FALCON 7X 02-29-05 ATA 29 – HYDRAULIC SYSTEM ......02-29-05 FALCON 7X PAGE 4 / 6 CODDE 1 ISSUE 2 ATA 29 – HYDRAULIC SYSTEM GENERAL DGT97831 DASSAULT AVIATION Proprietary Data HYDRAULIC

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ATA 29 – HYDRAULIC SYSTEM GENERAL

ISSUE 2

DASSAULT AVIATION Proprietary Data

ACRONYMS

B/U BackUpCAS Crew Alerting SystemEBHA Electrical Backup Hydraulic ActuatorEEC Electronic Engine ControllerEDP Engine Driven PumpENG EngineFADEC Full Authority Digital Electronic ControlFPGA Field Programmable Gate ArraysHYD SOV HYDraulic ShutOff Valve (also referred to as Hydraulic Firewall Shut Off

Valve)HSCB Hydraulic System Control BoardINBD InboardLH Left HandMAU Modular Avionics UnitN/W Nose WheelOUTBD OUTBoarDPFCS Primary Flight Control SystemPV Priority ValveRH Right HandSFCS Secondary Flight Control SystemSOV Shut Off ValveT/R Thrust ReverserWOW Weight on Wheels

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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.

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FIGURE 02-29-05-00 - HYDRAULIC POWER


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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.

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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.

.

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FIGURE 02-29-05-01 - FLIGHT DECK OVERVIEW

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ATA 29 – HYDRAULIC SYSTEM DESCRIPTION

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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

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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.

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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.

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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.

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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.

Refer to ATA 70 and 32 for additional information.


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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.

HYDRAULIC SHUT-OFF VALVE

In the event of an engine fire or hydraulic overheat, each EDP can be isolated from the Hydraulic System through an electrically-controlled HYDraulic Shut-Off Valve (HYD SOV), located in the suction lines. When activated, the HYD SOV isolates the suction line from the pump, preventing hydraulic fluid from reaching the engine, should an engine fire occur. A thermal relief valve protects the downstream system when the HYD SOV is closed. The five HYD SOV can be manually activated by the crew members through five CLOSE switches on the overhead panel and/or engine fire/handle button.

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FILTERING

Filtration components installed on the three hydraulic systems supply clean fluid to the hydraulic components. The filters contain:

- An electrical differential pressure indicator for on condition maintenance support purpose,

- A bypass valve to allow system operation with a clogged filter (return filter only).

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DESIGN PRINCIPLES

Hydraulic system was designed considering following design principles:

- Tube routing and placement of hydraulic components is designed so that no single aircraft failure would cause loss of more than one hydraulic system and no two hydraulic system failures would result in complete loss of flight control,

- Rotor burst considerations are addressed so at least one system is functional after a worst case tri-sector burst,

- No hydraulic generation system component is installed in the passenger or flight crew compartments.

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EQUIPMENT LOCATION

ENGINE DRIVEN PUMPS

Engine Driven Pump A1 is mounted on the engine 1. Engine Driven Pumps A2 and C2 are mounted on engine 2. Engine Driven Pumps A3 and B3 are mounted on engine 3.

FIGURE 02-29-15-00 - ENGINE DRIVEN PUMPS LOCATION

FIGURE 02-29-15-01 - ENGINE DRIVEN PUMPS VIEW

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HYDRAULIC SYSTEM EQUIPMENT

Backup pump, backup pump select valve and reservoirs are located in the service compartment.

FIGURE 02-29-15-02 - HYDRAULIC SYSTEM EQUIPMENT LOCATION


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ATA 29 – HYDRAULIC SYSTEM DESCRIPTION - SUPPLEME

1 NTARY INFORMATION

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FIGURE 02-29-15-03 - HYDRAULIC EQUIPMENTS

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ELECTRICAL POWER SUPPLY

Following paragraph describes the power supply of the different equipment of the hydraulic system.

Electrical protection is provided either:

- By Solid State Power Controllers (SSPC) ,

- By Circuit Breakers (CB).

Refer to ATA 24 – ELECTRICAL POWER for additional information.

