Embraer 190 - Flight Controls
-
The jammed half of the aileron system can be disconnected by ...
-
Pulling the aileron disconnect handle located in the cockpit.
-
The FMS.
-
About This Quiz
FLIGHT CONTROLS QUESTIONS MADE FROM AOM VOL. 2
GOOD LUCK!SANTIAGO STOCKER.
Quiz Preview
- 2.
The Flight Control System is comprised of the ...
-
Primary and the secondary flight control systems and their associated system components.
-
Primary flight control systems and their associated system components.
Correct Answer
A. Primary and the secondary flight control systems and their associated system components.Explanation
The Flight Control System consists of two main components: the primary flight control system and the secondary flight control system. Both of these systems are essential for controlling the aircraft's movements and ensuring its stability and maneuverability. Additionally, the associated system components play a crucial role in supporting the operation of these flight control systems. Therefore, the correct answer is that the Flight Control System is comprised of the primary and the secondary flight control systems and their associated system components.Rate this question:
-
- 3.
There are three P-ACE units, two installed in the forward electronics bay and one installed in the aft electronics bay. Each P-ACE has ...
-
One active channel.
-
Two channels one is the active and the other is the standby.
Correct Answer
A. Two channels one is the active and the other is the standby.Explanation
The correct answer is two channels, one is the active and the other is the standby. This means that each P-ACE unit has two channels, with one channel being actively used and the other channel serving as a backup or standby. This setup ensures redundancy and reliability in case of any failures or malfunctions in the active channel.Rate this question:
-
- 4.
What does FCM mean?
Correct Answer
flight control modules
flight control moduleExplanation
FCM stands for flight control module(s), which refers to the electronic components responsible for controlling and managing the various systems and functions of an aircraft during flight. These modules play a crucial role in ensuring the safe and efficient operation of the aircraft, including controlling the flight surfaces, managing the engine performance, and monitoring various sensors and systems. Therefore, the correct answer is flight control modules and flight control module, as both terms accurately describe the electronic components involved in aircraft control.Rate this question:
- 5.
The Controller Area Network BUS (CAN BUS) is the communication link between the ...
-
FCMs and the P-ACE units.
-
FCMs and the HS-ACE unit.
Correct Answer
A. FCMs and the P-ACE units.Explanation
The correct answer is FCMs and the P-ACE units. The Controller Area Network BUS (CAN BUS) serves as the communication link between the FCMs (Fuel Control Modules) and the P-ACE (Power-Assisted Control Electronics) units. This means that the CAN BUS allows for the exchange of data and information between these two components, enabling them to work together effectively in controlling and managing the vehicle's fuel system.Rate this question:
-
- 6.
The ailerons are ...
-
Commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.
-
Controlled electronically using Fly-by-Wire (FBW) technology.
Correct Answer
A. Commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.Explanation
The ailerons are commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators. This means that the pilot's input on the control wheel is transmitted through the control cables to the actuators, which then move the ailerons accordingly. This traditional method of control provides a direct mechanical connection between the pilot and the ailerons, allowing for precise and immediate control of the aircraft's roll.Rate this question:
-
- 7.
The HS-ACE unit controls the ...
-
Rudder and the elevator surfaces.
-
Slat and flaps surface.
-
Horizontal stabilizer surface.
-
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
A. Horizontal stabilizer surface.Explanation
The correct answer is the horizontal stabilizer surface. The HS-ACE unit is responsible for controlling the horizontal stabilizer, which is an important component of the aircraft's control system. It helps to stabilize the aircraft in pitch, allowing for smooth and controlled movements of the nose up and down. The rudder and elevator surfaces, slat and flaps surfaces, and multifunction spoilers are all separate components that serve different purposes in the aircraft's control system.Rate this question:
-
- 8.
A disconnect mechanism is provided to allow separation of the First Officer and Captain’s control columns. In the event of a jam in one of the control columns, the disconnect mechanism can be actuated by pilots through the ...
-
FMS.
-
Disconnect handle in the cockpit.
Correct Answer
A. Disconnect handle in the cockpit.Explanation
A disconnect mechanism is provided in the cockpit to allow separation of the First Officer and Captain's control columns. This mechanism is important in case one of the control columns becomes jammed. The pilots can actuate the disconnect mechanism by using the disconnect handle in the cockpit. This handle allows them to physically disconnect the control columns, giving each pilot independent control over their own column. This ensures that even if one column is jammed, the other pilot can still control the aircraft effectively.Rate this question:
-
- 9.
