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True Blue Power, Wichita, KS
REV. B February 11, 2014
7
Manual Number 9018067
SECTION 3
INSTALLATION PROCEDURES
3.1
GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information pertaining to
the installation of the TI250 Static Inverter. After installation of cabling and before installation of the
equipment, ensure that power is applied only to the pins specified in the interconnect diagram.
3.2
UNPACKING AND INSPECTING EQUIPMENT
When unpacking this equipment, make a visual inspection for evidence of any damage that may have
incurred during shipment. The following parts should be included:
a.
Static Inverter –
MCI P/N 6430250-( )
b.
Mating Connector (& cable clamp) – MCI P/N 9016905-1 and 9016905-2
c.
Installation Manual –
MCI P/N 9018067
Equipment not provided:
a.
Mounting Hardware –
four (4) ¼-20 pan head screws
¼” lock washers (optional)
b.
Cable Harness Wire –
See Section 3.3 for specifications
3.3
CABLE HARNESS
Construct the cable harness with regards to the instructions below, and using the Connector Pinout of
Figure 3.3, Figure 3.4, and Wiring Diagram of Table 3.3.
Refer to Section 2: Pre-Installation Considerations in regards to routing precautions.
3.3.1
WIRE GAUGE SELECTION
Use of PTFE, ETFE, TFE, Teflon, or tefzel insulated wire is recommended for aircraft use. Use
the following wire gauges for each of the pins in the connector:
Pin A and C – 14 AWG stranded or solid
Pin B and D – 18 AWG stranded or solid
Pin E and F – 18-24 AWG stranded or solid
Suggestion: If the TI250 is installed in an application where the pin-compatible 500 Watt
MD50 inverter may be later used, the larger wire gauge sizes of the MD50 can be used.
3.3.2
PIN ASSIGNMENT INFORMATION
INVERTER INPUT POWER:
Pin A – Positive DC input +24 to 32 VDC. Connect to the aircraft 28 VDC bus using a 15 Amp
circuit breaker.
Pin D – Negative DC input. Connect to aircraft ground.
Note: Two common practices for the connecting the -28V of power devices in aircraft are:
1.
The negative lead connects from the device to the negative power bus.
2.
The negative lead connects from the device to the negative power bus, and a second
lead connects to the aircraft structure close to the power device.
The TI250 passes DO160G Section 21 Table 1.2.3 conducted emissions testing using both
methods.