EQUIPMENT POWER SUPPLY TYPE OF PROTECTION Backup pump RH Essential CB

EDP A1 SOV Battery 1 CB

EDP A3 SOV Battery 2 CB

EDP B2 SOV Battery 2 CB

EDP B3 SOV Battery 1 CB

EDP C2 SOV Battery 1 CB

EDP A1 depress valve RH Essential SSPC

EDP A3 depress valve LH Essential SSPC

EDP B2 depress valve LH Essential SSPC

EDP B3 depress valve RH Essential SSPC

LH HSCB LH Essentiel CB

RH HSCB RH Essentiel CB

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DETAILED ARCHITECTURE OF HYDRAULIC SYSTEM

FIGURE 02-29-15-04 - HYDRAULIC SYSTEMS SCHEMATIC

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COMPONENTS DETAILED DESCRIPTION

RESERVOIRS

Each of the three hydraulic systems contains a reservoir.

FIGURE 02-29-15-05 - RESERVOIR ASSEMBLY

SYSTEM A

RESERVOIR SYSTEM B

RESERVOIR SYSTEM C

RESERVOIR

450 cu. in

(7.4 liters)

575 cu. in

(9.4 liters)

200 cu. in

(3.3 liters)

The assembly is a bootstrap type, utilizing system high-pressure fluid acting on a piston and provides the following functions:

- Supply fluid to the system, or accept fluid from the system - Provide sufficient static pressure to deliver fluid to the pump - Collect air for manual removal with a bleed/relief valve. - Maintain sufficient pressure in the hydraulic system to energize seals for a period of 72

hours after aircraft shutdown to minimize air ingress into the system. The reservoir provides the necessary fluid volume demanded by the hydraulic system. Changes in fluid volume due to thermal expansion/contraction, system leakage, and differential area of the user actuators have been taken into account in sizing the volume of each reservoir.

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The major components of the reservoir assembly include: - Low-pressure storage chamber, - Bootstrap cylinder, - Maintenance free accumulator, - Pressure maintaining & dump valve, - Bleed / relief valve, - Quantity indicator, - Temperature transducer, - Temperature switch.

FIGURE 02-29-15-06 - HYDRAULIC RESERVOIR

Low-Pressure Storage Chamber

The low-pressure piston is acted upon by the bootstrap piston to maintain chamber pressure.

System A and B reservoirs each utilize the same diameter storage chamber, while the system C reservoir utilizes a smaller storage chamber piston diameter.

A drain provided on the atmospheric side of the piston head routes any leakage fluid overboard.

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Bootstrap Cylinder

This assembly contains a small-area piston exposed to system pressure, nominally 3000 psig (207 bar), which provides force to drive the low-pressure piston and pressurize the reservoir.

Maintenance Free Accumulator

This accumulator provides the pressure and volume to maintain seal energisation for a period of 72 hours after aircraft shutdown.

Pressure Maintaining Valve

It is mounted in the reservoir manifold to provide for: - Maintaining bootstrap pressure without system pressure being applied, - To protect the reservoir from overpressurization.

EDP

System A and B EDP

Systems A and B each use two Engine Driven Pumps (EDP), as the primary source of supply of pressurized hydraulic fluid for the flight control and utility systems.

The Parker Model AP1V is a conventional axial piston type pump wherein a cylinder barrel containing nine pistons is driven by an external power source.

The pump timing and displacement controls provide for low-pressure ripple and smooth response to rapid changes in flow demand. Each of the System A & B EDP incorporates an integral attenuator ball on the discharge to provide pressure ripple and noise reduction.

■ Depressurization mode

The FADEC will energize the EDP de-pressurization solenoids to minimize engine drag torque for ground starts and for in air engine restarts. If all three engines are non-operational during flight but are windmilling at a speed greater than 15% N2, the EDP A1, A3, B3, and B2 will not be de-pressurized so that they can provide limited hydraulic power to the hydraulic systems from the windmilling engines: PFCS. The EDP will be depressurized when windmilling engine speed reduces below 15% N2 to minimize the engine load during a relight attempt. The pump will produce full pressure when its respective engine speed is greater than 40% on increasing speed to minimize starting and windmilling torque loads on that engine. The Hydraulic System Controller will energize the EDP de-pressurization solenoids to minimize heat rejection into the system, if required.

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EDP A3 or B2 will be de-pressurized when the system fluid reaches 92°C to minimize heat rejection into the system (if EDP A1 or B3 is producing pressure). If the Backup Pump is commanded on and is producing pressure, EDP B3 and B2 will be depressurized (to protect the Standby Pump).

