AIRCRAFT SYSTEMS Sample Clauses

AIRCRAFT SYSTEMS. Environmental Control System The dual environmental control system (ECS) provides the following: A supply of sufficient fresh conditioned air to the cabin, baggage compartment and cockpit; Cabin pressurization; Ventilation and cooling air for the avionics equipment; Auxiliary pressurization; Independent temperature control of cockpit, forward cabin and aft cabin. Each ECS consists of an air cycle machine and powered by the bleed management system. . Conditioned air supply to the cabin is provided by two separate temperature selectors; one temperature selection Date: February 2006, Revision 5 Effectivity: s/n A10-216-9282 and subs SCHEDULE “A” within the cockpit and the others within each cabin zone. Cabin air temperature is sensed in two locations and the signals input to the ECS temperature controller. Conditioned air to the cabin is distributed from ducts on each side of the cabin. Conditioned air for the cockpit is supplied to the roof, side console panels and to the forward cockpit panel. Individual adjustable overhead air vents (xxxxxxx) are installed at each pilot and passenger’s seating position. The cabin pressure system consists of two independent controllers. The controllers automatically command the cabin altitude through their auto schedule, by regulating the electrically actuated outflow valves. Landing altitude is set via the FMS; however, a cockpit panel mounted selector provides an alternate means of choosing landing altitude if the FMS is not used. An independent protection is provided to automatically close the outflow valves, should cabin altitude exceed 14,500 ± 500 ft. In automatic mode, the system controls and maintains a relative cabin pressure altitude not to exceed 4,500 ft. at altitudes up to 45,000 ft., and 5,680 ft. at 51,000 ft., providing appropriate cabin pressure control performance during steady and transient conditions. Cabin differential pressure, cabin pressure altitude and cabin pressure altitude rate of change are indicated on EICAS. A warning is displayed if the cabin pressure altitude exceeds 9,000 ft (for non-high altitude airfield operation). Electrical System Primary electrical power is provided by four (4) 40-kVA alternating current (AC) generators and is distributed and controlled from the AC power center (ACPC). Two generators are coupled to each engine’s auxiliary gearbox. Electrical power can also be provided by a 40/45-kVA in-flight/on-ground generator coupled to the APU. Direct current (DC) electrical power...
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