Tcw Ibbs-12v-3ah-crt User manual

p/n 725.0002 REV 1.4

Integrated Back-up Battery System

Model: IBBS-12v-3ah-CRT

The Integrated Back-up Battery System, IBBS,is an electronic system

that combines a Lithium-Iron-Phosphate (Li-Fe-PO4) battery pack, a

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 simplifies the wiring and installation of a source

of back-up power by integrating all of the key elements in a single

enclosure. The IBBS system provides back-up power to critical

electronic loads such as EFIS, GPS, Autopilots, Radios 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 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 signals to other equipment such as EFIS

systems to communicate the operating state of the main aircraft bus as

well as the state of the battery.

The IBBS system connects to the standard aircraft power bus and

provides outputs to critical equipment that require back-up power.

Additionally, the IBBS system provides surge and sag protection for

p/n 725.0002 REV 1.4

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 EFIS systems, Advanced Flight Systems EFIS, Dynon

EFIS, and MGL EFIS, TruTrak Autopilots and EFIS, Trio Autopilots,

SureFly electronic ignitions, Lycoming EIS electronic ignitions, and

ElectroAir electronic ignitions.

IBBS must be installed using the current aircraft standards and practices

as shown in AC 43.13-2A/1B.

IBBS products are covered by US Patent 8,189,305

Table of Contents

Limitations pg. 3

Installation Information: pg. 3-5

General Product information: pg. 5-7

Battery Capacity details: pg. 7

Product Operation: pg. 8

Instructions for Continued Airworthiness: pg. 9-11

Specifications pg. 12

Functional performance, environmental testing pg. 13

Connector Pin-out pg. 14

Mounting plate drawing pg. 15

General Wiring diagram pg. 16

Example Wiring diagrams pg. 17-18

Environmental Qualification Statement pg. 19

Support and Warranty information pg. 20

p/n 725.0002 REV 1.4

Limitations:

The conditions and tests for TSO approval of this article are minimum performance

standards. Those installing this article, on or in a specific 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 system to qualify for installation.)

See page 13 for Performance Specifications 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 GPS’s and EFIS systems may

be provided with multiple power inputs. These inputs are often identified as “Aircraft Power

2”.For these installations the output of the IBBS must be connected to the “back-up” power

input of the respective device. For equipment having only a single power input terminal the

IBBS pass-thru 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 off 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-12v-3ah-CRT: 5 amps maximum continuous current

10 amps peak for radio transmissions and transient loads*

*(30 seconds max duration)

3. Mount the IBBS to structure in a suitable location in the aircraft utilizing the practices

identified in AC 43.13-2A/1B. 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 preferred operating temperature range of the system is -40 C° to

60 C°, the effective charging temperature range is -40 C° to 40 C° with extended charging

times below 0 C°. Select an installation location that takes these temperatures into

consideration.

p/n 725.0002 REV 1.4

4. Connect the aircraft wiring according to one of the wiring diagrams shown.

The IBBS must be powered from properly sized circuit breakers or fuses. Ensure the proper

size wire is utilized for the input feed, output supply and ground connection.

Power Requirements: The IBBS has multiple power inputs.

Pin 5 receives power for charging the internal battery and bus voltage sensing for the

switching logic within the IBBS unit. Pin 5 must be connected to an aircraft power bus.

When the voltage on pin 5 falls below 11 volts the system automatically transfers the load

current on the output pins to the internal back-up battery source. Pin 5 nominal current draw

is 1.8 amps during charging.

Pin 4 provides power to an internal battery heater system utilized when the battery

temperature is below 0 C°. The nominal current draw is 0.7 amps when the battery

temperature is below 0 C°.

Pins 6,7,8 provide power that is passed-thru the IBBS unit to the loads connected to the

output pins. These pass-thru power connections are optional and 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; join the wires together and feed all of

these inputs from 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

the load that is connected to the IBBS outputs. The maximum combined load is 10 amps

peak, 5 amps continuous. If Pins 6,7,8 are used they must be connected to the same

source of power as Pin 5.

