Instruction Manual

Page 2-6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air
Revision 9 190-00915-01
2.1.8 GEA 71 Engine/Airframe Unit (2)
The Garmin GEA 71 Engine/Airframe Units provide engine/airframe data to the G1000 system. Data
received from transducers/sensors is processed and sent to GIA 63Ws (via RS-485 digital interface), and
subsequently to the GDU 1500 MFD. Engine parameters are normally displayed on the MFD. In the
event of MFD failure, the engine parameters can be displayed on PFD 1 and/or PFD 2 using display
reversion. The GEAs are located behind the instrument panel and is mounted in a vertical orientation.
Electrical power to GEA 1 is provided from Dual Fed Bus No. 1 and to GEA 2 from Dual Fed Bus No. 2.
Both GEA units will power-up immediately with external or aircraft power or battery operation.
NOTE
On serial numbers BB-1484, 1486 and subsequent, the electrical system includes the L
ENG INSTR and R ENG INSTR buses which (after this STC) are powered from Dual
Fed Bus No. 1 and No. 2 respectively. On these aircraft, GEA 1 receives power from
Dual Fed Bus No. 1 via the L ENG INSTR bus and GEA 2 receives power from Dual
Fed Bus No. 2 via the R ENG INSTR bus.
Each GEA interfaces to the following sensors for its onside engine:
• Oil Pressure Sensor
• Oil Temperature Sensor
• Fuel Flow Sensor (via onside Signal Conditioner)
• Turbine Speed Sensor (via onside Signal Conditioner)
• Propeller Speed Sensor(via onside Signal Conditioner)
• Torque Sensor
• Interstage Turbine Temperature (ITT) Sensor
Figure 2-7, GEA unit