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Part 121 - CRJ 701/900 > Landing Gear And Brakes > Flashcards

Landing Gear And Brakes Flashcards

1
Q

PSEU

A

Proximity Sensing Electronic Unit

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2
Q

How does the PSEU work?

A

Uses sensors to determine gear and gear door position and supplies this to the Data Concentrator Unit (DCU) for display on the EICAS primary page

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3
Q

What controls the nose wheel?

A

Controlled by a steering Electronic Control Unit (ECU)

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4
Q

Which way does the NLG retract?

A

Forward into nosewheel bay.

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5
Q

How does NLG lock?

A

In both extended and retracted positions via spring-loaded, over-center locking mechanism.

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6
Q

Which way do the MLGs retract?

A

Inboard to the fuselage.

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7
Q

Proximity Sensor System components

A
  1. PSEU

2. Proximity sensors and switches

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8
Q

What landing gear related functions does the PSS provide?

A

Normal landing gear positioning control, landing gear position indication and weight on wheels monitoring.

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9
Q

When is the landing gear position indication removed?

A

30 seconds after the gear is up and locked position with flaps at 0

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10
Q

If gear and handle positions disagree, what will happen?

A

Warning message displays and aural sounds

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11
Q

How is the PSS tested?

A

Continuously through the PSEU

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12
Q

“PROX SYS CHAN” caution

A

1 PSEU channel loss

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13
Q

“PROX SYS” caution

A

Loss of both PSEU channels

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14
Q

WOW

A

Weight on Wheels sensor

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15
Q

What is the purpose of the solenoid lock in the landing gear control handle?

A

Prevents the lever from being moved to UP position on the ground

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16
Q

Weight Off Wheels signal from PSEU is sent to _______ the landing gear lock

A

Unlock

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17
Q

If the landing gear handle solenoid lock malfunctions, what can we do?

A

DN LCK REL button will allow us to override the solenoid lock.

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18
Q

What is the purpose of the tire spin-down assembly in the NLG bay?

A

Stops nosewheel rotation when NLG is retracted

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19
Q

Which hydraulic system powers the landing gear?

A

Number 3.

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20
Q

What retracts and extends the landing gear?

A

A retract/extend actuator

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21
Q

If a failure occurs in the landing gear control system or in the hydraulic system number 3, the _______ will allow for alternate gear lowering

A

Landing gear manual release

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22
Q

What happens when the landing gear manual release handle is pulled and held to its full extension?

A

MLG unlocks are released

Bypass valve dumps number 3 hydraulic pressure which permits the gear to partially extend under its own weight.

Hydraulic system 2 will pressure MLG auxiliary actuators and NLG uplock manual release actuator

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23
Q

MLG auxiliary actuators

A

Assist the gear to the down and locked position

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24
Q

When can the Landing gear Manual Release be released during a manual extension of the landing gear?

A

Once EICAS indicates NLG and MLG are down and locked

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25
Q

When will the landing gear warning horn sound?

A

Incorrect configuration during landing phase of flight:

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26
Q

Can the gear warning horn always be muted?

A

Only in certain configurations.

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27
Q

What hydraulic system powers the NWS?

A

Hydraulic system number 3.

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28
Q

When is NWS enabled?

A

System armed, on the ground (WOW) and gear down and locked.

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29
Q

What is the maximum angle either side of center for the nosewheel using the tiller?

A

80 degrees

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30
Q

How much can the rudder pedals move the nosewheel?

A

8 degrees either side of center.

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31
Q

What straightens the nosewheel prior to extraction and what keeps it centered?

A

Prior to retraction: ECU

Keeps centered: centering cam on nosewheel strut.

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32
Q

How is directional control maintained in the shimmy dampening mode?

A

Differential braking

Differential thrust

33
Q

When will the NWS enter the shimmy dampening mode?

A
  1. Failure detected by the steering control system or…

2. Hydraulic system number 3 is lost

34
Q

What may cause the “STEERING INOP” caution to display prior to landing?

A

Moving the nosewheel steering tiller more than 2 degrees

35
Q

How are the main wheel disc brakes actuated?

A

2 independent systems, No. 2 and No. 3 hydraulic system

36
Q

Fusible plugs

A

Fitted to main gear wheels which prevent against tire burst in the event of overheat

37
Q

How do you check the wear pin indicators?

A

With the brakes applied and No. 2 and No. 3 hydraulic systems pressurized

38
Q

Inboard brakes are powered by hydraulic system number _____ and the outboard by number ______.

A

3; 2

39
Q

During landing gear retraction, hydraulic pressure is applied to the main brakes to ________.

