Abstract: A compartment based inlet particle separator system for an aircraft that includes an auxiliary power unit (APU) system compartment is provided. The system includes a separation barrier wall, a ram air inlet opening, a diffuser, and an inlet particle separator (IPS). The separation barrier wall is disposed within the APU system compartment and divides the APU system compartment into two compartments. The ram air inlet opening is formed one of the compartments. The diffuser receives ram air from a ram air inlet opening and discharges ram air into a compartment. The IPS is disposed within the a compartment between the diffuser outlet and the APU air inlet port.

Abstract: A compartment based inlet particle separator system for an aircraft that includes an auxiliary power unit (APU) system compartment is provided. The system includes a separation barrier wall, a ram air inlet opening, a diffuser, and an inlet particle separator (IPS). The separation barrier wall is disposed within the APU system compartment and divides the APU system compartment into two compartments. The ram air inlet opening is formed one of the compartments. The diffuser receives ram air from a ram air inlet opening and discharges ram air into a compartment. The IPS is disposed within the a compartment between the diffuser outlet and the APU air inlet port.

Abstract: An outer fuel access tank cover (FTAC) of an aircraft, a wing including such outer FTAC of an aircraft, and an aircraft are disclosed. The outer FTAC of an aircraft is related to designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank.

Abstract: An outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft are provided. In one example, an outer fuel tank access cover (FTAC) (4) of an aircraft includes an inner surface and an outer surface. The outer FTAC is to cover the outer opening of a void area of a manhole for accessing the interior of a wing of an aircraft in which the interior of the wing comprises a fuel tank. The outer FTAC comprises absorption means adapted for absorbing the impact energy due to an object impacting against the outer FTAC.

Abstract: The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of “designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank”.