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G650 Intial > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

G650 uses fly-by-wire technology.
How does this work?

A

Pilot inputs are read by a computer that in turn
decides how to move control surfaces to best achieve
what the pilot wants.
Ref: AOM 2A

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2
Q

Describe some benefits of this fly-by-
wire system.

A

Enhanced flying qualities, enhanced stability, greater
protection through entire flight envelope, and
continuous monitoring
Ref: AOM 2A

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3
Q

Name the primary flight controls.

A

Ailerons, elevators, rudder, and multifunction spoilers
(i.e., mid-board and outboard spoiler panels).
Ref: AOM 2A

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4
Q

Name the secondary flight controls.

A

Horizontal stabilizer, flaps, and inboard spoilers
Ref: AOM 2A

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5
Q

How is pitch trim accomplished

A

From either yoke mounted switch or center console
mounted BACKUP PITCH trim switch

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6
Q

What’s the purpose of A/P DISC
switch?

A

It disengages the autopilot and stops runaway trim in
all three axes.
Ref: AOM 2A

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7
Q

What’s the function of FLT CTRL
RESET switch?

A

Used to reset flight control computers and
REUs/control surface actuators when directed by a
checklist.
Ref: AOM 2A

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8
Q

What effect does loss of one
hydraulic system have on the flight
controls?

A

Loss of one spoiler pair
Airspeed limitation 285/.90
Ref: AOM 2A

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9
Q

What is common among primary
flight control surfaces?

A

They have two (2) actuators and two (2) REU’s for
each primary flight control surface except outboard
spoilers. One of the actuators is an EBHA
Ref: AOM 2A

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10
Q

What are control laws?

A

Software in the FCC’s that translate electrical
commands from cockpit control sensors and aircraft
motion sensors (inertial/air data) into flight control
surface commands
Ref: AOM 2A

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11
Q

How many computers control the fly-
by-wire flight control system?

A

Three (3) computers: two (2) flight control computers
for normal operation and Backup Flight Control Unit
in case both flight control computers fail.
Ref: AOM 2A

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12
Q

What’s the minimum number of FCC
channels that can command all flight
control surfaces on the aircraft.

A

One

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13
Q

What’s the purpose of Backup Flight
Control Unit (BFCU)?

A

It’s designed to provide what Gulfstream calls “get
home capability” if both primary FCC’s fail.
Ref: AOM 2A

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14
Q

What happens once the BFCU
becomes active?

A

It communicates directly with EBHA remote
electronics units (REU’s) on separate backup data
buses, and is active for the duration of flight.
Ref: AOM 2A

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15
Q

Describe the Electric Backup
Hydraulic Actuator (EBHA)

A

It’s a special actuator with self contained electric
motor/pump and hydraulic reservoir.
Ref: AOM 2A

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16
Q

What type of sensor input is provided
to FCC’s?

A

Input from IRS’s, AHRS, ADS’s and radio altimeters

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17
Q

Describe the AOA limiting feature.

A

In this mode, full aft column input commands the
maximum nose angle-of-attack of 0.96.
Ref: AOM 2A

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18
Q

Which mode protects from surface
flutter and separation that would
occur greater than Vdive speed?

A

High speed protection
Ref: AOM 2A

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19
Q

What’s the auto-retract feature?

A

It retracts speed brakes at high power settings
Ref: AOM 2A

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20
Q

Name the four (4) flight control
modes.

A

Normal, alternate, direct, and backup
Ref: AOM 2A

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21
Q

Describe requirements for the flight
control mode to remain in normal.

A

Normal mode requires air data (multifunction probes)
and inertial data. HSCU must also be capable of
receiving FCC commands on one of its two (2)
channels.
Ref: AOM 2A

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22
Q

When would flight control mode
change from normal to alternate?

A

You need to lose multiple air data or inertial sensors
for this to occur. It may also drop into alternate mode
if FCC receives a message that HSCU has reverted to
backup mode.
Ref: AOM 2A

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23
Q

What happens if all four (4) FCC
channels are invalid?

A

Flight control system reverts to direct mode
Ref: AOM 2A

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24
Q

What happens if all four (4) FCC
channels are unable to compute the
control law?

A

Backup Flight Control Unit (BFCU) activates to
provide “get home” capability
Ref: AOM 2A

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25
Q

What term is used to describe the
amplification, attenuation, boosting,
or magnification that’s applied to the
forward signal to achieve the desired
aircraft response?

A

Gain

Ref: AOM 2A

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26
Q

The normal mode has five (5)
primary operating sub modes. What
are they?

A

On ground, Takeoff & landing, Cruise, AOA
limiting, and High speed protection
Ref: AOM 2A

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27
Q

What sub mode is the flight control
system in when flying with the gear
and/or flap handle down and
autopilot disengaged?

