Embraer 190 - Flight Controls
FLIGHT CONTROLS QUESTIONS MADE FROM AOM VOL. 2
GOOD LUCK!SANTIAGO STOCKER.
Questions and Answers
- 1.
The Flight Control System is comprised of the ...
- A.
Primary and the secondary flight control systems and their associated system components.
- B.
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:
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- 2.
The primary flight control system consists of: (Check all correct options) lklk (C
- A.
Horizontal stabilizer
- B.
Ailerons and the multi function roll spoilers for roll axis control.
- C.
Rudder for yaw axis control.
- D.
Flaps and Slats
- E.
Elevators for pitch axis control.
- F.
The multi-function spoiler (when used as speed brakes or groundspoilers).
- G.
Dedicated ground spoilers
Correct Answer(s)
B. Ailerons and the multi function roll spoilers for roll axis control.
C. Rudder for yaw axis control.
E. Elevators for pitch axis control.Explanation
The primary flight control system consists of a combination of different components that are responsible for controlling the aircraft's movement along different axes. The ailerons and multi-function roll spoilers work together to control the roll axis, allowing the aircraft to bank left or right. The rudder is used for controlling the yaw axis, enabling the aircraft to turn left or right. The elevators are responsible for controlling the pitch axis, allowing the aircraft to climb or descend. These components are essential for maintaining stability and control during flight.Rate this question:
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- 3.
The secondary flight control system consists of: (Check all correct options) lklk (C
- A.
Horizontal stabilizer
- B.
Ailerons and the multi function roll spoilers for roll axis control.
- C.
Rudder for yaw axis control.
- D.
Flaps and Slats
- E.
Elevators for pitch axis control.
- F.
The multi-function spoiler (when used as speed brakes or groundspoilers).
- G.
Dedicated ground spoilers
Correct Answer(s)
A. Horizontal stabilizer
D. Flaps and Slats
F. The multi-function spoiler (when used as speed brakes or groundspoilers).
G. Dedicated ground spoilersExplanation
The secondary flight control system consists of the horizontal stabilizer, flaps and slats, the multi-function spoiler (when used as speed brakes or ground spoilers), and dedicated ground spoilers. These components are responsible for controlling the aircraft's roll, pitch, and yaw axes, as well as providing additional lift and drag during various flight phases.Rate this question:
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- 4.
Hydraulic actuators control the respective flight control surfaces. These are referred to as ____________________ (PCUs).
Correct Answer(s)
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:
- 5.
The ailerons are ...
- A.
Commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.
- B.
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:
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- 6.
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 ...
- A.
Commanded by conventional control cables that run from each control wheel back to a pair of hydro-mechanical actuators.
- B.
Controlled electronically using Fly-by-Wire (FBW) technology.
Correct Answer
B. 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:
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- 7.
The primary flight control electronics include ...
- A.
One part:• The Primary Actuator Control Electronics (P-ACE).
- B.
Two complementary parts:• The Primary Actuator Control Electronics (P-ACE).• The Flight Control Module (FCM).
Correct Answer
B. 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:
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- 8.
Primary Actuator Control Electronics (P-ACE) and/or Flight Control Modules (FCM) are employed to operate the respective ...
- A.
Electro-hydraulic or electro-mechanical actuators.
- B.
Electro-hydraulic.
Correct Answer
A. Electro-hydraulic or electro-mechanical actuators.Explanation
The correct answer is "electro-hydraulic or electro-mechanical actuators." This means that both the Primary Actuator Control Electronics (P-ACE) and/or Flight Control Modules (FCM) can be used to operate either electro-hydraulic or electro-mechanical actuators. These actuators are essential for controlling the movement of various components in a system, and they can be operated using either electrical or hydraulic mechanisms.Rate this question:
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- 9.
The EMBRAER FBW system is composed of a set of ...
- A.
