22-13-00
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FLIGHT CONTROL COMPUTER
SYSTEM OFF OR ENTER ANOTHER MODE HDG SEL MODE REQAutopilot/Flight Director System Roll and Yaw Modes LogicFigure 10 (Sheet 1)
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MAINTENANCE MANUAL

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 GUN 001-050, 052-999 ú 22-13-00
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FLIGHT CONTROL COMPUTER SYSTEM OFF OR ENTER ANOTHER MODE
Autopilot/Flight Director System Roll and Yaw Modes LogicFigure 10 (Sheet 2)
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MAINTENANCE MANUAL

IN CMD WITH HEADING HOLD ARMED UNTIL WINGS LEVEL 2.SYNC UNTIL HDG HOLD,
HDG SEL, OR G/ASYNC UNTIL MODE ENGA
Autopilot/Flight Director System Roll and Yaw Control Signal Flow Schematic
Figure 11 (Sheet 1)

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 22-13-00
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(HDG/TRK HOLD OR G/A)
ON GROUND WITH MULTICHANNEL ENGA
1.

 FOR 2 SEC IN CWS WITH NO WHEEL FORCE AND BANK BELOW 3` OR 1` THRESHOLD
2.

3 SYNC UNTIL HDG HOLD,HDG SEL OR G/A
IN CMD WITH HEADING HOLD ARMED UNTIL WINGS LEVEL 3.
Autopilot/Flight Director System Roll and Yaw Control Signal Flow Schematic
Figure 11 (Sheet 2)

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MAINTENANCE MANUAL

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 GUN 001-050, 052-999 ú 22-13-00
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D00420
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MAINTENANCE MANUAL

 (7) Output Signal Synchronization
 (a)
Aileron Servo Command

 1)  Aileron surface position from the ALCS is applied to the Aileron Trim Integrator (ATI). A synchronization loop established when the A/P is not engaged, synchronizes the roll servo command to |65 degrees of wheel rotation. With the A/P engaged, the limiter is set at |18 degrees in single channel operation and |40 degrees in multi-channel operation. Any servo command in response to aileron position change is supplied to the EHSV. Since the ALCS is hydraulically armed, the servo actuator moves in response to the EHSV. The actuator piston LVDT output nulls the command. The EHSV centers but the servo actuator piston is off center and the detent pistons are retracted. When APENG occurs, detents clamp the crank at the off-center position.

 (b)
Flight Director Roll Command

 1)  Flight Director roll commands are computed continuously whether the A/P is engaged or not and whether the F/D is on or off.
 2)  The computed F/D roll command is transmitted to the EFIS. The F/D ON discrete is not present when F/D switches are OFF, therefore, EFIS displays are inhibited.
 (c)
Rudder Servo Command

 1)  Rudder surface position from the ARGS is applied to the rudder command processor. A synchronization loop is established when directional yaw steering (DYS) is not engaged. This synchronizes the rudder commands up to |25 degrees. With DYS engaged, servo commands are applied to the EHSV. Servo actuator operation and LVDT output is similar to that described above for the ALCS. Output to the Runway Alignment Command Signal Processor (RACSP) is held at zero by synchronizing loop. When DYS is engaged, the RACSP receives only the rudder servo command.

 (d)
Computed Commands

 1)  The roll F/D command for aileron and the rudder command are individually synchronized in appropriate sections of the FCC. The source for F/D commands depends on the mode. Computed F/D commands are applied to the symbol generators and EADIs of the EFIS. During CMD ENG, a fixed bias is applied and the F/D command bars on the EADI are biased out of view.
　
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