Flight Controls Flashcards by JJ Tsunoda

In normal operation, most A330 flight controls are:

a. electrically controlled and hydraulically actuated

b. electrically controlled with mechanical back-up control and hydraulically actuated

c. electrically controlled and hydraulically actuated with mechanical reversion capability

a. electrically controlled and hydraulically actuated

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All A330 flight controls are actuated by hydraulic servos which are controlled by computers:

a. or cables

b. but the stabilizer and rudder trim may also be controlled by cables

c. but the stabilizer and rudder servos may also be controlled by cables

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The side stick inputs results in adjusting:

a. the pitch and roll only

b. the pitch, roll and yaw (for turn coordination)

c. the elevators, ailerons and nosewheel steering (during ground operation)

b. the pitch, roll and yaw ( for turn coordination)

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Pitch control is provided by:

a. two independent elevators and a Trimmable Horizontal Stabilizer

b. Two inter-connected elevators and a Trimmable Horizontal Stabilizer

c. Two inter-connected elevators with trim tabs and a Trimmable Horizontal Stabilizer

a. two independent elevators and a Trimmable Horizontal Stabilizer

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The ailerons are each actuated by:

a. Two hydraulic servos, each powered by one of two hydraulic systems

b. Two hydraulic servos, each powered by one of three hydraulic systems

c. Three hydraulic servos, each powered by one of three hydraulic systems

b. Two hydraulic servos, each powered by one of three hydraulic systems

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The speedbrake surfaces are:

a. spoilers 2 through 4

b. spoilers 2 through 5

c. spoilers 1 through 6

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The autopilot function is lost in case of:

a. PRIM 1 + 2 failure with SEC 1 + 2 available

b. PRIM 1 and 2 SEC 1 + 2 failure

c. PRIM 1 + 2 + 3 failure with Sec 1 + 2 available

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Each PRIM provides:

a. Normal control laws and characteristics speed computations only

b. Normal, Alternate, Direct Laws, speed brakes and ground spoilers control logic, characteristics speed computations

c. Normal and alternate laws only, speed brakes and ground spoilers control logic

b. Normal, Alternate, Direct Laws, speed brakes and ground spoilers control logic, characteristics speed computations

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Each SEC provides at least:

a. Direct control laws, rudder trim, yaw damper, rudder and rudder pedals travel limits

b. Direct control laws, speed brakes and ground spoilers control logic

c. Alternate control laws, characteristic speeds computation

a. Direct control laws, rudder trim, yaw damper, rudder and rudder pedals travel limits

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For elevators control, each servo jack has:

a. 2 control modes: active and damping

b. 2 control modes: active and centering

c. 3 control modes: active, damping and centering

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On one control surface if an active servo jack fails:

a. the related surface is lost

b. the damped servo jack on the same surface becomes automatically active

c. the surface deflection is reduced

b. the damped servo jack on the same surface becomes automatically active

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Normal pitch control uses:

a. PRIM 1, the elevator green hydraulic jacks and the number 1 THS electric control motor

b. PRIM 1, the elevator green hydraulic jacks, and the number 2 THS electric control motor

c. PRIM 2, the elevator blue and yellow hydraulic jacks and the number 2 THS electric control motor

a. PRIM 1, the elevator green hydraulic jacks and the number 1 THS electric control motor

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If neither PRIM 1 or PRIM 2 are available, pitch control is transferred to:

a. SEC 2 for elevator control and PRIM 3 using the number 2 electric motor for THS control

b. SEC 1 for elevator control and PRIM 3 using the number 3 electric motor for THS control

c. PRIM 3 for elevator control and SEC 2 using the number 2 electric motor for THS control

b. SEC 1 for elevator control and PRIM 3 using the number 3 electric motor for THS control

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If all three PRIM computers are not available:

a. the THS is controlled by the manual pitch trim wheel only

b. the THS is controlled by the manual pitch trim wheel and the number 2 electric motor

c. the THS is controlled by the manual pitch trim wheel and the number 3 electric motor

a. the THS is controlled by the manual pitch trim wheel only

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Aileron droop:

a. occurs when the slats and flaps are extended

b. occurs when flaps are extended and is single droop setting

c. occurs when the flaps are extended and is a variable droop setting

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When the RAT is extended to recover hydraulic or electric power, the servo jacks that revert to damping mode control:

a. the outboard ailerons

b. the inboard ailerons

c. spoiler 1 to 6

a. the outboard ailerons

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Loss of hydraulic power to one of the single spoiler servos will cause that surface to:

a. retract

b. remain at the existing deflection or less if pushed down by aerodynamic forces

c. extend fully

b. remain at the existing deflection or less if pushed down by aerodynamic forces

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According to these cockpit indications the ground spoilers are: (speed brake lever pulled,
white marking visible and ECAM flight control page show a retracted spoiler)

a. armed and extended

b. armed and not extended

c. unarmed and not extended

b. armed and not extended

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The speed brake lever is not ARMED and ECAM shows a retracted spoilers. According to these cockpit indications, when this aircraft lands the ground spoilers will:

a. extend automatically on touchdown

b. extend when the pilot selects reverse on at least 1 engine (other engine at idle).

c. not extend, no matter what the pilot does with thrust levers

b. extend when the pilot selects reverse on at least 1 engine (other engine at idle).

