Hydraulics

Question 1

How many hydraulic systems does the aircraft have?

Answer 1

Three. Main systems A & B, and the Standby system

Question 2

Where are the hydraulic fluid reservoirs located?

Answer 2

In the main wheel well

Question 3

Which systems use hydraulic fluid?

Answer 3

Flight Controls, Leading edge devices, Trailing edge flaps, Landing gear, Wheel brakes, Nose wheel steering, Thrust reversers, Autopilot

Question 4

Normal hydraulic system operating pressure

Answer 4

3,000 psi

Question 5

Maximum hydraulic system operating pressure

Answer 5

3,500 psi

Question 6

How many pumps do the Hydraulic A & B systems have?

Answer 6

2 each - An engine driven pump and an electric motor driven pump

Question 7

How many pumps does the standby hydraulic system have?

Answer 7

1 electric motor driven pump

Question 8

T/F: Hydraulic A’s engine-driven pump is powered by the No. 2 engine

Answer 8

False (No. 1 Engine)

Question 9

Yaw dampener uses fluid from ____________ for it’s operation

Answer 9

Hydraulic System B

Question 10

Two ways of manually activating the Standby Hydraulic Pump

Answer 10

1. Selecting either FLT CONTROL switch to STBY RUD
2. Selecting the ALTERNATE FLAPS Master switch to ARM

Question 11

When does the STANDBY HYD LOW QUANTITY light illuminate?

Answer 11

When the standby fluid level drops below 50%

Question 12

The standby hydraulic reservoir is serviced/filled through Hydraulic System ______Reservoir

Answer 12

B

Question 13

An RF next to the hydraulic quantity on the Lower Display unit indicates….

Answer 13

That reservoir needs to be serviced/refilled. (Only displays on the ground with engines shut down or after landing with flaps retracted)

Question 14

T/F: The standby reservoir is not directly pressurized by bleed air

Answer 14

True. (However, Hydraulic B is pressurized and exerts some of that pressure on the standby)

Question 15

The power source for hydraulic system A & B respective electric pumps is

Answer 15

A - AC Transfer Bus 2
B - AC Transfer Bus 1

Question 16

For the hydraulic fluid heat exchangers to provide proper cooling there must be ____________ pounds of fuel in the related main tank

Answer 16

1,675

Question 17

The preflight minimum hydraulic pressure for the main systems (A&B) is

Answer 17

2,800 psi

Question 18

After a No. 1 engine failure, the Landing Gear Transfer Unit will help raise the gear using hydraulic fluid from __________

Answer 18

Hydraulic System B

Question 19

T/F: The electric motor driven hydraulic pumps are able to pump the same volume as the engine driven pumps

Answer 19

False. It can match the pressure (3,000 psi) but the volume is lower

Question 20

The PTU uses fluid pressure from system ____ to drive a pump which in turn pressurizes system ___when its engine driven pump pressure is lost.

Answer 20

A, B

Question 21

The Hydraulic Power Transfer Unit (PTU) operates what?

Answer 21

Leading edge flaps, Slats, Autoslat

Question 22

What happens when an ENG 1 or ENG 2 hydraulic switch is set to OFF?

Answer 22

Its corresponding blocking valve is energized which blocks the fluid downstream of the pump (the pump continues to operate)

The associated LOW PRESSURE light illuminates

Question 23

What does an OVERHEAT light on the Hydraulic Panel indicate?

Answer 23

Hydraulic fluid used to cool & lubricate the electric pump has overheated, or the pump itself has overheated

Question 24

System hydraulic fluid passes through a ___________ before returning to the reservoir

Answer 24

heat exchanger located in the same side main fuel tank

Question 25

T/F: Either Hydraulic system A or B can provide sufficient pressure to operate all the Primary flight controls (ailerons, elevators, rudder)

Answer 25

True