Shadin Avionics AIS-380 User manual

SHADIN AVIONICS
www.shadin.com Customer Service: [phone] [e-mail]
AIS-380 FUEL FLOW ADAPTER
P/N: 833811-01
INSTALLATION MANUAL
MANUAL P/N: M833811-01
REV C
SHADIN AVIONICS
Sales: [phone]
www.shadin.com

DOCUMENT
AIS-380 Fuel Flow Adapter
Control SC1
INSTALLATION MANUAL
Revision C
M833811-01
Page: 2 of 30
SHADIN AVIONICS
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REVISION LOG
Rev Date ERN DESCRIPTION
–
22 JAN 2016
1509/004
Baseline Release
A
16 OCT 2018
1810/004
Corrected typo bit 29 on page 8
B
15 JAN 2019
1901/001
Updated table 1 and deleted Bell 412 EPI Installation
C
23 JAN 2020
2001/009
Added bonding section, section 5 clarification and updated
company address
digitally signed
by ShadinCM-zk
2020.01.24
11:36:45 -06'00'

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AIS-380 Fuel Flow Adapter
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INSTALLATION MANUAL
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TABLE OF CONTENTS
1OVERVIEW .....................................................................................................................5
1.1 SCOPE ..............................................................................................................................5
1.2 PRODUCT DESCRIPTION................................................................................................ 5
2SPECIFICATIONS...........................................................................................................6
2.1 PHYSICAL.........................................................................................................................6
2.2 ELECTRICAL..................................................................................................................... 6
2.3 FUNCTIONAL....................................................................................................................6
2.3.1 INPUTS:.....................................................................................................................................6
2.3.2 OUTPUTS:.................................................................................................................................6
2.3.3 AIRDATA AND HEADING CONVERSION (OPTIONAL) ..........................................................8
2.4 ENVIRONMENTAL ............................................................................................................ 8
2.5 SOFTWARE CERTIFICATION........................................................................................... 9
2.6 REGULATORY CERTIFICATION...................................................................................... 9
2.7 RELIABILITY...................................................................................................................... 9
2.8 ACCURACY.......................................................................................................................9
3INSTALLATION.............................................................................................................10
3.1 LIMITATIONS .................................................................................................................. 10
3.2 INCOMPLETE SYSTEM.................................................................................................. 10
3.2.1 PERFORMANCE STANDARDS..............................................................................................10
3.3 MOUNTING ..................................................................................................................... 10
3.4 ELECTRICAL CONNECTION.......................................................................................... 10
3.4.1 TYPICAL INSTALLATION WIRING.........................................................................................11
3.4.2 DC TO FREQUENCY INSTALLATION EXAMPLE .................................................................12
3.4.3 GARMIN RECEIVER INSTALLATION EXAMPLE ..................................................................14
3.4.4 SINE TO SQUARE WAVE CONVERTER INSTALLATION EXAMPLE..................................15
3.5 BONDING........................................................................................................................ 15
3.6 REPAIR ........................................................................................................................... 15
4ENVIRONMENTAL QUALIFICATION FORM (EQF) ....................................................16
5CONFIGURATION TOOL..............................................................................................17
5.1.1 CONFIGURATION TOOL SOFTWARE INSTALLATION........................................................18
5.1.2 USING THE CONFIGURATION TOOL.....................................................................................21
6APPENDIX A: INSTALLATION DRAWING..................................................................26
7APPENDIX B: INSTALL KIT, PARTS LIST..................................................................29

