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Page 4-102
LMM for the Kodiak 100
190-02102-00 Rev.4
The control processor contains the following logs:
3 – Pitch Servo
5 – Roll Servo
7 - Yaw
9 – Pitch Trim Servo
There are two main groupings of faults that can occur in the control processor. The first
grouping of faults can occur during the GSA unit pre-flight test (PFT). If there is a fault
during PFT, the unit will not be able to transition to normal mode and the only way to
clear this state is to cycle unit power.
The second grouping of faults can occur during normal mode. These faults generally
cause a disconnect of power to the GSA and report that a fault has occurred to the GIA.
The Notes column indicates any actions that can be taken to troubleshoot the problem in
the aircraft by the technician. Any faults that are not listed here indicate an internal
problem requiring replacement of the servo. If the items in the Notes column check out
OK, replace the servo.
Table 4-23. Normal Mode Faults
Monitor Fault
Notes
GIA DIS FAULT
Check the AP Disconnect power to the unit.
HOST DATA DIF
Check the AHRS wiring to the system.
HOST DATA INV
Check the AHRS wiring to the system.
SVO PWER INV
Check unit power and AP Disconnect power.
STRP CODE CHNG
Check the connector strap inputs to the unit.
MET STUCK SWTCH
Check the MET switch inputs into the system.
MET STATUS DIF
Check the MET switch inputs into the system.
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Summary of Contents for Cessna Caravan G1000
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