Embraer 190 - Landing Gear And Brakes

If two WOW sensors on the same landing gear leg fail, the PSEMs will activate a logic that prevents the landing gear lever from moving up. This means that even if the pilot tries to retract the landing gear, it will remain in the down position. This is indicated by the LG NO DISPATCH caution message on the EICAS when the airplane is on the ground. In-flight, the failure is recognized by the landing gear lever being stuck in the DOWN position and the EICAS message LG WOW SYS FAIL may be displayed.

The emergency/parking brake has the ability to stop the airplane if a failure happens simultaneously on both hydraulic systems or if both brake control modules fail. This brake serves as a backup system in case of emergencies or failures in the primary braking systems. It provides an additional layer of safety and control to ensure that the airplane can be brought to a stop in critical situations.

To operate in handwheel steering mode, the handwheel steering must be kept pressed. The maximum steering angle allowed in this mode is ± 76°. This means that the steering wheel can be turned up to 76 degrees in either direction when the vessel is traveling at a speed of up to 10 knots.

Touchdown protection is a safety feature in an airplane that prevents the main landing gear brakes from being applied when the airplane is about to touch down. This is important because applying the brakes at this critical moment could result in a loss of control or damage to the landing gear. The touchdown protection is deactivated either three seconds after the Weight-On-Wheels (WOW) system senses the ground or when the wheel speed exceeds 50 kt. This ensures that the brakes are only applied when it is safe to do so, preventing any potential accidents or mishaps during landing.

When the landing gear lever is positioned to the UP position, hydraulic pressure is released for the nose and main landing gear locks, and the respective actuators are pressurized to retract the landing gear. Once the retraction is completed, the landing gear is held in place by uplocks.

The correct answer is "airplane on ground status." This is because when the PSEM (Primary Structural Element Manager) computes a signal of weight on wheels, it means that the airplane is on the ground. In this situation, the SPDA (Secondary Power Distribution Assembly) commands the landing gear lever to lock mechanically in the DOWN position.

The dedicated device inside the nose landing gear bay stops the nose landing gear wheels from spinning.

When the SLAT/FLAP lever is in the 0, 1, 2, 3, or 4 position, the aural warning "LANDING GEAR" is announced and cannot be silenced in specific situations. These situations include when the radio altitude is below 700 ft AGL and either the thrust lever is set below 38° for two operative engines or the thrust lever is set below 57° for a one-engine inoperative condition.

To engage the nose wheel steering system, the hydraulic system 2 needs to be pressurized. Additionally, the external steering disengage switch must be in the engaged position. Finally, the handwheel steering must be pressed and released for rudder pedal steering or kept pressed for handwheel steering.

The correct answer is ± 7°. This means that the maximum steering angle of the rudder pedal can be either 7 degrees to the left or 7 degrees to the right. This range of motion allows for precise control and maneuverability of the aircraft during flight.

The mechanical lock on the landing gear lever is released and allows it to move to the UP position when the weight on wheels signal is no longer valid. This indicates that the airplane is no longer on the ground and has transitioned to an in-flight status.

The statement is incomplete and does not provide enough information to determine if anti skid protection is available or not for the emergency/parking brake system.

The correct answer is anti-skid protection. The emergency/parking brake does not have anti-skid protection, which means that if the wheels lock up while the brake is engaged, there is no mechanism in place to prevent skidding. This can be dangerous, especially in slippery conditions, as skidding can lead to a loss of control of the vehicle.

Upon releasing the handwheel steering, the system reverts to rudder pedal steering mode. This means that when the handwheel steering is no longer being used, the control of the steering is transferred to the rudder pedals. The rudder pedals allow the pilot to control the direction of the aircraft by manipulating the rudder, which is a movable control surface on the vertical tail of the aircraft. Therefore, the correct answer is rudder pedal steering mode.

There are two weight-on-wheels (WOW) proximity sensors installed on each landing gear.

The correct answer is 33%. In this system, the brake control module compares the wheel speed signals between the left and right brakes. If one wheel's speed is 33% or below its associated paired wheel speed, the module commands zero pressure to the slower wheel's brake. This allows for equalization of speed between the wheels.

