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E170 Aircraft Systems Manual > Chapter 8: Flight Controls > Flashcards

Chapter 8: Flight Controls Flashcards

1
Q

Primary Flight Controls

A
  • Ailerons
  • Multi-function spoilers (used for roll control)
  • Elevators
  • Rudder
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2
Q

Secondary Flight Controls

A
  • Horizontal Stabilizer
  • Flaps and Slats
  • Multi-function spoilers (used as speed brakes)
  • Ground spoilers
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3
Q

Fly-by-wire Control Surfaces

A

Everything but the ailerons

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4
Q

Pitch Trim Switch Limits

A
  • Both sides must be pressed to actuate
  • If only half is pressed for more than 5 seconds, switch is disabled
  • Movement limited to 3 seconds
  • “PITCH TRIM FAIL” EICAS message if AP/TRIM DISC button held for more than 11 seconds
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5
Q

Slat/Flap Positions vs. Lever Position

A 
Lever    Slat    Flap
0           0        0
1            15       5
2           15       10
3           15       20
4           25      20
5           25      20
Full       25      35
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6
Q

PITCH TRIM SYS 1(2) CUTOUT Button

A

(1) : De-activates HS-ACE channel 1 and the PITCH TRIM DISC function of the CA’s AP/TRIM DISC button
(2) : De-activates HS-ACE channel 2 and the PITCH TRIM DISC function of the FO’s AP/TRIM DISC button

Can be cycled to reactivate a disabled trim switch

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7
Q

Fly-by-Wire Components

A
  • Three (3) Primary ACEs (P-ACE)
  • Two (2) Slat/Flap ACEs (SF-ACE)
  • One (1) Horizontal Stabilizer ACE (HS-ACE)
  • Three (3) Spoiler ACEs (S-ACE)
  • Four (4) Flight Control Modules (FCM)
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8
Q

Actuator Control Electronics (ACE)

A

Connect flight control electronically to the control surface, providing direct analog control

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9
Q

Primary Control Electronics (P-ACE)

A

Active-Standby configuration

Three (3) total, Two (2) in Forward E-Bay, one (1) in aft E-Bay

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10
Q

Flat/Flap Actuator Control Electronics (SF-ACE)

A

Each SF-ACE has two channels, one for flaps, one for slats

Two (2) units, middle E-Bay

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11
Q

Horizontal Stabilizer Actuator Control Electronics (HS-ACE)

A

One (1) unit, two (2) channels in active/standby configuration, changes daily
Installed in aft E-Bay

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12
Q

Spoiler Actuation Control Electronics (S-ACE)

A

Three (3) S-ACEs, reside in FCMs 1, 3, and 4

Each S-ACE controls a MF-spoiler pair

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13
Q

Flight Control Modules

A

Four (4) Flight Control Modules.
FCM 1 and 2 are located in MAU 1
FCM 3 and 4 are located in MAU 3

Provide software-based assistance to P-ACEs through the CAN BUS

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14
Q

Higher Level Functions

A
  • Elevator gain w/ airspeed
  • Auto-thrust compensation with elevator
  • AOA limiting with elevator offset
  • Rudder gain w/ airspeed and stroke limiting
  • Yaw damper and turn coordination
  • Rudder flight authority
  • Roll Spoiler gain w/ airspeed
  • Configuration change compensation with horizontal stabilizer due to speed brake actuation
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15
Q

CAN BUS and ASCB

A 
CAN BUS (Controller Area Network)
-Provides communication between FCMs and P-ACEs

ASCB (Avionics Standard Communications Bus)
-Provides data exchange between FCMs and other avionics components

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16
Q

Electrical PBIT

A
  • Initiated automatically after being powered by an AC source
  • Takes 3 minutes to complete
  • Interrupted if a hydraulic pump is turned on, AC power is interrupted, or FCP switches are cycled
17
Q

Hydraulic PBIT

A
  • Runs when all 3 hydraulic systems are pressurized
  • Takes 1 minute
  • Cancelled if flight controls are moved or hydraulic pumps turned off
18
Q

Fly By Wire (FBW) Backup Battery

A
  • Keeps the proper number of elevator and rudder actuators operating for at least 15 minutes
  • Lead acid battery charged by DC ESS BUS 3
19
Q

