Landing (descent or approach)

The crew was completing a cargo service from Khmelnytskyi to Samara with an intermediate stop in Donetsk. The approach was completed by night and limited visibility due to thunderstorm activity and heavy rain falls. On final, the crew failed to realize the aircraft was not properly aligned and continued the approach when the aircraft landed hard 80 metres to the left of the runway. Out of control, it rolled for few dozen metres and eventually collided with a building. The aircraft was destroyed and all five occupants were seriously injured.

Because of the failure of the thrust reverser relay circuit board, the thrust reversers failed to deploy when selected by the pilot. Because the reversers failed to deploy, the 'reversers in transition' lights, and the 'reversers deployed' lights did not illuminate. Even though the aircraft flight manual warns against moving the reverser throttle levers into the power range without the illumination of these lights, the pilot did so anyway. The pilot continued to select reverse power even after the activation of the throttle mismatch warning horn, resulting in an increase in forward thrust while attempting to stop. During this sequence of events the second-in-command moved the parking brake lever to full override, locking the main wheel brakes and overriding the antiskid system.

On final approach to Aldan Airport, at a speed of 196 km/h, the crew extended the flaps to 42° when the aircraft adopted a 42,5° nose-up attitude. The crew elected to go-around but, as the speed dropped to 52 km/h, the aircraft stalled and crashed 273 metres short of runway and 160 metres to the left of its extended centreline. The aircraft was destroyed by impact forces and all 24 occupants were killed.

Flight 808 took off from Norfolk at 14:13 for a cargo flight to Guantánamo Bay. The flight and arrival into the Guantánamo terminal area was uneventful. At 16:34, while the flight was descending from FL320, radio contact was established with the Guantánamo radar controller. The radar controller instructed flight 808 to maintain VFR 12 miles off the Cuban coast and report at East Point. The runway in use was runway 10. The flight crew then requested a runway 28 approach, but changed this back to a runway 10 approach a couple of minutes later. Clearance was given at 16:46 with wind reported at 200°/7 knots. The runway 10 threshold was located 0,75 mile East of Cuban airspace, designated by a strobe light, mounted on a Marine Corps guard tower, located at the corner of the Cuban border and the shoreline. On the day of the accident, the strobe light was not operational (both controller and flight crew were not aware of this). The aircraft was approached from the south and was making a right turn for runway 10 with an increasing angle of bank in order to align with the runway. At 200-300 feet agl the wings started to rock towards wings level and the nose pitched up. The right wing appeared to stall, the aircraft rolled to 90deg. angle of bank and the nose pitched down. The aircraft then struck level terrain 1400 feet west of the approach end of the runway and 200 feet north of the extended centreline.

On an approach to land at the destination, the second-in-command (sic) was flying the airplane. The plane touched down with the landing gear retracted, and the propeller blades contacted the runway. The sic initiated a go-around (aborted landing). Witnesses saw the airplane in a steep left bank just before impact in a river next to the airport. Propeller strikes on the runway extended 380 feet, indicating a touchdown speed of 96 knots. The last propeller strikes on the right side indicated a speed of 86 knots. The last strikes on the left side indicated a slowing propeller. Published VMC for the airplane was 94 knots. The CVR tape revealed the crew completed a descent arrival check, performed an incomplete approach briefing, and did not perform a before landing check. The CVR revealed no sound of a gear warning horn. Company personnel stated that the circuit breaker for the warning horn had been found pulled at the completion of previous flights by other crew; this was to prevent a warning horn from sounding during a high rate of descent. Both pilots were killed.

After landing, the single engine aircraft deviated to the right, causing the right main gear to struck a ditch and to be torn off. The aircraft came to rest on its belly and was damaged beyond repair. All seven occupants escaped with minor injuries.

The instrument flight was cleared for an ILS approach to the destination airport. While maneuvering for the final approach course, the flight encountered convective activity (thunderstorms). The pilot was questioned by the tower concerning his position on the approach course. The tower radar placed the flight's position 1/4 to 1/2 mile east of the final approach course. The pilot stated that he was on the localizer. Subsequent functional checks of the ils system by air ways facilities, failed to reveal a problem with the ils approach system. The airplane collided with trees about one and one half miles northeast of the airport and one half mile east of the approach course. Weather reports recorded level four thunderstorm activity within the immediate vicinity of the destination airport. Wreckage examination failed to disclose any mechanical problems with the airplane. The air traffic controllers provided the pilot with current weather conditions at the airport throughout the final minutes of the flight, therefore the pilot was aware of the thunderstorm activity near and at the airport. All four occupants were killed.

On August 2, 1993, at 1500 Alaska daylight time, an amphibious Cessna 208 airplane, N9526F, operated by MarkAir, Inc., nosed over after landing on the water with the wheels extended at Geographic Harbor, located about 75 miles west of Kodiak, Alaska. The commercial pilot, the sole occupant, sustained minor injuries, and the airplane was substantially damaged. The unscheduled domestic cargo flight, operating under 14 CFR Part 135, departed King Salmon, Alaska at 1426. Visual meteorological conditions existed, and a company VFR flight plan was filed.
During a telephone conversation with the pilot shortly after the accident, he stated that he "just failed to use and comply with the airplanes checklist to ensure that the wheels were retracted for the water landing". He further stated that he was very distracted and preoccupied with several other mission related activities.

While descending to Bharatpur Airport, the crew encountered poor weather conditions. Too low, the aircraft struck the slope of a rocky peak located about 6,5 km short of runway 15 threshold. The aircraft was destroyed and all 19 occupants were killed.

The Rockwell 690A, N707BP, was flying a straight-in entry to a downwind leg for runway 19 at the non-controlled airport. The only radio call heard from the Rockwell was a request for an airport advisory when it was about 20 miles southeast. The Piper PA-28R, N33056, had departed from runway 19. No radio calls were heard from the Piper. Witnesses observed the Rockwell heading north and the Piper heading east moments before the collision. The witnesses stated the Piper pitched up and banked steeply moments before the collision. The collision occurred approximately 2 miles east-southeast of the airport. On-scene investigation showed that the Piper's left main landing gear tire had made an imprint on the bottom of the Rockwell's outboard left wing. Paint color from the Rockwell had transferred to the Piper's left wing skin. All six people in both aircraft were killed.