190-02246-10 GI 275 Part 23 AML STC Installation Manual
Rev. 11 Page 2-2
2.1 Installation Limitations
2.1.1 System
Only the equipment or aircraft systems with interface(s) approved by this STC can be connected to the
GI 275. Installation of equipment that is not on the STC Equipment List but is interfaced to a GI 275
requires separate airworthiness approval.
Configuration and number of GI 275 displays installed under this STC is limited to a maximum of:
• Six displays total
• Two EIS displays
The GI 275 system is limited to a maximum of three ADAHRS or AHRS/ADC sensors installed under this
STC. If multiple ADC/AHRS sensors are interfaced to a single GI 275, the internal sensor must be
configured as the default sensor (refer to Section 5.5.4).
CAUTION
The total weight of new equipment installed in the instrument panel must not exceed the total
weight of equipment removed from the panel, unless the total weight of all the equipment installed
in the instrument panel is within the weight limits established by the aircraft manufacturer.
The aircraft’s magnetic compass must be retained for all GI 275 installations.
2.1.2 General Installation
The GI 275 is designed to replace existing 3â…›-inch gauges. Therefore, minimum modification of the panel
will be necessary.
For GI 275 system components that are mounted outside the pressure vessel of pressurized aircraft, wires
that penetrate the pressure vessel must use aircraft type design provisions such as spare pins in existing
bulkhead connectors or existing cutouts in the aircraft pressure bulkheads. Substantiation for additional
holes or cutouts in the aircraft pressure vessel are beyond the scope of the GI 275 AML STC and require
separate airworthiness approval.
2.1.3 Primary Attitude Direction Indicator (ADI)
The GI 275 must be configured such that its airspeed tape conveys all operating limitations that were
previously conveyed to the pilot by the approved type design airspeed indicator and limitations published
in the aircraft POH/AFM.
The Primary ADI must be installed in the primary field-of-view of the pilot (±15° from centerline). Refer
to Section 4.4 for additional guidance.
The Primary ADI requires one of the following combinations of standby information:
• Standby display of attitude, altitude, and airspeed
• Standby display of altitude, airspeed, stabilized heading, and standard turn-rate coordination
(existing instruments may be retained)
The pitot-static system must be connected to the Primary ADI. This includes installations with the ADI as
a basic, 3-in-1, or 4-in-1 display. A GPS source must be interfaced to the Primary ADI. Approved GPS
sources are listed in Appendix Section C.4.
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