Elevator Control

A
  • Two (2) PCUs on each elevator, active-standby configuration
  • Two (2) LVDTs on each control column, providing redundant analog signal to on-side P-ACE channels
  • Two (2) artificial feel units, pre-loaded spring attached to each torque tube

L,OB Elevator Hyd 1 P-ACE 1-1 FCM 1A, 4B
L,IB Elevator Hyd 2 P-ACE 2-1 FCM 2A, 3B
R,IB Elevator Hyd 2 P-ACE 2-2 FCM 2B, 3A
R,OB Elevator Hyd 3 P-ACE 3-1 FCM 1B, 4A

20
Q

Horizontal Stabilizer Control

A
  • One (1) dual channel HS-ACE, active-standby configuration
  • Two (2) DC motors in active/standby configuration
  • One (1) Horizontal Stabilizer Actuator (HSA)

HS-ACE input priority:

- Backup Trim Switch
- CA Trim Switch
- FO Trim Switch
- FCM
  • Will ignore trim up commands if stick shaker is activated
  • Only HS-ACE Channel 2 is active during electrical emergency at low rate
  • Loss of FCM data => low rate operation
21
Q

Roll Control

A
  • Conventional cable system
  • Two (2) PCUs per aileron, load-sharing
  • Hydraulic system 2 powers inboard PCUs
  • Hydraulic system 3 powers outboard PCUs
  • CA commands MF-spoilers L5, R5
  • FO commands MF-spoilers L4, R4
  • Artificial feel unit on CA’s side
22
Q

Multi-Function Spoiler Control (Roll)

A
  • Normal Mode: Spoiler deflection is reduced with increasing airspeed
  • Direct Mode: If FCM/S-ACE failure, only the affected spoilers revert to direct mode
  • Hydraulic System 1 powers L3/R3 and L4/R4
  • Hydraulic System 2 powers L5/R5
23
Q

Rudder Control

A
  • Two PCUs, active-standby configuration, (Odd-Even Day)
  • CA controls upper PCU, FO controls lower PCU
  • LVDT’s from rudder pedals send analog signal to respective P-ACE

Lower Rudder Hyd 3 P-ACE 3-2
Upper Rudder Hyd 1 P-ACE 1-2

  • Direct Mode: 1 of 2 Fixed Gain’s
    • Low Speed: Flaps extended, maximum authority
    • High Speed: Flaps retracted, structural protection
24
Q

Slat/Flap Control

A
  • Slat/Flap lever sends signal to both SF-ACEs
  • Channel 1 controls flaps, channel 2 controls slats
  • Slat PDU powers all 8 slat panels via torque tubes (4 panels per side)
  • Flap PDU powers all 8 flap actuators (4 actuators per side)
25
Q

Slat/Flap Protections/Interlocks

A
  • Skew Protection
  • Strike Protection
  • RAT Interlock
  • Slat/Flap Failure Interlock
26
Q

Slat/Flap Skew Protection

A

Skew sensors monitor differential movement of neighboring panels. If movement exceeds acceptable limits, SF-ACE shuts down the flap (slat) system.

27
Q

Slat/Flap Strike Protection

A
  • SF-ACE monitors PDU for excessive load and stops the PDU from moving further in the selected direction
  • Can be returned to previously selected position
  • SF-ACE allows two additional attempts to select desired position before cutting power in both directions
28
Q

Slat/Flap w/ RAT Deployed

A
  • Operate at half-speed

- Limited to position 3

29
Q

Slat/Flap Failure Interlock

A
  • Ignores invalid slat/flap combinations in the event of a slat/flap failure
  • (Flaps cannot be extended beyond 10 degrees with slats less than 15 degrees)
  • Only provides protection in-flight
30
Q

Spoiler Ground Operation

A 
MF Spoilers 40 degrees and Ground Spoilers 60 degrees when:
    -WOW
    -Wheel speed > 45 kt or KIAS > 60 kt
    -TLA < 26 degrees
Retract when:
    -Wheel speed < 45 kt for 5 seconds
    -TLA > 35 degrees

Bounced Landing:
-FCM “holds” WOW for 5 seconds unless TLA > 24 degrees

*Ground spoilers not available in direct mode

31
Q

Spoiler In-Flight Operation (speedbrakes)

A
  • Speed brakes use MF spoilers up to 30 degrees
  • Automatically retract if flaps > 1, KIAS < 180, or TLA > 70 degrees

*Not available in direct mode

E170 Aircraft Systems Manual (13 decks)

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