A

Stop the main wheels from spinning

40
Q

If a leak occurs in a brake line, what will happen?

A

The associated hydraulic fuse will close off the hydraulic line

41
Q

With loss of 1 hydraulic system, the aircraft has ______ symmetric braking capability and ____ anti-skid braking on operative brakes.

A

50%; FULL

42
Q

If Hydraulic No. 2 and 3 fail, what will happen to the braking system?

A

Accumulators in each system will provide reserve pressure for braking

43
Q

When will anti skid engage?

A
  1. Anti Skid switch is ARMED
  2. Parking brake is not engaged
  3. Both main landing gear are down and locked
  4. WOW signal is received
  5. 35 knot wheel spin-up signal is present
44
Q

How does the anti-skid system work?

A

Monitors each wheel speed individually to detect skidding. If detected, the ASCU reduces brake pressure at the skidding wheel by modulating pressure outputs of the appropriate anti-skid control valve

45
Q

When is a “A/SKID FAULT” status message generated?

A
  1. Loss of redundancy of ASCU
  2. Loss of WOW input
  3. Spin down failure
  4. Loss of internal communication
46
Q

When will a “A/SKID OUTBD” caution display?

A

When that anti skid channel has failed.

47
Q

What provides braking when aircraft is parked?

A

The inboard brakes and the parking brake shutoff valve

48
Q

How do we set the parking brake?

A

Pull the parking brake handle and turn it 90 degrees while fully depressing the brakes.

49
Q

When is the parking brake on advisory message displayed?

A
  1. On the ground
  2. Both engines not at take-off power
  3. Inboard brake pressure greater than 800 psi
50
Q

When will the parking brake SOV caution be generated?

A

Parking brake shutoff valve fails open

Inboard brake pressure greater than 800 psi

51
Q

BTMS

A

Brake Temperature Monitoring System

52
Q

What makes up the BTMS?

A

Four temperature sensors

ASCU

BTMS OVHT WARN RESET switch

53
Q

BTMS Temp indications:

A

Green: normal

White: caution

Red: Exceeded

Amber: sensor failure

54
Q

NLG consists of:

A

2 forward and one aft door

55
Q

MLG is held in the up and locked position by:

A

A mechanical lock

56
Q

“PROX SYS FAULT 2” status message indicates:

A

Any one non-critical sensor or input or output has failed

57
Q

Retraction and extension of the landing gear is normally powered using:

A

Hydraulic system No. 3

58
Q

When the aircraft is configured for takeoff, but the parking brake is set, what will happen?

A

A “PARKING BRAKE” WARNING will sound.

59
Q

Landing gear is _____ controlled and ______ actuated

A

Electronically / hydraulically

60
Q

The normal hydraulic system for retracting and extending the landing gear is…

A

Hydraulic system 3

61
Q

Turn limit for the NLG is?

A

80 Degrees

62
Q

What can absorb side loads during landing?

A

Side stay

63
Q

How is the MLG held in the retracted position?

A

Mechanical uplock

64
Q

How is main wheel rotation stopped on MLG retraction?

A

Hydraulic system 3 brake application

65
Q

Without #2 hydraulic pressure, nose gear ______

A

Cannot be extended

66
Q

When can you no longer silence the gear horn?

A

160 KIAS

67
Q

When will EGPWS say “Too Low, Gear”

A

Less than 500’ and airspeed is less than 190 KIAS with the gear not down.

68
Q

PSS

A

Proximity sensing unit, senses location of the gear, electro magnetic, no mechanical parts. Takes place of squat switches

69
Q

Each digit on the BTMS is how many degrees?

A

35 degrees

70
Q

How long will a RED BTMS indicator stay?

A

Forever until… maintenance resets. Requires an inspection of the fuse plugs on the wheel wells

71
Q

What is the maximum BTMS indication?

A

20

72
Q

PSEU

A

Proximity sensor electronic unit. Monitors position of unlocks and down locks, controls valve position for landing gear.

73
Q

Maximum tire limit speed:

A

182 - 700

192 - 900

74
Q

Do we disable NWS in flight?

A

No

75
Q

What is the purpose of the electronic control unit?

A

To command the NLG to turn based on the Tiller.

76
Q

How do you reset the Electronic Control Unit when “STEERING INOP” caution is displayed?

A

Turn NWS OFF and ON again.

77
Q

When are landing gear indications removed from EICAS?

A

30 seconds after the gear is up and locked, the flaps are at 0 degrees and the BTMS indications are normal.

78
Q

What do we have to do in order to get an accurate brake wear test?

A

Pressurize inboard and outboard brakes and set the parking brake

Part 121 - CRJ 701/900 (25 decks)

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