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Flight test for turbo system performance
Critical Altitude for your Seneca TSIO-360
Performance of your Seneca is dependant on the fuel and turbo-charging system working correctly.
If your turbo system does not preform up to specifications your aircraft will not maintain that critical single engine altitude in an emergency.
Just had an annual!
Chances are the aircraft was not flown by the shop, so this critical adjustment was not checked. Please print the proceedure listed below and test your own system next flight.
The following proceedure was taken from the Piper Seneca II Service Manual dated 10/11/79 Power Plant section Card 2C15
Flight Test
A complete flight test should be made for final adjustments of fuel flow and bypass.
- At 8,000 feet density altitude, set the engines to operate at 2,450 (+-25)RPM and 31.0 to 32.0 in. Hg manifold pressure.
- Lean each engine to 25F rich of peak exhaust gas temperature (EGT). (Peak EGT may not be the same for both engines; however, the difference should not exceed 50F).
- Fuel flows ______________ Left ____________________Right
- Fuel flow at these conditions should be 11.0 to 12.0 gph.
- Critical Altitude test
- Mixture full rich
- Cowl flaps open
- Airspeed 105mph
- Propellers high pitch (2575 +-25 RPM)
- Full Throttle (Manifold pressure 39.8-40.0 in Hg).
- Continue to climb until overboost annunciator lights go out (indicating critical altitude). As lights go out note:
- Fuel flow ________________ Left ___________________ Right
- Indicated altitude ________________________
- OAT________________________________
- Fuel flow at critical altitude should be 23.0-25.0 GPH and density altitude of 11,500 minimum to 12,500 maximum.
If your aircraft does not maintain boost as required your performance and single engine service ceiling will suffer.
Call Fessler Aviation to assist in restoring full performance for your Seneca!
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