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G650 > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

The 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 the control surfaces to best achieve what the pilot wants.

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2
Q

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

A

New level of enhanced flying qualities, enhanced stability, greater protection through the entire flight envelope, and continuous monitoring

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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).

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4
Q

Name the secondary flight controls.

A

Horizontal stabilizer, flaps, and inboard spoilers

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5
Q

How is pitch trim accomplished?

A

From either of the yoke mounted switches or the center console mounted BACKUP PITCH trim switch

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6
Q

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

A

It disengages the autopilot and stops runaway trim in all three axes.

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7
Q

What’s the function of the FLT CTRL RESET switch?

A

Used to reset flight control computers and control surface actuators when directed by a checklist.

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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

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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

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10
Q

What’s the difference between inboard, midboard, and outboard spoiler panel actuators?

A

Each has a single REU and single actuator but outboard spoilers have EBHA’s

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11
Q

What are control laws?

A

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

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12
Q

How many computers control the fly-

by-wire flight control?

A

Three (3) computers: two (2) Flight Control Computers for normal operation and a Backup Flight Control Unit in case both FCCs fail.

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13
Q

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

A

One. This is because each channel contains two lanes: one command lane and one monitor lane.

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14
Q

What’s the purpose of the backup flight control unit (BFCU)?

A

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

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15
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 the flight.

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16
Q

Describe the electric backup hydraulic actuator (EBHA).

A

It’s a special actuator with a self contained electric motor/pump and hydraulic reservoir.

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17
Q

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

A

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

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18
Q

Describe the AOA limiting feature.

A

In this mode, full aft column input commands the maximum nose angle-of-attack of 0.96.

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19
Q

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

A

High speed protection

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20
Q

What’s the auto-retract feature?

A

It retracts the speed brakes at high power settings

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21
Q

Name the four (4) flight control modes.

A

Normal, alternate, direct, and backup

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22
Q

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

A

The normal mode requires air data(multifunction probes) and inertial data.The HSCU must also be capable of receiving FCC commands on one of its two (2) channels.

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23
Q

When would the 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.

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24
Q

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

A

The flight control system reverts to the direct mode

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25
Q

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

A

Backup Flight Control Unit (BFCU) will activate to provide a “get home” capability

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26
Q

Can you dispatch with the BFCU inoperative?

A

Yes; may be inoperative provided BFCU CB is pulled and collared and repairs made within one flight day.

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27
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

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28
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

29
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.

30
Q

Describe how the flight control system operates in the 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

31
Q

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

A

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

32
Q

What functions with the ailerons to improve roll response?

A

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

33
Q

Name the two types of flight control actuators.

A

Hydraulic Actuator (HA) and Electric Backup Hydraulic Actuator (EBHA)

34
Q

Describe HA operation.

A

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

35
Q

What’s the function of the REU?

A

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

36
Q

What additional features do the EBHA’s have?

A

Able to operate in an electric backup mode if the normal source of hydraulic pressure is lost or operate in MCE direct control mode for failure of both REU’s

37
Q

Describe EB operation.

A

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

38
Q

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

A

The EBHA REU normally controls the MCE when the EBHA is in EB (electric backup) operation. The MCE controls operation of the backup electric motor. For REU failure, the MCE can directly control the EBHA.

39
Q

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

A

Green for active/healthy and amber for inactive/unhealthy

40
Q

Which actuator has an electric backup mode?

A

EBHA

41
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 the EBHA is in electric backup. This mode is designed to operate when there’s a complete loss of hydraulics to a critical flight control surface.

42
Q

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

A

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

43
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.

44
Q

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

A

The roll trim switches bypass the control columns and send signals directly to the FCC’s. The only downside to this is the lack of corresponding control wheel movement.

45
Q

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

A

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

46
Q

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

A

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

47
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.

48
Q

Under what condition would the BACKUP PITCH switch have to be used?

A

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

49
Q

Why do pitch trim switches have a split design?

A

It prevents inadvertent activation and minimizes the chance of a runaway due to a stuck or jammed pitch trim switch, or electrical fault.

50
Q

What pilot action is required in the unlikely event that the 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.

51
Q

What happens with selection of the AUTO CENTER switch?

A

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

52
Q

What component is responsible for moving the stabilizer surface?

A

The Horizontal Stabilizer Trim Actuator (HSTA), which is a dual electric motor

53
Q

Describe HSTS operation in the primary or normal mode.

A

The FCC’s provide rate commands to the Horizontal Stabilizer Control Unit (HSCU).

54
Q

True/False: Standby mode of the 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.

55
Q

When is the backup mode of the 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, the BACKUP PITCH switch on the pedestal is used to move the horizontal stabilizer at a constant, minimum rate.

56
Q

What is the elevator off-load feature?

A

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

57
Q

Describe how the flaps operate.

A

Manually operated, electrically controlled, hydraulically powered, and mechanically actuated

58
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

59
Q

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

A

A load limiter device prevents the flaps from extending

60
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)

61
Q

What is maximum spoiler deflection?

A

55°

62
Q

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

A

30° in-flight or 55° on ground with flap handle not up

63
Q

What indications would you get during speed brake extension?

A

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

64
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.

65
Q

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

A

The speed brakes automatically retract although the speed brake handle remains in the extended position, and an amber Speed Brake Auto Retract message is displayed.

66
Q

What function do the 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 the ground.

67
Q

What are the requirements for ground spoiler deployment?

A

The switch must be ARMED, power levers must be at idle, and you must have either wheel spin up greater than 47 kts, or weight on wheels

68
Q

What happens when the GPWS/GND SPLR FLAP ORIDE switch is selected to ON?

A

Automatic ground spoiler deployment will occur with wheel spin up if flaps are less than 22° and all other parameters are satisfied. GPWS voice alarm, “TOO LOW, FLAPS”, is inhibited.

G650 (20 decks)

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