Hydraulics System

Question 1

The aircraft has ______ hydraulic systems.

Answer 1

three

Question 2

_____________ can power all flight controls with no decrease in aircraft controllability.

Answer 2

Either A or B hydraulic system

Question 3

Normal operating pressure for each hydraulic system is ______________ psi.

Answer 3

3,000

Question 4

Positioning the ENG 1 hydraulic pump switch to OFF isolates fluid flow from the system components and the pump ________ to rotate.

Answer 4

continues

Question 5

Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and ______________.

Answer 5

deactivates it LOW PRESSURE light

Question 6

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

Answer 6

1676 lbs.

Question 7

If a leak develops in the A system hydraulic engine-driven pump or its related lines, ________________________.

Answer 7

a standpipe in the reservoir prevents a total system fluid loss

Question 8

If a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines, ________________________

Answer 8

the quantity in the reservoir steadily decreases to zero and all system pressure is lost

Question 9

If a leak develops in either pump, line or component of system B, ________________________.

Answer 9

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 10

A leak in hydraulic system B __________ the operation of the standby hydraulic system.

Answer 10

does not affect

Question 11

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 ___________________.

Answer 11

system B engine-driven pump volume is lost

Question 12

The purpose of the landing gear transfer unit is to raise the landing gear at the normal rate when _______________.

Answer 12

system A engine-driven pump volume is lost

Question 13

The landing gear transfer unit operates when airborne, the No. 1 engine RPM drops below a limit value, ____________.

Answer 13

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

Question 14

The standby system ____________________ and uses a single electric motor-driven pump

Answer 14

can be activated manually or automatically

Question 15

The standby hydraulic system powers the thrust reversers, rudder, ____________.

Answer 15

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

Question 16

Automatic operation of the standby hydraulic pump is initiated when loss of hydraulic system A or B; and __________

Answer 16

flaps extended; and airborne, or wheel speed greater than 60 knots

Question 17

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 ___________________________________________

Answer 17

() all answers are correct
() activates the standby electric motor-driven pump
() opens the standby rudder shutoff valve

Question 18

Positioning the ALTERNATE FLAPS master switch to ARM: operates the trailing edge flap bypass valve, allows the standby system to power the leading edge flaps and slats and thrust reversers, arms the ALTERNATE FLAPS position switch and _________________

Answer 18

() activates the standby electric motor-driven pump
() engages the alternate asymmetrical flap protection computer
() positions the leading edge devices to FULL EXTEND

Question 19

On the B737-800, what occurs when there is a leak in the standby hydraulic system ___________________________________________

Answer 19

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

Question 20

An amber illuminated Electric Hydraulic Pump OVERHEAT light indicates ___________________________________________

Answer 20

() all answers are correct
() the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated
() the pump itself has overheated

Question 21

Pulling the Engine 1 fire warning switch ____________ the respective hydraulic pump LOW PRESSURE lights

Answer 21

deactivates

Question 22

Positioning the ELECTRIC HYDRAULIC PUMP Switch to ON ________________.

Answer 22

controls the related electric motor-driven pump

Question 23

The HYDRAULIC System QUANTITY is shown on the DU, and indicates digital ____________ of hydraulic quantity

Answer 23

percentage

Question 24

On the ground with both engines shutdown, a REFILL indication, illuminated white RF next to the Hydraulic quantity indicates ___________.

Answer 24

hydraulic quantity below 76%

Question 25

An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to ___________.

Answer 25

() all answers are correct
() ailerons and elevator
() rudder

Question 26

An illuminated amber standby hydraulic LOW QUANTITY light indicates low quantity in standby hydraulic reservoir, and is ___________.

Answer 26

always armed

Question 27

An illuminated amber standby hydraulic LOW PRESSURE light indicates low output pressure, and is ___________.

Answer 27

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

Question 28

On the PFD/ND, hydraulic system quantity is displayed __________.

Answer 28

by pushing the MFD System (SYS) switch