Only just worked up the courage to post this. Constructive comments welcome, particularly those directed at solutions. Keep the flamethrowers stored.
About 1 month ago during Phase 1 testing.
Top of the first ever stall turn.
Left rudder. Yaw established. Throttle to idle. Propellor stops.
Fail to restart in air.
Land in paddock.
Check over of plane and paddock. Engine restarts and runs normally including normal runups.
Short field take off and climb to safe altitude over the paddock and fly 10 minutes back to base airfield.
Put the aircraft away for another day.
This has put a real cloud over what is otherwise a lovely plane. I feel I can never have confidence in it or myself again.
Why did the engine stop?
Configuration
RV8
YO320 D1A
New from Vans in 2015 run for 162 hours on another RV8 then removed and installed on mine. All ground testing and in flight testing appeared normal until this incident except low oil temp which I’m still trying to fix.
Avstar Carb LVC-5-4PA
Idle was a bit low and mixture a bit lean initially but adjusted them long before this flight.
Standard Vans FAB
Slick mags
Engine driven fuel pump that came with the engine
Facet electric fuel pump ES 40108
Aircraft Spruce gascolator
Whirlwind GA200L propellor.
Flop tube on right tank. Standard pickup on left tank. Tanks about half full at time of engine failure.
I had been gradually expanding the envelope in Phase 1 testing including steep turns to 3.6g (the plane could take more but I can’t at the moment) and pushovers to -0.6g which led to the engine producing no power until positive g is reintroduced. That is what I think I should expect of the carbureted engine.
Multiple stalls in all configurations, loops and barrel rolls were completed with no indication of this sort of issue.
Before next flight after the engine failure I checked the fuel flow to the carby and the filter screen in gascolator. Both apparently normal.
Next flight did some stalls and circuits. Again all benign.
The plane and engine appear to operate normally in the ordinary flight envelope of take off climb cruise and descent.
The second flight after the engine failure at the end of climb and glide performance testing I did some higher angle climbs between about 5000 and 6000 feet amsl. At that point the tanks had approx 65 liters each side.
Starting at 130 kts I did a number of climbs working up to 30 degrees to 40 degrees nose above the horizon with throttle fully open and mixture rich and the electric boost pump on. At the top of the climb as the speed deteriorates to close to stall speed the engine starts to lose power although the throttle is still fully open. At that point the fuel pressure is still approx 4.8-5psi. Allowing the nose to drop restores normal power. That is the case for both fuel tanks.
I don’t know what the fuel flow is at that point. I have downloaded the Dynon data but the spreadsheet is so enormous I don’t know how to make it useful to find what is happening. I suspect the fuel flow is dropping dramatically there.
On the occasion of the engine failure I think I pulled the throttle to idle too soon. Poor technique. Neil Williams in the Bible on aerobatics advises keeping the throttle fully open until the vertical down line is established for a left stall turn. I have spoken to another experienced RV instructor who advises the same. But the subsequent climb testing shows that would not have made any difference.
What is going on here?
I don’t think the tank unported in the stall turn because the problem can be reproduced with almost full tanks without yaw or bank and the fuel pressure remains at the upper end even when the engine stops producing power.
Is this normal for a carbureted engine?
Perhaps the top of the climb is the top of a parabola producing less than 1g or approaching 0g resulting in the carb not distributing the fuel.
Do I have to avoid low-speed, low-g, high nose-angle manouvres like stall turns without fuel injection particularly with the low inertia carbon fiber propellor?
Should I get the carb checked? What should they be looking for when it is checked?
There is an explanation for the failure to get the engine restarted in the air. Multiple factors including high stress and not bringing to mind the need to turn off the non impulse coupled mag so that the starter would engage. Whether that was a good design decision is an issue for another day. I’ve changed my emergency checks to accommodate that design. Indeed if I had properly done my existing checks the engine likely would have restarted.
Whether I should have flown out of the paddock or left it for the insurance company is also a question for another day.
What I am interested in is why the engine stopped and what I need to do to prevent it happening again.
