INTRODUCTION SYSTEM 1 AND 2 - SmartCockpit
Transcript of INTRODUCTION SYSTEM 1 AND 2 - SmartCockpit
INTRODUCTION
Hydraulic power is provided by three independent and isolated systems designated 1,
2 and 3 and operate at a nominal pressure of 3000 psi.
SYSTEM 1 AND 2
Systems 1 and 2 are each powered by an Engine-Driven Pump (EDP), and an AC-
Motor Pump (ACMP). The EDPs designated as 1A and 2A are mounted on the
respective engine accessory gearbox, and hydraulically power systems 1 and 2 when
the engines are operating.
The ACMPs designated as 1B and 2B are used as essential pumps for takeoff,
approach, landing and in support of the EDPs in the event of failure. The ACMPs are
selectable through switches located on the HYDRAULIC control panel in the flight
compartment.
During normal operations, system 1 provides hydraulic pressure to the left side
primary flight controls and rudder, left and right flight spoilers, left and right ground
spoilers, and the left thrust reverser. System 2 provides hydraulic pressure to the right
side primary flight controls and rudder, left and right flight spoilers, main gear assist
(left and right main landing gear extension/retraction), right thrust reverser and
outboard brakes.
SYSTEM 3
System 3 is powered by two ACMPs designated as 3A and 3B, and are selectable
through switches located on the HYDRAULIC control panel in the flight
compartment. The ACMPs 3A and 3B provide hydraulic pressure to the primary flight
controls (all), left and right ground spoilers, landing gear side brace actuator and
doors, inboard and park/emergency brakes, and the nose wheel steering.
Hydraulic pump 3A normally runs continuously while pump 3B is used as an essential
pump for takeoff, approach, landing, and in support of the primary pump 3A in the
event of failure.
EMERGENCY HYDRAULIC POWER
In the event that all normal electrical power is lost, a Ram Air Turbine (RAT) is
deployed and will power an independent hydraulic pump for system 3.
HYDRAULIC ACCUMULATORS
The RAT uses an accumulator to maintain pressure at the reservoir during RAT
deployment. Two additional hydraulic accumulators are installed on the airplane and
are used by the brake control system. One is used for brake system 2, and the other for
brake system 3 emergency operation.
Bombardier Global Express - Hydraulics
Page 1
DISTRIBUTION TABLE SCHEMATIC
GX
_12_001
SYSTEM NO. 1 SYSTEM NO. 3 SYSTEM NO. 2
RUDDER
RIGHTELEVATOR
RIGHTAILERON
LEFT AND RIGHTMULTIFUNCTION
SPOILERS
MAIN LANDINGGEAR
OUTBOARDBRAKES
RUDDER
LEFTELEVATOR
LEFTAILERON
LEFT AND RIGHTMULTIFUNCTION
SPOILERS
LEFT AND RIGHTGROUND SPOILERS
LEFTREVERSER
RUDDER
LEFT ANDRIGHT ELEVATOR
LEFT ANDRIGHT AILERON
LANDING GEAR
NOSEWHEELSTEERING
LEFT AND RIGHTGROUND SPOILERS
GEARDOORS
INBOARD ANDPARK/EMER
BRAKES
RIGHTREVERSER
ENGINE-DRIVENPUMP(1A)
ACMOTORPUMP(1B)
ENGINE-DRIVENPUMP(2A)
ACMOTORPUMP(2B)
ACMOTORPUMP(3A)
ACMOTORPUMP(3B)
RATPUMP
Bombardier Global Express - Hydraulics
Page 2
HYDRAULIC SYSTEM DISTRIBUTION SCHEMATIC
GX
_12_002
SYSTEM 3SYSTEM 1
ELEVATOR RHELEVATOR LH
AILERON LH AILERON RH
MFS 2LH
MFS 4LH
MFS 3LH
GRND SPRH OUTBD
GRND SPLH OUTBD
MFS 1LH
THRUST REVLH
THRUST REVRH
GRND SPLH INBD
GRND SPRH INBD
NLGUPLOCK
NLGACTUATOR
NLGDOORS
NLGDOWNLOCK
NLGSTEERING
RH MLGACTUATORS
LH MLGUPLOCK
MLGDOORS
LH MLGACTUATORS
RH MLGUPLOCK
PARKINGBRAKE
BRAKELH OUTBD
BRAKELH INBD
BRAKERH OUTBD
BRAKERH INBD
ACMP 3A ACMP 3B RATPUMP
EDP1A
ACMP1B
SYSTEM 2
ACMP2B EDP
2A
RUDDER
MFS 2RH
MFS 4RH
MFS 3RH
MFS 1RH
LH MLGSIDEBRACE
RH MLGSIDEBRACE
Note:MFS = Multifunction Spoiler
Bombardier Global Express - Hydraulics
Page 3
SYSTEMS OVERVIEW SCHEMATIC
GX
_12_003
System pressure 1
System pressure 2
System pressure 3
AC motor pump
Engine-driven pump
RAT hydraulic pump
Central HydraulicSystem Components• Filters• Reservoir• Relief Valve• Press/temp Sensing Multifunctional Spoilers
Reverser
Rudder
Aileron
Ground Spoiler
Heat Exchanger Landing GearSteering and Brakes
AccumulatorsSystem 3 RAT (forward)System 3 Brake (aft)
Elevator
LEGEND
RAT Pump
AccumulatorSystem 2 Brake
Bombardier Global Express - Hydraulics
Page 4
HYDRAULIC SYSTEM INDICATION
The HYDRAULIC synoptic page provides an overview of normal system status, and
RAT deployment as represented below.
