Flight 9252: Some additional questions on the Cargo Door hydraulic system

With all I have so far of the Germanwings crash of flight 9252 on March 24 2015, I am convinced the official story is not true. There is no reason to think Andreas Lubitz committed suicide taking 149 lives with him. Instead pilot Patrick Sonderheimer committed the act and framed Lubitz. Read a summary of my analysis here: link.

19Below a more technical analysis of the cargo door operations. I am by no means an expert, so analysing this case is more difficult than my own case. Since these terrorist events are too important to blindly trust the formal story, I feel obliged to try nonetheless. Any expert in the field is encouraged to bring in knowledge. Below some questions, based on what I found so far.

The cargo doors can only be opened from outside, when the plane has landed and is standing still. For safety, whenever the cargo doors are opened, operations in the cockpit to steer the plane are limited. We do not want a pilot to manoeuvre around, when someone is loading or unloading the cargo at the airport. On the other hand, it is not possible to open the cargo door mid flight. However, I think that is exactly what they did. Is there anyone who can help me out here? What is the impact of opening the cargo door?

1998.07-Aircraft Fig 1 hydraulic systemsMany parts of the A320 airplane are operated using hydraulic mechanisms [picture right is an example]. There are three hydraulic flow circuits in the A320, of which the fluid flow is seperated: green, blue, and yellow. These 3 hydraulic systems provides hydraulic pressure to operate the: Flight controls; Slats and flaps; Landing A320 hydraulic system steering plane a380steuerflaechengear/Brakes/Nosewheel steering; Cargo doors; and the Production of electrical power with an emergency electrical generator. The fluids circuits in these three systems are always seperated, but the three systems do provide eachother back-up power (link).

The two pictures to the right are examples of hydraulic systems in an aircraft (different types of planes, not the Airbus A320). The hydraulic system is (besides for the cargo doors) also used to control the direction of the plane, by steering its wings, tail and brakes. 

In an A320, the cargo doors can only be opened (a) from the outside, and (b) when the aircraft is standing still. They are operated by the water pressure in the “yellow system”. The yellow system is pressurized by an engine driven pump on engine number 2 (the green system is on engine 1). The yellow system is pressured by the hydraulic power coming from engine 2 and also has (as backup) an electrically driven hydraulic pump. When both do not work in the yellow system (for instance when the plane is standing still and there is no AC power), a hand pump provides backup pressure to the yellow hydraulic system specifically to operate the cargo doors. This handpump is to be operated from outside the plane and is solely meant to open the cargo door (from the outside) when the operating systems in the airplane are down (generally speaking: the plane has landed, both engines are off, and cargo doors need to be opened, yet the AC power doesnot work).

I thus have some questions for an aviation expert or an A320 airbus maker:

  • What happens when someone is able to open the cargo door, somehow, mid flight?
  • How can an A320 be adjusted so that the manual handles to open the cargo door (positioned outside the plane) are in fact operated from inside the cargo storage unit?
  • What would it take to simply (brutally) open the door with force mid flight?
  • Opening of a cargo door would normally only happen when standing still in an airport. For safety, when opening the cargo door, normal cockpit activities to operate the plane are blocked. So when someone somehow would be able to open the cargo door mid flight, does that mean some cockpit steering mechanisms are no longer operational?
  • When the yellow hydraulic system is blocked (cargo door is open), does it mean water pressure remains as it is and thus steering gear remains in a fixed position, e.g. exactly like it was the moment it is blocked?

capture-d-ecran-flightradar

What is needed to make these adjustments without suspicions? Bring on board the ejection cabin in Barcelona? Make some preps to sabbotage the cargo door?

From what I understand, the yellow system switches automatically to the electric hydraulic pump when the cargo doors are operated, provided AC power is available (if no AC power is available, there is the hand-pump). Also, an inhibition system prevents the operation of all other components powered by the yellow hydraulic system, except for the cargo doors. I am by no means an expert in this area. To me it seems the cargo door system is designed, so that it can not be opened when in the air. Also, it is designed so that when someone is opening the cargo doors (which theoretically can only happen when on the ground), in the cockpit one can no longer change the direction of the plane?

My quess is, terrorists who sabotage a plane, are able to open the cargo door somehow mid air. The main question is: would that limit any last attempts of a crew member to steer the plane upwards and avoid the mountain?

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BELOW: A TRAINING SCHEDULE ON A320 HYDRAULIC SYSTEMS

Hydraulics Story board    Printed:  10/19/04   Source: www.avso.com

Scene 1 Audio: B29S233 __________    Last Modified:7/8/2004

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Scene 2 Audio: B29S234 __________    Last Modified:7/22/2004

In this module, we will cover the hydraulics system installed on the A320.  We will start out with a general overview of the hydraulics system.  Next, we will cover each system in detail.  We will then look at the controls and indications associated with the hydraulic system.

A validation exam will conclude this module.

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Scene 3 Audio: B29S235 __________    Last Modified:7/22/2004

The hydraulic system provides hydraulic pressure to operate:

*  The flight controls
*  Slats and flaps
*  The landing gear, brakes, and nosewheel steering
*  The cargo doors

and

*  Produce electrical power through a hydraulically driven emergency electrical generator.

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Scene 4 Audio: B29S236 __________    Last Modified:7/8/2004

The hydraulic system is divided into three systems.  These are called the GREEN, BLUE, and YELLOW hydraulic systems.

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The hydraulic system is designed so that there is no interchange of fluid between the three systems. This arrangement segregates the three hydraulic systems from each other.

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Each hydraulic system has its own reservoir.  Hydraulic pumps supply hydraulic pressure at 3000 PSI.

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Scene 7 Audio: B29S239 __________    Last Modified:7/22/2004

The GREEN system is pressurized by an engine driven hydraulic pump.  This pump is turned by engine number 1.  The YELLOW system is also pressurized by an engine driven pump, this one driven by engine number 2.

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Scene 8 Audio: B29S339 __________    Last Modified:7/22/2004

A Power Transfer Unit, or PTU, enables the GREEN system to pressurize the YELLOW system, and vice-versa.  There is no interchange of fluid.

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The YELLOW system incorporates a backup electrically driven hydraulic pump.

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The BLUE hydraulic system is pressurized by an electric hydraulic pump.

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A Ram Air Turbine, or RAT, can provide back up hydraulic pressure source to the BLUE hydraulic system.

This RAT consists of a hydraulic pump which is driven by a propeller.  When RAT hydraulic pressure is required, the RAT is extended into the air stream, and the propeller drives a shaft which, in turn, drives a hydraulic pump.

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Scene 12 Audio: B29S241 __________    Last Modified:7/8/2004

A hand pump provides backup pressure to the yellow hydraulic system when no electric power is available.  This pressure is used to operate the cargo doors.

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Scene 13 Audio: B29S242 __________    Last Modified:7/22/2004

The hydraulic system is monitored by the Hydraulic System Monitoring Unit, or HSMU.

Hydraulic system information is displayed on the Hydraulic ECAM page.

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Scene 14 Audio: B29S244 __________    Last Modified:7/22/2004

The HSMU controls functions of the hydraulic system such as:

*  Extension of the Ram Air Turbine
*  Reservoir overheat warnings
*  Illumination of the various FAULT lights

and

* Automatic operation of the BLUE electric hydraulic pump

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Scene 15 Audio: B29S243 __________    Last Modified:7/8/2004

The controls and indicators associated with the hydraulic system are on the Hydraulic panel, located on the cockpit overhead panel.

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We will now take a detailed look at the hydraulic system. We will start with a description of the GREEN hydraulic system.

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Scene 17 Audio: B29S247 __________    Last Modified:7/8/2004

The GREEN hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 18 Audio: B29S251 __________    Last Modified:7/8/2004

The GREEN hydraulic system supplies the following components:

*  The Emergency electrical generator
*  The nose wheel steering system
*  The normal brakes
*  The flaps and slats
*  The flight control surfaces.

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Scene 19 Audio: B29S252 __________    Last Modified:7/22/2004

GREEN hydraulic pressure is provided by an engine driven hydraulic pumps.  The pump is driven by engine number 1.

