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ERJ 175 > Flight Controls - Complete > Flashcards

Flight Controls - Complete Flashcards

1
Q

The ailerons are commanded by… ?

A

Conventional control cables

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2
Q

How are the ailerons controlled?

A

Via control cables that run from each control wheel to a pair of hydro-mechanical actuators: PCU’s

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3
Q

The primary control electronics include what two complimentary parts?

A

The PACE - Primary Actuator Control ElectonicsFCM - Flight Control Module

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4
Q

The Pitch Trim Switch on the yoke will be deactivated under what circumstances?

A

If only half the switch is activated for longer than 7 seconds

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5
Q

Maual pilot trims are limited to… ?

A

3 seconds

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6
Q

The AP/TRIM DISCONNECT button on the yoke does what?

A

It disables both the HS-ACE channels while pressed. Once released the channels are active.

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7
Q

The guarded PITCH TRIM SYS 1/2 CUTOUT button accommplishes what?

A

Disables the respective HS-ACE channels.

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8
Q

Pushing the guarded FLIGHT CONTROL MODE BUTTON

A

Places the associated system into direct mode.

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9
Q

What does a white dashed box represent on the flight controls page?

A

A white dashed box is shown only for suface position greater than 50% of its deflection.

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10
Q

What does a surface line and the surface with green stripes represent on the flight controls page?

A

Deployed

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11
Q

What does an amber line, a white dashed box and an amber cross represent on the flight controls page?

A

Failed retracted

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12
Q

What does a white dashed box, surface amber stripes and amber cross represent?

A

Failed deployed.

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13
Q

If the value of the PBIT remaining time is higher or equal to _____ the value is shown in _____

A

5 , green

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14
Q

If the value of the PBIT remaining time is lower than ____ the value is shown in ____

A

lower than 5, cyan

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15
Q

The cyan pointers on the SLAT/FLAP position show what?

A

Show the commanded position

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16
Q

Tick marks at the end of the SLAT scale represent what?

A

positions at 0 and 25

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17
Q

Tick marks at the end of the FLAP sacle represent what?

A

positions at 0 and 35

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18
Q

In the case of a SLAT/FLAP jamming what indications are there?

A

There is an additional box displayed in amber, as well as the readout.

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19
Q

There are 5 tic marks on the ROLL and YAW trim indicator representing what?

A

0-50-100% each side

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20
Q

How many ACE - Actuator Control Electronics are there?

A

9

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21
Q

How many FCM’s are there?

A

4

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22
Q

How many primary ACEs are there?

A

3 Primary ACE ( P-ACE)

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23
Q

What do the P-ACE do?

A

Control the rudder and elevator surfaces

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24
Q

Each P-ACE has how many channels

A

Each P-ACE has two channels, one is active the other is standby

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25
Q

How many SF-ACEs are there? What are they for?

A

Two SF-ACEs. They are for the SLAT/FLAP

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26
Q

How many different types of ACE’s are there and what are they?

A 
4 ACEs - Actuator Control Electronics
P-ACE - Primary
SF-ACE - Slat / Flap
HS-ACE - Horizontal Stabilizer
S-ACE - Spoiler
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27
Q

How many FCM’s are there?

A

Four

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28
Q

The SF-ACEs reside within… ??

A

The FCM’s

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29
Q

What do the ACE unites do?

A

They connect the control column electronically to the respective flight control surfaces

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30
Q

What do the FCMs do?

A

Provide software-based assistance to the P-ACE and is required for normal - mode operation. Provides high - level functions such as AOA limiting to the P-ACE units

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31
Q

FCM 1 and 2 are located in?

A

MAU #1

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32
Q

FCM 3 and 4 are located in?

A

MAU #3

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33
Q

What connects the FCMs to the P-ACE?

A

The Controller Area Network Bus ( CAN BUS )

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34
Q

What are the modes of operation for the FBW system?

A

Normal Mode and Direct Mode

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35
Q

What does Normal Mode include to limit the P-ACE?

A

Takes into account airspeed, elevator control laws, auto thrust compensation, AOA, rudder airspeed gain and limiting, yaw damper, rudder authority, configuration gain compensation.

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36
Q

In Direct Mode what changes are there to the FBW system

A

The FCMs are removed from the control loop.

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37
Q

When the FCM’s are removed what mode is that and what happens?

A

Direct Mode: control limits default to fixed control laws, values set by the hardware in the P-ACE

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38
Q

If air data is lost what happens.