Four Actuator Control Electronics (ACEs) and nine Flight Control Modules (FCMs):
- B.
Nine Actuator Control Electronics (ACEs) and four Flight Control Modules (FCMs):
Correct Answer
B. Nine Actuator Control Electronics (ACEs) and four Flight Control Modules (FCMs):Explanation
The correct answer is "nine Actuator Control Electronics (ACEs) and four Flight Control Modules (FCMs)". This means that the EMBRAER FBW system consists of nine ACEs and four FCMs. The ACEs are responsible for controlling the actuators, while the FCMs are responsible for controlling the overall flight control system. This configuration allows for redundancy and ensures that the system can continue to function even if some of the components fail.Rate this question:
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- 10.
______ Primary-ACEs (P-ACE).
- A.
One
- B.
Two
- C.
Three
Correct Answer
C. ThreeExplanation
The correct answer is "Three." This suggests that there are three primary Adverse Childhood Experiences (ACEs) being referred to in the question. However, without further context or information, it is not possible to provide a more detailed explanation.Rate this question:
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- 11.
______ Slat/Flap ACEs (SF-ACE).
- A.
One
- B.
Two
- C.
Three
Correct Answer
B. Two -
- 12.
______ Horizontal Stabilizer ACE (HS-ACE).
- A.
One
- B.
Two
- C.
Three
Correct Answer
A. One -
- 13.
______ Spoiler ACEs (S-ACE).
- A.
One
- B.
Two
- C.
Three
Correct Answer
C. Three -
- 14.
______ Flight Control Modules (FCM).
- A.
Two
- B.
Four
- C.
Six
Correct Answer
B. FourExplanation
The correct answer is "Four". This suggests that there are four Flight Control Modules (FCM) involved in the given situation.Rate this question:
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- 15.
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:
- 16.
The ACE units connect the control column ______________ to the respective control surface, providing direct analog control of the surface.
- A.
Electronically
- B.
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:
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- 17.
There are ______ different ACE units:
- A.
Four
- B.
Six
Correct Answer
A. FourExplanation
There are four different ACE units.Rate this question:
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- 18.
The P-ACE units control the ...
- A.
Rudder and the elevator surfaces.
- B.
Slat and flaps surface.
- C.
Horizontal stabilizer surface.
- D.
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:
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- 19.
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 ...
- A.
One active channel.
- B.
Two channels one is the active and the other is the standby.
Correct Answer
B. 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:
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- 20.
The SF-ACE units control the ...
- A.
Rudder and the elevator surfaces.
- B.
Slat and flaps surface.
- C.
Horizontal stabilizer surface.
- D.
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
B. 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:
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- 21.
There are two SF-ACE units installed in the middle electronics bay. Each SF-ACE has two channels ...
- A.
One channel for flap and one channel for slat.
- B.
One is the active and the other is the standby.
Correct Answer
A. One channel for flap and one channel for slat.Explanation
The given correct answer states that each SF-ACE unit has two channels, one for flap and one for slat. This means that there is a separate channel dedicated to controlling the movement of the flap and another channel dedicated to controlling the movement of the slat. Additionally, it is mentioned that one channel is active while the other is on standby, suggesting that there is redundancy in the system to ensure continuous operation even if one channel fails.Rate this question:
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- 22.
The HS-ACE unit controls the ...
- A.
Rudder and the elevator surfaces.
- B.
Slat and flaps surface.
- C.
Horizontal stabilizer surface.
- D.
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
C. 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:
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- 23.
The Horizontal Stabilizer ACE (HS-ACE) is installed in the aft electronics bay. The HS-ACE has ...
- A.
One active channel.
- B.
Two channels one is the active and the other is the standby.
Correct Answer
B. 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:
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- 24.
The S-ACE resides within the FCMs and is used to control the ...
- A.
Rudder and the elevator surfaces.
- B.
Slat and flaps surface.
- C.
Horizontal stabilizer surface.
