Power Plant Flashcards
LP compressor has 1 stage and LP turbine
Has 4 stages
N3 pertains to
High Speed rotor
Annular combustion chamber is fitter with
2 igniters and 24 fuel nozzles
FADEC is also known as
EEC Electronic Engine Control
FADEC powered from electrical system when
N3 below 8% and self powered by magnetic alternator above that level.
Data transmitted from the Engine Interface Unit EIU to the FADEC is used for
engine management throughout the flight regime.
Taxi – below 80 kt – to prevent
Fan instability, FADEC avoids stabilized engine operation from 1.16 to 1.28 EPR
FADEC system has a redundancy of
2 channels
Engine Interface Unit transmits data to FADEC
To prevent fan instability, FADEC keep-out zone logic avoids
Stabilized engine operation from 1.16.
to 1.28 EPR on the ground and below 80 kt
In the automatic mode the Flight Management Guidance System computes
the thrust.
Setting engine thrust is accomplished via
Control of Engine Pressure Ratio EPR
FADEC computes and displays the
Thrust Rating Limit and EPR for a given thrust lever angle based on the thrust lever position
EPR mode is the normal mode to
Control the thrust
FADEC computes the command EPR as a function of:
Altitude, Mach number, Thrust Lever Angle
During reverse operation, thrust is controlled as a function of
N1
Engines are in the manual mode when
Autothrottle is not armed and inactive
From IDLE to TOGA, each thrust lever position
corresponds to EPR
LVR CLB flashes white on FMA if
Levers not in Climb when aircraft above thrust reduction altitude
Engine at idle – FADEC –
Modulated/Approach/Reverse Idle
Modulated idle
Ground, no Reverse / flight flaps retracted and gear up
Flaps 2 or gear down (type of idle)
Approach idle to accelerate rapid to GO AROUND if required
Reverse on ground – (type of idle)
Idle slightly higher than forward Idle Thrust
TCC improves engine performance by controlling the Intermediate Stability is provided by
2 air bleed systems
Fuel in the tank is fed to each engine via
Main Engine Pump, Fuel / oil heat exchanger, Fuel Metering Unit FMU and Fuel nozzles
Overspeed protection is accomplished by closing the
HP shutoff valve
Doors on engine 1 and 2 are actuated by
The blue and yellow hydraulic systems, respectively
Hydraulic isolation valve is controlled by
FADEC
FADEC will automatically command the engine to idle and the blocker door to stow if at least one door is unstowed by more than
5% and reverse thrust is not selected while engine running
FADEC commands full reverse thrust when blocker doors are more than
90% deployed
Hot start =
EGT overlimit
Hung start=
Stall
Failure to light=
No light up
Locked N1 rotor =
Low N1
Automatic start abort is inhibited on ground when
N3 goes above 50%
FADEC controls ignition and starting system according to position of
ENG START SEL, ENG MASTER sw, ENG MAN START pb, ENG ANTI ICE pb
All functions except _____________ remain available if the signal from EIU is lost
manual start and wet crank
A start valve and ____________comprise the Engine Starting System
an air turbine starter
In case of N1 rotor locked, how many more automatic start attempts after cracking does FADEC initiate?
0
In terms of N3, the start valve closure valve is above
50%
With ENG START SEL in CRANK position and MAN START pb selected ON,
Start valve opens
With ENG START SEL set to NORM and ENG ANTI ICE ON,
Continuous ignition via FADEC channels A and B is also automatically selected
With ENG START SELE set to NORM, in the event of an engine flame-out detected by FADEC
Continuous ignition is automatically activated for 10 seconds
With ENG START SEL in IGN START position,
During an automatic start, ignition occurs on ground when N3 is at least 25%
With ENG MASTER sw OFF, a signal is sent to
HP an LP fuel valves to close, which resets both FADEC channels
With ENG FADEC GND PWR pb is selected ON, FADEC receives power from the aircraft network for five minutes except if the
ENG FIRE pb is out or the FADEC generator is available.
The upper ECAM screen displays the primary parameters and the lower ECAM screen displays the secondary parameters when selected
manually or automatically
The engine Primary parameters can be displayed on each Navigation Display using the selector on the EFIS Control Panel if
a Display Management Computer ECAM channel failure occurs.
EPR commanded by FADEC is displayed via a green needle and a green triangle next to the needle indicates the direction of EPR tendency. The symbols are shown when
the Autothrust is active.
Transient EPR is the difference between Actual EPR and EPR command. It is shown only when
the autothrust is active
EPR MAX is a line displayed in
solid amber
When the reverse thrust blocker doors are fully deployed and reverse thrust mode is selected,
the thrust reverse indication changes to green and is over-illuminated.
When at or above idle, to indicate a successful engine relight in flight the
AVAIL indication pulses in green
EGT indication becomes solid red if the EGT exceeds
920ºC or 900º C for 20 seconds
EGT MAX is not available when Takeoff Thrust is applied,
A FLOOR is active, Reverse Thrust is selected
Above 100%, N3 indication becomes solid red and a
solid red cross appears next to it.
If N2 exceeds 103,3% the indication becomes
Red and a red cross appears beside it, which disappears after a new start on the ground
Oil quantity is shown in quarts. The numbers and needles are normally green. If the oil quantity drops below
4 quarts, numbers pulse.
If vibration of N1 is greater than 3.3 units, N2 more than 2.6 units, or N3 in excess of 4 units,
the indication pulses
FADEC detects
Hot, hung, no light up, surge, locked N1 rotor, FAULT ECAM starts
After second engine started, ECAM ENGINE page is replaced by WHEEL page
15 seconds after start, if ENG START sw is not returned to NORM
Rotating ENG START SEL to the ignition (IGN) position causes the pack valves to
Close and the ECAM ENGINE page to appear
If after START sel is moved to the ignition IGN position the ENG MASTER sw is not moved to ON within
30 seconds, the pack valves reopen
If START sel is not rotated back to NORM, the ECAM WHEEL page automatically
Replaces the ENG page 15 seconds after starting ENG 2
Before raising the guard on any guarded switch or control, what is required?
Confirmation with the other crew member that the current switch or control is selected
ECAM procedures require that any Master warning or master caution is
Cancelled first, then the title of the abnormal is read out to the Pilot Flying
If an engine is damaged the N2 or N3 rotors may be seized or a red spike marker on the EGT gauge may show an exceedance; After confirmation with PF, the Inner tank split switches are turned off for a short period; after confirmation with PF, the
FIRE pb is pushed and after 10 seconds the FIRE pb is pushed, if the indication of fire is still on, the Agent 1 DISCH pb is pushed
If FADEC fails , what references are there for normal engine operation?
Other indications such as hydraulic, electrical, AC or bleed pages must be used to confirm engine status
If a reverser unlocks in flight, what is the first crew action?
Cancel the master caution and read the ECAM actions on the ECAM memo page to the PF
