TI5200 GPU-24
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Section 3 – Operating Procedures
3.1 – Operating Procedures
This section covers normal procedures and steps necessary to ensure safe and effi cient operation of the
unit.
NOTE
!
When not in use, the unit should always remain plugged into a suitable ac
power source to ensure operational readiness at all times.
NOTE
!
If current demand exceeds 25 amps, converter output voltage will drop below
28.5 Vdc and two or more LED status indicator bars will illuminate. If all
LED status indicator bars illuminate, both the converter and power cells are
supplying 24 Vdc power output.
3.2 – General
The user should be well-versed in both pre-use and functional checks for correct operations of this unit.
Knowledge of the operating limits, restrictions, performance, unit capabilities and functions aids in correct
and safe operations. Compliance with the instructions in this manual affect operational safety as well as the
warranty of the unit.
3.3 – Operating Limits and Restrictions
The minimum, maximum and normal operating ranges result from careful engineering and evaluation of test
data. These limitations must be adhered to during all phases of operation.
3.4 – Performance
Refer to Section 7, PERFORMANCE DATA to determine the capability of the unit. Consideration must be given
to changes in performance resulting from variations in ambient temperature, mode of operation, state of
charge (with or without ac power), and aircraft dc bus system ineffi ciency (voltage drops).
3.5 – Engine Starting Power
The unit should always be charged above 80% prior to ground support engine starting. However, circumstances
may exist during use where unit recharge is not readily available and immediate external engine starting
power is required. The following provides minimum states of charge necessary to provide ample power for
an effi cient engine start under specifi c current load demands.
MINIMUM CHARGE
MINIMUM CHARGE
This section covers normal procedures and steps necessary to ensure safe and effi cient operation of the
Refer to Section 7, PERFORMANCE DATA to determine the capability of the unit. Consideration must be given
charge (with or without ac power), and aircraft dc bus system ineffi ciency (voltage drops).
an effi cient engine start under specifi c current load demands.
MINIMUM CHARGE
ENGINE START PEAK CURRENT Requirements
MINIMUM CHARGE
Under 1200 peak starting amps
0-40% charged
1200 - 1500 peak starting amps
40-50% charged
1500 - 1800 peak starting amps
50-60% charged
1800 - 2100 peak starting amps
60-70% charged
2100 - 2400 peak starting amps
70-80% charged
2400 - 3000 peak starting amps
80-100% charged
If current demand exceeds 200 amps, converter output voltage will drop
below 28.5 Vdc and two or more LED status indicator bars will illuminate.
If all LED status indicator bars illuminate, both the converter and power cells
are supplying 24 Vdc power output.
