Accident Summary
On 24 March 1980 at approximately 0730 hours, a Partenavia P68 Victor, registration 5Y-BBA, crashed near Gura Falls in the Aberdares mountain range, Kenya. The aircraft had departed Nyeri aerodrome at 0654 hours and was observed turning towards the Aberdares before the accident. The crash site was about 18 nautical miles (34 km) from Nyeri, at an elevation of approximately 10,090 ft. The aircraft caught fire on impact and was destroyed. The accident was not survivable.
Aircraft Information
The aircraft was a Partenavia P68 Victor, serial number 93, manufactured in April 1977. It was registered to Caspair Limited and Credit Finance Corporation of Nairobi. The aircraft was powered by two Lycoming IO-360-A1B6 engines. The starboard engine had 2,167.45 hours since new and 587.45 hours since last overhaul; the port engine had 587.45 hours since new. The total airframe time was 2,191.50 hours. The aircraft's maximum takeoff weight was 4,387 lb. At the time of the accident, the estimated takeoff weight from Nyeri was 4,570 lb, exceeding the maximum by 255 lb.
Pilot Information
The pilot, Mr. Suha Ayata, was a Turkish national born on 2 June 1952. He held a commercial pilot's license (No. 2021) issued on 20 December 1979, based on a FAA commercial license. He also held a Radio Telephony Operator's license. His total flying experience was 1,117 hours, including 229.24 hours on the Partenavia P68. His medical certificate was current at the time of the accident.
Wreckage and Impact
The aircraft hit trees at the top of a ridge and crashed in a river valley about 300 ft below the ridge top. The wreckage examination revealed that the aircraft caught fire on impact. The starboard engine was found lying 3 ft from the mainplane and had been feathered; it did not catch fire. The port engine was detached and destroyed by fire. There was no evidence of pre-impact fire.
Tests and Research
The starboard engine was salvaged for workshop tests. The propeller blades showed one blade feathered with damage, and the other blade bent backwards over 90°. The propeller was likely stationary or low speed at impact. The pitch change mechanism had a broken piston rod, but this was consistent with impact damage. The engine components, including the crankshaft, fuel pump, magnetos, injector, and constant speed unit, were examined and found serviceable. No evidence of pre-impact failure was found.
Analysis
The investigation found it extremely difficult to establish the probable cause of the accident due to lack of evidence. One contributing factor considered was that the aircraft was overloaded by 255 lb, exceeding the maximum takeoff weight. The center of gravity was calculated at 14.783 inches aft of the datum, within limits for the overloaded weight. No definitive probable cause was determined.