Cessna 208B Grand Caravan POH Test

The Cessna 208B is powered by which engine?. PT6A-67. PT6A-114A. TPE331. PW150.

The PT6A-114A is best described as a: Direct-drive turboprop. Free-turbine turboprop. Turbocharged piston engine. FADEC turbofan.

Which cockpit indication represents gas-generator speed?. NP. Torque. NG. ITT.

ITT measures. Exhaust gas temperature. Compressor outlet temperature. Turbine inlet temperature. Oil temperature.

Which instrument is the primary indication of engine power output?. Ng. NP. Torque. ITT.

What is the primary function of the condition lever?. Control propeller blade angle. Control fuel flow to the engine. Control torque. Engage the starter.

How is the propeller described in the POH?. Fixed-pitch propeller. Two-position propeller. Constant-speed, full-feathering. Ground-adjustable propeller.

Ignition during engine start is provided by: Magnetos. Continuous ignition only. Dual electric igniters. Starter-generator.

The Caravan is pressurized. Fully. Semi-pressurized. Only above 10,000 ft. Not pressurized.

How is engine control accomplished on the Caravan?. FADEC. Electrical. Mechanical / hydro-mechanical. Digital.

Approved fuel is: 100LL. Jet B. Jet A / Jet A-1. Diesel.

Maximum ITT during engine start is: 850°C. 900°C. 1000°C. 1090°C.

Maximum continuous torque is: 1600 ft-lb. 1750 ft-lb. 1865 ft-lb. 1970 ft-lb.

Maximum oil temperature is: 90°C. 95°C. 99°C. 110°C.

Maximum oil pressure is: 100 PSI. 120 PSI. 135 PSI. 150 PSI.

Minimum oil for dispatch is: Drain-and-refill quantity. Maximum quantity. Within operating range. Above minimum red line.

Electrical system voltage is: 14 VDC. 24 VDC. 28 VDC. 115 VAC.

Approved takeoff flap settings are: 0° only. 10° only. 20° only. 10° or 20°.

Maximum takeoff weight is approximately. 8,000 lb. 8,750 lb. 9,062 lb. 9,500 lb.

Maximum operating altitude is: 20,000 ft. 23,000 ft. 25,000 ft. 27,500 ft.

Beta mode operation is: Allowed in flight. Allowed only below 10,000 ft. Ground operations only. Emergency use only.

Reverse thrust is: Allowed in flight. Allowed above taxi speed. Prohibited in flight. Required for landing.

When is continuous ignition required?. At all times. During icing conditions. During cruise. During landing.

Flight into known icing is: Prohibited. Approved when properly equipped. Approved without limitation. Emergency only.

Propeller RPM is controlled by the: Condition lever. Power lever. Governor. Torque limiter.

Oil type used must be: Automotive oil. Mineral oil only. Approved turbine engine oil. Synthetic oil only.

Placards and markings are: Advisory. Optional. Mandatory. Training-only.

Operation outside published limitations is: In emergencies. For short duration. With maintenance approval. Never.

Maximum landing weight is: 8500 Lb. 8750 Lb. 8250 Lb. 9000 Lb.

Operating outside limitations primarily risks: Passenger comfort. Performance only. Structural or engine damage. Fuel imbalance.

First action after engine failure after takeoff is: Feather propeller. Maintain aircraft control and airspeed. Condition Lever Fuel Cutoff. Land.

During an engine fire on start, what is the first memory item action?. Starter disengage. Condition lever cutoff. Fire extinguisher. Battery off.

During an engine fire in flight, the propeller is placed: High RPM. Windmill. Feather. Reverse.

During an engine fire in flight, the firewall shutoff valve is: Open. Half. Closed / pulled. As required.

With smoke in the cabin, the immediate priority is: Land immediately. Identify source. Ventilation / oxygen. Shut down engine.

For an emergency descent, the power lever is set to: Maximum. Idle. Cruise. Reverse.

During an emergency descent, propeller RPM is set: Feather. Low RPM. High RPM. Auto.

