TM 1-1520-238-T-7
11–3
11–1.
EQUIPMENT CHARACTERISTICS, CAPABILITIES, AND FEATURES (cont)
11–1
(6) DASE.
The DASE system incorporates the stability augmentation system (SAS), the command
augmentation system (CAS), attitude hold, turn coordination, the hover augmentation system, heading hold, and
BUCS.
(7) SCS.
The SCS can be operated in automatic or manual mode. The automatic mode is normally used
and becomes functional when forward airspeed reaches 30 knots. Manual mode is engaged automatically, when
the automatic mode fails, and can only be engaged when airspeed is below 80 knots. The SCS is continuously
monitored by the fault detection/location system (FD/LS). The SCS is fail-safe, in that a failure of a stabilator
control unit (SCU) cannot cause an aircraft pitch rate in excess of 10 per second. The SCS receives various
airspeed information from the air data subsystem (ADSS).
11–2.
LOCATION AND DESCRIPTION OF MAJOR COMPONENTS
11–2
a. Force Trim System.
The force trim system (fig. 11–1) consists of three feel spring and magnetic brake
assemblies which are attached to the longitudinal (pitch), lateral (roll), and directional (yaw) flight controls under
the pilot’s station. When force trim is selected a trim brake relay, located in the electrical power distribution box,
engages the magnetic brake assemblies which lock and establish a trim position (reference). The spring
assemblies override the magnetic brake assemblies allowing flight control inputs to deviate from the reference
force trim setting.
