PD9B01M0 1ST ISSUE 1/07/2019 26
By turning ON the Master Switch, while the engine is running, a red warning light, located just
above the Ignition Switch, will flash on if the generator has failed or the regulator/rectifier is not
operating. Just alongside the red light there is a green light that will flash on when the battery is
rightly connected.
Breakers and switches are listed into ANNEX C12 of your POH, within the panel description.
The schematic diagram of the electrical system including the typical legend of electrical
components is shown in ANNEX A (Electrical & Avionics group).
9.1 Battery check, removal and installation
Battery check should be performed every 100 hours or more frequently if operating in warm
climates. See ANNEX A (Electrical & Avionics group) for detailed maintenance procedures and
information.
9.2 Internal AC Generator
The generator is a permanent magnet type and supplies alternate current to a regulator/rectifier.
Servicing or repair of the generator must be carried out only by Rotax authorized personnel and
based on the Rotax approved Maintenance Manuals.
9.3 Exterior lights
Exterior lights, whose electric wiring drawing is illustrated by many operational sheets into ANNEX
A (Electrical & Avionics group), consist of:
✓
Navigation Lights
Navigation lights are installed on the wing, controlled by a single switch located on
instrument panel and protected by a breaker. A green light is located on right wing tip, whilst
a red light is on the left wing tip
;
✓
Landing lights
The landing lights are located on the lower engine cowling. Each light is protected by a
breaker. Switches and breakers are located on the instrument panel;
✓
Strobe lights
The strobe lights are installed in the wing tips. Strobe lights are activated by a switch and are
protected by a breaker. Switches and breakers are located on the instrument panel. A test of
the strobe light may have to be done while the engine is running since the battery may or not
have enough voltage to power the strobe lights.
9.4 Stall warnings (if installed)
The stall warning system consists of an airflow sensor and of an electric horn. The airflow sensor is
mounted on the leading edge of the right wing. As the aircraft approaches to a stall speed, the
sensor activates the acoustic alarm system which is made up of a cabin-installed horn. In case of
removal or replacement of the stall sensor, it is recommended to reinstall it so as to be effective in
detecting stall condition from 1 to 3 kts before the stall speed indicated in the POH. Never paint the
stall-warning sensor under any circumstance. Details are described in the ANNEX A (Electrical &
Avionics group).