Fusible plugs are safety devices that are designed to melt and release pressure in case of overheating. In the context of the given question, the fusible plugs are attached to the wheels and they melt when the tire overheats. This helps to relieve the pressure and prevent any potential damage or accidents caused by an overheated tire.

The amber cross-hatched box is a visual indicator used in aviation to show that the landing gear is in transit, meaning it is in the process of being raised or lowered. This is important information for pilots to know the status of the landing gear during takeoff or landing.

The BCM (Brake Control Module) provides several functions during normal operation. It protects the wheels from skidding and locking, ensuring that they maintain traction on the road. It also provides antiskid protection, preventing the wheels from losing traction and improving overall braking performance. Additionally, the BCM automatically applies the brakes to individual wheels as necessary, improving the vehicle's stability and control. Lastly, it provides touchdown protection, which helps to prevent the wheels from locking up when the aircraft touches down during landing. Therefore, the correct answer is that the BCM provides locked wheel protection, antiskid protection, automatic wheel braking, and touchdown protection.

Automatic wheel braking prevents the main landing gear from being retracted with the wheels spinning. This is important because retracting the landing gear while the wheels are still spinning could cause damage to the aircraft and compromise its safety. By automatically applying the brakes, the system ensures that the landing gear is securely locked in place before it is retracted.

The correct answer is "proximity sensors electronic modules" and "proximity sensor electronic module". This suggests that "PSEM" refers to both a singular and plural form of electronic modules used in proximity sensors.

The red DN label inside a red circle and the red UP label inside a red box indicate a discrepancy between the landing gear lever position and the respective landing gear position. This means that there is a difference between the position of the landing gear lever (either up or down) and the actual position of the landing gear itself. This could indicate a problem with the landing gear system or a potential safety issue.

Based on the given answer, there are 2 PSEM (Plane System Equipment Module) installed in the plane.

The emergency/parking brake system has pressure accumulators that are isolated from both normal hydraulic systems. These accumulators are designed to store enough pressure to provide six full-brake applications. This means that the emergency/parking brake system can be used multiple times in emergency situations or for parking purposes before the pressure accumulators need to be recharged.

The correct answer is "airplane stopped" because the hardover test, which is a test of the steering system's ability to move the rudder to its maximum travel, can only be successfully accomplished when the airplane is not in motion. If the first steering engagement is performed while the airplane is taxiing, the test may not be accurately completed and the system may display a "STEER FAIL" message. Therefore, it is important to engage the steering system for the first time after a power up when the airplane is stopped.

The correct answer is "All of above." This means that the free wheel mode is automatically selected when any of the following conditions occur: failure of the Air/Ground signal, nose wheel angle is greater than 76°, or nose wheel steering system failure is detected.

The correct answer is hydraulic system 2. This means that the steer-by-wire control of the airplane nose landing gear is powered by hydraulic system 2 and electronically controlled by the Nosewheel Steering Control Module.

The correct answer is 2 uplock sensors and 2 downlock sensors. This means that each landing gear has two sensors that detect when the gear is locked in the up position and two sensors that detect when the gear is locked in the down position. Having multiple sensors for each position helps to ensure the accuracy and reliability of the gear locking system.

The red cross-hatched box indicates that the respective landing gear is kept in transit and is not locked in the commanded position. This means that the landing gear is not securely in place and may not be ready for landing or takeoff. It suggests that there may be an issue with the landing gear and it needs to be addressed before the aircraft can safely operate.

In the landing and RTO modes, the landing and RTO modes will be disarmed if the selector switch is set to the OFF position, pedal braking is applied, brake control system failure is detected, or either thrust lever is advanced beyond idle during autobrake application.

The brake system has 2 brake control modules (BCM).

Each PSEM (Primary Structural Element Monitor) is responsible for monitoring the total of 6 weight-on-wheels (WOW) proximity sensors. These sensors are installed to determine whether the airplane is on the ground or in flight.