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LIST OF FIGURES
Figure 1 : AIS-380 Fuel Flow Adapter Overview.................................................................................................5
Figure 2 : Air Data Computer/Heading ARINC 429 to RS-232...........................................................................8
Figure 3 : Standard Fuel Flow Configuration................................................................................................... 11
Figure 4 : DC Fuel Flow Installation with P/N 630502 ..................................................................................... 12
Figure 5 : Garmin Receiver Installation............................................................................................................ 14
Figure 6 : Sine to Square Wave Converter Installation.................................................................................... 15
Figure 7 : Field Configuration Cable ................................................................................................................ 17
LIST OF TABLES
Table 1 – ARINC 429 Data I/O.............................................................................................................................7
Table 2 – DC Fuel Flow K-Factors.................................................................................................................... 13
Table 3 – Serial Output Formats....................................................................................................................... 24

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1 OVERVIEW
The information in this manual is subject to change without notification.
1.1 SCOPE
This manual is intended to determine a proper installation of the AIS-380 FUEL FLOW ADAPTER. Installation
instructions should be read and followed.
1.2 PRODUCT DESCRIPTION
The AIS 380 Fuel Flow is a product designed to provide fuel flow on a digital output bus to a display or GPS
receiver that can receive ARINC 429 or RS-232. The AIS Fuel Flow receives a digital frequency signal from a
fuel transducer or equivalent, ARINC 429 air data, and ARINC 429 heading. The AIS Fuel Flow combines this
data and re-transmits it on an ARINC 429 or RS-232 serial output bus.
The ARINC 429 speed, K-factor, single/twin engine selection, fuel density, and serial output formats are
configurable using the PC based configuration tool referenced later in this installation manual.
A basic overview is shown below in Figure 1.
AIS-380
Fuel Flow Adapter
P/N 833811
ARINC 429
HS/LS Receiver 1
ARINC 429
HS/LS Receiver 2
ARINC 429
HS/LS Transmitter 1
ARINC 429
HS/LS Transmitter 2
SERIAL 1
RS-232
Maintenance
SERIAL 2
RS-232 Air Data/
Fuel Flow Data
Output
SERIAL 4
RS-422 Fuel Flow
Parameter Receiver
Pulse/Freq 1
Input
Pulse/Freq 2
Input
Figure 1 : AIS-380 Fuel Flow Adapter Overview
The features which are applicable to all standard installations are listed below:
•Two +12 VDC power supplies are available for powering fuel flow transducers
•ARINC 429 inputs are forwarded to the ARINC 429 outputs
•ARINC 429 speed (high or low) is configurable. Each ARINC 429 channel input and output speed is
matched when configured, e.g. ARINC 429 channel 1 input channel set for high speed results in
ARINC 429 channel 1 output set for high speed
•Fuel Flow labels 244 (Total Fuel Flow) and 347 (Left and Right independent Fuel Flow based on SDI)
are generated and output at an 8 Hz rate when configured for normal fuel flow format.

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2 SPECIFICATIONS
For a complete listing of product qualifications please review the Environmental Qualification Form (EQF)
found in Section 4.
2.1 PHYSICAL
Nominal Dimensions: 6.90”L x 4.24”W x 1.57”H
Weight: 0.7 pounds (lbs)
Mounting: 4 Screws (See Installation Drawing D833811-01)
Mounting Locations: 6.25”L x 2.00”W
2.2 ELECTRICAL
Power Supply Voltage: +28VDC Nominal
Supply Current: 100mA at +28VDC
Protection: Not internally fused
2.3 FUNCTIONAL
2.3.1 INPUTS:
The AIS-380 accepts the following inputs
•Two Discrete Fuel Flow pulse/frequency signals
•One RS-232 Serial Interface for Maintenance
•One RS-422 Serial Interface compatible to fuel flow parameters
•Two ARINC 429 High Speed or Low Speed signals with Air Data and Heading labels as shown in
Table 1 below.
2.3.2 OUTPUTS:
The AIS-380 provides the following outputs
•ARINC 429 label set described in section 1.4 forwarded from input
•Two ARINC 429 High Speed or Low Speed signals
oLabel 244 and 347
•One RS-232 Serial Interface with fuel flow data, reference Table 3 for serial output formats.
Table 1 below defines the ARINC 429 labels which are received at the input of the AIS-380 and the labels that
are transmitted out.

