DOCUMENT No.:
REVISION: 1.2
DATE: 2014/11/10
DC-MAM-001-X-C-2
Page 276
10.
ELECTRICAL SYSTEM
This aircraft electrical system consists of a 12 V DC circuit. An 17 Ah lead acid battery provides the
energy to drive the starter and acts as an emergency standby supply of electrical power in case of an
alternator malfunction.
The EFIS and iBox are provided with a 5 Ah back-up battery which charges via the back-up battery
charging circuit (refer to Figure 77). The RDAC unit, compass and AHRS unit are powered from the iBox
unit. Refer to the MGL Avionics iBOX installation manual.
Figure 64: Electrical system (overview).
A single-phase alternator (integral to the engine) connected to a regulator / rectifier (mounted in the cabin)
supplies DC power to the main bus bar and to recharge the battery. The supply end of the rectifier is
connected to the main bus and battery through 30 A circuit breaker mounted on the instrument panel and
a 12 V relay. A red warning light on the instrument panel will turn on (indicating to the pilot) when the
alternator is not operating. Service users are connected between the main bus and the ground bus via
switches and / or circuit breakers located on the instrument panel.
An external alternator can be fitted as an option.
Refer to paragraph 13 for electrical wiring diagrams.
Summary of Contents for Sling 4
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