Output Power connections:

The IBBS-12v-3ah-CRT has four output pins, Pins 12,13,14,15. These pins provide power

to the connected load. These four wires may be paralleled together for redundancy and

load current sharing. Use 20 awg wire for each pin. The total combined load for all four

pins is 5 amps continuous, 10 amps peak. The output wires of the IBBS system are

protected with a single 10 amp, Mini fuse. This fuse is accessible on the side of the

enclosure.

IMPORTANT NOTE ON CHANGING FUSE:

Disconnect the main product connector before changing the fuse!

Replace fuse with 10 amp, MINI type fuse only

5. The Back-up Power Master switch must be utilized to turn the back-up battery system

off when not in use. The back-up power master switch gives the pilot the ability to turn the

back-up battery system off. In some installations this may be the only means to shut down

the connected equipment.

6. The IBBS unit has a low voltage warning output, pin 3. This pin may be used to drive

an LED indicator or to provide a digital signal to indicate the main input bus is in a low

p/n 725.0002 REV 1.4

voltage condition. When the main input bus (connected to pin 5) falls below about 11 volts

this output will drive to a low state. Maximum current sourced into this pin is 25 milliamps.

7. The IBBS unit has in internal battery monitor connection, pin 2. This pin allows the

voltage state of the internal battery to be monitored with a separate volt meter or an analog

input of a monitor system. This pin will only report internal battery voltage when the unit is

enabled by turning the Back-up Master switch ON. A fully charged battery back will indicate

about 13-14.7 volts on this pin.

Important note: the meter utilized to measure pin 2 must have an input impedance

>100k ohms otherwise it will load down pin 2 and provide an artificially low voltage

reading.

When used with the following EFIS systems wire pin 2 to the Volts2 input of the

EFIS or engine monitor as follows:

8. Complete the installation of the wiring harness and connector prior to attaching the

connector to the IBBS product. It is essential to ensure the wires do not inadvertently short

together during installation. Remember, the IBBS pack is a back-up source of power and is

ready to deliver output power even when the aircraft electrical system is in the off state.

9. When using the IBBS product to provide back-up power to an electronic ignition

system it MUST be used to back-up one and only one electronic ignition module. Do not

use one IBBS to back up both electronic ignition modules in a dual electronic ignition

system. Follow the instructions per the electronic ignition manufacture. Do not connect

any other loads to the IBBS when using the IBBS to power an electronic ignition module. Do

not use the IBBS system to back-up a dual ignition system having only a single power input.

Do not use a single IBBS system to back-up two electronic ignition systems.

Manufacturer/model

Volts 2 input location

Garmin G3x system GEA 24

J244, Pin 28

Advanced Flight Systems 5000 series:

Expansion Port Pin 13

p/n 725.0002 REV 1.4

Product Details and General Information:

The Charging System:

The IBBS automatically maintains its internal battery pack. The internal charging circuit

monitors the state of the internal battery and recharges the battery as necessary when the

aircraft is operational. The input current for battery recharging is nominally 1.8 amps.

Battery charging only occurs when the aircraft supply bus connected to pin 5 is above 13.7

volts. (charging only occurs when the aircraft alternator is running and has available capacity)

If the internal battery is fully discharged for any reason it may require up to 90 minutes of

recharge time. NOTE: Do not attempt to recharge the IBBS product by using an external

lead-acid type battery charger directly connected to the input of the IBBS. Battery chargers

typically provide pulsating voltages that may damage the IBBS product if the system is not

connected to a typical primary aircraft battery.