The correct answer is 1 and 2. This means that both option 1 (The Emergency/Parking brake is operated through a handle located on the pedestal control panel) and option 2 (The Emergency/Parking brake is powered by hydraulic systems) are correct. This suggests that the emergency/parking brake can be operated using a handle on the control panel and it is powered by hydraulic systems.

The anti skid protection is deactivated for wheel speeds below 10 kt. This allows the pilot to lock and pivot on a wheel for maneuvering.

The minimum runway width for a 180° turn is 22 mt. This means that in order to safely execute a 180° turn on a runway, the width of the runway should be at least 22 mt. This is necessary to provide enough space for the aircraft to maneuver and complete the turn without any risk of collision or damage. A wider runway would be even better, allowing for more margin of error and ensuring safer operations.

In landing mode, the main landing gear WOW (Weight on Wheels) must indicate that the airplane is on the ground for more than 2 seconds in order to allow the autobrake system to be applied. This ensures that the aircraft has fully touched down and is stable on the runway before the autobrake system engages to assist with braking.

The aural message "AUTOBRAKE" is activated when the "armed" condition (LO, MED, HI or RTO) is changed to "disarmed" by the autobrake module (ABM) or brake control module (BCM) failure during parking, taxiing, takeoff roll or landing.

In the free wheel mode, the airplane steering can be carried out by using the rudder, differential brake, or asymmetrical thrust. The rudder is a control surface on the vertical stabilizer that helps to control the yawing motion of the aircraft. The differential brake is a braking system that allows the pilot to apply different amounts of brake pressure to each wheel independently, helping to steer the aircraft on the ground. Asymmetrical thrust refers to the ability to control the direction of the aircraft by adjusting the power output of the engines on each side.

The correct answer is the 0, 1, 2, 3, and 4 position. This means that if the SLAT/FLAP lever is in any of these positions, the warning inhibition button will silence the aural warning in the event of dual radio altimeter failure.

During autobrake operation, the system provides anti skid protection to prevent the wheels from locking up and skidding, touchdown protection to ensure smooth landing by automatically applying brakes when the aircraft touches down, and locked wheel protection to prevent the wheels from locking up and causing loss of control.

The steering system can be disengaged reverting to free wheel by using the steering disengage button located on both control wheels or the external steering disengage switch located on the external power connection access.

Locked wheel protection is active anytime on the ground and at wheel speeds above 30 kt. This means that the system is designed to prevent the wheels from locking up, which can occur when braking too hard or abruptly. By activating the locked wheel protection, the system helps maintain control and stability of the vehicle, especially during braking maneuvers at higher speeds.

The correct answer is "airplane on ground." This means that if the shock absorber of any landing gear does not extend completely, the Primary Structural Element Monitor (PSEM) will continue to compute a signal indicating that the airplane is on the ground.

The "LANDING GEAR" aural logic is used to check the inputs of thrust lever angle, flap setting, and radio altimeter. This means that the landing gear system is monitoring and verifying these inputs to ensure that they are within the correct parameters for safe landing gear operation. The other inputs, angle of attack and ground speed, are not specifically mentioned as being part of the "LANDING GEAR" aural logic, so they are not included in the correct answer.

In the event of a hydraulic pressure failure, the landing gear can still be extended using the alternate gear extension lever. This lever provides a manual mechanism to extend the landing gear when the hydraulic system is not functioning properly. It allows the pilot to manually release the locks and lower the landing gear using mechanical force. This ensures that the landing gear can be extended even without hydraulic pressure, providing a backup method for safe landing in case of hydraulic failure.

The correct answer is 20 seconds. This means that the indication changes to red 20 seconds after the discrepancy is detected.

The downlock release button bypasses the system protection logic mechanically. This means that it is not done through an electrical process, but rather through a physical mechanism or action.

The aural warning "LANDING GEAR" cannot be silenced when the SLAT/FLAP lever is in a landing position (5 or FULL) regardless of the thrust lever position and radio altitude. This means that even if the thrust lever is at any position and the radio altitude is at any level, the warning will continue to sound until the landing gear is properly extended.

The landing gear override switch is located on the landing gear free fall lever compartment. In the event of a failure of the landing gear lever, this switch can be used to manually extend the landing gear.