Mid-Continent Instruments and Avionics, Wichita, KS
REV. B, October 31, 2012 16 Manual Number 9017782
To assembly the aircraft cable harness and Configuration Module refer to the following
instructions and Figure 2.3:
1) Install a pin/socket as supplied in the Connector Kit using an appropriate crimping tool for
each wire in the aircraft cable harness. Be sure to make the harness long enough to remove
the unit from the front of the panel without stressing the harness (approx. 8” longer than
required to reach the unit connector).
2) Braids from shielded wires should separate from the wire conductors and pulled back from
the pin/socket termination approximately 2” and gathered together.
a. NOTE: Additional chafe protection, such as heat shrink or nylon wire braid is
recommended over the bundle (not including the shields) to prevent wear when
installed in the cable clamp.
3) Insert the pins of the cable harness into the rear of the 15-pin D-Sub connector (Item 4) per
Table 2.1 and Figure 2.2using an appropriate pin insertion tool.
NOTE: The Configuration Module PC Board Assembly contains sensitive electronics that can be
damaged by electrostatic discharge (ESD). Appropriate precautions should be applied prior to
handling this component.
4) Insert the pins of the Configuration Module PC Board Assembly (Item 3) into their
corresponding locations as noted below using an appropriate pin insertion tool.
a. The wires coming from the Configuration Module PC Board Assembly are marked as
follows on the circuit board: TP1, TP2, TP3, TP4.
b. With the D-Sub oriented up (pin locations 1-5 on top), orient the Configuration
Module PC Board Assembly with the electronic parts facing UP prior to pin insertion.
c. Install each pin into the rear of the D-Sub connector as follows:
TP1 = config return = pin 15
TP2 = config data = pin 14
TP3 = config clock = pin 10
TP4 = config power = pin 5
5) Install the D-Sub Backshell Spring (Item 5) as shown.
6) Place the D-Sub Slide Lock (Item 6) over the D-Sub connector.
7) Install the D-Sub connector with Slide Lock and cable harness attached into the Backshell
(Item 9) and secure with (2) screws (Item 8). Verify that the Backshell Spring is between
the Slide Lock and Backshell. Move the Slide Lock back and forth to verify free movement.
8) Route the aircraft wire harness bundle (excluding shield braids) between the two halves of
the Cable Strain Relief Clamp (Item 7). The Clamp should be placed over the chafe
protection installed in Step 2 (if used).
9) Loosely connect the two halves of the Cable Strain Relief Clamp with (2) screws (Item 8).
10) Place the Cable Strain Relief Clamp in the Backshell as shown.
11) Bend the wires of the Configuration Module PC Board Assembly 180 degrees so that the PC
Board has its electrical components facing down as shown. Be careful not to place excess
strain on the solder connections between the wires and the PC Board.
12) Capture the Configuration Module PC Board Assembly into the Backshell by placing the
Backshell Cover (Item 2) on top of the Backshell.
13)
Secure the Backshell Cover onto the Backshell using (2) Screws (Item 9).
14) Bundle the exposed shield braids and secure them to either side of the rear of the Backshell,
along with a connection to aircraft chassis ground, in the threaded holes using the one or
both of the remaining two 4-40 screws provided in the connector kit. Use of a ring terminal
(not included) may be useful.
15) The completed assembly should look as shown. Verify that the Slide Lock operates freely
and that no wires are pinched, nicked, or otherwise damaged.
16) Verify that power and ground signals are installed appropriately before connecting to the
unit.
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