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R  F. Low Energy Warning 
R  (1) General 
R  The Low Energy Function is to prevent the A/C from entering a low 
R  energy situation by alerting the pilot through an audio warning: 
R  "SPEED...SPEED...SPEED". 
R  Pilot has to increase thrust and low energy warning disappears as 
R  soon as: 
R  - Thrust level is high enough or 
R  - Alpha floor protection is triggered or 
R  - Pitch go around mode is triggered. 
R  Low energy warning is available in configuration 2, 3 and FULL and 
R  between 100 ft and 2000 ft RA. 
R  (Ref. Fig. 013) 
R  (2) Warning 
R  (Ref. Fig. 014) 
R  A combination of angle-of-attack, flight-path angle and deceleration 
R  is computed and compared to a threshold, depending on slat/flap 
R  configuration, typically 0.4 deg. to 1 deg. lower than alpha floor 
R  threshold. 
R  When the result of the combination is above this threshold for more 
R  than 0.5 sec, low energy condition is triggered for at least 3 sec 
R  and sent to the FWC that elaborates the audio warning. 
R  (3) System aspects 
R  The low energy detection is not duplicated.

 1EFF : ALL 1 22-64-00Page 28 1 1 Feb 01/05 1 1 1CES 1

 MCDU - AFS/Windshear Test
 Figure 012

 1EFF : ALL 1 22-64-00Page 29/30 1 1 May 01/04 1 1 1CES
1

R  Low Energy Warning Principle Figure 013
 1EFF : 1 1 1CES  ALL  1 111 22-64-00 Page 31 Feb 01/05

 

R  Low Energy Warning Architecture Figure 014
 1EFF : 1 1 1CES  ALL  1 111 22-64-00 Page 32 Feb 01/05

 

 ENGAGEMENT AND INTERNAL MONITORING - DESCRIPTION AND OPERATION
______________________________________________________________
 1. General
_______ Each Flight Augmentation Computer (FAC) includes two independent computation channels with digital processors. The engagement and monitoring principles ensure:
 -Safe operation through the failure detectors
 -Maximum availability through the reconfigurations further to failures. These principles are:
 -Duplication of the monitoring circuits (engage and monitoring logic)
 -Utilization of hard-wired logic for the sensible parts of the system (engage circuit, actuator control circuit, circuit of global internal monitoring)
 -
Monitoring of the peripherals by the FAC: . Failures detected by self-test through monitoring of the parameter status matrix. These failures are not latched. . Failures not detected by self-test which deal with critical information through comparison of different sensors (two-by-two comparison or passivation through voters) or validation of a data bus by a hard-wired discrete.

 -
Monitoring of the computer by self-monitoring of the computation channels (comparison) specific monitoring: . Aircraft 28V power-supply application software (real-time monitor) . Watchdog . ARINC sequencers . Oscillation detectors transmission monitoring.

 2. System Description
__________________
 Each FAC comprises these devices for function monitoring:

 -An engagement device per FLT CTL/FAC pushbutton switch common to the yaw damper, rudder trim and rudder travel limiting functions.
 -Global internal monitoring of the computer in software (real-time monitor) and hard-wired circuitry (FAC HEALTHY, watchdog)
 -
Monitoring specific to the functions fulfilled: . In the software . In the hard-wired circuitry for the actuator controls, the changeover signals and the warnings.

 -
Monitoring of reconfiguration of certain peripherals

 -
Monitoring of sensors. Each monitoring circuit is duplicated (one logic in the command channel and another one in the monitoring channel). Some signals are exchanged between the two channels in the hardware and software parts (watchdog, power supply monitoring). The logic circuits specific to the functions lead to the loss of the considered function without illumination of the FAULT legend. The result of the failure is memorized in flight only (engine-running signal to allow or not allow the reset).

 1EFF : ALL 1 22-65-00Page 1 1 1 Feb 01/98 1 1 1CES 1 The logic circuits common to all the functions lead to the total loss of the FAC with illumination of the FAULT legend. The result of the failure is memorized in a material flip-flop. The reset will be possible only upon manual action by the pilot on the FLT CTL/FAC pushbutton switch. This action reactivates the watchdog and the microprocessor. The whole computer can be disengaged through action on the pushbutton switches.
　
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