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Overview
The Command Stability Augmentation
System is comprised of the following line replaceable units,
1 Rudder pedal position transmitter
Between front rudder pedals.
2 CSAS Power Distribution Unit
Right hand forward avionic compartment.
3 CSAS Control Unit
Front Cockpit - left hand console.
4 Pitch Computer
Right hand rear avionic compartment.
5 Lateral Computer
Right hand rear avionic compartment.
6 Roll Position Transmitter
Zone 19. Roll crate.
7 Pitch Position Transmitter
Zone 19. Pitch crate.
8 Yaw Rate Gyro
Zone 22. Right hand under-carriage bay.
9 Roll Rate Gyro
Zone 21. Left hand under-carriage bay.
10 Pitch Rate Gyro
Zone 21. Left hand under-carriage bay.
CSAS Control Limits
|
AXIS
|
MD
|
DEL
|
MECH
|
PHYSICAL
LIMITS
|
|
PITCH
TAILERONS
|
+10° to -30°
|
+5° to –25°
|
+5° to -25°
|
+10° to -30°
|
|
ROLL
TAILERONS
|
+
10°
|
+
2.1° or
* +4.2°
|
+
5°
|
MAX
+
10°
|
|
ROLL
SPOILERS
|
50°
|
20° or
*40°
|
CLOSED
|
50°
|
|
YAW
RUDDER
|
+
30°
|
+
30°
|
LOCKED
|
+
30°
|
|
PITCH
TRIM DATUM
|
- 6.5°
|
- 4.5°
|
- 4.5°
|
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CSAS Schematic |
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