• VFR Day
• VFR Night
• IFR
• Reduced Vertical Separation Minimum (RVSM)

1. Autopilot
2. Altitude Alerting System
3. Altitude Reporting - Transponder 1
4. Air Data Systems - ADC 1 and ADC 2

1. Pilot occupies left seat
2. Autopilot is operative
3. Use of Headset mounted microphone
4. Ident button on sidestick works
5. QRH is available to pilot

1. Maximum Certified Takeoff Weight
2. Maximum Weight Permitted by Climb
3. Takeoff Distance

1. Maximum Certified Landing Weight
2. Landing Distance

1. Jet A / A1
2. JP-8

1. AFM Section 2 - Limitations
2. AFM section 8 - Handling Service and Maintenance

160 KEAS and below

20,000 ft max

Start Battery

Increasing N2 speed between 52%-54% will ensure 30 minutes of battery power

When must the engine anti-ice system be turned on?

At all times when the outside air temperature is 10°C, or below, and there is visible moisture present.

Wing Ice switches must be ____ at temperatures below ____ .

OFF

-40 degrees

• Pneumatic de-ice boots on the leading edges of the wings and horizontal stabilizer
• Left and right heated windshields
• Heated pitot/AOA probes
• Heated pitot/static probe
• Heated static ports
• Engine anti-ice

Bleed air comes from the P3 port on the engine to the Pressure Regulating Shut-off Valves (PRSOV), then directed into a perforated tube inside each engine cowl.  The air is then exhausted overboard.

What are the meanings of the following depictions for windshield heat: green outline, white outline, yellow outline, white temperature, red temperature?

• Green outline -- Windshield heat on
• White outline -- Windshield heat off
• Yellow outline -- Windshield overheat or failure
• White temperature -- Normal temperature range
• Red temperature -- Overheat (with red OCHT)

On the main landing gear, what positions do the proximity switches detect and report?

• Down and locked
• Up and stowed
• Weight on wheels (WOW)

On the nose gear, what positions do the proximity switches detect and report?

• Down and locked
• Up and stowed

There are mechanical brakes that hold the landing gear in the extended position, with the aid of over-center braces.

The landing gear warning horn sounds when under 12,500 feet MSL if any gear is not down and locked under the following conditions:

• Flaps extended beyond the take-off (TO) position
• Airspeed less than 120 knots with one or both throttle below mid-range (30° TLA)
• Airspeed less than 140 knots with one or both throttle below mid-range (30° TLA)

Note: the warning horn cannot be silenced under condition 1 and 2

How is an emergency landing gear extension accomplished?

Emergency extension of the landing gear is accomplished by pulling the emergency landing gear extension handle which mechanically releases the actuator brakes.  The landing gear free falls with the aid of wind stream and gravity.  When emergency extension handle is pulled, the ACS automatically pulls the three landing gear actuator ECBs and reports if the handle remain unsecured.

• Extension -- 10 seconds
• Retraction -- 7 seconds

• Main gear -- 103 +/- 2 psi
• Nose gear -- 85 +/- 2 PSI

What indicates that the brake pads are worn and in need of replacement?

Two brake pad indicators are located on the inside of each wheel assembly.  With the brakes set, if the indicator pin is flush with the hex nut of the retainer housing, the brake pads need replacement.

There are mechanical brakes on the landing gear actuator motors

What type of actuators are used for the landing gear extension and retraction?

How many degrees of steering do the rudder pedals provide?

Rudder pedals provide 15° of steering.  Steering beyond 15° degrees disengages the centering cam and steering is accomplish with differential braking.

What are the landing gear position indications on the MFD?

• Down and locked -- three green circles with a white border
• In transit -- an amber-hatched square
• Up and stowed -- hollow white square, after 10 seconds the squares and GEAR label disappear

What sidestick switch controls are routed through the center switch panel to the ACSs?

• ALL INTERPT switch
• Autopilot disconnect
• Transponder IDENT
• Pitch and roll trim
• Landing gear warning mute

How are throttle control inputs sent to the engines?

