Hydraulic System Flashcards
Pulling the Engine 1 fire warning switch _____ the respective hydraulic pump LOW PRESSURE lights
deactivates
Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and _____.
deactivates the LOW PRESSURE light
If a leak develops in either pump, line or component of system B, _____.
the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational
If a leak develops in the A system hydraulic ENGINE-driven pump or its related lines, _____.
a standpipe in the reservoir prevents a total system fluid loss
Automatic operation of the standby pump is initiated when loss of the hydraulic system A or B; and _____.
flaps extend and airborne, or wheel speed greater than 60 knots
Positioning either FLT CONTROL switch to STBY RUD, closes the related flight control shutoff valve; deactivates the related flight control LOW PRESSURE light; allows the standby system to power the rudder and thrust reversers; and _____.
activates the standby electric motor-driven pump; opens the standby rudder shutoff valve (all answers correct)
On the ground with both engines shutdown, a REFILL indication, illuminated white RF next to the Hydraulic quantity indicates _____.
hydraulic quantity below 76%
On the B737-800, what occurs when there is a leak in the standby hydraulic system _____
The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72%
The standby system _____ and uses a single electric motor driven pump.
can be activated manually or automatically
The landing gear transfer unit operates when airborne, the No. 1 engine RPM drops below a limit value, _____.
the landing gear is positioned up and either main landing gear is not up and locked
The purpose of the PTU is to supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when _____.
system B engine-driven pump volume is lost
The purpose of the landing gear transfer unit is to raise the landing gear at the normal rate when _____.
system A engine-driven pump volume is lost
If a leak develops in the A system hydraulic ELECTRIC motor-driven pump or its related lines, _____.
the quantity in the reservoir steadily decreases to zero and all system pressure is lost
Positioning the ENG 1 hydraulic pump switch to OFF isolates fluid flow from the system components and the pump _____ to rotate.
continues