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With yaw damping or turn coordination functions:

a. you can “feel” the inputs with rudder pedal movement

b. feedback is provided only when the autopilot is off

c. no feedback to the rudder pedals are provided

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In flight during a turn, when you bank the aircraft for a turn:

a. you must input the required rudder to maintain coordination

b. the correct amount of rudder is calculated by the computers

c. the redder pedals move automatically to maintain turn coordination

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b. the correct amount of rudder is calculated by the computers

When you see the rudder trim panel to set rudder trim, the input:

a. is fed back to the rudder pedals

b. is fed back to the rudder pedals only when you push reset

c. is not feedback to the rudder pedals

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a. is fed back to the rudder pedals

If one hydraulic system is inoperative:

a. the corresponding slats or flaps are normally operating

b. the corresponding slats or flaps are operating at half speed

c. the wing tip brakes (WTB) are activated and the corresponding slats or flaps remain at previous position

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b. the corresponding slats or flaps are operating at half speed

On the PFD speed portion, the following are the indications:VMO = 241 kts IAS=210 kts SPEED TREND = 190 kts
VFE = 195 kts and S Speed = 173 kts
```
Your present flap setting is FLAPS 1
In order to select FLAPS 2
```

a. you must decrease speed below S speed

b. you must decrease speed below 195 kts

c. you are not restricted by speed limit (below 240 kts)

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b. you must decrease speed below 195 kts

188. The flap lever is at Flaps 1. Flaps indication shows 1 in green. According to this cockpit indications: a. the pilot has selected the flap handle to 1 from 0 while in flight b. the pilot has selected flap position 1 while on the ground c. the aircraft could be either on ground or in the air

a. the pilot has selected the flap handle to 1 from 0 while in flight

189. Flaps position shows 1 + F in green. Speed is 193 kts and increasing. According to these indications, when the airspeed reaches 200 kts, if the pilot does not touch the flap handle: a. a flap overspeed will occur b. autothrust will prevent acceleration beyond 200 kts c. the flaps will automatically retract to prevent a flap overspeed

c. the flaps will automatically retract to prevent a flap overspeed

190. This A330 is in slight climb in Normal law. Immediately after the pilot releases the stick to neutral, the flight control will: a. lower the nose to regain a level fight path b. maintain the current flight path c. raise the nose to a steeper flight path

b. maintain the current flight path

191. The A330 is in level flight in Normal law. With stick released and airspeed slowed by 20kts, the flight control will: a. maintain the current pitch altitude and allow the aircraft to begin to sink b. lower the nose to maintain the current airspeed c. raise the nose as necessary to maintain the current flight path

c. raise the nose as necessary to maintain the current flight path

192. The A330 is being hand flown in Normal law. It is established in a 20 degree right bank turn. To maintain altitude, the pilot: a. must continually apply aft pressure to the sidestick b. does not need to make additional pitch inputs, the flight control system will maintain a level flight path c. is required to apply minor forward stick inputs

b. does not need to make additional pitch inputs, the flight control system will maintain a level flight path

193. Pith attitude protection limits the pitch attitude of the aircraft to: a. 30 degrees nose up, 20 degrees nose down b. 30 degrees nose up, 15 degrees nose down c. 15 degrees nose up, 30 degrees nose down

b. 30 degrees nose up, 15 degrees nose down

194. The A330 is in a 45 degree bank and has entered high speed protection. If the stick is released to neutral position, the aircraft will: a. maintain 45 degrees of bank b. roll to 33 degrees of bank c. roll to 0 degrees of bank (wings level)

c. roll to 0 degrees of bank (wings level)

195. The aircraft speed is at V alpha max. If the pilot is maintaining the sidestick in the full aft position: a. airspeed will decrease; the aircraft will stall b. airspeed will stabilize; the aircraft will not stall c. airspeed will increase because of Alpha floor

b. airspeed will stabilize; the aircraft will not stall

196. When the aircraft is under the NORMAL law, high angle of attack protection: a. cannot be overridden by the pilot b. can be overridden by the pilot c. is not available

a. cannot be overridden by the pilot

197. On the PFD, when the pitch and bank limit symbol is replaced by an amber X, this means that: a. the aircraft is in ALTERNATE LAW 1 b. the aircraft is in ALTERNATE LAW 2 c. the aircraft is in ALTERNATE LAW but the pilot cannot determine 1 or 2 from the PFD

c. the aircraft is in ALTERNATE LAW but the pilot cannot determine 1 or 2 from the PFD