GREEN hydraulic pressure  is available anytime the number 1 engine is running, provided the associated fire shutoff valve is open.

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Scene 20 Audio: B29S250 __________    Last Modified:7/24/2004

The engine driven hydraulic pump supplies approximately 3000 PSI of pressure.

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Scene 21 Audio: B29S256 __________    Last Modified:7/22/2004

The GREEN engine driven hydraulic pump is controlled by the ENGine 1 PUMP pushbutton, located on the Hydraulic control panel.

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Scene 22 Audio: B29S253 __________    Last Modified:7/22/2004

In addition, the GREEN hydraulic system can be pressurized by the Power Transfer Unit, or PTU.  The PTU uses hydraulic pressure in the YELLOW system to drive a pump in the GREEN system, thereby pressurizing the GREEN hydraulic system.  The PTU will operate in the event there is a pressure differential between the GREEN and YELLOW systems.

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Scene 23 Audio: B29S248 __________    Last Modified:7/24/2004

A fire shutoff valve is located between the GREEN hydraulic reservoir and the engine driven hydraulic pump.  This valves is closed by pressing, and releasing the engine 1 fire pushbutton, located on the engine fire control panel.  In the event of an engine fire, the hydraulic fluid will not be supplied to the GREEN engine driven hydraulic pump.

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Scene 24 Audio: B29S254 __________    Last Modified:7/22/2004

An accumulator, located downstream of the engine driven hydraulic pump, provides dampening during pressure fluctuations.  The accumulator is pressurized by the engine driven hydraulic pump.

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Scene 25 Audio: B29S264 __________    Last Modified:7/9/2004

We will now look at the BLUE hydraulic system.

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Scene 26 Audio: B29S266 __________    Last Modified:7/9/2004

The BLUE hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 27 Audio: B29S267 __________    Last Modified:7/9/2004

The BLUE hydraulic system supplies pressure to the following systems:

*  Alternate brakes and the parking brake
*  Slats and slats wing tip brakes
*  Pitch Trim 2
*  The Backup control module
*  Spoliers 2 and 3
*  The inboard ailerons
*  The left elevator
*  The rudder

and

*  Engine 1 thrust reverser

The BLUE system does not incorporate a priority valve.

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Scene 28 Audio: B29S268 __________    Last Modified:7/22/2004

BLUE hydraulic pressure is provided by a single electrically driven hydraulic pump.  This pump supplies approximately 3000 PSI of hydraulic pressure.

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Scene 29 Audio: B29S269 __________    Last Modified:7/24/2004

Unlike the GREEN and YELLOW systems, the BLUE system does not have a fire shutoff valve between the BLUE hydraulic system reservoir, and the electric hydraulic pump.

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Scene 30 Audio: B29S271 __________    Last Modified:7/22/2004

On the ground, the Blue Hydraulic system electric hydraulic pump automatically operates when:

     *  Either engine is running

OR

     *  AC Bus 1 is powered.

In flight, the BLUE system hydraulic pump operates when the elctrical system is normally configured.

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Scene 31 Audio: B29S272 __________    Last Modified:7/22/2004

The BLUE electrically driven hydraulic pump is controlled by the  guarded ELECtric PUMP pushbutton, located on the Hydraulic control panel.

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Scene 32 Audio: B29S342 __________    Last Modified:7/22/2004

A Ram Air Turbine, also known as the RAT, can also pressurize the BLUE hydraulic system.  This RAT is mounted in parallel to the electric hydraulic pump.

The RAT is used to pressurize the BLUE electric system in the event of an electrical power loss, or a dual engine failure.

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Scene 33 Audio: B29S255 __________    Last Modified:7/22/2004

When the RAT is extended, the attached hydraulic pump will be able to draw hydraulic fluid from the BLUE hydraulic reservoir.  The RAt can provide a nominal system pressure, provided the aircraft speed is above a certain limit.

The RAT is only used to provide emergency hydraulic pressure, and, in the case of an electrical emergency, drive a hydraulic motor which runs an emergency electrical generator..

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Scene 34 Audio: B29S261 __________    Last Modified:7/22/2004

The RAT is mounted in the lower fuselage, near the left wing root.

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Scene 35 Audio: B29S337 __________    Last Modified:7/21/2004

The minimum airspeed for proper RAT operation is 140 knots.

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Scene 36 Audio: B29S262 __________    Last Modified:7/23/2004

The RAT is controlled by the red guarded RAT MAN ON pushbutton, located on the Hydraulic Control Panel.  Lifting the guard and pressing the RAT MANual ON pushbutton will deploy the Ram Air Turbine.  The RAT can be extended when the aircraft is on the ground, or in flight.  Once deployed, the RAT can only be stowed when the aircraft is on the ground.

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Scene 37 Audio: B29S263 __________    Last Modified:7/22/2004

The RAT can also deploy automatically when the aircraft is in flight.  In flight, the RAT will automatically deploy when the aircraft is in the emergency electrical configuration.  This will be covered during the electrical module.

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Scene 38 Audio: B29S343 __________    Last Modified:7/22/2004

Once the RAT is deployed, the E/WD will display the RAT OUT message.

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Scene 39 Audio: B29S265 __________    Last Modified:7/23/2004

It should also be noted that you can manually deploy the RAT by pressing the EMERgency ELECtrical pushbutton, on the electrical control panel.  However, this action connects the emergency electrical generator to the essential AC and DC buses.  Due to this, it is not recommended to use this method to deploy the RAT in the event of a hydraulic malfunction.

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Scene 40 Audio: B29S344 __________    Last Modified:7/22/2004

An accumulator is pressurized by the BLUE hydraulic pumps.  This accumulator dampens any pressure fluctuations in the BLUE hydraulic system

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Scene 41 Audio: B29S345 __________    Last Modified:7/22/2004

Certain conditions can cause the BLUE hydraulic system to degrade.  These conditions are:

     *  A failure of the BLUE electric hydraulic pump
     *  A failure of the BLUE hydraulic reservoir

and

     *  A failure of the Ram Air Turbine, following the failure of the BLUE electric hydraulic pump.

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Scene 42 Audio: B29S346 __________    Last Modified:7/22/2004

In the event of a failure of the BLUE electric Hydraulic pump, the RAT can be deployed and used to provide hydraulic pressure to the BLUE hydraulic system.  The RAT does not automatically deploy in the event of a failure of the BLUE electric hydraulic pump.

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Scene 43 Audio: B29S347 __________    Last Modified:7/23/2004

In the event the BLUE hydraulic system reservoir is depleted, the electric hydraulic pump will have to be shut down, and you will not be able to use the RAT for backup power.

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Scene 44 Audio: B29S348 __________    Last Modified:7/22/2004

A BLUE reservoir overheat will require the shut down of the BLUE electric hydraulic pump.  In this case, the pump can be restarted after the overheat condition has been corrected.

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Scene 45 Audio: B29S349 __________    Last Modified:7/22/2004

The BLUE hydraulic system can remain unpressurized as long as the other two hydraulic systems are pressurized.

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Scene 46 Audio: B29S276 __________    Last Modified:7/9/2004

We will now look at the YELLOW hydraulic system.

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Scene 47 Audio: B29S277 __________    Last Modified:7/9/2004

The YELLOW hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 48 Audio: B29S278 __________    Last Modified:7/17/2004

The YELLOW hydraulic system powers the following systems:

*  Flaps and flaps wing tip brakes
*  Pitch Trim 1
*  Backup control module
*  Spoilers 4 and 6
*  The outboard ailerons
*  The right elevator
*  The rudder
and

*  Engine 2 thrust reverser

The YELLOW hydraulic system does not incorporate a priority valve.

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Scene 49 Audio: B29S279 __________    Last Modified:7/23/2004

The YELLOW hydraulic system can be pressurized by one of four sources:

      *  An engine driven pump
      *  An electric pump
      *  The Power Transfer Unit

and

      *  A hand pump can be used to pressurize the YELLOW system to open the cargo door.

