F900EX EASY
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
TABLE OF CONTENTS
DGT91832
02-29 ATA 29 - HYDRAULIC SYSTEM
02-29-00 TABLE OF CONTENTS
02-29-05 GENERAL
Introduction
Sources
Equipment location
02-29-10 DESCRIPTION
Sub-systems
Accumulators
Distribution
02-29-15 CONTROL AND INDICATION
Control
Indication
02-29-20 SYSTEM PROTECTION
Circuit breakers
Relief valves
02-29-25 NORMAL OPERATION
Introduction
On ground operation
In-flight operation
02-29-30 ABNORMAL OPERATION
Introduction
HYD 2 fluid leak
Engine-driven pump 1 and 3 failure
CAS messages
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ISSUE 4
02-29-00
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ISSUE 4
ATA 29 – HYDRAULIC SYSTEM
TABLE OF CONTENTS
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ATA 29 – HYDRAULIC SYSTEM
GENERAL
DGT91832
02-29-05
PAGE 1 / 4
ISSUE 4
INTRODUCTION
The hydraulic power system provides pressure for actuation of several airplane components.
It is composed of two fully independent systems (HYD 1 and HYD 2 systems) operating
simultaneously and powered by:
-
three engine-driven pumps with a regulated pressure output of 3,000 psi (+/- 200 psi),
-
one electrical stand-by pump.
Hydraulic system is a “set and forget” type. After initialization for flight (ST-BY PUMP set to
AUTO) no crew action is required for the rest of the flight if no failure occurs.
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ISSUE 4
ATA 29 – HYDRAULIC SYSTEM
GENERAL
FIGURE 02-29-05-00 FLIGHT DECK OVERVIEW
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ATA 29 – HYDRAULIC SYSTEM
GENERAL
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02-29-05
PAGE 3 / 4
ISSUE 4
SOURCES
Each hydraulic system has its own hydraulic fluid reservoir located in the mechanic servicing
compartment.
Each reservoir is pressurized by its corresponding hydraulic system. The reservoirs are
pressurized to avoid pump cavitation.
HYD 1 RESERVOIR
HYD 2 RESERVOIR
2.38 USG
1.58 USG
(9 l)
(6 l)
Main hydraulic power is provided by three engine-driven mechanical pumps.
HYD 1 system is supplied by two pumps:
-
engine 1 hydraulic pump,
-
engine 3 hydraulic pump.
HYD 2 system is supplied by two pumps:
-
engine 2 hydraulic pump,
-
electrical stand-by pump, automatically activated in case of HYD 2 engine-driven pump
failure (fail-safe system).
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ATA 29 – HYDRAULIC SYSTEM
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GENERAL
ISSUE 4
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CODDE 1
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EQUIPMENT LOCATION
Hydraulic pumps
Parking brake
accumulator
Circuit breaker
panel
Ground servicing
connectors
Overhead
panel
Hydraulic
reservoirs
Accumulators
Stand-by pump
and selector valve
Instrument panel
FIGURE 02-29-05-01 EQUIPMENT LOCATION
The hydraulic system components are mainly installed in the hydraulic racks in the mechanic
servicing compartment.
Except for very few items, the HYD 1 system components are located on the left side of the
airplane, the HYD 2 system and stand-by components on the right side.
External hydraulic cart connections are provided for ground checks and maintenance tests of
each system.
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ATA 29 – HYDRAULIC SYSTEM
DESCRIPTION
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02-29-10
PAGE 1 / 4
ISSUE 4
SUB-SYSTEMS
HYDRAULIC ENGINE DRIVEN PUMPS
The three self-regulating, piston-type pumps are driven by the accessory gearbox of the
corresponding engine.
They automatically regulate the output pressure at 3,000 psi (± 200 psi).
The pumps are not controlled from the cockpit.
The pumps are lubricated by the hydraulic fluid. A shear section in the pump drive shaft
protects the engine gearbox in case of pump seizure.
STAND-BY ELECTRICAL PUMP
In case of HYD 2 pump failure, a stand-by electrical pump (A1 bus) allows operation of
components powered by the HYD 2 system.
In AUTO mode, the stand-by pump starts automatically as soon as a pressure drop
(pressure below 1,500 psi) is detected in the HYD 2 system: the stand-by pump cycles
continuously between 1,500 and 2,150 psi and stops operating as long as pressure stays
above 2,150 psi.
