190-02246-10 GI 275 Part 23 AML STC Installation Manual
Rev. 11 Page 3-29
3.5 Electrical Load Analysis
An Electrical Load Analysis (ELA) must be completed before the GI 275 is installed to verify that the
aircraft electrical system is adequate. The purpose of the ELA is to show compliance with 14 CFR 23.1351
and 23.1353(h) by demonstrating that the maximum electrical system demand does not exceed 80% of the
alternator data plate rating and the aircraft battery is capable of providing electrical power to equipment
essential for continued safe flight and landing in the event of a complete loss of the primary electrical
system. Satisfactory completion of the ELA must be recorded on FAA Form 337.
NOTE
Certain operating requirements (e.g., 14 CFR Part 135) may impose additional requirements in
the event of electrical power loss. It is the installer’s responsibility to ensure that the aircraft meets
the additional requirements if used for these operations.
Typical current draw of all GI 275 system components is summarized in Table 3-24.
Table 3-24 LRU Current Draw
Notes:
[1] All GI 275 current draws include the GMU 11/44B and GTP 59.
LRU
Current Draw [1]
14V System 28V System
Typical Maximum Typical Maximum
GI 275 Base (without battery) 0.65 A 0.75 A 0.32 A 0.40 A
GI 275 Base (with battery) 0.65 A 1.70 A 0.32 A 0.80 A
GI 275 ADAHRS (without battery) 0.75A 0.90 A 0.35 A 0.50 A
GI 275 ADAHRS (with battery) 0.75A 2.00 A 0.35 A 1.00 A
GI 275 ADAHRS+AP (without battery) 0.80 A 1.10 A 0.40 A 0.65 A
GI 275 ADAHRS+AP (with battery) 0.80 A 2.00 A 0.40 A 1.00 A
GEA 110 0.30 A 0.60 A 0.15 A 0.30 A
GEA 24 0.20 A 0.40 A 0.10 A 0.20 A
GSB 15 Dual Type-A
(charging from both ports)
Varies 2.86 A Varies 1.43 A
GSB 15 Type-A & C and Dual Type-C
(charging from both ports)
Varies 4.86 A Varies 2.43 A
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