The throttle have no direct connection to the ACS.  Information sensed by two position sensors for each throttle is sent directly to the FADEC units.

What is the purpose on the USB port under the pilot's left armrest?

The USB port under the pilot's left armrest allows for uploading of important software and database updates (example: GPS nav data).

How are the flap actuators commanded?

The left flap actuators receive their commands and report their status to the right ACS, and the right flap actuators receive their commands and report their status to the left ACS.  All actuators communicate with each other to assure flap position agreement.

The emergency/essential systems are designed to operate autonomously, and do not require Avio.  What are they?

• Battery power and electrical contactor control
• Electrical circuit protection
• Oxygen and passenger masks
• Emergency landing gear extension
• Cabin pressurization dump
• Emergency locator beacon (ELT)

The Avio Processing Center (APC) is a Line Replaceable Unit (LRU) that consists of what components?

There are two APCs in the aircraft.  Each APC consists of one ACS and one FADEC.

What is the purpose of the USB port under the copilot's right armrest?

The USB port under the copilot's right armrest is for maintenance purposes only. (DSU Downloads)

Most aircraft systems have MFD synoptics that provide direct pilot control.  Which systems cannot be controlled through the MFD?

• Oxygen -- controlled on the left switch panel
• Landing Gear -- controlled through the center switch panel
• Autoflight -- controlled through the autopilot control panel

What is the one hydraulic system installed in the aircraft?

How many trim control motors are on the aircraft, and what are their functions?

There are (4) trim motors on the aircraft:

• (2) Pitch trim
• (1) Roll trim
• (1) Yaw trim

How many flap positions are on the flap selector?

• Up (0°)
• Takeoff (TO - 17°)
• Landing (LDG - 34°)

What is an alternate method of adjusting the trim besides adjusting it from the hat switch on the sidestick?

The trim can also be adjusted from the flight controls synoptic (FLCS) page.  The flight controls synoptic page can be accessed by pressing the ALL INTERRUPT button for two seconds, or more.

When does the FLAP FAIL caution message get displayed?

What functions are disconnected when you press the ALL INTERRUPT button on the side-stick

• Autopilot
• Autothrottle
• Flight director
• Yaw damper
• Overspeed / underspeed protection
• Stick pusher (while the button is depressed)
• All trim motors (while the button is depressed)

Pressing and holding the ALL INTERRUPT button for two seconds prompts the FLCS synoptic page to be displayed on the MFD.

What sidestick switch controls are not routed through the center switch panel to the ACS?

The push-to-talk switch on the left sidestick is routed directly to the left PFD, and the push-to-talk switch on the right sidestick is routed directly to the right PFD.

Which ACS has primary control over the landing gear actuators?

Both ACSs control the landing gear actuators.  The landing gear actuators are controlled by the on-side ACS (left actuators by the left ACS, right actuators by the right ACS).

What is the meaning of the CAS warning message: "L Fuel Qty Low" or "R Fuel Qty Low"?

The fuel sump tank quantity is less than 105 pounds.

What is the meaning of the CAS advisory message: "Avionics Databus Fail"?

What is the meaning of the CAS caution message: "Hot Fuel"?

The fuel temperature in either wing is between 65°C and 76°C.

What is the meaning of the CAS advisory message: "L Fuel Filter" or "R Fuel Filter"?

What is the meaning of the CAS caution message: "Landing Gear Fail"?

The engine is running and the generator switch is set to AUTO but no current is flowing, or the generator switch is set to OFF.

What is the meaning of the CAS status message: "T/O Config OK"?

The aircraft has been properly configured for takeoff:

• Aileron, elevator, and rudder trims have been set within the takeoff limits
• Flaps are set to the UP or T/O position
• Parking brake has been release
• Door is closed and locked
• Both engines are running

The fuel sump tank quantity is less than 105 pounds.

The engine oil temperature is below 20°C and the throttles are advanced to high power.

The OAT has not been entered into the OPs page and the throttles are advanced for takeoff.

The fuel imbalance is greater than 65 pounds.

The cabin altitude environment has exceeded 8750 feet.