- D.
Multifunction spoilers. Each FCM controls one pair of multi-function spoiler.
Correct Answer
D. 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:
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- 25.
FCM #1, FCM #3 and FCM #4 have wiring to control spoilers. FCM #2 does not control any spoiler pair.
- A.
True
- B.
False
Correct Answer
A. TrueExplanation
The given statement suggests that FCM #1, FCM #3, and FCM #4 have wiring to control spoilers, while FCM #2 does not control any spoiler pair. This means that FCM #2 does not have the capability to control the spoilers, while the other three FCMs do. Therefore, the correct answer is True.Rate this question:
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- 26.
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:
- 27.
The FCMs provide software-based assistance to the ________ and is required for normal-mode operation of the flight controls system.
- A.
P-ACE
- B.
FS-ACE
- C.
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:
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- 28.
The FCM units are connected to the P-ACE via the _____________________________ , providing digital inputs to the P-ACE, which are combined with pilot inputs. This is used to augment pilot inputs for different airspeeds, and provides other high-level functions such as Angle-of-attack (AOA) limiting to the P-ACE units.
- A.
Modular Avionics Units (MAU)
- B.
Controller Area Network Bus (CAN BUS)
Correct Answer
B. Controller Area Network Bus (CAN BUS)Explanation
The FCM units are connected to the P-ACE via the Controller Area Network Bus (CAN BUS), providing digital inputs to the P-ACE. This allows the FCM units to communicate with the P-ACE and share information such as airspeed and pilot inputs. The CAN BUS is used to combine pilot inputs with the digital inputs from the FCM units, augmenting pilot inputs for different airspeeds. Additionally, the CAN BUS enables high-level functions such as Angle-of-attack (AOA) limiting to be implemented by the P-ACE units.Rate this question:
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- 29.
The Flight Control System provides two basic modes of operation: – NORMAL MODE:
- A.
The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE.
- B.
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:
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- 30.
The Flight Control System provides two basic modes of operation: – DIRECT MODE:
- A.
The Flight Control Module (FCM) provides software based airspeed gain schedules and control limits to the P-ACE.
- B.
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
B. 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:
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- 31.
The mode selection is ...
- A.
Automatic when a channel failure is detected or manually selected by using a “Mode Select” switch on the Flight Control Panel.
- B.
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:
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- 32.
The “Mode Selection” switch provides the capability to the flight crew to reset the system to Normal Mode in case of the system defaulting to Direct Mode, or to manually default the flight control system to Direct Mode in case of a wrong gain computed by the FCMs being transmitted to the P-ACEs or S-ACEs. In this case the “Mode Selection” switch toggles ...
- A.
The Normal Channel of the active P-ACE to the Direct Channel of the active P-ACE.
- B.
The Normal Channel of the active P-ACE to the Direct Channel of the standby P-ACE.
Correct Answer
B. The Normal Channel of the active P-ACE to the Direct Channel of the standby P-ACE.Explanation
The "Mode Selection" switch is used to reset the flight control system to Normal Mode when it defaults to Direct Mode or to manually default the system to Direct Mode when there is an incorrect gain computed by the FCMs. In this case, the switch toggles the Normal Channel of the active P-ACE to the Direct Channel of the standby P-ACE. This allows for a smooth transition between the two modes and ensures that the flight control system remains operational and responsive.Rate this question:
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- 33.
The Controller Area Network BUS (CAN BUS) is the communication link between the ...
- A.
FCMs and the P-ACE units.
- B.
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:
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- 34.
The Avionics Standard Communication Bus (ASCB) provides data exchange between all _____, and with other components of the avionic system.
- A.
P-ACEs
- B.
FCMs
Correct Answer
B. FCMsExplanation
The Avionics Standard Communication Bus (ASCB) provides data exchange between all FCMs (Flight Control Modules), and with other components of the avionic system. The FCMs are responsible for controlling various aspects of the aircraft's flight, such as navigation, autopilot, and engine management. The ASCB facilitates communication between these modules, allowing them to share data and coordinate their actions effectively.Rate this question:
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- 35.
