|Title:||Runway departure, Accident of aircraft FOKKER 50, registration PH-FZE, at Melilla Airport (Spain), on 17 January 2003|
|Micro summary:||Runway departure of this Fokker 50 after failure of ground reverse thrust.|
|Event Time:||2003-01-17 at 1100 UTC|
|Publishing Agency:||Civil Aviation Accident and Incident Investigation Commission (CIAIAC)|
|Site of event:||Landing, Melilla runway 15|
|Departure:||Malaga Airport, Malaga, Spain|
|Destination:||Melilla Airport, Melilla, Spain|
|Airplane Type(s):||Fokker 50|
|Type of flight:||Revenue|
|Executive Summary:||The accident was notified by phone to the CIAIAC on 17 January 2003 at around 12:30 h local. Investigators of the CIAIAC travelled to the place of the accident on the same day, inspected the wreckage and recovered the flight recorders. The Dutch Transport Safety Board (DTSB)1 was notified and participated in the investigation as State of Registration, of Operation, and of Manufacture of the aircraft. Experts from Fokker Services B.V., Denim Air and Air Nostrum also assisted in the investigation.|
On 17 January 2003, the aircraft Fokker 50 registered PH-FZE, with 5 crew and 14 passengers on board, landed on runway 15 of Melilla Airport. During the landing, the pilot in command noticed that he could not engage the ground idle/reverse of both propellers, and that the aircraft did not brake normally. The aircraft started to deviate to the left of the runway axis while both pilots were applying brakes. After tyre number 3 burst, the deviation continued until the aircraft left the paved surface of the runway and finally fell through an embankment with around 15 m of height located at the end of runway 15.
The aircraft was destroyed and the pilot in command and other nine people suffered minor injuries. There was no fire.
The investigation determined that the accident was probably produced by a combination of three factors:
1. An unstable approach that resulted in a higher than normal touchdown speed.
2. The inability to select propeller reverse due to the probable tripping of the circuit breaker «FLIGH IDLE SOLENOID 1 & 2» before or at touchdown.
3. The cross connection of the wheel speed transducer wire harness of wheels 3 and 4, which, due to heavy braking, produced a flat spot in, and subsequent deflation of wheel 3 and reduced the braking capability of wheel 4.
Several safety actions were already taken by the manufacturer and the operator of the aircraft during the investigation, and other were recommended as a result of the conclusions of this report.
|Learning Keywords:||Operations - Runway Excursion|
|Systems - Engine Reversers|
|Systems - Landing Gear|
|Systems - Landing Gear - Tires|
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