_____________ can power all flight controls with no decrease in aircraft controllability. The standby hydraulic system The RAT Either A or B hydraulic system.
Normal operating pressure for each hydraulic system is ______________ psi. 3,500 3,000 2,000.
Positioning the ENG 1 hydraulic pump switch to OFF isolates fluid flow from the system components and the pump ________ to rotate. continues ceases.
Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and ______________. deactivates it LOW PRESSURE light engages the standby hydraulic system activates the LOW PRESSURE ligh.
The minimum fuel for ground operation of electric hydraulic pumps is _____ in the related main tank. 1000 lbs. 1676 lbs. 2000 lbs.
If a leak develops in the A system hydraulic engine-driven pump or its related lines, ________________________. the system quantity will steadily decrease to 15% a standpipe in the reservoir prevents a total system fluid loss the quantity in the reservoir steadily decreases to zero and all system pressure is lost.
If a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines, ________________________. the system quantity will steadily decrease to 15% a standpipe in the reservoir prevents a total system fluid loss the quantity in the reservoir steadily decreases to zero and all system pressure is lost.
If a leak develops in either pump, line or component of system B, ________________________. the system quantity will steadily decrease to 15% the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational the quantity in the reservoir steadily decreases approximately zero, system B pressure and the standby system pressure is lost.
A leak in hydraulic system B __________ the operation of the standby hydraulic system. does not affect inhibits.
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 A engine-driven pump volume is lost system B engine-driven pump volume is lost the standby system 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 system B engine-driven pump volume is lost the standby system volume is lost.
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 landing gear is positioned up and both main landing gear is not up and locked and a main landing gear is not up and locked.
The standby system ____________________ and uses a single electric motor-driven pump. can only be activated by placing the ALTERNATE FLAPS Master Switch to ARM can only be activated by positioning either FLIGHT CONTROL switch to STBY RUD can be activated manually or automatically.
The standby hydraulic system powers the thrust reversers, rudder, ____________. leading edge flaps and slats (extend and retract) and the standby yaw damper leading edge flaps and slats (extend only), autobrakes and the standby yaw damper leading edge flaps and slats (extend only) and the standby yaw damper.
Automatic operation of the standby hydraulic pump is initiated when loss of hydraulic system A or B; and __________ flaps extended; and airborne, or wheel speed greater than 60 knots flaps retracted and airborne all answers are correct.
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 are correct.
On the B737-800, what occurs when there is a leak in the standby hydraulic system ___________________________________________ The LOW QUANTITY light illuminates, and the system A reservoir fluid decreases to zero The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72% The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to zero.
An amber illuminated Electric Hydraulic Pump OVERHEAT light indicates ___________________________________________ the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated the pump itself has overheated all answers are correct.
Pulling the Engine 1 fire warning switch ____________ the respective hydraulic pump LOW PRESSURE lights. activates deactivates.
Positioning the ELECTRIC HYDRAULIC PUMP Switch to ON ________________. allows for transfer of hydraulic system fluid between system A and the standby system allows for transfer of hydraulic system fluid between system B and A with the parking brake set controls the related electric motor-driven pump.
The HYDRAULIC System QUANTITY is shown on the DU, and indicates digital ____________ of hydraulic quantity. gallons percentage quarts.
On the ground with both engines shutdown, a REFILL indication, illuminated white RF next to the Hydraulic quantity indicates ___________. hydraulic quantity below 86% hydraulic quantity below 76% the related hydraulic system is currently being refilled.
An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to ___________. ailerons and elevator rudder all answers are correct.
An illuminated amber standby hydraulic LOW QUANTITY light indicates low quantity in standby hydraulic reservoir, and is ___________. armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated deactivated when Engine 2 fire switch has been pulled always armed.
An illuminated amber standby hydraulic LOW PRESSURE light indicates low output pressure, and is ___________.
armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated deactivated when Engine 2 fire switch has been pulled always armed.
On the PFD/ND, hydraulic system quantity is displayed __________.
on the Upper Display Unit by pushing the MFD System (SYS) switch at all times with the secondary engine indications.
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