In normal operation, most A340 flight controls are:
Electrically controlled and hydraulically actuated.
All A340 flight controls are actuated by hydraulic servos which are controlled by computers:
But the stabilizer and rudder servos may also be controlled by cables.
Which of the following statements is correct concerning the spoiler elevator computers (SEC's)?
Three computers which achieve spoiler control and standby elevator and THS control.
The autopilot will disconnect if the side stick takeover push button is depressed.
Ailerons are deflected down when flaps are:
The sidestick inputs result in adjusting:
The pitch, roll, and yaw (for turn coordination).
Flight control normal law provides:
3 axis control
Flight envelope protection
Maneuver load alleviation
The rudder is actuated by _____ independent hydraulic jacks which operate in parallel.
Which of the following statements are correct concerning the side stick takeover push button?
Both are correct.
Are there any control surfaces with a mechanical backup?
Yes, the THS and the rudder.
What control surfaces do the FACs control?
Pitch control is provided by:
Two independent elevators and a Trimmable Horizontal Stabilizer (THS)
Which of the following will automatically reset after landing?
Both are correct.
What happens in the event of an single ELAC failure?
The functions of the failed ELAC will be assumed by the remaining ELAC.
The alpha speed lock function:
Will inhibit slat retraction during an inadvertent movement of the flap selector at high AOA or low speeds.
In normal law, if one stick is rapidly pulled fully back, can the aircraft's maximum allowable 'G' load be exceeded?
No. The load factor limitation overrides side stick commands to avoid excessive 'G' loads.
The ailerons are each actuated:
Two hydraulic servos, each powered by one of the three hydraulic systems.
Each aileron hydraulic servojack has two control modes: active and damping.
Which controls are used for the mechanical backup?
THS and rudder.
Mechanically backed-up control surfaces:
Require hydraulic power for actuation.
Selection of flaps one prior to takeoff will select which of the following?
Slats 1 and flaps 1 (1+F).
Which of the following statements best describes the Load Alleviation function(LAF)?
Relieves wing structure loads by deflecting the ailerons and spoilers.
When ground spoilers deploy automatically:
All ten spoiler panels fully deploy.
The slats alpha / speed lock function inhibits slats retraction at high angle-of-attack and/or low speed.
Each SEC provides at least:
Direct control law, rudder trim, yaw damper, rudder and rudder pedals travel limits.
The FAC's primarily control which control surface?
Pitch altitude is limited to ______ nose up.
Pitch altitude is limited to _____ nose down.
Which altitude limitation is associated with high lift devices?
Max altitude for extension is 20, 000 ft.
Let's assume the aircraft is in a slight climb in Normal Law. Immediately after the pilot releases the stick to neutral, the flight control will:
Maitain the current flight path.
You are in a 45 degree bank and the aircraft has entered high speed protection. If the stick is released to neutral position, the aircraft will:
Roll to 0 degree of bank (wings level)
The message WING TIP BRK ON appears on the E/WD. What does it mean?
A hydraulic device locks the flaps in their present position.
Where does the SFCCs obtain AOA and air data information from?
How many actuators are provided to control the ailerons and how many hydraulic sources supply these actuators?
2 hydraulic sources with 4 actuators.
If both FAC's fail, what happens to the rudder limiter?
It freezes at its present position and assumes the low speed position when flaps 1 are selected.
Normal pitch control uses:
PRIM 1, the elevator green hydraulic jacks, and the number 1 THS electric control motor.
Which of the following statements is correct concerning the elevator aileron computers (ELAC's)?:
Two computers which achieve normal and standby control of the elevators, ailerons, and trimmable horizontal stabilizer.
The wing tip brakes, once activated:
Lock only the affected high lift system surfaces in their current position
Which of the following controls and monitors flaps and slats?
Two slat flap control computers (SFCC's).
The spoiler panels are the only flight control surfaces with no redundant control.
Occurs when the flaps are extended and is a single droop setting.
What happens in the side stick-neutral high speed protection mode?
The autopilot disengages, bank angle limit is 45� and the aircraft rolls wings level and pitches up to slow down to VMO/MMO.
Can the crew make a flight control inmput that will over-stress the airplane in direct law?
Yes, there are no protections provided in direct law.
The stabilizer is actuated by a screw jack driven by two hydraulic motors, which in turn are controlled by:
One of three electric motors
A mechanical trim wheel
Both are correct.
Can you manually trim the rudder with the autopilot engaged?
When is the Flight Mode active?
From liftoff until flare mode engages at 50 ft RA.
OVER SPEED ECAM warning is provided at:
None of the above.
Automatic pitch trim is provided both on ground and in flight.
It is only active when the aircraft is in flight
The Ground Mode is different in Alternate Law.
It is the same as in Normal Law.
In normal law, what is the maximum bank angle you can reach with the side stick fully deflected?
Failure to retract the flaps after takeoff will:
Result in automatic flap retraction.
MLA (maneuver load alleviation) becomes active when side stick is pulled less than 8 degrees and the load factor is more than 2 g.
FAC generated slat and flap extension, retraction, and limiting speeds are visually displayed on which of the following?
The MCDU perf page.
The lower ECAM F/CTL page.
Both pilot's PFD airspeed displays.
The wing tip brakes are:
Selection of flaps 1 in flight will select which of the following configurations?
Slats 1 and flaps 0 (1).
The aircraft rudder can be manually trimmed with the autopilot engaged.
What happens if you release the stick at 40 degrees of bank?
The aircraft rolls back to 33� and resumes flight path stability.
The elevators are ______ controlled.
When is alpha floor not available?
Out of normal law.
Below 100 feet RA in landing configuration.
If the A/THR is deactivated or unavailable.
What kind of protections are provided if the aircraft is in Alternate Law?
G-load protection and speed stability if the ADIRS and elevators are working.
In Normal Law, what are the limits of Pitch Attitude protections with flaps Full
25� nose up, progressively reduced to 20� at low speed.
The rudder trim rotary switch is not active when autopilot is engaged.
You can degrade directly from Normal Law to Direct Law with gear down and a dual radio altimeter fault.
When do you get FLARE Mode in Alternate Law?
Never. It goes directly from Alternate Law to Direct Law when the gear is selected down.
Turn coordination is available in Alternate Law.
You get yaw damping only.
If both pilots deflect their side sticks fully back:
The 'pitch up' order is equal to a single stick deflection.
To disable a side-stick, you have to depress the red take-over button on the active stick. Holding the button down for 40 seconds will electrically lock the other stick out until its own red take-over button is pushed again.
Let's assume the F/O presses his takeover pushbutton and releases it after more than 40 seconds.
The Captain's side stick is de-activated unless he presses his takeover pushbutton.
The speed brakes are _____ controlled.
Ailerons max deflection is:
If neither PRIM 1 nor PRIM 2 are available, pitch control is transferred to:
SEC 1 for elevator control and PRIM 3 using the number 3 electric motor for THS control.
What happens to the rudder limits if both FAC's fault?
The limit freezes at the fault condition until Flaps 1 is selected. Then it resets to the low speed limits for increased control.
What happens to high speed (VMO/MMO) when you are in Alternate Law?
VMO is reduced to 320 kt and MMO does not change.
If all three PRIM computers are not available with B or Y hydraulic system available:
The THS is controlled by the manual pitch trim wheel only.
Spoilers max deflection is:
Can the rudders be moved with both FAC's inoperative?
Yes, if both FACs fail, maximum rudder deflection can be obtained when the slats are extended
On one control surface if an active servo jack fails
The damped servo jack on the same surface becomes automatically active.
If an active servo jack fails, the damped one becomes active. The failed jack is automatically switched to the damping mode.
The FLAP lever sends signal to Slat Flap Control Computer (SFCC) to command movement.
Is there any rudder pedal feedback for the yaw damping and turn coordination functions?
When the RAT is extended to recover hydraulic pressure or electrical power, the servo jacks that revert to damping mode control:
The outboard ailerons.
The speedbrake surfaces are:
Spoilers 1 to 6.
The autopilot function is lost in case of:
PRIM 1+2+3 failure with SEC 1+2 available
Each PRIM provides:
Normal, alternate and direct laws, speed brake and ground spoiler control logic, characteristic speed computations.
For elevators control, each servo jack has:
3 control modes: Active, Damping and Centering.
When you set rudder trim, the input:
Is fed back to the rudder pedals.
Loss of hydraulic power to one of the single spoiler servos will cause that surface to:
Remain at the existing deflection or less if pushed down by aerodynamic forces.