REV 1.6
© 2019 TCW Technologies, LLC.
3
Installation Instructions:
1.
IMPORTANT NOTE:
Consult the attached wiring diagrams to identify wiring connections similar to your particular
installation. Please note, some equipment such as GPS’s and EFIS systems may be
provided with multiple power inputs. For these installations the output of the IBBS must be
connected to their “back-up” power input. The “back-up” power source should be provided
through the IBBS product. For equipment having a single source of power, the IBBS system
may be fed from a bus that remains active during engine starting, such as the master bus or
it may be fed from an avionics bus that is switched off during engine starting.
2.
Check that the total connected load (summed value of all four output wires) is less
than the following product ratings:
IBBS-12v-6ah: 8 amps maximum continuous current
12 amps peak for radio transmissions and transient loads*
*(30 seconds max duration)
3.
Mount the IBBS in a suitable location in the aircraft. Ensure the mounting points and
fasteners are suitable for the weight of the product, consult the specifications for details. The
IBBS must be mounted inside the aircraft, do not mount the IBBS in the firewall forward
area. Do not mount the IBBS unit up under the instrument panel unless the panel is
properly ventilated to ensure heat does not build up in the area. Select an area that is
accessible to allow for future battery servicing. The operating temperature range of the
system is -10 C° to 60 C°, the effective charging temperature range is 0 C° to 40 C°.
Select an installation location that will comply with these requirements.
4.
Connect the aircraft wiring according to one of the wiring diagrams shown.
The IBBS must be powered through a properly sized circuit breaker or fuse. ENSURE the
proper size wire is utilized for the input feed, output supply and ground connection.
Power Input Requirements
: The IBBS has multiple power inputs.
Pin 5 provides charging and bus voltage sensing for the IBBS unit and must be connected
to an aircraft power bus. When the voltage on pin 5 falls below about 11 volts the system
automatically transfers the load current on the output pins to the internal back-up battery
source. Pin 5 maximum current draw is 4.0 amps during charging.
Pins 6,7,8 receive power that is passed-thru the IBBS unit to the loads connected to the
output pins. These pass-thru power connections are optional and are only required for
systems that do not have multiple power inputs. These pins can also be used if it is desired
to have redundant power paths feeding the connected loads. These pins are internally
wired in parallel, it is recommended to populate all three pins and join the wires together at
the pass thru power breaker. Note: these pins do not individually correspond to any
particular output pin (12-15). The pass-thru breaker must be sized for whatever load is
connected to the IBBS outputs. The maximum combined load is 12 amps peak, 8 amps
continuous. If Pins 6,7,8 are used they MUST be connected to the same power bus as Pin
5.