Airstart capability on the PT6: Not possible. Starter only. Yes, under appropriate conditions. Prop-driven only.

After completing memory items, the pilot should: Land immediately. Declare emergency. Accomplish checklist. Restart engine.

Cabin fire requires landing: When convenient. At destination. As soon as possible. Only if uncontrollable.

For an electrical fire, the initial response includes: Increasing ventilation. Turning electrical power off. Using reverse thrust. Feathering prop.

In the event of propeller overspeed, the immediate corrective action is to: Increase torque. Reduce power. Feather immediately. Shut down engine.

After an engine failure in cruise, the first aerodynamic action is to: Restart immediately. Maintain altitude. Establish best glide. Feather prop.

During an engine fire in flight, when is the fire extinguisher discharged?. Immediately upon fire warning. Before feathering the propeller. After fuel, air, and electrical sources are secured. Only if landing is not possible.

Memory items are defined as: Optional procedures. Reference items. Immediate action steps requiring memorization. Maintenance actions.

The correct engine start sequence is: Fuel → starter → ignition. Starter → fuel → monitor. Ignition → fuel → starter. Fuel → ignition → starter.

Fuel is introduced during start at approximately: 8% Ng. 10% Ng. 12–15% Ng. 20% Ng.

The first positive indication of a successful start is: Torque rise. ITT rise. Oil pressure rise. Prop rotation.

The generator is brought online: Before engine start. During start. After stabilized idle. At taxi power.

Propeller RPM for takeoff is set to: Feather. Low RPM. High RPM. Beta.

Normal taxi speed is controlled primarily using: Brakes. Power lever only. Beta range. Reverse thrust.

Propeller governing is checked during run-up by: Cycling reverse. Moving the condition lever. Observing torque. Feathering.

Takeoff power is set and verified using: Ng. ITT. Torque. NP.

After landing, reverse thrust should be reduced: Immediately. Above 40 knots. Below taxi speed. Never.

Normal engine shutdown is accomplished by: Power lever idle. Generator off. Condition lever to CUTOFF. Battery off.

Correct oil quantity indication is obtained: Cold only. Without oil check. After performing the oil check procedure. During taxi.

During a normal engine start, the avionics master remains OFF. According to the POH normal procedures, at what point may avionics be switched ON without risk of electrical transients?. Before engaging the starter. During start. After the engine has stabilized at idle and the generator is online. After takeoff and climb power is set.

Prior to takeoff, the POH requires a full-travel flight control check. When must this check be completed to satisfy POH requirements?. Any time during taxi. Immediately before takeoff with no restrictions or obstructions present. During the initial climb after liftoff. While lined up on the runway.

During normal operations, elevator trim may be adjusted multiple times. According to the POH Before Takeoff checklist, when must takeoff trim be correctly set?. During taxi as a convenience. After lining up on the runway. Before takeoff, prior to applying takeoff power. After rotation.

According to the POH normal procedures, the takeoff briefing must be completed at which point to comply with required procedures?. After engine start. During climb. Before takeoff and prior to applying takeoff power. Only for multi-pilot operations.

You are operating from a short, soft field near maximum weight. According to the POH, how is the takeoff flap setting determined?. Pilot preference. Always 20. Always 10. By performance charts accounting for weight, runway, and obstacles.

After liftoff and obstacle clearance, propeller RPM should be managed based on: Noise abatement only. Engine temperature. Torque, Ng, and POH climb power limitations. Airspeed alone.

According to normal procedures, landing lights should be ON: At night only. Below 10,000 ft. For takeoff, landing, and when operating near other traffic. Only in IMC.

Pitot heat must be selected ON when: OAT is below 10°C. In IMC only. Visible moisture exists with OAT near or below freezing. Airspeed fluctuates.

The POH directs the ice protection system to be activated: After ice accumulates. Prior to ice accumulation when icing conditions are encountered. At pilot discretion. Only when required by ATC.

During cruise, power is set primarily by torque. What additional limitation must be respected?. Ng and ITT limits per POH charts. Fuel flow. Oil pressure. Cabin comfort.