Recharge time at normal temperatures: 0C° to 40 C° 90 minutes nominal

Recharge time at low temperatures: -18C° to 0 C° nominal + 15 minutes preheat

-40 C° to -18C° nominal + 60 minutes preheat

Back-up Power Master Switch:

The IBBS has one input switch connection as identified in the wiring diagrams: Back-up

Power Master. This switch enables back-up power from the IBBS system to be available on

the output wires when power on the normal aircraft bus falls below 11 volts. Pin 1 is pulled to

ground when the back-up master switch is turned on, this enables the IBBS system.

If the back-up power master switch is enabled and normal aircraft power falls below 11 volts

then the internal back-up battery will be connected to the outputs and be utilized to supply

back-up power to the connected load.

If the normal aircraft power bus is above 11 volts, then the outputs are energized with normal

aircraft power (if the pass thru-power connections are utilized) and the back-up battery

remains off-line. The pass thru power feature does NOT depend on the state of the back-up

master switch. If power is made available on the pass-thru power inputs it will pass through

and be available on the outputs. This allows for automatic pass through of power during

normal operation.

Ground Based Recharging:

To accomplish ground based charging, connect an approved battery charger or DC power

source (set to 14 volts) to the main aircraft battery and energize the main aircraft power bus

by turning on the master switch, leave all other aircraft loads in their off state. Note, the

ground base source of power must be capable to suppling the load current of all devices that

can not be turned off in this nominal state, plus the 1.8 amps of IBBS recharge current.

Leave the ground-based charging system connected and powered until the IBBS system

completes its recharge cycle of its internal battery. See page 5 for details on battery

charging time. If voltage monitoring of pin 2 of the IBBS is available a peak charging voltage

of 14-15 volts will be observed as the battery reaches full capacity.

p/n 725.0002 REV 1.4

Alternately, a ground based charger is available from TCW Technologies LLC., model #

IBBS-12v-CHARGER-LI-FE. This charger may be used for recharging the IBBS unit as

well as keeping it fully charged during long term product storage. (9 months or longer)

Battery Capacity:

The IBBS provides an energy capacity of 3 amp-hours at 12.8 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. With a

fully charged battery, the following average performance can be expected in terms of

operating duration. The operating duration is for an output voltage down to 9.0 volts. (end

point voltage). The battery is also rated for at least 500 shallow discharge cycles, this is

defined as a 10 minute discharge operation at 3 amps followed by 30 minutes of recharge

time.

Nominal Current Draw Duration Effective Nominal Capacity

Total connected load all outputs

1.5 amps 120 minutes 3 amp-hrs

3.0 amps 55 minutes 2.75 amp hrs.

5.0 amps 30 minutes 2.5 amp-hrs

Capacity at Low Temperatures:

-18 C° 75% of effective nominal capacity

-30 C° 70% of effective nominal capacity

-40 C° 45% of effective nominal capacity

Servicing:

The internal battery in the IBBS system is replaceable; however, the IBBS product must be

returned to TCW Technologies, LLC. for this service. Battery life depends strongly on many

factors including operating and storage temperature, number of discharge cycles and depth

of discharge. The battery capacity should be checked at least annually for suitable back-up

power operation of the connected equipment. When the battery capacity no longer meets

the operating criteria of the aircraft it must be replaced. Contact TCW Technologies, LLC.

regarding battery replacement.

Storage beyond 9 months:

If the IBBS unit is to be stored without connection to the aircraft for a period greater than 9

months it must be connected to a source of DC power to maintain the battery’s charge. Only

connections to the ground terminal and the main power terminal are required. Connect Pin

5 (main power) and Pin 9 (ground) of the IBBS to any source of regulated DC power at 14-15

volts with a current capability of at least 1.8 amps to accomplish full recharging. Ensure the

IBBS unit is in an ambient temp of 0-40 C° for ground-based charging. Charger model

IBBS-12v-CHARGER-Li-Fe is available from TCW Technologies, LLC. to simplify this

activity.

p/n 725.0002 REV 1.4

Normal Product Operation:

For normal operation the following is the recommend operating procedure, the following is

the basis for a flight manual supplement. The following is the standard procedures.

