Aerospace Systems and Operations Quiz

During an auto start or normal operation with the ignition switch set to _____, the PMU will energize and de-energize the igniters as required.

Ensure light has extinguished prior to _____.

After initial power-up, the OBOGS FAIL annunciator will be inhibited for _____ during OBOGS monitor warm-up.

The canopy shall not be opened on the ground when the surface winds exceed ___ knots.

The SCU will activate the red OIL PX annunciator if oil pressure falls below ___ psi when the engine is above ___ power.

Taxi over arresting cables at _____.

If a fuel probe fails, _____ will continue to provide an accurate indication of minimum fuel level.

Power for the start control (START) is provided by the _____ bus.

The SCU will activate the OIL PX annunciator if the oil pressure drops below ___ psi at idle power.

Illumination of both the ___ and ___ annunciators indicates the system is in the manual mode.

Increase takeoff speeds by ___% of the gust increment up to a maximum of 10 knots.

Final turn speed for a no-flap landing is ___.

Engine starts are recommended with the PMU in the manual mode.

Controls neutral spin recoveries have been demonstrated and, generally, spin rotation will cease within ___ additional turns after neutralizing controls in each axis.

Aircraft empty weight is ___ pounds and max takeoff gross weight is ___ pounds.

Oil system capacity

Maximum airspeed in turbulence

On the ground, IDLE torque is ___ to ___%.

If cockpit pressure altitude rises above ___ feet, an amber ___ caution illuminates.

When correcting a fuel imbalance, set the MANUAL FUEL BAL switch to the tank that is ___.

With the landing gear down and flaps and speed brake retracted, best glide speed is ___ KIAS with a sink rate of ___ feet per minute.

A PMU STATUS light in flight indicates:

When flying solo, failure to secure the rear seat oxygen regulator will result in the loss of ability to ___.

In the ground mode, the engine idle N1 is ___%, and in the flight mode, idle is normally ___%.

The PMU is normally powered by ___.

The engine has been flat-rated to produce ___ shaft horsepower.

Pulling the emergency landing gear extension handle will extend the gear AND flaps.

The ___ senses torque, altitude, airspeed, and pitch rate and computes a desired rudder trim tab position.

The trim system control circuits give ___ priority if trim conflicts between cockpits.

Do not touch the parking brake ___ when actuating or releasing the parking brake.

Define 'land as soon as possible.'

Define 'land as soon as practical.'

Define 'suitable landing area.'

Any fault discovered during the ___ check is reason for a ground abort.

If the hydraulic pressure in the emergency accumulator drops below ___ psi, an amber EHYD PX LO annunciator will illuminate.

Maximum ___ speed is the maximum speed at which an abort may be started and the aircraft stopped within the remaining runway length.

During inverted flight, the inverted flight fuel pickup provides ___ of fuel supply and prevents air ingestion into the fuel system.

The wheel brake system is affected by failure of the aircraft hydraulic system.

The chip detector is mounted in the ___ to detect metal contamination in the oil.

Oil level must be serviced within ___ minutes of engine shutdown.

If oil pressure remains between ___ and ___ psi at IDLE power for ___ seconds or more, both amber and red OIL PX lights will illuminate.

Hydroplaning can occur above ___ knots for the nose tire and above ___ knots for the main tires when inflated to nominal tire pressures.

The auto fuel balance system keeps the indicated fuel level in the wing tanks within ___ pounds of each other.

The top latch mechanism on the ejection seat shall be checked on preflight.

A normal gear extension/retraction sequence takes approximately ___ seconds.

The ___ and the ___ automatically control the propeller blade angle (pitch) and propeller speed (Np).

Following a successful airstart, the PCL should be advanced as required after N1 reaches ___.

Auxiliary power is supplied by a ___ auxiliary battery, located in the left avionics compartment.

The propeller system is designed to maintain a constant speed of ___ RPM (100% Np) during most flight conditions.

Using external power during engine starts provides for lower ___ during engine starts and preserves ___.

Above ___% torque, full right rudder and full right aileron may not prevent a left roll-off at stall.

When checking the brake wear indicators, if an indicator reads low, ___ and re-check.

The incipient spin phase of the aircraft lasts approximately ___ turns.

The firewall shutoff handle mechanically operates cables that:

The cockpit will depressurize when power to the battery bus is lost.

During a spin, oil pressure may decrease below ___ psi with idle power.

Engine start should be aborted manually if: