Aircraft is on ground for 30 seconds and the aileron trim is not correctly configured for take-off.

Aircraft is on ground and the flaps are not correctly configured for take-off.

Aircraft is on ground for 30 seconds and the rudder trim is not correctly configured for take-off.

Aircraft is on ground and the spoilers are not correctly configured for take-off.

Aircraft is on ground and the stabilizer trim is not correctly configured for take-off.

Pitch disconnect has occurred when the aircraft is in take-off configuration.

Roll disconnect has occurred when the aircraft is in take-off configuration.

The stall warning computer has sensed a limit angle of attack.

Elevator has a split of more than 7.5 degrees

FCU senses a malfunction in the flap system which can not be corrected in flight.

FCU senses a malfunction in the flap system which can be corrected in flight.

Flaps normal hydraulic pressure is low.

Flight spoilers are deployed below 500ft (not on ground) and/or the throttles are above idle (not on ground).

Flight spoilers have failed.

Inboard or outboard flight spoilers have failed.

Ground spoilers are not armed and not set OFF.

Ground spoilers have failed.

Mach trim has failed.

Primary channel of the stab trim has failed.

Roll assist function has failed.

Inboard or outboard roll spoilers have failed.

Roll spoiler switch is set to OFF and the roll disconnect switch is not set to disconnect.

Rudder limiter has failed.

Secondary channel of the stab trim has failed.

Spoilers have failed.

A fault that causes the loss of redundancy has occurred in the spoiler system but does not affect spoiler operation.

SPC has sensed a fail condition.

MSW on one or the other control wheel has been pushed for longer than 10s.

There is a small malfunction in the flap system which does not stop the operation of the flaps.

FCU controls the flap system at a lower speed than the nominal speed.

Left stall shaker has failed.

Right stall shaker has failed.

A minor failure that causes the loss of redundancy has occurred in the rudder limiter system.

A fault that causes the loss of redundancy has occurred in the spoiler system but does not affect spoiler operation.

Stab Trim system has lost redundancy.

SPC has sensed a fault and has reverted to a default flap settings of 30 degrees.

SPC has sensed a fail condition.

Ground spoilers are set OFF.

Pitch disconnect has occurred when the aircraft is not in take-off configuration.

Roll disconnect has occurred when the aircraft is not in take-off configuration.

Roll spoiler switch is set to OFF and the roll disconnect switch is set to disconnect.

Rudder travel limiter system does the manually started system test.

Secondary channel of the horizontal stabilizer (pitch) trim system is set.

STAB TRIM switch is set OFF.

MSW on one or the other control wheel has been pushed for less than 10 seconds or the pusher has been inhibited by the STALL PUSHER PBA.