|Mark's Mustang II Project Pages|
Electrical System for Mustang II - N515MD
panel is an all electric panel with no vacuum system.
Future upgrades are to add a backup alternator to the vacuum
pump pad for redundancy. The
system includes the standard 6 instruments and a GI106 GS/LOC/VOR
indicator driven by the Garmin GNS430.
A GTX327 Provides transponder functions.
Each instrument is lighted with a Nulite and is dimmable via a
voltage regulator provided by B&C Specialty products.
Engine instrumentation is
provided by a LCD display that reads engine info via an array of
sensors. This was custom
built by me. The computer
is a 68hc11/3Mhz and a 300Mhz PC to process the graphics.
The electrical system is divided up into two busses. In the event of an alternator failure the primary bus is powered down via the master switch and the plane is operated from the essential bus with a total loading of approximately 8amps. The battery is a Concorde 25Amp/Hour RG battery. The essential bus is isolated from the primary bus via a diode.
the ‘Aeroelectric Connection’ documentation to design the
electrical system (www.aeroelectric.com).
connected to all instrument lights
Bus voltage wire is direct from the battery + terminal to the switch
on the panel. This wire
is protected by a 15A fuse located near the battery in an inline blade
wire is 4AWG and runs to a single ground point on the firewall.
A 48 fast-on tab bus is located here for all systems ground.
wire is 2AWG and runs directly from the battery to the starter.
Primary bus is powered from this point by a 10AWG wire.
intercom is grounded at the radio ground (essentially at the firewall
single point ground) to eliminate ground loop induced noise.
used for Attitude, DG, and T&B.
Pin out is as follows:
B *D Looking into the
pins at the back of the instrument
Switches on Panel
(Starting on left)
Dimmer Knob – controls instrument
Outside Lights Group
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