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Table 1 – ARINC 429 Data I/O
ARINC 429 Input
ARINC 429 Output
ARINC 429
Channel 1
102, 203, 204, 205, 206, 207,
210, 211, 212, 213, 234, 235,
236, 237, 312, 314, 350, 353
102, 203, 204, 205, 206, 207,
210, 211, 212, 213, 234, 235,
236, 237, 312, 314, 350, 353,
244, 347
ARINC 429
Channel 2 320 320, 244, 347
Labels 244 and 347 are the labels generated by the AIS-380 and are shown in bold at the ARINC 429 output.
All of the data listed in the ARINC 429 Output column in Table 1 above is sent out on SERIAL 2 in RS-232
format.
Label 347 - The AIS-380 converts the fuel flow from gallons/hr to lbs/hr to be transmitted on label 347. Label
347 provides fuel flow per engine by using the SDI bits to indicate which engine, and sending
each engine’s data in a round robin fashion. SDI bits 10,9 = 0,1 (Left), 1,0 (Right). Transmit
interval = 125 msec, for an effective transmit interval of 250 msec per engine. The data format is
as follows:
Bits
1 2 3 4 5 6 7 8
9 10
11 12
13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28
29
30 31
32
Label 347
SDI
0 0
DATA
S
SM
Parity
Data type BNR Equipment ID: 029 Bit 29 = 0 (Sign)
Significant bits 16 Bit 30, 31 = 1, 1 (Normal Op)
Resolution 0.5 lbs/hr (LSB value) Bit 30, 31 = 0, 0 (Failed)
Range 32768 lbs/hr Bit 32 ⇒ODD Parity
Label 244 - The AIS-380 outputs Total Fuel Flow Rate on label 244 also in lbs/hr. Label 244 provides total
fuel flow. Transmit interval = 125 msec, for an effective transmit interval of 250 msec per engine.
The data format is as follows:
Bits
1 2 3 4 5 6 7 8
9 10
11 12
13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28
29
30 31
32
Label 244
0 0
0 0
DATA
S
SM
Parity
Data type BNR Equipment ID: 08D Bit 29 = 0 (Sign)
Significant bits 16 Bit 30, 31 = 1, 1 (Normal Op)
Resolution 0.5 lbs/hr (LSB value) Bit 30, 31 = 0, 0 (Failed)
Range 32768 lbs/hr Bit 32 ⇒ODD Parity

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2.3.3 AIRDATA AND HEADING CONVERSION (OPTIONAL)
See Figure 2 below
Inputs: The Air Data and Heading sources provide data to the AIS-380 via ARINC 429 inputs. ARINC 429
Channel 1 accepts Altitude, Airspeed, and OAT ARINC 429 labels. ARINC 429 Channel 2 accepts the
Mag Heading ARINC 429 label. See Table 1 above for specific ARINC 429 labels used.
Output: The AIS-380 transmits the data along with fuel flow data to the GPS via the RS-232 port, Channel 2.
The RS-232 serial format is programmed using the Maintenance Interface. The available formats are
listed in Table 3 below in Section 5.1.2.
RS-232 Ch 2
GPS
Air Data Computer
Mag Heading ARINC 429 In CH 2
ARINC 429 In CH 1
AIS-380
Fuel Flow Adapter
Figure 2 : Air Data Computer/Heading ARINC 429 to RS-232
2.4 ENVIRONMENTAL
Qualification testing was conducted on P/N 833811-00 which uses the identical hardware as the 833811-01.
MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION:
RTCA/DO-160F [A4X]BBB[R(B,B1) U2(F,F1)]EXXXXXZ[BXX]AZ[CC][RR]M[XXJ33]XXAX
Operating Temperature -40°C to +70°C
Storage Temperature -55°C to +85°C
Equipment can run indefinitely within stated environmental range with no external cooling.