Start-up Procedure:

1) Prior to turning on the Aircraft Master Switch, turn ON the IBBS Back-up Power master

switch.

2) Turn on any equipment that derives back-up power from the IBBS product.

3) Ensure the connected equipment successfully boots-up and is operating properly. (During

this period of time the equipment is running off of the back-up battery within the IBBS

product. This test ensures the transfer circuit and back-up battery are properly working)

4) Verify the low voltage warning light is indicating a low voltage condition.

5) Turn on the Aircraft Master Switch; ensure the connected equipment remains energized.

The low voltage warning light should go out.

(If a separate avionics bus is utilized, this may need to be turned ON to continue the operation of equipment

connected to the IBBS output.)

6) Start and operate the aircraft according to normal operating procedures.

Shut-down Procedure:

1) Shut down the aircraft engine using normal procedures.

2) Shut down the Aircraft Master Switch

3) Verify that the equipment that derives back-up power from the IBBS remains ON

4) Turn-off the Back-up Power Master switch, ensure that equipment powers down.

(This procedure further ensures the operation of the transfer circuit within the IBBS.)

Emergency Procedure for loss of main aircraft electrical power:

1) Operate the Aircraft Master Power Switch per the Emergency Procedure checklist already

established for the aircraft.

2) Ensure the Back-up Master Switch is in the ON position.

3) Land aircraft as soon as practical to resolve the loss of main electrical power.

p/n 725.0002 REV 1.4

Instructions for Continued airworthiness:

GENERAL USE

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 LLC. for details.

Procedure for endurance testing

All applications except electronic ignition systems

1) Turn off the Aircraft Master Switch

2) Turn on the Back-up Power Master Switch

3) Turn on all equipment connected to and supplied with back-up power from the IBBS

product.

4) Measure and record at least the following information: The time until the first piece of

connected equipment no longer functions or the time until the output of back-up power

supply voltage drops to 9.5 volts. Discontinue the test when the back-up battery voltage

falls below 9.5 volts.

5) After completing the endurance test, recharge the IBBS product by operating the system

with the Aircraft Master Switch in the ON position for up to two hours. This may be done

by operating the aircraft in conditions known to not require back-up power or by powering

the aircraft system on a suitable ground power source as described in the section:

Ground Base Recharging.

6) Record the results of the endurance testing in the aircraft logbook.

7) If the IBBS no longer meets the endurance testing requirement, the back-up battery may

need replacement.

p/n 725.0002 REV 1.4

Instructions for Continued Airworthiness:

Electronic Ignition System Back-up

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 or at least 30 minutes, whichever is

greater.

As an alternate to these tests the IBBS unit may be returned to TCW Technologies for a

loaded endurance test, contact TCW for details.

Procedure for endurance testing of system providing back-up power

to electronic ignition systems:

COMPLETE THESE STEPS IN ORDER! Perform these tests with the aircraft properly

secured on the ground, these are not flight test procedures.

1) Start the aircraft using normal starting procedures, including turning ON the Back-up

Master switch

2) Select engine operation based on the use of only the electronic ignition module provided

with back-up battery power.

3) PULL the circuit breaker feeding pins 4,5 of the IBBS system, confirm engine continues to

run.

4) PULL the circuit breaker feeding pins 6,7,8 of the IBBS, confirm the engine continues to

run.

5) Perform the following; test A or test B:

Test A: abbreviated battery test:

Monitor engine operation and voltmeter reading on any of pin 12,13,14,15, the back-up

power output. Confirm back-up voltage begins above 13 volts and for a period of 15

minutes remains above 12.5 volts. If these requirements are met the battery pack is

satisfactory.

Test B: full endurance test:

Operate the engine on the electronic ignition system for the required minimum run-time

requirement (at least 30 minutes), monitor the back-up battery voltage on the voltmeter

connected to an output pin, the battery voltage must remain above 11 volts for the

duration of the test. If this requirement is met the battery pack is satisfactory.

p/n 725.0002 REV 1.4

6) Turn off the Back-up Master Switch and confirm that the engine turns off.