Wisdom on that issue please.
About 1 month ago during Phase 1 testing.
Top of the first ever stall turn.
Left rudder. Yaw established. Throttle to idle. Propellor stops.
Fail to restart in air.
Land in paddock.
Check over of plane and paddock. Engine restarts and runs normally including normal runups.
Short field take off and climb to safe altitude over the paddock and fly 10 minutes back to base airfield.
Put the aircraft away for another day.
This has put a real cloud over what is otherwise a lovely plane. I feel I can never have confidence in it or myself again.
Why did the engine stop?
Configuration
RV8
YO320 D1A
New from Vans in 2015 run for 162 hours on another RV8 then removed and installed on mine. All ground testing and in flight testing appeared normal until this incident except low oil temp which I’m still trying to fix.
Avstar Carb LVC-5-4PA
Idle was a bit low and mixture a bit lean initially but adjusted them long before this flight.
Standard Vans FAB
Slick mags
Engine driven fuel pump that came with the engine
Facet electric fuel pump ES 40108
Aircraft Spruce gascolator
Whirlwind GA200L propellor.
Flop tube on right tank. Standard pickup on left tank. Tanks about half full at time of engine failure.
I had been gradually expanding the envelope in Phase 1 testing including steep turns to 3.6g (the plane could take more but I can’t at the moment) and pushovers to -0.6g which led to the engine producing no power until positive g is reintroduced. That is what I think I should expect of the carbureted engine.
Multiple stalls in all configurations, loops and barrel rolls were completed with no indication of this sort of issue.
Before next flight after the engine failure I checked the fuel flow to the carby and the filter screen in gascolator. Both apparently normal.
Next flight did some stalls and circuits. Again all benign.
The plane and engine appear to operate normally in the ordinary flight envelope of take off climb cruise and descent.
The second flight after the engine failure at the end of climb and glide performance testing I did some higher angle climbs between about 5000 and 6000 feet amsl. At that point the tanks had approx 65 liters each side.
Starting at 130 kts I did a number of climbs working up to 30 degrees to 40 degrees nose above the horizon with throttle fully open and mixture rich and the electric boost pump on. At the top of the climb as the speed deteriorates to close to stall speed the engine starts to lose power although the throttle is still fully open. At that point the fuel pressure is still approx 4.8-5psi. Allowing the nose to drop restores normal power. That is the case for both fuel tanks.
I don’t know what the fuel flow is at that point. I have downloaded the Dynon data but the spreadsheet is so enormous I don’t know how to make it useful to find what is happening. I suspect the fuel flow is dropping dramatically there.
On the occasion of the engine failure I think I pulled the throttle to idle too soon. Poor technique. Neil Williams in the Bible on aerobatics advises keeping the throttle fully open until the vertical down line is established for a left stall turn. I have spoken to another experienced RV instructor who advises the same. But the subsequent climb testing shows that would not have made any difference.
What is going on here?
I don’t think the tank unported in the stall turn because the problem can be reproduced with almost full tanks without yaw or bank and the fuel pressure remains at the upper end even when the engine stops producing power.
Is this normal for a carbureted engine?
Perhaps the top of the climb is the top of a parabola producing less than 1g or approaching 0g resulting in the carb not distributing the fuel.
Do I have to avoid low-speed, low-g, high nose-angle manouvres like stall turns without fuel injection particularly with the low inertia carbon fiber propellor?
Should I get the carb checked? What should they be looking for when it is checked?
There is an explanation for the failure to get the engine restarted in the air. Multiple factors including high stress and not bringing to mind the need to turn off the non impulse coupled mag so that the starter would engage. Whether that was a good design decision is an issue for another day. I’ve changed my emergency checks to accommodate that design. Indeed if I had properly done my existing checks the engine likely would have restarted.
Whether I should have flown out of the paddock or left it for the insurance company is also a question for another day.
What I am interested in is why the engine stopped and what I need to do to prevent it happening again.
Wisdom on that issue please.