Book 3 - FADEC Flashcards
FADEC performs functions necessary to control the engine during:
- _____ up
- acceleration
- ____-off
- climb
- normal cruise
FADEC performs functions necessary to control the engine during:
- START up
- acceleration
- TAKE-off
- climb
- normal cruise
fuel flow is controlled by the FADEC to achieve the required _____ (as determined by the throttle settings) by monitoring and controlling either:
- engine ________ ratio (EPR) orr
- N1 ___ pressure compressor or fan speed
fuel flow is controlled by the FADEC to achieve the required THRUST (as determined by the throttle settings) by monitoring and controlling either:
- engine PRESSURE ratio (EPR) orr
- N1 LOW pressure compressor or fan speed
the FADEC system is fully ________ and hence is failure tolerant
the FADEC system is fully REDUNDANT and hence is failure tolerant
as well as fuel control, FADEC will manage ___ flow control systems such as VSV’s and _____ valves
as well as fuel control, FADEC will manage AIR flow control systems such as VSV’s and BLEED valves
FADEC has complete ______ loop control, achieved by feeding parameters back to the computer
FADEC has complete CLOSED loop control, achieved by feeding parameters back to the computer
FADEC reduces ____ workload, achieves ________ operation for efficiency ad economy and prevents ____ speed and temp condition
FADEC reduces CREW workload, achieves OPTIMUM operation for efficiency ad economy and prevents OVER speed and temp condition
engine parameters from the FADEC will be projected in the ______ on visual display units
engine parameters from the FADEC will be projected in the COCKPIT on visual display units
each engine has two FADECs, designated _ and _. all signals between the FADEC’S and the aeroplane are completely ________. FADEC’s are interconnected by a _____ ______ ____ ____ (CCDL) to share engine data and FADEC status
each engine has two FADECs, designated A and B. all signals between the FADEC’S and the aeroplane are completely REDUNDANT. FADEC’s are interconnected by a CROSS CHANNEL DATA LINK (CCDL) to share engine data and FADEC status
one FADEC is automatically in ________ mode. whilst in standby mode, a FADEC will still monitor all inputs and perform all computations, however the outputs are de-__________. the active FADEC has complete control over the engine
one FADEC is automatically in STANDBY mode. whilst in standby mode, a FADEC will still monitor all inputs and perform all computations, however the outputs are de-ENERGISED. the active FADEC has complete control over the engine
FADEC is powered both by __VDC from the essential bus and from a PMA (_________ ______ _________)
FADEC is powered both by 28VDC from the essential bus and from a PMA (PERMANENT MAGNET ALTERNATOR)
cockpit discretes inputs into FADEC:
- thrust ratings
- engine start/stop
- ignition on/off
- anti-ice on/off
- FADEC reset
- alternate FADEC select
cockpit discretes fed into FADEC:
- thrust ratings
- engine start/stop
- ignition on/off
- anti-ice on/off
- FADEC reset
- alternate FADEC select
aircraft discretes inputs into FADEC:
- WOW
- landing gear down
- thrust reverser deployed
- thrust reverse stowed
aircraft discretes FED into FADEC:
- WOW
- landing gear down
- thrust reverser deployed
- thrust reverse stowed
all discrete inputs to FADEC have a __kOhm resister across the contacts and are supplied with a current limited _________ voltage allowing FADEC to detect ope and short circuit failure conditions in engine wiring
all discrete inputs to FADEC have a 10kOhm resister across the contacts and are supplied with a current limited EXCITATION voltage allowing FADEC to detect ope and short circuit failure conditions in engine wiring
each FADEC engine control system includes four harnesses, two designated ________, clamped to the right and left side of the HP _________ and two designated _________, routed right and left of the engine. the harnesses are labelled A and B and are dedicated to the corresponding FADEC
each FADEC engine control system includes four harnesses, two designated INTERNAL, clamped to the right and left side of the HP COMPRESSOR and two designated EXTERNAL, routed right and left of the engine. the harnesses are labelled A and B and are dedicated to the corresponding FADEC
during engine starts, the FADEC is fed from the 28VDC _________ bus. above __% N2, the PMA automatically takes over
during engine starts, the FADEC is fed from the 28VDC ESSENTIAL bus. above 50% N2, the PMA automatically takes over
FADEC has a fuel flow limiting function which prevents the ITT from exceeding a maximum value of 1690F (___ celsius)
FADEC has a fuel flow limiting function which prevents the ITT from exceeding a maximum value of 1690F (921 celsius)
FADEC engine protection and shut down
should N1 exceed ___% (approx 9135 RPM) or N2 exceed 105.5% (approx 16750 RPM) the over speed logic _____ the engine down if both FADECs agree
engine shut down also occurs if N2 is less than __% (approx 8500 RPM)
FADEC engine protection and shut down
should N1 exceed 105% (approx 9135 RPM) or N2 exceed 105.5% (approx 16750 RPM) the over speed logic SHUTS the engine down if both FADECs agree
engine shut down also occurs if N2 is less than 54% (approx 8500 RPM)
