F900EX EASY 02-36-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-36 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 protection 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 F900EX EASY PAGE 2 / 2 CODDE 1 TABLE OF CONTENTS INTENTIONALLY LEFT BLANK
F900EX EASY 02-36-05 CODDE 1 PAGE 1 / 4 GENERAL INTRODUCTION The pneumatic system on the Falcon 900EX EASy uses engine and APU bleed air as a high and low pressure energy source for the air-conditioning, cabin and fuel and potable water tanks pressurization, and ice and rain protection system.
02-36-05 F900EX EASY PAGE 2 / 4 CODDE 1 GENERAL FIGURE 02-36-05-00 FLIGHT DECK OVERVIEW
F900EX EASY 02-36-05 CODDE 1 PAGE 3 / 4 GENERAL SOURCES ON GROUND Bleed air from APU compressor discharge Low and high pressure bleed air supplied from engines No 1, 2 and 3 if running: - LP supplied from the last stage of LP compressor section - HP supplied from HP compressor discharge IN-FLIGHT Low and high-pressure bleed air supplied from engines No 1, 2 and 3: - LP supplied from the last stage of LP compressor section - HP supplied from HP compressor discharge
02-36-05 F900EX EASY PAGE 4 / 4 CODDE 1 GENERAL INTENTIONALLY LEFT BLANK
F900EX EASY 02-36-10 CODDE 1 PAGE 1 / 4 DESCRIPTION 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 all three engines. The bleed air from the APU is supplied, on the ground only, from a plenum surrounding the combustor. FIGURE 02-36-10-00 ENGINE BLEED AIR PORTS
02-36-10 F900EX EASY PAGE 2 / 4 CODDE 1 DESCRIPTION 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 3 and the left side of No 2 engine bleed ports. An auxiliary outboard bleed port on the No 1 and No 2 engines provides fuel tank pressurization. The outboard bleed port of the No 3 engine is not used. HP BLEED AIR The main sources 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. BLEED-AIR SYSTEM CONTROL All three 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 and No 2 engine anti-ice pushbuttons and the HP valve pushbutton. Using the inputs provided, the BASC regulates the HP valves position and controls warning circuits 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 the wing and engine anti-ice systems are satisfied. In case of air conditioning requirements without anti-ice, the BASC opens the HP valves to 70% max. For air conditioning requirements with anti-ice, the BASC can open the HP valves up to 100%. If the WINGS O RIDE pushbutton is selected, the BASC automatic control of HP1 and HP3 is overridden and the valves are fully open. If ENG 2 O RIDE pushbutton is selected, the BASC control of HP 2 is overridden and the valve is fully open. The override position of the anti-ice pushbuttons are only used in case of BASC failure.
F900EX EASY 02-36-10 CODDE 1 PAGE 3 / 4 DESCRIPTION ENGINE LP + HP BLEED-AIR MIXING At the outlet of each engine, airflow from the main LP and HP ports are mixed by venturiaction. The resulting pressure is greater than LP bleed-air pressure. The mixed airflow supplies a common bleed air manifold. Bleed air back flow from an operating engine to an inoperative engine, an engine with a lower power setting, or injection of HP bleed air into the LP bleed-air system is prevented by check valves. LP bleed air (from main or auxiliary sources) is available upon operation of any engines. There are no LP bleed-air shut-off valves. APU BLEED AIR When the airplane is on the ground, the bleed air from the APU can supply the common bleed-air manifold 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. MANIFOLD The manifold supplies a mixture of HP and LP air to the pilot and passenger air-conditioning systems as well as to the wing and No 2 engine S-duct anti-icing systems. An auxiliary LP port on engines No 1 and 2 feeds the fuel tank pressurization system. Three auxiliary HP ports feed the anti-icing systems of the No 1, 2 and 3 engine air intakes. Pressurization jet pump and wastewater lines are supplied by HP air from the No 1 and 2 engines and the APU. The manifold can be divided into two separate subsystems by means of an electrically motor-operated isolation valve. The valve is normally selected open as long as no fault (leakage, smoke,...) is detected in either of the subsystems. One side of the isolation valve is connected to the No 1 and No 3 engines and supplies compressed air to the cockpit and baggage compartment air-conditioning and the wing anti-icing systems. The other side is connected to the No 2 engine and supplies the passenger cabin air-conditioning and the S- duct anti-icing systems. ISOLATION VALVE The ISOL rotary switch, located on the BLEED AIR overhead panel, controls the electrically operated isolation valve. When the isolation valve is closed, the manifold is divided into two separate systems. One system receives bleed air from the No 1 and No 3 engines and the other system receives bleed air from the No 2 engine or from the APU (when the airplane is on the ground).
