M833811-00
Shadin Avionics
INSTALLATION MANUAL
AIS-380 FUEL FLOW ADAPTER
Rev: C
P/N 833811-00
Page: 10 of 20
Shadin Avionics
6831 Oxford Street
St. Louis Park, MN 55426
USA
The example for a Bell 412 EPI installation 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
37
Fuel Flow
Interface 1
17
2
1 16
+ 28 VDC
ARINC 429
Input 1
ADC
Source
(optional)
Heading
Source
(optional)
ARINC 429
Input 2
ARINC 429
Output 1
Fuel Flow
Interface 2
Serial
RS-232
I/O Port 1
Serial 1
(Maintenance)
Bell ADIU
RX pos
RX neg
35
36
ARINC 429
Output 2
TX
20
Serial
RS-232
Output 2
Nav
Receiver
(optional)
28 RTN
+
+
28 V POWER
Serial
RS-422
Receiver 4
26
11
AIS-380
Fuel Flow
Adapter
SIGNAL
SIGNAL
24
39
PWR
RTN
PWR
RTN
14
28
13
42
LEFT
FF
XDCR
A
B
C
RIGHT
FF
XDCR
A
B
C
NC
NC
Figure 4: Bell 412 EPI Installation
Provisional wiring and interconnections to the ADIU can be found in Bell STC SR09600RC.
1.7
INSTALLATION NOTES
Aircraft power +28 VDC can be connected to both pins 2 and 17 for redundancy as shown above.
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.
