Garmin G1000 Line Maintenance Manual page 281

Uncontrolled if Printed
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6. Position the control surface in the neutral position (full aft position if the PITCH
SERVO is selected). Press the DIS CLCH softkey
7. Press the TEST SVO softkey. Highlight YES and press the ENT key.
NOTE
Once the test starts the servo will begin to move the aircraft controls. If, for
any reason, the test must be stopped, firmly grasp the aircraft control being
moved and press the red AP DISC switch on the aircraft control stick..
8. The test begins, and the selected servo drives the control surface to either the
NOSE UP stop (Pitch & Pitch Trim), or the LEFT stop (Roll and Yaw). If the
PITCH SERVO is selected, firmly hold the control yoke in the full aft position until
the NOSE UP portion of the test is completed
9. Upon reaching the control stop, the test initializes and begins a 50 second data
collection period, where the servo is commanded to drive at ~2.5 rpm while the
servo load cell measures clutch torque.
10. Monitor the CURRENT field and verify the current displayed is greater than zero.
11. After the data is collected and processed, the test displays the results of the first
direction on the PFD. The servo immediately begins to drive in the opposite
direction toward the opposite control stop. If the PITCH SERVO is selected, let
the control yoke move to the full forward position
12. Upon reaching the stop, the test repeats the data collection process and displays
the results on the PFD.
13. Firmly grasp the aircraft control under test and press the red AP DISC button to
relieve any control tension. Press the ENT key to acknowledge the COMPLETE
prompt on the PFD.
14. Record the clutch measurement values in the appropriate aircraft maintenance
records.
15. Repeat this procedure for each servo axis.
16. Verify the minimum and maximum torque values measured are within the
Minimum and Maximum torque values allowed, for the given axis, listed below.
The minimum and maximum allowable torque values are based on nominal slip
clutch settings for part number 011-02147-11 (roll and pitch trim) of 61 in-lbs. and
011-02147-13 (pitch and yaw) of 103 in-lbs. These values should be verified for
equipment installed on aircraft.
NOTE
If the measured values exceed these limits, the servo must be replaced.
GSM 86 settings are set at the factory and cannot be adjusted in the field.
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LMM for the Kodiak 100
190-02102-00 Rev.4
Page 8-5