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Scene 50 Audio: B29S351 __________    Last Modified:7/23/2004

An accumulator located downstream of the various pressure sources supplies hydraulic pressure when the pump is unable to meet transient system demands.

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Scene 51 Audio: B29S350 __________    Last Modified:7/23/2004

The primary means of pressurization of the YELLOW hydraulic system is an engine driven pump, driven by engine number 2.

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Scene 52 Audio: B29S282 __________    Last Modified:7/23/2004

The engine driven hydraulic pump supplies approximately 3000 PSI of pressure.

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Scene 53 Audio: B29S280 __________    Last Modified:7/9/2004

A fire shutoff valve is located between the YELLOW hydraulic reservoir and the engine driven hydraulic pump.  This valve is closed by pressing, and releasing the engine 2 fire pushbutton, located on the engine fire control panel.  In the event of an engine fire, the hydraulic fluid will not be supplied to the YELLOW engine driven hydraulic pump.

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Scene 54 Audio: B29S283 __________    Last Modified:7/23/2004

The YELLOW engine driven hydraulic pump is controlled by the ENGine 2 pushbutton, located on the Hydraulic control panel.

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Scene 55 Audio: B29S284 __________    Last Modified:7/23/2004

An electric hydraulic pump can also supply hydraulic pressure to the YELLOW system.  Hydraulic fluid is supplied to this electric pump prior to the hydraulic pump fire shutoff valve.  Therefore, in the event of an engine 2 fire, the YELLOW hydraulic system will be able to be pressurized, even though the engine 2 hydraulic pump is no longer operational.  

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Scene 56 Audio: B29S285 __________    Last Modified:7/23/2004

The YELLOW electric hydraulic pump is controlled by the electric hydraulic pump pushbutton, on the hydraulic control panel.

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Scene 57 Audio: B29S289 __________    Last Modified:7/9/2004

In addition, the YELLOW electric hydraulic pump will automatically activate when the cargo doors are operated, provided AC power is available.  However, an inhibition system prevents the operation of components powered by the YELLOW hydraulic system, except for the cargo doors.

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Scene 58 Audio: B29S290 __________    Last Modified:7/17/2004

In the event AC power is not available, the YELLOW hydraulic system incorporates a hand pump which enables the pressurization of the YELLOW system to operate the cargo doors only.  This hand pump is accessible from a panel located on the exterior of the aircraft.

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Scene 59 Audio: B29S352 __________    Last Modified:7/24/2004

In addition, the YELLOW hydraulic system can be pressurized by the Power Transfer Unit, or PTU.  The PTU uses hydraulic pressure in the GREEN system to drive a pump in the YELLOW system, thereby pressurizing the YELLOW hydraulic system.  The PTU will operate in the event there is a certain pressure differential between the GREEN and YELLOW systems.

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Scene 60 Audio: B29S353 __________    Last Modified:7/24/2004

The PTU and engine driven pumps should not be used in the event of a low level reservoir in either the GREEN or YELLOW systems, a reservoir overheat or reservoir low air pressure in either of these two systems.  Under these circumstances, FAULT lights will illuminate in the PTU and affected engine pump pushbuttons, and the engine driven pump nor the PTU should not be used.  They should be selected OFF if they are in use.

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Scene 61 Audio: B29S354 __________    Last Modified:7/24/2004

If the YELLOW electric hydraulic pump is supplying the pressure when one of these malfunctions occurs, then the YELLOW electric pump pushbutton will have an illuminated FAULT light, and the pump should be selected OFF.

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Scene 62 Audio: B29S355 __________    Last Modified:7/24/2004

If the fault was due to a reservoir overheat, then the affected engine pump and PTU can be turned ON.

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Scene 63 Audio: B29S356 __________    Last Modified:7/24/2004

The PTU can be used to pressurize a system, even if the fire shutoff valve is closed.

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Scene 64 Audio: B29S291 __________    Last Modified:7/9/2004

We will now look at the controls and indicators associated with the hydraulic system.

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Scene 65 Audio: B29S292 __________    Last Modified:7/16/2004

The Hydraulic ECAM page indicates the status of the various components of the hydraulic system.  We will now look at each component.

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Scene 66 Audio: B29S293 __________    Last Modified:7/16/2004

The Hydraulic reservoir quantity is displayed at the bottom of the Hydraulic page.  The indication consists of a pointer against a white, vertical scale.  The green pointer indicates the hydraulic quantity in the particular reservoir.

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Scene 67 Audio: B29S294 __________    Last Modified:7/16/2004

A green box near the top of the scale indicates the normal reservoir fill level.  This quantity is corrected for temperature variations, and in the event the temperature correction is inoperative, the green box is displayed in white.

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Scene 68 Audio: B29S295 __________    Last Modified:7/17/2004

The hydraulic quantity indications change colors when the fluid level drops below the low fluid level.  In this case, the fluid level pointer changes from green to amber, the white vertical scale changes to amber, and a HYDraulic ReSerVoiR LOw LeVeL message is displayed in the E/WD.  This message will also indicate which hydraulic system is affected.  In addition, the Hydraulic page is automatically displayed.

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Scene 69 Audio: B29S296 __________    Last Modified:7/21/2004

An amber OverHeaT message is displayed near the bottom of the affected reservoir indication in the event of a reservoir fluid overheat.  In addition, the E/WD displays a HYDraulic ReSerVoiR OVerHeaT message.

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Scene 70 Audio: B29S297 __________    Last Modified:7/21/2004

A LOw AIR PRESSure amber message is displayed near the affected reservoir indication in the event the reservoir head pressure is below a certain limit.  In addition, the E/WD displays a HYDraulic ReSerVoiR LOw AIR PRessure.

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Scene 71 Audio: B29S301 __________    Last Modified:7/24/2004

The position of the engine fire shutoff valves is displayed immediately above the GREEN and YELLOW reservoir indications.  The valve is displayed in green, with an in-line, when the associated fire shutoff valve is not fully closed.  It is displayed in amber, with a cross-line when the associated fire shutoff valve is fully closed.

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Scene 72 Audio: B29S302 __________    Last Modified:7/24/2004

The engine driven hydraulic pumps are represented by a square with a line within the square.  A green, in-line square indicates that the associated hydraulic pushbutton is ON and the hydraulic pressure is normal.

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Scene 73 Audio: B29S303 __________    Last Modified:7/16/2004

An amber, cross-line square indicates that the associated pushbutton is OFF.

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Scene 74 Audio: B29S304 __________    Last Modified:7/21/2004

An amber square with a LOw label indicates the associated engine hydraulic pump pushbutton is ON, and the pressure is low. The E/WD displays a HYDraulic ENGine PUMP LOw PRessure message.

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Scene 75 Audio: B29S361 __________    Last Modified:7/24/2004

The engine number is normally displayed in white, next to the associated engine driven hydraulic pump.  They are displayed in amber when the associated engine is not running.

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Scene 76 Audio: B29S359 __________    Last Modified:7/24/2004

The representation for the electric pump in the BLUE system is identical to the engine driven pump indications.  The only difference is the white ELECtric label.

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Scene 77 Audio: B29S305 __________    Last Modified:7/24/2004

The electric hydraulic pump in the YELLOW system is indicated by a triangle labeled ELECtric.  The color of the triangle and label indicates the status of the associated electric hydraulic pump.

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Scene 78 Audio: B29S334 __________    Last Modified:7/21/2004

The ELECtric label is displayed in amber in the event of a failure of the power supply to the pump.

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Scene 79 Audio: B29S306 __________    Last Modified:7/16/2004

A white, hollow triangle, and label, indicates that the associated electric hydraulic pump is not commanded to run.

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Scene 80 Audio: B29S307 __________    Last Modified:7/21/2004

A solid green triangle, with a white electric label, indicates that the associated electric hydraulic pump is ON, and it is supplying normal pressure.

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Scene 81 Audio: B29S308 __________    Last Modified:7/24/2004

A amber, solid triangle indicates that the associated electric hydraulic pump is commanded to run, but the output pressure is low.