In order to avoid a possible pitch trim runaway condition, manual pilot trim commands are limited to ...
-
3 seconds.
-
10 seconds.
Correct Answer
A. 3 seconds.Explanation
Manual pilot trim commands are limited to 3 seconds in order to prevent a potential pitch trim runaway condition. This limitation ensures that the pilot's input does not cause excessive or continuous trim adjustments, which could lead to an uncontrolled change in the aircraft's pitch attitude. By limiting the duration of manual trim commands, the pilot can make small adjustments to the trim without the risk of overcompensating or destabilizing the aircraft.Rate this question:
-
- 10.
The multifunction spoiler control system consists of 6 panels numbered from inboard to outboard as:
-
L3, L4, L5 (left wing) and R3, R4, R5 (right wing).
-
L3, L4, L5 (right wing) and R3, R4, R5 (left wing).
Correct Answer
A. L3, L4, L5 (left wing) and R3, R4, R5 (right wing). -
- 11.
Rudder trim function is limited to ______ seconds. If further displacement of the trim system is required the command must be released and reapplied. Position indication of the trim actuator is provided on the EICAS.
-
Three
-
Ten
Correct Answer
A. ThreeExplanation
The correct answer is three. This means that the rudder trim function is limited to three seconds. If the trim system needs to be further adjusted, the command must be released and then reapplied. The position of the trim actuator is indicated on the EICAS.Rate this question:
-
- 12.
Elevators, rudders, roll spoilers as well as all secondary flight control systems, including the horizontal stabilizer, flaps and slats, ground spoilers and speed brakes, are ...
-
Commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.
-
Controlled electronically using Fly-by-Wire (FBW) technology.
Correct Answer
A. Controlled electronically using Fly-by-Wire (FBW) technology.Explanation
The correct answer is controlled electronically using Fly-by-Wire (FBW) technology. This means that instead of using conventional control cables, the various flight control systems are controlled electronically. This technology allows for more precise and efficient control of the aircraft's movements.Rate this question:
-
- 13.
The PBIT expires after ____________ (elapsed time) since the last successful PBIT. Once the PBIT is expired, FLT CTRL BIT EXPIRED EICAS CAUTION message is displayed.
-
50 hours
-
100 hours
Correct Answer
A. 50 hoursExplanation
The PBIT (Power-On Built-In Test) expires after 50 hours since the last successful PBIT. Once the PBIT is expired, the FLT CTRL BIT EXPIRED EICAS CAUTION message is displayed.Rate this question:
-
- 14.
_____ independent FCM units, located in MAU 1 and 3, provide highlevel system augmentation on the P-ACE units, such as yaw damping, turn coordination, as well as gain scheduling as a function of airspeed.
-
Four
-
Six
Correct Answer
A. FourExplanation
There are four independent FCM units located in MAU 1 and 3. These units provide high-level system augmentation on the P-ACE units, including yaw damping, turn coordination, and gain scheduling based on airspeed.Rate this question:
-
- 15.
Hydraulic actuators control the respective flight control surfaces. These are referred to as ____________________ (PCUs).
Correct Answer
Power Control Units
Power Control UnitExplanation
Hydraulic actuators control the respective flight control surfaces. These actuators are referred to as Power Control Units (PCUs). PCUs are responsible for converting hydraulic power into mechanical motion, allowing for precise control of the flight control surfaces. They play a crucial role in maintaining the stability and maneuverability of the aircraft during flight.Rate this question:
- 16.
The SF-ACE units control the ...
-
Rudder and the elevator surfaces.
-
Slat and flaps surface.
-
Horizontal stabilizer surface.
-
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
A. Slat and flaps surface.Explanation
The correct answer is "slat and flaps surface." This means that the SF-ACE units are responsible for controlling the movement and positioning of the slats and flaps on the aircraft. The other options mentioned, such as the rudder and elevator surfaces, horizontal stabilizer surface, and multifunction spoilers, are not controlled by the SF-ACE units according to the given information.Rate this question:
-
- 17.
The FCMs provide software-based assistance to the ________ and is required for normal-mode operation of the flight controls system.
-
P-ACE
-
FS-ACE
-
HS-ACE
Correct Answer
A. P-ACEExplanation
The correct answer is P-ACE. The FCMs (Flight Control Modules) provide software-based assistance to the P-ACE (Primary Avionics Control Electronics) and are required for normal-mode operation of the flight controls system.Rate this question:
-
- 18.
