AIRBUS FLIGHT CONTROL LAWS

AIRBUS FLIGHT CONTROL LAWS

High AOA Protection	Load Factor Limitation	Pitch Attitude Protection
NORMAL LAW
High Speed Protection	Flight Augmentation (Yaw)	Bank Angle Protection

Low Speed Stability	Load Factor Limitation
ALTERNATE LAW
High Speed Stability	Yaw Damping Only

	Load Factor Limitation
ABNORMAL ALTERNATE LAW w/o Speed Stability
	Yaw Damping Only

DIRECT LAW

FLIGHT CONTROL LAWS SUMMARY
NORMAL LAW
Normal operating configuration of the system. Failure of any single computer does not affect normal law. Covers 3-axis control, flight envelope protection, and load alleviation. Has 3 modes according to phase of flight.
Ground Mode	Active when aircraft is on the ground. Direct proportional relationship between the sidestick deflection and deflection of the flight controls. Is active until shortly after liftoff. After touchdown, ground mode is reactivated and resets the stabilizer trim to zero.
Flight Mode	Becomes active shortly after takeoff and remains active until shortly before touchdown. Sidestick deflection and load factor imposed on the aircraft are directly proportional, regardless of airspeed. With sidestick neutral and wings level, system maintains a 1 g load in pitch. No requirement to change pitch trim for changes in airspeed, configuration, or bank up to 33 degrees. At full aft/fwd sidestick deflection system maintains maximum load factor for flap position. Sidestick roll input commands a roll rate request. Roll rate is independent of airspeed. A given sidestick deflection always results in the same roll rate response. Turn coordination and yaw damping are computed by the ELACs and transmitted to the FACs. No rudder pedal feedback for the yaw damping and turn coordination functions.
Flare Mode	Transition to flare mode occurs at 50' RA during landing. System memorizes pitch attitude at 50' and begins to progressively reduce pitch, forcing pilot to flare the aircraft In the event of a go-around, transition to flight mode occurs again at 50' RA.
Protections	Load factor Limitation Prevents pilot from overstressing the aircraft even if full sidestick deflections are applied. Attitude Protection Pitch limited to 30 deg up, 15 deg down, and 67 deg of bank. These limits are indicated by green = signs on the PFD. Bank angles in excess of 33 deg require constant sidestick input. If input is released the aircraft returns to and maintains 33 deg of bank. High Angle of Attack Protection (alpha): When alpha exceeds alpha prot, elevator control switches to alpha protection mode in which angle of attack is proportional to sidestick deflection. Alpha max will not be exceeded even if the pilot applies full aft deflection High Speed Protection: Prevents exceeding VMO or MMO by introducing a pitch up load factor demand. The pilot can NOT override the pitch up command. Low Energy Warning: Available in CONF 2,3, or FULL between 100' and 2,000' RA when TOGA not selected. Produces aural "SPEED SPEED SPEED" when change in flight path alone is insufficient to regain a positive flight path (Thrust must be increased).
ALTERNATE LAW
If Multiple Failures of Redundant Systems occur, the flight controls revert to Alternate Law. The ECAM displays the message: ALTN LAW: PROT LOST
Ground Mode	The ground mode is identical to Normal Law.
Flight Mode	In pitch alternate law the flight mode is a load factor demand law similar to the Normal Law flight mode, with reduced protections. Pitch alternate law degrades to pitch direct law when the landing gear is extended to provide feel for flare and landing, since there is no flare mode when pitch normal law is lost. Automatic pitch trim and yaw damping (with limited authority) is available. Turn coordination is lost. When pitch law degrades from normal law, roll degrades to Direct Law - roll rate depends on airspeed.
Protections	All protections except for load factor maneuvering protection are lost. The load factor limitation is similar to to that under Normal Law. Amber XX's replace the green = attitude limits on the PFD. A low speed stability function replaces the normal angle-of-attack protection System introduces a progressive nose down command which attempts to prevent the speed from decaying further. This command CAN be overridden by sidestick input. The airplane CAN be stalled in Alternate Law. An audio stall warning consisting of "crickets" and a "STALL" aural message is activated. The Alpha Floor function is inoperative. The PFD airspeed scale is modified: VLS remains displayed VALPHA PROT and VALPHA MAX are removed They are replaced by a red and black barber pole, the top indicating the stall warning speed VSW A nose up command is introduced any time the airplane exceeds VMO/MMO to keep the speed from increasing further, which CAN be overridden by the sidestick. Bank angle protection is lost. Certain failures cause the system to revert to Alternate Law without speed stability. Yaw damping is lost if the fault is a triple ADR failure.
ABNORMAL ALTERNATE LAW
Abnormal Alternate Law is activated if the airplane enters an unusual attitude, allowing recovery from the unusual attitude.
	Pitch law becomes Alternate (without autotrim or protection other than Load Factor protection). Roll law becomes Direct law with mechanical yaw control. After recovery from the unusual attitude, the following laws are active for the remainder of the flight: Pitch: Alternate law without protections and with autotrim. Roll: Direct law Yaw: Alternate law There is no reversion to Direct law when the landing gear is extended.
DIRECT LAW
Direct law is the lowest level of computer flight control and occurs with certain multiple failures.
	Pilot control inputs are transmitted unmodified to the control surfaces, providing a direct relationship between sidestick and control surface. Control sensitivity depends on airspeed and NO autotrimming is available. An amber message USE MAN PITCH TRIM appears on the PFD. If the flight controls degrade to Alternate Law, Direct Law automatically becomes active when the landing gear is extended if no autopilots are engaged. If an autopilot is engaged, the airplane will remain in Alternate Law until the autopilot is disconnected. There are no protections provided in Direct Law, however overspeed and stall aural warnings are provided. The PFD airspeed scale remains the same as in Alternate Law.
MECHANICAL BACKUP
In case of a complete loss of electrical flight control signals, the aircraft can be temporarily controlled by mechanical mode.
	Pitch control is achieved through the horizontal stabilizer by using the manual trim wheel. Lateral control is accomplished using the rudder pedals. Both controls require hydraulic power. A red MAN PITCH TRIM ONLY warning appears on the PFD.