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Republic E170 > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

The primary flight control system consists of:

A
  • ailerons and multi-function spoilers
  • elevators
  • rudder
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2
Q

The secondary flight control system consists of:

A
  • horizontal stabilizer
  • flaps and slats
  • multi-function spoilers used as speed brakes or ground spoilers
  • dedicated ground spoilers
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3
Q

The primary flight control electronics are generally comprised of two parts:

A
  • the Primary Actuator Control Electronics (P-ACE)

- the Flight Control Module (FCM)

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4
Q

Flight Control Mode Button PUSH IN/PUSH OUT

A

IN - direct mode

OUT - normal mode

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5
Q

Name the nine Actuator Control Electronics (ACEs)

A
  • three primary ACEs (P-ACE)
  • two slat/flap ACEs (SF-ACE)
  • one horizontal stabilizer ACE (HS-ACE)
  • three spoiler ACEs (S-ACE)
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6
Q

How many flight control modules (FCM)?

A

four

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7
Q

How many channels does each ACE have?

A

two, one active and one standby

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8
Q

Location of P-ACEs

A

fwd ebay - 2

aft ebay - 1

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9
Q

Location of SF-ACEs

A

middle ebay

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10
Q

Location of HS-ACE

A

aft ebay

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11
Q

What do the FCMs do?

A

provide software based assistance to the P-ACE by providing higher level function augmentation to pilot inputs

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12
Q

FCM location

A

FCM 1 and 2 - MAU 1

FCM 3 and 4 - MAU 3

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13
Q

Name the higher level functions that the FCM provides in “normal mode”

A
  • elevator control laws w/ airspeed
  • auto thrust compensation with elevator
  • mach trim and autopilot trim
  • AOA limiting with elevator offset
  • rudder airspeed gain scheduling and stroke limiting
  • yaw damper and turn coordination via AFCS
  • rudder flight authority
  • roll spoiler scheduling and speed brake deployment
  • automatic spoiler deployment at high mach number
  • configuration change compensation with horizontal stabilizer
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14
Q

Describe direct mode

A

FCM is removed from control loop because of loss of data or multiple failures in both ACEs

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15
Q

What is the CAN BUS

A

Controller Area Network; communication link between the FCMs and the P-ACE units

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16
Q

The following systems provide data to the flight control system:

A
  • smart probes and Air Data Application modules
  • IRS
  • Proximity Sensor Electronic Modules (weight on wheels)
  • Brake Control Modules
  • FADEC provides thrust lever angle
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17
Q

Describe the Fly By Wire Backup system

A

a dedicated backup battery with internal heater keeps elevator and rudder actuators operating for at least 15 minutes, charged by DC ESS 3

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18
Q

Describe the pitch system components

A
  • electro-hydraulic commanded elevators

- electro-mechanical horizontal stabilizer

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19
Q

How many elevator PCUs

A

four, operate on active/standby mode alternating every time elevator system is powered up

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20
Q

Which hydraulic system power which elevator PCU

A

1 - left outboard
2 - left and right inboard
3 - right outboard

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21
Q

What happens during an elevator jam

A

if jam in one elevator actuator, respective elevator surface remains fixed in position, pilot controls remaining elevator

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22
Q

Elevator/Rudder Flight Control Panel Button

A

cycles between normal or direct mode and cycles active and standby PCUs

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23
Q

Describe the Elevator Thrust Compensation Function

A

helps reduce pilot workload by applying elevator commands to reduce pitching moment by increasing or decreasing engine thrust

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24
Q

Describe the elevator Artificial Feel Units

A

provide the feel and centering force for the control columns, consist of pre-loaded springs

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25
Q

Describe the elevator Disconnect Mechanism

A

allows separation of control columns in the event of a jam, mx must reset on ground

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26
Q

Control of the Horizontal Stabilizer is commanded by:

A
  • wheel main trim switches
  • pedestal mounted back up trim switches
  • FCM for autopilot trim and speed brake auto trim
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27
Q

What is used to control the horizontal stabilizer

A
  • HS-ACE

- Horizontal Stabilizer Actuator

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28
Q

Describe the Horizontal Stabilizer Actuator

A

single electrical-mechanical actuator with two DC motors (active/standby)

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29
Q

HS-ACE trim command priority

A
  • back up switches
  • captain
  • first officer
  • FCM auto trim
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30
Q

Manual pilot trim commands are limited to

A

3 seconds

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31
Q

What causes a low rate condition in the horizontal stabilizer actuator

A
  • electrical emergency

- loss of airspeed data from FCM

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32
Q

Autopilot trim function will be active only if:

A
  • autopilot engaged
  • configuration trim is operational
  • manual electric trim is not active
  • on side autopilot channel is priority
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33
Q

Describe the aileron control system

A

conventional cable connected to two hydromechanical actuators for each aileron

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34
Q

Which hydraulic system powers which aileron actuators

A

2 - left and right inboard PCUs

3 - left and right outboard PCUs

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35
Q

How does the aileron system handle jams

A

divided into left and right systems which can be disconnected, thereby allowing movement in the functional half

36
Q

Name the 6 multi function spoiler panels

A

inboard to outboard
L3 L4 L5 (left wing)
R3 R4 R5 (right wing)

37
Q

Describe the multi function spoiler jam

A

captain controls outboard spoilers, first officer controls middle spoilers, inboard become disabled

38
Q

Describe the roll trim system

A

adjusts neutral position of control wheel

39
Q

How many rudder PCUs?

A

two (active/standby)

40
Q

Who powers which rudder PCU

A

captain - upper

first officer - lower

41
Q

Which hydraulic system powers which rudder PCU?