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.
- A.
50 hours
- B.
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:
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- 36.
No action is required if the PBIT expires in-flight, as the EICAS CAUTION message will ...
- A.
Only be displayed after landing.
- B.
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:
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- 37.
The Power Up Built in Test (PBIT) reduces the _________________ exposition to latent faults, ensuring that the system components remain capable of executing their functions.
- A.
Electrical system
- B.
Flight control system
Correct Answer
B. Flight control systemExplanation
The Power Up Built in Test (PBIT) is a feature that checks the functionality of various system components during power-up. In the context of the given question, the PBIT specifically reduces the exposure of the flight control system to latent faults. This means that the PBIT ensures that the flight control system remains capable of executing its functions by detecting and addressing any potential faults or issues.Rate this question:
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- 38.
The Electrical PBIT provides detection of out-of-tolerance conditions and failures in the ...
- A.
FCMs, HS-ACE and E-ACEs.
- B.
FCMs, P-ACEs and SF-ACEs.
- C.
FCMs, P-ACEs and S-ACEs.
Correct Answer
B. FCMs, P-ACEs and SF-ACEs.Explanation
The correct answer is FCMs, P-ACEs and SF-ACEs. The Electrical PBIT is responsible for detecting out-of-tolerance conditions and failures in the FCMs (Fuel Control Modules), P-ACEs (Power Amplifier Control Electronics), and SF-ACEs (Signal Filter Amplifier Control Electronics). These components are crucial in the electrical system and their proper functioning is essential for the overall performance and safety of the system.Rate this question:
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- 39.
The Electrical PBIT is automatically performed during power up after the airplane is powered by any AC source and takes approximately _____ to complete. If the FLT CTRL BIT EXPIRED message is displayed, the hydraulic built in test must be performed.
- A.
3 min
- B.
1 min
Correct Answer
A. 3 minExplanation
The Electrical PBIT is a test that is automatically performed during power up after the airplane is powered by any AC source. It takes approximately 3 minutes to complete. If the FLT CTRL BIT EXPIRED message is displayed, it means that the hydraulic built-in test must be performed.Rate this question:
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- 40.
The Electrical PBIT will be interrupted if ...
- A.
Any electric hydraulic pump is turned OFF, if the FCP switches are cycled or if AC power is interrupted while the test is running.
- B.
Any electric hydraulic pump is turned ON, if the FCP switches are cycled or if AC power is interrupted while the test is running.
Correct Answer
B. Any electric hydraulic pump is turned ON, if the FCP switches are cycled or if AC power is interrupted while the test is running.Explanation
If any electric hydraulic pump is turned ON, if the FCP switches are cycled, or if AC power is interrupted while the test is running, the Electrical PBIT will be interrupted.Rate this question:
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- 41.
The Hydraulic PBIT is performed automatically, only on the ground when all three hydraulic systems are pressurized. The test takes ______ to complete and will be interrupted if any flight control surface is moved while the test is in progress.
- A.
3 min
- B.
1 min
Correct Answer
B. 1 minExplanation
The Hydraulic PBIT is a test that is performed automatically on the ground when all three hydraulic systems are pressurized. This test takes 1 minute to complete. It is important to note that if any flight control surface is moved during the test, it will be interrupted.Rate this question:
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- 42.
The FLT CTRL TEST IN PROG Status message is displayed while ...
- A.
Electrical PBIT is in progress.
- B.
Hydraulic PBIT is in progress.
- C.
Electrical and hydraulic PBIT are in progress.
Correct Answer
C. Electrical and hydraulic PBIT are in progress.Explanation
The correct answer is "electrical and hydraulic PBIT are in progress." This means that both the electrical and hydraulic Power-On Built-In Test (PBIT) are currently being conducted. The FLT CTRL TEST IN PROG status message is displayed to indicate that these tests are ongoing.Rate this question:
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- 43.
