钻石40飞机维护手册 DA 40 SERIES AMM 2(20)

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) UP/DN (vertical trim) buttons. The action of these buttons is dependent upon the vertical mode present when pressed. If VS mode is active, the initial button stroke will bring up the commanded vertical speed in the display. Subsequent immediate button strokes will increment the vertical commanded either up or down at the rate of 100 ft/min per button press, or at the rate of approximately 300 ft/min per second if pressed continuously. If the ALT mode is active, incremental button strokes will move the altitude hold reference altitude either up or down by 20 feet per press, or if held continuously will command the airplane up or down at the rate of 500 ft/min, synchronizing the altitude hold reference to the actual airplane altitude upon button release. (Note that the altitude hold reference is not displayed. The display will continue to show the altitude alerter reference.)
ARM ) (altitude arm) button (only if altitude preselect option is installed). It toggles altitude arming on or off. When ALT ARM is annunciated, the autopilot will capture the altitude alerter displayed altitude (provided the airplane is climbing or descending in VS to the displayed altitude). ALT hold arming when the autopilot is engaged is automatic upon altitude alerter altitude selection via the rotary knobs. Note that the alerter functions are independent of the arming process, thus providing full time alerting, even when the autopilot is disengaged.
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) BARO (baro set) button (only if Altitude Preselect Option is installed). When pushed and released, it will change the display from the altitude alerter selected altitude to the baro setting display (either IN HG or HPA) for 3 seconds. If pushed and held for 2 seconds, it will change the baro setting display from IN HG to HPA or vice versa. Once the baro setting display is visible, the rotary knobs may be used to manually adjust the baro setting if the system configuration does not employ automatic correction.
The flight control computer is connected to these controls on the control sticks:
) AP DISC (autopilot disconnect) switch on pilot′s and co-pilot′s stick. When pressed, it will disengage the autopilot, and interrupt electric trim power.
) Manual electric trim switches on the pilot′s stick. When both switches are pressed in the same direction, they will activate pitch trim in the selected direction. If only one switch is moved, the trim system will not operate. If one switch fails or is moved and held for 3 seconds, the trim monitoring system will detect a switch failure resulting in a PT annunciation on the autopilot display and the disabling of the electric trim system. Autopilot power will have to be cycled to clear the fault. Use of manual electric trim during autopilot operation will disengage the autopilot.
) CWS (control wheel steering) mode button on the pilot′s stick. When pressed and held, it disengages the pitch, roll, and pitch trim clutches allowing the pilot to maneuver the airplane by hand. Pressing the CWS button will also sync the autopilot ALT or VS commands to the actual altitude or vertical speed present at the time the button is released.
The following controls on the HSI (refer to Section 34-28) are also used for autopilot operation:
) Omni bearing select knob. It selects the desired course to be tracked by the autopilot.
) Heading select knob. It positions the heading bug on the compass card.
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B. KCM 100 Configuration Module
The data which is specific to the DA 40 (for example: gain settings) is stored in the KCM 100 configuration module. It is located on the instrument panel floor, between the instrument panel and the firewall.
C. KS 271C Roll Servo
The roll servo is located behind the rear main bulkhead on the right side. It is mounted on a mounting plate which is made from sheet aluminum. Two aluminum clamps connect a bridle cable to the aileron push-rod.
　
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