A

Takeoff & landing mode. Here’s a clue: you’ll see a
number in the pitch trim digital readout.
Ref: AOM 2A

28
Q

Describe how the flight control
system operates in alternate mode.

A

Pitch, roll, and rudder pedal inputs are multiplied by a
set of fixed gains to command the elevator, ailerons,
roll spoilers, and rudder
Ref: AOM 2A

29
Q

How many sets of gains are
associated with degraded flight
control modes?

A

Two: one set of generally smaller numbers used when
flap handle and gear handle are up (and aircraft is
presumed to be traveling at higher speed – 340 kts),
and a set of generally larger numbers that are used if
flap handle or gear handle is down (and aircraft is
presumed to be traveling slower – 250 kts).
Ref: AOM 2A

30
Q

What functions with the ailerons to
improve roll response?

A

Mid and outboard spoiler panels extend to a
maximum of 55°

Ref: AOM 2A

31
Q

Name the two types of flight control
actuators.

A 
Hydraulic Actuator (HA) and Electric Backup 
Hydraulic Actuator (EBHA) 
Ref: AOM 2A
32
Q

Describe HA operation

A

It’s controlled electrically by its Remote Electronics
Unit (REU) and uses hydraulic power to move the
control surface.
Ref: AOM 2A

33
Q

What’s the function of REU?

A

It’s mounted on associated hydraulic manifold,
averages FCC1 and FCC2 commands and electrically
controls a valve in hydraulic manifold to control
actuator position to match FCC commands.
Ref: AOM 2A

34
Q

What additional features do EBHA’s
have?

A

Able to operate in electric backup mode if normal
source of hydraulic pressure is lost or operate in MCE
direct control mode for failure of both REU’s
Ref: AOM 2A

35
Q

Describe EB operation.

A

Within EB hydraulic manifold, an electric motor
turns a hydraulic pump that draws fluid from self-
contained reservoir: it acts like third hydraulic
system. The fluid is trapped from normal source of
hydraulics.
Ref: AOM 2A

36
Q

What’s the purpose of Motor Control
Electronics (MCE)?

A

EBHA REU normally controls MCE when EBHA is
in EB (electric backup) operation and MCE controls
operation of backup electric motor. For REU failure,
MCE can directly control the EBHA.
Ref: AOM 2A

37
Q

What does the color of HA or EBHA status border indicate on flight
control synoptic page?

A

Green for active/healthy and amber for inactive/unhealthy
Ref: AOM 2A

38
Q

Which actuator has an electric
backup mode?

A

EBHA

Ref: AOM 2A

39
Q

When does the EB mode function?

A

Only if both HA and EBHA systems cannot function
in their normal hydraulic mode. There will never be
mixed operation where an HA is operating in its
normal hydraulic mode, and EBHA is in electric
backup. This mode is designed to operate when
there’s a complete loss of hydraulics to critical flight
control surface.
Ref: AOM 2A

40
Q

What action is required for a jam in
cockpit roll controls?

A

A force-based roll override device under cockpit floor
is provided to overpower and isolate the jammed
portion of roll controls. Activation of roll override
device is accomplished by applying sufficient force
(approximately 10 lbs) to roll control wheels to
overcome breakout force of roll override device. Roll
control is recovered by using unrestricted side of roll
controls. Important note: sensor input from roll
controls is averaged.
Ref: AOM 2A

41
Q

What pilot action is required for an
aileron surface or spoiler surface
jam?

A

Both pilot and copilot roll control wheels remain
available to control the unrestricted aileron and
spoiler surfaces: fly normally and trim, and refer to
QRH.
Ref: AOM 2A

42
Q

What happens when ROLL MOTOR
CONTROL switch is selected to
OFF?

A

Roll trim switches bypass control columns and send
signals directly to FCC’s. The only downside to this
is lack of corresponding control wheel movement.
Ref: AOM 2A

43
Q

What’s the primary purpose of ROLL
MOTOR CONTROL switch?

A

To remove electrical power from Roll Control Motor
(under the floor) in the unlikely event of Roll Motor
Control runaway or mechanical jam, and at the same
time enable direct trimming of ailerons via the
FCC’s.
Ref: AOM 2A

44
Q

What action is required for a jam in
cockpit elevator controls?

A

A force-based elevator override device under cockpit
floor is provided to isolate the jammed portion of
elevator controls. Activation of this device is
accomplished by applying sufficient force
(approximately 40 lbs) to elevator control columns to
overcome breakout force of elevator override device. Elevator control is recovered by using unrestricted
side of the elevator controls.
Ref: AOM 2A

45
Q

What pilot action is required for an
elevator surface jam?

A

No pilot action is required since both pilot and copilot
elevator control columns remain available to control
the unrestricted elevator surface.
Ref: AOM 2A

46
Q

Under what condition would
BACKUP PITCH switch have to be

used?

