Engine Indication System (Eis) - Garmin GI 275 Installation Manual

3.2.2

Engine Indication System (EIS)

Installation of the EIS must maintain compliance with the minimum number of gauges required by
14 CFR 91.205 for the type of flight allowed by the aircraft's Type Certificate. The following must be
considered for an EIS installation:
CAUTION
Engine damage may occur if length of oil temperature probe is incorrect. Refer to Section 4.6.3.
1. Only install EIS in aircraft that comply with all limitations in Section 2.1.3.
2. Engine RPM, Oil Temperature, Oil Pressure, EGT, CHT, and Manifold Pressure (if installed) must
be displayed on the EIS.
3. Optional EIS gauges listed in Table 3-12 that are not currently installed in the aircraft may be
added as approved in this STC.
4. No indication/parameter on the EIS display(s) can be duplicated by any other installed indicator
that is not connected to the GEA.
5. Ensure engine sensors can be installed and the corresponding gauges can be displayed. Refer to
Appendix E, Table 3-11, and Table 3-12 for gauge layout information. Depending on the number
of gauges, a second EIS display may be required (only permitted in single-engine aircraft). Refer
to Section 2.1.3.
6. Some turbocharged aircraft require a differential pressure sensor for fuel pressure. This STC
provides electrical interface for select differential pressure sensors (refer to Appendix Section
C.12); however, installation approval is not provided and must be obtained separately
7. Do not replace an existing gauge if the GI 275 will not provide the functions and markings
required by the POH/AFM, TCDS, or other aircraft model-specific data. Refer to Section 5.7.4.2
for available EIS gauge markings. If the EIS gauges cannot be configured as noted in the POH/
AFM, the installation does not qualify for EIS unless alternate airworthiness approval is obtained.
8. Annunciator lights, including alternator/generator annunciators operated by a sensor or switch
independent of the existing gauge, must remain operative and independent from the GI 275 EIS. If
an annunciator is operated by a gauge that might be replaced by the GI 275 EIS, the associated
annunciator can be deactivated only if the GI 275 Caution/Warning alert activates for the same
condition as the original annunciator. The GI 275 Caution/Warning alert is provided on the display
or an independent annunciator. However, if the new GI 275 EIS gauge does not support a Caution/
Warning alert for the same condition, the existing gauge and annunciator must remain installed.
9. If an annunciator is replaced by the GI 275 EIS display, deactivate the existing annunciator so it
does not illuminate and then install a placard over the deactivated lens or as close as practical
within view of the pilot that states: "X ANNUN DISABLD", with "X" being the deactivated
annunciator(s). Modification of the existing annunciator panel is outside the scope of this STC.
10. All placards that were associated with any/all gauges being replaced (non-limitation data) must
remain in the proximity of the EIS display.
11. Reused sensors must function through the sensor's entire range. For example, fuel tank floats may
have worn resistive elements that will result in performance issues with the gauge display.
12. If the aircraft POH or AFM has a fuel flow limit (i.e., red line), the installer must verify fuel flow
accuracy ±10% of the full scale range and adjust the K-Factor if necessary. Obtain the correct fuel
flow value using the engine or aircraft manufacturer manuals. If that data is not available, perform
a pre-installation static RPM ground check and document the pre-installation fuel flow using the
existing fuel flow indicator. Refer to Section 6.8.2 for post-installation K-Factor adjustment.
13. A single display that is a standalone EIS allows for the GPS connection to be optional. Standalone
EIS displays that do not have a GPS source connected will display dashes (---) for Fuel Endurance.
190-02246-14
Rev. 11
GI 275 STC EIS & MFD Installation Manual
Page 3-8