Brakes

Front 1

What has to be done before removing the aircraft assembly?

Back 1

The wheel assembly shall be deflated

Front 2

When troubleshooting hydraulic pressure what must be done?

Back 2

make sure the brake pressure is depleted prior to performing maintenance.

Front 3

What are hot brakes?

Back 3

Are over heated brakes.

Front 4

When can they occur?

Back 4

due to an aborted takeoff, after excessive braking when landing. or after towing an aircraft with a dragging brake assembly.

Front 5

What are signs of hot brakes?

Back 5

1.Loud popping

2 cracking noises.

3. A burning smell coming from the wheel assembly.

4 Glowing red brakes.

Front 6

What do you do if you suspect a hot brake?

Back 6

Notify supervisor and let it cool.

Front 7

From where do you approach hot wheels or brakes?

Back 7

Fore and aft.

never from the sides.

Front 8

Three types of material that contribute to wheel assembly fires?

Back 8

1. Hydraulic Fluid

2. Grease and bearing lubricants

3. Rubber tires

Front 9

What do bearing lubricants do when ignited?

Back 9

May ignite brake fluid adding more fuel to the fire causing wheel temps to climb to the point of explosion.

Front 10

Hydraulic Fluid safety?

Back 10

Broken or cracked line can result in the misting of petroleum based fluids onto the hot wheel assembly. The heat may ignite this misting fluid spread and will accelerate fires growth.

Front 11

At what temps may rubber tires ignite?

Back 11

500 to 600 F

Front 12

What force do brake systems provide?

Back 12

1. Slow and stop aircraft in a reasonable distance

2. Hold the aircraft for normal engine run up.

3. Aid in steering the aircraft during taxi operations.

Front 13

Where are brakes installed?

Back 13

On each main landing wheel and may be actuated independently

Front 14

What are the three most common aircraft brake systems?

Back 14

1. Independent: not part of the main hydraulic system

2. Power Boost system: System uses aircraft hydraulic system intermittently when needed.

3. Power brake system: System that only uses the aircraft main hydraulic systems as a source of pressure.

Front 15

When is an independent brake system used?

Back 15

In small, light aircrafts without hydraulic systems. Master cylinders are used to create the necessary pressure to operate the brakes.

Front 16

Independent brake systems is composed of:

Back 16

1. Brake pedals

2. Mechanical linkage

3.master cylinder

4. Disk brake assembly

5. parking brake

6. Fluid lines.

Front 17

What is Mechanical linkage?

Back 17

Is used to transfer the motion of the brake pedal to the master cylinder.

Front 18

Master cylinder?

Back 18

Displaces fluid to the brake assembly through brake lines by movement of the piston inside the cylinder.

Front 19

Vent

Back 19

Allows air to flow in and out of the reservoir.

Front 20

Reservoir

Back 20

Contains brake fluid for use in the system

Front 21

Piston

Back 21

Displaces brake fluid from the master cylinder to the brake assembly

Front 22

Piston return spring

Back 22

Returns the piston to the up position when the brakes are released.

Front 23

Brake line connection

Back 23

Serves as the attachment point for the brake lines.

Front 24

Parking brake

Back 24

A single parking brake handle will actuate valves in both the left and right brake lines.

Front 25

Fluid lines

Back 25

Are used to transfer brake fluid from the master cylinder to the disk brake assembly.

Front 26

Two types of fuel lines?

Back 26

1. Rigid steel

2. Flexible

Front 27

When is a power boost brake system utilized?

Back 27

When an aircraft lands to fast but are too light to require the power brake system.

Front 28

Power Boost components

Back 28

1. Shuttle valves

2.Power boost brake resevior

3. Power boost master cylinder

4. Emergency brake compressed air bottle

5. Emergency brake control

6. Emergency brake air release valve

7. Emergency air vent valve

8. Multiple disk brake assembly

Front 29

Shuttle valve

Back 29

Is used to direct pressure from two different systems. The valves inner assembly will shift to allow the system with the highest air pressure to operate the brakes.

Front 30

Power Boost reservoir

Back 30

Stores fluid for the brake master cylinder

Front 31

Power Boost master cylinder

Back 31

Supplies metered pressure to the brake assemblies.

Front 32

Emergency Brake compressed air bottle

Back 32

A separate bottle storing air under pressure for use by the emergency brake system.

Front 33

Emergency brake control

Back 33

Is mechanically connected to an air release valve. Allows an emergency air bottle to pressurize the brake lines.

Front 34

Emergency air release valve

Back 34

When opened air pressure from the air bottle is routed through the shuttle valves to pressurize brake lines and brake assemblies.

Front 35

Emergency air vent valve

Back 35

Relieves air pressure during emergency brake system actuation.

Front 36

When are Power brakes control valve system used?

Back 36

When the aircrafts requires a large amount of fluid to operate the brakes

Front 37

Power Brake system components

Back 37

1. Check valve

2. Accumulator

3. Control valves

4. Pressure relief Valve

Front 38

From where does the hydraulic pressure system gets its pressure?

Back 38

From the aircraft hydraulic pressure system

Front 39

Check Valves

Back 39

Allow fluid flow in one direction

Front 40

Accumulator

Back 40

The accumulator hold fluid under pressure for emergency use and acts as a shock absorber to protect the system from pressure surges

Front 41

Control valves

Back 41

Regulate and control the volume and pressure of fluid directed to the brake assemblies.

Front 42

Pressure relief valves

Back 42

Will prevent over pressurization in the brake system .

Front 43

Two types of disk brakes

Back 43

1. Single

2. multiple

Front 44

Single disk

Back 44

Installed on smaller aircrafts used primarily as a steering device and do not require dissipation of great amounts of heat or kinetic energy.

Linings made of organic and metallic material

Front 45

Brake housing

Back 45

A cast metal assembly housing the components of the disk brake assembly

Front 46

Fluid inlet bushing

Back 46

The brake line connection

Front 47

Piston for disk brake assembly

Back 47

Transmits break fluid to the brake lining

Front 48

Lining puck

Back 48

Pressed against the brake rotor to produce the braking action

Front 49

Brake disk

Back 49

The portion of the brake assembly that is rotated by the wheel

Front 50

Brake Release unit

Back 50

Pulls the brake lining back from the rotor

Front 51

Bleed valve

Back 51

Used to bleed air from the brake fluid lines.

Front 52

Multiple disk brake components

Back 52

1. Stators: do not rotate

2. Rotors: turn with the aircraft wheel hub

3.Wear indictor pins: With brakes applied indicate the amount if material remaining on the stators.

Front 53

Automatic braking

Back 53

Used to continuously adjust brake pressure to maintain optimum braking power. ensures maximum aircraft deceleration

Front 54

Antiskid brake system

Back 54

Senses an impending slip of a tire and adjust brake pressure to keep up the brakes from fully locking up on an individual tire.

Front 55

Antiskid components

Back 55

1. Wheel speed sensors

2. Antiskid computer

3.Control Valves

Front 56

Antiskid four functions

Back 56

1.Fail safe protection

2. touchdown protection

3.locked wheel skid control

4. normal skid control

Front 57

Wheel speed sensor

Back 57

Located on every wheel. An AC or DC generator that produces voltage that corresponds to the speed of the rotating wheel

Front 58

Antiskid computer

Back 58

Generates electrical signals usable by the control valve. regulates brake pressure to prevent skidding. prevents brake application prior to touchdown

Front 59

Control valve anti skid

Back 59

Receives signal and provides hydraulic pressure to the brake assembly. Maintains output pressure that is proportional.