Hydraulic reservoirs, valve positioning, and pump operations are pictorially displayed.
System temperatures, fluid quantities and pressures are represented digitally. Flow
lines connect components and legends display system status.
HYDRAULIC SYNOPTIC PAGE
The synoptic page is displayed in detail later in this chapter.
HYDRAULIC CONTROL PANEL
The hydraulic control panel is located on the overhead panel in the flight
compartment. There are four switches which control electrically operated pumps for
each system. The function of each switch is described later in this chapter.
RAT
INBDBRAKES
PSI3000
3A 3B
3000PSI
54%
RUDL ELEV
L AILFLT SPLRS
GND SPLRSL REVERSER
RUDELEV RAIL RFLT SPLRSGEARREVERSER R
RUDL ELEV RL AIL R
GND SPLRSGEAR
NOSE STEERPARK/ BRAKEEMER
INBDBRAKES
PSI3000
OUTBDBRAKES
NORM
2B3A 3B
HYDRAULIC
3000PSI
3000PSI
2A
3000PSI
45 °C
1B
60%
45 °C
54%
45 °C
60%
1A
GX
_12_004
Reservoir
AC MotorPumpStatus
Engine-DrivenPumpStatus
HydraulicFluidTemperatureReadout
HydraulicFluidQuantityReadout
FirewallShutoffValvePosition
HydraulicPressureReadout
RATDeployed
HYDRAULICSYSTEM NO. 3
HYDRAULIC1B 3A 3B 2B
OFF
AUTO
OFF
ON ON ON
ON
OFF
AUTO
OFF
AUTOAAOA
GX
_12_005
Bombardier Global Express - Hydraulics
Page 5
HYDRAULIC SYNOPTIC PAGE (Cont)
RUDL ELEV
L AILFLT SPLRS
GND SPLRSL REVERSER
RUDELEV RAIL RFLT SPLRSGEARREVERSER R
RUDL ELEV RL AIL R
GND SPLRSGEAR
NOSE STEERPARK/ BRAKEEMER
INBDBRAKES
PSI3000
OUTBDBRAKES
NORM
2B3A 3B
HYDRAULIC
3000PSI
3000PSI
2A
3000PSI
45 °C
1B
60%
45 °C
54%
45 °C
60%
1A
GX
_12_006
3A 3BRAT
81%
3000PSI
Hydraulic RAT PumpDisplays RAT pumpdeployed and poweringsystem No. 3. The pumpsymbol and flow linesonly appear when theRAT is deployed.
Hydraulic Pumps 1A,2A, 1B, 2B, 3A, 3B andRAT
GreenAmber
White
Displays the condition ofeach of the hydraulicpumps.• – Pressure >1800 psi.• – Hydraulic supplyto system inoperative 1800 psi.• – Hydraulic pump isnot commanded to operate.
<
RAT
INBDBRAKES
PSI3000
3A 3B
3000PSI
54%
HYDRAULIC SYSTEM #3
Bombardier Global Express - Hydraulics
Page 6
HYDRAULIC SYNOPTIC PAGE (Cont)
RUDL ELEV
L AILFLT SPLRS
GND SPLRSL REVERSER
RUDELEV RAIL RFLT SPLRSGEARREVERSER R
RUDL ELEV RL AIL R
GND SPLRSGEAR
NOSE STEERPARK/ BRAKEEMER
INBDBRAKES
PSI3000
OUTBDBRAKES
NORM
2B3A 3B
HYDRAULIC
3000PSI
3000PSI
2A
3000PSI
45 °C
1B
60%
45 °C
54%
45 °C
60%
1A
GX
_12_007
Engine-Driven PumpInput Line• Green – SOV open.• Amber – SOV failed.• Red – SOV not closedwith the fire handlepulled.