A

The FBW defaults to Direct Mode

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39
Q

When in Direct Mode explain how control input affects the flight controls.

A

Control Input provided by either control yoke is sent directly to the surface, bypassing the FCM.

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40
Q

What is the communication link between the P-ACE and the FCM?

A

The Controller Area Network BUS - CAN BUS

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41
Q

The IRS provides attitude and acceleration information to the … ?

A

… to the FCM’s for AOA limiting.

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42
Q

What Modes of Operation are there under Normal Mode?

A

Elevator Control Laws scheduling with airspeed
Auto-Thrust Compensation with Elevator
Rudder Airspeed Gain Scheduling and Stroke Limiting
Yaw Damper and turn coordination via the AFCS
Rudder Flight Authority
Roll Spoiler Scheduling with Airspeed and Speed Brake Deployment

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43
Q

What are some sources of information for the Flight Control Systems

A 
Smart probe and Air Data Application modules
IRS
Proximity Sensors
BCM - Brake Control Module
FADEC
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44
Q

The Electrical PBIT expires when

A

After 50 hours

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45
Q

What interrupts the Electrical PBIT

A

if any ACMP - Electric Hydraulic Pump is turned on
if the FCP switches are cycled
if AC power is interrupted

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46
Q

When is the Electrical PBIT completed

A

Automatically performed with the power up of any AC source

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47
Q

How long does the Electrical PBIT take to accomplish?

A

3 minutes

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48
Q

What does the electric PBIT accomplish?

A

Tests the FCMs, P-ACEs, and SF-ACEs for failures and out of tolerance conditions

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49
Q

What is displayed while the Electrical PBIT is in progress

A

FLT CTRL TEST IN PROG status message ( White )

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50
Q

What does the Hydraulic PBIT do?

A

Provides functional test of the flight control actuators

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51
Q

When is the Hydraulic PBIT accomplished

A

Automatically on the ground when all 3 hydraulic systems are pressurized.

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52
Q

How long does the Hydraulic PBIT take to complete

A

One minute

53
Q

What will interrupt the Hydraulic PBIT?

A

If any flight control surface is moved

54
Q

What are the conditions when the Hydraulic PBIT is not automatically completed?

A

If the temperature of the Hydraulic Reservoir is lower than 10 deg C ( 50 deg F )

55
Q

How do is the Hydraulic PBIT re-run if interrupted

A

All 3 hydraulic systems must be completely depressurized then pressurized.

56
Q

If the hydraulic reservoir temperature is lower than 10 degrees will the Hydraulic PBIT run automatically?

A

NO… unless it is expired indicated by the EICAS message: FLT CTRL BIT EXPIRED

57
Q

Where can you find the time remaining for each PBIT?

A

On the flight control page

58
Q

How many control channels are there for the elevator, rudder and horizontal stabilizer

A

There are 2 each

59
Q

Which channels are active on the elevator, rudder and horizontal stabilizer?

A

1 of 2. They alternate based on Odd-Even Day Logic to allow for even wear.

60
Q

If the Odd - Even day logic results in a different configuration, does it require a write up and can the aircraft depart?

A

No write up is required unless it is accompanied by an EICAS message. YES the aircraft can depart.

61
Q

In the case of loss of all electrical, what back up is there for the FBW system?

A

There is a DEDICATED battery charged by DC ESS 3 that provides power to keep the elevator and rudder actuarors operating for 15 minutes.

62
Q

What keeps the FBW back up battery functional?

A

There is an internal heater to insure proper temperatures and protected from powering back to the DC ESS BUS via an internal rectifier.

63
Q

Explain the FBW Pitch Control

A

Electro-Hydraulic Elevators

Electro-Mechanical Horizontal Stabilizer

64
Q

How many PCU’s are there on the Elevator

A

Total of 4 and they are independently controlled by the four P-ACE channels.

65
Q

How is the Elevator Control System effected with the loss of the FCM

A

Loss of gain scheduling as a function of airspeed, elevator thrust compensation, and AOA limiting.

66
Q

With the loss of the Elevator FCM what is lost?

A

Elevator High Level Functions as well as the AUTO PILOT

67
Q

What will cause the loss of Auto Pilot

A

In Direct Mode when the FCM is removed from the control loop

68
Q

How many PCUs on the elevator?

A

Total of 4 with the actuators on each surface alternating between active and standby every time the system is powered up.

69
Q

What causes the standby PCU to become active?

A

The loss of hydraulic supply to the other, forces the standby PCU to become active.

