Servo Tests; Roll Servo Functional Check; Pitch Servo Functional Check; Yaw Damper Functional Check - AUTO GYRO Cavalon Maintenance Manual

6. If the aircraft is configured for miles per hour (mph) instead of knots (Kt), utilize mph as the
unit in any step that references Kt. Conversion of value is not required.

22-08-51 Servo Tests

If a servo has been removed and reinstalled (or replaced), perform the following steps.
1. Load software as shown 22-08-21 GMC 507 and GSA 28 Software Loading.
2. Power the GFC 500 in normal mode.
3. Complete Pre-Flight Test (PFT) as shown in 22-08-40 Pre-Flight Test (PFT).
4. Proceed to the sub-section below as appropriate for the servo that has been replaced.

22-08-52 Roll Servo Functional Check

1. Verify that the steps in 22-08-51 Servo Tests have been completed.
2. Center the heading bug on the aircraft heading.
3. Engage the autopilot by pressing the AP button on the GMC 507.
4. Verify that the roll control is restricted from free movement.
5. Press the HDG button to engage roll mode.
6. Rotate the heading bug to the left of the current aircraft heading.
7. Ensure that the command bars indicate a left roll and that the servo drives the flight controls
to the left.
8. Rotate the heading bug to the right of the current aircraft heading.
9. Ensure that the command bars indicate a right roll and that the servo drives the flight controls
to the right.
Firmly grasp the control wheel and press the AP DISC switch on the pilot's flight controls.
10.
11. Verify that the autopilot disconnects and the roll control moves freely.

22-08-53 Pitch Servo Functional Check

1. Verify that the steps in 22-08-51 Servo Tests have been completed.
2. Center the elevator controls approximately mid-travel.
3. Engage the autopilot by pressing the AP button on the GMC 507.
4. Verify that the pitch control is restricted from free movement.
5. Rotate the NOSE UP/DN thumbwheel on the GMC 507 UP three clicks.
6. Ensure that the flight director command bars indicate a pitch up and that the pitch servo
drives the controls in a nose up direction. NOTE: In some aircraft, some assistance may be
needed to drive the flight controls against any counterweight or springs.
7. Rotate the NOSE UP/DN thumbwheel on the GMC 507 DN three clicks.
8. Apply continuous forward pressure on the pitch control in a nose down direction.
9. Ensure that TRIM UP is displayed on the G5 or G3X PFD.
10. Apply continuous aft pressure to the flight controls in a nose up direction.
11. Ensure that TRIM DN is displayed on the G5 or G3X PFD.
12. Rotate the NOSE UP/DN thumbwheel on the GMC 507 DN three clicks.
13. Ensure that the flight director command bars indicate a pitch down and that the pitch servo
drives the controls in a nose down direction.
Firmly grasp the control wheel and press the AP DISC switch on the pilot's flight controls.
14.
15. Verify that the autopilot disconnects and the pitch control moves freely.

22-08-54 Yaw Damper Functional Check

1. Verify that the steps in Section 9.3.1 have been completed.
2. Engage the Yaw Damper by pressing the YD button the GMC 507.
3. Verify that resistance if felt in the rudder pedals.

22-08-60 GFC 500 Functional Checks

Perform the following test procedures when the GMC 507 is replaced.
AMM-CV-915iS/916iS-EN-
C-2023-12
Aircraft
Maintenance Manual
Part C – System Description Section
(Chapter 21 – 90)
AutoGyro
Cavalon 915 iS / 916 iS
Page 31 of 67