ENGINE MANUAL
IAE50R – AA
E1.01.05 – E
Issue date: 25.Jan.2018
Page: 18-2
Revision no: 9
The liquid cooling system is designed to run at 0.9 bar (13 psi). The aircraft manufacturer or
engine installer should provide a relief valve. It should be fitted with a vacuum valve to ensure
that no undue negative pressure is generated on cooling after engines switch off. Therefore
the relief valve should open for reverse flow at -0.2 bar.
A VDO temperature sensor is fitted to the engine in the front end plate. Provision of a
compatible gauge is the responsibility.
Coolant 50/50 water / ethylene glycol mix (A corrosion inhibiting anti–freeze must be used,
refer to 5.2.7). This water/glycol mix will provide protection down to -36 °C.
Operating temperature is in the range of 60 °C to 90 °C after warm up. Maximum continuous
100 °C.
Heat rejection rate approximately 25 kW of heat is rejected to the coolant when the engine is
operated at max continuous power (50 BHP).
An integral water pump is provided with the engine. This provides a water flow of approx. 40
liters per minute at 7000 rpm.
Radiator. The optimum radiator design will vary with each
installation. It is the responsibility of the installer to provide
an adequate cooling system and thus ensure that the
maximum recommended coolant temperature is never
exceeded even under the most adverse operation
conditions. The design should also ensure that the minimum
operating temperature can be achieved under all flying
weather conditions.
Flight trials will probably be necessary to confirm that the
design caters for the above conditions.
18.3
Fuel System
18.3.1
Fuel Specification
Refer to chapter 5.2.8
18.3.2
Fuel delivery
No fuel pumps are provided by Austro Engine GmbH. Therefore electric pumps each capable
of delivering 80 liters an hour at three–bar pressure.
