Country
code
West Sussex
Crash of a Beechcraft E90 King Air in Goodwood
Date & Time:
Apr 22, 1985 at 1053 LT
Registration:
G-BHUL
Survivors:
Yes
Schedule:
Elstree - Goodwood
MSN:
LW-83
YOM:
1974
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total hours on type:
1036.00
Circumstances:
The aircraft took off on the grass runway 06 with the P U/S in the left seat as handling pilot. The visibility was good, with high cloud cover, and wind recorded as from 060° to 080° at 20 to 30 knots, gusting to 35 knots. During the initial climb, PI simulated an engine failure, and after the touch drills and climb out were established, restored power to the 'failed' engine. The climb was continued to 2,500 feet and an engine failure was again simulated before an NDB approach was made to runway 33. P U/S then executed a single engined missed approach on completion of the let down, and entered the runway 06 circuit pattern. When at the downwind position he called 'downwind full stop'. The aircraft continued to the final approach with the simulated failed engine at a zero thrust setting of 120 feet lb torque and 1800 rpm. The P U/S stated that he had some difficulty in stabilising the approach and controlling the airspeed in the gusty conditions. At approximately 300 feet agl he was not satisfied with the approach and initiated a single engined go-around, raising gear and flaps. At some later stage PI took control and pushed the two throttle and rpm levers fully forward. P U/S remembers the aircraft entering a spiral descent to the left, and both pilots remember their evacuation of the aircraft. However, they have to recollection of airspeed, height, which engine was 'failed' on either occasion, or indeed the event which prompted PI to take control. The aircraft was seen to overfly the airfield in a north easterly direction with gear and flaps raised, and at a height variously estimated as between 100 and 300 feet agl. Just outside the airfield boundary the aircraft was seen to roll to the right then roll, or yaw and roll to the left and enter a spiral descent into an open field. The left wing tip struck the ground at an angle of 30° to the surface of the field, the aircraft then yawed left through 90° and slid and rolled a further 45 yards. It came to rest almost inverted and on its right side, with the detached left wing lying alongside the stub of the right wing. Both pilots were seriously injured.
Probable cause:
The wreckage of the aircraft was removed to the AIB facility at Farnborough for further examination which included an inspection of controls and control runs, and stripping the engines and propellers. No significant fault or failure was found. The airspeed indicators were also calibrated and found to be accurate.
Final Report:
Crash of a De Havilland DH.104 Dove 2A in Shoreham-by-Sea: 1 killed
Date & Time:
Jul 9, 1983 at 1005 LT
Registration:
G-AMYP
Survivors:
No
Schedule:
Shoreham-by-Sea - Shoreham-by-Sea
MSN:
04421
YOM:
1953
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total hours on type:
13.00
Circumstances:
The pilot, also owner of the aircraft, elected to make a post-engine change test flight himself. After takeoff from Shoreham-by-Sea Airport runway 07 in good weather, eye-witnesses considered that the take-off and initial climb were normal except that intermittent puffs of dark smoke were seen coming from the right engine. At about 600 feet above ground level the aircraft was seen to roll to the right then turn on to its back and spin to the ground. After a short pause the aircraft burst into flames and was largely consumed by an intense fire. The pilot, sole on board, was killed.
Probable cause:
Examination of the wreckage revealed that the aircraft impacted with the sloping side of the west flood bank of the River Adur. At impact the aircraft was 60° nose down, rolled to the right, and was yawing to the right. Both engines were rotating, with the left engine developing more power than the right. Detailed wreckage examination at the AIB engineering facility at Farnborough showed that the rudder was approximately fully left and the elevator fully up. Engine strip examination yielded no evidence of any pre-crash defect in the left engine, but severe corrosion was found in the fuel control boost capsule (Part n° CH 90274) of the right engine. Tests were carried out on an engine test bed to examine the effects of boost capsule perforation. It was found that such a fault would induce power fluctuations, and that the engine could experience a rich cut when the throttle was retarded. Research into previous incidents on the same type of aircraft revealed two occasions during which fluctuating boost and rpm had been experienced after take-off and later attributed to boost capsule perforation.
Final Report:
Crash of a Vickers VC-10-1109 at London-Gatwick
Date & Time:
Jan 28, 1972
Operator:
Registration:
G-ARTA
Survivors:
Yes
Schedule:
London-Heathrow - London-Gatwick
MSN:
803
YOM:
1962
Crew on board:
4
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Circumstances:
The crew was completing a positioning flight from Heathrow to Gatwick. After touchdown on runway 08, the pilot selected spoilers and reverse thrust when the airplane became airborne again then landed back heavily and bounced twice. The fuselage was bent just prior to the wings, a tyre on the nose wheel burst and a wheel separated. The aircraft rolled for several hundred meters before coming to rest. All four crew members escaped uninjured while the aircraft was damaged beyond repair.
