ENGINE MANUAL
IAE50R – AA
E1.01.05 – E
Issue date: 25.Jan.2018
Page: 19-26
Revision no: 9
19.6.2
Environmental tests
Operation Shock & Crash Safety Tests.
DO-160D, Section 7. Category B
Sinusoidal Vibration Tests.
DO-160D, Section 8 Cat. S
Curve M
Standard vibration test
fixed wing aircraft
Humidity Tests
DO-160C; Section 6.3.2 Cat. B
Category B severed
humidity environment
65°C @ 95% humidity.
Waterproofness (Drip) Tests
DO-160D, Section 10, Cat W,
falling water test
The ECU has been designed to operate between -15 °C and +70 °C. For the purposes of this
test, the ECU was operated at -45 °C and tested to -55 °C for ground survival (non –
operating).
Temperature & Altitude Tests
DO-160C, Sections 4.5.1, 4.5.2,
4.5.3 and 4.6.1;
Cat B2
Temperature Variation Test
DO-160C, Section 5 Cat B2
Fluids Susceptibility
DO-160D,
Section 11.*
The ECU and associated equipment is compatible with fluids liable to be found in
the vicinity of the engine.
The ECU and a sample of the cable loom complete with ident sleeve and tag were
subjected to the following fluids:
AVGAS 100LL, leaded and unleaded motor fuel, Jet A1 turbine fuel, “Comp-2” and
”SRG-75” lube oil, “Procool” coolant, “Aeroshell” fluids 31, 41 and “Skydrol 500B”
Hydraulic oils, Ethylene Glycol and “Kilfrost ABC-3” De-icing fluids, Isopropyl Alcohol,
Denatured Alcohol, and Trichoroethane solvents.
The ECU was not affected by the application of fluids.
The ECU was tested to determine its magnetic effect to assist the installer in choosing
the proper location of the equipment in the aircraft.
