British Airways

Dornier DO328

The aircraft was parked on the ramp and subject to engine test run with one or two engineers on board. During the test, the aircraft jumped over the chocks then collided with obstacles and came to rest. There were no injuries while the aircraft was damaged beyond repair. It was operated by Sun-Air of Scandinavia on behalf of British Airways.

Boeing 747-400

The British Airways aircraft B747-400, flight number BA034 with registration G-BNLL, was going to embark on a commercial international air transportation long haul flight from FAOR to EGLL. The ATC gave the crew instructions to push back, start and face south, then taxi using taxiway Bravo to the Category 2 holding point for Runway 03L. During the taxi, instead of turning to the left to follow Bravo, the crew continued straight ahead, crossing the intersection of taxiway Bravo and aircraft stand taxilane Mike. After crossing the intersection, still being on Mike, the aircraft collided with a building. An investigation was conducted and several causal factors were determined. Amongst others, it was determined that the crew erred in thinking they were still taxiing on Bravo while in fact they were taxiing on Mike. This mistake, coupled with other contributory factors such as the briefing information, taxi information, ground movement visual aids, confusion and loss of situational awareness led to the collision. All 202 occupants evacuated safely while four people in the building were injured. The aircraft was damaged beyond repair.

Avro RJ100

Following a normal touchdown, the fracture of the nose landing gear main fitting allowed the nose gear to collapse rearwards and penetrate the lower fuselage, causing significant damage to the equipment bay and the battery to become disconnected. The penetration of the fuselage allowed smoke and fumes produced by the consequent release of hydraulic fluid to enter the cockpit and passenger cabin. With the battery disconnected and after the engines were shut down, all power to the aircraft PA systems was lost and the remote cockpit door release mechanism became inoperative. No pre-accident defects were identified with the manual cockpit door release mechanism or the PA system.

Boeing 777-200

G-YMMM was on a scheduled return flight from Beijing, China, to London (Heathrow) with a flight crew consisting of a commander and two co-pilots; the additional co-pilot enabled the crew to take in-flight rest. There had been no reported defects with G-YMMM during the outboard flight from London (Heathrow) to Beijing, China. The flight plan for the return sector, produced by the aircraft’s operator, required an initial climb to 10,400 m (FL341) with a descent to 9,600 m (FL315) because of predicted ‘Extreme Cold’ at POLHO (a waypoint that lies on the border between China and Mongolia). Having checked the flight plan and the weather in more detail the crew agreed on a total fuel load for the flight of 79,000 kg. The startup, taxi, takeoff at 0209 hrs and the departure were all uneventful. During the climb, Air Traffic Control (ATC) requested that G-YMMM climb to an initial cruise altitude of 10,600 m (FL348). The crew accepted this altitude and, due to the predicted low temperatures, briefed that they would monitor the fuel temperature en route. The initial climb to altitude was completed using the autopilot set in the Vertical Navigation (VNAV) mode. Approximately 350 nm north of Moscow the aircraft climbed to FL380; this step climb was carried out using the Vertical Speed (VS) mode of the autoflight system. Another climb was then carried out whilst the aircraft was over Sweden, this time to FL400, and again this was completed in VS mode. During the flight the crew monitored the fuel temperature displayed on the Engine Indication and Crew Alerting System (EICAS) and noted that the minimum indicated fuel temperature en route was -34°C. At no time did the low fuel temperature warning annunciate. The flight continued uneventfully until the later stages of the approach into Heathrow. The commander was flying at this time and during the descent, from FL400, the aircraft entered the hold at Lambourne at FL110; it remained in the hold for approximately five minutes, during which it descended to FL90. The aircraft was radar vectored for an Instrument Landing System (ILS) approach to Runway 27L at Heathrow and subsequently stabilised on the ILS with the autopilot and autothrottle engaged. At 1,000 ft aal, and 83 seconds before touchdown, the aircraft was fully configured for the landing, with the landing gear down and flap 30 selected. At approximately 800 ft aal the co-pilot took control of the aircraft, in accordance with the briefed procedure. The landing was to be under manual control and the co-pilot intended to disconnect the autopilot at 600 ft aal. Shortly after the co-pilot had assumed control, the autothrottles commanded an increase in thrust from both engines. The engines initially responded but, at a height of about 720 ft, 57 seconds before touchdown, the thrust of the right engine reduced. Some seven seconds later, the thrust reduced on the left engine to a similar level. The engines did not shut down and both engines continued to produce thrust above flight idle, but less than the commanded thrust. At this time, and 48 seconds before touchdown, the co-pilot noted that the thrust lever positions had begun to ‘split’. On passing 500 ft agl there was an automatic call of the Radio Altimeter height, at this time Heathrow Tower gave the aircraft a landing clearance, which the crew acknowledged. Some 34 seconds before touchdown, at 430 ft agl, the commander announced that the approach was stable, to which the co-pilot responded “just”. Seven seconds later, the co-pilot noticed that the airspeed was reducing below the expected approach speed of 135 kt. On the Cockpit Voice Recorder (CVR) the flight crew were heard to comment that the engines were at idle power and they attempted to identify what was causing the loss of thrust. The engines failed to respond to further demands for increased thrust from the autothrottle and manual movement of the thrust levers to fully forward. The airspeed reduced as the autopilot attempted to maintain the ILS glide slope. When the airspeed reached 115 kt the ‘airspeed low’ warning was annunciated, along with a master caution aural warning. The airspeed stabilised for a short period, so in an attempt to reduce drag the commander retracted the flaps from flap 30 to flap 25. In addition, he moved what he believed to be an engine starter/ignition switch on the overhead panel. The airspeed continued to reduce and by 200 ft it had decreased to about 108 kt. Ten seconds before touchdown the stick shaker operated, indicating that the aircraft was nearing a stall and in response the co-pilot pushed the control column forward. This caused the autopilot to disconnect as well as reducing the aircraft’s nose-high pitch attitude. In the last few seconds before impact, the commander attempted to start the APU and on realising that a crash was imminent he transmitted a ‘MAYDAY’ call. As the aircraft approached the ground the co-pilot pulled back on the control column, but the aircraft struck the ground in the grass undershoot for 27L approximately 330 m short of the paved runway surface and 110 m inside the airfield perimeter fence. During the impact and short round roll the nose landing gear (NLG) and both the main landing gears (MLG) collapsed. The right MLG separated from the aircraft but the left MLG remained attached. The aircraft came to rest on the paved surface in the undershoot area of Runway 27L. The commander attempted to initiate an evacuation by making an evacuation call, which he believed was on the cabin Passenger Announcement (PA) system but which he inadvertently transmitted on the Heathrow Tower frequency. During this period the co-pilot started the actions from his evacuation checklist. Heathrow Tower advised the commander that his call had been on the tower frequency so the commander repeated the evacuation call over the aircraft’s PA system before completing his evacuation checklist. The flight crew then left the flight deck and exited the aircraft via the escape slides at Doors 1L and 1R. The cabin crew supervised the emergency evacuation of the cabin and all occupants left the aircraft via the slides, all of which operated correctly. One passenger was seriously injured, having suffered a broken leg, as a result of detached items from the right MLG penetrating the fuselage. Heathrow Tower initiated their accident plan, with a crash message sent at 1242:22 hrs and fire crews were on scene 1 minute and 43 seconds later. The evacuation was completed shortly after the arrival of the fire vehicles. After the aircraft came to rest there was a significant fuel leak from the engines and an oxygen leak from the disrupted passenger oxygen bottles, but there was no fire. Fuel continued to leak from the engine fuel pipes until the spar valves were manually closed.

Hawker Siddeley HS.121 Trident

Hawker Siddeley HS-121 Trident 3B operated by British Airways as flight BE476 and a McDonnell Douglas DC-9-32, operated by Inex-Adria Aviopromet, were destroyed when both aircraft crashed near Vrobec following a mid-air collision. All 176 on board both aircraft were killed. The Trident was on a scheduled flight from London-Heathrow Airport in England to Istanbul-Yesilköy Airport in Turkey, carrying 54 passengers and a crew of 9. The aircraft took off at 08:32 GMT and the flight proceeded normally. First contact with the Zagreb Area Control Centre was established on the Upper Sector frequency 134,45 MHz at 10:04 GMT. The flight was requested to report passing the Zagreb VOR at flight level 330. The aircraft flew along the centreline of airway UB5 with slight side deviation 1-2 km to the right due to wind. At 2 minutes and 50 seconds before the collision, the aircraft changed heading to 115° to head back towards the airway centreline. Airspeed was 295 Kts. The DC-9 departed Split Airport at 09:48 GMT to fly 108 West German tourists back to Cologne. Flight JP550 was issued instructions to climb to FL180. At 09:54 the flight, on passing flight level 130, switched to the Zagreb Area Control Centre lower sector east frequency of 124.6 MHz, receiving clearance to climb to FL240 and later to FL260. At 10:03 the crew switched to the frequency of the middle sector controller, responsible for safety and regulation of traffic between flight levels 250 and 310. This controller cleared to flight to FL350. The aircraft assumed a heading of 353° and a speed of 273 Kts as it passed a beam and to the west of the KOS NDB, approximately 2-3 km from the airway centreline. While heading towards the Zagreb VOR, the flight crew radioed the Upper Sector controller on frequency 134,45 MHz at 10:14:04 GMT and reported that they were climbing through FL325. The controller then requested, in Serbo-Croatian, flight JP550 to maintain their present altitude and report passing the Zagreb VOR. The controller stated that an aircraft was in front passing from left to right at FL335, while in fact BE476 was at FL330. At 10:14:38 the crew replied, also in Serbo-Croatian, that they where maintaining FL330. Three seconds later both aircraft collided. The outer five meters of the DC-9's left wing cut through the Trident's cockpit. Due to the sudden decompression, the forward part of the Trident's fuselage disintegrated. The remaining part of the fuselage struck the ground tail-first. With it's left wing torn off, the DC-9 tumbled down and hit the ground right-wing first.

Hawker Siddeley HS.121 Trident

The taxi drills were actioned by the First Officer and the Flight Engineer during this time and "runway items" were completed after the Commander turned the aircraft through 180° close to the threshold of runway 28, aligned it on the runway centre line, and selected the wheel brakes to park. A power setting of 100 per cent thrust was made, all engine indications were checked as correct, and the engine relight switches were selected 'ON' before the wheel brakes were released and the takeoff run commenced at about 13:46 with the Commander piloting the aircraft. The aircraft accelerated normally ; the First Officer called out the indicated airspeeds at 80 knots and 100 knots and made a call of 'Wet V1' at 117 knots then removed his hand from the throttles. At the time or just after 'Wet V1' was called the Flight Engineer and the First Officer heard a noise which the latter crew member attributed to the aircraft's entry into standing water. According to the Flight Engineer the aircraft appeared to decelerate at the same time that he heard the noise. The Commander felt a marked deceleration consistent with a loss of engine power, whereupon he immediately closed the throttles, called "Abandon", deployed the airbrakes and lift dumpers and applied the wheel brakes fully. However according to the Flight Engineer all engine indications had been normal prior to the closing of the throttles. On seeing a hand close the throttles the First Officer selected emergency reverse thrust on the pod engines, checked the engine indications were correct and maintained the application of emergency reverse thrust until the aircraft eventually came to rest. The First Officer and the Commander checked the indicated pressures on the wheel brake gauges which showed the wheel brakes were fully applied. The initial deceleration felt satisfactory to the crew, then quickly deteriorated and the First Officer formed the impression that the aircraft was aquaplaning. The Flight Engineer then noticed that the aircraft had begun to drift gradually to the left of the runway centreline apparently as the result of a deliberate action by the Commander. Subsequently it became evident to the Commander that he could not bring the aircraft to a halt within the runway confines. Some 200 metres to 300 metres before the end of the runway he turned the aircraft to the left using nose-wheel steering and applied full left rudder. As the nose wheels ran off the runway onto the grass, the aircraft slewed to the left then skidded broadside to the right for a short distance before it came to an abrupt stop at the side of the runway in a right wing down attitude with the right wing tip close to the threshold lights of runway 10. Evacuation drills were initiated and the passengers left the aircraft in a reasonably orderly manner, the majority by slide from the main exit doors and foremost right overwing emergency exit. Catering equipment in the galleys came out of stowage during the accident obstructing access to the forward emergency exit door and preventing use of this exit and its slide during the evacuation. All 117 occupants escaped uninjured while the aircraft was considered as damaged beyond repair.

Lockheed 14 Super Electra

Crashed on landing in unknown circumstances. All nine occupants were injured while the aircraft was damaged beyond repair.

Lockheed 14 Super Electra

Less than one hour after his departure from El Salloum Airport, at the border between Egypt and Libya, the pilot sent a mayday message due to unknown technical problems. He was forced to ditch the aircraft off the Libyan coast. The crew of a ship was quickly on the scene and was able to rescue six occupants, among them the pilot, while five other occupants were killed.

Airspeed AS.10 Oxford

The crew was performing a training flight from Heston when flying in the region of Gosport, the twin engine aircraft collided with the moorings of a balloon. The aircraft went out of control and crashed in a huge explosion. Both pilots were killed. Crew: Arthur George Nicholson, pilot, Arthur Edward Eady, radio operator.

Lockheed 10 Electra

While flying some 80 km south of Copenhagen, the crew informed ATC about a fire on board and reduced his altitude. Due to a sudden hazardous situation, the captain attempted to ditch the aircraft into the sea, off the Vordingborg coast. The aircraft hit the water surface and before it came to rest, the copilot jump into the water. He was slightly injured and quickly rescued while the aircraft sunk rapidly. All five other occupants were killed, among them two employees from the Standard Oil Company based in New Jersey.

Lockheed 14 Super Electra

While cruising at 10,000 feet between London and Basel, crew encountered technical problems on both engines and reduced his altitude. Few minutes later, one engine fired and the captain attempted to make an emergency landing in Saint Sauveur, in the suburb of Luxeuil-les-Bains. The pilot lowered the gear and while landing in a wheat field, the aircraft lost its undercarriage and slid for several yards before coming to rest in flames. All twelve occupants were able to evacuate the cabin unhurt while the aircraft was destroyed by fire.

Lockheed 10 Electra

While landing by night and in a blizzard, the twin engine aircraft became out of control. It veered off runway and collided with fuel station. The aircraft was destroyed but there was no casualties.

Fokker F12

The aircraft was employed on the regular night mail service between Gatwick and Hanover and the crash occurred on the return flight from Hanover when the pilot was preparing to approach the vicinity of Gatwick Airport. The pilot Hattersley was, in fact, on his first ever return flight on this route with this type of aircraft, although he had flown the double journey four times previously in a DH.86. On the flight in question the pilot had been flying in cloud over most of the route and particularly over England. The weather conditions were bad with lots of low cloud at about 200 metres and there was a strong NE wind reaching as much as 60kn/h at ground level. The pilot navigated by means of W/T bearings sent from Croydon, Lympne, Pulham and Gatwick. Hattersley successfully brought the Fokker through cloud to the vicinity of the airport, and his engines were clearly heard from the ground. Control told him that they had heard him and sent a further five bearings in quick succession - no acknowledgement was received for the last bearing and the Fokker sent no further messages. Repeated attempts were made to communicate with G-AEOT but without success. Gatwick then telephoned every local police station in an endeavour to learn whether anyone had heard anything of the aircraft. A search party, including the airport ambulance and fire engine, set out. At 0610 the wireless operator (C.G.V. Wheeler) of the missing aircraft telephoned the control officer at Crawley and stated that the machine had crashed to the south of Crawley. The local ambulance was informed and it left immediately for the scene of the accident. G-AEOT had crashed into trees on Round Hill, 4 miles south of Gatwick Airport. It was upside down and extensively damaged, with the fuselage completely broken up. The flight engineer, G.R.C. Blowers, was lying injured on the ground near the machine, and Hattersley and the second pilot, V.C.W. Bredenkamp, were both dead in the wreckage. Source: http://sussexhistoryforum.co.uk/index.php?topic=925.0

De Havilland DH.86 Express

The chief pilot of British Airways, Captain W. F. Anderson, and two members of the crew were killed when the four engine aircraft carrying the night mail to Germany crashed soon after taking off from Gatwick Airport. Until the inquest has been held and an investigation made, it is impossible to guess at the cause of this disaster, but there appears to be no doubt that the machine turned through 180 degrees immediately after leaving the airport, lost height, and hit a tree.

Fokker F12

The crew was on its way from London to Madrid to deliver the aircraft to the Spanish Nationalists Air Force. En route, crew encountered poor weather conditions and low visibility due to fog and decided to divert to La Rochelle-Lagord Airport. On landing, the left main gear collapsed. The aircraft went out of control and skidded for several yards before coming to rest with its left wing and left engine partially sheared off. While both crew were unhurt, the aircraft was damaged beyond repair. Crew: Mr. Czarkowski 1.

Fokker F12

The crew was on its way from London to Madrid with an intermediate stop in Biarritz to deliver the aircraft to the Spanish Nationalists Air Force. On approach to Biarritz-Parme Airport, crew encountered an unknown situation and decided to make a go around. While trying to climb, the three engine aircraft stalled and crashed in flames in an open field. Both crew were killed and the aircraft was destroyed by post crash fire. It is not clear if the crew was attempting a first, a second or a third approach when the accident occurred. It is also possible that the aircraft was hit by lightning as the weather conditions were marginal at the time of the accident. Crew: Mr. Lasocki, Mr. Morawski.

De Havilland DH.86 Express

The crew was performing a mail flight from Germany to London-Gatwick Airport. While cruising by night, the four engine aircraft went out of control and crashed in unknown circumstances some 50 km southeast of Cologne. Both crew were killed.

De Havilland DH.89 Dragon Rapide

On landing, the twin engine aircraft went out of control, veered off runway and collided with a hangar. All eight occupants were slightly injured while the aircraft was damaged beyond repair. The exact cause of the loss of control on touch down is unknown.

Spartan Cruiser

On landing, the three engine aircraft went out of control and came to rest. While all three occupants were unhurt, the aircraft was damaged beyond repair.