Rostov oblast

The right engine caught fire during takeoff for unknown reasons.

The fatal air accident to the Boeing 737-8KN A6-FDN aircraft occurred during the second go around, due to an incorrect aircraft configuration and crew piloting, the subsequent loss of PIC’s situational awareness in nighttime in IMC. This resulted in a loss of control of the aircraft and its impact with the ground. The accident is classified as Loss of Control In-Flight (LOC-I) occurrence.
Most probably, the contributing factors to the accident were:
- The presence of turbulence and gusty wind with the parameters, classified as a moderate to-strong "windshear" that resulted in the need to perform two go-arounds;
- The lack of psychological readiness (not go-around minded) of the PIC to perform the second go-around as he had the dominant mindset on the landing performance exactly at the destination aerodrome, having formed out of the "emotional distress" after the first unsuccessful approach (despite the RWY had been in sight and the aircraft stabilized on the glide path, the PIC had been forced to initiate go-around due to the windshear warning activation), concern on the potential exceedance of the duty time to perform the return flight and the recommendation of the airline on the priority of landing at the destination aerodrome;
- The loss of the PIC’s leadership in the crew after the initiation of go-around and his "confusion" that led to the impossibility of the on-time transition of the flight mental mode from "approach with landing" into "go-around";
- The absence of the instructions of the maneuver type specification at the go-around callout in the aircraft manufacturer documentation and the airline OM;
- The crew’s uncoordinated actions during the second go-around: on the low weight aircraft the crew was performing the standard go-around procedure (with the retraction of landing gear and flaps), but with the maximum available thrust, consistent with the Windshear Escape Maneuver procedure that led to the generation of the substantial excessive nose-up moment and significant (up to 50 lb/23 kg) "pushing" forces on the control column to counteract it;
- The failure of the PIC within a long time to create the pitch, required to perform go around and maintain the required climb profile while piloting aircraft unbalanced in forces;
- The PIC’s insufficient knowledge and skills on the stabilizer manual trim operation, which led to the long-time (for 12 sec) continuous stabilizer nose-down trim with the subsequent substantial imbalance of the aircraft and its upset encounter with the generation of the negative G, which the crew had not been prepared to. The potential impact of the somatogravic "pitch-up illusion" on the PIC might have contributed to the long keeping the stabilizer trim switches pressed;
- The psychological incapacitation of the PIC that resulted in his total spatial disorientation, did not allow him to respond to the correct prompts of the F/O;
- The absence of the criteria of the psychological incapacitation in the airline OM, which prevented the F/O from the in-time recognition of the situation and undertaking more decisive actions;
- The possible operational tiredness of the crew: by the time of the accident the crew had been proceeding the flight for 6 hours, of which 2 hours under intense workload that implied the need to make non-standard decisions; in this context the fatal accident occurred at the worst possible time in terms of the circadian rhythms, when the human performance is severely degraded and is at its lower level along with the increase of the risk of errors.
The lack of the objective information on the HUD operation (there were no flight tests of the unit carried out into the entire range of the operational G, including the negative ones; the impossibility to reproduce the real HUD readings in the progress of the accident flight, that is the image the pilot was watching with the consideration of his posture in the seat trough the stream video or at the FFS) did not allow making conclusion on its possible impact on the flight outcome. At the same time the investigation team is of the opinion that the specific features of the HUD indication and display in conditions existed during final phase of the accident flight (severe turbulence, the aircraft upset encounter with the resulting negative G, the significant difference between the actual and the target flight path) that generally do not occur under conditions of the standard simulator sessions, could have affected the situational awareness of the PIC, having been in the highly stressed state.

The reason for the accident with An-2 RA-84553 was performing a flight in a known defective aircraft, leading to engine failure and the need for in-flight forced landing, during which there was a collision with power lines, followed by a rough landing that led to the structural failure and fire. Investigation to determine the cause of the engine failure was not possible due to the failure to ensure the safety of the aircraft after the accident and the absence of operational and technical documentation. The adoption of the decision by the pilot to reject takeoff after detecting a loss engine power on the takeoff could have prevented the accident. The aircraft did not have a valid Certificate of Airworthiness and the time between overhauls had been exceeded on 10 April 2015.

Loss of engine power for unknown reasons.

Engine failure for unknown reasons.

The Federal Safety Board (FSB) reported 3 days later that the accident was the consequence of the explosion of a bomb. Two women flying from Makhatshala landed in Moscow at 1945LT and were able to embark with the explosive device following security deficiencies. Traces of hexogene were found on debris.

Following a wrong manipulation, the flight engineer activated the thrust reversers on engine n°1 and n°3 but not on the engine n°2 that was providing full power. Such configuration reduced the braking action and the crew was unable to stop the aircraft within the landing distance available.

Birdstrike.