Hydraulic

Question 1

Electric Hydraulic Pump OVERHEAT​ Lights

Answer 1

Hydraulic fluid used to cool​ and​ lubricate the ​corresponding electric motor driven​ pump​ has overheated or the pump itself has ​overheated

Question 2

Hydraulic “RF”
When and how much

Answer 2

hydraulic quantity below 76%

Valid only when airplane is on ground with both engines shutdown or after ​landing​ with flaps up during​ taxi–in

Question 3

HYDRAULIC System QUANTITY​ Indications

Answer 3

White

Indicates digital​ percentage (0%​ to 106%)​ of hydraulic quantity.​

Note:​ Quantity also displayed at each reservoir

Question 4

HYDRAULIC System PRESSURE Indications

Answer 4

(white)​
Indicates system pressure:​
•​ Normal​ pressure – 3,000psi
​•​ Maximum​ pressure – 3,500psi.​
N.P.
Verify that the brake pressure is​ 2,800psi minimum.​
Verify that the system A​ and B pressures are 2,800psi minimum

Note:​ When​ both​ pumps for a system​ are OFF, the indication may read hydraulic ​system​ reservoir pressure, normally​ less than​ 100psi

Question 5

FLIGHT​ CONTROL​ Switches​ - STBY​ RUD

Answer 5

Activates standby​ pump and opens standby​ rudder shutoff valve to ​pressurize standby rudder power control unit.​

Question 6

FLIGHT​ CONTROL​ Switches​ - OFF

Answer 6

OFF – closes flight control shutoff valve isolating​ ailerons, elevators​ and rudder ​from​ associated hydraulic system pressure.​

Question 7

FLIGHT​ CONTROL​ Switches​ - On

Answer 7

ON (guarded position) – normal operating position

Question 8

Flight Control LOW​ PRESSURE Lights​

Answer 8

(amber) –​
•​ indicates low hydraulic system (A​ or​ B) pressure to ailerons, elevator ​and rudder
​•​ deactivated when associated FLIGHT​ CONTROL​ switch is​ positioned ​to STBY​ RUD and standby rudder shutoff valve opens.

Question 9

STANDBY​ HYDRAULIC LOW​ QUANTITY​ Light​

Answer 9

Illuminated (amber) –​
•​ indicates low quantity in standby hydraulic reservoir​
•​ always armed

Question 10

STANDBY​ HYDRAULIC LOW​ PRESSURE​ Light​

Answer 10

Illuminated (amber) –​
•​ indicates output pressure of standby pump​ is low​
•​ armed only when standby pump operation has been selected or ​automatic standby​ function is activated

Question 11

ALTERNATE FLAPS Master​ Switch​

Answer 11

OFF (guarded position) – normal operating position.​
ARM –​ closes trailing edge flap bypass valve, activates standby pump, and arms ​ALTERNATE FLAPS position switch

Question 12

STBY​ RUD ON​ Light ​

Answer 12

Illuminated (amber) -
Indicates the standby hydraulic system​ is commanded on to ​pressurize the standby rudder power control unit.

Question 13

Minimum fuel for​ ground operation of electric motor-driven ​pumps

Answer 13

760kg in the related main tank

Question 14

What is powered by hydraulic system A only

Answer 14

1. No. 1 thrust reverser
2. Autopilot A
   —————————-
3. P. PTU
4. L. Landing gear
5. A. Alternate Brakes
6. N. Nose Wheel Steering
7. G. Ground Spoilers

Question 15

What’s is powered by Hydraulic System B only

Answer 15

• No. 2 thrust reverser
• Autopilot B
——————————
1. LED - Leading Edge Device
2. TED - Trailing Edge Device
3. L. LGTU Landing Gear Transfer Unit
4. A. Autoslats
5. B. Brakes
6. A. Altn NWS
7. Y. Yaw Damper

Question 16

What is powered by Both Hydraulic Systems

Answer 16

1. ailerons
2. rudder
3. elevator and elevator feel
4. flight spoilers (two on each wing)

Question 17

The purpose of the PTU is…

Answer 17

to supply​ the additional volume of hydraulic fluid ​needed to operate the autoslats and leading edge flaps and slats​ at the normal rate ​when​ system B engine-driven​ hydraulic pump is inoperative.

Question 18

The PTU uses …

Answer 18

system A​ pressure to power a hydraulic​ motor-driven pump, which pressurizes ​system​ B hydraulic fluid.

Question 19

The PTU operates automatically when​ all of the ​following​ conditions exist:​

Answer 19

•​ system​ B engine-driven pump hydraulic pressure drops below limits​
•​ airborne
•​ flaps not up* (tail# specific)

Question 20

Does a​ leak in system B does​ affect the operation of the standby hydraulic system

Answer 20

A​ leak in system B does​ NOT affect the operation of the standby hydraulic system

Question 21

The purpose of the landing gear transfer unit is…

Answer 21

to supply​ the volume of hydraulic ​fluid needed to raise the landing gear​ at the normal rate when system A​ ​engine–driven pump volume is lost

Question 22

Landing gear transfer unit ​operates using ___ and when​ all of​ the following conditions exist:

Answer 22

The system B engine–driven​ pump​ supplies ​the volume of hydraulic fluid needed​

•​ airborne​
•​ No. 1 engine​ RPM drops below​ a limit​ value​
•​ landing​ gear lever is positioned UP​
•​ either main landing gear is not up and locked.

Question 23

Standby Hydraulic System powers what? (4)

Answer 23

•​ thrust reversers​
•​ rudder
​•​ leading edge flaps and slats (extend only)​
•​ standby yaw damper

Question 24

Standby Hydraulic Automatic Operation occurs when?

Answer 24

•​ loss of system A​ or B,​ and​
•​ flaps extended,​ and​
•​ airborne, or wheel speed greater than 60kt, and​
•​ FLT​ CONTROL​ switch A​ or​ B Hydraulic System ON​
OR:​
•​ the main PCU Force Fight Monitor​ (FFM) trips

Question 25

Automatic operation of the standby hydraulics, what happens?

Answer 25

•​ activates the standby​ electric motor-driven pump​
•​ opens​ the standby​ rudder shutoff valve​
•​ allows the standby system to power the rudder and thrust reversers.​
•​ illuminates the STBY​ RUD ON, Master Caution, and Flight Controls ​(FLT​ CONT) lights

Question 26

Hydraulic system A standpipe

Answer 26

EDP leak - quantity = 20% = EMDP works satisfactorily

EMDP leak - quantity = 0% = system inoperable

Question 27

Hydraulic B standpipe

Answer 27

Standby leak - Quantity = 70%

EDP or EMDP leak, quantity = 0%. However 5 litres remains and PTU is able to operate