The Flight Control System provides two basic modes of operation: – DIRECT MODE:
-
The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE.
-
The FCM is removed from the control loop (for instance, due to loss of airspeed data) and the control limits default to values set by hardware in the P-ACE.
Correct Answer
A. The FCM is removed from the control loop (for instance, due to loss of airspeed data) and the control limits default to values set by hardware in the P-ACE.Explanation
The Flight Control Module (FCM) is responsible for providing software-based airspeed gain schedules and control limits to the P-ACE. However, in the event of a loss of airspeed data or any other reason that causes the FCM to be removed from the control loop, the control limits will default to values that are set by the hardware in the P-ACE. This ensures that the aircraft can still maintain control and operate safely even without the input from the FCM.Rate this question:
-
- 19.
_____ independent FCM units, located in the MAU 1 and 3, provide high-level system augmentation to the P-ACE units, such as gain scheduling as a function of airspeed, elevator thrust compensation and AOA limiting.
-
Four
-
Six
Correct Answer
A. FourExplanation
The correct answer is Four. The question states that there are independent FCM units located in the MAU 1 and 3, which provide high-level system augmentation to the P-ACE units. The question asks for the number of these independent FCM units, and the answer is Four.Rate this question:
-
- 20.
The hydraulic systems responsible for powering the actuators are: Hydraulic System 3:
-
Left outboard actuator.
-
Left & right inboard actuators.
-
Right outboard actuator.
Correct Answer
A. Right outboard actuator.Explanation
The correct answer is "right outboard actuator." This means that the hydraulic system 3 is responsible for powering the right outboard actuator.Rate this question:
-
- 21.
If a jam in one of the elevator actuator is detected, the respective elevator surface will remain fixed at the position where the jam occurred.
-
The pilot will be able to control the airplane using the remaining elevator.
-
There is no way to control the elevator.
Correct Answer
A. The pilot will be able to control the airplane using the remaining elevator.Explanation
If a jam occurs in one of the elevator actuators, it means that the elevator surface connected to that actuator will be unable to move. However, the remaining elevator surface that is not affected by the jam will still be functional and controllable by the pilot. This allows the pilot to have some level of control over the airplane's pitch and maneuverability, even though one of the elevators is fixed in position due to the jam.Rate this question:
-
- 22.
When the flight control panel elevator button is pushed in, it commands all four elevator channel to change from Normal to Direct mode.
-
In addition, pushing the button also results in the active elevator channels transitioning to the standby state, and the channels that were previously in standby would become active.
-
Channel will remain the same states.
Correct Answer
A. In addition, pushing the button also results in the active elevator channels transitioning to the standby state, and the channels that were previously in standby would become active.Explanation
When the flight control panel elevator button is pushed in, it not only commands all four elevator channels to change from Normal to Direct mode, but it also causes the active elevator channels to transition to the standby state. At the same time, the channels that were previously in standby become active. Therefore, pushing the button has the effect of switching the roles of the active and standby elevator channels.Rate this question:
-
- 23.
For landings and GO AROUND with flap 5, it is not possible to engage TSA function before ______ have elapsed from takeoff.
-
5 min
-
20 min
Correct Answer
A. 5 minExplanation
After takeoff, there is a minimum time requirement of 5 minutes before the TSA (Takeoff Safety Altitude) function can be engaged for landings and go-arounds with flap 5. This is to ensure that the aircraft has reached a safe altitude and is stable before activating the TSA function.Rate this question:
-
- 24.
PCU JAMMED In case of a jammed PCU actuator the rudder will be hydraulically locked at the current position. Aircraft control will be established through the ...
-
Ailerons only.
-
Ailerons and roll spoilers.
Correct Answer
A. Ailerons and roll spoilers.Explanation
In case of a jammed PCU actuator, the rudder will be hydraulically locked at the current position. This means that the rudder cannot be moved, so the aircraft control cannot rely on the rudder for maneuvering. Instead, control will be established through the ailerons and roll spoilers. The ailerons control the roll of the aircraft, allowing it to bank left or right, while the roll spoilers help in reducing the lift on the wings, aiding in roll control. Therefore, the correct answer is ailerons and roll spoilers.Rate this question:
-
- 25.
The primary flight control electronics include ...
-
One part:• The Primary Actuator Control Electronics (P-ACE).
-
Two complementary parts:• The Primary Actuator Control Electronics (P-ACE).• The Flight Control Module (FCM).
