Garmin GDL 82 Installation Manual

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Garmin GDL 82 Installation Manual Manual pdf 23 page image

GDL 82 Mooney M20( ) Series STC Installation Manual 190-01810-10Rev. 1Page 16 of 493.5 Electrical Load AnalysisBefore the GDL 82 is installed, an Electrical Load Analysis (ELA) must be completed on the aircraft toverify the electrical system can support the GDL 82. The purpose of the ELA is to show compliance with14 CFR 23.1351 by demonstrating that the maximum electrical system demand does not exceed 80% ofthe alternator data plate rating. Satisfactory completion of the ELA must be recorded on FAA Form 337.GDL 82 current draw values are listed in Table 1-3.The net change to the electrical load with the GDL 82 installed must be determined. The amendedelectrical load calculation documenting the load change should be filed with the aircraft permanentrecords.A complete electrical load analysis must be performed to show that the capacity of the alternator orgenerator is sufficient for the electrical load. For guidance on preparing an ELA, refer to ASTM F2490-05, Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis.3.5.1 Aircraft with Existing Electrical Load AnalysisIf there is an existing aircraft electrical load analysis for the aircraft, it must be updated to reflect themodification. It must show the electrical system has adequate capacity to supply power to the modifiedsystems in all expected conditions. Add the maximum current draw of the GDL 82 to the ELA and verifythat the electrical load remains at or below 80% of the rated alternator (or generator) current. Refer to theaircraft manufacturer’s documentation for guidance on revising and maintaining the electrical loadanalysis.3.5.2 Aircraft without Existing Electrical Load AnalysisAs an alternative to adding the GDL 82 to an existing ELA (Section 3.5.1), an ELA can be determined byload measurement, under different operating conditions, using the tabulation form provided below and thefollowing steps. During measurement, applied electrical system loads must account for combinations anddurations probable in aircraft operation.CAUTIONTo avoid damage to equipment, ensure the ammeter is capable of handling the expected load.CAUTIONThe Pitot Heat must only be switched on long enough to take the current measurement and thenswitched off. The Pitot probe can get hot so care must be exercised to avoid burns or damagingthe unit.NOTENormal Operation is when the primary electrical power generating system is operating normally.Emergency Operation is when the primary electrical power generating system is inoperative anda back-up electrical power generating system is being used. This typically requires load sheddingof non-essential equipment to provide adequate electrical power to essential required equipmentfor safe flight and landing of the airplane.