The cabin altitude environment has exceeded 10,000 feet.

The fuel temperature in either wing is between 65°C and 76°C.

Either fuel sump tank quantity is less than 140 pounds.

The engine is manually selected to motor without ignition or fuel.  This message is displayed on the ground only.

70 knots

180 knots

90 knots

8.7 psi

-0.5 PSI

8.33 psi

• Continuous, no time limit.
• Fuel temperature range from 18° C to 121° C.

Oil temperature range from 20° C to 135° C

• Continuous, no time limit.
• Fuel temperature range from 18° C to 121° C.

• Continuous, no time limit.
• Fuel temperature range from -40° C to 121° C.

• Engine starts are not permitted at an oil temperature below -20° C.
• Engine starts between -20° C and 5° C must be accomplished with a GPU supplying electrical power.
• Minimum battery voltage is 23 volts.

• 30 knot maximum crosswind limit
• 25 knot maximum tailwind limit
• 15 knot maximum tailwind limit for N1 > 75%

-40° C to 121° C

The maximum transient ITT is 850° C, for a maximum of 20 seconds over 795° C.

• 5 minute time limit.
• Fuel temperature range from 18° C to 121° C.

• Throttles
• Full Authority Digital Engine Control units (FADEC)
• Fuel Metering Units (FMU)

The Start battery is connected to the hot battery bus.

There are four equipment busses, left and right forward, and left and right aft, that supply power to the aircraft.   During normal operation, the ACS divides the busses into a left / right configuration, with the left forward and left aft busses receiving power from the left generator, and the right forward and right aft busses receiving power from the right generator.

-15° C

• External power is plugged in
• External power is of the correct polarity
• External power is between 24 VDC and 29 VDC

Note: Illumination of the external power light does not indicate that external power is being used.  Both battery switches must be in the ON position.

During normal operation, the start battery is connected to the right side of the electrical system through the start battery contactor.  The start battery is also connected to the hot battery bus, which supplies power for equipment that must be operated before either battery switch is turned on.

The start battery also supplies power for engine starting either by itself or in parallel with external power, if it is connected.  With one engine running, the start battery supplies power in parallel with the generator to start the second engine

• Single generator operation
• Battery only power
• External power

• Ground fault
• Over-voltage and under-voltage from the starter / generators
• Reverse current
• Overspeed
• Open ground

• Neither generator is online
• External power is of the correct polarity
• External voltage is between 24 VDC and 29 VDC
• Both battery switches are on

There are two 22 amp, 24 volt DC, sealed, maintenance-free lead acid batteries located in the nose compartment of the aircraft.

The Bus Tie Contactor (BTC) electrically ties together or isolates the left or right aft busses.  The BTC is controlled by the Bus Tie switch on the left switch panel.  During normal operation with the BTC is the Auto position, the ACS controls the position of the BTC; however, it can be manually opened by placing the Bus Tie switch in the Open position.

• Green at voltages above 20 volts
• White at voltages less than 20 volts

• Auto/On - normal state, white outline with a green interior
• Auto/Off - ECB turned off by the ACS, white outline with a gray interior
• Tripped - ECB off due to a circuit fault, amber
• Pulled - ECB opened by the pilot, gray
• Collared - ECB locked out by maintenance technician, white outline with cyan interior

The air conditioning system is the only system load shed.

• System battery
• Left battery bus
• Right battery bus
• Start battery contactor
• Bus Tie contactor
• Left generator contactor
• Right generator contactor
• External power contactor
• Left forward circuit breaker / contactor
• Right forward circuit breaker / contactor

Entry, overhead, and baggage compartment lights are powered directly from the hot battery bus allowing them to be turned on without powering the avionics.  These lights are on a timer to avoid depleting the batteries.

• External voltage is greater than 29 VDC at any time
• Aircraft current draw is greater than 400 amps
• External power current draw from the aircraft is greater than 5 amps
• External power voltage is less than 24 VDC for more than 45 seconds
• External power voltage is less than 10 VDC at any time
• When generator power is available (online) after engine start