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Scene 82 Audio: B29S310 __________    Last Modified:7/24/2004

An amber, hollow triangle, with an amber ELECtric OVerHeat label, indicates that the associated electric hydraulic pump has automatically shutdown due to an overheat. In addition, the vertical line, adjacent to the triangle, connecting the engine driven pump to the pressure indication  will no longer be displayed.

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Scene 83 Audio: B29S311 __________    Last Modified:7/17/2004

The status of the Ram Air Turbine is indicated by a triangle labeled RAT.  A white, hollow triangle with a white RAT label indicates that the Ram Air Turbine is stowed.

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Scene 84 Audio: B29S312 __________    Last Modified:7/24/2004

A solid, green triangle and a white RAT label indicates that the RAT is not stowed.

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Scene 85 Audio: B29S313 __________    Last Modified:7/24/2004

A solid amber triangle and amber RAT label indicate that the RAT is not available.

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Scene 86 Audio: B29S336 __________    Last Modified:7/24/2004

The E/WD displays a green RAT OUT message when the RAT is not fully stowed when the aircraft is in flight.

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Scene 87 Audio: B29S360 __________    Last Modified:7/24/2004

An amber RAT OUT message is displayed in the E/WD when the RAT is not fully stowed when the aircraft is on the ground, prior to takeoff power application.

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Scene 88 Audio: B29S362 __________    Last Modified:7/24/2004

The line labeled PTU represents the status of the PTU.  This indication is located between the GREEN and YELLOW systems.

Green arrows pointing away from a white PTU label indicate that the PTU pushbutton is in the AUTO, or armed position, but the PTU is not supplying pressure to either system.  This would be the normal indication when both engines are running.

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Scene 89 Audio: B29S363 __________    Last Modified:7/24/2004

The line and arrows are displayed in amber when the PTU pushbutton is in the OFF position.

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Scene 90 Audio: B29S364 __________    Last Modified:7/24/2004

Green arrows, a green line, and a green PTU label indicate that the PTU is operating.  The arrows point to the hydraulic system being pressurized by the PTU.  In this example, the GREEN system is using the PTU to pressurize the YELLOW system.

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Scene 91 Audio: B29S365 __________    Last Modified:7/24/2004

The E/WD displays a green HYDraulic PTU message when the PTU is running.

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Scene 92 Audio: B29S315 __________    Last Modified:7/24/2004

The pressure within each hydraulic system is displayed at the top of the hydraulic page.  The numerical indication is displayed in green if the associated system pressure is normal.  The indication is displayed in amber if the pressure is below a certain value.

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Scene 93 Audio: B29S316 __________    Last Modified:7/24/2004

The system label – green, blue, or yellow, is displayed in white, and the associated distribution triangle is displayed in green if the associated hydraulic system pressure is normal.  Both the label and the distribution triangle turn amber if the associated hydraulic system pressure decreases below a certain value.

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Scene 94 Audio: B29S317 __________    Last Modified:7/17/2004

There is an exception to this logic.  When the yellow hydraulic electric pump is operating for cargo door operation, the numerical system pressure is displayed in green.  However, the yellow label, and the associated distribution triangle, will be displayed in amber to indicate that only a portion of the yellow system is powered.

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Scene 95 Audio: B29S335 __________    Last Modified:7/21/2004

The E/WD displays an amber SYStem LOw PRessure message in the event the system pressure in a particular system is low.  The message identifies the affected hydraulic system.

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Scene 96 Audio: B29S338 __________    Last Modified:7/21/2004

In the event of there is a low pressure in two hydraulic system, the E/WD will display a red SYStem LOw PRessure message.  The message will identify the affected hydraulic systems.  The Master warning lights flash in the event this message is displayed.

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Scene 97 Audio: B29S320 __________    Last Modified:7/17/2004

The controls for the hydraulic system are located on the Hydraulic control panel, on the cockpit overhead panel.

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Scene 98 Audio: B29S321 __________    Last Modified:7/24/2004

The engine driven hydraulic pumps are controlled by the ENGine 1, or 2, pushbutton for the respective hydraulic system.  In the ON position, the respective pump is operating when the associated engine is running.

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Scene 99 Audio: B29S322 __________    Last Modified:7/24/2004

Selecting the OFF position will cause the associated pump to depressurize.  No hydraulic pressure will be produced, even though the pump continues to turn.  The OFF light illuminates in the pushbutton to indicate that it has been selected OFF.

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Scene 100 Audio: B29S323 __________    Last Modified:7/24/2004

The FAULT light illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats.
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low while the aircraft is on the ground and the associated engine is running, or anytime while in flight.  The fault light is inhibited when the aircraft is on the ground and the associated engine is not running.

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Scene 101 Audio: B29S324 __________    Last Modified:7/17/2004

The FAULT light extinguishes when the associated pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 102 Audio: B29S325 __________    Last Modified:7/24/2004

The BLUE electric hydraulic pump is controlled by the guarded electric pump pushbutton, also located on the hydraulic control panel.  This pushbutton is normally in the AUTO, or lights out position.

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Scene 103 Audio: B29S326 __________    Last Modified:7/24/2004

In the AUTO position, the BLUE electric hydraulic pump is always energized while the aircraft is in flight, provided AC power is available.  The pump will start to run on the ground when at least one engine is operating, provided AC power is available.

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Scene 104 Audio: B29S329 __________    Last Modified:7/24/2004

The FAULT light in the BLUE electric pump pushbutton illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats
     *  The associated electric hydraulic pump overheats
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low when an engine is running on the ground, or anytime in flight.  The fault light is inhibited when the aircraft is on the ground and the associated engine is not running.

The E/WD displays a HYDraulic ELECtric PUMP FAULT message.

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Scene 105 Audio: B29S330 __________    Last Modified:7/17/2004

The FAULT light extinguishes when the associated OFF pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 106 Audio: B29S378 __________    Last Modified:7/24/2004

A guarded BLUE PUMP OVeRiDe pushbutton, located on the overhead maintenance panel, provides a way to operate the BLUE system electric pump when the engines are not running.

In the normal, lights out position, the BLUE electric pump will operate when an engine is running.

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Scene 107 Audio: B29S379 __________    Last Modified:7/24/2004

Lifting the guard, and selecting the ON position will energize the BLUE electric hydraulic pump, even if none of the engines is running.

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Scene 108 Audio: B29S366 __________    Last Modified:7/24/2004

The YELLOW electric hydraulic pump is controlled by the electric pump pushbutton, also located on the hydraulic control panel.  This pushbutton is normally in the OFF, or lights out position.

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Scene 109 Audio: B29S367 __________    Last Modified:7/24/2004

In the OFF position, the YELLOW electric hydraulic pump will be automatically energized when the cargo door manual selector valve is moved.  The PTU and flight controls will be inhibited in this situation.

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Scene 110 Audio: B29S368 __________    Last Modified:7/24/2004

In the ON position, the YELLOW electric hydraulic pump is energized, and the flight controls and flaps will be pressurized, even if the engines are not running.  They will be pressurized by the YELLOW and GREEN systems, via the PTU.

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Scene 111 Audio: B29S369 __________    Last Modified:7/24/2004

The FAULT light in the YELLOW electric pump pushbutton illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats
     *  The associated electric hydraulic pump overheats
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low.

The E/WD displays a HYDraulic ELECtric PUMP FAULT message.

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Scene 112 Audio: B29S370 __________    Last Modified:7/24/2004

The FAULT light extinguishes when the associated OFF pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 113 Audio: B29S332 __________    Last Modified:7/24/2004

The red guarded RAT ON pusbutton is used to manually deploy the RAT.  The RAT is stowed when the pushbutton is in the guarded position.  Lifting the guard, and pressing the RAT MAN ON pushbutton deploys the RAT.

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Scene 114 Audio: B29S371 __________    Last Modified:7/24/2004

The RAT will automatically deploy while in flight when AC bus 1 and 2 are not powered.  In this case, the emergency generator will be operating.

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Scene 115 Audio: B29S372 __________    Last Modified:7/24/2004

The PTU is controlled by the PTU pushbutton, on the overhead hydraulic control panel.  This pushbutton is normally in the AUTO, or lights out, position. This will cause the PTU to automatically operate when there is a certain pressure differential between the GREEN and YELLOW systems.