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2.5 SOFTWARE CERTIFICATION
This product was developed in accordance with RTCA/DO-178B Design Assurance Level C.
2.6 REGULATORY CERTIFICATION
This product meets requirements of TSO-C44c INCOMPLETE SYSTEM.
2.7 RELIABILITY
MTBF (Mean Time Between Failures) Greater than 20,000 hours
Mean time between failures (MTBF) is calculated following MIL-HDBK-217F guidance as a starting point, when
available field or vendor data is used in place of MIL-HDBK-217F predictions. The AIS-380 prediction is for an
environment of airborne, inhabited, cargo. At 20°C the prediction is 36,367 hours and at 40°C it is 22,607
hours.
2.8 ACCURACY
Fuel Flow conversion based on ± 10Hz of max input of 2 KHz typical accuracy is 0.1% of full scale with max
of 0.5% of full scale.

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3 INSTALLATION
3.1 LIMITATIONS
The conditions and tests required for TSO approval of this article are minimum performance standards. It is
the responsibility of those installing this article either on or within a specific type or class of aircraft to
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 if performed under 14 CFR
part 43 or the applicable airworthiness requirements.
This equipment is developed to Design Assurance Level (DAL C). TSO-C44c lists the loss of fuel flow
functionality to be Hazardous. It is the responsibility of those installing this article to determine if it meets the
needs set forth in the System Safety Assessment.
3.2 INCOMPLETE SYSTEM
Shadin Avionics manufactures the AIS-380 833811 as an incomplete system under TSO-C44c, Fuel
Flowmeters and performs to the relevant performance standards of AS407C, Fuel Flowmeters as tested by
RTCA/DO-160F, Environmental Conditions and Test Procedures for Airborne Equipment.
The AIS-380 is compatible with any fuel transducer whose output is a pulse/frequency in the range of 0 to
+13VDC and within 2Hz to 2KHz. Installation Drawing D833811-01, included in Appendix A of this manual,
provides connector J1 pin out information for proper wiring.
The AIS-380 provides data conversion for display. The installer must substantiate the interoperability when
showing compliance to the applicable airworthiness.
3.2.1 PERFORMANCE STANDARDS
The AIS-380 meets the performance standards of AS407C paragraph 3.3 for Environmental Conditions, 4.5
for Power Variations, as defined in section 4 of this document in the Environmental Qualification Form (EQF)
for an incomplete system to the fuel flowmeter. Scale errors are within 0.5% in accordance with paragraph
6.1 of AS407C.
3.3 MOUNTING
The AIS-380 FUEL FLOW ADAPTER (P/N 833811-01) can be mounted in any orientation in the aircraft. The
hardware should be mounted using four (4) number 8 size screws in a dry location. The equipment should be
installed in a controlled temperature and pressurized location.
3.4 ELECTRICAL CONNECTION
Installation Drawing D833811-01, included in Section 6 of this manual, provides connector J1 pinout
information. The wiring type specified on the installation drawing should be used to interface with the
AIS-380.

