Results
Q1. A gravity erector system is used to correct the errors on:
an artificial horizon.
Q2. Following 180° stabilized turn with a constant attitude and bank, the artificial horizon indicates (assume air-driven and turning clockwise, when viewed from above):
too high pitch up and too high banking
Q3. When an aircraft has turned 270 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
too much nose-up and bank too high.
Q4. When an aircraft has turned 90 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
too much nose-up and bank too low
Q5. What angle of bank should you adopt on the attitude indicator for a standard rate (rate 1) turn while flying at an IAS of 130 Kt?
20°
Q6. In a vacuum operated attitude indicator, automatic erection of the gyro is performed by:
the pendulous unit
Q7. Among the flight control instruments, the artificial horizon plays an essential part. It uses a gyroscope with:
two degrees of freedom, whose axis is oriented and continously maintained to local vertical by an automatic erecting system.
Q8. A gravity type erector is used in a vertical gyro device to correct errors on:
an artificial horizon
Q9. A Stand-by-horizon or emergency attitude indicator:
Contains its own separate gyro
Q10. The higher the airspeed is:
The higher the bank angle must be to turn at the standard rate.
Q11. When an aircraft has turned 360 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
attitude and bank correct
Q12. You have just taken off in a fast aircraft fitted with a vacuum operated attitude indicator. While climbing straight ahead – still accelerating – the instrument may for a short while indicate:
a climbing turn to the right
Q13. If a 180° steep turn is made to the right and the aircraft is rolled out to straight and level flight by visual reference, the miniature aircraft on the Attitude Indicator will ….
show a slight climb and turn to the left
Q14. During an acceleration phase at constant attitude, the resetting principle of the artificial horizon results in the horizon bar indicating a:
nose-up attitude
