Homebuilt test flying hazards
Sussit has asked for info on a Lancair fatal near Melbourne, Australia. I am not a ETPS graduate so please understand that the following questions may be a bit amateur.
The Lancair concerned was a first of type unpressurised version with a Walther 700 SHP turbo-prop. Around three flights were carried out by non-test pilot qualified pilots - but experienced flying instructors. It is believed that the fatal flight was for purpose of stall checking at 4000 ft. Control was obviously lost with one witness stating that aircraft appeared to perform an aerobatic manoeuvre.
It was known that on previous flights that the engine idled at high rpm producing significant torque. The owner had also opted to change the engine centre line angle downwards by three degrees to solve a problem with fitting of the nose cowl. Also one of the pilots who first flew the aircraft reported a severe wing drop at the stall.
Questions: Would a high idle rpm contribute towards a severe wing drop?
With this type of engine, would a significant power application as would normally be applied in a stall recovery, cause a torque roll at low IAS?
Would there be a significant gyroscopic effect if rapid power was introduced as part of a stall recovery - and the nose lowered harshly?
What effect would a three degree lowering of the engine centre line have on aircraft handling near the stall?
The wreckage pattern seems to indicate high angle of descent in a flat attitude. This observation is purely from a media picture of the scene and may well be misleading.