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Scene 116 Audio: B29S373 __________    Last Modified:7/24/2004

The PTU will not automatically operate for the following conditions:

     *  The cargo doors are being operated.  

     *  During the first engine start, and when only one engine is operating while the aircraft is on the ground.

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Scene 117 Audio: B29S374 __________    Last Modified:7/24/2004

The engine inhibition is based on the following conditions:

     *  One engine is running, and the other engine master switch is OFF
     *  The parking brake is set
and, or
     *  The tow bar is attached.

After the second engine master switch is placed to ON, the PTU performs a self-test, and it will automatically enter the AUTO mode following a successful test, provided the PTU pushbutton is in the AUTO position.

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Scene 118 Audio: B29S377 __________    Last Modified:7/24/2004

The ECAM will not inform the crew in the event the PTU fails the self-test.  The crew will become aware of the problem only if there is a subsequent GREEN or YELLOW hydraulic pump failure.  The indication on the ECAM Hydraulic page is that the PTU is not operating as expected.

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Scene 119 Audio: B29S375 __________    Last Modified:7/24/2004

Placing the PTU pushbutton to the OFF position will deactivate the PTU.

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Scene 120 Audio: B29S376 __________    Last Modified:7/24/2004

The FAULT light illuminates in the PTU pushbutton for one of the following conditions:

     *  GREEN or YELLOW system low reservoir level
     *  GREEN or YELLOW reservoir overheat
     *  GREEN or YELLOW reservoir low head pressure

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Scene 121 Audio: B29S333 __________    Last Modified:7/17/2004

This concludes the Hydraulic module.  The following questions should be answered to validate this module.

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-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-  END OF STORY BOARD  *-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*-*

Hydraulics Story board    Printed:  10/19/04

Scene 1 Audio: B29S233 __________    Last Modified:7/8/2004

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Scene 2 Audio: B29S234 __________    Last Modified:7/22/2004

In this module, we will cover the hydraulics system installed on the A320.  We will start out with a general overview of the hydraulics system.  Next, we will cover each system in detail.  We will then look at the controls and indications associated with the hydraulic system.

A validation exam will conclude this module.

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Scene 3 Audio: B29S235 __________    Last Modified:7/22/2004

The hydraulic system provides hydraulic pressure to operate:

*  The flight controls
*  Slats and flaps
*  The landing gear, brakes, and nosewheel steering
*  The cargo doors

and

*  Produce electrical power through a hydraulically driven emergency electrical generator.

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Scene 4 Audio: B29S236 __________    Last Modified:7/8/2004

The hydraulic system is divided into three systems.  These are called the GREEN, BLUE, and YELLOW hydraulic systems.

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Scene 5 Audio: B29S245 __________    Last Modified:7/8/2004

The hydraulic system is designed so that there is no interchange of fluid between the three systems. This arrangement segregates the three hydraulic systems from each other.

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Scene 6 Audio: B29S237 __________    Last Modified:7/8/2004

Each hydraulic system has its own reservoir.  Hydraulic pumps supply hydraulic pressure at 3000 PSI.

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Scene 7 Audio: B29S239 __________    Last Modified:7/22/2004

The GREEN system is pressurized by an engine driven hydraulic pump.  This pump is turned by engine number 1.  The YELLOW system is also pressurized by an engine driven pump, this one driven by engine number 2.

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Scene 8 Audio: B29S339 __________    Last Modified:7/22/2004

A Power Transfer Unit, or PTU, enables the GREEN system to pressurize the YELLOW system, and vice-versa.  There is no interchange of fluid.

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Scene 9 Audio: B29S340 __________    Last Modified:7/22/2004

The YELLOW system incorporates a backup electrically driven hydraulic pump.

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Scene 10 Audio: B29S341 __________    Last Modified:7/22/2004

The BLUE hydraulic system is pressurized by an electric hydraulic pump.

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Scene 11 Audio: B29S240 __________    Last Modified:7/22/2004

A Ram Air Turbine, or RAT, can provide back up hydraulic pressure source to the BLUE hydraulic system.

This RAT consists of a hydraulic pump which is driven by a propeller.  When RAT hydraulic pressure is required, the RAT is extended into the air stream, and the propeller drives a shaft which, in turn, drives a hydraulic pump.

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Scene 12 Audio: B29S241 __________    Last Modified:7/8/2004

A hand pump provides backup pressure to the yellow hydraulic system when no electric power is available.  This pressure is used to operate the cargo doors.

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Scene 13 Audio: B29S242 __________    Last Modified:7/22/2004

The hydraulic system is monitored by the Hydraulic System Monitoring Unit, or HSMU.

Hydraulic system information is displayed on the Hydraulic ECAM page.

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Scene 14 Audio: B29S244 __________    Last Modified:7/22/2004

The HSMU controls functions of the hydraulic system such as:

*  Extension of the Ram Air Turbine
*  Reservoir overheat warnings
*  Illumination of the various FAULT lights

and

* Automatic operation of the BLUE electric hydraulic pump

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Scene 15 Audio: B29S243 __________    Last Modified:7/8/2004

The controls and indicators associated with the hydraulic system are on the Hydraulic panel, located on the cockpit overhead panel.

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Scene 16 Audio: B29S246 __________    Last Modified:7/8/2004

We will now take a detailed look at the hydraulic system. We will start with a description of the GREEN hydraulic system.

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Scene 17 Audio: B29S247 __________    Last Modified:7/8/2004

The GREEN hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 18 Audio: B29S251 __________    Last Modified:7/8/2004

The GREEN hydraulic system supplies the following components:

*  The Emergency electrical generator
*  The nose wheel steering system
*  The normal brakes
*  The flaps and slats
*  The flight control surfaces.

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Scene 19 Audio: B29S252 __________    Last Modified:7/22/2004

GREEN hydraulic pressure is provided by an engine driven hydraulic pumps.  The pump is driven by engine number 1.

GREEN hydraulic pressure  is available anytime the number 1 engine is running, provided the associated fire shutoff valve is open.

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Scene 20 Audio: B29S250 __________    Last Modified:7/24/2004

The engine driven hydraulic pump supplies approximately 3000 PSI of pressure.

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Scene 21 Audio: B29S256 __________    Last Modified:7/22/2004

The GREEN engine driven hydraulic pump is controlled by the ENGine 1 PUMP pushbutton, located on the Hydraulic control panel.

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Scene 22 Audio: B29S253 __________    Last Modified:7/22/2004

In addition, the GREEN hydraulic system can be pressurized by the Power Transfer Unit, or PTU.  The PTU uses hydraulic pressure in the YELLOW system to drive a pump in the GREEN system, thereby pressurizing the GREEN hydraulic system.  The PTU will operate in the event there is a pressure differential between the GREEN and YELLOW systems.

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Scene 23 Audio: B29S248 __________    Last Modified:7/24/2004

A fire shutoff valve is located between the GREEN hydraulic reservoir and the engine driven hydraulic pump.  This valves is closed by pressing, and releasing the engine 1 fire pushbutton, located on the engine fire control panel.  In the event of an engine fire, the hydraulic fluid will not be supplied to the GREEN engine driven hydraulic pump.

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Scene 24 Audio: B29S254 __________    Last Modified:7/22/2004

An accumulator, located downstream of the engine driven hydraulic pump, provides dampening during pressure fluctuations.  The accumulator is pressurized by the engine driven hydraulic pump.

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Scene 25 Audio: B29S264 __________    Last Modified:7/9/2004

We will now look at the BLUE hydraulic system.

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Scene 26 Audio: B29S266 __________    Last Modified:7/9/2004

The BLUE hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 27 Audio: B29S267 __________    Last Modified:7/9/2004

The BLUE hydraulic system supplies pressure to the following systems:

*  Alternate brakes and the parking brake
*  Slats and slats wing tip brakes
*  Pitch Trim 2
*  The Backup control module
*  Spoliers 2 and 3
*  The inboard ailerons
*  The left elevator
*  The rudder

and

*  Engine 1 thrust reverser

The BLUE system does not incorporate a priority valve.