Pressure ManifoldOutput Line• Green – Pressure> 1800 psi.• Amber 1800 psi.<
Reservoir Output Lines(all three systems)Flow line is green whensufficient reservoir quantityis displayed.
Pump Output Line• Green – Pressure>1800 psi.• Amber – Lowpressure 1800 psi.<
Pressure manifoldInput Line• Green – Pressure>1800 psi.• Amber – Lowpressure 1800 psi.<
Outboard BrakePressure ReadoutDisplays pressure in theoutboard brake system.• NORM Green –>1400 psi.• LO PRESS Amber –
1400 psi.<
Inboard BrakePressure ReadoutDisplays in incrementsof 50 psi, pressure inthe inboard brake system.• Green - between 1800and 3200 psi.• Amber – 1800 psi.• White – 3200 psi.
<>
Bombardier Global Express - Hydraulics
Page 7
HYDRAULIC SYNOPTIC PAGE (Cont)
RUDL ELEV
L AILFLT SPLRS
GND SPLRSL REVERSER
RUDELEV RAIL RFLT SPLRSGEARREVERSER R
RUDL ELEV RL AIL R
GND SPLRSGEAR
NOSE STEERPARK/ BRAKEEMER
INBDBRAKES
PSI3000
OUTBDBRAKES
NORM
2B3A 3B
HYDRAULIC
3000PSI
3000PSI
2A
3000PSI
45 °C
1B
60%
45 °C
54%
45 °C
60%
1AG
X_12_008
Fluid QuantitySymbol and readoutDisplays, incrementsof 2%, reservoir fluidquantity in thecorrespondingsystem.
System Distribution TableDisplays status ofcorresponding airplanesystems powered bysystem 1, 2, or 3.• White – Adequate pressure>1800 psi to operate.• Amber – Hydraulic supply tosystem inoperative 1800 psi.<
Hydraulic Pressure ReadoutDisplays, increments of 50, hydraulicpressure in the corresponding system,Normal operating pressure is 2950 to3050 psi.• White – Hydraulic pressure >3200 psi.• Green – Hydraulic pressure >1800 psiand 3200 psi.• Amber – Hydraulic pressure 1800 psi.
<<
Shutoff Valve toEngine Flow LineThe flow line from thefire wall SOV to theengine will display redif the SOV fails to close,when the fire handleis pulled.
Hydraulic Shutoff ValvePosition IndicatorDisplays valve open,closed and invalid data.
Hydraulic Fluid TemperatureReadoutDisplays, increments of 2°C,reservoir fluid temperature inthe corresponding system.• Green <96 C (205 F).• Amber 96 C (205 F).
° °° °>
Bombardier Global Express - Hydraulics
Page 8
HYDRAULIC SYNOPTIC PAGE SYMBOLS
The following represents the EICAS symbols and flow line logic for the hydraulic
synoptic page. The symbols are shown in serviceable and failure conditions.
EICAS PHILOSOPHY
GX
_12_009
VALVE AND FLOW LINE LOGIC
DIRECTION OF FLOW
VALVENOT FAILED
VALVEFAILED
OPEN
CLOSED
TRANSIT
INVALID
PUMP AND FLOW LINE LOGIC
INVALID
OFF
ON
PUMPFAILEDOFF
PUMPFAILEDON
DIRECTION OF FLOW
P
P
P
P
P
VALVE FAILEDFIRE HANDLE PULLED
VALVE FAILED TRANSITFIRE HANDLE PULLED
Bombardier Global Express - Hydraulics
Page 9
DESCRIPTION
HYDRAULIC SYSTEM 1 AND 2
Each system comprises an EDP, reservoir, ACMP, manifolds with pressure, return and
case drain filters, hydraulic shutoff valve, heat exchanger, and ground servicing panel.
Hydraulic overfill bottles for system 1 and 2 are provided and located near their
system components.
ENGINE-DRIVEN PUMPS
The EDPs 1A and 2A are used as primary pumps and draw fluid from the reservoirs
through hydraulic shutoff valves. Fluid is delivered to the applicable manifold, filtered
and distributed to the airplane’s hydraulically-actuated components.
AFT EQUIPMENT BAY COMPONENTS
GX
_12_010
Engine-Driven PumpLocated on the accessorydrive of each engine
GX
_12_011
Reservoirs
ACMPs
DirectReadingGauge
FilterManifolds
Bombardier Global Express - Hydraulics
Page 10
RESERVOIR
System 1 and 2 reservoirs are located at the top of the aft equipment bay. Fluid
quantity and temperature transducers are located on the reservoir and are indicated on
the HYDRAULIC synoptic page.