Fuel crossfeed operation is permitted: Only as required to maintain fuel balance or engine supply. Anytime in cruise. Anytime imbalance exists. Never in flight.

According to the POH, the landing checklist must be completed: After landing. On final only. While taxiing. Before landing, with time to correct configuration errors.

Final approach speed must be selected based on: Aircraft weight and flap configuration per POH tables. Runway length only. Wind only. Pilot experience.

Engine shutdown on ramp requires: Beta mode. Full power. Condition lever to fuel cutoff, ignition off, electrical off. Feather prop only.

Maximum ramp weight is: 9,000 lb. 9,100 lb. 9,050 lb. 9,062 lb.

Maximum zero fuel weight is: 8,500 lb. 8,750 lb. 9,000 lb. 8,900 lb.

Maximum landing weight is: 8,900 lb. 9,062 lb. 9,202 lb. 9,000 lb.

Maximum baggage weight in cargo area is: 1,500 lb. 1,000 lb. 1,200 lb. 1,300 lb.

Maximum weight in nose baggage compartment: 50 lb. 150 lb. 120 lb. 100 lb.

Fuel capacity per tank is: 200 US gal. 335 US gal. 235 US gal. 300 US gal.

Fuel density used for weight calculations: 5.5 lb/gal. 6.7 lb/gal. 7.5 lb/gal. 6.5 lb/gal.

CG limits forward: 85 in. 85.5 in. 86.5 in. 86 in.

CG limits aft: 102 in. 103 in. 104.5 in. 101.5 in.

Takeoff distance over 50-ft obstacle at MTOW: 2,960 ft. 2,500 ft. 2,840 ft. 2,550 ft.

Landing distance over 50-ft obstacle at MLW: 2,100 ft. 2,300 ft. 2,160 ft. 2,220 ft.

Best rate of climb speed: VY. VX. VY adjusted per weight and altitude chart. VX adjusted per weight and altitude chart.

Maximum cruise speed: 160 KIAS. 170 KIAS. 178 KIAS. 183 KIAS.

Maximum flap-extended speed (VFE) 10°: 120 KIAS. 140 KIAS. 160 KIAS. 150 KIAS.

Maximum flap-extended speed (VFE) 30°: 140 KIAS. 120 KIAS. 130 KIAS. 125 KIAS.

Electrical system normal operating voltage: 24 VDC. 28 VDC. 26 VDC. 32 VDC.

Generator rating: 150 A. 200 A. 300 A. 400 A.

Battery type and rating: Lead acid, 24V 20A. Lead acid, 24V 17A. Li-ion 28V. Nickel-cadmium.

A hydraulic system failure most directly affects: Steering only. Flaps. Braking effectiveness. Propeller.

Landing gear retraction speed limitation: 100 KIAS. 120 KIAS. 115 KIAS. 125 KIAS.

Nose gear steering limit at taxi: 20°. 25°. 30°. 35°.

Fuel system includes: Two main tanks, collector cell, and sump drains. One main tank. Two main tanks and collector cell. Wing tanks only.

Fuel crossfeed is allowed: Always. Never. In cruise only. Only if required to balance fuel or supply engine.

Cabin heating uses: Engine-driven heater via exhaust heat exchanger. Bleed air. Electrical heaters only. Fuel heat.

De-ice / anti-ice system protects: Wing, tail, and propeller. Only prop. Only wings. Prop, and wings.

Ice protection system is required when: Temperature below 10°C. Visible moisture below freezing. Temperature below 0°C only. Operator discretion.

Propeller feathering is controlled by: Power lever only. Electric switch. Beta lever. Condition lever and prop governor.

Reverse pitch is permitted: In fligh. Taxi only. Landing only. On the ground only.

Beta range usage is: Cruise flight. Ground operations only. Takeoff. Approach.

In-flight operation outside limitations: Never permitted. Allowed for emergencies. Allowed with ATC approval. Allowed if following checklist.