Table 3-13 Gi 275 Hsi/Standby Adi Restrictions; Engine Indication System (Eis) - Garmin GI 275 Installation Manual

System
GI 275
Notes:
[1] Refer to Section 1 for aircraft class designations.
[2] Refer to Section 5.3.4 for Instrument Type configuration instructions.
The markings on the standby airspeed indicator must match the TCDS, POH/AFM, or an applicable STC
AFMS for the specific aircraft. Verify that the existing airspeed indicator is correctly marked per the
applicable documents. The units on the standby altimeter (Hg or millibars) must match those on the current
altimeter in the aircraft.
3.2.3

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 the length of the oil temperature probe is incorrect. Refer to
Section 4.7.4.
1. Only install EIS in aircraft that comply with all limitations in Section 2.1.5.
2. Engine RPM, Oil Temperature, Oil Pressure, EGT, CHT, and Manifold Pressure (if installed) must
be displayed on the EIS display.
3. Optional EIS gauges listed in Table 3-15 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 F, Table 3-14, and Table 3-15 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 2.1.5.
6. 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 5.6.4.2
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.
7. 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. The GI 275 Caution/Warning alert is provided on the display or an
independent annunciator(s). 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.
8. 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.
190-02246-10
Rev. 11

Table 3-13 GI 275 HSI/Standby ADI Restrictions

Aircraft Class Restriction [1]
C I & II
LASS
Instrument Type [2]
HSI/S ADI
TANDBY
GI 275 Part 23 AML STC Installation Manual
Display Backup Switch
Required
Y
ES
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