AC-MOTOR PUMPS (ACMP’S)
The backup ACMPs 1B and 2B pumps are normally operated in the AUTO mode and
come on automatically during takeoff, approach and landing, or in support of a
primary pump failure.
ACMPs 1B and 2B are powered from AC bus 3 and AC bus 2, respectively. Both
pumps are controlled by separate toggle switches on the flight compartment
HYDRAULIC control panel. Refer to External and APU Power - ACMP Operation
Electrical Pump operation in this chapter for external/APU ground services.
FILTER MANIFOLD
The filter manifold for system 1 is located on the left side of the aft equipment bay, and
on the right side for system 2. Each hydraulic system accommodates pressure, return
and case drain (pump lubrication fluid) filters, and a system pressure relief valve. They
also contain filter “pop-up” indicators to show when the filters are clogged. Two
pressure switches and a transducer are part of the pressure manifold and are used to
provide EICAS displays for pump failures and loss of system pressure. Fluid quantity
and temperature transducers are located on the reservoir and are indicated on the
HYDRAULIC synoptic page.
Bombardier Global Express - Hydraulics
Page 11
HYDRAULIC SHUTOFF VALVE CONTROL PANEL
Two switches are provided on the HYDRAULIC shutoff valve panel to isolate the
applicable shutoff valve in the event of a hydraulic overtemperature. These switches
should not be selected closed with the engine running except for isolation in the event
of system overtemperature. The engine-driven pump will cavitate and greatly reduce
the efficiency and life of the pump.
The purpose of isolation is to permit the fluid to cool and control the overtemperature,
without having to shut down the engine. These switches operate in parallel with the
switch in the fire handle to control the operation of the applicable hydraulic shutoff
valve.
HYDRAULIC SHUTOFF VALVES
Electrically-operated shutoff valves (normally open) are installed on the suction lines
for the engine-driven pumps 1A and 2A, and their position is indicated on the
HYDRAULIC synoptic page.
HYDRAULIC
R HYD SOV
CLOSED
L HYD SOV
CLOSED
GX
_12_012
Left/Right Hydraulic Shutoff Valve SwitchesControls the operation of the hydraulic shutoffvalve in the following condition:• CLOSED – When the switch is selected, itisolates the hydraulic fluid to the respectiveengine-driven pump by closing the hydraulicshutoff valve.
R HYD SOV
CLOSED
GX
_12_013
2B3A 3B
HYDRAULIC22 °C
1B
62%
38 °C
61%
20 °C
60%
DISCH
1 2
RPULL
HYDRAULIC SYNOPTIC PAGE
NOTE:The right SOVis shown, left issimilar.
Bombardier Global Express - Hydraulics
Page 12
The corresponding hydraulic shutoff valve is motored closed during an engine fire
condition (fire handle pulled), or selection of a HYD SOV switch. Selection of a HYD
SOV switch will illuminate a CLOSED legend on the switch to indicate the switch
position. When the hydraulic shutoff valve is closed, a L or R HYD SOV CLSD white
status message (described in Chapter 9, FIRE PROTECTION) is displayed on EICAS.
Deselection of either the fire handle or HYD SOV switch will command the SOV
open, and extinguish the message. Deselecting the HYD SOV switch will extinguish
the CLOSED legend.
HEAT EXCHANGER
System 1 heat exchanger is positioned within the left fuel feed tank, and system 2 in
the right. The purpose of each exchanger is to cool the case drain fluid (lubrication
fluid within each pump), prior to returning it to the reservoir.
If the fluid temperature is sufficiently cooled, a by-pass of the exchanger will allow the
fluid to go directly to the reservoir. Fuel in the wing feed tank is the cooling medium.
GX
_12_014
System 2 HeatExchanger
HeatExchanger
System 1 HeatExchanger
Bombardier Global Express - Hydraulics
Page 13
SYSTEM 2 ACCUMULATOR
The brake control system uses an accumulator from hydraulic system 2 for brake
operations.
There is a direct reading gauge to check the precharge condition of the accumulator.
Refer to Chapter 14, LANDING GEAR for more information on the brake and control
system.
GROUND SERVICE ACCESS
The ground service access for systems 1 and 2 is located in the aft equipment bay.
