King Air 350 Theoretical Exam - Only exam - Qrosscheck Aviation E-Learning

What is the maximum certified altitude for the King Air 350?

29,000 FT
25,000 FT
31,000 FT
35,000 FT

What is the maximum certified (FAA) occupancy onboard, including crew?

9
11
17
12

What is the maximum landing weight?

11,500 lbs
15,500 lbs
15,000 lbs
12,500 lbs

You can use Aviation Gasoline but with some limitations, which one of the below is applicable?

Operation above FL310 is prohibited.
Operation is limited to 200 hrs
Operation with either standby pump inoperative is prohibited
Operation is limited to 100 hrs

What is the max indicated airspeed for flaps Approach?

157 KIAS
210 KIAS
202 KIAS
181 KIAS

What is the VMO/MMO?

263 KIAS / 0.58 Mach
282 KIAS / 0.65 Mach
250 KIAS / 0.49 Mach
260 KIAS / 0.56 Mach

Airspeed for One-Engine-Inoperative Best Rate of Climb? (VYSE)

153 KIAS
98 KIAS
125 KIAS
157 KIAS

Which engine is installed?

Pratt & Whitney PT6A-60A
Pratt & Whitney PT6A-42
Pratt & Whitney PT6A-61
Pratt & Whitney PT6A-62

What is the maximum fuel imbalance?

79 USG
1000 LBS
300 LBS
453 LBS

What is the minimum amount of fuel required for takeoff?

265 LBS
150 LBS
1000 LBS
325 LBS

What is the maximum ITT during engine start?

1000°C
750°C
1020°C
850°C

What is the minimum oil temperature for engine start?

0°C
-10°C
-50°C
-40°C

The engine is a free spooling turbine, what does that mean?

There is no physical linkage between the power turbine and the propeller shaft.
There is no physical linkage between the compressor and the power turbine which is connected to the propeller shaft.
There is a physical linkage between the compressor and the power turbine which is connected to the propeller shaft.
The power turbine can rotate backwards for reverse

A magnetic chip detector is installed, where is the detector located and how will a CAS be displayed?

Bottom of each reduction gearbox. As a yellow (amber) R Chip Detect (applicable side).
top of each reduction gearbox. As a yellow (amber) R Chip Detect (applicable side).
Bottom of each compressor turbine. As a red "R Chip Detect" (applicable side).
Inside of the power turbine. As a yellow (amber) R Chip Detect (applicable side).

When the auto-ignition is armed, when will the igniter activate?

If engine torque falls below 50%
If engine torque falls below 17%
If engine N1 falls below 52%
If engine ITT falls below 350°C

The fuel is sprayed into the combustion chamber, by how many fuel nozzles?

10
14
22
12

The power lever in the cockpit is linked to what?

The propeller pitch links
The governor in the FCU
The fuel flow valve
The engine parameter computer

What is correct regarding the fuel?

The fuel is pre-heated by the oil to fuel heater
The fuel is never pre-heated
The fuel is cooled by Ram air
The fuel is pre-heated by circulating inside the engine oil tank.

Upon engine shutdown, what happens with the fuel?

The FCU will close the fuel valve at the high pressure fuel pump
The flow divider will cut the fuel supply. Any eventual residual fuel in the fuel nozzles will be burnt on the next engine start
It will drain overboard from the combustion chamber, and the fuel nozzles by gravity.
The purge tank pressure will emtpy the fuel nozzles, a dump valve will then drain any residual fuel overboard, if not combusted in the combustion chamber.

In the event of an engine fire, what will be the indications?

MASTER WARNING + ENG FIRE F/W VALVE will illuminate
A Red warning "Engine Fire" will be illuminated over that side ITT
A bell will sound, a red message will be displayed on the PFD "FIRE"
A bell will sound, and an amber annunciator will illuminate on the dash board "FIRE"

What is true regarding the fire detection system?

It senses high excessive temperatures of the engine compartment
It senses fire by detecting smoke in the engine compartment.
It senses excessive temperatures of the engine compartment, and smoke detection in the cabin
It senses smoke by using optic sensors

How does the system protect the propeller from overspeed?