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Scene 28 Audio: B29S268 __________    Last Modified:7/22/2004

BLUE hydraulic pressure is provided by a single electrically driven hydraulic pump.  This pump supplies approximately 3000 PSI of hydraulic pressure.

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Scene 29 Audio: B29S269 __________    Last Modified:7/24/2004

Unlike the GREEN and YELLOW systems, the BLUE system does not have a fire shutoff valve between the BLUE hydraulic system reservoir, and the electric hydraulic pump.

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Scene 30 Audio: B29S271 __________    Last Modified:7/22/2004

On the ground, the Blue Hydraulic system electric hydraulic pump automatically operates when:

     *  Either engine is running

OR

     *  AC Bus 1 is powered.

In flight, the BLUE system hydraulic pump operates when the elctrical system is normally configured.

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Scene 31 Audio: B29S272 __________    Last Modified:7/22/2004

The BLUE electrically driven hydraulic pump is controlled by the  guarded ELECtric PUMP pushbutton, located on the Hydraulic control panel.

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Scene 32 Audio: B29S342 __________    Last Modified:7/22/2004

A Ram Air Turbine, also known as the RAT, can also pressurize the BLUE hydraulic system.  This RAT is mounted in parallel to the electric hydraulic pump.

The RAT is used to pressurize the BLUE electric system in the event of an electrical power loss, or a dual engine failure.

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Scene 33 Audio: B29S255 __________    Last Modified:7/22/2004

When the RAT is extended, the attached hydraulic pump will be able to draw hydraulic fluid from the BLUE hydraulic reservoir.  The RAt can provide a nominal system pressure, provided the aircraft speed is above a certain limit.

The RAT is only used to provide emergency hydraulic pressure, and, in the case of an electrical emergency, drive a hydraulic motor which runs an emergency electrical generator..

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Scene 34 Audio: B29S261 __________    Last Modified:7/22/2004

The RAT is mounted in the lower fuselage, near the left wing root.

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Scene 35 Audio: B29S337 __________    Last Modified:7/21/2004

The minimum airspeed for proper RAT operation is 140 knots.

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Scene 36 Audio: B29S262 __________    Last Modified:7/23/2004

The RAT is controlled by the red guarded RAT MAN ON pushbutton, located on the Hydraulic Control Panel.  Lifting the guard and pressing the RAT MANual ON pushbutton will deploy the Ram Air Turbine.  The RAT can be extended when the aircraft is on the ground, or in flight.  Once deployed, the RAT can only be stowed when the aircraft is on the ground.

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Scene 37 Audio: B29S263 __________    Last Modified:7/22/2004

The RAT can also deploy automatically when the aircraft is in flight.  In flight, the RAT will automatically deploy when the aircraft is in the emergency electrical configuration.  This will be covered during the electrical module.

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Scene 38 Audio: B29S343 __________    Last Modified:7/22/2004

Once the RAT is deployed, the E/WD will display the RAT OUT message.

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Scene 39 Audio: B29S265 __________    Last Modified:7/23/2004

It should also be noted that you can manually deploy the RAT by pressing the EMERgency ELECtrical pushbutton, on the electrical control panel.  However, this action connects the emergency electrical generator to the essential AC and DC buses.  Due to this, it is not recommended to use this method to deploy the RAT in the event of a hydraulic malfunction.

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Scene 40 Audio: B29S344 __________    Last Modified:7/22/2004

An accumulator is pressurized by the BLUE hydraulic pumps.  This accumulator dampens any pressure fluctuations in the BLUE hydraulic system

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Scene 41 Audio: B29S345 __________    Last Modified:7/22/2004

Certain conditions can cause the BLUE hydraulic system to degrade.  These conditions are:

     *  A failure of the BLUE electric hydraulic pump
     *  A failure of the BLUE hydraulic reservoir

and

     *  A failure of the Ram Air Turbine, following the failure of the BLUE electric hydraulic pump.

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Scene 42 Audio: B29S346 __________    Last Modified:7/22/2004

In the event of a failure of the BLUE electric Hydraulic pump, the RAT can be deployed and used to provide hydraulic pressure to the BLUE hydraulic system.  The RAT does not automatically deploy in the event of a failure of the BLUE electric hydraulic pump.

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Scene 43 Audio: B29S347 __________    Last Modified:7/23/2004

In the event the BLUE hydraulic system reservoir is depleted, the electric hydraulic pump will have to be shut down, and you will not be able to use the RAT for backup power.

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Scene 44 Audio: B29S348 __________    Last Modified:7/22/2004

A BLUE reservoir overheat will require the shut down of the BLUE electric hydraulic pump.  In this case, the pump can be restarted after the overheat condition has been corrected.

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Scene 45 Audio: B29S349 __________    Last Modified:7/22/2004

The BLUE hydraulic system can remain unpressurized as long as the other two hydraulic systems are pressurized.

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Scene 46 Audio: B29S276 __________    Last Modified:7/9/2004

We will now look at the YELLOW hydraulic system.

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Scene 47 Audio: B29S277 __________    Last Modified:7/9/2004

The YELLOW hydraulic system is supplied from its respective hydraulic reservoir.  In order to avoid pump cavitations, pneumatic air is used to provide a head pressure which prevents foaming of the hydraulic fluid.

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Scene 48 Audio: B29S278 __________    Last Modified:7/17/2004

The YELLOW hydraulic system powers the following systems:

*  Flaps and flaps wing tip brakes
*  Pitch Trim 1
*  Backup control module
*  Spoilers 4 and 6
*  The outboard ailerons
*  The right elevator
*  The rudder
and

*  Engine 2 thrust reverser

The YELLOW hydraulic system does not incorporate a priority valve.

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Scene 49 Audio: B29S279 __________    Last Modified:7/23/2004

The YELLOW hydraulic system can be pressurized by one of four sources:

      *  An engine driven pump
      *  An electric pump
      *  The Power Transfer Unit

and

      *  A hand pump can be used to pressurize the YELLOW system to open the cargo door.

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Scene 50 Audio: B29S351 __________    Last Modified:7/23/2004

An accumulator located downstream of the various pressure sources supplies hydraulic pressure when the pump is unable to meet transient system demands.

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Scene 51 Audio: B29S350 __________    Last Modified:7/23/2004

The primary means of pressurization of the YELLOW hydraulic system is an engine driven pump, driven by engine number 2.

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Scene 52 Audio: B29S282 __________    Last Modified:7/23/2004

The engine driven hydraulic pump supplies approximately 3000 PSI of pressure.

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Scene 53 Audio: B29S280 __________    Last Modified:7/9/2004

A fire shutoff valve is located between the YELLOW hydraulic reservoir and the engine driven hydraulic pump.  This valve is closed by pressing, and releasing the engine 2 fire pushbutton, located on the engine fire control panel.  In the event of an engine fire, the hydraulic fluid will not be supplied to the YELLOW engine driven hydraulic pump.

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Scene 54 Audio: B29S283 __________    Last Modified:7/23/2004

The YELLOW engine driven hydraulic pump is controlled by the ENGine 2 pushbutton, located on the Hydraulic control panel.

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Scene 55 Audio: B29S284 __________    Last Modified:7/23/2004

An electric hydraulic pump can also supply hydraulic pressure to the YELLOW system.  Hydraulic fluid is supplied to this electric pump prior to the hydraulic pump fire shutoff valve.  Therefore, in the event of an engine 2 fire, the YELLOW hydraulic system will be able to be pressurized, even though the engine 2 hydraulic pump is no longer operational.  

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Scene 56 Audio: B29S285 __________    Last Modified:7/23/2004

The YELLOW electric hydraulic pump is controlled by the electric hydraulic pump pushbutton, on the hydraulic control panel.

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Scene 57 Audio: B29S289 __________    Last Modified:7/9/2004

In addition, the YELLOW electric hydraulic pump will automatically activate when the cargo doors are operated, provided AC power is available.  However, an inhibition system prevents the operation of components powered by the YELLOW hydraulic system, except for the cargo doors.

