18 Questions
What powers the aircraft's primary hydraulic systems?
Engine-Driven Pump (EDP) installed on the respective left and right engine
How are the left and right hydraulic systems designed to maintain independence?
Each system has separate lines and no common point for fluid interchange
What is unique about the left hydraulic system's fluid pressurization?
Left system fluid may be pressurized by two sources other than the EDP
What is the primary function of the PTU and AUX pump?
Pressurize and deliver stored hydraulic fluid to components operated by the individual system.
What kind of hydraulic fluid is the system designed to use?
Fire resistant phosphate-ester type hydraulic fluid to AS 1241, Type IV or Type V at 2850 to 3075 psi with only a 20 psi ripple throughout the system.
What is the purpose of the Power Transfer Unit (PTU) in the aircraft's hydraulic system?
Transfer hydraulic power from the right system to the left system, without transferring fluid.
What conditions trigger the PTU operation in the aircraft's hydraulic system?
Left system hydraulic pressure < 2400 psi AND Left system hydraulic quantity > 0.36 Gallons (uncompensated quantity) AND Right system hydraulic pressure > 2850 psi AND Right system hydraulic temperature < 107°C (225°F)
What is the maximum pressure supplied by the electrically motor driven hydraulic pump?
3100 psi
When does the AUX pump automatically power on for flap and landing gear operation during flight?
After dual engine failure, dual EDP failure, left EDP failure plus PTU failure, or left EDP failure plus landing gear in transition.
What are the specific conditions under which the hydraulic pump is offloaded in flight?
When the engine N2 speed drops below 55%.
Describe the functionality of the onboard replenisher system in terms of hydraulic servicing of the aircraft.
The onboard replenisher system includes a 1.5 U.S. gallon reservoir, an electric motor driven pump, a hydraulic selector valve, and an ONIOFF switch. The pump outputs 0.5 GPM at 60 psi to the reservoir.
What is the function of the Rotary Variable Differential Transformer (RVDT) in the hydraulic system?
To determine fluid level through rotary movement and provide output for the Fluid Quantity Indicator (FQI) and Modular Avionics Units (MAUs).
Where is the left reservoir located and what is its purpose?
The left reservoir is located in the tail compartment, forward at approximately the 10:00 o'clock position. Its purpose is to supply fluid to the left hydraulic system.
What are the conditions for deactivating the PTU based on left system hydraulic pressure?
2750 psi or above to deactivate the PTU, and immediately at 2400 psi to activate the PTU.
What is the purpose of the motor-operated shutoff valve in the PTU?
The shutoff valve prevents the right system from pressurizing the PTU motor when the motor is not commanded to run.
What are the conditions under which the crew can still immediately turn the AUX pump back on again?
By cycling the NORMION switch
What is the range of the hydraulic pressure displayed and at what resolution?
0 - 4,000 psi with a 100 psi resolution
What conditions trigger the automatic power on of the AUX pump for flap and landing gear operation during flight?
Dual engine failure, Dual EDP failure, Left EDP failure plus PTU failure, Left EDP failure plus landing gear in transition, Timed (two minutes) operation in flight
Test your knowledge of hydraulic reservoir systems with this quiz. Learn about the storage of hydraulic fluid under pressure, air separation, and the functionality of the reservoir in hydraulic pumps.
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