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Ata 29 – Hydraulic System Codde 1 Page 1 / 6 General Dgt97831 Issue 2

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Ata 29 – Hydraulic System Codde 1 Page 1 / 6 General Dgt97831 Issue 2 FALCON 7X 02-29-05 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 1 / 6 GENERAL DGT97831 ISSUE 2 ACRONYMS B/U BackUp CAS Crew Alerting System EBHA Electrical Backup Hydraulic Actuator EEC Electronic Engine Controller EDP Engine Driven Pump ENG Engine FADEC Full Authority Digital Electronic Control FPGA Field Programmable Gate Arrays HYD SOV HYDraulic ShutOff Valve (also referred to as Hydraulic Firewall Shut Off Valve) HSCB Hydraulic System Control Board INBD Inboard LH Left Hand MAU Modular Avionics Unit N/W Nose Wheel OUTBD OUTBoarD PFCS Primary Flight Control System PV Priority Valve RH Right Hand SFCS Secondary Flight Control System SOV Shut Off Valve T/R Thrust Reverser WOW Weight on Wheels DASSAULT AVIATION Proprietary Data 02-29-05 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 2 / 6 CODDE 1 GENERAL ISSUE 2 DGT97831 INTRODUCTION GENERAL The hydraulic power system provides pressure for actuation of: - Primary Flight Controls System (PFCS: ailerons, elevators, rudder and spoilers), - Secondary Flight Controls System (SFCS: slats, flaps and airbrakes), - landing gear, brakes and nose wheel steering, - Thrust reverser of engine 2. DASSAULT AVIATION Proprietary Data FALCON 7X 02-29-05 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 3 / 6 GENERAL DGT97831 ISSUE 2 FIGURE 02-29-05-00 - HYDRAULIC POWER DASSAULT AVIATION Proprietary Data 02-29-05 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 4 / 6 CODDE 1 GENERAL ISSUE 2 DGT97831 HYDRAULIC POWER Hydraulic power is supplied by: - The primary hydraulic systems during normal flight operation - The auxiliary hydraulic supply o On ground if primary hydraulic power is not available or for maintenance operations, o In flight in case of failure of the primary hydraulic system. The primary hydraulic power supply features three independent hydraulic systems (referred to as A, B, and C systems), each operating with hydraulic fluid at a nominal pressure of 3000 psi (207 bar). It is powered by five Engine Driven Pumps (EDP). The auxiliary hydraulic supply, which is provided by the electrical backup pump and selector valve, provide back-up power between 2900 psi (200 bar) and 1500 psi for system B as well as power to systems A or B for ground maintenance activities. DASSAULT AVIATION Proprietary Data FALCON 7X 02-29-05 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 5 / 6 GENERAL DGT97831 ISSUE 2 FLIGHT DECK OVERVIEW CONTROLS Crew control of the Hydraulic system is performed - Primarily via the HYDRAULIC section of the overhead panel (OP) - Via the Fire Control Panel in case of engine fire. INDICATIONS Crew indications with regard to Hydraulic system are located in: - The HYDraulic synoptic - The STATus page synoptic for a recapitulative of main parameters concerning the Hydraulic system, - The STATus synoptic / FAULT tab for fault messages - The ENG-CAS window for CAS messages. DASSAULT AVIATION Proprietary Data 02-29-05 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 6 / 6 CODDE 1 GENERAL ISSUE 2 DGT97831 FIGURE 02-29-05-01 - FLIGHT DECK OVERVIEW DASSAULT AVIATION Proprietary Data FALCON 7X 02-29-10 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 1 / 8 DESCRIPTION DGT97831 ISSUE 2 GENERAL Each of the three hydraulic systems contains: - A reservoir for storage of hydraulic fluid, - One to three hydraulic pumps, - An Hydraulic Shut Off Valve associated to each Engine Driven Pump, - A Priority Valve for systems A and B. FIGURE 02-29-10-00 - HYDRAULIC SYSTEMS SCHEMATIC DASSAULT AVIATION Proprietary Data 02-29-10 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 2 / 8 CODDE 1 DESCRIPTION ISSUE 2 DGT97831 GENERATION GENERAL The pumps of the hydraulic system are driven: - Mechanically via the accessory gear box for the 5 Engine Driven Pumps (EDP), - Electrically for the backup pump. Repartition of hydraulic pumps on each hydraulic system is the following: - System A is powered by two EDP: o One on engine 1 (A1) o One on engine 3 (A3), - System B is powered by two EDP: o One on engine 2 (B2), o One on engine 3 (B3) o The electrical backup pump, - System C is powered by a single EDP: o On engine 2 (C2). Additionally to the normal hydraulic systems generation: - The spoilers feature a local Electrical Backup Hydraulic Actuator (EBHA), - The braking system and the thrust reverser feature an accumulator. RESERVOIRS Each of the three hydraulic systems stores hydraulic fluid in a dedicated reservoir embedding its own accumulator. Each reservoir is pressurized by its corresponding hydraulic system to avoid pump cavitation and draining. No bleed air is used to pressurize the hydraulic tanks. Fluid quantity can be visually checked on the reservoir itself or on the hydraulic synoptic. Fluid temperature for each reservoir is also given on the hydraulic synoptic. ENGINE DRIVEN PUMPS (EDP) General The Falcon 7X hydraulic system uses five EDP of two different sizes: - Systems A and B use a 1-gallon frame size pump, - System C uses a 