A visual sight gage is installed on high pressure end of each hydraulic reservoir and clearly indicates proper FULL and REFILL levels of the reservoir. What is required for an accurate reading?
Flight crew operation of the PTU Pump is accomplished by the PTU ON or the PTU OFF/ARM pushbutton switches located on the HYDRAULIC CONTROL section of the Cockpit Overhead Panel (COP).
It is not a 'OR' but a 'AND': the operation of the PTU Pump is accomplished by the PTU ON and the PTU OFF/ARM pushbutton switches located on the HYDRAULIC CONTROL section of the Cockpit Overhead Panel (COP).
An external service panel mounted on the underside of the tail of the aircraft has provisions for servicing the reservoirs of both hydraulic systems as well as connections for attaching pressurized lines and system drain lines.
The Aux pumps are primarily designed for ground and maintenance operations. It’s part of the _____ and, when activated, can power the flaps, landing gear, inboard brakes and inboard parking brake, cabin door, and nose wheel steering.
The primary purpose of the pump is to provide hydraulic pressure to the utility systems for ground and maintenance activities. The AUX pump has a secondary function as an inflight backup power source. This system is normally inactive in flight, but will automatically power on for flap and landing gear operation after any of the dual engine failure, dual EDP failure, left EDP failure plus PTU failure, left EDP failure plus landing gear in transition.
The hydraulic engine-driven pump is a constant pressure, variable volume pump, that produces _____ anytime the engine is running (except for a pump unloading feature during engine start in-flight).
There are two replenishing systems in the tail compartment. What are they for?
The amber caution 'Aux Hydraulic Pump Overload' CAS message is displayed. What does it mean?
There is a switch to disable the Engine-Driven Hydraulic Pump (EDP). It is controlled by an engine fire handle on the forward section of the cockpit center console.
There is no switch to disable the Engine-Driven Hydraulic Pump (EDP). Instead, a shutoff valve, located in the tail compartment, is installed in the supply line between the reservoir and the pump. It is controlled by the left engine fire handle on the forward section of the cockpit center console. The shutoff valve is powered by 28V DC from the left essential bus.
The purpose of the heat exchanger is to cool hydraulic fluid heated in the pumps and heat fuel in the wings to delay fuel jelling.
What is the purpose of Power Transfer Unit (PTU)?
The PTU is used when there is pressure available in the right system and containment of the left system has not been lost, but there is no pressure available in the system. The PTU transfers hydraulic power, but not fluid, from the right to left system. It is a combination motor and pump that uses hydraulic pressure from the right system to turn a hydraulic motor. The motor then turns a pump that pressurizes the left system. The PTU is capable to operate flaps, landing gear, nose wheel steering, inboard brakes, inboard parking brakes and cabin door.
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The amber caution 'PTU Hydraulic Fail' CAS message is displayed. What does it mean?
The left hydraulic system is operationally similar to the right system, but is functionally limited to providing hydraulic power to the flight controls, and single source power to the right engine thrust reverser and the motor drive of the Power Transfer Unit (PTU) impeller.
This the right hydraulic system that is operationally similar to the left system, but is functionally limited to providing hydraulic power to the flight controls, and single source power to the right engine thrust reverser and the motor drive of the Power Transfer Unit (PTU) impeller.
How many hydraulic reservoirs are there? Where are hydraulic reservoirs located?
Left hydraulic system reservoir on left and right hydraulic system reservoir on the right.
How many hydraulic heat exchangers are there?
One for each system located in each hopper close to the floor.
How many hydraulic accumulators are there?
The preflight requirement is to check for 1200 psi at 70 deg.F (21 deg.C) nitrogen pre-charge.