The overspeed governor dumps oil from the propeller to keep the RPM below 1768 RPM.
The primary governor dumps oil from the propeller to keep the RPM below 1780 RPM.
The fuel topping governor dumps oil from the propeller to keep the RPM below 2120 RPM.
By counter weights

If the AUTO FEATHER is armed, at approximately what N1 will the system be armed?

53%
100%
90%
85%

During the engine start, when will you move the condition lever to add fuel?

When selecting the engine start switch to Start
When the N1 is at 5% or more
They should be in low position before engine start
at 12% N1 or above

What is the limitation of the starter?

30 sec ON, 5 min OFF, 30 sec ON, 5 min OFF, 30 sec ON then 30 minutes OFF
60 sec ON, 40 sec OFF, 60 sec ON, 40 sec OFF, 60 sec ON then 30 minutes OFF
40 sec ON, 60 sec OFF, 40 sec ON, 60 sec OFF, 40 sec ON , then 60 minutes OFF
30 sec ON, 40 sec OFF, 30 sec ON, 40 sec OFF, 30 sec ON then 40 minutes OFF

What is recommended minimum engine oil temperature prior to takeoff?

+55°C
+5°C
0°C
+90°C

When landing on a short runway, you would like to achieve full reverse thrust as quickly as possible, how would you do that?

By setting the condition levers to HIGH IDLE before moving the power levers to reverse.
By lifting the power levers to reverse before touchdown
By setting the condition levers to HIGH IDLE before moving the propeller levers to reverse.
By setting the condition levers to LOW IDLE before moving the power levers to reverse.

What will happen if the engine-driven fuel pump (high pressure) fails?

The boost pump will still supply pressure
The primary low pressure pump is then supplying pressure
The fuel is still suction fed to the engine, but will limit the operating altitude
The engine will flame out

On the fuel gauge, without moving any switch, what does the gauge shows?

The total amount of all fuel tanks
The fuel in the main tank
The fuel in the AUX tank
One will show the fuel in the main tanks while the other will show the fuel in the AUX tanks

With fuel in both main tank and AUX tank, how will the fuel be drawn to the engine?

It will use the fuel from the AUX tank first, then from the main tank.
It will use equal amount from each tank, the AUX will be empty when the main tank is approx. 60%.
I will use the fuel from the main tank unless you have switched the fuel cross feed on.
You can select manually from which tank the fuel will be used by switching the AUX transfer switch to ON or OFF.

What type of electrical system is installed?

28 VDC multi bus fed system
24 VDC dual fed system with 28VAC
24 VDC system
32 VDC triple fed system

What is true regarding the battery and the dual fed bus?

It is only powered when the battery switch is placed to ON or GND OPS
It is only powered when the battery switch is placed to ON
It is powered when the standby battery switch is placed to ON
It is always powered if the battery is connected and the BAT BUS switch is in NORM

What is controlling the output of the generator?

The current limiter
The Generator Control Unit, GCU
The generator output solenoid
The Voltage Regulator Unit, VRU

To meet the requirement for battery power duration, what is the maximum battery charge current before take off?

50 amp
20 amp
10 amp
0 amp

What is true regarding the usage of external power?

It can only be used for engine start
The battery switch must be on before connecting the external power
The battery must be placed to OFF before connecting the external power
The ground power unit must be able to produce 500 amps continuously

What is a true statement?

The battery must indicate a minimum of 20 Volt before connecting the external power
If the battery voltage is low, the external power is always used to re-charge a depleted battery
A maximum continuous load of 300 amp, or more will damage the external power relay.
A ground power unit must be able to produce 1200 amp for engine start

What is true regarding AC power?

It is available as soon as the battery is placed to ON
Anytime the Center Bus is powered, Inverter 1 has DC power and #1 Inverter switch is ON
AC power is always automatically supplied to equipment without pilot action
The inverters are located under the cabin floor, aft of the main spar

The flashing yellow annunciator message “External Power” means?

The external power source is faulty
External DC power plug is connected to the aircraft and power is being supplied
The voltage from the ground power unit is not correct
External power socket is connected to the aircraft.

