CHAPTER 22
AUTOPILOT
22-00 Description
The optional, factory-installed autopilot system consists of two electric servo assemblies, a
flight control computer, a control panel, and control buttons on the pilot’s cyclic grip.
The autopilot system also utilizes the Attitude Heading Reference System (AHRS; refer to §
97-13).
Two electric servo assemblies attach via push-pull tubes to the bottom of the cyclic stick.
One servo controls pitch and is installed in the control tunnel forward of the cyclic stick.
The other servo controls roll and is installed under the pilot’s seat. Electromagnetic clutches
engage or disengage servo inputs from the cyclic control system when selected by the pilot.
The flight control computer is located on a forward panel under the pilot's seat. The control
panel is located below the GPS in the instrument console.
The primary autopilot mode is Stability Augmentation System (SAS) mode. In SAS mode
the autopilot senses aircraft attitude from the flight control computer and the AHRS. The
computer controls servo inputs to the cyclic to maintain attitude.
Additional modes, which may be used simultaneously when in SAS mode, are described
in the Normal Procedures section of the R66 Pilot's Operating Handbook (POH) Autopilot
Supplement.
The control panel has a row of buttons to control autopilot modes and annunciators to
indicate mode status. A dark annunciator indicates that a mode is off, a white annunciator
indicates that a mode is armed or on standby, and a green annunciator indicates that a mode
is active. The annunciators flash alternating white and green during start up.
The cyclic grip-mounted buttons are the TRIM and AP OFF buttons. The TRIM button is
used to reset the trim attitude. The autopilot tries to maintain the attitude at which the
button is released. In addition, holding the TRIM button for more than 1.25 seconds engages
the system from standby mode. The AP OFF button allows disengagement with hands on
controls.
Safety monitors automatically disengage individual modes or the entire system if a
malfunction is detected. Audio warnings consisting of beeps in the headset accompany the
safety monitors and are described in the Normal Procedures section of the POH Autopilot
Supplement.
The autopilot is protected by a dedicated circuit breaker on the avionics bus (autopilot is not
powered with the avionics master switch off).
A. Schematic
Refer to MM Figure 98-8 for autopilot installation electrical schematic.
MAY 2015 Chapter 22 Autopilot Page 22.1
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