The stand-by electrical pump may also be used, on ground only, to pressurize the HYD 1
system for maintenance checks. The mechanical selector that switches the pump between
HYD 1 and HYD 2 systems is located in the mechanic servicing compartment (right side).
CAUTION
The stand-by pump selector must be set to IN FLIGHT position prior to flight.
NOTE
The stand-by pump must be switched off in case of HYD 2 system leakage.
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ATA 29 – HYDRAULIC SYSTEM
DESCRIPTION
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ACCUMULATORS
Each system includes a hydraulic accumulator to dampen pressure surges in the system and
provide instantaneously available reserve power. Each accumulator is fitted with a refiller port
and a nitrogen pressure gage.
The HYD 2 system includes two additional accumulators to provide reserve power for the
parking brake system and the thrust reverser operation in case of HYD 2 system failure.
NOTE
After engine shutdown or hydraulic failure, hydraulic pressure in each system accumulator
drops to zero. Check valves maintain the pressure in the parking brake and thrust reverser
accumulators. Pressure holding valves keep the reservoirs pressurized.
FIGURE 02-29-10-00 ACCUMULATORS DIAGRAM AND TYPICAL HYDRAULIC ACCUMULATORS
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ATA 29 – HYDRAULIC SYSTEM
DESCRIPTION
DISTRIBUTION
FIGURE 02-29-10-01 HYDRAULIC SYSTEM DIAGRAM
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02-29-10
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ISSUE 4
ATA 29 – HYDRAULIC SYSTEM
DESCRIPTION
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HYD 1 SYSTEM
HYD 1 system is pressurized by two self-regulating (constant pressure) hydraulic pumps
driven by the No 1 and No 3 engine gearboxes (PUMP 1 and PUMP 3).
Both pumps draw operating fluid from the No 1 hydraulic reservoir and feed the system at a
rated pressure of 3,000 psi (± 200 psi).
The output pressure of the pumps hydraulically charges the HYD 1 system accumulator and
supplies pressure to:
- pitch servoactuator (one barrel),
- rudder servoactuator (one barrel),
- aileron servoactuator (one barrel),
- pitch feel unit,
- normal slats (inboard and outboard),
- landing gears and corresponding doors,
- No 1 brake system,
- nose wheel steering.
HYD 2 SYSTEM
HYD 2 system is pressurized by one self-regulating (constant pressure) hydraulic pump
(same characteristics as No 1 and No 3 pumps) driven by the No 2 engine gearbox (PUMP
2).
PUMP 2 draws operating fluid from the No 2 hydraulic reservoir and feeds the system at a
rated pressure of 3,000 psi (± 200 psi).
HYD 2 system can be pressurized by an automatic electrical pump (ST-BY PUMP)
connected to A1 bus.
The output pressure of the pump hydraulically charges the No 2 system accumulator and
supplies pressure to :
- pitch servoactuator (one barrel),
- rudder servoactuator (one barrel),
- aileron servoactuator (one barrel),
- flaps,
- airbrakes,
- emergency slats (outboard only),
- No 2 brake system,
- parking brake (with one monitored pressure accumulator),
- thrust reverser (with one pressure accumulator, not monitored).
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ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
02-29-15
PAGE 1 / 10
CONTROL
FIGURE 02-29-15-00 STAND-BY PUMP OVERHEAD PANEL CONTROL
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02-29-15
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ATA 29 – HYDRAULIC SYSTEM
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CODDE 1
CONTROL AND INDICATION
ISSUE 4
DGT91832
SYNTHETIC TABLE
CONTROL
FUNCTION
TO ACTIVATE
SYNOPTIC
TO DEACTIVATE
In AUTO
mode,
not cycling
-
-
It must be in AUTO
mode in flight
(normal condition)
-
In the AUTO mode,
it automatically
operates in case of
PUMP 2 failure
pushbutton
-
status light
Push on
(AUTO
ST-BY pump can be
mode)
set to AUTO mode
or OFF
ST-BY pump starts
operation when
HYD 2 pressure
drops below 1,500
psi and stops when
pressure reaches
2,150 psi (green
range on the psi
scale is adjusted to
normal operating
range)
In AUTO
mode,
cycling
In AUTO
mode
running for
more than
60 sec
OFF
On ground
test,
cycling on
Push OFF
On ground
test,
cycling off
Invalid data
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ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
02-29-15
PAGE 3 / 10
ISSUE 4
INDICATION
Hydraulic indications are displayed on the MDU:
-
in the HYD synoptic,
-
in the STAT synoptic (hydraulic quantity and pressure indications).