70
Q

What happens if there is a jam detected in the elevator?q

A

The respective elevator surface will remain fixed in that position, allowing the pilot to control the pitch with the remaining elevator.

71
Q

If the Elevator FBW system defaulted to Direct Mode how is it reset?

A

By pressing the dedicated “ELEVATORS” on the FLIGHT CONTROLS MODE panel

72
Q

What happens when the ELEVATORS button is pressed on the FLIGHT CONTROLS MODE panel?

A

All 4 FCM Elevator channels to change from Normal to Direct Mode. In addition, the active elevator channels transition to standby.

73
Q

On the horizontal stabilizer, how many actuators are there?

A

One - A single electrical mechanical actuator with 2 DC motors to drive the actuator.

74
Q

How many degrees is the elevator command limited to under the FCM guided ELEVATOR THRUST COMPENSATION FUNCTION

A

5 degrees.

75
Q

What is the ETC - Elevator Thrust Compensation OFF LOAD function.

A

For long term control, the ETC commands are off loaded to the stabilizer.

76
Q

What is the time limit of the split trim switches when activated seperately

A

7 seconds… If only one half is activated for 7 seconds, that switch is then deactivated.

77
Q

Manual trim inputs are limited to …

A

3 seconds.

78
Q

What is the Stabilizer Trim Priority Logic

A

Backup Switches
Captain
FO
FCM commands

79
Q

Is there a mechanical connection between the control column and the elevator control surfaces?

A

NO - FBW

80
Q

How many Artificial Feel Units are there?

A

2 - one for each torque tube incase a disconnect, the remaining elevator surface will retain artificial feel.

81
Q

Can the elevator disconnect mechanism be reconnected if pushed in?

A

NO

82
Q

Aileron Control is accomplished through… ?

A

Conventional cable system

83
Q

If the RAT is powering the aircraft during an electrical failure, how is the trim effected?

A

It operates at half speed.

84
Q

If there is an aileron jam on the right side, does the captain retain artificial feel?

A

Yes… the captain retains control of the left aileron and the pair #5 multi function spoilers with artificial feel

85
Q

If there is an aileron jam on the left side, what control remains.

A

The FO retains control of the right aileron with #4 multi function pair… yet WITHOUT artificial feel.

86
Q

Horizontal Stabilizer is …

A

Electro Mechanical

87
Q

What else besides the pilot’s input via the trim switches affect the control of the electro mechanical servo motor couples to the Horizontal Stabilizer Actuator - HSA

A

the FCM for autopilot trim and speed brake auto trim

88
Q

What moves the Horizontal Stabilizer

A

HS-ACE and one HSA - Horizontal Stabilizer Actuator

89
Q

What control surface are you moving with the horizontal trim switches?

A

The Forward Surface - Horizontal Stabilizer.

90
Q

How many PCU actuators are there on the rudder

A

2

91
Q

The upper Rudder PCU is commanded by who?

A

The captain commands the upper PCU

92
Q

The Lower Rudder PCU is commanded by who?

A

The FO commands the lower PCU

93
Q

In the event of electrical emergency how is the Horizontal Stabilizer effected?

A

Only the HS-ACE channel 2 is operational at half rate.

94
Q

The lateral roll system is controlled by what?

A

Conventional cable controls for the ailerons and FBW multi function spoilers.

95
Q

In the event of the captains side aileron jam, can the FO trim the ailerons?

A

NO… he loses both artificial feel and roll trim.

Why? Because the AFU is attached to the captains side of the system.

96
Q

If one aileron PCU is lost… what happens?

A

It will be disconnected and the other will provide control. yet the force authority will be halved as they share force authority. If the FCM detects this an EICAS message will be displayed.

97
Q

How many Multi Function Spoiler Panels are there?

A

6 panels numbered from inboard to outboard.
L3-4-5
R3-4-5

98
Q

In the event of Spoiler FCM failure what happens?

A

The FCM associated with the failure turns to Direct Mode. Yet the rest of the spoilers remain in Normal Mode.

99
Q

The rudder has how many PCU’s

A

2 PCUs
The upper actuator is controlled by Hydraulic 1
The lower actuator is controlled by Hydraulic 3

100
Q

The Rudder is controlled by how many P-ACE modules and how many FCM units?

A

Two independent P-ACE modules drive the upper and lower PCU’s
Four independent FCM units provide high level control such as yaw damping, turn coordination, as well as gain scheduling as a function of airspeed.

