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G650 Intial > Flight Controls > Flashcards

Flight Controls Flashcards

(66 cards)

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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
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?
Gain | Ref: AOM 2A
26
The normal mode has five (5) primary operating sub modes. What are they?
On ground, Takeoff & landing, Cruise, AOA limiting, and High speed protection Ref: AOM 2A
27
What sub mode is the flight control system in when flying with the gear and/or flap handle down and autopilot disengaged?
Takeoff & landing mode. Here’s a clue: you’ll see a number in the pitch trim digital readout. Ref: AOM 2A
28
Describe how the flight control system operates in alternate mode.
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
How many sets of gains are associated with degraded flight control modes?
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
What functions with the ailerons to improve roll response?
Mid and outboard spoiler panels extend to a maximum of 55° | Ref: AOM 2A
31
Name the two types of flight control actuators.
``` Hydraulic Actuator (HA) and Electric Backup Hydraulic Actuator (EBHA) Ref: AOM 2A ```
32
Describe HA operation
It’s controlled electrically by its Remote Electronics Unit (REU) and uses hydraulic power to move the control surface. Ref: AOM 2A
33
What’s the function of REU?
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
What additional features do EBHA’s have?
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
Describe EB operation.
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
What’s the purpose of Motor Control Electronics (MCE)?
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
What does the color of HA or EBHA status border indicate on flight control synoptic page?
Green for active/healthy and amber for inactive/unhealthy Ref: AOM 2A
38
Which actuator has an electric backup mode?
EBHA | Ref: AOM 2A
39
When does the EB mode function?
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
What action is required for a jam in cockpit roll controls?
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
What pilot action is required for an aileron surface or spoiler surface jam?
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
What happens when ROLL MOTOR CONTROL switch is selected to OFF?
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
What’s the primary purpose of ROLL MOTOR CONTROL switch?
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
What action is required for a jam in cockpit elevator controls?
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
What pilot action is required for an elevator surface jam?
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
Under what condition would BACKUP PITCH switch have to be | used?
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
Why do pitch trim switches have a split design?
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
What pilot action is required in the unlikely event that rudder pedals become mechanically jammed?
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
What happens with selection of AUTO CENTER switch?
A signal is sent to FCC’s which then electrically direct the rudder trim actuation system to center the rudder. Ref: AOM 2A
50
What component is responsible for moving the stabilizer surface?
Horizontal Stabilizer Trim Actuator (HSTA), which is a dual electric motor Ref: AOM 2A
51
Describe HSTS operation in primary or normal mode.
FCC’s provide rate commands to Horizontal Stabilizer Control Unit (HSCU). Ref: AOM 2A
52
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).
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
When is backup mode of HSTS | entered (indicated by an amber Stab Primary Trim Fail CAS message)?
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
What is the elevator off-load feature?
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
Describe how the flaps operate.
Manually operated, electrically controlled, hydraulically powered, and mechanically actuated Ref: AOM 2A
56
What happens if there’s any sort of malfunction (e.g., flap jam, asymmetry, runaway, etc.) during flap operation?
Flap motion is interrupted Ref: AOM 2A
57
What happens if you attempt to extend the flaps at high rate of speed?
A load limiter device prevents the flaps from extending | Ref: AOM 2A
58
When do the spoilers function?
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
What is maximum spoiler deflection?
55°
60
What’s the maximum deflection with full speed brake extension?
30° in-flight or 55° on ground with flap handle not up Ref: AOM 2A P
61
What indications would you get during speed brake extension?
When moved left and aft out of forward detent, a light illuminates inside handle and a blue Speed Brake Extended message displays.
62
How would the indications change during level off?
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
What happens if speed brakes are extended and pilot advances throttles to a high power setting?
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
What function do ground spoilers perform on touchdown or during rejected takeoff?
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
What are the requirements for ground spoiler deployment?
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
What happens when GPWS/GND SPLR FLAP ORIDE switch is | selected to ON?
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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