A

Loss of input from both FCC’s (i.e., backup mode). If
this were to occur, BACKUP PITCH switch bypasses
FCC’s and controls the horizontal stabilizer directly
at a constant, minimum rate.
Ref: AOM 2A

47
Q

Why do pitch trim switches have a
split design?

A

It prevents inadvertent activation and minimizes the
chance of runaway due to stuck or jammed pitch trim
switch, or electrical fault.
Ref: AOM 2A

48
Q

What pilot action is required in the
unlikely event that rudder pedals
become mechanically jammed?

A

The pilots would have to use other flight controls or
differential power to control the aircraft: there is no
breakout capability.
Ref: AOM 2A

49
Q

What happens with selection of
AUTO CENTER switch?

A

A signal is sent to FCC’s which then electrically
direct the rudder trim actuation system to center the
rudder.
Ref: AOM 2A

50
Q

What component is responsible for
moving the stabilizer surface?

A

Horizontal Stabilizer Trim Actuator (HSTA), which
is a dual electric motor
Ref: AOM 2A

51
Q

Describe HSTS operation in primary
or normal mode.

A

FCC’s provide rate commands to Horizontal
Stabilizer Control Unit (HSCU).
Ref: AOM 2A

52
Q

True/False: Standby mode of
Horizontal Stab, indicated by an
amber Stabilizer Failed CAS
message, occurs when you lose the
ability to trim the stab (e.g., dual
motor failure, jam or dual HSCU
channel failure).

A

True: in standby, you’re trimming elevators as
opposed to horizontal stab and there’s no off-load
feature. Don’t use backup pitch trim switch.

53
Q

When is backup mode of HSTS

entered (indicated by an amber Stab Primary Trim Fail CAS message)?

A

With loss of input from both FCC’s (i.e., backup
mode). In this mode, BACKUP PITCH switch on pedestal is used to move the horizontal stabilizer at a
constant, minimum rate.
Ref: AOM 2A

54
Q

What is the elevator off-load feature?

A

Once elevator deflection exceeds a preset value for
predetermined amount of time, horizontal stabilizer
and elevators move simultaneously: horizontal stab
moves to the new trim position as elevators move to
“faired” position (0 degrees relative to horizontal stab
surface). It’s controlled or commanded from FCC’s to
reduce elevator deflection.
Ref: AOM 2A

55
Q

Describe how the flaps operate.

A

Manually operated, electrically controlled,
hydraulically powered, and mechanically actuated
Ref: AOM 2A

56
Q

What happens if there’s any sort of
malfunction (e.g., flap jam,
asymmetry, runaway, etc.) during
flap operation?

A

Flap motion is interrupted
Ref: AOM 2A

57
Q

What happens if you attempt to
extend the flaps at high rate of speed?

A

A load limiter device prevents the flaps from
extending

Ref: AOM 2A

58
Q

When do the spoilers function?

A

Six spoiler panels (three on each wing) operate as
speed brakes/air brakes and ground spoilers; four
operate as flight spoilers (i.e., two outboard)
Ref: AOM 2A

59
Q

What is maximum spoiler deflection?

A

55°

60
Q

What’s the maximum deflection with
full speed brake extension?

A

30° in-flight or 55° on ground with flap handle not up
Ref: AOM 2A
P

61
Q

What indications would you get
during speed brake extension?

A

When moved left and aft out of forward detent, a
light illuminates inside handle and a blue Speed
Brake Extended message displays.

62
Q

How would the indications change
during level off?

A

As power is increased during level off, the blue Speed
Brake Extended message changes to amber and you get the associated two bong caution chime.
Ref: AOM 2A

63
Q

What happens if speed brakes are
extended and pilot advances throttles
to a high power setting?

A

Speed brakes automatically retract although speed
brake handle remains in extended position, and an
amber Speed Brake Auto Retract message displays.
Ref: AOM 2A

64
Q

What function do ground spoilers
perform on touchdown or during
rejected takeoff?

A

They provide a method for full and automatic
deployment of all spoiler panels in order to reduce lift
and increase braking effectiveness on ground.
Ref: AOM 2A

65
Q

What are the requirements for ground
spoiler deployment?

A

Switch must be ARMED, power levers must be at
idle, and you must have either wheel spin up > 47 kts,
or weight on wheels
Ref: AOM 2A

66
Q

What happens when GPWS/GND
SPLR FLAP ORIDE switch is

selected to ON?

A

Automatic ground spoiler deployment occurs with
wheel spin up if flaps < 22° and all other parameters
are satisfied. GPWS voice alarm, “TOO LOW,
FLAPS”, is inhibited.
Ref: AOM 2A

G650 Intial (17 decks)

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