Garmin GI 275 Installation Manual page 254

Flight Director Gain Adjustment Procedure
The following adjustment is required for all KFC 225 installations displaying the flight director on the
GI 275.
1. Verify that the attitude input to the autopilot is level (i.e., zero pitch/roll).
a. Using the GI 275, verify that the output test values are 0° UP, 0° RT, and Attitude Valid on the
Gyro Output Test page (Calibration/Test → Autopilot → Gyro Output Test).
b. Using an analog gyro, verify that the gyro is operational and level (may require an extender
harness and tilt table).
2. Navigate to the Flight Director Calibration page to view the FD Pitch value (Calibration/Test →
Autopilot → Flight Director).
3. Press and hold the GA button.
4. Adjust potentiometer on the front of the KC 225 until the FD Pitch value matches the pitch value
specified in the autopilot installation data for go-around mode (e.g., 6.00°) as closely as possible.
5. Verify the FD Gain adjustment.
a. Press CWS. The FD Pitch value should be approximately zero.
b. Make five discrete clicks using the UP keys on the KC 225. The FD Pitch value should be
approximately +2.5° Up.
Altimeter Calibration Procedure
The following calibration is required if the GI 275 is used to provide analog baro-correction to the
autopilot:
1. Power on the GI 275 in Normal mode and set Barometric setting to 29.92 IN.
2. Perform the Altimeter Calibration Procedure as specified in Honeywell KFC 225 Flight Control
System Installation Manual, with the following difference:
a. When instructed to set the barometric setting to 29.92 inches, set the Barometric setting on the
GI 275 to 29.92 IN.
5.7.2.5 Honeywell (Bendix/King) KFC 250 Autopilot
Gyro Alignment Procedure
1. Power on the GI 275 in Configuration mode.
2. Navigate to the Gyro Output Test page (Calibration/Test → Autopilot → Gyro Output Test).
3. Set the Attitude Valid selection to valid (i.e., touch the Attitude Valid button so that it is
illuminated green).
4. Perform the alignment procedure as specified in the King installation manual, with the following
difference:
a. It is not necessary to remove the AHRS from the aircraft. To set pitch and roll as directed in
the procedure, use the Gyro Output Test page to set the pitch angle and roll angle to the
desired values.
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Rev. 11
GI 275 Part 23 AML STC Installation Manual
Page 5-76