King Air C90 Theoretical Exam

What is the maximum certified altitude for the King Air C90B?

29,000 FT
25,000 FT
30,000 FT
35,000 FT

What is the maximum occupancy onboard, including crew?

9
15
8
13

What is the maximum landing weight for the C90B or GT?

11,500 lbs
10,100 lbs
9,600 lbs
12,590 lbs

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

Operation with crossfeed capability above 8,000 feet is prohibited
Operation is limited to 200 hrs
Operation above FL250 is prohibited
Operation is limited to 100 hrs

What is the max indicated airspeed for flaps Approach (C90B/GT)?

157 KIAS
210 KIAS
184 KIAS
181 KIAS

What is the VMO/MMO for the King Air C90B?

259 KIAS / 0.52 Mach
282 KIAS / 0.65 Mach
226 KIAS / 0.46 Mach
260 KIAS / 0.56 Mach

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

108 KIAS
85 KIAS
121 KIAS
100 KIAS

Which engine is installed in the King Air C90B?

Pratt & Whitney PT6A-52
Pratt & Whitney PT6A-21 or PT6A-135A
Pratt & Whitney PT6A-42
Pratt & Whitney PT6A-62

What is the maximum fuel imbalance for the King Air C90B?

79 USG
267 LBS
200 LBS
350 LBS

What is the minimum amount of fuel required for takeoff per side?

265 LBS
150 LBS
1000 LBS
325 LBS

What is the maximum ITT during engine start, PT6A-135A?

1000°C
750°C
1090°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 200 FT LBS
If engine torque falls below 400 FT LBS
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(with fire detection and extinguishers installed)?

A master caution. Warning annunciator "Engine Fire" in red. If extinguisher is installed, the "ENG FIRE – PUSH TO EXT" will illuminate.
An amber master caution"Engine Fire" will be illuminated.
A bell will sound, a red fire warning will illuminate on the PFD.
A bell will sound, a red CAS will be displayed on the EICAS "ENG FIRE"

What is true regarding the fire detection system?

It senses infrared radiation, the system has photo conductive cells.
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, if the primary governor fails?

The overspeed governor dumps oil from the propeller to keep the RPM below 1976 RPM (PT6A-135A).
The primary governor dumps oil from the propeller to keep the RPM below 2000 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?

40 sec ON, 60 sec OFF, 40 sec ON, 60 sec OFF, 40 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 conditioning levers to HIGH IDLE before moving the power levers to reverse.
By lifting the power levers to reverse before touchdown
By setting the conditioning levers to HIGH IDLE before moving the propeller levers to reverse.
By setting the conditioning 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

If you want to fill all fuel tanks full, which tank must you begin to fill up?

The nacelle tank
The wing tank
It does not matter
the wing tank first, then the nacelle tank, then top off the wing tank again

What type of electrical system is installed?

28 VDC triple fed system
24 VDC dual fed system with 28VAC
24 VDC system
32 AC triple fed system

What is true regarding the hot battery bus?

It is powered when the battery switch is placed to ON or GND OPS
It is 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.

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

What is the absolut minimum voltage of the battery to connect an external power?

22 Volts
20 Volts
no limitation
23 Volts

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 may be damaged if exposed to voltages higher than 30 volts for extended periods of time
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

The yellow annunciator “EXT PWR” mean?

The external power source is faulty
External DC power plug is connected to the aircraft
The voltage from the ground power unit is not correct
External power is available but not yet connected.

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 generator needs to be reset by the pilot in order to bring it back online.
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 is the purpose of the Hot Battery bus?

Provides a path for generators to charge the battery
Provides a different electrical path when using external power
Provides power to essential systems
Sheds excessive load from the battery

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

What is true regarding the pump in the center fuel tank?

It is submerged electrically driven pump
Its a jet pump driven by motive flow from the engine driven fuel pump
its a a submerged jet transfer pump driven by the motive flow from the wing tank fuel pump
This tank does not have a tank, the transfer is done by gravity

The boost pumps are operated by

Electrical power
Motive flow
High pressure fuel
Ram pressure

What is the maximum differential pressure for the pressurization?

5.1 psi
6.6 psi
7.0 psi
5.9 psi

Pneumatic bleed air is used to operate everything except

Engine inlet de-ice
Yaw damping
door seal, air-stair door
Surface deicing

The supplemental electric heating system will not operate when:

Windshield heat or prop-deice is operating
The ELEC HEAT switch is set in GND MAX and the airplane becomes airborne
The de-ice boots are operating
The engine bleed air is warming the cabin

The air conditioning compressor is located in the

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

Windshield defogging is controlled by

The DEFROST AIR knob
The MAN HEAT switch
The TEMP MODE SELECTOR switch
The ELEC HEAT mode

The “Cabin Alt High” warning annunciator illuminates respectively at

10,000 FEET
13,500 FEET
14,500 FEET
12,500 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
The passenger masks are plugged in to the connection in the ceiling.

Propeller deicing boots, with the switch set to ON

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
Can be confirmed by changes on the ammeter

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 hydraulic landing gear is:

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

The pilot can test the “HYD FLUID LO” caution annunciator 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

The electric elevator trim system can be disengaged by

Pressing the AP/YD TRIM INTERRUPT button on the yoke. When released, trim will resume operation.
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

What is the maximum altitude with the yawdamper inop?

12,000 feet
17,000 feet
25,000 feet
31,000 feet

What is the minimum airspeed for sustained flight in icing conditions?

163 KIAS
140 KIAS
200 KIAS
223 KIAS

How is the cabin pressure maintained?

By regulating the outflow valve
By regulating the bleed air valves
By regulating the hydraulic lines
By an outflow valve in the bleed air lines

Before descent, what is the best practice for the cabin pressurization controller?

Close the rate of descent before setting the landing altitude
Ensure the rate of descent is set to max
Set the landing altitude always at the runway elevation
Set the landing altitude 500 feet below the landing altitude

Regarding pressurization, what is true?

Set the landing altitude +500 feet, adjusted for pressure setting
Set always 500 feet above the landing altitude
Set the landing altitude at 0
Set the landing alttiude 1000 feet above airport reference point.

What could happen if you try to start an engine (using battery) with too low voltage?

A hung start
A hot start
Battery runaway
The battery will be destroyed

King Air C90 Theoretical Exam

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