B737 System Validation Question Bank – Hydraulics R1

Front 1

Hydraulic System Schematic
7/8/9

Back 1

Front 2

Hydraulic Standby System Schematic
7/8/9

Back 2

Front 3

Hydraulic System Schematic
/5

Back 3

Front 4

Hydraulic System Components
A & B Systems

Back 4

Front 5

These Cards are not verified accurate. Please, if you find a mistake, email: [e-mail]

Back 5

Check back for future revisions!

Front 6

1. Which statement is true regarding the standby hydraulic system connection to other reservoirs?
a. Connected to system A reservoir
b. Connected to system B reservoir
c. Connected to system A & B reservoirs

Back 6

b. Connected to system B reservoir

Front 7

2. A leak in the number two engine driven hydraulic pump will drain the B system reservoir to empty.
a. True
b. False

Back 7

b. False

Front 8

3. What would be the first indication of a leak in the Standby Hydraulic system?
a. Standby system LOW PRESSURE amber light illuminates
b. Standby system LOW QUANTITY amber light illuminates
c. System B quantity decreases

Back 8

c. System B quantity decreases

Front 9

4. During cruise at FL310, the pilots notice that the brake pressure read 0 psi. System B pressure is 300 psi and system B quantity is full. What is the problem?
a. The brake accumulator pre-charge has leaked out
b. A loss of system B reservoir pressurization
c. A brake accumulator check valve failure

Back 9

a. The brake accumulator pre-charge has leaked out

Front 10

5. How is hydraulic fluid cooled?
a. Heat exchangers in the respective main fuel tank
b. Heat exchangers in the center fuel tank
c. Heat exchangers in the respective hydraulic reservoirs

Back 10

a. Heat exchangers in the respective main fuel tank

Front 11

6. What occurs when a fire switch is pulled?
a. Shuts off hydraulic fluid supply to respective hydraulic system reservoir
b. Shuts off hydraulic fluid supply to respective engine driven pump
c. Shuts off hydraulic fluid supply to respective electric pump

Back 11

b. Shuts off hydraulic fluid supply to respective engine driven pump

Front 12

7. What would extinguish (disarm) a number one engine driven hydraulic pump LOW PRESSURE light?
a. Moving an engine pump switch OFF
b. Moving the respective FLT CONTROL switch to OFF
c. Pulling the respective fire switch

Back 12

c. Pulling the respective fire switch

Front 13

8. Which of the following are operated by the A hydraulic system?
a. LE flaps & slats and TE flaps
b. Normal brakes for inboard main wheels
c. Alternate brakes for all main wheels

Back 13

c. Alternate brakes for all main wheels

Front 14

9. Which of the following is/are normally operated by the B hydraulic system?
a. Ground spoilers
b. Normal brakes for all wheels
c. Nose wheel steering
d. All answer are correct

Back 14

b. Normal brakes for all wheels

Front 15

10. What does an illuminated single hydraulic pump LOW PRESSURE light indicate?
a. The pump output pressure is below acceptable limits
b. The fire switch has been pulled for the engine pump
c. Hydraulic system pressure is below acceptable limits

Back 15

a. The pump output pressure is below acceptable limits

Front 16

11. What does an illuminated hydraulic OVERHEAT light indicate?
a. Engine pump overheat
b. Electric pump overheat
c. Electric or engine pump case overheat

Back 16

b. Electric pump overheat

Front 17

12. When is the STANDBY HYD LOW QUANTITY light armed?
a. Whenever the standby pump is signaled to operate
b. When the standby rudder shutoff valves opens
c. Whenever the aircraft electrical buses are powered

Back 17

c. Whenever the aircraft electrical buses are powered

Front 18

13. When is the STANDBY HYD LOW PRESSURE light armed?
a. Whenever the Generator Buses are powered
b. Whenever hydraulic B system fails inflight with the flaps up
c. When electric power is supplied to the standby pump

Back 18

c. When electric power is supplied to the standby pump

Front 19

14. When performing the Standby Rudder check (crew option), what occurs when the B FLT CONTROL switch is placed to OFF?
a. The B system flight control valve closes and B system pressure is isolated from the primary flight controls
b. The Standby System hydraulic pump is started
c. System B pressure to the trailing pump is started

Back 19

a. The B system flight control valve closes and B system pressure is isolated from the primary flight controls

Front 20

15. What occurs when the B FLT CONTROL switch is placed from OFF to STBY RUD position?
a. The Standby System hydraulic pump starts
b. The Standby Rudder Shutoff Valve opens
c. The System B pressure to the flight controls remains isolated
d. All answers are correct

Back 20

d. All answers are correct

Front 21

16. After placing a FLT CONTROL switch to STBY RUDDER, how is the open position of the standby rudder shutoff valve indicated?
a. The respective FLT CONTROL LOW PRESSURE light extinguishes
b. The FEEL DIFF PRESS light extinguishes
c. The STANDBY HYD LOW PRESSURE light extinguishes

Back 21

a. The respective FLT CONTROL LOW PRESSURE light extinguishes

Front 22

17. When does the standby pump activate automatically?
a. Loss of either engine driven hydraulic pump, gear lever in the UP position, and #1 engine N2 drops below limit
b. Loss of A or B system pressure with flaps extended while airborne or on the ground with wheel speed greater than 60 knots
c. Loss of B system engine driven pump with the trailing edge flaps in the 1, 2, or 5 position

Back 22

b. Loss of A or B system pressure with flaps extended while airborne or on the ground with wheel speed greater than 60 knots

Front 23

18. Which action turns on the STANDBY HYD pump?
a. ALTERNATE FLAP master switch placed to ARM position
b. ALTERNATE FLAP position switch placed to DOWN position
c. Either flight control switch to OFF

Back 23

a. ALTERNATE FLAP master switch placed to ARM position

Front 24

19. The Power Transfer Unit provides a backup source of hydraulic pressure (power) to operate:
a. Trailing edge flaps
b. Leading edge flaps and slats
c. Landing gear

Back 24

b. Leading edge flaps and slats

Front 25

20. The electric hydraulic pumps of system A and B are equipped with thermal switches. What is the cockpit indication when a pump thermal switch activates?
a. Electric power is removed from the pump
b. The respective OVERHEAT light illuminates
c. The respective LOW QUANTITY light illuminates

Back 25

b. The respective OVERHEAT light illuminates

Front 26

21. The Auto Slat system?
a. Is normally powered by System A
b. Is normally powered by the Power Transfer Unit
c. Is normally powered by System B

Back 26

c. Is normally powered by System B

Front 27

22. Pulling the #2 Fire Switch:
a. Shuts off fluid to the engine driven hydraulic pump in System A
b. Shuts off fluid to the electric hydraulic pump in System B
c. Shuts off fluid to the electric hydraulic pump in System A
d. Shuts off fluid to the engine driven hydraulic pump in System B

Back 27

d. Shuts off fluid to the engine driven hydraulic pump in System B

Front 28

23. A standby system hydraulic leak is first indicated by:
a. A decrease in A quantity indication
b. A decrease in B quantity indication
c. A decrease in standby gauge quantity indication
d. The standby LOW PRESSURE light

Back 28

b. A decrease in B quantity indication

Front 29

24. System A electric hydraulic pump is powered by which electrical power source?
a. Gen bus #2
b. Gen bus #1
c. DC bus #2
d. DC bus #1

Back 29

a. Gen bus #2

Front 30

25. The Standby Hydraulic System provides hydraulic power to the:
a. Trailing edge flaps, ground spoilers, and thrust reversers
b. Alternate brakes, thrust reversers, and leading edge devices
c. Trailing edge flaps, alternate brakes, and thrust reversers
d. Rudder, thrust reversers, and leading edge devices

Back 30

d. Rudder, thrust reversers, and leading edge devices

Front 31

26. The normal brake system is powered by:
a. Hydraulic system B
b. Hydraulic system A
c. Standby hydraulic system
d. Hydraulic power transfer unit

Back 31

a. Hydraulic system B

Front 32

27. What is the minimum fuel quantity in each wing tank for operation of the electric hydraulic pumps on the ground?
a. 1676 pounds
b. 1776 pounds
c. 1749 pounds
d. 1800 pounds

Back 32

a. 1676 pounds

Front 33

28. The Standby System hydraulic pump is driven by
a. The engine N2 accessory drive
b. An electric motor
c. A hydraulic motor driven by system A pressure
d. A pneumatic motor

Back 33

b. An electric motor

Front 34

29. The Power Transfer Unit is driven by
a. Hydraulic pressure from system A
b. Hydraulic pressure from system B
c. Hydraulic pressure from the Standby System
d. An electric motor

Back 34

a. Hydraulic pressure from system A

Front 35

30. Which hydraulic system pumps must be turned OFF during pushback if the nosewheel steering bypass pin is not installed?
a. Standby System
b. System A
c. System B
d. All hydraulic pumps

Back 35

b. System A

Front 36

31. What is the power source for the system B Elect 1 hydraulic pump?
a. #1 Generator Bus
b. #2 Generator Bus
c. Battery Bus
d. Standby Bus

Back 36

a. #1 Generator Bus