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F2000EX EASY 02-36-00
CODDE 1 PAGE 1 / 2
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
02-36-00 F2000EX EASY
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ATA 36 – PNEUMATIC TABLE OF CONTENTS
DGT94085
DASSAULT AVIATION Proprietary Data
INTENTIONALLY LEFT BLANK
F2000EX EASY 02-36-05
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ATA 36 – PNEUMATIC GENERAL
ISSUE 3
DASSAULT AVIATION Proprietary Data
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
02-36-05 F2000EX EASY
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ATA 36 – PNEUMATIC GENERAL
DGT94085
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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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CODDE 1 PAGE 1 / 6
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ATA 36 – PNEUMATIC DESCRIPTION
ISSUE 3
DASSAULT AVIATION Proprietary Data
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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ATA 36 – PNEUMATIC DESCRIPTION
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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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ATA 36 – PNEUMATIC DESCRIPTION
ISSUE 3
DASSAULT AVIATION Proprietary Data
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.
02-36-10 F2000EX EASY
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ATA 36 – PNEUMATIC DESCRIPTION
DGT94085
DASSAULT AVIATION Proprietary Data
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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INTENTIONALLY LEFT BLANK
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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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ATA 36 – PNEUMATIC CONTROL AND INDICATION
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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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ATA 36 – PNEUMATIC CONTROL AND INDICATION
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TO ACTIVATE
CONTROL FUNCTION TO DE-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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ATA 36 – PNEUMATIC CONTROL AND INDICATION
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TO ACTIVATE
CONTROL FUNCTION TO DE-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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ATA 36 – PNEUMATIC CONTROL AND INDICATION
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DASSAULT AVIATION Proprietary Data
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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ATA 36 – PNEUMATIC SYSTEM PROTECTION
ISSUE 3
DASSAULT AVIATION Proprietary Data
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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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
DASSAULT AVIATION Proprietary Data
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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DASSAULT AVIATION Proprietary Data
INTENTIONALLY LEFT BLANK
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CODDE 1 PAGE 1 / 4
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ATA 36 – PNEUMATIC ABNORMAL OPERATION
ISSUE 3
DASSAULT AVIATION Proprietary Data
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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ATA 36 – PNEUMATIC ABNORMAL OPERATION
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INTENTIONALLY LEFT BLANK