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Scene 58 Audio: B29S290 __________    Last Modified:7/17/2004

In the event AC power is not available, the YELLOW hydraulic system incorporates a hand pump which enables the pressurization of the YELLOW system to operate the cargo doors only.  This hand pump is accessible from a panel located on the exterior of the aircraft.

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Scene 59 Audio: B29S352 __________    Last Modified:7/24/2004

In addition, the YELLOW hydraulic system can be pressurized by the Power Transfer Unit, or PTU.  The PTU uses hydraulic pressure in the GREEN system to drive a pump in the YELLOW system, thereby pressurizing the YELLOW hydraulic system.  The PTU will operate in the event there is a certain pressure differential between the GREEN and YELLOW systems.

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Scene 60 Audio: B29S353 __________    Last Modified:7/24/2004

The PTU and engine driven pumps should not be used in the event of a low level reservoir in either the GREEN or YELLOW systems, a reservoir overheat or reservoir low air pressure in either of these two systems.  Under these circumstances, FAULT lights will illuminate in the PTU and affected engine pump pushbuttons, and the engine driven pump nor the PTU should not be used.  They should be selected OFF if they are in use.

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Scene 61 Audio: B29S354 __________    Last Modified:7/24/2004

If the YELLOW electric hydraulic pump is supplying the pressure when one of these malfunctions occurs, then the YELLOW electric pump pushbutton will have an illuminated FAULT light, and the pump should be selected OFF.

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Scene 62 Audio: B29S355 __________    Last Modified:7/24/2004

If the fault was due to a reservoir overheat, then the affected engine pump and PTU can be turned ON.

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Scene 63 Audio: B29S356 __________    Last Modified:7/24/2004

The PTU can be used to pressurize a system, even if the fire shutoff valve is closed.

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Scene 64 Audio: B29S291 __________    Last Modified:7/9/2004

We will now look at the controls and indicators associated with the hydraulic system.

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Scene 65 Audio: B29S292 __________    Last Modified:7/16/2004

The Hydraulic ECAM page indicates the status of the various components of the hydraulic system.  We will now look at each component.

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Scene 66 Audio: B29S293 __________    Last Modified:7/16/2004

The Hydraulic reservoir quantity is displayed at the bottom of the Hydraulic page.  The indication consists of a pointer against a white, vertical scale.  The green pointer indicates the hydraulic quantity in the particular reservoir.

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Scene 67 Audio: B29S294 __________    Last Modified:7/16/2004

A green box near the top of the scale indicates the normal reservoir fill level.  This quantity is corrected for temperature variations, and in the event the temperature correction is inoperative, the green box is displayed in white.

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Scene 68 Audio: B29S295 __________    Last Modified:7/17/2004

The hydraulic quantity indications change colors when the fluid level drops below the low fluid level.  In this case, the fluid level pointer changes from green to amber, the white vertical scale changes to amber, and a HYDraulic ReSerVoiR LOw LeVeL message is displayed in the E/WD.  This message will also indicate which hydraulic system is affected.  In addition, the Hydraulic page is automatically displayed.

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Scene 69 Audio: B29S296 __________    Last Modified:7/21/2004

An amber OverHeaT message is displayed near the bottom of the affected reservoir indication in the event of a reservoir fluid overheat.  In addition, the E/WD displays a HYDraulic ReSerVoiR OVerHeaT message.

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Scene 70 Audio: B29S297 __________    Last Modified:7/21/2004

A LOw AIR PRESSure amber message is displayed near the affected reservoir indication in the event the reservoir head pressure is below a certain limit.  In addition, the E/WD displays a HYDraulic ReSerVoiR LOw AIR PRessure.

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Scene 71 Audio: B29S301 __________    Last Modified:7/24/2004

The position of the engine fire shutoff valves is displayed immediately above the GREEN and YELLOW reservoir indications.  The valve is displayed in green, with an in-line, when the associated fire shutoff valve is not fully closed.  It is displayed in amber, with a cross-line when the associated fire shutoff valve is fully closed.

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Scene 72 Audio: B29S302 __________    Last Modified:7/24/2004

The engine driven hydraulic pumps are represented by a square with a line within the square.  A green, in-line square indicates that the associated hydraulic pushbutton is ON and the hydraulic pressure is normal.

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Scene 73 Audio: B29S303 __________    Last Modified:7/16/2004

An amber, cross-line square indicates that the associated pushbutton is OFF.

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Scene 74 Audio: B29S304 __________    Last Modified:7/21/2004

An amber square with a LOw label indicates the associated engine hydraulic pump pushbutton is ON, and the pressure is low. The E/WD displays a HYDraulic ENGine PUMP LOw PRessure message.

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Scene 75 Audio: B29S361 __________    Last Modified:7/24/2004

The engine number is normally displayed in white, next to the associated engine driven hydraulic pump.  They are displayed in amber when the associated engine is not running.

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Scene 76 Audio: B29S359 __________    Last Modified:7/24/2004

The representation for the electric pump in the BLUE system is identical to the engine driven pump indications.  The only difference is the white ELECtric label.

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Scene 77 Audio: B29S305 __________    Last Modified:7/24/2004

The electric hydraulic pump in the YELLOW system is indicated by a triangle labeled ELECtric.  The color of the triangle and label indicates the status of the associated electric hydraulic pump.

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Scene 78 Audio: B29S334 __________    Last Modified:7/21/2004

The ELECtric label is displayed in amber in the event of a failure of the power supply to the pump.

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Scene 79 Audio: B29S306 __________    Last Modified:7/16/2004

A white, hollow triangle, and label, indicates that the associated electric hydraulic pump is not commanded to run.

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Scene 80 Audio: B29S307 __________    Last Modified:7/21/2004

A solid green triangle, with a white electric label, indicates that the associated electric hydraulic pump is ON, and it is supplying normal pressure.

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Scene 81 Audio: B29S308 __________    Last Modified:7/24/2004

A amber, solid triangle indicates that the associated electric hydraulic pump is commanded to run, but the output pressure is low.

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Scene 82 Audio: B29S310 __________    Last Modified:7/24/2004

An amber, hollow triangle, with an amber ELECtric OVerHeat label, indicates that the associated electric hydraulic pump has automatically shutdown due to an overheat. In addition, the vertical line, adjacent to the triangle, connecting the engine driven pump to the pressure indication  will no longer be displayed.

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Scene 83 Audio: B29S311 __________    Last Modified:7/17/2004

The status of the Ram Air Turbine is indicated by a triangle labeled RAT.  A white, hollow triangle with a white RAT label indicates that the Ram Air Turbine is stowed.

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Scene 84 Audio: B29S312 __________    Last Modified:7/24/2004

A solid, green triangle and a white RAT label indicates that the RAT is not stowed.

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Scene 85 Audio: B29S313 __________    Last Modified:7/24/2004

A solid amber triangle and amber RAT label indicate that the RAT is not available.

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Scene 86 Audio: B29S336 __________    Last Modified:7/24/2004

The E/WD displays a green RAT OUT message when the RAT is not fully stowed when the aircraft is in flight.

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Scene 87 Audio: B29S360 __________    Last Modified:7/24/2004

An amber RAT OUT message is displayed in the E/WD when the RAT is not fully stowed when the aircraft is on the ground, prior to takeoff power application.

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Scene 88 Audio: B29S362 __________    Last Modified:7/24/2004

The line labeled PTU represents the status of the PTU.  This indication is located between the GREEN and YELLOW systems.

Green arrows pointing away from a white PTU label indicate that the PTU pushbutton is in the AUTO, or armed position, but the PTU is not supplying pressure to either system.  This would be the normal indication when both engines are running.

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Scene 89 Audio: B29S363 __________    Last Modified:7/24/2004

The line and arrows are displayed in amber when the PTU pushbutton is in the OFF position.

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Scene 90 Audio: B29S364 __________    Last Modified:7/24/2004

Green arrows, a green line, and a green PTU label indicate that the PTU is operating.  The arrows point to the hydraulic system being pressurized by the PTU.  In this example, the GREEN system is using the PTU to pressurize the YELLOW system.

