FALCON 7X
CODDE 1
02-29-05
ATA 29 – HYDRAULIC SYSTEM
PAGE 1 / 6
GENERAL
DGT97831
ISSUE 2
ACRONYMS
B/U
CAS
EBHA
EEC
EDP
ENG
FADEC
FPGA
HYD SOV
HSCB
INBD
LH
MAU
N/W
OUTBD
PFCS
PV
RH
SFCS
SOV
T/R
WOW
BackUp
Crew Alerting System
Electrical Backup Hydraulic Actuator
Electronic Engine Controller
Engine Driven Pump
Engine
Full Authority Digital Electronic Control
Field Programmable Gate Arrays
HYDraulic ShutOff Valve (also referred to as Hydraulic Firewall Shut Off
Valve)
Hydraulic System Control Board
Inboard
Left Hand
Modular Avionics Unit
Nose Wheel
OUTBoarD
Primary Flight Control System
Priority Valve
Right Hand
Secondary Flight Control System
Shut Off Valve
Thrust Reverser
Weight on Wheels
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02-29-05
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
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.
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FALCON 7X
CODDE 1
02-29-05
ATA 29 – HYDRAULIC SYSTEM
PAGE 3 / 6
GENERAL
DGT97831
ISSUE 2
FIGURE 02-29-05-00 - HYDRAULIC POWER
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02-29-05
PAGE 4 / 6
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
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.
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FALCON 7X
CODDE 1
02-29-05
ATA 29 – HYDRAULIC SYSTEM
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.
.
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02-29-05
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
GENERAL
ISSUE 2
DGT97831
FIGURE 02-29-05-01 - FLIGHT DECK OVERVIEW
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FALCON 7X
CODDE 1
02-29-10
ATA 29 – HYDRAULIC SYSTEM
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
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02-29-10
PAGE 2 / 8
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
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.
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FALCON 7X
CODDE 1
02-29-10
ATA 29 – HYDRAULIC SYSTEM
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.
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02-29-10
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
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.
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FALCON 7X
CODDE 1
02-29-10
ATA 29 – HYDRAULIC SYSTEM
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.
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02-29-10
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
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.
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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FALCON 7X
CODDE 1
02-29-10
ATA 29 – HYDRAULIC SYSTEM
PAGE 7 / 8
DESCRIPTION
DGT97831
ISSUE 2
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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FALCON 7X
02-29-15
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
PAGE 1 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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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02-29-15
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
PAGE 2 / 12
CODDE 1
DESCRIPTION - SUPPLEMENTARY INFORMATION
ISSUE 2
DGT97831
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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FALCON 7X
CODDE 1
02-29-15
ATA 29 – HYDRAULIC SYSTEM
PAGE 3 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
DESCRIPTION - SUPPLEMENTARY INFORMATION
ISSUE 2
DGT97831
FIGURE 02-29-15-03 - HYDRAULIC EQUIPMENTS
DASSAULT AVIATION Proprietary Data
FALCON 7X
02-29-15
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
PAGE 5 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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).
¾ 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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02-29-15
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
DESCRIPTION - SUPPLEMENTARY INFORMATION
ISSUE 2
DGT97831
DETAILED ARCHITECTURE OF HYDRAULIC SYSTEM
FIGURE 02-29-15-04 - HYDRAULIC SYSTEMS SCHEMATIC
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FALCON 7X
02-29-15
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
PAGE 7 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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
575 cu. in
200 cu. in
(7.4 liters)
(9.4 liters)
(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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02-29-15
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
DESCRIPTION - SUPPLEMENTARY INFORMATION
ISSUE 2
DGT97831
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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FALCON 7X
02-29-15
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
PAGE 9 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
PAGE 10 / 12
CODDE 1
DESCRIPTION - SUPPLEMENTARY INFORMATION
ISSUE 2
DGT97831
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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FALCON 7X
CODDE 1
02-29-15
ATA 29 – HYDRAULIC SYSTEM
PAGE 11 / 12
DESCRIPTION - SUPPLEMENTARY INFORMATION
DGT97831
ISSUE 2
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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FALCON 7X
CODDE 1
02-29-20
ATA 29 – HYDRAULIC SYSTEM
PAGE 1 / 8
CONTROLS AND INDICATIONS
DGT97831
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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02-29-20
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
PAGE 2 / 8
CODDE 1
CONTROLS AND INDICATIONS
ISSUE 2
DGT97831
SYNTHETIC TABLE
CONTROL
FUNCTION
TO ACTIVATE
OPEN
Unlighted open
(normal): HYD
SOV is open,
-
CLOSE: HYD
SOV is closed.
