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self study > Hydraulics > Flashcards

Hydraulics Flashcards

1
Q

Which control has no means of back up in event of hydraulic failure?

A

Ground spoilers

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2
Q

Which controls are powered by Hyd #A? (10 items)

A

Ailerons, Rudder, Elevator, Landing gear, Autopilot A, Alternate brakes, ground spoilers, 2 flight spoilers per wing, No 1 thrust reverser, Nose wheel steering

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3
Q

Which controls are powered by Hyd #B? (12 items)

A

Ailerons, Rudder, Elevator, Leading edge flaps, Leading edge slats, Trailing edge flaps, yaw damper, Normal braking, Alternate nose wheel steering, 2 flight spoilers per wing, Autopilot B, No 2 thrust reverser

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4
Q

What does the landing gear transfer unit do?

A

Allows the retraction of the landing gear in case No 1 engine RPM insufficient to power Hyd #A

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5
Q

What does the power transfer unit do?

A

In case the engine driven pump for Hyd #B has low output, allows the normal rate extension and retraction of the leading edge devices

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6
Q

How are system A and B hydraulic reservoirs pressurised?

A

By bleed air

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7
Q

Where are the reservoirs located?

A

In the main wheel well area

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8
Q

What is normal hydraulic system pressure?

A

3000PSI

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9
Q

What is the maximum hydraulic system pressure?

A

3500PSI

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10
Q

What is the minimum hydraulic system pressure?

A

2800PSI

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11
Q

What does it mean if a small white RF is against the hydraulic fluid quantity and what triggers it?

A

Refill required, comes on at 76% QTY

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12
Q

When is the hydraulic fluid quantity reading valid?

A

On the ground with engines shut down or after landing with flaps retracted

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13
Q

How are the engine driven pumps driven?

A

From the engine accessory drive box using engine RPM

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14
Q

Are the engine driven pumps or electrical driven pumps more powerful?

A

Engine driven pumps, pump 6 times more fluid volume

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15
Q

How many hydraulic pumps are there?

A

5

Hyd #A - engine driven and electric pump
Hyd #B - engine driven and electric pump
Standby system - standby electric pump

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16
Q

What does turning the engine drive pumps off do?

A

Isolates the fluid from system components, pump still rotates with accessory drive

17
Q

Which bus powers the electrical driven pump?

A

XFR bus from opposite side

18
Q

What is the name of the electric pump which powers system Hyd #A?

A

Electric 2

19
Q

What is the name of the electric pump which powers system Hyd #B?

A

Electric 1

20
Q

What happens if the electric pump overheats?

A

OVERHEAT light illuminates, power is removed

MC for HYD

21
Q

What indications would result from loss of the System A EDP?

A

LOW PRESSURE light above EDP switch, MC for HYD.

With high system A demand, intermittent LOW PRESSURE indications on the electric pump. MC for HYD and FLT CONT

22
Q

How is hydraulic fluid from system A and B cooled?

A

Heat exchangers in the Main fuel tanks

Sys A - Main fuel tank No. 1
Sys B - Main fuel tank No. 2

23
Q

What is the minimum tank fuel quantity for cooling?

A

1675lbs 760kg

24
Q

What does the overheat light indicate and is there a MC?

A

Overheating of the hydraulic fluid or the pump itself leading to shutdown of the pump. MC for HYD

25
Q

What happens if a leak develops in the system A EDP or associated line?

A

standpipe limits fluid loss to 20% reservoir quantity

26
Q

What happens if a leak develops in the system A electric pump or associated line?

A

Fluid quantity decrease to zero, all pressure can be lost

27
Q

What happens if a leak develops in either system B EDP or electric pump?

A

Indicated quantity decreases to zero. Sufficient fluid remains below standpipe for PTU operation.

28
Q

How does the Power transfer unit work?

A

System A provides fluid to power the PTU pump, pressurising system B fluid for the relevant flight controls

29
Q

Under what conditions with the PTU automatically activate?

A

System B hydraulic pump pressure below limits
Airborne
Flaps less than 15 but not up

30
Q

How does the landing gear transfer unit operate?

A

Hydraulic system B output is used to operate the gear when criteria met

31
Q

What is the criteria for landing gear transfer unit operation?

A

A - irborne
N - o. 1 engine RPM below limits
U - ndercarriage lever up
L - anding gear not up and locked

32
Q

Which systems does the standby hydraulic system power?

A

Thrust reversers
Rudder - standby PCU
Yaw damper - standby yaw damper
Slats - leading edge flaps and slats(extend only)

33
Q

How can the standby hydraulic system be activated manually and what does it do?

A

Moving either FLT CONTROL switch to STBY RUD

Closes the appropriate flight control shut off valve
Activates standby pump
Opens standby rudder control valve
Deactivates LOW PRESSURE flight control light
Enables standby system power to rudder and thrust reverser

34
Q

What indications will be received when a FLT CONTROL switch is moved to STBY RUD?

A

STBY RUD ON, MC for FLT CONT

35
Q

What happens when ALTERNATE FLAPS switch is moved to arm?

A

Standby pump activates
Trailing edge flap bypass valve closes
Flaps can be extended using alternate flaps switch
Standby system powers leading edge flaps and slats, thrust reversers

36
Q

When does the standby system activate automatically?

A

Loss of Hydraulic system A or B and,
Flaps extended and,
Wheel speed >60knots or airborne and,
FLT CONTROL A or B switch ON or
Main PCU force flight monitor trips

37
Q

What will happen if there is a leak in the standby reservoir system?

A

Quantity decreases to zero
LOW QTY light when reservoir is 1/2 empty
System B pressure decreases to 72%

38
Q

What would cause the hydraulic system to foam?

A

Operating at high altitudes with insufficient reservoir pressurisation

self study (12 decks)

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