GX
_12_015
SYSTEM 2BRAKEACCUMULATOR
DIRECTREADINGGAUGE
Bombardier Global Express - Hydraulics
Page 14
HYDRAULIC SYSTEM 1 SCHEMATIC
GX
_12_016
Heat Exchanger
FIRE PULLHANDLE
ACPUMP
1B
1A
RESERVOIR
CaseDrain Fluid
FirewallShutoffValve
S
OW
OW
S
S
P
P
3000PSI
DIGITALREADOUT
EICAS
TOAIRPLANESYSTEMSCheck valve indicates
direction of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
ITEM OPERATES
Pressure switchesPump FailureDisplay to EICAS
PSI display to EICASPressure transducer
PRESSURE MANIFOLDLeft Engine-Driven Pump
LEGEND
1B
OFF
AUTO
ON
A
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTERELECTRICAL LOGIC
AC BUS 3
M
DISCH
1 2
LPULL
DC EMER BUS
DC POWERCENTER
CLOSED
Bombardier Global Express - Hydraulics
Page 15
HYDRAULIC SYSTEM 2 SCHEMATIC
GX
_12_017
Heat Exchanger
FIRE PULLHANDLE
ACPUMP
2 B
2A
RESERVOIR
CaseDrain Fluid
FirewallShutoffValve
S
OW
S
P
3000PSI
DIGITALREADOUT
EICAS
TOAIRPLANESYSTEMS
S
P
ITEM OPERATES
Pressure switchesPump FailureDisplay to EICAS
PSI display to EICASPressure transducer
PRESSURE MANIFOLDRight Engine-Driven Pump
2B
ON ON
OFF
AUTO
OFF
AUTOAA
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTERELECTRICAL LOGIC
AC BUS 2
M
DISCH
1 2
RPULL
DC EMER BUS
DC POWERCENTER
CLOSED
OW
Check valve indicatesdirection of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
LEGEND
Bombardier Global Express - Hydraulics
Page 16
HYDRAULIC SYSTEM 3
System 3 includes a reservoir, ACMPs 3A and 3B, RAT pump, manifold with
pressure, return and case drain filters heat exchanger, and ground servicing panel.
Hydraulic overfill bottles for the system are provided and located near system 3
components.
RESERVOIR
System 3 reservoir is located in the lower belly fairing. Fluid quantity and temperature
transducers are located on the reservoir and their indications are displayed on the
HYDRAULIC synoptic page.
ACMP’S 3A AND 3B
System 3 ACMPs are located in the lower belly fairing. System 3A pump is used as
primary pump (runs continuously in the ON position) and 3B as the backup pump.
GX
_12_018
DirectReadingGauge
System 3Reservoir
GX
_12_019
3A and3B Pumps
FilterManifold
Bombardier Global Express - Hydraulics
Page 17
RAM AIR TURBINE (RAT)
In case of an emergency (example: dual-engine failure), the RAT is deployed and will
power an independent hydraulic pump for system 3. Therefore, system 3 has three
hydraulic pumps available to power the system.
The RAT hydraulic pump is mounted at the rear of the RAT. It uses system 3 hydraulic
fluid for emergency operations. An additional feature is that the RAT pump shares a
common pressure switch with ACMP 3B. The RAT operation is described in Chapter
6, ELECTRICAL of this manual.
HEAT EXCHANGER
The heat exchanger is positioned in the left fuel feed tank. System 3 heat exchanger
has the same function as systems 1 and 2.
FILTER MANIFOLD
The filter manifold for system 3 is located in the lower belly fairing of the aircraft, and
contains all the features of system 1 and 2.
Fluid quantity and temperature transducers are located on the reservoir and their
indications are displayed on the HYDRAULIC synoptic page.
Two pressure switches and a transducer are part of the pressure manifold and are used
to provide EICAS displays for pump failures and loss of system pressure.
GX
_12_020
System 3Heat Exchanger
Bombardier Global Express - Hydraulics
Page 18
GROUND SERVICE PANEL
The ground service panel for system 3 is located on the left side of the fuselage aft of
the wing trailing edge.
RAT AND SYSTEM 3 ACCUMULATORS
A RAT accumulator is used to maintain pressure to the reservoir when 3A and 3B
ACMPs are inoperative in flight. This will provide a continuous pressure for up to 44
seconds from the reservoir suction line to the pump, enabling the RAT pump to come
on line quickly. There is a direct reading gauge to check the precharge condition of the
accumulator. Normal precharge pressure equals 1000 psi.
The brake control system uses an accumulator from hydraulic system 3 for brake
operations. There is a direct reading gauge to check the condition of the accumulator.
Normal precharge pressure of the brake accumulator equals 500 psi. Refer to Chapter
14, LANDING GEAR for more information on the brake control system.
GX
_12_021
RATAccumulator
System 3Brake
Accumulator
Direct ReadingGauge
Bombardier Global Express - Hydraulics
Page 19
HYDRAULIC SYSTEM 3 SCHEMATIC
GX
_12_022
Heat Exchanger
ACPUMP
3A
RESERVOIR
CaseDrain Fluid
S
OW
S
PDIGITAL
READOUTEICAS
TOAIRPLANESYSTEMS
S
P
ITEM OPERATES
Pressure switchesPump FailureDisplay to EICAS
PSI display to EICASPressure transducer
PRESSURE MANIFOLD
OW
Check valve indicatesdirection of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
LEGEND
ACPUMP
3B
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTERELECTRICAL LOGIC
AC BUS 4 AC BUS 1
HYDRAULIC3A 3B
OFF
ON
ON
OFF
AUTOAO
3000PSI
Bombardier Global Express - Hydraulics
Page 20
RAT DEPLOYMENT HYDRAULIC SCHEMATIC
GX
_12_023
HeatExchanger RESERVOIR
S
OW
S
P
DIGITALREADOUT
EICAS
TOAIRPLANESYSTEMS
S
P
ITEM OPERATES
Pressure switchesPump FailureDisplay to EICAS
PSI display to EICASPressure transducer
PRESSURE MANIFOLD
OW
Check valve indicatesdirection of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
LEGEND
AIRPLANE CONFIGURATION
AIR/GROUND SENSING
AC POWER CENTERELECTRICAL LOGIC
AC BUS 3 AC BUS 4AC BUS 1 AC BUS 2
RATPUMP
RAT
ACCUMULATOR
ACPUMP
3A
ACPUMP
3B
CaseDrain Fluid
3000PSI
Bombardier Global Express - Hydraulics
Page 21
HYDRAULIC CONTROL PANEL
The HYDRAULIC control panel is located on the overhead panel in the flight
compartment and contains the ACMP switches.
MANUAL MODE
Manual mode is accomplished by placing the respective ACMP control switch into
either the OFF or ON position. The pumps will run when selected to ON and their
respective bus is powered. In the OFF position each pump is inoperative for all
operating conditions.
AUTO MODE (PUMPS 1B, 2B AND 3B)
When the pump switch is set to AUTO, the respective pump automatically starts under
one of the following conditions:
• When the correct electrical logic is determined by the Alternating Current Power
Center (ACPC), either slats or flaps are not at the IN/0° position and at least one
Variable Frequency Generator (VFG) operating
• When the primary pump (EDP 1A, 2A or ACMP 3A) falls below normal system
pressure (≤ 1800 psi) in flight.
HYDRAULIC1B 3A 3B 2B
OFF
AUTO
OFF
ON ON ON
ON
OFF
AUTO
OFF
AUTOAAOA
GX
_12_024
AC Motor Pump 1B and 2B
ON
OFFAUTO
Controls the operation of each pump under the following conditions:• – When the correct electrical logic is set, the applicable pumpwill operate at normal operating pressure.• – Pump is inoperative• – Pump is in automatic/standby mode. Each pump willenergize when its system primary pump fails in flight, or when thecorrect logic is set with slats/flaps not at 0-degree position.
AC Motor Pump 3A
ON
OFF
Controls the operation of the pumpin the following conditions:• – When the correct electricallogic is set, the pump will operate atnormal operating pressure.• – Pump is inoperative.
AC Motor Pump 3B
ON
OFFAUTO
Controls the operation of the pump in thefollowing conditions:• – When the correct electrical logic is set,the pump will operate at normal operatingpressure.• – Pump is inoperative.• – Pump is in automatic/standby mode.The pump will energize if the ACMP 3A pumpfails in flight, or when the correct logic is setwith slats/flaps not at 0-degree position.
Bombardier Global Express - Hydraulics
Page 22
GROUND OPERATION INHIBITS
When the APU is the airplane single source of electrical power, only one ACMP is
allowed to run at a time to prevent overloading the APU generator. The priority for
running the ACMPs are as follows:
• No. 1 priority - ACMP 3A
• No. 2 priority - ACMP 3B
• No. 3 priority - ACMP 2B
• No. 4 priority - ACMP 1B
If a lower priority ACMP is running and a higher priority ACMP is activated, the
lowest priority ACMP will shut off and the higher priority ACMP will turn on
automatically.
The B pump automatic start mode is inhibited when no engines are running to enhance
system safety during normal maintenance operations.
The B pumps will not come on automatically (AUTO mode selected) in support of a
primary pump failure on the ground.
All B pumps will be commanded on automatically (AUTO mode selected) when flaps/
slats are selected out of 0° and slats motion has stopped, and a minimum of two VFGs
are operating (i.e. all electrical buses powered).
FLIGHT OPERATION
The normal pump switch configuration in flight is AUTO mode of operation for
pumps 1B, 2B and 3B and ON selection for pump 3A.
