TCW Technologies IBBS-12v-3ah-CRT Bedienungsanleitung
TCW Technologies
Akku
IBBS-12v-3ah-CRT
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72 002 1. 205. 7- R EV 9 © 21 TCW Technologies, LLC.
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Integrated Back-up Battery System
Model: IBBS- -3 -CRT 24v ah
The is an electronic system Integrated Back-up Battery System IBBS, ,
that combines a Lithium-Iron-Phosphate (Li- -PO4) battery pack, a Fe
charger and switching logic in one convenient package. The IBBS
provides an engineered solution to enable an endurance bus for critical
loads found in aircraft. It simpliîes the wiring and installation of a source
of back-up power by integrating all of the key elements into a single
enclosure. e system provides back-up power to critical Th IBBS
electronic loads such as EFIS, GPS, Autopilots and engine monitor
systems.
Integral to the IBBS is a lithium-iron-phosphate battery pack and a
matched charging system to ensure the battery is properly ch ged and ar
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 signals to other equipment such as EFIS
systems to communicate the operati state of the main aircraft bus as ng
well as the state of the battery.
72 002 1. 205. 7- R EV 9 © 21 TCW Technologies, LLC.
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The IBBS system connects to the standard aircraft power bus and
provides an output to critical equipment that require back-up power.
Additionally, the IBBS system provides surge and sag protection for
connected equipment, allowing operation of critical equipment during
engine starting.
The IBBS system is suitable for use with equipment such as Garmin
GNS and GTN series navigators, G3X series of avionics, Grand Rapids
Technologies EF systems, Advanced Flight Systems EFIS, Dynon IS
EFIS, and MGL EFIS, TruTrak Autopilots and EFIS, Trio Autopilots,
SureFly electronic ignitions, Lycoming EIS electronic ignitions, and
ElectroAir electronic ignitions.
The IBBS must be installed using the current aircraft standards and
practices as detailed AC 43.13-2A/1B in .
IBBS products are protected by US Patent 8,189,305
Table of Contents
Limitations . 3 pg
Installation Information: pg. 3-5
General Product info: 6-7 pg.
Battery Capacity details: pg. 8
Product Operation: pg. 9
Instructions for Continued Airworthiness: pg. - 10 12
Speciîcations pg. 13
Functional performan pg. 14 ce
Environmental qualiîcation pg. 15
Connector Pin- t pg. 16 ou
Mounting plate drawing 17 pg.
General Wiring diagram pg. 18
Example Wiring diagrams pg. -20 19
Support and Warranty information pg. 21
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Limitations:
This article meets the minimum requirements of technical standard order (TS C179b. O)
Installation of this article requires separate approval.
The conditions and tests for TSO approval of this article are minimum performance standards.
Those installing this article, on or in a speciîc type or class of aircraft must determine that the
aircraft installation conditions are within the TSO standards. TSO articles must have separate
approval for installation in an aircraft. The article may be installed only according to 14 CFR part
43 or the applicable airworthiness requirements.
This article may not be installed as the sole source of power for an instrument or avionic device
that has no other redundancy in the aircraft. (i.e., If an aircraft has one and only one vhf radio, it must
have an additional source of power beside the IBBS sys to qualify for installation.) tem
See page 14 for Performance Speciîcations and potential limitations and ratings under various
conditions, including environmental and application installations. See Item 3 below for
installation location limitations.
Installation Instructions:
1. IMPORTANT NOTE:
Consult the attached wiring diagrams to identify wiring connections appropriate to the
particular installation. Please note, some equipment such as GPSâs and EFIS systems may
be provided with multiple power inputs. For these installations the output of the IBBS must
be connected to their âback upâ power input. â- These inputs are often identiîed as Aircraft
Power 2 . For equipment having only a single power input terminal the IBBS pass-thru â
power function must be utilized. (This is typical of devices such as comm radios,
transponders, autopilots, fuel pumps, and electronic ignitions) 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 oî during engine starting.
2. Check that the total connected load (summed value of all four output wires of the
IBBS) is less than the following product ratings:
IBBS- -3 - : 5 amps maximum continuous cu nt 24v ah CRT rre
amps peak for radio transmissions and transient loads* 10 *(30 seconds max duration)
3. unt the IBBS to structure in a suitable location in the aircraft utilizing the practices Mo
identiîed in AC 43.13-2A/1B. Ensure the mounting points and fasteners are suitable for the
weight of the product, consult the speciîcations for details. The IBBS must be mounted
inside the aircraft, do not mount the IBBS in the îrewall forward area. Select an area that is
accessible to allow for future battery servicing. The preferred operating temperature range
of the system is -40 C° to 60 C°, the eîective charging temperature range is -40 C° to 40 C°.
Select an installation location that takes these temperatures into consideration.
Produktspezifikationen
| Marke: | TCW Technologies |
| Kategorie: | Akku |
| Modell: | IBBS-12v-3ah-CRT |
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