7) If all these tests pass, the IBBS system is functioning properly, record the results in the

aircraft logbook.

8) If any of these tests fail, the IBBS system is not functioning properly and corrective action

must take place. If the IBBS no longer meets the endurance testing requirement, the

back-up battery may need replacement or service.

9) Return all pullable breakers to the normal ON position and ensure aircraft engine is

properly returned to the off position by following normal run and shut down procedures.

10)After completing these tests, recharge the IBBS product by operating the system normally

for up to 1.5 hours. This may be accomplished by operating the aircraft in conditions

known to not require back-up power or by powering the aircraft system on a suitable

ground power source as described in the section: Ground Base Recharging.

Service Life:

Expected service life for the internal battery pack is greater than 500 discharge

cycles. Operational performance must be checked at least annually per the requirements

for continued airworthiness listed above. At the end of 72 months of service installation the

internal battery pack must be replaced.

p/n 725.0002 REV 1.4

SPECIFICATIONS:

Input Voltage* 13.7-15 volts DC for battery charging.

Transition Voltage** 10.5-11.5 volts

Input Current: 1.8 amps on main input for charging

0.7 amps for battery heating at low temps

Pass-thru Current: 5 amps continuous, 10 amps peak (30 seconds)

Output Voltage: 10-14 volts DC during back-up operation

Output Current: 5 amps continuous

10 amps peak for radio transmissions and transient

load (30 second duration max)

Battery: Internal sealed Li-Fe-PO4, nominal 12.8 volts

Charger: Integral high performance fast charger with cell balancing and

thermal monitoring

Surge Protection: 34 volt active clamp, 1500w 10/1000uS waveform

Wiring: 15 pin male D-sub on product.

Enclosure: Aluminum 7.7” x 2.3” x 1.6”

Weight: 18 oz.

Temperature range: Operating: -40 C° to 60 C°

Charging: -40 C° to 40 C°

Connector: Standard density 15 pin D-sub, male on product

Note: Input voltages in excess of 18 volts or reverse polarity may damage unit

*minimum input voltage to start a charge cycle is 13.7 volts, this ensures aircraft alternator is running prior to

starting a charge cycle.

**transition voltage is the voltage level on the input (pin 5) that causes the system to provide output power via the

internal back-up battery

p/n 725.0002 REV 1.4

Functional performance

Certification:

FAA TSO-C179a

Performance

Qualification:

RTCA DO-311 Minimum Operational Performance

Standards for Rechargeable Lithium Battery Systems

Environmental

Qualification:

RTCA DO-160 (F)

F2BBBSC1XYXXF2ZB(IX)XXXXAZ(ZC)[TT]MA3H3L3XXAX

DO-160(G), Section 14, cat S; Section 8, cat S(c1), Section 7, cat B,

Section 22, cat A3H3L3

Power input

14 volts nominal, 1.8 amps charging, 0.7 amps heating

Power Output

12.8 volts nominal, 5 amps continuous

Battery capacity

2.75 amp-hrs at 1C rate @ 25 C°

Maintenance

Perform annual capacity check

p/n 725.0002 REV 1.4

Wiring connector detail:

Male on IBBS unit

Female on aircraft wiring harness

View from back of connector

Pin # Function

5 PWR + in, charge, sensing

2 Batt-info

3 Low Volt Warn

12 Output

13 Output

14 Output

15 Output

6 Pwr +, pass-thru input

1 Enable- backup switch

9 Ground

10 Ground

11 Ground

15 pin Male Dsub on unit

7 Pwr +, pass-thru input

8 Pwr +, pass-thru input

4 Pwr +, battery heater

p/n 725.0002 REV 1.4

Product mounting footprint

4 mounting holes. 0.190

1.50

7.25

2.290

7.70

Top View

0.225

All dimensions in inches

Product height = 1.75”