What is a true statement?

The GCU provides voltage regulation of an output of 24,5 VDC.
If the GCU senses a reverse current, it will open the line contactor and disengage the generator. The reset is automatic
If the GCU senses an overvoltage, it will open the line contactor and disengage the generator. The generator needs to be reset by the pilot in order to bring it back online.
Paralleling of generator output is provided by the current limiters

What does a loadmeter indicate?

Available power from a generator
Total amount of current drawn by airplane systems
Amount of current drawn by a generator
Generator load as a percentage of generator rating

Motive flow pressure for auxiliary transfer pump comes from

The engine fuel outlet nozzles
The primary boost pump
The fuel shutoff valve
The standby pump valve

The standby boost pumps are operated by

Electrical power
Motive flow
High pressure fuel
Ram pressure

What is the maximum differential pressure for the pressurization?

6.5 psi
6.6 psi
7.0 psi
5.9 psi

Pneumatic bleed air is used to operate everything except

Brake deicing
Yaw damping
Engine inlet lip heating
Surface deicing

The supplemental electric heating system warms the

Cockpit windshields
Cargo door
Cabin area
Cabin windows

The air conditioning compressor is located in the

Nose of the aircraft
Right engine
Lower mid-point of the fuselage
Right wing

The ENVIR BLEED AIR switch should be set to ______ for climbs

AUTO
HI
NORMAL
LOW

Windshield defogging is controlled by

The MAN HEAT
The MAN TEMP switch
The WINDOW DEFOG switch
The ELEC HEAT mode

The “Cabin Alt High” CAS message illuminates respectively at

10,000 FEET
13,500 FEET
14,500 FEET
12,000 FEET

The maximum selectable rate at which cabin pressurization can change is

1000 ft per minute
200 feet per minute
2000 feet per minute
10,000 feet per minute

The oxygen systems must first be enabled by

A PULL ON – SYSTEM READY handle
A diluter-demand flow valve
Pulling the pin in each mask hose
Setting all mask switches to 100%

Oxygen flow in the passenger masks when

A barometric switch energizes
A pressure-sensitive switch in the passenger line opens
A lanyard valve pin is pulled
Plungers open the mask dispenser doors

Propeller deicing boots, with the switch set to AUTO

Heat all blades continuously
Inflate all deice boots simultaneously
Heat blades according to a set cycle
Inflate all deice boots according to a set cycle

Anti-icing for the leading edge engine inlet

Utilizes a deployable vane barrier
Can release ice pellets into the engine compressor
Utilizes pneumatic boots
Utilizes hot exhaust gases

Propeller deicing

Is pneumatically-powered
Is electrically-powered
Utilizes inflatable boots
Utilizes de-ice fluid

The engine inertial vane

Protects the engine compressor screen
Protects the leading edge air intake
Utilizes engine bleed air
Is automatically extended when ambient temperatures are below -40°C

Fuel heating

Uses oil-to-fuel heat exchange
is selected when weight is off the landing gear
Is selected when ambient temperatures are below -40°C
Is powered electrically

Wing deice boots should be used

At frequent time intervals, when icing is observed
Only after about ½ inch of ice buildup on the wings
In the automatic cycling mode
No more than once per ten-minute period

Hydraulic power for the landing gear comes from:

An engine-driven pump
A hydraulic power pack
Integral pumps at each actuator
Electric motors at each actuator

Landing gear:

Separate hydraulic lines are provided for all of the operating modes except:

Emergency extension
Normal retraction
Normal extension
Manual retraction

The landing gear are:

Electrically controlled and electrically actuated
Hydraulically controlled and electrically actuated
Electrically controlled and hydraulically actuated
Hydraulically controlled and hydraulically actuated

The aircrew can test the “Hyd Fluid Low” message circuitry by:

Pressing the Warning Light Panel press-to-test button
Holding down the toe brakes while parked
Pressing the HYD FLUID SENSOR TEST button
There is no test function

The landing gear warning horn will sound continuously when the gear is not down and locked and:

The red LDG GEAR CONTROL lights are extinguished
The flaps are beyond the APPROACH position
The LDG GEAR CONTROL handle is down
The LANDING GEAR ALTERNATE EXTENSION handle is not in its securing clip

Electric elevator trim system can be disengaged by

Pressing the AP/TRIM MASTER switch to the second detent
Cycling either BLEED AIR VALVES switch to INSTR & ENVIR OFF
Pressing the AP/TRIM MASTER switch to the first detent
Sliding the YD/AP DISC switch down

In the case of a mismatch between flap positions

Flaps movement will stop
Electric elevator trim will be inoperative
The flaps will return to the full up position
A safety mechanism will disconnect power to the electric motor

Normally, a PFD will display

A common set of flight information
TCAS information
Weather radar information
Engine data and checklists

The yaw damp system…

should be de-activated for take off and landing.
should be activated for take off and landing.
should be de-activated for take off and activated for landing.
should be activated for take off and de-activated for landing.

What is true regarding the yaw damp system?

It assist the pilot with directional control during an engine failure
The yaw damper is automatically engaged any time the auto pilot is engaged
The auto pilot does not require yaw damper to be engaged
The yaw damper should not be used above 17,000 feet

The rudder boost…

assist with directional control in flight and works against dutch roll.
assist with directional control during an engine failure
is hydraulically powered
Is electrically powered

When will the warning “Cabin Diff High” be illuminated?

with a cabin altitude exceeding 12,500 feet
with a failed outflow valve
with a cabin differential pressure exceeding 6.9 psi
any time the cabin is not able to control the rate of climb or descend

When will the yellow “Hyd Fluid Low” be illuminated?

When the hydraulic level in the propeller gear box is below 50%
When the pressure in the hydraulic reservoir is below 2.25 psi
When the hydraulic fluid level in the landing gear system is low
When the hydraulic brake oil level is low

The VMCA is

94 KIAS and indicated with a red line
121 KIAS and indicated with a blue line
86 KIAS and indicated with a white bar
the ground minimum control speed. 98 KIAS, no indication

What is the max transient Torque?

150 %
100 %
110 %
156 %

What is true regarding the engine oil?

You should never mix different types, a placard should be placed with the type used at the filling port
You can mix different types of oil as long it is the same viscosity, a placard should be placed with the type used at the filling port
Always check the oil level when the engine has not been started, this will indicate the correct oil level
The engine oil is always under high pressure

The fuel capacity, usable fuel of the AUX tank is:

79 USG
132 USG
82 USG
193 USG

If you see the “L FUEL PRESS” illuminate, what is true?

The engine driven high pressure fuel pump has failed.
No fuel will be fed to the nacelle tank
The Left engine should be shut down
You are limited to 10 hrs of flight

What is the range of the propeller RPM you must avoid?

400 – 1050 RPM
300 – 760 RPM
1250 – 1560 RPM
920 – 1550 RPM

What is the flight load limit for flights with flaps down?

2.00 positive G's and 0 negative G's
2.20 positive G's and 0 negative G's
3.17 positive G's and 1.27 negative G's
1.27 positive G's and 2.00 negative G's

When using engine anti-ice, (ice vanes) what would be one result?

Less torque available?
A higher ITT
A high oil temperature
A low ITT
A high N1

How does fuel transfer from the AUX tank and to where?

Only by the standby boost pump, to the nacelle tank
By a motive flow jet pump to the nacelle tank
By the motive flow in the nacelle tank, fuel is pumped directly to the engine driven fuel pump
By switching on the jet pumps, fuel is then transferred to the collector tank

What causes the transfer of the fuel from the AUX tank to stop?

A float valve switch will close the motive flow valve with a delay of 6-7 seconds after depletion
A pressure switch in the motive flow line will close the motive flow valve with a delay of 30 to 60 seconds after depletion
By pilot action, turning the pumps to OFF
The pump in the AUX tank will never stop as log as the engine driven fuel pump is operating

When crossfeeding fuel from one side to the other…

The standby fuel pumps should be switched ON
The standby fuel pumps should be switched OFF
The standby fuel pump of the side to where the fuel is being transferred to should be switched ON
The standby fuel pump of the side from where the fuel is transferred from should be switched ON

What is true regarding the fuel tanks?

