Engine Indicating System; Gea 24 - Garmin GI 275 Installation Manual

4.7 Engine Indicating System

The aircraft must retain all engine indications for engine and aircraft operations within the limits defined in
the Pilot's Operating Handbook or other approved manual.
Only the GI 275 EIS sensors specified in this section are approved for installation as part of the GI 275
STC. Installation of other sensors requires separate airworthiness approval from the cognizant authority.
The following sections contain information applicable to EIS sensor installation:
• List of compatible sensor interfaces – Appendix Section C.19
• Selection of aircraft specific sensors – Appendix Section C.19
• Sensor configuration – Section 5.6.2 and Appendix Section C.19
• Interconnect diagrams of sensor connections to the GEA 24/110 – Appendix B
NOTE
This STC does not approve any modifications to the engine firewall.
In addition to the data in this manual, the installation of each probe/sensor and wire must be accomplished
in accordance with the sensor manufacturer's instructions or as recommended by the engine manufacturer.
Wire routing and clamping must follow procedures defined in the aircraft maintenance manual or standard
practices manual. Practices defined in Chapter 11, Electrical Systems, of AC 43.13-1B Aircraft Inspection
and Repair are acceptable.
Sensors must be connected using hoses and fittings approved as part of the aircraft or engine type
certificated design or standard aircraft parts (AN/MS).
Sensors must not be mounted directly to the engine or engine baffle unless otherwise instructed in this
manual.
CAUTION
Check hose routing for sharp bends. Check sensors and fittings for leaks during engine
run-up; correct any leaks prior to flight.
4.7.1

GEA 24

The GEA 24 must be installed in the fuselage cabin environment where it is protected from accidental
damage by occupants and rapid thermal change. It can be mounted directly or indirectly (i.e., via a support
structure) on the aircraft structure. It can be mounted in any orientation, but vertical with the connectors
pointing down is preferred. The unit should be mounted so that the connectors and status LED is viewable
and where it can be inspected and serviced.
CAUTION
The GEA 24 cannot be mounted in the engine compartment or where it could be exposed
to moisture or fluids.
If provisioned by the aircraft structural repair manual or standard practices manual, the GEA 24 can be
mounted on the engine firewall (opposite surface of the powerplant), fuselage frames, or stringers. The
GEA 24 wiring must be routed through existing pass-through holes in the firewall or use existing bulkhead
connectors; otherwise, separate airworthiness approval is required for added holes in the engine firewall.
The GEA 24 must not be placed directly below fluid lines (e.g., fuel lines, oil or hydraulic lines). It also
must be installed as far away as practical from heat sources.
190-02246-10
Rev. 11
GI 275 Part 23 AML STC Installation Manual
Page 4-60