Landing Gear And Brakes

Question 1

How many air/ground sensors are there on the landing gear?

Answer 1

6. Two on each gear

Question 2

Where do these sensors send information to?

Answer 2

The proximity switch electronics unit (PSEU)

Question 3

What are some of the systems and components controlled by the PSEU?

Answer 3

Landing gear position indication and warning
Takeoff warning
Air/ground relays
Stall warning
Engine control
Anti-ice
Cabin pressurization

Question 4

When will the PSEU light illuminate?

Answer 4

On the ground only when a fault exists.

Question 5

When is the PSEU light inhibited?

Answer 5

In flight,
When the thrust levers are advanced towards takeoff power,
And for 30 seconds after landing

Question 6

What indications will show when the landing gear and landing gear lever indication are in disagreement?

Answer 6

The landing indicator lights are red.

Question 7

For what other reasons will the landing gear indicator lights illuminate red?

Answer 7

When the landing gear is not down and locked, with the thrust lever at idle and the aircraft is below 800 AGL

Question 8

When will the landing gear warning horn sound?

Answer 8

1. Single engine, thrust lever less than 34 degrees, flap setting 15-25
2. Single engine, thrust lever less than 34 degrees, flap setting up-10, operating below 800 AGL
3. Anytime flaps greater than 25
4. Both engines operating, thrust levers less than 20 degrees, flaps 15-25
5. Both engines operating, thrust levers less than 20 degrees, up-10, operating below 800’ AGL

Question 9

When can’t you silence the landing gear warning horn?

Answer 9

Anytime flaps greater than 10 or below 200’ RA and gear is not down & locked

Question 10

Which hydraulic system supplies the pressure to retract the landing gear?

Answer 10

Hydraulic system A

Question 11

How many degrees can the nose wheel be turned using the tiller and using the rudders?

Answer 11

Tiller 78 degrees
Rudders 7 degrees

Question 12

Which hydraulic system provides pressure for the brakes?

Answer 12

System B is normal and system A is an alternate source

Question 13

Using the alternate hydraulic system, which brake functions are usable and unusable?

Answer 13

Anti skid is available
Auto brakes are inoperative

Question 14

The auto brake system disarms and the AUTO BRAKE DISARM light illuminates during any of which conditions?

Answer 14

SPEED BRAKE lever moved to the DOWN detent
Manual braking is applied
The RTO position is selected for landing
The AUTO. RALE selector is moved to the OFF position
Malfunction exists in the system
Thrust levers are advanced

Question 15

How do you arm RTO setting?

Answer 15

Must be on ground
Wheels speed less than 60 knots
Thrust levers at idle

Question 16

When will the auto brake setting RTO become active?

Answer 16

At or above wheel speed 90 knots
Thrust levers idle

Question 17

In the event of a system A And B pressure loss, what brake system remains to stop the aircraft?

Answer 17

Brake accumulator approx. 3,000 psi

Question 18

Which systems and components are controlled by the PSEU (Proximity Sensor Electronic Unit)?

Answer 18

Cabin Pressurization
LG position & Indication warning
Engine control
Air/ground relays
Anti - Ice
Takeoff warning
Stall warning

Question 19

When does the PSEU light illuminate?

Answer 19

If a fault exists on the ground only

Question 20

When is the PSEU light inhibited?

Answer 20

1. In flight
2. When thrust levers advanced toward takeoff power
3. 30 seconds after landing

Question 21

When will the RED landing gear indicator lights illuminate?

Answer 21

1. Landing gear is in disagreement with the landing gear lever position.
2. Also when:
   - Landing gear is not down and locked
   - Either thrust lever at idle and
   - Aircraft below 800’ AGL

Question 22

When will Hydraulic system B (Alternate source of pressure) retract the landing gear through the landing gear transfer unit?

Answer 22

All conditions exist:

1. In flight
2. No. 1 engine RPM drops below certain limit value
3. LANDING GEAR lever positioned up
4. Either main landing gear is not up and locked