A

1 - upper

3 - lower

42
Q

Describe a rudder pedal jam

A

rudder remains active and will be actuated by high-level functions

43
Q

Describe a rudder PCU jam

A

rudder will be hydraulically locked at the current position

44
Q

How many slat surfaces

A

eight (four per wing)

45
Q

How many flap surfaces

A

four double slotted flap surfaces (two per wing)

46
Q

Slat and flap motion sequence

A

slats extend first, flaps retract first

47
Q

How are the slats and flaps deployed

A

electrical commanded and operated using Power Driver Units (PDUs), four flaps actuators per side, eight slat actuators per side

48
Q

If an excessive load is detected on the flaps PDUs:

A

electrical power is stopped to that PDU, can still be commanded in opposite direction or both directions (for three consecutive attempts)

49
Q

What happens to flap/slats during RAT deployment

A
  • operate at half speed

- prevents deployment beyond position 3

50
Q

What happens after a flap/slat failure

A

affected surface is de-energized, non affected surface still commanded except for:
- flaps beyond 10 degrees with slats below 15 degrees (flaps 2 limits flap deflection to 10 degrees)

51
Q

How many spoiler panels total

A

10 (5 per wing)

52
Q

Multifunction spoilers have three modes of operation:

A
  • roll control
  • speed brakes
  • ground spoilers
53
Q

Hyd system 1 powers which multi function spoiler panels?

A

left and right inboard and middle (L3, R3, L4, R4)

54
Q

Hyd system 2 powers which multi function spoiler panels?

A

left and right outboard (L5, R5)

55
Q

Hyd system 1 powers which dedicated ground spoiler panels?

A

left and right outboard (R2, L2)

56
Q

Hyd system 2 powers which dedicated ground spoiler panels?

A

left and right inboard (R1, L1)

57
Q

Spoilers deploy on ground during the following condition:

A
  • WOW
  • wheel speed above 45 kts or airspeed above 60 KIAS
  • TLA below 26 degrees
58
Q

When do the ground spoilers automatically retract?

A
  • wheel speed below 45 kts for at least 5 seconds

- throttles moved beyond 35 degrees

59
Q

When are ground spoilers and/or speed brakes not available

A

direct mode

60
Q

When will speed brakes automatically retract?

A
  • slat/flap 2 or above
  • airspeed below 180 KIAS
  • TLA beyond 70 degrees
61
Q

ELEV (RUDDER) (SPOILER) NML MODE FAIL warning

A

normal mode no longer operative

62
Q

GROUND SPOILERS FAIL warning

A

one of the ground spoiler surfaces has extended inadvertently or has failed to extend when commanded

63
Q

AOA LIMIT FAIL caution

A

stall protection function has failed

64
Q

ELEV THR COMP FAIL caution

A

one or more sensors required to perform Elevator Thrust Compensation function has failed and the function is no longer available

65
Q

ELEVATOR FAULT caution

A

left and right elevator control system has reverted to direct mode

66
Q

ELEVATOR (LH or RH) FAIL caution

A

left or right elevator control system has reverted to direct mode

67
Q

FLAP FAIL caution

A

both flaps electronic control channels are inoperative and the flap system is no longer available or there is a jam in the mechanical portion that precludes the flaps from moving

68
Q

FLT CTRL BIT EXPIRED caution

A

50 hours or more has passed since the last time PBIT was activated

69
Q

FLT CTRL NO DISPATCH caution

A

one of the components associated with the flight control system has failed to a no-go position

70
Q

PITCH TRIM FAIL caution

A

pitch trim function is no longer available

71
Q

RUDDER FAIL caution

A

active and standby rudder channels have failed or rudder has jammed

72
Q

RUDDER FAULT caution

A

indicated that the rudder control system has reverted to direct mode

73
Q

RUDDER LIMITER FAIL caution

A

indicates that rudder ground authority is retained after takeoff

74
Q

SLAT FAIL caution

A

both slats electronic control channels are inoperative and the slats system is no longer available; or there is a jam in the mechanical portion that precludes the slats from moving

75
Q

SLAT-FLAP LVR DISAG caution

A

flaps were commanded above VFE

76
Q

SPOILER FAULT caution

A

airspeed gain scheduling has failed in one or more pairs of multi function spoilers, and the system has defaulted to a fixed gain

77
Q

STAB LOCK FAULT caution

A

the mechanical device that locks the horizontal stabilizer has failed, direct mode is not allowed

78
Q

AILERON (LH or RH) FAIL advisory

A

indicates that the left or right aileron is no longer available or there is a mechanical disconnection in the surface

79
Q

AUTO CONFIG TRIM FAIL advisory

A

pitch trim auto configuration function is inoperative

80
Q

FLAP LO RATE advisory

A

one of the flaps electronic control channels is inoperative and the flap system is still available but running at low speed

81
Q

FLT CTRL FAULT advisory

A

one of the components associated with the flight control system has failed

82
Q

PITCH CONTROL DISC advisory

A

control columns are disconnected

83
Q

PITCH TRIM BKUP FL advisory

A

backup pitch trim switch is inoperative

84
Q

PITCH TRIM SW 1 FAIL advisory

A

captains pitch trim switch is inoperative

85
Q

PITCH TRIM SW 2 FAIL advisory

A

first officers pitch trim switch is inoperative

86
Q

ROLL CONTROL DISC advisory

A

control wheels are disconnected

87
Q

SLAT LO RATE status

A

one of the slats electronic control channels is inoperative and the slat system is still available but in low speed

Republic E170 (22 decks)

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