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3.4.1 TYPICAL INSTALLATION WIRING
Standard installation is shown below in Figure 3.
RX 1 A
RX 1 B
RX 2 A
RX 2 B
40
41
27
12
TX 1 A
TX 1 B
25
10
TX
RX 34
19
SIGNAL
SIGNAL
24
39
PWR
RTN
PWR
RTN
14
28
13
42
37
Fuel Flow
Interface 1
17
2
1 16
+ 28 VDC
ARINC 429
Input 1
ADC
Source
Heading
Source ARINC 429
Input 2
ARINC 429
Output 1
Fuel Flow
Interface 2
Serial
RS-232
I/O Port 1
Serial 1
(Maintenance)
ARINC 429
Output 2
TX
20
Serial
RS-232
Output 2
Nav
Receiver
28 RTN
ARINC
Receiver 2
+ +
28 V POWER
TX 2 A
TX 2 B
26
11
AIS-380
Fuel
Flow
Adapter
ARINC
Receiver 1
LEFT
FF
XDCR
A
B
C
RIGHT
FF
XDCR
A
B
C
Figure 3 : Standard Fuel Flow Configuration
Aircraft power +28 VDC can be connected to both pins 2 and 17 for redundancy as shown in Figure 3.
Alternatively, the unit can be powered only through pin 2, or only through pin 17. The same applies to the
return lines: Pins 1 and 16 can both routed to the aircraft 28 V return, or return can be connected to either pin
1 or pin 16.
Pin 37 is tied directly to the AIS-380 chassis. After the AIS-380 is mounted to the airframe, this pin is
equivalent to airframe ground and can be used as a connection to cable shields in the connector backshell.
The Fuel Flow transducer wiring should be shielded twisted triple wires. Optimal shielding connections are
shown above. Both fuel flow interfaces are wired identically. Tie each shield to pin 37 inside the backshell of
the mating connector to the AIS-380. The shields are then left open at the transducer ends as shown in
Figure 3.

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3.4.2 DC TO FREQUENCY INSTALLATION EXAMPLE
DC Fuel Flow installation with P/N 630502 is shown below in Figure 4.
RX 1 A
RX 1 B
RX 2 A
RX 2 B
40
41
27
12
TX 1 A
TX 1 B
25
10
TX
RX 34
19
L. FF
R. FF
24
39
37
Fuel Flow
Interface 1
17
2
1 16
+ 28 VDC
ARINC 429
Input 1
ADC
Source
Heading
Source ARINC 429
Input 2
ARINC 429
Output 1
Fuel Flow
Interface 2
Serial
RS-232
I/O Port 1
Serial 1
(Maintenance)
ARINC 429
Output 2
TX
20
Serial
RS-232
Output 2
Nav
Receiver
28 RTN
ARINC
Receiver 2
+ +
28 V POWER
TX 2 A
TX 2 B
26
11
AIS-380
Fuel
Flow
Adapter
ARINC
Receiver 1
DC to
Frequency
Converter
P/N 630502
L. FF In -
R. FF In -
L. FF In +
L. FF GND
R. FF In +
R. FF GND
13
6
9
10
11
1
2
3
8
15
Power GND
+28VDC
+ 28 VDC
28 RTN
Left Fuel
Flow Ind.
Right Fuel
Flow Ind.
Figure 4 : DC Fuel Flow Installation with P/N 630502

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The DC Fuel Flow K-Factors and Offsets for specific aircraft/indicators are listed below in Table 2. If a
specific aircraft/indicator is not listed, contact Shadin Avionics technical support at [phone].
Table 2 – DC Fuel Flow K-Factors
Indicator P/N
K-factor
(ppg)
Offset
(Hz)
Beech King Air
90-380009-2
49,050
24
90-380009-5
49,050
24
101-384009-1
49,050
24
101-384153-1,3
19,647
0
PC900-6A0600-XXX
24,599
0
PC900-1A0750-XXX
19,679
0
PC900-1A0800-XXX
18,449
0
Beechjet 400A
PC900-3B2000-PH-1
7,400
0
Piper Cheyenne
3265013-0601
29,470
0
3260513-1201
29,470
0
Cessna Citation
393002-009
9,400
0
9912049-2
9,400
0
9912147-16
10,400
0
VSDL-OC208E
10,400
0
9912560-5
14,020
0
Israeli Aircraft Ind.
Westwind
1291-2
6,700
0

