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A306, vicinity London Gatwick, 2011
From SKYbrary Wiki
On 12 January 2011, an Airbus A300-600 being operated by Monarch Airlines on a passenger flight from London Gatwick to Chania, Greece experienced activations of the stall protection system after an unintended configuration change shortly after take off but following recovery, the flight continued as intended without further event. There were no abrupt manoeuvres and no injuries to the 347 occupants.
It was found that after engine start, selection of the slats/flaps lever to obtain the required configuration of the wing for take off had led to the appearance of a system fault. A radio call to the Operator’s engineers had produced the advice that the system might require several resets to clear the fault. This reset process involved tripping and resetting the relevant circuit breakers and then moving the slats/flaps lever to check if the slats operated. Each time, the First Officer operated the slats/flaps as directed by the aircraft commander and the indicated repetition eventually produced the desired position of ‘15/15’ free of an ECAM fault annunciation. It was estimated that the First Officer had cycled the slats/flaps lever between positions ‘0/0’ and ‘15/15’ approximately six times. The possibility of the fault recurring on takeoff and the appropriate response, beginning with the cycling of the slats/flaps lever, was discussed.
Take off from Runway 08R with the aircraft commander as PF was uneventful but when he called for gear up, the First Officer moved the slats/flaps lever to 0/0 instead. The PF observed an unexpected primary flight display (PFD) indication of airspeed and initially suspected that there was a problem with the airspeed indication, but after checking his PFD airspeed against the standby ASI and confirming that the aircraft was at the pitch attitude and power setting required by the ‘Unreliable Airspeed’ procedure, he noticed that the landing gear selector was still down and so repeated the gear up call. The First Officer had then advised of the previous inadvertent retraction of the slats/flaps and selected the landing gear up.
The stall warning system had activated twice during the subsequent 10 seconds and each time the PF reduced the aircraft pitch attitude in response whilst maintaining a positive rate of climb. The aircraft had accelerated to climb speed and the flight then proceeded to destination without further event.