System C EDP

This pump provides same functions as EDP of systems A and B.

The operation and pressure control features of the System C EDP are very similar to the System A & B EDP. However, due to its smaller displacement and subsequently lower load on the engine gearbox, a depressurization valve and solenoid are not included with this pump.

PRESSURE TRANSDUCERS

The pressure transducer transmits electrical signals, proportional to each hydraulic system pressure, to the crew members for monitoring of pressure in each system. There is one pressure transducer located downstream of the filter pressure element in each system module (3 total).

PRESSURE SWITCHES

Each hydraulic pump output (the EDP and the Backup Pump) is monitored by a dedicated pressure switch. These switches are used to annunciate hydraulic pump specific faults to the cockpit crew when pump pressure falls below a predetermined value.

BACKUP PUMP SELECT VALVE

This valve is used to power system A for maintenance activities only. The valve will switch both the suction and discharge lines of the backup pump from system A to B. The select valve is designed to prevent any possibility of fluid propagating from one system to another by utilizing rip-stop construction, such that any structural failure will not result in the loss of both system A and B hydraulic pressure. The valve incorporates an integral pin to allow latching in both the “GROUND” (System A powered) and “FLIGHT” (System B powered) positions. An electrical switch is provided to status spool position to prevent dispatch with the valve set to the “GROUND” position.

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FIGURE 02-29-15-07 - BACKUP PUMP SELECT VALVE

HYDRAULIC SYSTEM CONTROL BOARD

The HSCB controls the backup pump and EDP A3, B3 and B2 depressurization solenoids. The HSCB will depressurize the EDP to control fluid temperature. The HSCB will command the EDP B3 and B2 pumps to depress when the standby pump is commanded ON. The HSCB implements the logic using two electronic components called Field Programmable Gate Arrays (FPGA):

- One FPGA is used to implement the logic for EDP A3 and B2 depress solenoids. - The other is used to implement the logic for the backup pump and EDP B3 depress

solenoid. Circuits for the two FPGA are powered by different buses. Therefore, the loss of one bus will only disable part of the HSCB.


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ATA 29 – HYDRAULIC SYSTEM CONTROLS AND INDICATIONS

ISSUE 2


CONTROLS

The hydraulic system is mainly controlled through the switches of the HYDRAULICS section of the Overhead Panel:

- The five Hydraulic Shut-Off Valves (HYD SOV) are controlled by SHUT OFF A1, A3, B2, B3 and C2 guarded pushbuttons,

- The backup pump is controlled by the "BACKUP PUMP" pushbutton.

FIGURE 02-29-20-00 - HYDRAULICS OVERHEAD PANEL CONTROL

The five HYD SOV can also be activated through the respective engine FIRE guarded pushbuttons on the Fire Control Panel.

FIGURE 02-29-20-01 – HYDRAULIC FIREWALL SHUT-OFF VALVE CONTROL ON FIRE CONTROL PANEL

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SYNTHETIC TABLE

TO ACTIVATECONTROL FUNCTION

TO DEACTIVATESYNOPTIC

OPEN EDP A1

HYD SOV open

EDP A1 HYD SOV

closed

CLOSE

EDP A1 HYD SOV is not in its

commanded position

Guarded pushbuttons control the closing of the corresponding HYD SOV:

- Unlighted open (normal): HYD SOV is open,

- CLOSE: HYD SOV is closed.

EDP A1

HYD SOV invalid data

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TO ACTIVATE

CONTROL FUNCTION TO DEACTIVATE

SYNOPTIC

Backup pump

stopped and ready to supply

System B Normal Backup pump

started and supplying System B

ON ON mode running

OFF OFF mode

Invalid data

Backup pump switch controls the Backup Pump

This pushbutton cycles through:

- Unlighted auto: Backup Pump starts when the pressure drops in systems A and B,

- ON: Backup Pump runs continuously,

- OFF: Backup Pump shutdown or failure.

Short push: Normal/OFF

Long push: ON.

No control available for crew members.

Indicating a ground maintenance

operation.

Test


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INDICATIONS

Indications related to the Hydraulic system are provided within the HYDraulic synoptic and within the STATus page.

