From MAK
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 runway 19 (length - 3060 m) to Vnukovo Airport. Piloting was carried by PIC. Before entering the glide the aircraft was in the landing configuration: Flaps - 37°, slats - 23°, and landing gear extended. Setpoint decision height was set at 60m, landing weight of the aircraft was approximately 67.5 tons, alignment - ~ 26.5%, which is not to exceed the limits set by Flight Manual.
During preplant preparation PIC has identified the target speed of the glide path as 210 km / h, with the PIC said that the need to withstand 230 km / h Reduction took place on the final approach in the director mode with disabled automatic throttle with an average speed of about instrument 255 km / h and vertical speed -3 ... -5 m / s. Reduction was performed without significant deviations from the glide path. Inner beacon marker was passed at an altitude of 65 ... 70 m, end of the runway (runway) was passed at the height of 15 meters and air speed of 260 km / h
Landing of an aircraft was within 5 seconds after the thrust lever (throttle) to mode "idle" at the speed of 230 km / h, at a distance of about 900 m from the 1000 input threshold, ahead of the left landing gear (left bank 1 ... 1.5 °), while there was a signal compression left strut. During the landing of the aircraft on the right side wind gusts reached up to ~ 11.5 m / s. The maximum value of the vertical congestion at touchdown was 1.12g on the record of objective control (hereinafter - MSRP). Since the passage of the true height of 4 meters to touchdown was about 10 seconds.
3 seconds after touchdown nose landing gear was lowered and there was signal of nose landing gear strut compression. Signal of compression of right landing gear strut at this stage not yet formed.
Almost simultaneously with the lowering of the nose landing gear crew moved the controls throttle engines to the "maximum reverse" in one motion and applied the brake pedal on.
Opening of valves reversing system on both engines did not happen. Also did not happen automatically release air brakes and spoilers. Issue spoilers manually crew did not make.
After the transfer of throttle to the "maximum reverse" mode registered an increase with both motors (forward thrust) to the regime Nvd ~ 90%, which actually corresponds to the nominal operation.
The pressure in the wheel brakes left (compressed) landing gear was up to 50 kgf / cm ², the pressure in the wheel brakes right (not compressed) landing gear was missing.
Minimum airspeed to which aircraft slowed after 7-8 seconds field landing was 200-205 km / h at ~ 0 ° pitch and roll of 1 ° to the left, after which the rate began to increase.
2 seconds after the transfer of throttle to the "maximum reverse" flight engineer reported on the non-inclusion of a reverse.
Throttle is in the "maximum reverse" for about 8 seconds, then the reverse was off. During this time the airspeed increased to 240 km / h
The increase in speed of the instrument 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) compression occurred then left, then right landing gear. Simultaneous compression of both main landing gear did not happen. Almost simultaneously with the reversal recorded off compression of brake pedal by left pilot to 60 °. As before braking was ineffective - the pressure in the wheel brakes was applied only when the landing gear strut is compressed.
5 seconds after turning off the reverse, a flight engineer after the words "Turn of Reverse! Reverse!". Registered retransfer throttle to "maximize reverse." As the first attempt, including the reverse has happened, both engines again took to the regime of a direct link (Nvd ~ 84%). Aircraft braking happening, airspeed was 230 ... 240 km / h After 4 seconds the reverse was off. At the time of re-enable reverse the aircraft was a distance of about 950 ... 1000 m from the exit threshold.
Within 6 seconds, reverse is in the off position, at this time the crew attempted to automatic braking, as evidenced by The in talks crew and transient appearance of single commands: "Automatic braking inclusive" for primary and backup subsystems.
In the area of the output threshold throttle were transferred to a small reverse mode.
Rolling out the aircraft as the runway was over 32 seconds after landing, almost on its axis, the air speed of about 215 km / h In the process of rolling out at the command of PIC flight engineer turned off the engine by means of the emergency brake.
Further movement of the aircraft took place almost on the runway extended. After turning off the engine, by braking when driving on snow cover for the runway and arrivals on irregularities occurred simultaneously compress the left and right main landing gear. Compression main landing gear led to the automatic release of air brakes and spoilers, as well as to roll direction valves engine thrust reverser. Clash of the plane with the slopes of ravines happened to ground speed of about 190 km / h
Last edited by Bandures; 24th Jan 2013 at 14:22.