BRP-Rotax
INSTALLATION MANUAL
VALIDATION OF INSTALLATION
General The validation procedures described in this chapter do not claim to be complete. The cor-
rect execution and compliance with all given system limitations and interface descriptions
as well as with standards and norms given by authorities must be proven by the aircraft
manufacturer.
External Power
Supply
If an engine is installed in a specific aircraft type for the first time, it is required to measure
the voltage on three positions:
• Battery Voltage (separate Voltmeter)
• Voltage on Electric Starter (separate Voltmeter)
• ECU Bus Voltage (displayed in BUDS Aircraft diagnostic tool)
Depending on the location where the engine should be used, this measurement must be
done at the lowest reachable temperature. In case the measured voltages drop below 9 V
especially during engine start, the installation is insufficient. In this case specification of
the external power source the execution of the wiring as well as the total consumption of
all electrical loads needs to be checked.
Separation of
EMS and Airframe
circuit
Proof the continuity between Fusebox Regulator A and Fusebox Regulator B in static con-
dition (Fusebox is not supplied with power by an external power source). To determine the
ECU BUS voltage at the transient moment of the engine start a oscilloscope must be used
as well as the total consumption of all electrical loads needs to be checked.
916 i TYPE A
Figure 3.24: Validation of EMS and Airframe Circuit separation
1 Multimeter 2
Regulator A (black connector)
3
Regulator B (Amphenol connector)
4
Ground connectors regulator A
5
Ground connectors regulator B
In case of continuity the installation is not sufficient and the wiring concept needs to be
revised.
24–00–00
Page 28
December 01 2023
Effectivity: 916 i A / C24
Edition 0/Rev. 1
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