ATA 29 – HYDRAULIC SYSTEM CODDE 1 PAGE 1 / 2 TABLE OF ...

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ATA 29 – HYDRAULIC SYSTEMTABLE OF CONTENTS

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DASSAULT AVIATION Proprietary Data

02-29 ATA 29 - HYDRAULIC SYSTEM

02-29-00 TABLE OF CONTENTS

02-29-05 GENERAL

IntroductionSourcesEquipment location

02-29-10 DESCRIPTION

Sub-systemsAccumulatorsDistribution

02-29-15 CONTROL AND INDICATION

ControlIndication

02-29-20 SYSTEM PROTECTION

Circuit breakersRelief valves

02-29-25 NORMAL OPERATION

IntroductionOn ground operationIn-flight operation

02-29-30 ABNORMAL OPERATION

IntroductionHYD 2 fluid leakEngine-driven pump 1 and 3 failureCAS messages

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ATA 29 – HYDRAULIC SYSTEMTABLE OF CONTENTS

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INTENTIONALLY LEFT BLANK

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ATA 29 – HYDRAULIC SYSTEMGENERAL

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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) operatingsimultaneously 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 toAUTO) no crew action is required for the rest of the flight if no failure occurs.

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FIGURE 02-29-05-00 FLIGHT DECK OVERVIEW

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SOURCES

Each hydraulic system has its own hydraulic fluid reservoir located in the mechanic servicingcompartment.

Each reservoir is pressurized by its corresponding hydraulic system. The reservoirs arepressurized to avoid pump cavitation.

HYD 1 RESERVOIR HYD 2 RESERVOIR

2.38 USG

(9 l)

1.58 USG

(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 pumpfailure (fail-safe system).

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EQUIPMENT LOCATION

Ground servicingconnectors

Circuit breakerpanel

Overheadpanel

Stand-by pumpand selector valve

Hydraulic pumps

Parking brakeaccumulator

Instrument panel

Hydraulicreservoirs

Accumulators

FIGURE 02-29-05-01 EQUIPMENT LOCATION

The hydraulic system components are mainly installed in the hydraulic racks in the mechanicservicing compartment.

Except for very few items, the HYD 1 system components are located on the left side of theairplane, the HYD 2 system and stand-by components on the right side.

External hydraulic cart connections are provided for ground checks and maintenance tests ofeach system.

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ATA 29 – HYDRAULIC SYSTEM DESCRIPTION

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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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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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DISTRIBUTION

FIGURE 02-29-10-01 HYDRAULIC SYSTEM DIAGRAM

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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

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CONTROL

FIGURE 02-29-15-00 STAND-BY PUMP OVERHEAD PANEL CONTROL

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SYNTHETIC TABLE

TO ACTIVATE CONTROL FUNCTION

TO DEACTIVATE SYNOPTIC

In AUTO mode, not cycling

In AUTO mode, cycling

Push on (AUTO mode)

In AUTO mode running for more than 60 sec

OFF

On ground test, cycling on

On ground test, cycling off

pushbutton

status light

- ST-BY pump can be set to AUTO mode or OFF

- It must be in AUTO mode in flight (normal condition)

- In the AUTO mode, it automatically operates in case of PUMP 2 failure

- 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)

Push OFF

Invalid data

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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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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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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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Park brake, Thrust Reverser (T/R) and corresponding accumulators

FIGURE 02-29-15-06 PARK BRAKE AND THRUST REVERSER INDICATIONS

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STATUS synoptic

HYD 1 and HYD 2 quantitiesand pressure indications

FIGURE 02-29-15-07 STAT SYNOPTIC

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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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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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ATA 29 – HYDRAULIC SYSTEMSYSTEM PROTECTION

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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 SYSTEMSYSTEM PROTECTION

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ATA 29 – HYDRAULIC SYSTEMNORMAL OPERATION

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INTRODUCTION

In the following, typical on ground and in-flight situations have been selected to help the crewto 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 3are inactive as engines are not running

HYD pumps 1, 2 and 3 symbols are gray andHYD 1 system is inoperative.

ST-BY pump overhead panel pushbutton inAUTO mode

ST-BY pump cycling as HYD 2 is inactive

HYD 2 equipment symbol are green

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ATA 29 – HYDRAULIC SYSTEMNORMAL OPERATION

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IN-FLIGHT OPERATION

AIRPLANE FLYING IN NORMAL OPERATION (3 ENGINES RUNNING)


NORMAL STATUS RESULT

Hydraulic engine-driven pumps 1, 2 and 3active

HYD 1 and HYD 2 systems operating:

- HYD pumps symbol is green,

- HYD 1 and HYD 2 system equipmentsymbols are green

ST-BY pump overhead panel pushbutton onAUTO position

AUTO indication above ST-BY pumpsymbol

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ATA 29 – HYDRAULIC SYSTEMABNORMAL OPERATION

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INTRODUCTION

In the following, abnormal situations have been illustrated to help the crew to understand thesymbols provided in the various panels and displays.

HYD 2 FLUID LEAK

ABNORMAL STATUS

FIGURE 02-29-30-00 ST-BY PUMP OVERHEAD PANEL CONTROL


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CONTEXT RESULT

HYD 2 fluid leak

- HYD 2 fluid quantity symbol is amber

- HYD 2 hydraulic pressure symbol in amber

- HYD 2 corresponding symbol in amber

+ HYD 2 PUMP 2 CAS message

+ % MASTER

CAUTION light on

ST-BY pump on AUTO,running for more than 60 sec

- ST-BY pump symbol is amber

- ST-BY PUMP PERMANENTCAS message

AFTER PROCEDURE COMPLETE

FIGURE 02-29-30-02 ST-BY PUMP OVERHEAD PANEL CONTROL

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ACTION RESULT

ST-BY pump overhead panel pushbutton setto OFF

ST-BY pump symbol is graywith OFF indication in amber

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ENGINE-DRIVEN PUMP 1 AND 3 FAILURE


CONTEXT RESULT

Engine-driven pumps 1 and 3 failure

- PUMP 1,PUMP 3, HYD 1 pressure andequipment 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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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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