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3.4.3 GARMIN RECEIVER INSTALLATION EXAMPLE
Garmin GTN GPS Source installation is shown below in Figure 5.
Serial 1
(Maintenance)
Serial
RS-232
I/O Port 2
Garmin GTN
RS-232 In 4
RS-232 In 1
RS-232 In 3
RS-232 In 2
ARINC 429
Input CH 2
ARINC 429
Input CH 1
AIS-380
Fuel
Flow
Adapter
RX 1 A
RX 1 B
RX 2 A
RX 2 B
40
41
27
12
ADC
Source
Heading
Source
Fuel Flow
Interface 1
Fuel Flow
Interface 2
SIGNAL
SIGNAL
24
39
PWR
RTN
PWR
RTN
14
28
13
42
LEFT
FF
XDCR
A
B
C
RIGHT
FF
XDCR
A
B
C
TX
RX
34
19 Serial
RS-232
I/O Port 1
TX
20
17
2
1 16
+ 28 VDC
28 RTN
+ +
28 V POWER
37
Figure 5 : Garmin Receiver Installation

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3.4.4 SINE TO SQUARE WAVE CONVERTER INSTALLATION EXAMPLE
The example for a Sine Wave to Square Wave converter installation is show below in Figure 6.
SIGNAL
J1: B
PWR
RTN
J1: A
J1: C
FF
XDCR
Sine to Square
Wave Converter
P/N 631201
J2: B
J2: A
AC Fuel Flow Signal
AC Fuel Flow Signal AIS-380
Fuel Flow
Interface
Figure 6 : Sine to Square Wave Converter Installation
3.5 BONDING
The primary bonding is achieved through metal-to-metal contact of the mounting feet. The two mounting feet
(2.4 x 3.2 inches) are unpainted, chemical conversion coated per MIL-DTL-5541F Type 1, Class 3.
Additionally, the top of the four mounting holes are unpainted to a diameter of roughly 0.45 inches. The
aircraft’s mating surface should be free of paint or any anodizing primer or finish which would prevent solid
grounding contact between the aircraft and the unit.
3.6 REPAIR
Units needing repair or that have failed should be returned to Shadin Avionics. Contact technical support for
assistance by phone at [phone] or [phone], or email at servic[email protected]m

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4 ENVIRONMENTAL QUALIFICATION FORM (EQF)
The AIS-380 hardware was environmentally tested with all functions active to RTCA/DO-160F and is
documented in Shadin Qualification Testing Report SD-110037. Qualification testing was conducted on P/N
833811-00; the hardware is identical to 833811-01, therefore qualified by similarity. Explosive Atmosphere testing
was conducted P/N 833812-10 and passed. The 833812-10 contains the same circuit card assembly and similar
enclosure as the 833811-00/-01, testing is documented in Shadin Qualification Testing Report SD-140054.
NOMENCLATURE: AIS-380 FUEL FLOW ADAPTER
TYPE/MODEL/PART NO: 833811-01 TSO NUMBER:TSO-C44c INCOMPLETE SYSTEM
MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION:
Report SD-110037 and SD-140054, RTCA/DO-160F
MANUFACTURER: Shadin Avionics ADDRESS: 7555 Market Place Drive, Eden Prairie, Minnesota 55344
CONDITIONS
SECTION
DESCRIPTION OF TESTS CONDUCTED
Temperature and Altitude
4.0
A4X
Low Temperature (Operating)
High Temperature (Operating)
Altitude
Decompression
Overpressure
4.0
-40˚C [See remarks (1)]
+70˚C
42,000ft [See remarks (2)]
42,000ft [See remarks (2)]
-15,000ft
Temperature Variation
5.0
Tested to Category B
Humidity
6.0
Tested to Category B
Operational Shock and Crash Safety
7.0
Tested to Category B
Vibration
8.0
Tested to Category R(B,B1)U2(F,F1)
Explosion
9.0
Qual by Similarity to Category E [See remarks (3)]
Waterproofness
10.0
Identified as Category X. Not tested
Fluids Susceptibility
11.0
Identified as Category X. Not tested
Sand and Dust
12.0
Identified as Category X. Not tested
Fungus
13.0
Identified as Category X. Not tested
Salt Spray
14.0
Identified as Category X. Not tested
Magnetic Effect
15.0
Tested to Category Z
Power Input
16.0
Tested to Category BXX
Voltage Spike
17.0
Tested to Category A
Audio Frequency Susceptibility
18.0
Tested to Category Z
Induced Signal Susceptibility
19.0
Tested to Category CC
Radio Frequency Susceptibility
20.0
Tested to Category RR
Radio Frequency Emission
21.0
Tested to Category M
Lightning Induced Transient Susceptibility
22.0
Tested to Category XXJ33
Lightning Direct Effects
23.0
Identified as Category X. Not tested
Icing
24.0
Identified as Category X. Not tested
Electrostatic Discharge
25.0
Tested to Category A.
Fire, Flammability
26.0
Identified as Category X. Not tested
REMARKS:
(1) The 833811-00 was tested to -40°C, beyond the normal A4 category temperature limits.
(2) The 833811-00 was tested to +42,000 ft., beyond the normal A4 category altitude and decompression limits.
(3) The 833812-10 was tested in Explosive Atmosphere category E and passed.