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.
- A.
The rudder, elevator and stabilizer
- B.
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:
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- 44.
In case of an extremely improbable failure that would render complete loss of normal and emergency electrical power to the FBW, the backup power system, with no pilot intervention, keeps the appropriate number of elevator and rudder actuators operating for at least ________. There is no dedicated message to indicate the failure of this system; therefore there is no flight crew action required if this happens.
- A.
15 min
- B.
30 min
- C.
45 min
Correct Answer
A. 15 minExplanation
In case of an extremely improbable failure that would render complete loss of normal and emergency electrical power to the FBW, the backup power system will keep the appropriate number of elevator and rudder actuators operating for at least 15 minutes. This means that even if there is a failure in the electrical power system, the backup system will ensure that the necessary controls for the elevator and rudder are still functioning for a minimum of 15 minutes. There is no dedicated message to indicate the failure of this system, so the flight crew does not need to take any action if this happens.Rate this question:
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- 45.
The backup battery is charged by the ________ bus during normal operation and consists of sealed lead acid cells with built-in-test (BIT) capability and an internal heater that guarantees the minimum battery temperature.
- A.
DC ESS 2
- B.
DC ESS 3
Correct Answer
B. DC ESS 3Explanation
During normal operation, the backup battery is charged by the DC ESS 3 bus. The backup battery is made up of sealed lead acid cells that have built-in-test capability and an internal heater to ensure that the battery maintains a minimum temperature.Rate this question:
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- 46.
Pitch axis control is by means of ...
- A.
Electro-hydraulic commanded elevators and an electro-mechanical horizontal stabilizer.
- B.
Electro-hydraulic commanded elevators and horizontal stabilizer.
Correct Answer
A. Electro-hydraulic commanded elevators and an electro-mechanical horizontal stabilizer.Explanation
Pitch axis control refers to the control of the aircraft's movement around its lateral axis, which affects its pitch or nose-up/nose-down attitude. This control is achieved through the use of electro-hydraulic commanded elevators, which are responsible for changing the aircraft's pitch by moving the horizontal stabilizer. The horizontal stabilizer itself is operated by an electro-mechanical system. Therefore, the correct answer is that pitch axis control is achieved through the use of both electro-hydraulic commanded elevators and an electro-mechanical horizontal stabilizer.Rate this question:
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- 47.
Pilot’s inputs to the elevators are through the cockpit control columns in ____________________. The elevators can be automatically controlled through the FCM via the autopilot.
- A.
Normal mode
- B.
Normal or direct mode
Correct Answer
B. Normal or direct modeExplanation
In normal or direct mode, the pilot's inputs to the elevators are directly transmitted through the cockpit control columns. This means that the pilot has direct control over the elevators and can manually adjust them as needed. Additionally, in this mode, the elevators can also be controlled automatically through the Flight Control Module (FCM) via the autopilot.Rate this question:
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- 48.
A total of four P-ACE channels are used to independently control each of the _____ PCUs, providing the analog elevator control functions implemented in the P-ACE units.
- A.
Four
- B.
Two
Correct Answer
A. FourExplanation
The correct answer is four. This means that a total of four P-ACE channels are used to independently control each of the PCUs. The P-ACE units implement the analog elevator control functions.Rate this question:
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- 49.
_____ 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.
- A.
Four
- B.
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:
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- 50.
The elevator surfaces are ________________ actuated through the PCU units.
- A.
Electrically
- B.
Hydraulically
Correct Answer
B. HydraulicallyExplanation
The correct answer is "hydraulically". This means that the elevator surfaces are controlled and operated using hydraulic power.Rate this question:
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Mar 22, 2023Quiz Edited by
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Jun 12, 2011Quiz Created by
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