198. On the PFD, the pitch and bank limit symbol is replaced by an amber X. A red MAN PITCH TRIM ONLY message also appear in the FMA. This means that: a. the aircraft can be controlled using the side sticks b. the aircraft can be controlled using the trimmable horizontal and the rudder c. the aircraft cannot be controlled

b. the aircraft can be controlled using the trimmable horizontal and the rudder

199. On the ECAM F/CTL page, all ailerons are at neutral position and the RH outboard aileron symbol is in amber color: a. clean config and the right inboard aileron has failed b. clean config and the right outboard aileron has failed c. flaps 2 and the right outboard aileron has failed

b. clean config and the right outboard aileron has failed

200. The sidestick are used to: a. control the aircraft in pitch and roll only and are spring loaded to the neutral position b. control the aircraft in pitch, roll and yaw and are manually returned to the neutral position c. control the aircraft in pitch, roll and yaw and are spring loaded to the neutral position

c. control the aircraft in pitch, roll and yaw and are spring loaded to the neutral position

201. The RESET push button on the Rudder Trim Control Panel, when pushed: a. resets the rudder trim to zero degree b. resets the rudder trim to the value displayed on the position indicator c. resets the rudder trim to the last position prior to autopilot activation

a. resets the rudder trim to zero degree

202. PFD shows that the aircraft is in Mechanical Back Up. The pitch and bank limit symbol is replaced by an amber X, and the FMA show a red “MAN PITCH TRIM ONLY”. When confronted with these cockpit indications the pilot is expected to: a. land the aircraft using the current fight control law b. maintain aircraft control while resetting at least one flight control computer c. make no attempt to attain a different flight control law

b. maintain aircraft control while resetting at least one flight control computer

203. ECAM amber message “F/CTRL FLAPS LOCKED” with Master Caution light means: a. further slat operation is not possible b. further slat and flap operation is not possible c. further flap operation is not possible

c. further flap operation is not possible

204. On the ECAM F/CTL page, inboard ailerons shows a bank while outboard ailerons are in neutral: a. both outboard ailerons have jammed b. both outboard ailerons are in damping mode c. both outboard ailerons are controlled to zero deflection, speed being above 190 kts

c. both outboard ailerons are controlled to zero deflection, speed being above 190 kts

205. The A330 rolls upside down. According to this situation: a. the normal law remains active b. the alternate law (without autotrim) is active in pitch and the roll is in direct law c. the direct law is active without protections (except G maneuver protection)

b. the alternate law (without autotrim) is active in pitch and the roll is in direct law

206. The aircraft is on descent, in NORMAL LAW and is being hand flown, if the pilot applies and holds full forward stick, the aircraft will: a. accelerate until it automatically pitches up and will stabilize the airspeed at VMO plus a preset number of additional knots b. continue in the current pitch attitude and continue to accelerate well beyond VMO as long as the pilot maintains forward stick c. experience a continued lowering of the pitch attitude and continued acceleration

a. accelerate until it automatically pitches up and will stabilize the airspeed at VMO plus a preset number of additional knots

207. On the PFD, the pitch and roll limit symbol is in color green. The aircraft flight control system is operating in: a. normal law b. alternate law c. direct law

a. normal law

208. The aircraft is in a nose up attitude, in Alternate Law and is being hand flown. If the pilot applies and hold full aft stick, the aircraft will: a. experience an automatic pitch input which will prevent the pilot from slowing the aircraft to a speed less than alpha max b. continue to respond to the stick input and reach stall speed. Stall recovery procedure is mandatory c. maintain the current pitch attitude and not allow airspeed to reach stall speed

b. continue to respond to the stick input and reach stall speed. Stall recovery procedure is mandatory

Automatic load factor protection prevents the pilot from exceeding preset G limits depending on the aircraft’s current configuration. Load factor protection which is not depicted on the PFD or ECAM is available in: a. Normal Law only b. Normal Law and Direct Law c. Normal Law and Alternate Law

c. Normal Law and Alternate Law

210. The aircraft is in approach with flaps extended in position 2 and speed brakes extended. What will happen when the flaps are extended to position 3? a. the flaps don’t extend to 3 and the speed brakes remain extended to FULL b. the flaps extend to 3 and the speed brakes remain extended to FULL c. the flaps will extend to 3 and the speed brakes retract automatically

b. the flaps extend to 3 and the speed brakes remain extended to FULL

211. The aircraft is being hand flown in Normal Law. The bank now is 40 degrees. If the pilot releases the side stick to neutral, the aircraft will: a. maintain the current bank angle b. roll to and maintain 33 degrees of bank c. roll to wings level

b. roll to and maintain 33 degrees of bank

212. On the glareshield. The Captain’s SIDESTICK PRIORITY light shows CAPT in green, while on the F/O’s shows the red arrow. This indicates that: a. the takeover pb in the Captain side stick has been pressed , the F/O side stick is not in the neutral position b. the takeover pb in the F/O side stick has been pressed, the CAPT side stick is not in neutral position c. the takeover pb in the F/O side stick has been pressed, the CAPT side is in neutral position

a. the takeover pb in the Captain side stick has been pressed , the F/O side stick is not in the neutral position

213. When a pilot has pressed and held the take over push button for more than 40 seconds, what has the other pilot to do to reactivate his sidestick? a. he has to press and release the take over push button b. he has to press the takeover pushbutton for more than 40 seconds c. he can do nothing, his side stick is deactivated for the rest of the flight

a. he has to press and release the take over push button

Flight Controls Flashcards

(50 cards)