each engine has a dual __________ ignition system comprising two ________, two HT leads and two igniters. each igniter is controlled by a separate FADEC
normally, exciters are only used for starting, however, further operation will be necessary for restart and continuous operation for _______ weather conditions
each engine has a dual REDUNDANT ignition system comprising two EXCITERS, two HT leads and two igniters. each igniter is controlled by a separate FADEC
normally, exciters are only used for starting, however, further operation will be necessary for restart and continuous operation for ADVERSE weather conditions
for ground starts, only ___ exciter is used, for in flight restarts, both ignition systems are energised
for ground starts, only ONE exciter is used, for in flight restarts, both ignition systems are energised
primary supply for the ignition system is a ______ phase winding in the PMA which provides 20-40VAC at all N2 speeds above __%
power is stored in a ________ and discharged at 4-7 times per _______
primary supply for the ignition system is a SINGLE phase winding in the PMA which provides 20-40VAC at all N2 speeds above 10%
power is stored in a CAPACITOR and discharged at 4-7 times per SECOND
the ignition switches on the power plant control panel can be set to one of three positions:
- ON - power removed from exciter relay and _________ ignition takes place
- AUTO - power removed from exciter relay for ________ only, re-energised once ignition taken place
- OFF - exciter relay energised so no ignition takes place
the ignition switches on the power plant control panel can be set to one of three positions:
- ON - power removed from exciter relay and CONTINUOUS ignition takes place
- AUTO - power removed from exciter relay for IGNITION only, re-energised once ignition taken place
- OFF - exciter relay energised so no ignition takes place
an engine start is __________ by momentarily holding the STOP-RUN-START switch to the ______ position
an engine start is INITIATED by momentarily holding the STOP-RUN-START switch to the START position
the four thrust rating modes, controlled by buttons on the overhead panel and control pedestal are:
- T/O - maximum ____ ___ (100% N1)
- CON - maximum _________ (86% N1)
- CLB - maximum _____ (76% N1)
- CRZ - maximum ______ (70% N1)
note: CON, CLB AND CRZ switch inputs are __________ on the ground
the four thrust rating modes, controlled by buttons on the overhead panel and control pedestal are:
- T/O - maximum TAKE OFF (100% N1)
- CON - maximum CONTINUOUS (86% N1)
- CLB - maximum CLIMB (76% N1)
- CRZ - maximum CRUISE (70% N1)
note: CON, CLB AND CRZ switch inputs are INHIBITED on the ground
FADEC take off data setting enables the pilot to input reference data into the FADEC prior to take off. used to calculate N_ target during take off
the REF TO TEMP setting is used by the FADEC in place of the TAT supplied by the ADC and ensures a corrected ___ speed consistent with thrust levels used by the pilot in loading the aircraft
FADEC take off data setting enables the pilot to input reference data into the FADEC prior to take off. used to calculate N1 target during take off
the REF TO TEMP setting is used by the FADEC in place of the TAT supplied by the ADC and ensures a corrected FAN speed consistent with thrust levels used by the pilot in loading the aircraft
the RESET button on the PCP clears recorded ______ unless the fault is currently being detected
ALTN button on the PCP switches active FADEC unless selected FADEC not _________. this overrides the automatic switching
the RESET button on the PCP clears recorded FAULTS unless the fault is currently being detected
ALTN button on the PCP switches active FADEC unless selected FADEC not CAPABLE. this overrides the automatic switching
the FADEC receives _______ or _________ thrust reverser information
FADEC enables reverse thrust depending on position of reverser ______ and position of ______ lever
engine ______ reduced to idle if there is inadvertent thrust reverser deployment
the FADEC receives STOWED or DEPLOYED thrust reverser information
FADEC enables reverse thrust depending on position of reverser DOORS and position of THRUST lever
engine THRUST reduced to idle if there is inadvertent thrust reverser deployment
at __% N2 in the engine start sequence, the LSOV START solenoid is energised and fuel pressure from the LSCV to the PRV, so opening the PRV and allowing fuel to be supplied from the MMV to the fuel nozzles
at 23% N2 in the engine start sequence, the LSOV START solenoid is energised and fuel pressure from the LSCV to the PRV, so opening the PRV and allowing fuel to be supplied from the MMV to the fuel nozzles
an air ____ valve automatically vents entrapped air or fuel vapour during engine starting and motoring
an air VENT valve automatically vents entrapped air or fuel vapour during engine starting and motoring
CVG (compressor variable __________) hydraulically actuated, controlled by ____ pressure from the fuel pump
feedback from the LVDT on the CVG actuator
CVG (compressor variable GEOMETRY) hydraulically actuated, controlled by FUEL pressure from the fuel pump
feedback from the LVDT on the CVG actuator
