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Garmin GTN 650 Manual

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GTN 6XX/7XX AML STC Installation Manual 190-01007-A3
Page 3-38 Rev. 4
3.7.3 Performing an Electrical Load Analysis by Measurement
NOTE
According to FAR 23.1351(a)(2)(ii), performing an ELA using electrical measurements is
not acceptable for commuter category airplanes.
If the installation of the GTN/GMA 35 increases the overall load, an electrical load analysis must be
performed. Due to the age of much of the equipment, adequate information regarding the current draw of
this equipment may not exist. One acceptable method of performing an electrical load analysis is to
determine the electrical loads by measurement. The measurements must account for loads applied to the
electrical system in probable combinations and durations for aircraft operation. The maximum electrical
demand should not exceed 80% of the alternator data plate rating. The following section describes how to
perform an ELA for a single alternator / single battery electrical system. This should be modified
accordingly for aircraft with multiple batteries or alternators, and it must be shown that the maximum
electrical demand for each alternator does not exceed 80% of the alternator data plate rating.
In this section the following definitions are used:
normal operation: the primary electrical power generating system is operating normally
emergency operation: the primary electrical power generating system is inoperative
An in-circuit or clamp-on, calibrated ammeter with 0.5 A or better accuracy can be used for current
measurement. Record the continuous (data plate / nameplate) rating for the alternator and battery.
1. Using the blank electrical load tabulation form provided in Figure 3-15, compile a list of
electrical loads on the aircraft (generally, this is just a list of circuit breakers and circuit breaker
switches). Refer to the example in Figure 3-17.
2. Identify whether each load is continuous (e.g. GPS) or intermittent (e.g. stall warning horn,
landing gear).
3. Using the worst-case flight condition, identify whether each load is used in a particular phase of
flight for normal operation. If some loads are mutually exclusive and will not be turned on
simultaneously (e.g. pitot heat and air conditioning), use only those loads for the worst-case
condition.
4. Identify whether each load is used in a particular phase of flight for emergency operation. As a
minimum, these systems include:
o COM Radio #1
o NAV Radio #1
o Transponder and associated altitude source
o Audio Panel
o Stall Warning System (if applicable)
o Pitot Heat
o Landing Light (switched on during landing only)
o Instrument Panel Dimming
… 118 …


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