When may a Thruflight Setup Check be performed in lieu of a full Setup Check? - Correct Answers When
on a subsequent flight, and ALL of the following apply:
1. Crew keeps same aircraft
2. Flight crewmembers remain the same, provided one flight crewmember remains on board
3. Aircraft remains energized
4. No maintenance action has been taken
When must a terminating Check be accomplished? - Correct Answers When the aircraft is to be
completely powered down or left unattended
What are the engine start abort criteria? - Correct Answers 1. No light-off within 10 seconds after the
first fuel flow indications (on ground only)
2. Fuel flow drops to zero PPH immediately after lightoff
3. ITT rises rapidly toward start limit (800 C, hot start)
4. ITT approaches start limit (800 C, hot start)
5. N2 remains steady or decreases for more than 5 seconds (hung start)
6. Any unusual noise or vibration occurs
7. Engine instruments indicate abnormal conditions
8. Visible burning coming from the exhaust pipe
,9. Oil pressure does not reach at least 34 psi (limit below 88% N2) after the engine reaches stabilized
idle
NOTE: The FADEC will not shut down the start sequence automatically for an over-temperature during
start.
What is the proper response to windshear on takeoff? - Correct Answers 1. APPLY maximum available
thrust
2. DISENGAGE the autopilot, press the TO/GA buttons to activate the windshear escape mode and
rotate smoothly at a normal rate to the command bar
3. ADJUST pitch attitude smoothly and in small increments to control vertical speed and altitude
4. MAINTAIN present configuration (gear and flaps) until terrain contact is no longer a factor
Where is the APU located? - Correct Answers In the tail cone of the aircraft, just aft of the titanium
firewall
How does the APU receive its fuel? - Correct Answers Normally, the APU receives fuel from tank #2.
However, if the opposite side electric pump on the fuel panel is turned ON, the APU can draw fuel from
tank #1 if the crossfeed switch is selected to the LOW 2 position.
What controls the starting and normal operation of the APU? - Correct Answers The APU operates
under the full authority of its own FADEC
What electrical buses can the APU energize as the sole source of elecrical power? - Correct Answers
FLIGHT:
All buses, minus the shed buses
GROUND:
,All buses, assuming shed bus switch is in OVRD
How is a fire detected by the APU? - Correct Answers By its own dedicated fire loop
How many fire bottles are dedicated to the baggage compartment and what are their release times? -
Correct Answers Two fire bottles:
1. High Rate Discharge Bottle - Designed to instantaneously fill the baggage compartment
2. Metering Discharge Bottle - Provides the required level of fire extinguishing agent concentration for at
least 50 minutes
How is a fire extinguished in the APU? - Correct Answers By its own dedicated extinguishing bottle
What are the minimum battery temperatures and voltages for APU start? - Correct Answers Minimum
Battery Temperature: -20 degrees
Minimum Battery Voltage: 22.5 volts
NOTE:
At 22.5 volts and higher, the APU may be started off the batteries alone.
Between 19 volts and 22.4 volts, the APU must be started off a ground power unit.
Lower than 19 volts, the battery must be removed from the airplane to be recharged.
If battery voltage is below 24V and battery temperature is colder than -15 degrees C, replace the
battery, as it may not recharge under very low temperatures.
What is the primary component of the avionics integration system? - Correct Answers Two IC-600
Symbol Generators (SGs) - The SG's interface with many of the aircraft systems; they receive data from
multiple inputs and send the appropriate information to the 5 screens in the cockpit.
, The #1 Data Acquisition Unit (DAU) provides data for which engine and airplane systems? DAU #2? -
Correct Answers DAU #1:
Forward airplane systems
#1 engine
DAU #2:
Aft airplane systems
#2 engine
Which unit can be used as a backup display to the main display panels? - Correct Answers Radio
Management Unit (RMU)
How many systems can be displayed on the MFD? - Correct Answers 5 available pages (only one
displayed at a time)
Fuel
Electrical
Environmental and Ice Protection
Hydraulic and Brakes
Takeoff (Doors)
What is the maximum number of EICAS messages that can be displayed at once? - Correct Answers 15
messages (without using the scroll bezel)
What is the takeoff and landing inhibition logic, and when does it become effective? - Correct Answers
Takeoff and landing inhibition logic is designed to prevent non-critical EICAS messages from populating
on the EICAS during critical phases of flight.