The B pumps will come on automatically (AUTO mode selected) in support of the
applicable primary pump failure in flight. When an ACMP is commanded on due to a
low pressure condition of the primary pump, that ACMP will remain on for a
minimum of 5 minutes (including touchdown) unless ON or OFF is selected. This is
required to prevent ACMP overheating due to continuous restarts if the low pressure
alternates above and below 1800 psi.
During single VFG operation ACMPs 1B and 2B are load shed since their respective
buses are disconnected from the remaining good generator.
RAM AIR TURBINE (RAT)
When the RAT is deployed and on-speed, it will power the AC ESS bus and the
independent RAT hydraulic pump, to ensure that system 3 components are powered at
all times (see hydraulic synoptic page in this chapter).
Bombardier Global Express - Hydraulics
Page 23
ACMP POWER AND DISTRIBUTION
Electrical power and distribution using the ACMPs are described as follows:
ACMP’S 1B AND 2B
Hydraulic systems 1 and 2 are each powered by one EDP used as the primary system
pump. Each primary pump is backed up by a single ACMP (one per system) during
high flow demand flight phases or failure of the primary pump in flight.
The ACMPs are also used for system ground maintenance operation with the control
switch in the ON position. Each ACMP is powered by one of the electrical AC buses
supplied by both an onside generator(s) and cross-side generator(s) (ACMP 1B is
connected to AC bus 3. AC bus 3 is normally powered by its own generator (No. 3)
but is backed up by, in priority, generators 2, 1 and APU). This will ensure operation
of both hydraulic systems 1 and 2 in the case of a single engine failure.
When only one generator is operating, AC buses 2 and 3 are shed. Since their
respective AC buses are disconnected during single generator operation, ACMPs 1B
and 2B are automatically load shed.
ACMP’S 3A AND 3B
Hydraulic system 3 is powered by two ACMPs, 3A as the primary system pump and
3B as the backup pump. Each pump is powered by a different AC bus (ACMP 3A is
connected to AC bus 4 and ACMP 3B is connected to AC bus 1). In the event of one,
two or three generator failures, both 3A and 3B ACMPs will receive power from the
remaining generator. AC bus 1 and AC bus 4 are both powered during single generator
operation.
Bombardier Global Express - Hydraulics
Page 24
ACMP ELECTRICAL POWER SCHEMATIC
EXTERNAL AND APU POWER-ACMP OPERATION
External AC power has the capability to power all ACMPs for ground operation when
the hydraulic control switch is selected to the ON position.
During ground operation with either the APU or external ground power as the source
of electrical power, the AUTO mode of operation is not available. On ground with
APU as the single source of electrical power, only one pump at a time is allowed to run
with 3A, 3B, 2B and 1B in priority.
In flight with the APU as the single source of electrical power, two pumps only (3A
and 3B) are allowed to run to prevent overloading of the generator.
RESERVOIR QUANTITY LIMITS
The table on the following page describes the range of values between the upper and
lower fluid quantity limits for each system. The green brackets are variable in size, and
in combination with the reservoir filling and digital readout represent the level of
quantity in the reservoir for all airplane configurations.
The quantity indication (reservoir filling and digital readout) for systems 1 and 2 will
turn amber if the displayed reservoir quantity for that system is at or below the lower
limit.
GX
_12_025
Legend
Electrical Flow
Generator
ACMP
Electrical AC BUSAC BUS
ACMP Priority 3A, 3B, 2B, 1B
PUMP
GEN
AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4
LEFT ENGINE RIGHT ENGINE
ACMP3B
ACMP2B
ACMP1B
ACMP3A
GEN2
GEN3
GEN4
GEN1
Bombardier Global Express - Hydraulics
Page 25
The quantity indication for system 3 will turn amber when the displayed quantity is at
or below the lower limit or at or above the upper limit when the quantity reaches 70%.
