A system comprising: an air data computer, ADC (48; 70; 88) comprising a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output; a first pressure sensing probe (12; 14; 16; 42; 44L; 44R; 64; 66L; 66R; 82; 84L; 84R) comprising a first pressure sensing port for measuring a first pressure of an oncoming airflow about an exterior of an aircraft ; and a second pressure sensing probe (12; 14; 16; 42; 44L; 44R; 64; 66L; 66R; 82; 84L; 84R) having a second pressure port configured to sense a second pressure of the oncoming airflow; wherein the ADC is configured to transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals, wherein the first pressure sensing probe being discrete from and co-located with the ADC: a pneumatic connection (52; 74; 92) joining the first pressure sensing port to the pneumatic port of the ADC such that the pneumatic input is representative of the first pressure; and a second pressure module (46L; 46R; 68L; 68R; 86L; 86R) pneumatically coupled to the second pressure port and configured to output a second pressure signal representative of the second pressure to the ADC via one of the electrical inputs; wherein the system is configured such that the one or more electrical signals are indicative of one or more of the second pressure of the oncoming airflow about the aircraft exterior, a total air temperature of the oncoming airflow, an angle of attack of the aircraft, and an angle of sideslip of the aircraft. an air data computer, ADC (48; 70; 88) comprising a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output; a first pressure sensing probe (12; 14; 16; 42; 44L; 44R; 64; 66L; 66R; 82; 84L; 84R) comprising a first pressure sensing port for measuring a first pressure of an oncoming airflow about an exterior of an aircraft ; and a second pressure sensing probe (12; 14; 16; 42; 44L; 44R; 64; 66L; 66R; 82; 84L; 84R) having a second pressure port configured to sense a second pressure of the oncoming airflow; wherein the ADC is configured to transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals, wherein the first pressure sensing probe being discrete from and co-located with the ADC: a pneumatic connection (52; 74; 92) joining the first pressure sensing port to the pneumatic port of the ADC such that the pneumatic input is representative of the first pressure; and a second pressure module (46L; 46R; 68L; 68R; 86L; 86R) pneumatically coupled to the second pressure port and configured to output a second pressure signal representative of the second pressure to the ADC via one of the electrical inputs; wherein the system is configured such that the one or more electrical signals are indicative of one or more of the second pressure of the oncoming airflow about the aircraft exterior, a total air temperature of the oncoming airflow, an angle of attack of the aircraft, and an angle of sideslip of the aircraft. <EOS>