C.G at center of all axis

p/n 725.0002 REV 1.4

General Wiring Diagram

7.5 amp

Main Aircraft Bus

Back-up Power Master

15 pin, female

Dsub connector

Back-up power output

Total combined load on all outputs = 5 amps

Batt-info to volt meter

Back-up power output

20 awg

www.tcwtech.com

Emmaus, PA USA

MODEL: IBBS-12V-6AH-CRT

Input: 10-15 volts DC

Output: 12 volts,8 amps

INTEGRATED

Back-up Battery

SYSTEM

Back-up power output

20 awg

10 amp

Main Aircraft Bus

charge/sense

pass-thru

Pin # Function

15 pin Male Dsub on unit

12 Output

13 Output

14 Output

15 Output

9 Ground

10 Ground

11 Ground

5 PWR + in, charge, sensing

2 Batt-info

3 Low Volt Warn

6 Pwr +, pass-thru input

1 Back-up master switch

7 Pwr +, pass-thru input

8 Pwr +, pass-thru input

4 PWR + in, battery heater

Pin # Function

-Low Voltage Warning LED,

25 mA max

battery heat

p/n 725.0002 REV 1.4

Battery

Master Solenoid

Wiring Diagram IBBS-12v-3ah-CRT

Equipment being

powered via IBBS

Example wiring for systems without back-up power inputs

Equipment without Back-up Power Input

5 amp

Main Aircraft Bus

Back-up Power Master

Battery-Info

Back-up power output

20 awg

22 awg

20 awg

main power input

15 pin, female

Dsub connector

-Low Voltage Warning LED

NOTE: Use redundant ground pins 9,10,11

Use redundant power inputs 6,7,8

based on load current of connected

equipment

10 amp

15 output

output

www.tcwtech.com

Emmaus, PA USA

MODEL: IBBS-12V-3AH-CRT

Input: 10-15 volts DC

Output: 12 volts, 5 amps

INTEGRATED

Back-up Battery

SYSTEM

Close to enable

p/n 725.0002 REV 1.4

Avionics Bus Solenoid

Avionics Bus

Battery

Master Solenoid

Wiring Diagram IBBS-12v-3ah-CRT

Equipment being

powered via IBBS

Example wiring for systems with back-up power inputs

Equipment with Back-up Power Input

5 amp

Main Aircraft Bus

Back-up Power Master

Battery-Info

Back-up power output

20 awg

22 awg

20 awg

Main power input

15 pin, female

Dsub connector

-Low Voltage Warning LED

NOTES:

10 amp

15 output

output

Back-up power input

3) Use of power pins will power connected equipment even when avionics

bus is OFF via pass thru mode. Use of input pins 6,7,8 is OPTIONAL.

2) Use redundant power inputs 6,7,8 based on load

current of connected equipment.

1) Use redundant ground pins 9,10,11

www.tcwtech.com

Emmaus, PA USA

MODEL: IBBS-12V-3AH-CRT

Input: 10-15 volts DC

Output: 12 volts, 5 amps

INTEGRATED

Back-up Battery

SYSTEM

Close to enable

p/n 725.0002 REV 1.4

ENVIRONMENTAL QUALIFICATION STATEMENT

NOMENCLATURE: Integrated Back-up Battery System

MODEL/PART NUMBER: IBBS-12V-3AH-CRT

TSO NUMBER: C179a

MANUFACTURES SPECIFICATIONS:

Minimum Performance Specification:

IBBS product specification p/n 720.0004

QUALIFICATION STANDARD:

RTCA Do-160(f), dated Dec 6, 2007

RTCA Do-160(g), dated Dec 8, 2007 (*)

CONDITIONS

SECTION

DESCRIPTION OF TEST

Temperature and Altitude

Low Temperature

High Temperature

Decompression

Overpressure

4.5.1

4.5.2

4.6.2

4.6.3

Category B2

Operating Low Temp = -45 C°

Operating High Temp = +70C°

Altitude = +55,000 ft.

