Chapter 13 - Hydraulics

Question 1

The STANBY LOW Quantity light illuminates, what other indication will you have?

Answer 1

Both master caution lights and the flight control annunciator light will illuminate

Question 2

The refill indication (RF) is displayed adjacent to it’s respective hydraulic system quantity:

Answer 2

when the hydraulic quantity is below 76% in either system and valid only when the airplane is on the ground with both engines shutdown or after landing with flaps up during taxi-in

Question 3

If a leak occurs in the B system, the Standby hydraulic system will:

Answer 3

A leak in the B system has no effect on the standby hydraulic system.

Question 4

When the system B engine-driven hydraulic pump pressure is lost, the Power Transfer Unit (PTU) supplies an additional volume of hydraulic fluid to operate the:

Answer 4

autoslats and leading edge flaps and slats at the normal rate.

Question 5

Autoslats are normally powered by:

Answer 5

system B.

Question 6

Pulling the No.2 engine fire warning switch shuts off hydraulic fluid to:

Answer 6

the engine-driven pump in system B.

Question 7

The standby hydraulic system provides back-up power for:

Answer 7

thrust reversers, rudder, leading edge flaps and slats (extend only) and standby yaw damper.

Question 8

If a leak occurs in the standby system:

Answer 8

a. system B fluid level indication decreases and stabilizes at approximately 72% full.
b. the standby reservoir quantity decreases to zero.
c. All the answers are correct
d. The LOW Quantity light illuminates when the standby reservoir is approximately half empty

Question 9

The amber Standby Hydraulic System LOW PRESSURE light is armed:

Answer 9

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

Question 10

During normal operations, variations in hydraulic quantity indications occur when:

Answer 10

a. the system becomes pressurized after engine start.
b. raising or lowering the landing gear or leading edge devices.
c. cold soaking occurs during long periods of cruise.
d. all the answers are correct.

Question 11

If the system A engine-driven hydraulic pump (amber) annunciator light illuminates:

Answer 11

position the hydraulic pump switch to OFF

Question 12

What is the minimum fuel for ground operation of the electric hydraulic pumps?

Answer 12

1676 lbs. (760 kg.) in the related main tanks.

Question 13

The system B engine-driven pump supplies the volume of hydraulic fluid needed to operate the landing gear transfer unit when:

Answer 13

a. either main landing gear is not up and locked.
b. the No.1 engine RPM drops below a limit value.
c. airborne with the landing gear lever positioned up.
d. All conditions must exist together.

Question 14

The standby hydraulic system can be activated manually or automatically and uses a single
electric motor driven pump to power:

Answer 14

a. the rudder and thrust reversers
b. all of the answers are correct
c. the leading edge flaps and slats (extend only).
d. standby yaw damper

Question 15

If No.1 engine fails and the APU generator is inoperative, what hydraulic pumps are operational?

Answer 15

One system A electric pump, one system B engine-driven pump and the standby pump

Question 16

With the loss of hydraulic System B, (System A operating normally) and flaps up

Answer 16

standby yaw damper functions are available if the FLT Control B Switch is placed to STBY RUD and the YAW DAMPER Switch is reset to ON.

Question 17

An Engine Driven hydraulic pump supplies approximately ______ times the volume of an
electric hydraulic pump

Answer 17

4 times

Question 18

What does the Standby Hydraulic LOW Quantity light illuminated indicate:

Answer 18

Low-quantity in the standby hydraulic reservoir

Question 19

With a loss of system A hydraulic and the system A FLIGHT CONTROL switch in the STBY RUD position, what are some of the inoperative items?

Answer 19

Ground spoilers, flight spoilers (2 each wing), Autopilot A, normal nose wheel steering and alternate brakes

Question 20

With the loss of system B hydraulic fluid and the system B FLIGHT CONTROL switch to STBY RUD, what allows the movement of trailing edge flaps?

Answer 20

Electric motor.

Question 21

System A and B hydraulic fluid is cooled by:

Answer 21

heat exchangers located in the main fuel tanks

Question 22

If a leak develops in system B (either pump, line or component), the quantity decreases to:

Answer 22

approximately zero and B pressure is lost

Question 23

There are ___ reservoirs and ____ pumps, each delivering ___ PSI.

Answer 23

Three, five, 3000.

Question 24

The pumps of the main systems are:

Answer 24

A: #1 engine driven pump and #2 ELEC - AC Transfer Bus #2

B: #2 engine driven pump and #1 ELEC - AC Transfer Bus #1

Question 25

If a leak develops in the system A engine driven pump line, the reservoir will:

Answer 25

Maintain approximately 20% of the hydraulic fluid.

Question 26

If a leak develops in either electric driven pump line:

Answer 26

The system reservoir will empty

Question 27

To ensure proper cooling of either system fluid on the ground:

Answer 27

The main fuel tanks must have at least 760kgs of fuel.

Question 28

If electrical power is lost on either system, the engine driven pump shutoff valve:

Answer 28

Opens and the engine pump fails to the ON condition.

Question 29

If a leak develops in system B engine driven pump:

Answer 29

The reservoir will drain down until the quantity shows approximately zero and the system pressure will be lost. Sufficient pressure will remain to power the PTU.

Question 30

The landing gear transfer unit operates:

Answer 30

Using system B after takeoff when the #1 engine N2 falls below a set value with the landing gear up and either main gear not up and locked.

Question 31

The purpose of the PTU is:

Answer 31

To provide back-up hydraulic pressure to the Autoslat system and leading edge flaps and slats.

Question 32

The PTU automatically operates when:

Answer 32

Automatically when the output of the system B engine driven pump pressure falls below a limit when in-flight with the flaps extended.

Question 33

One reason the system B reservoir is larger than the system A reservoir is:

Answer 33

Because it can supply about 30% of fluid to the standby system via an interconnecting balance line.

Question 34

The standby system LOW QUANTITY light illuminates when:

Answer 34

The system is approximately half full

Question 35

The difference between the LOW QUANTITY and the LOW PRESSURE standby hydraulic lights is:

Answer 35

The LOW QUANTITY light is always enabled, though the LOW PRESSURE LIGHT is inhibited when the system is inactive.

Question 36

With the system A FLT CONTROL switch in the STBY RUD position:

Answer 36

The system A pressure is turned off, the standby rudder shutoff valve is opened and the standby motor pump is powered.

Question 37

The yaw damper switch will move to OFF automatically when:

Answer 37

The system B FLT CONTROL switch is moved to STBY RUD.

Question 38

When the ALTERNATE FLAPS switch is moved to ARM:

Answer 38

The standby motor pump activates, the alternate flaps UP/DOWN switch arms and the trailing edge bypass valve closes.

Question 39

The difference between the alternate modes for the trailing edge flaps and the leading edge flaps and slats is that:

Answer 39

The trailing edge flaps are electrically operated whereas the leading edge flaps and slats are hydraulically operated.

Question 40

Moving the ALTERNATE FLAPS switch to ARM:

Answer 40

Closes the trailing edge flaps bypass valve and arms the alternate flaps UP/DOWN switch.