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(1)

DOUGLAS AIRCRAFT CO., INC.

002-8 SIXTY SERIES

MAINTENANCE MARUAL

Automatic Pilot Indicator

Autopilot Release Switches

Accelerometers (six required)

Servo Drives and Brackets (two required)

Жан Axis Electrohydrautic Transfer Valve (part of rudder hydraulic power package)

Roll Channel Computer

Yaw Channel Computer

Pitch Channel Computer

Air Data Computer

vartoue modes of operation, and to initiate maneuvering commands,

Provides visual indication of aileron and elevator servo drive trim conditions and output of yaw actuator position transducer, Lights indicate autopilot off, glide path amed, auto trim off,

Provide disengagement of the rol) and pitch axes of the autopilot.

Translate acceleration in уам, roll, and pitch axes into electrical signals for damping short-period attitude changes,

Initiate movement of the ailerons and elevator in response to amplified signals from the roll and pitch channels.

Provides the means for yaw channel input to the mein control valve in the rudder hydraclic power package.

Provides roll axis interlock; computes and shapes error and command signals to drive the aileron servo drive.

Provides automatic stability augmentation and tum coordination in геsponse to command signals fron the autopilot sensing and control devices,

Provides pitch axis interlock; come putes and shapes error and comand signals to drive the elevator servo drive.

Provides signals for autopilot vertical speed, altitude hold, Mach Q. /р data, and airspeed (Q) switching of autopilot command parameters,

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DOUGLAS AIRCRAFT CO., INC.

OG-8 SIXTY SERIES =“

MAINTENANCE MANUAL

2. Operation A. Yow Axis

(2) Symehronization

(в) With yaw axis circuit breakers closed and powor applied, the autopilot provides self-synchronization within the yaw channel computer, The synchronization provides a null output from the torquer amplifier to the electrohydraulic transfer valve. With pitch and roll ахос circuit breakers also closed, synchronization to airplane magnetic heading, ав sensed by the directional gyro, is provided within the yaw channel computer by a heading synchronizer. The heading reference output signal is routed to the roll channel computer,

(2) Yaw Damper

(a) The yaw damper mode 16 engaged when yaw axis ac and de circuit breakers are closed and the servos engage lever on the automatic pilot controller is moved to yaw damper position. The servos engage lever is held at the yaw damper position if all yaw axis engage path ч interlock requirements are met. The yaw channel computer provides rudder command signals to dampen the airplane dutch roll characteristics during manually ала automatically controlled flight. Because of the rudder hydraulic and linkage tie-ins with the manual controls, yaw damper control actions are not reflected at the rudder pedals. Further, the pilot can maneuver the airplane in a norma) manner through the rudder pedals with no opposing force or action from the yaw damper.

=

(b) With pitch and roll axes circuit breakers closed, and the autopilot

mode engaged, the yaw channel computer also provides rudder command signals to assist turn maneuvers,

(3) Autopilot

(а) The autopilot mode is engaged when yaw axis, pitch and roll axes, and air data circuit breakers are closed and the servos engage lever is set at autopilot, This continues yaw damper operation and also engages the rcll and pitch axes. The yaw, roll, and pitch axes are series interlocked for autopilot control, When an interlock interruption occurs іп any axis, the autopilot mode is automatically disengaged. If the pitch or roll exis is malfunctioning, the servos engage lever drops to yaw demper position end the autopilot off light comes on ав an indication to the pilot, The light remains on until one of the autopilot release buttons is pressed. ғ

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(b) During the approach phase of ILS operation, the уан channel computer receives а roll command to rudder signal that compensates for longterm airplane heading asymetries such as loss of an engine. In

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