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2.37.5 Flight Control Servos. The four primary flight
control servos are tandem units that use hydraulic
pressure from both the primary and utility hydraulic
systems. The primary and utility sides of the servos are
independent of each other which provides redundancy
in the servos. If one hydraulic system fails, the remaining
system can drive the flight control servos. If both
systems fail simultaneously during flight, either crewmember
can use stored accumulator hydraulic pressure
to provide limited hydraulics for safe landing. Section
VI contains a detailed description of the emergency hydraulic
system. The primary side of each flight control
servo has two electrohydraulic solenoid valves. One responds
to DASE computer signals for stability augmentation.
w The second electrohydraulic solenoid valve responds
to DASE computer inputs for BUCS.
2.37.6 Digital Automatic Stabilization Equipment
(DASE). The DASE augments stability and enhances
maneuverability of the helicopter. DASE includes and/
or controls the following: stability and command augmentation
in pitch, roll, and yaw; attitude hold; heading
hold; hover augmentation; turn coordination; and
the BUCS. Major components include an ASE control
panel (fig 2-27), a DASE computer, eight linear variable
differential transducers (LVDT), two 26 vac transformers,
and four hydraulic servo actuators.
a. DASE Computer. The DASE computer receives
28 vdc from the No. 3 essential dc bus through the ASE
BUCS circuit breaker and a stepped down 26 vac reference
voltage from the No. 1 essential ac bus through the
ASE AC circuit breaker. Both circuit breakers are on
the pilot overhead circuit breaker panel. The DASE
computer automatically disengages a mistrack of more
than 35% and lights the ASE FAIL indicator on both
caution/warning panels; concurrently, the PITCH,
ROLL, and YAW switches on the ASE control panel
will drop to OFF The squat switch on the left main
landing gear disables the YAW CAS function during
ground taxi to prevent overcontrol of the helicopter.
The YAW channel circuitry in the DASE computer receives
sideslip data from the air data sensor which provides
turn coordination above 60 KTAS.
2-45
TM 1-1520-238-10
b. ASE Control Panel. The ASE control panel (fig
2-27) located in the pilot left console, has five singlethrow,
two-position magnetic switches labeled PITCH,
ROLL, YAW, and ATTD/HOVER HOLD and a BUCS
TEST (BUCS TST) switch.
q The BUCS TST switch on the ASE control panel
permits the pilot to perform a go no-go check of the
BUCS.
The NOE/APRCH switch is part of the stabilator system.
The ASE release button at the base of each cyclic
stick grip, when pressed, causes the three channel
switches and the ATTD/HOVER HOLD switch to drop
to OFF. The ASE control panel receives 28 vdc from the
No. 3 essential dc bus through the ASE DC circuit
breaker on the pilot overhead circuit breaker panel.
Figure 2-27. ASE Control Panel
c. Automatic Stabilization. The DASE has a stability
augmentation system (SAS) and a command augmentation
system (CAS). The SAS reduces pilot workload
by dampening airframe movement caused by
external forces such as in air turbulence and weapons
recoil. The CAS augments helicopter response by mechanical
control inputs and commands to the longitudinal
(pitch), lateral (roll), and directional (yaw) flight
control servoactuators. CAS signals are generated by
movement of crew station flight controls which are sent
to the DASE computer. The DASE computer sums the
SAS/CAS information with inputs from the heading
and attitude reference set (HARS) and the air data
sensor system (ADSS). The DASE computer provides
positioning commands to a two-stage electrohydraulic
SAS servo valve on the primary side of the longitudinal,
lateral, and directional flight control
servoactuators. The position of the SAS servo valve determines
the amount and direction of movement of the
SAS actuators. The position of each of the SAS actuators
is transmitted to the DASE computer by the
LVDTs. The motion of each SAS actuator is summed
with the mechanical input to each flight control servo,
but the SAS actuator authority is limited to 10% bidirectional
motion in all axes except the longitudinal
where the authority is 10% aft and 20% forward. The
DASE is engaged through the pilot ASE control panel.
d. Attitude/Hover Hold. The hover augmentation
system (HAS) or HOVER HOLD mode of the DASE
uses SAS actuators to maintain position and damp external
disturbances to the helicopter. HAS is set by engaging
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