Day 7 - Flight Controls, Navigation

The LE FLAPS TRANSIT amber light is illuminated until the LEDs are fully extended, which means when the trailing edge flaps are greater than 5 units. This indicates that the flaps are in the process of transitioning from one position to another. Once the flaps are fully extended, the light will no longer be illuminated.

The correct answer is B because the question asks about the hydraulic system that operates the leading edge devices. Since the answer options include only A, B, Stb system, and A and B, and B is the only option that mentions a hydraulic system, it can be inferred that the leading edge devices are normally operated by the hydraulic system mentioned in option B.

The maximum altitude for the flap section is 20,000 ft. This means that the flaps on an aircraft can be extended up to 20,000 ft above ground level. Flaps are aerodynamic surfaces on the wings that can be extended or retracted to change the shape and lift characteristics of the wing. They are typically used during takeoff and landing to increase lift and reduce the aircraft's speed. The maximum altitude for the flap section indicates the highest altitude at which the flaps can still be effectively used.

The trailing edge flaps are primarily operated by the B system, which is the main system. In case of any failure or backup, an electrical motor is used as a secondary option to operate the flaps.

When the IRSs (Inertial Reference Systems) are selected from OFF to ALIGN, the ON DC light momentarily illuminating indicates a short DC power test. This test is conducted to ensure that the DC power is functioning properly. Since no action is required after this test, it suggests that everything is functioning as expected and there is no need for any intervention or troubleshooting.

The yaw damper can disengage if the B system flight control switch is positioned to STBY RUD or OFF. Additionally, if there is a fault in the SMYD (Stability Augmentation and Yaw Damper) system or if the SMYD senses a fault in the yaw damper system or if the yaw damper does not respond to a command, it can also disengage.

The operation of the aileron trim switches repositions the neutral position of the aileron feel and centering unit, which helps to adjust the balance and responsiveness of the ailerons. Additionally, it displaces both control wheels, allowing the pilot to make fine adjustments to the aileron position and control the roll of the aircraft.

The correct answer is 1 to 5. The auto-slat system can operate when the aircraft is airborne with flaps set between 1 and 5 degrees. This means that the auto-slat system is designed to work within this range of flap settings to provide the necessary aerodynamic benefits and improve the aircraft's performance during flight.

The flaps/slats electronic unit (FSEU) provides "skew" detection for the trailing edge (TE) flaps and leading edge (LE) slats, excluding the outer LE slats numbered 1 and 8.

Positioning the VHF NAV Transfer switch to BOTH ON 1 selects the No1 VOR receiver to supply data to both FCCs and displays. This means that the navigation information from the No1 VOR receiver will be used by both Flight Control Computers (FCCs) and displayed on all relevant displays. This allows for redundancy and ensures that both FCCs have access to the same navigation data for accurate navigation and guidance.

The leading edge slats will be at the EXT position until the trailing edge flaps are beyond the 5 flap position.

To initiate a full IRS alignment procedure, the position that should be selected on the IRS control panel is "OFF then NAV." This means that the IRS system should first be turned off and then switched to the NAV (navigation) mode. This sequence allows the system to reset and then begin the alignment process for accurate navigation.

The HDG and WIND displays on the IRS display unit are true.

The flap load relief system is designed to automatically adjust the position of the trailing edge flaps to relieve excessive loads on the aircraft during flight. In this case, the system will move the flaps from 40 to 30 at a speed of 163 knots. This speed is likely determined based on the aircraft's design and engineering specifications to ensure safe and efficient operation.

The primary mode for updating the FMC position is from either GPS receiver. This means that the FMC can receive accurate position information from either the front GPS receiver or the aft GPS receiver. Both receivers are capable of providing the necessary data for updating the FMC position, ensuring accuracy in navigation and flight planning.

When an RTO (Rejected Takeoff) is performed with main gear wheel speed exceeding 60 knots, the spoilers will automatically deploy when the thrust levers are at the Idle position and the reverser is selected. This means that when the pilot reduces the thrust to idle and selects the reverser, the spoilers will deploy automatically to assist in decelerating the aircraft and enhancing braking effectiveness.

After a complete extend/retract cycle of the alternate flap duty, it is important to allow a cooling period before attempting another cycle. The correct cooling period that should be allowed is five minutes. This time is necessary to ensure that the flaps have enough time to cool down and prevent any potential overheating or damage that could occur if another cycle is attempted too soon.

The Mach trim starts to operate at a Mach number of 0.615.

The left IRS (Inertial Reference System) will operate indefinitely in this configuration. Even though the left IRS ON DC light illuminates, as long as AC power is normal, there is no time limit for the left IRS to operate.

When the amber flight control LOW PRESSURE lights are extinguished, it means that the associated flight control switch is in the STBY RUD position and the standby rudder shutoff valve is in motion. This indicates that the standby rudder system is functioning properly and there is no low pressure issue in the flight control system.

The aileron trim position is indicated by the displacement of both control wheels and the scale on the top of each control column. This means that when the aileron trim is adjusted, the position of the control wheels will change and the scale on the control column will show the corresponding trim position. This allows the pilot to visually see the current trim setting of the ailerons.