Boeing 737 - Hydraulic System Exam MCQ

1

The engine driven hydraulic pump switch

In the OFF position will de-activate the hydraulic LOW PRESS light.

Is left in the ON position on shutdown to prolong the life of the blocking valve solenoid.

Should be switched OFF in the event of the electric hydraulic pump OVERHEAT light illuminating.

2

The Standby hydraulic fluid

Is cooled by a heat exchanger located in NO. 2 tank.

Is cooled by a heat exchanger located in NO. 1 tank.

Is not cooled.

3

The standby system low quantity light is

Armed at all times and will illuminate whenever the reservoir is approximately half empty.

Armed at all times and will illuminate whenever the reservoir is approximately three quarters empty.

Armed only when either Flt Control switch is placed to the STBY RUD position.

4

Using the Standby Hydraulic power for thrust reverser deployment will cause

Deployment time not to be affected.

Deployment time to increase.

Deployment time to decrease.

5

The 'B' system reservoir has

One standpipe.

Two standpipes.

One standpipe used for reservoir pressurisation of the standby reservoir.

6

A leak in the hydraulic system A engine driven pump or its associated lines would be indicated by

System A contents falling to three quarters full (conventional engine instruments) or 64% (EIS).

System A contents falling to one quarter full (conventional engine instruments) or 40% (EIS).

System A contents falling to one quarter full (conventional engine instruments) or 22% (EIS).

7

The standby hydraulic pump is automatically activated on the loss of system A or B hydraulic pressure

During the take-off or landing with a wheel speed greater than 60 Kts and the wing flaps extended.

During the take-off or landing with a wheel speed greater than 90 Kts and wing flaps extended.

During d takeoff or landing wid wheel speed greater than 60Kts irrespective of the wing flaps positn

8

Loss of the B hydraulic system will result in the complete loss of the following

Outboard flight spoilers. Autopilot B. No. 2 thrust reverser. Yaw damper.

Outboard flight spoilers. Autopilot B. Normal brakes. Yaw damper.

Outboard flight spoilers. Autoslats. Autopilot B.

9

Loss of the A hydraulic system will result in the complete loss of the following

Ground spoilers. Inboard flight spoilers. Alternate brakes. Autopilot A.

Ground spoilers. Inboard flight spoilers. Normal brakes. Nose wheel steering.

Ground spoilers. Outboard flight spoilers. Elevator feel system. Alternate brakes. Autoslat system.

10

The maximum hydraulic system A or B pressure is

3000psi

2500psi

3500psi

11

Illumination of a electric hydraulic pump OVERHEAT light will

Automatically shut down the associated pump.

Not shut down the associated pump.

Automatically arm the LOW PRESSURE light for the associated pump.

12

Illumination of a Hydraulic Electric Pump OVERHEAT light indicates

An overheat condition in the hydraulic reservoir.

An overheat condition of the pump hydraulic supply line.

An overheat condition in the case drain line or the pump housing.

13

Hydraulic system A power sources are

One engine driven pump (ENG 1) and one electrical motor pump (ELECT 1).

One engine driven pump (ENG 1) and one electrical motor pump (ELECT 2).

One engine driven pump (ENG 1), one electrical motor pump (ELECT 1) and one standby electric pump.

14

The Standby hydraulic reservoir is kept topped up from

Oil containers used by engineers before each flight.

The system A reservoir.

The system B reservoir.

15

The normal and maximum readings on the hydraulic system pressure indicator are

3000 : 3500psi

2500 : 3200psi

3000 : 3750psi

16

Selecting an engine driven hydraulic pump switch to OFF will

Electrically close the fluid supply valve at the reservoir.

De-activate the solenoid-held blocking valve and isolate fluid from the using unit.

Activate the solenoid-held blocking valve and isolate fluid from the using unit.

17

The A and B hydraulic reservoirs are pressurised by

Air from the 14th stage only.

Air from the pneumatic manifold.

Hydraulic fluid from the standby reservoir.

18

If a total failure of both pumps supplying system B pressure occurs, which of the primary flight controls will be totally inoperative

None

Aileron and elevator.

Rudder only.

19

Low fluid quantity in the A system reservoir can be indicated by one of the following

Mechanical indication on the reservoir.

LOW QUANTITY light on the center instrument panel.

LOW QUANTITY light on the centre instrument panel along with a Master Caution ENG annunciator light.

20

The standby hydraulic pump only supplies pressure to the

Standby rudder and leading edge slats.

Standby rudder actuator, leading edge devices and thrust reversers.

Standby rudder, leading edge devices and brakes.

21

The standby system LOW PRESSURE light is armed

Only when the standby pump operation has been selected or automatic standby function is activated.

At all times.

Only when the standby pump operation has been selected or either Spoiler switch has been selected to

22

A leak in the hydraulic system B engine driven pump or its associated lines would be indicated by

System B contents falling to one quarter full (conventional engine instruments) or 25% (EIS).

System B contents falling to half full (conventional engine instruments) or 40% (EIS).

System B contents falling to three quarters full (conventional engine instruments) or 64% (EIS).

23

If an electric hydraulic pump OVERHEAT light comes on

The pump will be automatically switched off and the OVERHEAT LIGHT extinguished.

Turn the associated system electric and engine hydraulic pumps OFF.

Turn the associated system electric hydraulic pump OFF.

24

Complete loss of system 'B' pressure will deactivate

The outboard flight spoilers.

The inboard flight spoilers.

The ground spoilers.