EDP A1
HYD SOV
open
EDP A1
HYD SOV
closed
Guarded
pushbuttons control
the closing of the
corresponding
HYD SOV:
-
SYNOPTIC
TO DEACTIVATE
CLOSE
EDP A1
HYD SOV
is not in its
commanded
position
EDP A1
HYD SOV
invalid data
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FALCON 7X
02-29-20
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
PAGE 3 / 8
CONTROLS AND INDICATIONS
DGT97831
ISSUE 2
CONTROL
FUNCTION
TO ACTIVATE
SYNOPTIC
TO DEACTIVATE
Backup
pump
stopped and
ready to
supply
System B
Normal
Backup
pump
started and
supplying
System B
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,
-
ON
ON mode
running
OFF
OFF mode
OFF: Backup
Pump shutdown
or failure.
Short push:
Normal/OFF
Invalid data
Long push: ON.
No control available for
crew members.
Indicating a ground
maintenance
operation.
Test
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FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
CONTROLS AND INDICATIONS
ISSUE 2
DGT97831
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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CONTROLS AND INDICATIONS
DGT97831
ISSUE 2
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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ATA 29 – HYDRAULIC SYSTEM
PAGE 6 / 8
CODDE 1
CONTROLS AND INDICATIONS
ISSUE 2
DGT97831
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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CODDE 1
02-29-20
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CONTROLS AND INDICATIONS
DGT97831
ISSUE 2
Park brake accumulator
FIGURE 02-29-20-07 - PARK BRAKE ACCUMULATOR
DASSAULT AVIATION Proprietary Data
02-29-20
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
PAGE 8 / 8
CODDE 1
CONTROLS AND INDICATIONS
ISSUE 2
DGT97831
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
DASSAULT AVIATION Proprietary Data
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
02-29-25
CODDE 1
CONTROL AND INDICATIONS - SUPPLEMENTARY
INFORMATION
PAGE 1 / 2
DGT97831
ISSUE 2
No supplementary information to be provided on Controls and Indications at present time.
DASSAULT AVIATION Proprietary Data
FALCON 7X
CODDE 1
02-29-30
ATA 29 – HYDRAULIC SYSTEM
PAGE 1 / 2
SYSTEM PROTECTIONS
DGT97831
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.
¾ Refer to CODDE2 for a complete list and description of CAS messages.
DASSAULT AVIATION Proprietary Data
02-29-30
PAGE 2 / 2
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
SYSTEM PROTECTIONS
ISSUE 2
DGT97831
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.
DASSAULT AVIATION Proprietary Data
FALCON 7X
ATA 29 – HYDRAULIC SYSTEM
02-29-35
CODDE 1
SYSTEM PROTECTIONS - SUPPLEMENTARY
INFORMATION
PAGE 1 / 2
DGT97831
No supplementary information to be provided on system protection at present time.
DASSAULT AVIATION Proprietary Data
ISSUE 2
FALCON 7X
CODDE 1
02-29-40
ATA 29 – HYDRAULIC SYSTEM
PAGE 1 / 2
GROUND OPERATION
DGT97831
ISSUE 2
HYDRAULIC FILLING VALVE
¾ Refer to Ground Servicing manual.
DASSAULT AVIATION Proprietary Data