Direct-reading indicators are also available for the reservoirs fluid levels and for the
accumulators pressure mainly in the mechanic servicing compartment.
HYD SYNOPTIC
FIGURE 02-29-15-01 HYD SYNOPTIC
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ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
ISSUE 4
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Examples of hydraulic level indications
QTY above the minimum
required (1/4)
QTY below the minimum
required (1/4)
Invalid data
FIGURE 02-29-15-02 HYDRAULIC LEVEL INDICATORS
Examples of hydraulic pressure indications
FIGURE 02-29-15-03 HYDRAULIC FLUID PRESSURES
NOTE
When the stand-by pump is active, the green range of the pressure indication scale shifts
from 2,150 to 1,500 psi.
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02-29-15
ATA 29 – HYDRAULIC SYSTEM
PAGE 5 / 10
CONTROL AND INDICATION
ISSUE 4
Examples of hydraulic pump status
Running
Not running
Failed
Invalid data
FIGURE 02-29-15-04 HYDRAULIC PUMP STATUS
Examples of 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.
NOTE
As flight control actuators are connected to HYD 1 and HYD 2 circuits, the corresponding
symbols are (see figure below):
- 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 02-29-15-05 SYMBOLS OF FLIGHT CONTROLS
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ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
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Park brake, Thrust Reverser (T/R) and corresponding accumulators
FIGURE 02-29-15-06 PARK BRAKE AND THRUST REVERSER INDICATIONS
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ATA 29 – HYDRAULIC SYSTEM
CODDE 1
CONTROL AND INDICATION
DGT91832
STATUS synoptic
HYD 1 and HYD 2 quantities
and pressure indications
FIGURE 02-29-15-07 STAT SYNOPTIC
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ISSUE 4
ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
F900EX EASY
CODDE 1
DGT91832
DIRECT READING INDICATORS
Fluid level indicator
Each reservoir is equipped with a built-in fluid level indicator with two scales labeled
PRESSURIZED and UNPRESSURIZED.
Each scale includes two red ranges for low and excessive fluid quantity and one green
range for optimum level at temperature between – 40°C and + 90°C when the system
has been unpressurized for several hours. They are located in the mechanic servicing
compartment.
FIGURE 02-29-15-08 HYDRAULIC FLUID LEVEL DIRECT READING INDICATOR
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ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
02-29-15
PAGE 9 / 10
ISSUE 4
Accumulator nitrogen pressure gages
Visual check of accumulator nitrogen pressure gages is not possible from the outside. It
has to be done through the mechanic servicing compartment door, except for the gage of
the parking brake accumulator, which is located at the root of the RH wing.
FIGURE 02-29-15-09 PARKING BRAKE ACCUMULATOR NITROGEN PRESSURE GAGE
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ISSUE 4
ATA 29 – HYDRAULIC SYSTEM
CONTROL AND INDICATION
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F900EX EASY
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
SYSTEM PROTECTION
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02-29-20
PAGE 1 / 2
ISSUE 4
CIRCUIT BREAKERS
FIGURE 02-29-20-00 HYDRAULIC SYSTEM CIRCUIT BREAKERS
RELIEF VALVES
Reservoir overpressure is prevented by a relief valve.
Entrapped air is automatically purged through a vent valve. When engines are shut down,
reservoirs pressurization is maintained by an accumulator in the pressure valve.
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ATA 29 – HYDRAULIC SYSTEM
SYSTEM PROTECTION
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02-29-25
ATA 29 – HYDRAULIC SYSTEM
PAGE 1 / 2
NORMAL OPERATION
DGT91832
ISSUE 4
INTRODUCTION
In the following, typical on ground and in-flight situations have been selected to help the crew
to understand the symbols provided in the various panels and displays.
ON GROUND OPERATION
AIRPLANE WITH AUXILIARY POWER UNIT (APU) OPERATING
FIGURE 02-29-25-00 HYD SYNOPTIC, APU OPERATING AND STAND-BY PUMP CYCLING
NORMAL STATUS
RESULT
Hydraulic engine-driven pumps 1, 2 and 3
are inactive as engines are not running
HYD pumps 1, 2 and 3 symbols are gray and
HYD 1 system is inoperative.