0.5 gallon frame size pump. The self-regulating, piston-type EDP are driven by the accessory gearbox of the corresponding engine. The regulated pressure output is 3000 ± 50 psi. DASSAULT AVIATION Proprietary Data FALCON 7X 02-29-10 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 3 / 8 DESCRIPTION DGT97831 ISSUE 2 Depressurization mode The EDP of system A and B feature an electrical depressurization valve to minimize engine torque loads during engine ground start and restart: - EDP is depressurized when N2 is below 40% (engine speed increasing) and below 15% (engine speed decreasing), hydraulic pressure being reduced approximately 1000 psi. The depressurization mode is automatically commanded by the EEC of the engine. The depressurization mode is also automatically engaged in case of excessive temperature of system A or B. In that case, the depressurization mode is controlled by a dedicated control board named HSCB (Hydraulic System Control Board). The C2 pump has no depressurization capability. ELECTRICAL BACKUP PUMP General The electrical Backup Pump provides: - Back-up hydraulic power supply for system B, o mainly in case of a triple engine failure, o it is designed to allow an emergency descent with all engines out from 51,000ft - Power for ground maintenance activities on systems A and B: o For maintenance on system A, it is manually switched by using the FLIGHT/GROUND selector NOTE Prior to flight, Backup pump selector valve should be set on Hydraulic B. When activated, the backup pump operates continuously and delivers approximately 2,900 psi. The backup pump is supplied by the RH ESSential bus. The backup pump is air cooled by an internal fan attached to the motor rotor and is designed to provide sufficient cooling at or below 15,000 ft for a continuous use (no time limitation). NOTE Use of Backup pump above 15,000 ft should be limited in order to avoid overheating. DASSAULT AVIATION Proprietary Data 02-29-10 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 4 / 8 CODDE 1 DESCRIPTION ISSUE 2 DGT97831 Operation The Backup Pump is activated: - Automatically: by the HSCB (Hydraulic System Control Board) when the four EDP of systems A and B are (failed) not producing power (A1, A3, B2 and B3), ie. in case of a triple engine failure, - Manually: by setting the overhead panel BACKUP PUMP pushbutton to ON position. The backup pump can bet set to OFF, using the same BACKUP PUMP pushbutton of the overhead panel. HYDRAULIC SYSTEM CONTROL BOARD The Hydraulic System Control Board (HSCB): - Controls the backup pump, - Controls EDP A3, B3 and B2 depressurization valves in case of temperature increase and B2 and B3 depressurization valves in case of backup pump producing pressure in ON mode. BACKUP PUMP SELECT VALVE The backup pump select valve is manually operated on ground: - Allows the backup pump to be switched to power system A for maintenance activities only. - Incorporates a pin allowing latch in both the GROUND (system A powered) and FLIGHT (system B powered) positions - Switches both the suction and discharge lines of the backup pump from system B to A, no fluid mixing occurring between the two systems. An electrical position switch is used to annunciate a non standard flight configuration to the cockpit crew, which is any lever position other than “FLIGHT” position. DASSAULT AVIATION Proprietary Data FALCON 7X 02-29-10 ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 5 / 8 DESCRIPTION DGT97831 ISSUE 2 FIGURE 02-29-10-01 - BACKUP PUMP SELECT VALVE EBHA, THRUST REVERSER AND PARK BRAKE ACCUMULATORS The spoilers feature a dedicated Electrical Backup Hydraulic Actuator (EBHA), which provides local pressure with an internal accumulator in case of failure of the EDP C2. Two dedicated accumulators provide an hydraulic supply for: - Thrust reverser in case of a (total) system B hydraulic failure, - Park or emergency brake. ¾ Refer to ATA 70 and 32 for additional information. DASSAULT AVIATION Proprietary Data 02-29-10 FALCON 7X ATA 29 – HYDRAULIC SYSTEM PAGE 6 / 8 CODDE 1 DESCRIPTION ISSUE 2 DGT97831 DISTRIBUTION Each of systems A and B uses two Engine Driven Pumps (A1, A3, B2 and B3 pumps), as the primary source of supply of pressurized hydraulic fluid for: - The primary and the secondary flight controls, - The landing gear operation, and nose wheel steering - Normal and park braking, - Thrust reverser. Priority valves on system A and B give priority to flight controls and brakes in case of flow deficit. System C uses C2 pump to provide pressurized Hydraulic fluid to: - The spoilers - One barrel of right elevator - One barrel of right aileron. PRIORITY VALVES A priority valve is installed on system A and B ahead of the utility users of the hydraulic system giving flow delivery priority to the flight control components that are essential for flight and for the brakes system on ground. For example, the priority valves might be actuated when one EDP for system A or B is failed and the remaining pump produces insufficient flow to power the extension of landing gear, flaps, etc and to also power the flight controls: the priority valve then preserves pressure for the flight controls.
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