIVATE


SYNOPTIC

Automatic mode

or

Push ISOL

Controls the cross bleed valve which isolates the two sides of the bleed air common feeder duct. In normal position (automatic), the cross bleed valve is closed except if wing anti-icing system is in operation or heat exchanger ventilation jet pump valve is open or one engine is inoperative. In ISOL position, the bleed air sources are separated, in OPEN position they are interconnected.

Push OPEN

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TO ACTIVATE


SYNOPTIC

Automatic mode

In automatic mode, controls the cabin conditioning control valve via the air conditioning computer. In OFF position, closes the cabin conditioning valve.

Push OFF

Automatic mode

In automatic mode, controls the cockpit conditioning control valve via the air conditioning computer. In OFF position, closes the cockpit conditioning valve.

Push OFF

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INDICATION

BLEED AIR SYNOPTIC

The bleed air synoptic window can be selected by the pilot to be displayed on one or both center MDU.

Cockpit air conditioning valve

FIGURE 02-36-15-01 BLEED AIR SYNOPTIC INDICATIONS

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COLOR SYMBOLOGY

FIGURE 02-36-15-02 COCKPIT SYMBOL COLOR CODE

FIGURE 02-36-15-03 ENGINE SYMBOL COLOR CODE

FIGURE 02-36-15-04 VALVE SYMBOL COLOR CODE

FIGURE 02-36-15-05 FLOW LINE COLOR CODE

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ERRONEOUS INDICATION

APU bleed valve and flow line

When APU is stopped the bleed valve is amber (A) instead of gray (B).

FIGURE 02-36-15-06 APU BLEED VALVE ERRONEOUS INDICATION

Bleed flow line erroneous indications

In case of RH engine stopped with XBLEED closed, the right main bleed flow line is green (A) instead of gray (B).

CKPT

FIGURE 02-36-15-07 BLEED FLOW LINE ERRONEOUS

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DGT94085

ATA 36 – PNEUMATIC SYSTEM PROTECTION

ISSUE 3


INTRODUCTION

The pneumatic system is protected by conventional trip-free circuit breakers located above the overhead panel and by an overheat protection.

CIRCUIT BREAKERS

FIGURE 02-36-20-00 BLEED AIR CIRCUIT BREAKERS

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ATA 36 – PNEUMATIC SYSTEM PROTECTION

DGT94085


MAIN PROTECTIONS

OVERHEAT

To prevent any bleed air duct overheating (335°C), at a duct temperature of 305°C the BASC starts to close the associated HP valve. In the event of crew or passenger duct temperature exceeding 335°C or wing anti-icing duct temperature exceeding 310°C, probes within the duct trigger the BLEED .. OVHT on CAS window display. In this case, the OFF position of the HP pushbutton overrides the BASC automatic control of the valve and activates the valve motor to the closed position.

ENGINE START

If during an engine start the associated HP valve does not automatically close, a message, HP .. FAILED is displayed within CAS window. In this case, the OFF position of the HP pushbutton overrides the BASC automatic control of the valve and activates the valve motor to the closed position.

For more information, refer to CODDE 2 / ABNORMAL PROCEDURES / ATA 36.

APU

The APU electronic control unit monitors valve operation so that the APU EGT limit is not exceeded. (APU bleed valve is fully open as long as the EGT limit is not reached).

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ATA 36 – PNEUMATIC NORMAL OPERATION

ISSUE 3


INTRODUCTION

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-FLIGHT OPERATION WITHOUT ANTI-ICE

OVERHEAD PANEL

FIGURE 02-36-25-00 BLEED AIR OVERHEAD PANEL

BLEED SYNOPTIC

FIGURE 02-36-25-01 BLEED SYNOPTIC

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ATA 36 – PNEUMATIC NORMAL OPERATION

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ATA 36 – PNEUMATIC ABNORMAL OPERATION

ISSUE 3


INTRODUCTION

In the following, typical abnormal situations have been illustrated to help the crew to understand the symbols provided in the various panels and displays.

BLEED OVERHEAT

ABNORMAL STATUS

FIGURE 02-36-30-00 BLEED SYNOPTIC

CONTEXT RESULT

BASC fails to close the HP 1 valve

BLEED 1 OVHT CAS message

+ light on

LH flow lines in amber

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AFTER PROCEDURE COMPLETE

FIGURE 02-36-30-01 HP1 PUSHBUTTON SET TO OFF

FIGURE 02-36-30-02 BLEED SYNOPTIC WITH HP1 OFF

ACTION RESULT

Corresponding HP pushbutton pushed to set OFF

HP1 closes, OFF label displayed in amber

HP1 valve and line in gray

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CAS MESSAGES

CAS MESSAGE DEFINITION

APU FAULT Could indicate that APU bleed air valve has been commanded to close and has failed to do so.Refer also to ATA 49

BLEED .. OVHT Overheat detected in bleed air system

BLEED .. PYLON OVHT Overheat detected in engine pylon

CROSS BLEED FAIL Malfunction of the cross bleed valve

HP .. FAILED HP bleed valve detected failed

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F2000EX EASY 02-36-00 ATA 36 – PNEUMATIC CODDE 1 PAGE 1 … · 2012. 6. 27. · ATA 36 –PNEUMATIC DESCRIPTION DGT94085 DASSAULT AVIATION Proprietary Data HPBLEED AIR The main

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