For TAKEOFF, the inhibition logic is valid when the airplane crossed V1 minus 15 knots. The inhibition
logic is deactivated when one of the following occurs:
on a subsequent flight, and ALL of the following apply:
1. Crew keeps same aircraft
2. Flight crewmembers remain the same, provided one flight crewmember remains on board
3. Aircraft remains energized
4. No maintenance action has been taken
When must a terminating Check be accomplished? - Correct Answers When the aircraft is to be
completely powered down or left unattended
What are the engine start abort criteria? - Correct Answers 1. No light-off within 10 seconds after the
first fuel flow indications (on ground only)
2. Fuel flow drops to zero PPH immediately after lightoff
3. ITT rises rapidly toward start limit (800 C, hot start)
4. ITT approaches start limit (800 C, hot start)
5. N2 remains steady or decreases for more than 5 seconds (hung start)
6. Any unusual noise or vibration occurs
7. Engine instruments indicate abnormal conditions
8. Visible burning coming from the exhaust pipe
,9. Oil pressure does not reach at least 34 psi (limit below 88% N2) after the engine reaches stabilized
idle
NOTE: The FADEC will not shut down the start sequence automatically for an over-temperature during
start.
What is the proper response to windshear on takeoff? - Correct Answers 1. APPLY maximum available
thrust
2. DISENGAGE the autopilot, press the TO/GA buttons to activate the windshear escape mode and
rotate smoothly at a normal rate to the command bar
3. ADJUST pitch attitude smoothly and in small increments to control vertical speed and altitude
4. MAINTAIN present configuration (gear and flaps) until terrain contact is no longer a factor
Where is the APU located? - Correct Answers In the tail cone of the aircraft, just aft of the titanium
firewall
How does the APU receive its fuel? - Correct Answers Normally, the APU receives fuel from tank #2.
However, if the opposite side electric pump on the fuel panel is turned ON, the APU can draw fuel from
tank #1 if the crossfeed switch is selected to the LOW 2 position.
What controls the starting and normal operation of the APU? - Correct Answers The APU operates
under the full authority of its own FADEC
What electrical buses can the APU energize as the sole source of elecrical power? - Correct Answers
FLIGHT:
All buses, minus the shed buses
GROUND:
,All buses, assuming shed bus switch is in OVRD
How is a fire detected by the APU? - Correct Answers By its own dedicated fire loop
How many fire bottles are dedicated to the baggage compartment and what are their release times? -
Correct Answers Two fire bottles:
1. High Rate Discharge Bottle - Designed to instantaneously fill the baggage compartment
2. Metering Discharge Bottle - Provides the required level of fire extinguishing agent concentration for at
least 50 minutes
How is a fire extinguished in the APU? - Correct Answers By its own dedicated extinguishing bottle
What are the minimum battery temperatures and voltages for APU start? - Correct Answers Minimum
Battery Temperature: -20 degrees
Minimum Battery Voltage: 22.5 volts
NOTE:
At 22.5 volts and higher, the APU may be started off the batteries alone.
Between 19 volts and 22.4 volts, the APU must be started off a ground power unit.
Lower than 19 volts, the battery must be removed from the airplane to be recharged.
If battery voltage is below 24V and battery temperature is colder than -15 degrees C, replace the
battery, as it may not recharge under very low temperatures.
What is the primary component of the avionics integration system? - Correct Answers Two IC-600
Symbol Generators (SGs) - The SG's interface with many of the aircraft systems; they receive data from
multiple inputs and send the appropriate information to the 5 screens in the cockpit.
, The #1 Data Acquisition Unit (DAU) provides data for which engine and airplane systems? DAU #2? -
Correct Answers DAU #1:
Forward airplane systems
#1 engine
DAU #2:
Aft airplane systems
#2 engine
Which unit can be used as a backup display to the main display panels? - Correct Answers Radio
Management Unit (RMU)
How many systems can be displayed on the MFD? - Correct Answers 5 available pages (only one
displayed at a time)
Fuel
Electrical
Environmental and Ice Protection
Hydraulic and Brakes
Takeoff (Doors)
What is the maximum number of EICAS messages that can be displayed at once? - Correct Answers 15
messages (without using the scroll bezel)
What is the takeoff and landing inhibition logic, and when does it become effective? - Correct Answers
Takeoff and landing inhibition logic is designed to prevent non-critical EICAS messages from populating
on the EICAS during critical phases of flight.
For TAKEOFF, the inhibition logic is valid when the airplane crossed V1 minus 15 knots. The inhibition
logic is deactivated when one of the following occurs:
