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Chairman of the Technical Commission of Inquiry into the accident with the aircraft Tu-204 RA-64047 Airline «Red Wings» informs about the results of the preliminary analysis of the information of objective control and other information received.
Approach was carried out on the runway 19 (length - 3060 m) from Vnukovo Airport. PF was the Captain. Before entering the glideslope the aircraft was in the landing configuration: Flaps - 37 °, slats - 23 °, and landing gear down. Decision height was set at 60 m, landing weight of the aircraft was approximately 67.5 tons, CG - ~ 26.5%, which doesn’t exceed the limits set by the AC flight manual.
Going through Before landing checklist Captain has identified the Vref speed as to be 210 km/h, and added that the actual speed should be set at 230 km/h. Descent took place in the FD mode with disabled automatic throttle with an average instrument speed of about 255 km/h and vertical speed -3 ... -5 m / s. Descent was performed without significant deviations from the glide path. NDB outer marker was passed at an altitude of 65 ... 70 m; threshold of the runway was overflown at the height of 15 meters and with airspeed of 260 km/h.
Landing of the aircraft was within 5 seconds after the TL (throttle) was set to "idle" at the speed of 230 km/h, at a distance of about 900 – 1000 m after passing the threshold, left main landing gear touched down first (left bank 1 ... 1.5 °), -and WoW signal from the left main gear was registered. During the landing of the aircraft wind gusts (from right side) reached up to ~ 11.5 m/s.
The maximum value of 1.12g on the FDR was recorded. It was about 10 seconds since the passage of the true height(absolute altitude) of 4 meters to touchdown.
3 seconds after first contact (by MLG) with the runway the nose gear touched down and WoW from it was registered. At that point in time no WoW signal from the right main landing gear was recorded.
Almost simultaneously with the nose landing gear touch down crew moved the TL(reversers) to the "maximum reverse" in one motion and applied the brakes (using pedals).
Reverse flaps of the engines didn’t deploy. Also auto-spoilers didn’t come out. After the TL were set to the "maximum reverse" engines N1 indication was showing ~ 90%, which actually corresponds to the nominal operation.
The pressure in the wheel brakes of the left landing gear (with strut compressed) was up to 50 kgf / cm ², the pressure in the right (no WoW signal) landing gear wheel brakes was missing.
Minimum airspeed to which aircraft has slowed after 7-8 seconds after touchdown was 200-205 km/h at ~ 0 ° pitch and roll of 1 ° to the left, after which the speed began to increase.
2 seconds after the transfer of TL(reverse) to the "maximum reverse" it was followed by a report from the flight engineer that reverse was inoperative.
TL(reverse) is in the "maximum reverse" about 8 seconds, then the reverse was turned off. During this time the airspeed increased to 240 km/h
The increase in the speed led to additional "unloading" of the main landing gear. With fluctuations of the roll (from 4.5 ° to 2.6 ° to the left to the right) strut compression occurred only to the left main gear, then separately to the right landing gear. Simultaneous strut compression of the both main landing gear did not occur.
Almost simultaneously with the turning off of the reverse, the pressure on the brake pedals was registered from left pilot seat (down to 60 °). As before, braking was ineffective - the pressure in the wheel brakes is applied only when WoW from the corresponding landing gear exists.
5 seconds after turning off the reverse, and after the words from flight engineer "Deploy Reverse! Reverse!” TL(for reverse) was registered to be set at full reverse for the second time.
As it happened during the first attempt, reverse deployment didn’t happen again, both engines again took to the regime of a direct thrust (N1 ~ 84%). No braking was happening, airspeed was at 230 ... 240 km / h (IAS). After 4 seconds the reverse was off.
At the time of re-engaging reverse thrust levers the aircraft was at distance of about 950 ... 1000 m from the exit threshold of the runway.
Within 6 seconds, reverse was in off position, at this time the crew attempted to use automatic brakes, (according to CVR) – several short commands can be heard on the recording – “Automatic braking turned on” (for primary and backup systems).
In the area of the exit threshold, TL (for reverse) was set to idle-reverse mode.
Aircraft exited the runway after 32 seconds from landing, with AC being on the center line, the IAS was at about 215 km/h during the process of rolling out.
Captain commanded to turn off the engines (using stop valves). The flight engineer switched off the valves after the command from the captain.
Further movement of the aircraft took place almost along the center line of the runway extension. After turning off the engines, when moving through snow surface (after departed the runway) AC started to slow down and due to irregular terrain surface simultaneous WoW signal from both main landing gear was registered. That led to the activation of spoilers and reverse mechanisms of the engines.
AC collided with the side of the slope at ground speed of about 190 km / h