There are four sump drains and one filter drain in each wing.
There are four sump drains and two filter drain in each wing.
There are five sump drains and one filter drain in each wing.
There are five sump drains and two filter drain in each wing.

What does the “DUCT OVERTEMP” caution annunciator mean?

Excessive temperature in the bleed air system, the EVA tubes has melted
Excessive heat in the ducts supplying heat through the floor outlets
Excessive heat in the P3 bleed air valve connection
Excessive heat in the heat exchanger

What should you do if the annunciator “AIR COND N1 LOW” illuminates?

Increase N1 on the right engine by the condition lever
Switch off the bleed air
Switch on the air conditioning unit
Increase N1 by adding power with both power levers

The oxygen bottle…

is located in the nose compartment
is located in the cabin compartment
is located in the tail section in the pressurized section
is located in the tail section, unpressurized section

When the handle “PULL ON – SYS READY” for the oxygen is pushed in:

No oxygen will be available anywhere in the airplane
Oxygen is available
Oxygen is not available for the passengers but always for the crew
The oxygen lines are pressurized and ready

What is true regarding the surface de-ice?

Operation of the surface deice system in ambient temperatures below -40°C can cause permanent damage to the deice boots.
The de-ice boots are held deflated against the skin with airflow over the surfaces
You should always operate the de-ice boots as soon as you see any ice
The de-ice boots are electrically inflated

Whats is a true statement?

Windshield wipers shall never be used in flight, only on the ground
The propeller de-ice is pneumatically operated
The surfaces that has de-ice boots are: Wings, stabilizer, fin and propellers
The engine air inlet is heated with exhausts

The autofeather system….

is armed when the switch is placed to ARM
is armed when the switch is placed to ARM, and the power levers are advanced more than 90%N1
is always armed when the landing gear is down
will always be armed when one engine torque falls below 500 FT-LBS

The King Air requires

2 pilots for any IFR flight
1 pilot, seated in the left seat
1 pilot, seated in either seat
2 pilots

The fire test:

can only be tested when on the ground
can only be tested with the engines off
can always be tested
can only be tested before engine start

If the ground safety switch fails and the landing gear handle can not be moved to the UP position after take off:

The pilot can override the switch and raise the gear
The pilot must pull the CB for the landing gear and then manually retract the gear
The aircraft must return for landing
The landing gear is unsafe and not in the locked position

What is a true statement?

The autopilot requires the electric trim to operate, in order to operate properly
The autopilot can only be disconnected by the AP disconnect switch
The autopilot can be engaged for takeoff
The autopilot is capable of landing the aircraft

The fuel flow instrument indicates:

LBS per hour
USG per hour
weight per minute
Liters per second

The amount of fuel measured in the fuel tanks is measured by:

3 float probes
capacitance probes
a dipstick
electrical resistance probes, measuring the volume in USG

You are about to practice take-off and landings. Is there any limitation of the landing gear operation applicable?

Maximum 1 cycle per 5 minutes, a total of 6 followed by a cool-down period of 15 minutes.
There are no limitations
Maximum 1 cycle per 15 minutes, a total of 10 followed by a cool-down period of 15 minutes.
Maximum 5 cycles per 5 minutes, a total of 6 followed by a cool-down period of 15 minutes.

Where do you service the oxygen bottle?

On the right aft side of the fuselage
On the left aft side of the fuselage
On the left side of the nose compartment
By a filling port inside of the entrance door

Whet is true regarding doors and exits?

Maximum two occupants at the same time on the air stair door
The air stair door is locked by 4 bayonet pins and 2 hooks.
The over wing emergency exits opens outwards
The pilot side window can be opened and used as an emergency exit

What is the power source for the movement of the rudder boost?

Electrically, 28 VDC
Bleed air
Hydraulic
Electrically controlled hydraulic servos

King Air 350 Theoretical Exam – Only exam

King Air 350 Theoretical Exam – Only exam

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