03. 6. ACGA_L01-L09_2017

a) Ground mode, take off mode, in flight mode, flare mode.

b) Ground mode, take off mode, landing mode, flare mode.

c) Ground mode, take off mode, landing mode, approach mode.

d) Ground mode, air mode, take off mode, flare mode.

a) aircraft is fully protected against exceeding the maximum negative and positive load factors (with and without high lift devices extracted), angle of attack, stall, airspeed/Mach number, pitch attitude, roll rate, bank angle etc.

b) when the aircraft approaches to ground the control is gradually switched to this mode, where automatic trim is deactivated and modified flight laws are used for pitch control.

c) pilot has control on the nose wheel steering as a function of speed.

d) after lift-off the envelope protection is gradually introduced.

a) aircraft is fully protected against exceeding the maximum negative and positive load factors (with and without high lift devices extracted), angle of attack, stall, airspeed/Mach number, pitch attitude, roll rate, bank angle etc.

b) when the aircraft approaches to ground the control is gradually switched to this mode, where automatic trim is deactivated and modified flight laws are used for pitch control.

c) pilot has control on the nose wheel steering as a function of speed.

d) after lift-off the envelope protection is gradually introduced.

a. Each yaw damper has an associated coupler which operates as a rate gyro and senses pitch.

b. Minimise Duch Roll by automatic rudder displacement proportional to and opposing the amount of yaw experienced.

c. Minimise Duch Roll by manual rudder displacement proportional to and opposing the amount of yaw experienced.

d. The duch roll is detected when: directional > lateral stability.

a) Detect the movement of the aircraft in the air.

b) Detect higher frequency structural oscillations due to flexible modes.

c) Detect low frequency structural oscillations due to flexible modes.

d) Detect rigid body movement of the aircraft on landing configuration.

a) Digital system allows great flexibility and high complexity functions.

b) Analog system is affected by inherent delays.

c) Analog system allows the use of screens and simplify the work in the cockpit.

d) Digital system is instantaneous.

a) Improvement of system performances

b) Efficient energy management

c) Reduction in equipment space and mass

d) Improvement of resistance to G-forces.

a) aircraft is fully protected against exceeding the maximum negative and positive load factors (with and without high lift devices extracted), angle of attack, stall, airspeed/Mach number, pitch attitude, roll rate, bank angle etc.

b) when the aircraft approaches to ground the control is gradually switched to this mode, where automatic trim is deactivated and modified flight laws are used for pitch control.

c) pilot has control on the nose wheel steering as a function of speed.

d) after lift-off the envelope protection is gradually introduced.

a) They are not used if high aerodynamic efficiency is needed

b) They are an effective method for ice thickness between 1⁄4 (bridge) and 1⁄2 inch (strength)

c) Both “a” and “b” are wrong

d) Both “a” and “b” are right

a) The pneumatic de-icing boots

b) The termal anti-icing system

c) The airframe de-icing fluid system

d) The electro expulsive de-icing system

a) The leading edge of the tail and fin

b) Flaps and spoilers

c) The trailing edge

d) The engine cowling

a) A light in the cockpit warns the pilot that there is ice in the wing

b) A light that illuminates those parts of the wing that are deemed critical for ice accumulation

c) An acoustic alarm that warns the pilot that there is ice in the wing

d) No one is correct

a) A serrated rotor ice detector

b) A smiths ice detector

c) A hot rod ice detector

d) An ice detection light

a) A vibration frequency drops when ice increases

b) A heater breaks the ice

c) A vibration frequency drops before the ice increases, preventing it

d) High pressures destroy the ice formed

a) In most cases it is the aircraft itself that triggers the lightning when entering a region with intense electrostatic field

b) Aircraft accidents caused by lightning are very common

c) The basic solution to limit damage to a structure and systems from lighting is to make the whole structure a good electrical conductor

d) No one is true

a) Occurs when a lightning hits the aircraft

b) Happens when certain materials become electrically charged after they come into contact with another different material through friction.

c) In aircrafts is important in flying across clouds or in an ambient with particles in suspension

d) Both “b” and “c” are right

a) The fuel system must provide an uninterrupted flow of contaminant free fuel regardless of the aircraft’s attitude.

b) The gravity center of the aircraft must be preserved even when the fuel is consumed .

c) Previous two sentences must met regardless of the aircraft’s attitude.

d) Al three statements are true.

a) First way of feed the engine was by the use of manual pressure.

b) Higher performance was related with more complexity.

c) Jet engines, being more modern than their piston-engines predecessors, need less fuel.

d) Use of under-wing and under-fuselage ventral tanks was less efficient for the range.

a) Analog electronics.

b) Visual (Fuel tank visible for the pilot flying).

c) Digital Electronics.

d) Mechanical.

a) Polyurethane reticulated foam installed within the fuel tanks.

b) Gaseous Nitrogen Inert system.

c) On Board Inert Gas Generation System OBIGGS (separation O2 /N2) .

d) Previous three are correct.

ExcessiveTurbineEntryTemperature(TET).

Under-speed.

Compressor surge.

Excessive acceleration/deceleration.

Each fuel system is able to supply at least 90% of the fuel flow required under each intended operation condition or maneuver.

Each fuel system is able to supply at least 95% of the fuel flow required the majorityof operation condition or maneuver.

Each fuel system is able to supply at least 100% of the fuel flow required under the majority of operation condition or maneuver.

Each fuel system is able to supply at least 100% of the fuel flow required under each intended operation condition or maneuver.

a) To facilitate outboard fuel movement, a number of check valves (non-return valves) are installed along the ribs that form the boundaries between compartments.

b) The fuel tanks are normally located in the aircraft fuselage and tail.

c) In fighter aircrafts, there are complex shapes due to the lack of volume

d) A and C are correct.

a) Flexible Tanks

b) Rigid Tanks

c) External Tanks

d) Integral Tanks