FWD
R
L
AFT
STICK TRIM
GO AROUND CARGO HOOK
ENABLE SWITCH RELEASE SWITCH
ICS RADIO
CONTROL
TRIM I.C.S.
RELEASE
SWITCH
PANEL LIGHTS KILL SWITCH RADIO
PNL LTS
CYCLIC MOUNTED STABILATOR SLEW.UP SWITCH CYCLIC STICK GRIP (TYPICAL) SA AA0365_2
Figure 2-11. Collective and Cyclic Grips (Sheet 2 of 2)
Should one stage become inoperative due to pressure loss, a bypass valve within the depressurized stage will open, pre-venting a hydraulic lock. Tail rotor control loads are reacted by a two-stage tail rotor servo mounted on the tail gear box. With the TAIL SERVO switch at NORMAL, the .rst stage of this servo is powered by the No. 1 hydraulic sys-tem; the second stage is powered by the backup system when the switch is at BACKUP. Should the .rst stage become inoperative, the backup pump will come on and power the second stage. All aerodynamic loads are then reacted by the second stage. Electrical interlocks prevent both .ight control servos from being turned off simulta-neously. The servo switches marked SVO OFF, 1ST STG and 2ND STG are on the pilot and copilot collective stick grips (Figure 2-11). If the input pilot valve to the servo becomes jammed, bypass automatically occurs. Automatic bypass is indicated to the pilot by lighting of the associated PRI SERVO PRESS caution legend.
2.32.1 Flight Control Servo Switch. First and second stage primary servo systems are controlled by the servo switch, marked SVO OFF, on the pilot’s and copilot’s col-lective stick grips (Figure 2-11). The marked switch posi-
tions are 1ST STG and 2ND STG. The servo systems nor-mally operate with the switch in the unmarked center (on) position. To turn off the .rst stage primary servos, the SVO OFF switch is placed to 1ST STG. To turn off the second stage servo, the switch is placed to 2ND STG. The systems are interconnected electrically so that regardless of switch position, a system will not shut off unless there is at least 2350 psi in the remaining system. The servo shutoff valve operates on current from the No. 1 and No. 2 dc primary buses through circuit breakers marked NO. 1 and NO. 2 SERVO CONTR respectively.
2.32.2 Flight Control Servo Low-Pressure Caution Legends. The .rst, second, and tail rotor stage servo hydraulic low-pressure caution legends are marked #1 PRI SERVO PRESS, #2 PRI SERVO PRESS, and #1 TAIL RTR SERVO, and will go on if the pressure is below its respective switch setting, or if the servo pilot valve becomes jammed. The servo switches and warning legends operate on direct current from the No. 1 and No. 2 dc primary buses through circuit breakers, marked NO. 1 SERVO WARN and NO. 2 SERVO WARN, respectively.
2.32.3 Pilot-Assist Servos. Pilot assist servos are nor-mally powered by the No. 2 hydraulic system. If the No. 2 hydraulic pump fails, the pilot assist servos and pitch trim actuator are powered by the backup hydraulic pump. The following units are pilot-assist servos: collective, yaw, and pitch boost servos, which reduce control forces; and three (pitch, roll, yaw) SAS actuators which transfer the output of the SAS controllers into control actuations.
2.32.4 Boost Servo. There are three boost servos, col-lective, yaw, and pitch, installed between the cockpit con-trols and mixing unit, which reduce cockpit control forces. The collective and yaw boost servos are turned on and off by pressing the button marked BOOST on the AUTO FLT CONT panel (Figure 2-12). The pitch boost servo is turned on when SAS 1 or SAS 2 is ON. The boost shutoff valves receive power from the dc essential bus through a circuit breaker, marked SAS BOOST.
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