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Integrated Back-up Battery System
The Integrated Back-up Battery System, is an electronic system that combines a
Ni-mh battery pack, a charger and switching logic in one convenient package. The
back-up battery system has been engineered for use as a source of back-up power
for single instrument applications. This unit may also be used to provide back-up
power for electronic ignition systems utilized on 4 cylinder and smaller applications.
Integral to the IBBS is a nickel metal-hydride battery pack and a matched charging
system to ensure the battery is properly charged and maintained. The system also
includes switching circuitry to provide a stable source of output power during normal
and emergency operations. The IBBS system also provides an output signal to
communicate the operating state of the back-up bus as well as the state of the
battery.
The IBBS system connects to the standard aircraft power bus and provides an
output directly to the avionics requiring back-up power. The IBBS has a pass through
power feature allowing it to provide normal as well as back-up power to connected
equipment. Additionally, the IBBS system provides surge and sag protection for
connected equipment, allowing operation of critical equipment during engine starting.
No other uses of the IBBS system are permitted except for those identified in this
installation manual.
IBBS must be installed using the current aircraft standards and practices as shown
in AC 43.13-2A/1B. The installer/builder is solely responsible for determining the
suitability of the installation and use of this product.
REV 2.3
Model: IBBS-12v-2ah
1
© 2012 TCW Technologies, LLC.
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Summary of Contents for TCW IBBS-12v-2ah
- Page 1 IBBS must be installed using the current aircraft standards and practices as shown in AC 43.13-2A/1B. The installer/builder is solely responsible for determining the suitability of the installation and use of this product. REV 2.3 © 2012 TCW Technologies, LLC.
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Page 2: Installation Instructions
2. The IBBS-12v-2ah was designed to drive one piece of equipment, such as an EFIS, Autopilot or an electronics ignition module. The output current limit for this model is 3 amps maximum continuous current. - Page 3 Follow the wiring diagram on page 17 exactly. 10. The trickle charge wire must be connected as shown in the wiring diagram. This connection keeps the battery topped off when the aircraft remains unused for extended periods of time. REV 2.3 © 2012 TCW Technologies, LLC.
- Page 4 IBBS product by using an external battery charger directly connected to the input of the IBBS. Battery chargers typically provide pulsating voltages that will damage the IBBS product if the system is not connected to a typical primary aircraft battery. REV 2.3 © 2012 TCW Technologies, LLC.
- Page 5 (3 months or longer) Battery Capacity: The IBBS, model IBBS-12v-2ah provides an energy capacity of 2.0 amp-hours at 12 volts when the system is fully charged and operated at 25 C°. Depending on various conditions including operating and storage temperature and age of the battery pack, the capacity of the system will vary.
- Page 6 3) Verify that equipment that derives back-up power from the IBBS product remains ON 4) Turn-off Back-up Power Master switch, ensure that connected equipment powers down. (This procedure further ensures the operation of the transfer circuit in the IBBS product.) REV 2.3 © 2012 TCW Technologies, LLC.
- Page 7 On at least an annual basis the endurance capability of the IBBS system shall be confirmed and compared against the back-up endurance required for the connected equipment. As an alternate to these tests, the IBBS unit may be returned to TCW Technologies for a loaded endurance test, contact TCW Technologies for details.
- Page 8 On at least an annual basis the endurance capability of the IBBS system shall be confirmed and compared against the back-up endurance required for the connected equipment. As an alternate to these tests the IBBS unit may be returned to TCW Technologies for a loaded endurance test, contact TCW for details.
- Page 9 Ground Base Recharging. For service or if you have questions, please contact us. 610-928-3420 www.tcwtech.com email: support@tcwtech.com TCW Technologies, LLC. 2955 Main Road East Emmaus, PA 18049 REV 2.3 © 2012 TCW Technologies, LLC.
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Page 10: Specifications
Operating -10 C° to 60 C° Charging 0 C° to 40 C° Connectors: AMP type CPC # 206486-2 on product wiring harness. AMP type CPC # 206485-1 is utilized on the aircraft wiring harness. REV 2.3 © 2012 TCW Technologies, LLC. - Page 11 Aux Battery trickle charge, Always-ON Purple/yellow Aircraft ground Black Back-up power master switch White/black Info Green/red Main Aircraft Bus (pass thru power) Back-up battery output White Back-up battery output White Back-up battery output White REV 2.3 © 2012 TCW Technologies, LLC.
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Page 12: General Wiring Diagram
Pin #8 Back-up battery output Pin #9 Back-up battery output Note: If the main aircraft bus power supply (pins 1,6) is provided through a single wire to the cpc connector then 18 awg wire must be used. REV 2.3 © 2012 TCW Technologies, LLC. - Page 13 IBBS main power input Master Solenoid Example wiring for systems without back-up power inputs 1) For Garmin 430/530, supply IBBS protected power only to gps/nav power input, not com power input Battery REV 2.3 © 2012 TCW Technologies, LLC.
- Page 14 IBBS Avionics Bus Solenoid Master Solenoid Avionics Bus main power input Example wiring for systems with back-up power inputs Battery Note: terminal 7, 8, 9 may be used for back-up power outputs REV 2.3 © 2012 TCW Technologies, LLC.
- Page 15 REV 2.3 © 2012 TCW Technologies, LLC.
- Page 16 REV 2.3 © 2012 TCW Technologies, LLC.
- Page 17 Technologies are NOT COVERED BY THIS WARRANTY. LABOR, COSTS: TCW shall IN NO EVENT be responsible or liable for the cost of field labor or other charges incurred by any customer in removing and/or reaffixing any TCW product, part or component thereof.