22-00-00
AMM
Intentionally left blank
22-00-00
Auto Flight
AMM
Section 22-10
Autopilot
1. General
This Section tells you about the autopilot system that can be installed in the DA 40.
2. Description
The KAP 140 autopilot system is a digital flight control system that provides roll, pitch, and pitch trim steering with optional altitude preselect. The system has the following components (refer to Fig. 1): ) KC 140 flight control computer (FCC). ) KCM 100 configuration module. ) Turn and bank indicator with autopilot pick-off. ) KCS 55A gyro compass system. Refer to Section 34-28 for details about the gyro compass system. ) KS 271C roll servo. ) KS 270C pitch servo. ) KS 272C pitch trim servo.
) KM 275 and KM 277 servo mounts. Heading input must be supplied for the KAP 140 autopilot by the KCS 55A gyro compass system. Refer to Section 34-28 for details about the gyro compass system.
When the altitude preselect/vertical speed system option is installed, the airplane is equipped with the
KEA 130A encoding altimeter.
The KAP 140 roll axis features includes wing leveler, heading select, and VOR/LOC intercept and
tracking. The KAP 140 can also be coupled to the GPS and the RNAV receivers. Roll rate information
is derived from the turn coordinator.
Pitch axis features include vertical speed, glideslope and altitude hold along with the optional altitude
preselect. Pitch information is derived from a pressure sensor and accelerometer. The KAP 140
Autopilot System operates independent of the airplanes′s attitude gyro (artificial horizon). Internal
monitors keep constant track of the KAP 140′s status and provide for automatic shutdown of the
autopilot or trim system in the event of a malfunction.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003
22-10-00
AIRCRAFT AMM
Figure 1: Autopilot System Schematic
22-10-00
Auto Flight
AMM
A. Bendix/King KAP 140 Flight Control Computer
Figure 2 shows the Bendix/King KAP 140 flight control computer. It is located in the avionics rack in the instrument panel, see Section 31-10.
The Bendix/King KAP 140 has the following annunciators on the front panel, above the AP button:
) 'P' (pitch axis) annunciator. It indicates failure of the pitch axis and will either disengage the autopilot or does not allow engagement of the pitch axis. The 'P' annunciator may illuminate with the autopilot disengaged. This condition can occur during maneuvering flight when g thresholds are exceeded. The autopilot monitor will not allow engagement during illumination.
) 'R' (roll axis) annunciator. It indicates failure of the roll axis and will disengage the autopilot or does not allow engagement.
The Bendix/King KAP 140 controls the following annunciator on the annunciator panel (also see Section 31-50):
) TRIM FAIL annunciator. It illuminates whenever the automated preflight self test detects a pitch trim fault or a continuous monitoring system detects a pitch trim fault in flight. (Located on the White Wire annunciator panel.) Refer to the EMERGENCY PROCEDURES for proper response to a pitch trim fault.
The Bendix/King KAP 140 has a display which shows the following:
) Pitch and roll mode displays. Displays the active pitch modes (VS, ALT, ARM, ALT, GS ARM, GS) and roll modes (ROL, HDG, NAV ARM, NAV, APR ARM, APR, REV ARM, REV). Also displayed will be a flashing AP annunciation (5 seconds) at each autopilot disconnect, accompanied by an aural alert (for 2 seconds).
) PT (pitch trim) annunciation. It indicates the direction of required pitch trim. With electric trim installed, the annunciation simply provides status to the autopilot request for auto trim. A solid indication represents the lowest demand level for trim, whereas a flashing annunciation implies a greater demand. A solid PT annunciation without an arrow head is an indication of a pitch trim fault. During MET operation, this annunciation can be caused by a stuck MET switch. If the stuck switch fault clears, trim operation will resume.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：钻石40飞机维护手册 DA 40 SERIES AMM 2(18)
