Test 5

The flight control system failures are sent to the FWC through of?. FCDC for indication on the engine and warning display. FCDC for indication on the primary flight display. FCDC for indication on the Navigation display.

Which computers control the yaw damper servo controls?. The FAC 1 has priority and FAC 2 is in hot stand-by. The ELAC 2 has priority ELAC 1 is in hot stand-by. The SEC 1 has priority SEC 2 is in hot stand-by.

Where does the signals come from to the landing gear indicator panel?. LGCIU 1. LGCIU 1 & 2. LGCIU 2.

How is restored the landing gear operation after free fall extension?. Normal landing gear operation is restored after by rotating the crank handle 2 turns counter clockwise. Normal landing gear operation is restored after by rotating the crank handle 3 turns counter clockwise. Normal landing gear operation is restored after by rotating the crank handle 3 turns clockwise.

What happens when rotates the gravity extension crank handle BETWEEN 1.9 AND 3 TURNS?. The door uplocks are released and the landing gear extends by gravity. The gear uplocks are released and the landing gear extends by gravity. The doors uplocks and gear uplocks are released and the landing gear extends by gravity.

The speed brakes can be driven by: The (SECs) 1 and 3 and the surfaces ensuring this function are spoilers 2 thru 4. The (SECs) 1 and 2 and the surfaces ensuring this function are spoilers 3 thru 5. The (SECs) 2 and 3 and the surfaces ensuring this function are spoilers 1 thru 4.

The rudder travel limitation is: Above 160 kts the stops are in low-speed configuration, between 160 and 380 kts the rudder deflection is limited as a function of speed, under 380 kts the stops are in high-speed configuration. Under 160 kts the stops are in high-speed configuration, between 160 and 380 kts the rudder deflection is limited as a function of speed, above 380 kts the stops are in low-speed configuration. Under 160 kts the stops are in low-speed configuration, between 160 and 380 kts the rudder deflection is limited as a function of speed, above 380 kts the stops are in high-speed configuration.

What is the purpose of the FTIS?. The FTIS gives protection to decrease the risk of the fire and explosion in the center fuel tank. The FTIS gives protection to decrease the risk of the smoke and explosion in the center fuel tank. The FTIS gives protection to decrease the risk of the fire and explosion on the wings fuel tank.

What statement is correct regarding to Trim Wheels?. The mechanical trim, which has priority over the electrical trim is operated from the side sticks. The mechanical trim, which has priority over the electrical trim is operated from the manual trim wheels. The electrical trim, which has priority over the mechanical trim is operated from the manual trim wheels.

Which computer is used for yaw control?. FAC. SEC & FAC. SEC.

Which hydraulic system operates nose wheel steering (Enhanced nodels)?. Yellow system. Blue system. Green system.

Why the sliding tube on the nose landing gear is inclined 9 degrees forward?. This design allows wheels to return freely to the centered position and decreased the braking effect. This design allows wheels to return freely to the centered position and decreased the shimmy effect. This design don't allows wheels to return freely to the centered position and decreased the shimmy effect.

What is the condition of the elevator servo control when is operating in damping mode?. Disconnected. Depressurized. Pressurized.

How are the DDVs controlled?. The ABCU send a current to the DDVs which is proportional to the brake pedals pressure. The BSCU send a current to the DDVs which is proportional to the brake pedals pressure. The ABCU send a voltage to the DDVs which is proportional to the brake pedals pressure.

The wing tip brakes are provided in order to?. Stop and lock the system when minor failures are detected, they are hydraulically activated and can only be reset on ground. Stop and lock the system when major failures are detected, are hydraulically activated and can only be reset on ground. Stop and lock the system when major failures are detected, they are electrically activated and can only be reset on flight.