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LEFT RIGHT AUXILIARY
SYSTEM SYSTEM SYSTEM
NORMAL
UPPER LEVEL 85% 85% 85%
PERCENTAGES
NORMAL
LOWER LEVEL 30% 40% 20%
PERCENTAGES
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2
13-01-04
LEGEND
SUPPLY PRESSURE (P)SUCTION PRESSURE (S)RETURN PRESSURE (R)CASE DRAIN (C)ECOLOGY
LEGEND
SUPPLY PRESSURE (P)SUCTION PRESSURE (S)RETURN PRESSURE (R)CASE DRAIN (C)
AUXILIARY HYDRAULIC SYSTEM
DESCRIPTION
The purpose of the auxiliary hydraulic system is to provide hydraulic pressure to the lower rudder PCU as a result of the right hydraulic system failure. The auxiliary hydraulic system includes a DCMP, a reservoir, and an accumulator, all located aft of the engine rotor burst zone. The right hydraulic system normally powers the lower rudder PCU. During a loss of right system pressure, a hydraulic switching valve allows the auxiliary system to provide pressure to the lower rudder PCU. The left or right hydraulic system may be activated without the system already being pressurized. However, the auxiliary system has an intensifier pressurized by the right hydraulic system. During the preflight check, select R PUMP ON before selecting AUX PUMP to AUTO to prevent cavitation.
The auxiliary hydraulic system pressure is generated by a constant displacement DCMP. The pump is controlled by a two position AUX PUMP switch. The OFF position disables the pump. In the AUTO position, a pressure switch allows the pump to activate as needed.
COMPONENTS AND OPERATION AUXILIARY DC MOTOR-DRIVEN PUMP
The auxiliary DCMP function is to maintain fluid pressure on the auxiliary system accumulator. When the system pressure decreases to 2500 psi, an external pressure switch turns on the pump until pressure has reached 3350 psi. At that time, the pressure switch deactivates, commanding the pump off.
AUXILIARY HYDRAULIC SYSTEM ACCUMULATORS AND RESERVOIR
The auxiliary system accumulator has a nominal gas volume for 50 cubic inches of dry nitrogen, to satisfy the instantaneous demands of the hydraulic pressure and dampen out pressure surges with in the system. The pre-charge pressure versus tem-perature is set so that when the accumulator is discharged, the accumulator will still have sufficient oil for a smooth con-tinuous operation of the lower rudder as the pump comes on line at approximately 2500 psi.
The auxiliary system uses an intensifier to augment the inlet pressure to the auxiliary DCMP to prevent pump cavitation. The intensifier is a simple spring-loaded piston that transmits pressure from the RH system to the pressure side of the aux-iliary system reservoir. The DC pumps will come on prior to the engines starting and supply the intensifier with pressure. The AUX DCMP will come on if the AUX DCMP is selected to AUTO, there is power to the aircraft, and the aux system accumulator pressure is low. Once the AUX DCMP pressurizes, it is self-priming and its operation is independent of the RH system.
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