TM 1-1510-262-10
Table 3-2.
Digital Flight Control System Limits -- Continued
CONTROL OR
MODE
SENSOR
PARAMETER
VALUE
Glideslope Receiver, Air
Glideslope Capture
Function of beam and beam rate.
Data Computers and
Beam Capture
10
Radio Altimeter
Pitch Command Limit
Vertical Acceleration
Glideslope Damping
f (TAS)
Pitch Rate Limit
Starts at 1200 ft radio altitude, gain
Gain Programming
reduction 1 to 0.08
GA
Control switch on Left
Fixed pitch up, Command 8 pitch up
Power Lever or CP s
wings level
Control wheel
Pitch Sync
TCS switch on wheel
Pitch Attitude Command
20 maximum
ALT Hold
ALT Hold Engage
Air Data Computers
0 to 41,000 ft
Range
30 ft
ALT Hold Engage
20
Error
f (TAS)
Pitch Limit
Pitch Rate Limit
VS Hold
Air Data Computers
VERT Speed Engage
0 to 6,000 ft/min
Range
100 ft/min
VERT Speed Hold
20
Error
f (TAS)
Pitch Limit
Pitch Rate Limit
80 to 400 knots
IAS Hold
Air Data Computers
IAS Engage Range
5 knots
IAS Hold Error
20
Pitch Limit
f (TAS)
Pitch Rate Limit
ALT Preselect
Air Data Encoding
Preselect Capture
0 to 40,000 ft
Range
Altimeter and Altitude
Maximum
0.20 g
Preselect Controller
Gravitational force
20
During Capture
f (TAS)
Maneuver
Pitch Limit
Pitch Rate Limit
Rudder Boost
Rudder Force
Engine Sensors,
f (Engine torque differential)
Air Data Computers
f (IAS)
e. Yaw Damper. The yaw damper computer provides basic yaw damper functions with or without the autopilot.
When the autopilot is engaged, turn coordination is active. Yaw damper mode is active when either the YD or the
AP ENGAGE button on the autopilot controller is selected.
f. Rudder Boost. The yaw damper computer also provides rudder assist (boost) in the event of an engine fail-
ure. The amount of assist provided is dependent upon airspeed and engine power differential. The boost function
is armed when the rudder boost switch located on the pedestal extension is set to the RUDDER BOOST position.
g. Autopilot Controller (PC-400). The autopilot controller (Fig. 3-8), provides a means of engaging/disengag-
ing the autopilot and yaw damper as well as manually controlling the autopilot through the turn knob and pitch wheel.
Whenever the autopilot is engaged, it will ly basic roll and pitch hold, the selected lateral, and/or vertical light di-
rector modes.
3-16
