Hydraulic System

Question 1

The aircraft has ______ hydraulic systems. () two () three () four

Answer 1

Three

Question 2

_____________ can power all flight controls with no decrease in aircraft controllability. () The standby hydraulic system () The RAT () Either A or B hydraulic system

Answer 2

Either A or B hydraulic system

Question 3

Normal operating pressure for each hydraulic system is ______________ psi. () 3,500 () 3,000 () 2,000

Answer 3

3,000 psi

Question 4

Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and ______________. () deactivates its LOW PRESSURE light () engages the standby hydraulic system () activates the LOW PRESSURE light

Answer 4

Deactivates its LOW PRESSURE light

Question 5

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

Answer 5

the quantity in the reservoir steadily decrease. However a stand pipe will prevent total fluid loss in system A.

Question 6

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

Answer 6

the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational

Question 7

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

Answer 7

system B engine-driven pump volume is lost

Question 8

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

Answer 8

the landing gear is positioned up and either main landing gear is not up and locked

Question 9

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

Answer 9

leading edge flaps and slats (extend only) and the standby yaw damper

Question 10

Positioning either FLT CONTROL switch to STBY RUD, closes the related flight control shutoff valve; deactivates the related flight control LOW RPESSURE 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

Answer 10

all answers are correct

activates the standby electric motor-driven pump () opens the standby rudder shutoff valve ()

Question 11

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

Answer 11

The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72%

Question 12

Pulling the Engine 1 fire warning switch ____________ the respective hydraulic pump LOW PRESSURE lights. () activates () deactivates

Answer 12

deactivates

Question 13

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

Answer 13

controls the related electric motor-driven pump

Question 14

The HYDRAULIC System QUANTITY is shown on the DU, and indicates digital ____________ of hydraulic quantity. () gallons () percentage () quarts

Answer 14

percentage

Question 15

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

Answer 15

all answers are correct

ailerons and elevator & rudder

Question 16

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

Answer 16

always armed

Question 17

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

Answer 17

armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated

Question 18

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

Answer 18

by pushing the MFD System (SYS) switch

Question 19

The minimum fuel for ground operation of electric hydraulic pumps is ___ in the related main tank.

() 1000
() 2000
() 1676

Answer 19

() 1676

Question 20

On the ground with both engines shut down, a REFILL indication, illuminated white RF next to the hydraulic quantity indicates _____.

() Hydraulic quantity below 86%

()The related hydraulic system is currently being refilled

() Hydraulic quantity below 76%.

Answer 20

() Hydraulic quantity below 76%.