ST-BY pump overhead panel pushbutton in
AUTO mode
ST-BY pump cycling as HYD 2 is inactive
HYD 2 equipment symbol are green
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ATA 29 – HYDRAULIC SYSTEM
PAGE 2 / 2
CODDE 1
NORMAL OPERATION
ISSUE 4
DGT91832
IN-FLIGHT OPERATION
AIRPLANE FLYING IN NORMAL OPERATION (3 ENGINES RUNNING)
FIGURE 02-29-25-01 HYD SYNOPTIC
NORMAL STATUS
RESULT
HYD 1 and HYD 2 systems operating:
Hydraulic engine-driven pumps 1, 2 and 3
active
ST-BY pump overhead panel pushbutton on
AUTO position
-
HYD pumps symbol is green,
-
HYD 1 and HYD 2 system equipment
symbols are green
AUTO indication above ST-BY pump
symbol
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ATA 29 – HYDRAULIC SYSTEM
CODDE 1
ABNORMAL OPERATION
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02-29-30
PAGE 1 / 6
ISSUE 4
INTRODUCTION
In the following, abnormal situations have been illustrated to help the crew to understand the
symbols provided in the various panels and displays.
HYD 2 FLUID LEAK
ABNORMAL STATUS
FIGURE 02-29-30-00 ST-BY PUMP OVERHEAD PANEL CONTROL
FIGURE 02-29-30-01 HYD SYNOPTIC
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ATA 29 – HYDRAULIC SYSTEM
CODDE 1
ABNORMAL OPERATION
ISSUE 4
CONTEXT
RESULT
-
HYD 2 fluid quantity symbol is amber
-
HYD 2 hydraulic pressure symbol in amber
-
HYD 2 corresponding symbol in amber
+ HYD 2 PUMP 2
HYD 2 fluid leak
+
-
ST-BY pump on AUTO,
running for more than 60 sec
DGT91832
-
%
MASTER
CAUTION
CAS message
light on
ST-BY pump symbol is amber
ST-BY PUMP PERMANENT
CAS message
AFTER PROCEDURE COMPLETE
FIGURE 02-29-30-02 ST-BY PUMP OVERHEAD PANEL CONTROL
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ATA 29 – HYDRAULIC SYSTEM
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ABNORMAL OPERATION
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ISSUE 4
FIGURE 02-29-30-03 HYD SYNOPTIC
ACTION
RESULT
ST-BY pump overhead panel pushbutton set
to OFF
ST-BY pump symbol is gray
with OFF indication in amber
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F900EX EASY
ATA 29 – HYDRAULIC SYSTEM
CODDE 1
ABNORMAL OPERATION
ISSUE 4
DGT91832
ENGINE-DRIVEN PUMP 1 AND 3 FAILURE
FIGURE 02-29-30-04 HYD SYNOPTIC
CONTEXT
RESULT
-
Engine-driven pumps 1 and 3 failure
PUMP 1,PUMP 3, HYD 1 pressure and
equipment symbols in amber.
+ HYDR #1 PUMP 1+3
CAS message
+
%
MASTER
CAUTION
light on
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ATA 29 – HYDRAULIC SYSTEM
ABNORMAL OPERATION
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02-29-30
PAGE 5 / 6
ISSUE 4
CAS MESSAGES
CAS MESSAGE
DEFINITION
BOTH HYDR SYSTEM
Too low hydraulic pressure at pump outputs with
engines running
HYDRAULIC LOW LEVEL ..
Hydraulic level (1/2) less than ¼
HYDR #1 PUMP ..
Hydraulic pump (1/3) failure (HYD 1 system):
pressure below 1,500 psi (97 bar)
HYDR #2 PUMP 2
Hydraulic pump 2 failure (HYD 2 system): pressure
below 1,500 psi (97 bar)
ST-BY PUMP ON C#1
Stand-by pump connected on HYD 1 system for
maintenance
ST-BY PUMP PERMANENT
Stand-by pump cycling for more than 60 sec
HYDR .. FAIL
On ground, indication of hydraulic (1/2/3) pump
pressure switch failure
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ATA 29 – HYDRAULIC SYSTEM
ABNORMAL OPERATION
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