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Scene 91 Audio: B29S365 __________    Last Modified:7/24/2004

The E/WD displays a green HYDraulic PTU message when the PTU is running.

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Scene 92 Audio: B29S315 __________    Last Modified:7/24/2004

The pressure within each hydraulic system is displayed at the top of the hydraulic page.  The numerical indication is displayed in green if the associated system pressure is normal.  The indication is displayed in amber if the pressure is below a certain value.

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Scene 93 Audio: B29S316 __________    Last Modified:7/24/2004

The system label – green, blue, or yellow, is displayed in white, and the associated distribution triangle is displayed in green if the associated hydraulic system pressure is normal.  Both the label and the distribution triangle turn amber if the associated hydraulic system pressure decreases below a certain value.

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Scene 94 Audio: B29S317 __________    Last Modified:7/17/2004

There is an exception to this logic.  When the yellow hydraulic electric pump is operating for cargo door operation, the numerical system pressure is displayed in green.  However, the yellow label, and the associated distribution triangle, will be displayed in amber to indicate that only a portion of the yellow system is powered.

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Scene 95 Audio: B29S335 __________    Last Modified:7/21/2004

The E/WD displays an amber SYStem LOw PRessure message in the event the system pressure in a particular system is low.  The message identifies the affected hydraulic system.

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Scene 96 Audio: B29S338 __________    Last Modified:7/21/2004

In the event of there is a low pressure in two hydraulic system, the E/WD will display a red SYStem LOw PRessure message.  The message will identify the affected hydraulic systems.  The Master warning lights flash in the event this message is displayed.

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Scene 97 Audio: B29S320 __________    Last Modified:7/17/2004

The controls for the hydraulic system are located on the Hydraulic control panel, on the cockpit overhead panel.

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Scene 98 Audio: B29S321 __________    Last Modified:7/24/2004

The engine driven hydraulic pumps are controlled by the ENGine 1, or 2, pushbutton for the respective hydraulic system.  In the ON position, the respective pump is operating when the associated engine is running.

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Scene 99 Audio: B29S322 __________    Last Modified:7/24/2004

Selecting the OFF position will cause the associated pump to depressurize.  No hydraulic pressure will be produced, even though the pump continues to turn.  The OFF light illuminates in the pushbutton to indicate that it has been selected OFF.

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Scene 100 Audio: B29S323 __________    Last Modified:7/24/2004

The FAULT light illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats.
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low while the aircraft is on the ground and the associated engine is running, or anytime while in flight.  The fault light is inhibited when the aircraft is on the ground and the associated engine is not running.

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Scene 101 Audio: B29S324 __________    Last Modified:7/17/2004

The FAULT light extinguishes when the associated pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 102 Audio: B29S325 __________    Last Modified:7/24/2004

The BLUE electric hydraulic pump is controlled by the guarded electric pump pushbutton, also located on the hydraulic control panel.  This pushbutton is normally in the AUTO, or lights out position.

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Scene 103 Audio: B29S326 __________    Last Modified:7/24/2004

In the AUTO position, the BLUE electric hydraulic pump is always energized while the aircraft is in flight, provided AC power is available.  The pump will start to run on the ground when at least one engine is operating, provided AC power is available.

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Scene 104 Audio: B29S329 __________    Last Modified:7/24/2004

The FAULT light in the BLUE electric pump pushbutton illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats
     *  The associated electric hydraulic pump overheats
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low when an engine is running on the ground, or anytime in flight.  The fault light is inhibited when the aircraft is on the ground and the associated engine is not running.

The E/WD displays a HYDraulic ELECtric PUMP FAULT message.

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Scene 105 Audio: B29S330 __________    Last Modified:7/17/2004

The FAULT light extinguishes when the associated OFF pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 106 Audio: B29S378 __________    Last Modified:7/24/2004

A guarded BLUE PUMP OVeRiDe pushbutton, located on the overhead maintenance panel, provides a way to operate the BLUE system electric pump when the engines are not running.

In the normal, lights out position, the BLUE electric pump will operate when an engine is running.

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Scene 107 Audio: B29S379 __________    Last Modified:7/24/2004

Lifting the guard, and selecting the ON position will energize the BLUE electric hydraulic pump, even if none of the engines is running.

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Scene 108 Audio: B29S366 __________    Last Modified:7/24/2004

The YELLOW electric hydraulic pump is controlled by the electric pump pushbutton, also located on the hydraulic control panel.  This pushbutton is normally in the OFF, or lights out position.

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Scene 109 Audio: B29S367 __________    Last Modified:7/24/2004

In the OFF position, the YELLOW electric hydraulic pump will be automatically energized when the cargo door manual selector valve is moved.  The PTU and flight controls will be inhibited in this situation.

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Scene 110 Audio: B29S368 __________    Last Modified:7/24/2004

In the ON position, the YELLOW electric hydraulic pump is energized, and the flight controls and flaps will be pressurized, even if the engines are not running.  They will be pressurized by the YELLOW and GREEN systems, via the PTU.

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Scene 111 Audio: B29S369 __________    Last Modified:7/24/2004

The FAULT light in the YELLOW electric pump pushbutton illuminates amber for one of the following conditions:

     *  Low fluid level in the associated reservoir.
     *  The associated reservoir overheats
     *  The associated electric hydraulic pump overheats
     *  The associated reservoir head pressure is low

and

     *  The associated pump pressure is low.

The E/WD displays a HYDraulic ELECtric PUMP FAULT message.

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Scene 112 Audio: B29S370 __________    Last Modified:7/24/2004

The FAULT light extinguishes when the associated OFF pushbutton is selected to the off position.  However, if the fault is due to a reservoir overheat, the FAULT light will remain illuminated as long as the reservoir overheat condition exists.

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Scene 113 Audio: B29S332 __________    Last Modified:7/24/2004

The red guarded RAT ON pusbutton is used to manually deploy the RAT.  The RAT is stowed when the pushbutton is in the guarded position.  Lifting the guard, and pressing the RAT MAN ON pushbutton deploys the RAT.

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Scene 114 Audio: B29S371 __________    Last Modified:7/24/2004

The RAT will automatically deploy while in flight when AC bus 1 and 2 are not powered.  In this case, the emergency generator will be operating.

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Scene 115 Audio: B29S372 __________    Last Modified:7/24/2004

The PTU is controlled by the PTU pushbutton, on the overhead hydraulic control panel.  This pushbutton is normally in the AUTO, or lights out, position. This will cause the PTU to automatically operate when there is a certain pressure differential between the GREEN and YELLOW systems.

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Scene 116 Audio: B29S373 __________    Last Modified:7/24/2004

The PTU will not automatically operate for the following conditions:

     *  The cargo doors are being operated.  

     *  During the first engine start, and when only one engine is operating while the aircraft is on the ground.

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Scene 117 Audio: B29S374 __________    Last Modified:7/24/2004

The engine inhibition is based on the following conditions:

     *  One engine is running, and the other engine master switch is OFF
     *  The parking brake is set and, or
     *  The tow bar is attached.

After the second engine master switch is placed to ON, the PTU performs a self-test, and it will automatically enter the AUTO mode following a successful test, provided the PTU pushbutton is in the AUTO position.

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Scene 118 Audio: B29S377 __________    Last Modified:7/24/2004

The ECAM will not inform the crew in the event the PTU fails the self-test.  The crew will become aware of the problem only if there is a subsequent GREEN or YELLOW hydraulic pump failure.  The indication on the ECAM Hydraulic page is that the PTU is not operating as expected.

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Scene 119 Audio: B29S375 __________    Last Modified:7/24/2004

Placing the PTU pushbutton to the OFF position will deactivate the PTU.

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Scene 120 Audio: B29S376 __________    Last Modified:7/24/2004

The FAULT light illuminates in the PTU pushbutton for one of the following conditions:

     *  GREEN or YELLOW system low reservoir level
     *  GREEN or YELLOW reservoir overheat
     *  GREEN or YELLOW reservoir low head pressure

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                                                       END OF STORY BOARD

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