02-36-10 F900EX EASY PAGE 4 / 4 CODDE 1 DESCRIPTION APU BLEED VALVE The APU bleed valve is controlled by the APU pushbutton located on the BLEED AIR overhead panel. When it is open, APU bleed air supplies the pneumatic system. If the APU pushbutton is switched to AUTO position, the APU bleed valve is fully open as long as: - the APU is in operation, - the T5 limit is not reached, - the Power Lever Angle (PLA) is below 54. When the APU pushbutton is switched to OFF position, the APU bleed valve is closed regardless of engine speed or electrical signals received from the APU electronic control unit. DISTRIBUTION FIGURE 02-36-10-01 BLEED AIR SYSTEM GENERAL
F900EX EASY 02-36-15 CODDE 1 PAGE 1 / 6 CONTROL AND INDICATION CONTROL The bleed air panel, located within the overhead panel, controls engine and APU bleed valves and isolation valves for the CABIN, COCKPIT and BAG compartments. An isolation rotary switch can also isolate the bleed air manifold into two independent manifolds in the event of a failure. FIGURE 02-36-15-00 OVERHEAD BLEED AIR CONTROL PANEL
02-36-15 F900EX EASY PAGE 2 / 6 CODDE 1 CONTROL AND INDICATION SYNTHETIC TABLE CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC Automatic mode Pushbutton Status light When pushed, overrides the BASC and closes the corresponding HP1, HP2 or HP3 valves Automatic mode with WINGS O RIDE for HP1 or HP3, ENG 2 O RIDE for HP2 Push OFF Pushbutton Status light 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 and Power Lever Angle micro switches Automatic mode Push OFF
F900EX EASY 02-36-15 CODDE 1 PAGE 3 / 6 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC Status light Automatic mode Pushbutton In automatic mode, automatically controls the cabin conditioning valve. In ON position, opens the CABIN conditioning valve. Push ON In OFF position, closes the CABIN conditioning valve Status light Push OFF Status light Horizontal position Controls the isolation valve which isolates the two sides of the bleed air manifold Rotary switch Vertical position
02-36-15 F900EX EASY PAGE 4 / 6 CODDE 1 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC Status light Automatic mode Pushbutton In automatic mode, automatically controls the cockpit conditioning valve. In ON position, opens the CKPT conditioning valve Push ON In OFF position, closes the CKPT conditioning valve Status light Push OFF For more information, refer to CODDE 1 / Chapter 02 / ATA 21
F900EX EASY 02-36-15 CODDE 1 PAGE 5 / 6 CONTROL AND INDICATION INDICATION BLEED AIR SYNOPTIC Bleed air indications are displayed on the MDU BLD synoptic. Cabin air conditioning valve Isolation valve Crew air conditioning valve LH manifold HP valve RH manifold FIGURE 02-36-15-01 BLD SYNOPTIC
02-36-15 F900EX EASY PAGE 6 / 6 CODDE 1 CONTROL AND INDICATION COLOR SYMBOLOGY FIGURE 02-36-15-02 COCKPIT SYMBOL COLOR CODE FIGURE 02-36-15-03 VALVE SYMBOL COLOR CODE FIGURE 02-36-15-04 FLOW LINE COLOR CODE
F900EX EASY 02-36-20 CODDE 1 PAGE 1 / 2 SYSTEM PROTECTION 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
02-36-20 F900EX EASY PAGE 2 / 2 CODDE 1 SYSTEM PROTECTION MAIN PROTECTION 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, the BLEED.. OVERHEAT CAS message is displayed. 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 with N2 less than 45%, the associated HP valve does not automatically close, HP.. FAIL 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 T5 limit is not exceeded (APU bleed valve is fully open as long as the T5 limit is not reached). When at least one power lever is advanced, the APU bleed valve automatically closes.
F900EX EASY 02-36-25 CODDE 1 PAGE 1 / 2 NORMAL OPERATION INTRODUCTION In the following, typical normal situation has been selected to help the crew to understand the symbols provided in the various panels and displays. IN-FLIGHT OPERATION WITHOUT ANTI-ICE FIGURE 02-36-25-00 BLEED AIR OVERHEAD PANEL FIGURE 02-36-25-01 BLD SYNOPTIC
02-36-25 F900EX EASY PAGE 2 / 2 CODDE 1 NORMAL OPERATION INTENTIONALLY LEFT BLANK
F900EX EASY 02-36-30 CODDE 1 PAGE 1 / 4 ABNORMAL OPERATION INTRODUCTION In the following, abnormal situation has been selected to help the crew to understand the EASy symbols provided in the various panels and displays. BLEED 1 OVERHEAT ABNORMAL STATUS FIGURE 02-36-30-00 BLD SYNOPTIC PAGE CONTEXT RESULT BASC fails to close the HP 1 valve BLEED 1 OVERHEAT + light on CAS message Flow line and HP 1 valve in amber
02-36-30 F900EX EASY PAGE 2 / 4 CODDE 1 ABNORMAL OPERATION AFTER PROCEDURE COMPLETE FIGURE 02-36-30-01 HP1 PUSHBUTTON SET TO OFF FIGURE 02-36-30-02 BLD SYNOPTIC PAGE WITH HP1 OFF ACTION RESULT HP1 closes Corresponding HP pushbutton pushed to set OFF Status light amber OFF HP1 valve and line in gray, OFF label displayed in amber
F900EX EASY 02-36-30 CODDE 1 PAGE 3 / 4 ABNORMAL OPERATION CAS MESSAGES CAS MESSAGE BLEED APU BLEED.. OVERHEAT BLEED OVERHEAT HP.. FAIL DEFINITION APU bleed air valve is not closed after take-off Overheating detected in engine (1/2/3) bleed air port Overheating detected without engine identification HP (1/2/3) is failed open
02-36-30 F900EX EASY PAGE 4 / 4 CODDE 1 ABNORMAL OPERATION INTENTIONALLY LEFT BLANK