Correct Answer
A. Two complementary parts:• The Primary Actuator Control Electronics (P-ACE).• The Flight Control Module (FCM).Explanation
The correct answer is two complementary parts: The Primary Actuator Control Electronics (P-ACE) and The Flight Control Module (FCM).Rate this question:
-
- 26.
______ Flight Control Modules (FCM).
-
Two
-
Four
-
Six
Correct Answer
A. FourExplanation
The correct answer is "Four". This suggests that there are four Flight Control Modules (FCM) involved in the given situation.Rate this question:
-
- 27.
The mode selection is ...
-
Automatic when a channel failure is detected or manually selected by using a “Mode Select” switch on the Flight Control Panel.
-
Manually selected by using a “Mode Select” switch on the Flight Control Panel.
Correct Answer
A. Automatic when a channel failure is detected or manually selected by using a “Mode Select” switch on the Flight Control Panel.Explanation
The mode selection for the flight control panel can be done in two ways: automatically when a channel failure is detected or manually by using a "Mode Select" switch.Rate this question:
-
- 28.
The backup trim switch and the control wheel trim switches are dual split switches which have a __________ time limitation when actuated separately.
-
20 second
-
7 second
Correct Answer
A. 7 secondExplanation
The backup trim switch and the control wheel trim switches are dual split switches which have a time limitation of 7 seconds when actuated separately.Rate this question:
-
- 29.
In case of an electrical failure, followed by RAT deployment, the trim function will work at half speed operation, ...
-
For autopilot trim.
-
For either manual trim or autopilot trim.
Correct Answer
A. For either manual trim or autopilot trim.Explanation
In case of an electrical failure, followed by RAT deployment, the trim function will work at half speed operation for either manual trim or autopilot trim. This means that both manual trim and autopilot trim can be used to adjust the trim of the aircraft in this situation.Rate this question:
-
- 30.
Lateral control system includes ...
-
Conventional ailerons.
-
Both conventional ailerons and the fly by wire multi function spoilers witch provides the roll axis control.
Correct Answer
A. Both conventional ailerons and the fly by wire multi function spoilers witch provides the roll axis control.Explanation
The correct answer is both conventional ailerons and the fly by wire multi function spoilers which provide roll axis control. This means that the lateral control system includes both traditional ailerons as well as advanced fly by wire multi function spoilers. The conventional ailerons are used for roll control, while the fly by wire multi function spoilers provide additional control over the roll axis. This combination of control surfaces allows for precise and effective lateral control of the aircraft.Rate this question:
-
- 31.
HIGH SPEED FIXED GAIN
-
Is selected for Flaps/Slats extended.The rudder is set at the maximum authority to ensure that the pilot has sufficient authority to control the aircraft during the approach and landing.
-
Is selected for flaps/slats retracted. Ensures that the rudder movement is limited at high speeds, providing structural protection.
Correct Answer
A. Is selected for flaps/slats retracted. Ensures that the rudder movement is limited at high speeds, providing structural protection. -
- 32.
Speed brakes will not be deployed if airspeed is below _______, and will also automatically retract if airspeed decreases below this threshold.
-
180 KIAS
-
210 KIAS
Correct Answer
A. 180 KIASExplanation
Speed brakes are a mechanism used to slow down an aircraft by increasing drag. In this case, the correct answer is 180 KIAS, which stands for Knots Indicated Airspeed. This means that if the airspeed is below 180 KIAS, the speed brakes will not be deployed. Additionally, if the airspeed decreases below this threshold, the speed brakes will automatically retract. This ensures that the speed brakes are only deployed and used when the aircraft is flying at a certain speed range.Rate this question:
-
- 33.
What does ACE mean?
Correct Answer
actuator control electronics
actuator control electronicExplanation
ACE stands for actuator control electronics. This refers to the electronic components and systems that control and regulate the movement and operation of actuators. Actuators are devices that convert electrical signals into mechanical motion, such as opening and closing valves or adjusting the position of a control surface in an aircraft. The term "actuator control electronics" indicates the electronic systems responsible for controlling and coordinating the operation of these actuators.Rate this question:
- 34.
No action is required if the PBIT expires in-flight, as the EICAS CAUTION message will ...
-
Only be displayed after landing.
-
Be displayed any time.
Correct Answer
A. Only be displayed after landing.Explanation
The correct answer is that the EICAS CAUTION message will only be displayed after landing. This means that if the PBIT (Power-On Built-In Test) expires while the aircraft is in flight, there is no need for immediate action. The caution message will only appear once the aircraft has landed, indicating that the PBIT has expired.Rate this question:
-
- 35.
