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° |
 | CSAS Schematic |
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