Garmin GI 275 Installation Manual page 65

The aircraft electrical system is capable of supporting the GI 275 system if the maximum electrical system
demand, as documented on the tabulated ELA form, does not exceed 80% of the alternator capacity. It is
permissible for the electrical load to exceed 80% of the alternator capacity when the pitot heat and landing
light are both switched on during the takeoff/landing phase of flight. In this case, the electrical load must
not exceed 95% of the alternator capacity. If the pitot heat is on and the landing light is off, the electrical
load may not exceed 80% of the alternator capacity.
NOTE
The Electrical Load Analysis for this installation is only valid for modifications performed
under this STC. Subsequent changes to the aircraft electrical system will require a new
load analysis.
190-02246-14
Rev. 11
GI 275 STC EIS & MFD Installation Manual
Page 3-23