The manual selection of the Captain or First Officer’s wheel main trim switches or pedestal mounted backup trim switches which directly control an electrical servo motor coupled to the ___________ ___________ ___________ (HSA).
Correct Answer
Horizontal Stabilizer ActuatorExplanation
The correct answer is Horizontal Stabilizer Actuator. The manual selection of the Captain or First Officer's wheel main trim switches or pedestal mounted backup trim switches directly control an electrical servo motor coupled to the Horizontal Stabilizer Actuator (HSA). This means that when the pilot adjusts the trim switches, it directly affects the movement of the horizontal stabilizer actuator, which in turn adjusts the position of the horizontal stabilizer.Rate this question:
- 36.
The HSA is a single __________________ actuator. Two AC motors drive the actuator in an active/standby configuration. Stabilizer position is provided to the HS-ACE and is used for monitoring and EICAS indication.
-
Electrical-mechanical
-
Hydraulic-mechanical
Correct Answer
A. Electrical-mechanicalExplanation
The correct answer is electrical-mechanical. This means that the actuator is powered by electrical energy and converts it into mechanical motion. Two AC motors are used to drive the actuator, with one serving as the active motor and the other as the standby motor. The stabilizer position is provided to the HS-ACE (Horizontal Stabilizer Actuator Control Electronics) for monitoring and EICAS (Engine Indicating and Crew Alerting System) indication.Rate this question:
-
- 37.
The power control units are driven by the following hydraulic systems: Hydraulic System 3:
-
Left & right inboard PCU.
-
Left & right outboard PCU.
Correct Answer
A. Left & right outboard PCU.Explanation
The correct answer is left & right outboard PCU. This means that the power control units (PCUs) in the hydraulic system are driven by the left and right outboard PCUs.Rate this question:
-
- 38.
In the event of a disconnection of one aileron PCU from the surface or wing structure, the other PCU attached to the surface will ___________________________________________. Hence the aileron PCUs normally share air-loads during flight, if the FCM detects a difference in load sharing from the actuators, a message will be displayed on the EICAS.
-
Operate normally, but the force authority will be halved
-
Be also automatically disconnected
Correct Answer
A. Operate normally, but the force authority will be halvedExplanation
If one aileron PCU becomes disconnected from the surface or wing structure, the other PCU attached to the surface will still operate normally. However, the force authority, or the amount of force that the PCU can exert, will be halved. This means that the aileron will still function, but with reduced effectiveness. The aileron PCUs typically share air-loads during flight, but if the Flight Control Module (FCM) detects a difference in load sharing from the actuators, a message will be displayed on the Engine Indicating and Crew Alerting System (EICAS).Rate this question:
-
- 39.
The P-ACE units control the ...
-
Rudder and the elevator surfaces.
-
Slat and flaps surface.
-
Horizontal stabilizer surface.
-
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
A. Rudder and the elevator surfaces.Explanation
The correct answer is "rudder and the elevator surfaces." This means that the P-ACE units are responsible for controlling the movement of the rudder and the elevator surfaces on an aircraft.Rate this question:
-
- 40.
The Horizontal Stabilizer ACE (HS-ACE) is installed in the aft electronics bay. The HS-ACE has ...
-
One active channel.
-
Two channels one is the active and the other is the standby.
Correct Answer
A. Two channels one is the active and the other is the standby.Explanation
The correct answer is two channels, one is the active and the other is the standby. This means that the Horizontal Stabilizer ACE (HS-ACE) has two separate channels for operation. One channel is active and responsible for the normal functioning of the HS-ACE, while the other channel serves as a backup or standby in case the active channel fails. Having two channels ensures redundancy and enhances the reliability of the HS-ACE system.Rate this question:
-
- 41.
The Flight Control System provides two basic modes of operation: – NORMAL MODE:
-
The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE.
-
The FCM is removed from the control loop (for instance, due to loss of airspeed data) and the control limits default to values set by hardware in the P-ACE.
Correct Answer
A. The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE.Explanation
The Flight Control Module (FCM) is responsible for providing airspeed gain schedules and control limits to the P-ACE. In normal mode of operation, the FCM is actively involved in the control loop. However, in certain situations such as loss of airspeed data, the FCM is removed from the control loop. In such cases, the control limits default to values set by hardware in the P-ACE. This ensures that the aircraft maintains a safe and stable flight even when the FCM is not functioning properly.Rate this question:
-
- 42.
