Flight Controls Flashcards
In normal OPS, what controls the elevator and horizontal stabiliser? What happens if this fails?
In normal operations, ELAC2 controls the elevators and the horizontal stabilizer, and the green and yellow hydraulic jacks drive the left and right elevator surfaces respectively. THS is driven by No 1 of 3 electric motors.
If a failure occurs in ELAC2, or in the associated hydraulic systems, or with the hydraulic jacks, the system shifts pitch control to ELAC1. ELAC1 then controls the elevators via the blue hydraulic jacks and controls the THS via the N° 2 electric motor.
If neither ELAC1 nor ELAC2 is available, the system shifts pitch control either to SEC1 or to SEC2, (depending on the status of the associated circuits), and to THS motor N° 2 or N° 3.
What mechanical pitch control is available?
Pitch trim wheel which takes priority over electrical input.
What is the max deflection of the elevator and THS
Maximum elevator deflection is 30 ° nose up, and 17 ° nose down. The maximum THS deflection is 13.5 ° nose up, and 4 ° nose down.
How are the elevators actuated?
2 servo jacks controlling each elevator with 3 modes
Active :
The jack position is electrically-controlled.
Damping :
The jack follows surface movement.
Centering :
The jack is hydraulically retained in the neutral position.
What happens if an elevator servo jack fails?
If one elevator fails, the deflection of the remaining elevator is limited in order to avoid putting excessive asymmetric loads on the horizontal tailplane or rear fuselage.
If neither jack is being controlled electrically, both are automatically switched to the centering mode.
If neither jack is being controlled hydraulically, both are automatically switched to damping mode.
How is the stabilizer controlled?
A screwjack driven by two hydraulic motors drives the stabilizer.
The two hydraulic motors are controlled by :
One of three electric motors, or
The mechanical trim wheel.
How is the aircraft controlled about the roll axis? What is the max deflection?
One aileron and four spoilers on each wing control the aircraft about the roll axis.
The maximum deflection of the ailerons is 25 °.
The ailerons extend 5 ° down when the flaps are extended (aileron droop).
The maximum deflection of the spoilers is 35 °.
How are the spoilers and ailerons electrically controlled?
The ELAC 1 normally controls the ailerons.
If ELAC1 fails, the system automatically transfers aileron control to ELAC2.
If both ELACs fail, the ailerons revert to the damping mode.
SEC3 controls the N° 2 spoilers, SEC1 the N° 3 and 4 spoilers, and SEC2 the N° 5 spoilers.
If a SEC fails, the spoilers it controls are automatically retracted.
What happens if a spoiler fault is detected or hydraulic pressure is lost?
When a spoiler surface on one wing fails, the symmetric one on the other wing is inhibited.
If a fault is detected, the spoilers are retracted to their zero position.
If the system loses hydraulic pressure, the spoiler retains the deflection it had at the time of the loss, or a lesser deflection if aerodynamic forces push it down.
What spoiler panels are the speed brakes?
2, 3, 4
When are speed brakes inhibited? (6 cases)
SEC1 and SEC3 both are faulty, or
An elevator (L or R) is faulty, or
Angle-of-attack protection is active, or
Flaps are in configuration FULL, or
Thrust levers are above MCT position, or
Alpha Floor is activated.
The aircraft has achieved and is maintaining constant high alpha which has caused
speedbrake auto-retraction, how is speedbrake operation re-established?
If an inhibition occurs when the speedbrakes are extended, they retract automatically and stay retracted until the inhibition condition disappears and the flight crew resets the lever (the speedbrakes can be extended again 10 s or more after the lever is reset).
Under what conditions will spoilers extend in an RTO?
1 - If the ground spoilers are armed and the wheel speed exceeds 72 kt, the ground spoilers will automatically extend as soon as both thrust levers are reset to idle.
2 - If the ground spoilers are not armed and the wheel speed exceeds 72 kt, the ground spoilers will automatically extend as soon as reverse is selected on one engine (the other thrust lever remains at idle).
Under what conditions will the ground spoilers fully extend upon landing?
1) Spoilers armed and:
Both main landing gears on ground,
Both thrust levers at or below Idle position, or Reverse selected on at least one engine (and the other thrust lever below MCT position).
2) ground spoilers not armed and:
Both main landing gears on ground,
Reverse selected on at least one engine (and the other thrust lever below MCT position).
When do ground spoilers retract?
The ground spoilers retract:
After landing, when the ground spoilers are disarmed
After a rejected takeoff, when the ground spoilers are disarmed
During a touch and go, when at least one thrust lever is advanced above 20 °.
How is the rudder electrically controlled?
The yaw damping and turn coordination functions are automatic.
The ELACs compute yaw orders for coordinating turns and damping yaw oscillations, and transmit them to the FACs
How is the rudder actuated?
Three independent hydraulic servojacks, operating in parallel, actuate the rudder. In automatic operation (yaw damping, turn coordination) a green servo actuator drives all three servojacks. A yellow servo actuator remains synchronized and takes over if there is a failure.
There is no feedback to the rudder pedals from the yaw damping and turn coordination functions.
IF both FAC’s fail, what happens to the rudder limiter? How is this restriction
removed?
In the case of a failure that causes loss of the Rudder Travel limit system, the rudder deflection limit stops at the last value reached. At slats extension, full rudder travel authority is recovered.
What is demanded by a Pitch / Roll input on the sidestick in Flight?
Load factor / Roll Rate
