REVIEW SUBSET NUMBER 2
REVIEW SUBSET NUMBER 3
A1. Rudder.
A1. Newton's first law of motion.
A2. Acceleration.
A2. Angle of attack on the wing.
Velocity.
A3.
A3. By increasing the airfoil's angle of attack
(blade pitch).
To keep track opposition.
A4.
When the pilot applies collective to the
A4.
The accelerometer.
A5.
main rotor.
A6. No.
REVIEW SUBSET NUMBER 3
A7. Mounting another accelerometer per-
pendicular to the first one.
A1. Radar and barometric altimeter signals.
A8. The inner roll gimbal.
To prevent sudden and violent maneuvers
A2.
upon engagement.
A9. 84.4 minutes.
A3.
The air navigation computer.
A10. Centripetal errors.
A4.
Three axis rate gyro.
A11. Terrestrial, celestial, and inertial.
A 12. Earth.
A5. A clutched heading signal.
A6. Manual and AFCS engaged.
REVIEW SUBSET NUMBER 4
A7. Surface position transmitter.
The wander-azimuth system.
A1.
A8. Stability augmentation mode.
A2. Analytic inertial navigation system.
A3.
The gyros are not torqued.
REVIEW SUBSET NUMBER 4
A4. Universal screw and the loose magnet type.
A1. Stability augmentation system, stabilator
system, and digital automatic flight control
A5.
When coefficient A amounts to 2 or more
..
system.
in either direction.
A2. 5-percent control authority.
CHAPTER 8
A3.
To stop undesirable noseup attitudes.
When airspeed is below 50 knots.
A4.
REVIEW SUBSET NUMBER 1
A5. To improve helicopter stability.
A1. Ease pilot workload and provide aircraft
stability at all speeds.
A6. 10 percent per second.
A2. Any part of an aircraft designed to produce
A7. 0 to 5,000 feet.
lift.
A8. 120 feet/minute.
A3. The airfoil stalls.
AIV-6