The autopilot can directly operate the electric trim motor when the autopilot is engaged. If the autopilot trim function is inoperative, the autopilot cannot be engaged. If this function is lost during autopilot operation, the autopilot will ...
-
Be disengage.
-
Remians engaged.
Correct Answer
A. Be disengage.Explanation
If the autopilot trim function is inoperative or lost during autopilot operation, the autopilot will disengage. This means that the autopilot will no longer be engaged and the aircraft will no longer be under the control of the autopilot system.Rate this question:
-
- 43.
In the event of an electrical emergency, only the HS-ACE channel 2 is operational at ...
-
Low rate.
-
Normal rate.
Correct Answer
A. Low rate.Explanation
In the event of an electrical emergency, only the HS-ACE channel 2 is operational at a low rate. This means that during an electrical emergency, the communication on channel 2 will be limited or slowed down compared to the normal rate. This could be due to various factors such as power outages or equipment malfunctions, which may require the system to operate at a reduced capacity.Rate this question:
-
- 44.
The Captain’s half of the system is jammed. The First Officer retains control of the right aileron without artificial feel and roll trim since the feel mechanism is attached to Captain’s half of the system, the ______ of multi-function spoilers will remain available.
-
Pair #4
-
Pair #5
Correct Answer
A. Pair #4Explanation
The correct answer is pair #4. The reason for this is that since the Captain's half of the system is jammed, the feel mechanism, which is attached to the Captain's half, is not functioning. As a result, the First Officer retains control of the right aileron without artificial feel and roll trim. However, the multi-function spoilers are not affected by this issue and will remain available for use.Rate this question:
-
- 45.
Yaw control is performed by means of an electronic control system that commands _________________ actuators of the rudders.
-
Electro-hydraulic
-
Electro-mechanical
Correct Answer
A. Electro-hydraulicExplanation
Yaw control is performed by means of an electronic control system that commands electro-hydraulic actuators of the rudders. This means that the electronic control system uses electrical signals to control hydraulic actuators, which in turn control the movement of the rudders. This combination of electronic and hydraulic systems allows for precise and efficient control of the yaw movement of the vehicle.Rate this question:
-
- 46.
The ACE units connect the control column ______________ to the respective control surface, providing direct analog control of the surface.
-
Electronically
-
Mechanically
Correct Answer
A. ElectronicallyExplanation
The ACE units connect the control column to the respective control surface, providing direct analog control of the surface. This implies that the connection between the control column and control surface is done electronically, rather than mechanically.Rate this question:
-
- 47.
The S-ACE resides within the FCMs and is used to control the ...
-
Rudder and the elevator surfaces.
-
Slat and flaps surface.
-
Horizontal stabilizer surface.
-
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
A. Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.Explanation
The correct answer is "multifunction spoilers. Each FCM controls one pair of multi-function spoiler." This means that the S-ACE (System - Augmentation Control Electronics) is responsible for controlling the multifunction spoilers on the aircraft. Each Flight Control Module (FCM) is in charge of controlling one pair of these spoilers.Rate this question:
-
- 48.
For ______________________________________ control surfaces which have two controlling channels, the flight control system has a function to select which set of channels would be the active channels for a particular day. This function, called the ‘Odd-Even Day Engage’ configuration is implemented to reduce the latency in the flight control system and to allow for even wear of the flight control system components.
-
The rudder, elevator and stabilizer
-
The flaps/slats, spoilers and ailerons
Correct Answer
A. The rudder, elevator and stabilizerExplanation
The correct answer is the rudder, elevator, and stabilizer. The flight control system has a function called 'Odd-Even Day Engage' configuration, which allows for the selection of active channels for a particular day. This function is implemented to reduce latency in the flight control system and ensure even wear of the flight control system components.Rate this question:
-
- 49.
The authority of TSA function depends ...
-
Takeoff configuration.
-
Landing configuration.
-
On whether in takeoff or landing configuration.
Correct Answer
A. On whether in takeoff or landing configuration.Explanation
The authority of the TSA function depends on whether the aircraft is in the takeoff or landing configuration. This means that the effectiveness and control of the TSA function can vary depending on the specific configuration of the aircraft during these critical phases of flight.Rate this question:
-
Quiz Review Timeline (Updated): Sep 18, 2024 +
Our quizzes are rigorously reviewed, monitored and continuously updated by our expert board to maintain accuracy, relevance, and timeliness.
-
Current Version
-
Sep 18, 2024Quiz Edited by
ProProfs Editorial Team -
Jun 12, 2011Quiz Created by
Santisfaction
Back to top