101
Q

How many Direct Modes are there in relation to YAW?

A

There are Two
Low Speed Fixed Gain
High Speed Fixed Gain

102
Q

What is the Direct Mode HIGH SPEED FIXED GAIN in YAW

A

In DIRECT MODE it is automatically selected when the slats and flaps are extended. It ensures rudder movement is limited at high speeds, providing structural protection

103
Q

What is the Direct Mode LOW SPEED FIXED GAIN in YAW

A

In DIRECT MODE it is automatically selected with the slats and flaps extended. It ensures there is enough rudder authority to control the aircraft in the approach and landing.

104
Q

If the Rudder is jammed due to a jammed PCU what happens?

A

The rudder will be hydraulically locked at the current position.

105
Q

If the Rudder pedals become jammed what happens?

A

The rudder remains active and will be actuated by high level functions ( yaw damping and turn coordination )

106
Q

What are the high level functions for YAW

A

Yaw damping and turn coordination

107
Q

How many slat surfaces are there?

A

Four per wing - total of Eight

108
Q

How many SF-ACES are used to control the Slats and Flsps

A

Two

109
Q

The SF-ACES command what??

A

Power Drive Units - PDUs that are electrically operated

110
Q

How many flap actuators are there per side

A

Four flap actuators per side

111
Q

Do the SLATS operate normally in the case of a FLAP FAIL Caution EICAS Message?

A

Yes

112
Q

Do the FLAPS operate normally in the case of a SLAT FAIL Caution EICAS Message?

A

Yes

113
Q

Explain the Higher Functions in Normal Mode for the Rudder

A

With increasing airspeed, rudder gain is reduced by the FCM in order to compensate for the rudder effectiveness and maintain structural protection.
Also there is Yaw Damping and Turn Coordination.

114
Q

Do you lose yaw damping if pushing the RUDDER button and going into Direct Mode for Rudder?

A

…. ?? … I don’t know the answer to this question

115
Q

What are the 7 NORMAL MODES of operation

A 
Elevator Control Laws
Auto Thrust Compensation
AOA Limiting
Rudder Airspeed Gain
Yaw Damper and Turn Coordination
Rudder Flight Authority
Roll Spoiler Scheduling with AS and Speed Brakes
Configuration Change Compensation
116
Q

Can you move the Flaps / Slats when you have a FLAP FAIL or SLAT FAIL message on the EICAS

A

NO… the system is shut down as there is a differing movement of a panel

117
Q

What drives the flaps?

A

PDUs - Power Drive Units

118
Q

Are the flaps electric or hydraulic?

A

Electric via PDUs commanded by the SF-ACE

119
Q

What does the EICAS message SLAT-FLAP LEVER DISAG mean?

A

If the respective surface has not reached the selected position.

120
Q

With the EICAS message SLAT-FLAP LEVER DISAG what happens to the SLAT - FLAP system?

A

The other system can still be operated normally.

121
Q

What is going on when you have both
FLAP / SLAT FAIL
SLAT / FLAP LEVER DISAG

A

Strike Protection. Can reselect flaps / slats back to the previous position and try again… it can then be commanded in both directions up to 2 more times. After that, if a excessive load is detected, the affected surface is de-energized.

122
Q

If on emergency power via the RAT are the slats and flaps available?

A

YES… yet only at half speed
AND
The SF-ACE prevents deployment of slats and flaps beyond position THREE

123
Q

On the ground, when are the Multi Function Spoilers deployed?

A

Weight On Wheels
Wheel Speed is above 45 KT or Airspeed is above 60 KIAS
Thrust Lever Angle is below 26 degrees

124
Q

After landing the Multi-Function Spoilers will retract when?

A

Wheel speed is below 45 KTS for 5 seconds

If the throttles are moved beyond 35 TLA

125
Q

Do the ground spoilers deploy on a bounce landing?

A

The on ground signal is held for 5 seconds after the “In Air” WOW signal is sensed. If the TLA is greater than 24 degrees, the ground spoilers are retracted

126
Q

What is the multi function spoiler deploy limit on the ground and in flight

A

Full deflection on the ground 40 degrees

In flight limited to 30 degrees

127
Q

Are Speed Brakes available in Direct Mode

A

NO

128
Q

If Speed Brakes are extended on approach, when will they retract automatically?

A

When Flaps 2 selected
Below 180 KIAS - won’t deploy either
When the TLA is 70 degrees

129
Q

AOM and Notes Complete

A

Complete

ERJ 175 (28 decks)

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