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2.31.2 Collective Pitch Control Stick. The collective sticks change the pitch of the main rotor blades, causing an increase or decrease in lift on the entire main rotor disc. A friction control on the pilot’s lever can be turned to adjust the amount of friction and prevent the collective stick from creeping. The copilot’s stick telescopes by twisting the grip and pushing the stick aft to improve access to his seat. Each collective stick has a grip (Figure 2-11) with switches and controls for various helicopter systems. These systems are: landing light control, marked LDG LT PUSH ON/OFF EXT and RETR; searchlight controls, marked SRCH LT ON/OFF BRT, DIM, EXT, L, R, and RETR; servo shut-off control switch, marked SVO OFF 1ST STG and 2ND STG; a cargo hook emergency release switch, marked HOOK EMER REL, a radio select switch marked RAD SEL UP-DN and HUD control switch, marked BRT-DIM-MODE-DCLT. All switches are within easy reach of the left thumb. For a complete description of switches and con-trols, refer to major system description.
2.31.3 Mixing Unit. A mechanical mixing unit provides control mixing functions which minimizes inherent control coupling. The four types of mechanical mixing and their functions are:
a.
Collective to Pitch -Compensates for the effects of changes in rotor downwash on the stabilator caused by col-lective pitch changes. The mixing unit provides forward input to the main rotor as collective is increased and aft input as collective is decreased.

b.
Collective to Yaw -Compensates for changes in torque effect caused by changes in collective position. The mixing unit increases tail rotor pitch as collective is increased and decreases tail rotor pitch as collective is decreased.

c.
Collective to Roll -Compensates for the rolling moments and translating tendency caused by changes in tail rotor thrust. The mixing unit provides left lateral input to the main rotor system as collective is increased and right lateral input as collective is decreased.

d.
Yaw to Pitch -Compensates for changes in the ver-tical thrust component of the canted tail rotor as tail rotor pitch is changed. The mixing unit provides aft input to the main rotor system as tail rotor pitch is increased and for-ward input as tail rotor pitch is decreased.

2.31.4 Collective/Airspeed to Yaw (Electronic Cou-pling). This mixing is in addition to collective to yaw mechanical mixing. It helps compensate for the torque effect caused by changes in collective position. It has the ability to decrease tail rotor pitch as airspeed increases and the tail rotor and cambered .n become more efficient. As airspeed decreases, the opposite occurs. The SAS/FPS computer commands the yaw trim actuator to change tail rotor pitch as collective position changes. The amount of tail rotor pitch change is proportional to airspeed. Maxi-mum mixing occurs from 0 to 40 knots. As airspeed
SEARCHLIGHT SWITCH

SERVO SHUTOFF
AB0699_1
SA

increases above 40 knots, the amount of mixing decreases until 100 knots, after which no mixing occurs.
2.31.5 Tail Rotor Control. The tail rotor control system determines helicopter heading by controlling pitch of the tail rotor blades. Inputs by the pilot or copilot to the control pedals are transmitted through a series of control rods, bellcranks, a mixing unit, control cables and servos to the pitch change beam that changes blade pitch angle. Hydrau-lic power to the tail rotor servo is supplied from No. 1 or the backup hydraulic systems.
2.31.6 Tail Rotor Pedals. The pedals contain switches that, when pressed, disengage the heading hold feature of FPS below 60 KIAS. Adjustment for pilot leg length is done by pulling a T-handle, on each side of the instrument panel, marked PED ADJ. The pedals are spring-loaded and will move toward the operator when unlocked. Applying pressure to both pedals simultaneously will move the ped-als for desired leg position. The handle is then released to lock the pedal adjusted position.
　
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