Not withstanding the limits stated above, the following table lists the normal quantity
you should see on your walkaround or on a synoptic page.G
X_12_026
SYSTEM No. 1 SYSTEM No. 3 SYSTEM No. 2
LOWERLIMIT
UPPERLIMIT
Hydraulic QuantityLower Limit = 34%
Hydraulic QuantityLower Limit = 20%
Hydraulic QuantityLower Limit = 32%
Hydraulic QuantityUpper Limit = 70%
100% 100%
Hydraulic QuantityLower Limit (L & R gear
uplocked) = 28%
IN FLIGHT:
IN FLIGHT:
IN FLIGHT:IN FLIGHT:
Hydraulic QuantityLower Limit = 16%
Hydraulic QuantityLower Limit = 12%
Hydraulic QuantityUpper Limit = 100%
ON GROUND: ON GROUND:
ON GROUND:
ON GROUND:
22 °C
61%
38 °C
63%
20 °C
62%
Bombardier Global Express - Hydraulics
Page 26
Hydraulic System No. 1
(Sys on, spoilers down, TRs stow)
Max qty drop – pressurized = 4%
FLUID TEMP (°C) RESERVOIR LEVEL (%)
-16 to 4 38 to 47
5 to 26 47 to 56
27 to 49 56 to 66
50 to 71 66 to 74
72 to 93 74 to 83
Hydraulic System No. 2 – Quantity Check
(Sys on, spoilers down, TRs stow, brakes off)
Max qty drop – pressurized = 12%
FLUID TEMP (°C) RESERVOIR LEVEL (%)
-16 to 4 40 to 50
5 to 26 51 to 58
27 to 49 58 to 65
50 to 71 66 to 73
72 to 93 74 to 80
Hydraulic System No. 3 – Quantity Check
(Sys on, spoilers down, LDG doors closed,
brakes off)
Max qty drop – pressurized = 18%
FLUID TEMP (°C) RESERVOIR LEVEL (%)
-16 to 4 30 to 36
5 to 26 37 to 43
27 to 49 44 to 50
50 to 71 51 to 58
72 to 93 58 to 65
Bombardier Global Express - Hydraulics
Page 27
EICAS MESSAGES
789
1 . 65HYD 1 LO PRESSHYD 2 LO PRESSHYD 3 LO PRESSHYD 1 HI TEMPHYD 2 HI TEMPHYD 3 HI TEMPHYD RAT PUMP FAILHYD 1 LO QTY
HYD 3 OVERFILLEDL HYD SOV FAILR HYD SOV FAIL
HYD 2 LO QTYHYD 3 LO QTY
GX
_12_027
HYD 3 OVERFILLEDIndicates that system 3quantity is more than70% with the systempressurized on theground.
HYD 1 (2) (3) LO QTYIndicates that the corres-ponding system is at thelower quantity limit.
HYD 1 (2) (3) HI TEMPIndicates that thecorresponding systemfluid temperature is
96°C.>
HYD RAT PUMP FAILIndicates that the RATpump has a low outputpressure ( 1800 psi).<
HYD 1 (2) (3)LO PRESSIndicates that the corres-ponding system pumps(both) in each systemhave a low-pressureoutput ( 1800 psi).<
L (R) HYD SOV FAILIndicates that the leftand/or right hydraulicshutoff did not go to itscommanded position(open or closed) followingthe pull of a fire handle.
Bombardier Global Express - Hydraulics
Page 28
EICAS MESSAGES (Cont)
789
1 . 65HYD EDP 1A FAILHYD EDP 2A FAILHYD PUMP 1B FAILHYD PUMP 2B FAILHYD PUMP 3A FAILHYD PUMP 3B FAILHYD PUMP 1B OFFHYD PUMP 2B OFFHYD PUMP 3A OFFHYD PUMP 3B OFFHYD PUMP 1B ONHYD PUMP 2B ONHYD PUMP 3B ON
GX
_12_028
HYD PUMP (1B) (2B)(3B) ONIndicates that thecorresponding pump isselected on.
HYD PUMP 1B (2B) (3A)(3B) OFFIndicates that the corres-ponding pump is selectedoff.
HYD PUMP 1B (2B)(3A) (3B) FAILIndicates that thecorresponding pumphas a low-pressureoutput ( 1800 psi) whencommanded on.
<
HYD PUMP 1A (2A) FAILIndicates that thecorresponding enginedriven pump (1A or 2A)has a low-pressureoutput ( 1800 psi) whenthe engine is running.
<
Bombardier Global Express - Hydraulics
Page 29
EMS CIRCUIT PROTECTION
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
CB - HYD SYSTEM
CB - HYD SYSTEM
1/2
2/2
HYD 1 PRESS XDCR
HYD 2 PRESS XDCR
HYD 3 PRESS XDCR
HYD PUMP 1B
HYD PUMP 2B
HYD PUMP 3A
HYD PUMP 3B
L HYD SOV
R HYD SOV
DC 1
DC 2
BATT
AC 3
AC 2
AC 4
AC 1
DC EMER DCPC
DC EMER DCPC
IN
IN
IN
IN
IN
IN
IN
IN
IN
GX
_12_029
CIRCUIT BREAKER - STATUS 2/2
GEAR
HYD
ICE
IND/RECORD
LIGHTS
NAV
OIL
OXYGEN
THRUST REV
Bombardier Global Express - Hydraulics
Page 30