A system for providing supplemental power and fire suppression on an aircraft having a gas turbine engine, comprising: a turbine configured to convert the energy of a compressed gas into at least one of electrical power, hydraulic power, or pneumatic power; a storage tank configured to store the compressed gas; a fire suppression control valve configured to be coupled between the storage tank and a cargo compartment of the aircraft and having a suppression closed position in which the compressed gas is prevented from flowing to the cargo compartment and a suppression open position in which the compressed gas is ported through the fire suppression control valve to the cargo compartment to suppress a fire; a pump control valve configured to be coupled between the turbine and the storage tank and having a pump closed position in which the compressed gas is prevented from flowing to the turbine and a pump open position in which the compressed gas is ported through the pump control valve to the turbine to cause the turbine to convert the energy of the compressed gas into the at least one of the electrical power, the hydraulic power, or the pneumatic power; and an On Board Inert Gas Generating System, OBIGGS, configured to receive additional pneumatic, hydraulic, or electric power from the gas turbine engine and to generate an inert gas to provide low rate discharge, LRD, fire suppression to the cargo compartment; characterised in that: the system further comprises a controller coupled to the fire suppression control valve and the OBIGGS and configured to control the fire suppression control valve to change from the suppression closed position to the suppression open position in response to determining that the fire exists in the cargo compartment to provide an initial fire knockdown, and to control the OBIGGS to generate the inert gas to provide the LRD fire suppression to the cargo compartment; wherein the controller is further configured to control the pump control valve to be in the pump open position in response to determining that the aircraft lacks power. a turbine configured to convert the energy of a compressed gas into at least one of electrical power, hydraulic power, or pneumatic power; a storage tank configured to store the compressed gas; a fire suppression control valve configured to be coupled between the storage tank and a cargo compartment of the aircraft and having a suppression closed position in which the compressed gas is prevented from flowing to the cargo compartment and a suppression open position in which the compressed gas is ported through the fire suppression control valve to the cargo compartment to suppress a fire; a pump control valve configured to be coupled between the turbine and the storage tank and having a pump closed position in which the compressed gas is prevented from flowing to the turbine and a pump open position in which the compressed gas is ported through the pump control valve to the turbine to cause the turbine to convert the energy of the compressed gas into the at least one of the electrical power, the hydraulic power, or the pneumatic power; and an On Board Inert Gas Generating System, OBIGGS, configured to receive additional pneumatic, hydraulic, or electric power from the gas turbine engine and to generate an inert gas to provide low rate discharge, LRD, fire suppression to the cargo compartment; characterised in that: the system further comprises a controller coupled to the fire suppression control valve and the OBIGGS and configured to control the fire suppression control valve to change from the suppression closed position to the suppression open position in response to determining that the fire exists in the cargo compartment to provide an initial fire knockdown, and to control the OBIGGS to generate the inert gas to provide the LRD fire suppression to the cargo compartment; wherein the controller is further configured to control the pump control valve to be in the pump open position in response to determining that the aircraft lacks power. the system further comprises a controller coupled to the fire suppression control valve and the OBIGGS and configured to control the fire suppression control valve to change from the suppression closed position to the suppression open position in response to determining that the fire exists in the cargo compartment to provide an initial fire knockdown, and to control the OBIGGS to generate the inert gas to provide the LRD fire suppression to the cargo compartment; wherein the controller is further configured to control the pump control valve to be in the pump open position in response to determining that the aircraft lacks power.