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5 CONFIGURATION TOOL
This section describes the use of the 833811-01 Fuel Flow Configuration Tool. The AIS-380 is to be
configured on a test bench using the configuration tool prior to installation in the aircraft. Below is a list of the
equipment needed and the instructions for installing and configuring the AIS-380 with the configuration tool.
Equipment List
Installation Requirements for PC
•+18 V to +28 V DC Power Supply
•Windows XP SP3 or Windows 7/8/10
•CK833811-01 Configuration Kit for 833811-01*
•1 MB hard disk space
•Desktop or Laptop PC with serial port or USB
adapter if no serial port is available
•Intel® Pentium® Processor, 1.6 GHz
minimum
•500 MB RAM minimum
* Contact Shadin Tech Support to obtain CK833811-01:
Web: www.shadin.com
E-mail: [e-mail]
Phone: [phone]
The software and the cable required for this tool are included in the kit. Alternatively, a cable configured per
Figure 7 below can be built to interface the AIS-380 to the PC. The software is available at no charge at
www.shadin.com.
+28 VDC
Ground
RS-232 Transmit
RS-232 Receive
2
1
34
19
2
5
3
Ground
44-Pin Female
High Density D-Sub
(Mating connector to
AIS-380)
9-Pin Female
Standard D-Sub
(Mating connector to
PC RS-232 Port)
To Power Supply
+18 to +28 VDC
Figure 7 : Field Configuration Cable

DOCUMENT
AIS-380 Fuel Flow Adapter
Control SC1
INSTALLATION MANUAL
Revision C
M833811-01
Page: 18 of 30
SHADIN AVIONICS
www.shadin.com Customer Service: [phone] [e-mail]
5.1.1 CONFIGURATION TOOL SOFTWARE INSTALLATION
(1) Copy 463803-01.msi and setup.exe to a local folder on the PC.
(2) Run setup.exe. The following dialog box will appear:
(3) Follow the Setup Wizard instructions.
(4) Click Next

DOCUMENT
AIS-380 Fuel Flow Adapter
Control SC1
INSTALLATION MANUAL
Revision C
M833811-01
Page: 19 of 30
SHADIN AVIONICS
www.shadin.com Customer Service: [phone] [e-mail]
(5) Choose install location and user access to tool (Default settings are shown in the picture above) and click
on Next.
(6) A Confirm Installation window will appear as shown below, click Next.
(7) A progress bar will appear as seen below

DOCUMENT
AIS-380 Fuel Flow Adapter
Control SC1
INSTALLATION MANUAL
Revision C
M833811-01
Page: 20 of 30
SHADIN AVIONICS
www.shadin.com Customer Service: [phone] [e-mail]
(8) After installation, confirm the following message is displayed: “833811-01 Fuel Flow Configuration has
been successfully installed.”
(9) Close the 833811-01 Fuel Flow Configuration Wizard dialog box.