The HYDraulic (HYD) synoptic page displays the three hydraulic systems and the distribution of users between the systems:

- The five EDP, the backup pump and the five Firewall Shutoff Valves status are indicated by colour symbols and/or text fields

- The button WHEELS allow to access tire pressure and brake temperature information (these data are described in ATA 32)

- The following indications are available:

o Pressure of each hydraulic system,

o Fluid quantity of each hydraulic system,

o Fluid temperature of each hydraulic system,

o Shut-Off Valve positions (open, closed, transition),

o Accumulators pressure (park brake, thrust reverser being not monitored).

FIGURE 02-29-20-02 - HYDRAULIC SYNOPTIC IN NORMAL

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Hydraulic level indications

FIGURE 02-29-20-03 - HYDRAULIC LEVEL INDICATORS

Hydraulic fluid pressure indications

FIGURE 02-29-20-04 - HYDRAULIC FLUID PRESSURES


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Hydraulic pump status

Running Not running Failed Invalid data

FIGURE 02-29-20-05 - HYDRAULIC PUMP STATUS

Equipment status

In normal operation, symbols are green. If a failure occurs in a system, the symbols of equipment powered by this system become amber.

For flight control actuators connected to systems A and B, or A and C, or B and C, the corresponding symbols are:

- Green, in normal operating conditions, - Amber, in case of total hydraulic power loss, - Half green / half amber in case of loss of one system.

FIGURE 02-29-20-06 - SYMBOLS OF FLIGHT CONTROLS CONNECTED TO A AND B

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Park brake accumulator

FIGURE 02-29-20-07 - PARK BRAKE ACCUMULATOR


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STATUS synoptic

At the top of the STATus page, following information on the three Hydraulic systems are summarized:

- Hydraulic quantity, - Hydraulic pressure, - Hydraulic Temperature.

FIGURE 02-29-20-08 - STATUS SYNOPTIC PAGE

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ATA 29 – HYDRAULIC SYSTEM CONTROL AND INDICATIONS - SUPPLEMENTARY

INFORMATION ISSUE 2


No supplementary information to be provided on Controls and Indications at present time.

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ATA 29 – HYDRAULIC SYSTEM SYSTEM PROTECTIONS

ISSUE 2


SYSTEM MONITORING

Monitoring of following parameters is provided by the system:

- Hydraulic fluid pressure downstream of EDP or back up pump,

- Temperature of the Hydraulic fluid,

- Hydraulic fluid quantity in each tank,

- Position of the back up pump selector for flight,

- Condition of the filters.

Refer to CODDE2 for a complete list and description of CAS messages.

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ATA 29 – HYDRAULIC SYSTEM SYSTEM PROTECTIONS

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ACTIVE PROTECTIONS

OVERPRESSURE PROTECTION

Main system

Each hydraulic system comprises a pressure relief valve located in the filter manifold, protecting the system in the event of a runaway pump compensator.

Reservoir

A bleed and relief valve is integrated to each system reservoir for air removal and overpressure protection.

OVERHEAT PROTECTION

For Systems A, B: - EDP A3 and B2 are depressurized automatically when the hydraulic fluid gets too hot. - This depressurization is controlled by a fluid temperature switch located in the low

pressure section of each system reservoir. Additionally, in case of high temperature within the reservoirs of systems A and B:

- Hydraulic fluid is routed to an overboard drain - This is controlled through a thermal fuse:

o System A: when fluid reaches 143° C o System B: when fluid reaches 177° C

For System C: - Hydraulic Shut Off Valve C2 is automatically closed when the hydraulic fluid gets too

hot: 125 °C. - This is controlled by a fluid temperature switch located in a tee fitting directly mounted in

the system return port.

PRIORITY VALVES

As mentioned in the "DESCRIPTION" sub-section, a priority valve is installed on system A and B ahead of the utility users of the hydraulic system giving pressure delivery priority to the flight control components that are essential for flight and for the brakes system on ground.

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ATA 29 – HYDRAULIC SYSTEM SYSTEM PROTECTIONS - SUPPLEMENTARY

INFORMATION ISSUE 2


No supplementary information to be provided on system protection at present time.

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ATA 29 – HYDRAULIC SYSTEM GROUND OPERATION

ISSUE 2


HYDRAULIC FILLING VALVE

Refer to Ground Servicing manual.

Documents

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