-15,000

temp variation

Category B

Humidity

Category B

operational shock*

Category B

vibration*

Category S, curve C

explosion

Category X

waterproofness

Category Y

fluid susceptibility

Category x

sand and dust

Category X

fungus

Category F

salt fog salt spray *

Category S, curve C

magnetic effect

Category Z

power input

Category B(IX)

voltage spike

Category A

audio freq susceptibility

Category Z

induced sig susceptibility

Category ZC

Spikes induced into interconnect cables

19.3.4

Category CC

RF susceptibility *

Category TT

Emission of RF energy

Category M

lightning environment *

Category A3H3L3 level 3

lightning direct

Category X

icing

Category X

ESD

Category A

flammability

Category X

RTCA DO-160 F,G

B2BBBSC1XYXXF2ZB(IX)XXXXAZ(ZC)[TT]MA3H3L3XXAX

p/n 725.0002 REV 1.4

Service and Support information:

610-928-3420 TCW Technologies, LLC.

www.tcwtech.com 2955 Main Road East

email: [email protected] Emmaus, PA 18049

Warranty Information

TCW Technologies, LLC.

During the first 12 months from the date of purchase and subject to the conditions hereinafter set forth, TCW Technologies,

LLC. (TCW) will repair or replace to the original user or consumer any portion of your new TCW product which proves

defective due to defective materials or workmanship of TCW. Contact TCW Technologies for warranty service. TCW shall

have and possess the sole right and option to determine whether to repair or replace defective equipment, parts or components.

Damage due to equipment, environment or conditions beyond the control of TCW 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.

THIS WARRANTY WILL NOT APPLY: (a) to defects or malfunctions resulting from failure to properly install, operate or

maintain the unit in accordance with printed instructions provided; (b) to failures resulting from abuse, accident, or negligence;

(c) to normal maintenance services and the parts used in connection with such service; (d) to units which are not installed in

accordance good trade practices; or (e) to unit used for purposes other than for what it was designed and manufactured.

RETURN OR REPLACED COMPONENTS: any item to be replaced under this Warranty must be returned to TCW

Technologies in Emmaus, PA, or such place as TCW may designate, freight prepaid.

PRODUCT IMPROVEMENTS: TCW reserves the right to change or improve its products or any portions thereof

without being obligated to provide such a change or improvement for units sold and /or shipped prior to such

change or improvement.

WARRANTY EXCLUSIONS: as to any specific TCW product, after the expiration of the time period of the warranty

applicable thereto as set forth above. THERE WILL BE NO WARRANTIES, INCLUDING ANY IMPLIED

WARRANTIES OR MERCHANTABILITY OR FITNESS FOR ANY PARTICULAR PURPOSE.

Some states do not allow limitations on how long an implied warranty lasts, so the above limitation may not apply to

you. No warranties or representations at any time made by any representative of TCW shall vary or expand the

provisions hereof.

LIABILITY LIMITATION: IN NO EVENT SHALL TCW OR ITS AFFILIATES BE LIABLE OR RESPONSIBLE FOR

CONSEQUENTIAL, INCIDENTAL OR SPECIAL DAMAGES RESULTING FROM OR RELATED IN ANY MANNER

TO ANY TCW PRODUCT OR PARTS THEREOF.

Some states do not allow the exclusion or limitation of incidental or consequential damages, so the above limitation

or exclusion may not apply to you.

This Warranty gives you specific legal rights and you may also have other rights which vary from state to state. In

the absence of other suitable proof of this installation date, the effective date of this Warranty will be based upon the

date of manufacture plus one year. Direct All Notices To: Warranty and Product Service Department, TCW

Technologies, 2955 Main Road East. Emmaus, PA 18049

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