Standby Indicator; Eis - Garmin GI 275 Installation Manual

2.1.4

Standby Indicator

The standby indicator must be installed within ±35° from the centerline of the pilot's primary field-of-
view. Refer to AC 23.1311-1C for additional guidance.
Refer to Section 2.1.8 for limitations regarding autopilot interface with GI 275 standby attitude indicators.
If the original airspeed indicator is part of an aural airspeed warning system, it may have to be retained to
continue to generate warnings. It can only be removed when it is possible to configure GI 275 airspeed
discrete outputs to trigger aural airspeed warnings when paired with external devices. The airspeed
warning system must continue to operate after the installation of the GI 275 system.
If the original airspeed indicator had variable operating limits that change based on aircraft altitude (e.g.,
barber pole type airspeed indicators), the original pneumatic airspeed indicator, or an electronic standby
capable of replicating the variable limit, must be used.
A GI 275 configured as a standby indicator must have a backup battery installed and maintained per
GI 275 Part 23 AML STC Maintenance Manual (P/N 190-02246-11) unless the standby GI 275 unit is
powered by an electrical source that is independent from the aircraft's primary electrical power system. A
display backup switch may be required. Refer to Section 3.2.2 for more information and requirements for
configuring a GI 275 as a standby to various systems.
2.1.5

EIS

The existing engine gauges can be replaced by an EIS display only if the functionality, markings, and
operational limits of the original gauges are capable of being replicated on the EIS display. The original
gauge must not be removed if any operating parameter, marking, or annunciation required by aircraft type
design, engine type design, or aircraft POH/AFM (or similar) cannot be replicated on the display or an
appropriate placard cannot be installed.
GI 275 EIS is limited to one EIS display for single-engine aircraft and one EIS display per engine for
twin-engine aircraft. In twin-engine aircraft with two GI 275 EIS displays and GI 275 MFD, the Fuel page
is the only EIS page approved to be displayed on the MFD. All other EIS pages must be disabled on the
MFD.
EIS is only approved for air-cooled 4- and 6-cylinder reciprocating engine equipped aircraft. Select aircraft
models on the AML have EIS limitations. Refer to notes in Table D-1.
All gauges with red and/or yellow markings, if intended to be replaced by a GI 275 EIS display, must be
identically configured on the Main EIS page. In some cases, one GI 275 will not have enough available
spaces for gauges on the Main EIS page. Any of the following cases will require the retention of the
original gauge(s):
• Three or more of the following gauges have red or yellow marks: Fuel Flow, Fuel Pressure, CDT,
IAT, Carb Temp, and CDT/IAT Diff
• Two of the following gauges have red or yellow marks: Fuel Flow, Fuel Pressure, CDT, IAT, Carb
Temp, and CDT/IAT Diff, and one of the following is true:
◦ Dual Aux Fuel Tanks are configured and one or more electrical gauges have a red or yellow
marking
◦ A Single Aux Fuel Tank is configured and two or more electrical gauges have a red or
yellow marking
• More than two electrical gauges have a red or yellow marking
190-02246-10
Rev. 11
GI 275 Part 23 AML STC Installation Manual
Page 2-3