WorksheetsATA 29
Total questions: 47
Worksheet time: 24mins
Constant Speed Motor/Generator(CSM/G) is supplied by:
Green hydraulic system
Blue hydraulic system
Yellow hydraulic system
In Flight, if the Blue electric pump fails the Blue system:
Is lost
Can be recovered by the PTU
Can be recovered by Deploying the RAT
The priority valves in the aircraft hydraulic systems:
To isolate the hydraulically heavy load users in order to maintain normal supply to essential users
To isolate the hydraulically heavy load users in order to maintain normal supply to the primary and secondary flight controls in case of hydraulic pressure decrease
To isolate the hydraulically heavy load users in order to maintain normal supply to the landing gear extension system and A/C nose wheel steering
The Engines are operating, what happens when engine hydraulic pushbuttons are released OUT:
A. The “OFF” indication comes on, the pump stops working
A. The “OFF” indication comes on, the pump stops working, the systems are no longer supplied
A. The pump is depressurized, the system is no longer supplied, but lubrication and cooling of the pump are maintained
In Flight, under normal OPERATING condition, the PTU is:
A. In stand-by MODE
A. Working continuously
A. Working continuously and there is on transfer of hydraulic fluid from one system to the other
A/C in “Cold” configuration (electrically NOT supplied) P/B marked RAT MAN ON in the hydraulic panel pressed
RAT is not deployed, because A/C is not supplied
RAT is deployed
RAT is deployed only if batteries are ON
If no electrical power supply is available, the reservoir quantity can be checked
Never
By the gauge on the ground service panel of the yellow system
By the direct reading gauge on the reservoir
In normal condition, all the reservoirs are pressurized from:
Engine #1 or the bleed air system
Engine#2 or the bleed air system
The bleed air system
Reservoir overfilling occurs, hydraulic fluid is drained:
Directly out of A/C
Into collector tanks
Into the engine drain system
The Green hydraulic system is supplied by:
Enigine driven pump(edp) and an electric pum
An electric pump, RAT and the PTU
An EDP and the PTU ONLY
.On the Yellow system the normal source of pressure is:
Power Transfer Unit (PTU)
Engine Driven Pump (EDP)
Electrical-Pump
On the Yellow system, the electrical pump
Operates automatically when one engine is operating
Operates automatically when A/C is in flight configuration
Manually controlled or automatically operates
What is the purpose of the depressurization valve in the service panel:
Individual reservoir depressurization
Individual hydraulic system depressurization
Depressurization of all reservoirs at the same time
Constant speed motor/generator is supplied by:
Green hydraulic system
Blue hydraulic system
Yellow hydraulic system
In Flight, if the Blue electric pump fails the blue system:
Is lost
Can be recovered by the PTU
Can be recovered by DEPLOYING the RAT
A hydraulic accumulator is charged with initial air pressure of 1000 PSI. When the hydraulic system pressure of 3000 PSI is reached, the air pressure is.
4000 PSI
3000 PSI
1000 PSI
In Flight, under normal condition, the PTU is:
In stand-by
Working continuously
Working continuously and there is no transfer of hydraulic fluid from one system to the other
A Bidirectional Power Transfer Unit (PTU) enables:
The Green hydraulic fluid to flow into the Yellow system
The Green and Yellow hydraulic fluid to power both systems
The Green system powered by the Yellow system or vice versa, without fluid transfer.
A Ram Air Turbine (RAT) is provided in
The Blue system for emergency use.
The Green system for emergency use.
The Yellow system for emergency use.
A Hand pump is provided in:
The Yellow system for Landing Gear Door manual operation.
The Yellow system for Cargo Door manual operation.
The Yellow system for PTU operation.
The Green reservoir is located in:
The Main Landing Gear(MLG) bay
The Nose Landing Gear(NLG)bay
The Green hydraulic compartment
All the reservoirs are filled from:
The Green ground service panel
Separated service panel
The tail section
A fire shut-off valve is positioned:
Downstream of the Engine Driven Pump
Upstream of the Engine Driven Pump
On the Engine Driven pump
With the BLUE ELEC PUMP pushbutton set to AUTO:
The electric pump operates at first engine star
The pump is de-energize
The pump operates in case of both EDP failure
A leak measurement valve is positioned in each circuit:
Upstream of the primary flight controls
Downstream of the primary flight controls
Downstream of the landing gear system.
On the Blue hydraulic system, the Constant Speed Motor/Generator (CSM/G) is used
To provide A/C electrical power in case of emergency
To provide hydraulic power in case of emergency
To provide A/C electrical power and Blue hydraulic power in Emergency
.A/C in “cold” configuration (electrically NOT supplied: no APU, no GPU, battery P/Bs OFF)
Reservoirs cannot be filled and reservoir quantity cannot be checked
Reservoirs can be filled but reservoir quantity cannot be checked
Reservoirs can be filled and reservoir quantity can be checked
Where can you check the hydraulic quantity:On ECAM and Green service panel.
On ECAM and Green service panel.
On ECAM and reservoirs
On the ECAM SD HYD page or Hydraulic service Panel or Directly on the Resrviors
Hydraulic pressure can be restored by.
compressing the air charge in an accumulator
the use of a pressure/heat exchanger
compressing the fluid in a reservoir
What happens if a component has an internal hydraulic leak?
Fluid loss
Increase in fluid pressure
Increase in fluid temperature
.What happens to hydraulic fluid when it is overheated?
Increase acidity
Increase viscosity
Increase alkalinity
Accumulators as fitted to aircraft hydraulic systems
are only ever used in an emergency
store fluid under pressure
provide additional fluid if leaks occur
A normal hydraulic system will
show pressure and source of hydraulics
show fluid temperature and quantity
illuminate a light in the cockpit when the system is ready
Hydraulic systems normally operate at.
1800 PSI
3000 PSI
300 PSI
When replenishing a hydraulic system
use any hydraulic fluid
use any hydraulic fluid made by the same manufacturer.
use the same/correct hydraulic fluid
A check flow valve in a hydraulic system prevents
pump cavitation
reverse flow
overpressure
If an accumulator loses air pressure there will be
rapid depressurisation of system
pump cavitation
rapid fluctuations of instruments
"One reason for fitting an accumulator in an hydraulic system is to"
minimize the possibility of pump cavitation.
absorb pressure surges
relieve excess pressure
A component in a hydraulic system which ensures instantaneous action when a service is selected is
accumulator
engine driven pump
selector
The purpose of a mechanical sequence valve is to ensure the operation of
safety switches
landing gear and door
brake anti-skid units
The purpose of a non-return valve is to.
direct fluid to the hydraulic actuator
restrict the movement of components.
isolate one component from another
During a leak test of an hydraulic system, system pressure
is not important
must be minimum working
must be at maximum
Hydraulic reservoirs are pressurized to
provide a reserve of stored energy
maintain a constant fluid level
minimize the possibility of pump cavitation
In aircraft hydraulic systems, it is permissible to use
only the specified fluid
any fluid of the same specific gravity
any hydraulic fluid available
A RAT hydraulic pump is for
landing gear and auto-brake systems
nose wheel steering
flying controls if hydraulic power lost
Hydraulic hand-pump fluid supply is taken from
a tap into a convenient return line
a stack pipe higher than the normal level
the bottom of the reservoir
The force exerted by a hydraulic cylinder is equal to
area * volume
area * pressure
pressure * stroke
