Systems Flashcards
Voltage regulation from the generator control unit provides the following
Protection against
Overvoltage, overexcitation, reverse current absorbing power from the generator buses when the gens are not running
Cross start current limiting for second engine starts
Line contactor relay control in the event of an overvoltage -GEN RESET-
Generator paralleling
Flight control system include
Primary
Ailerons elevators and rudder and trim (cables and bell cranks)
Secondary
Flaps (electric motor with horn at 85%)
Systems Stall warning- static system with a weight on wheels electric transducer measures the AOA rudder boost(electric servo activated in an engine torque loss) and yaw damper
Fuel systems pumps and tanks
Boost pump DC low pressure on N1
EDP motive flow and transfer pump
Jet transfer pump (AUX to Nacelle)
Landing gear
Hydraulic electric pump w/ accumulator
Pressure 2775 to 2475 below this accumulator will run and after 14 secs power is removed circuit breaker is shorted
Fluid from the pump flows through the selector valve opens the pressure check valve, and then allows the return fluid to flow into the primary reservoir.
HYD FLUID LOW reservoir optical sensor indicates low fluid but enough to lower the gear
Pneu and suction runs the following
Tail and wing deice Door seal at 4psi Pressure gauge 12-20 Co pilots turn and slip indicator attitude indicator Hobbs meter Heats power pack for the landing gear Window defog Pressure gauge Runs at 18 psi Bleed fail warning Advisory deice on a 10 min timer off the r gen bus
Oxygen system responds when manually armed and deployed under the following conditions
Cabin altitude is greater then 12500 alt auto deploy when armed with light out advisory light at 10000alt if unable to maintain the safety valve will help hold cabin at 13000alt
Pressurization system major components are these
Cabin controller Safety valve Outflow valve Altitude limit controller Landing gear weight on wheels Flow control unit for cabin pressurization temperature that also controllers the air conditioning that requires a compression and N1 above 62% on the left engine compressor and conditioning lever on the file control unit on the throttle housing
Describe the fuel system
Five tank wing with nacelle tanks and box wing tanks fuel is automatically transferred to the center nacelle wing fuel is transferred from the gravity flow automatically and has a check valve that prevents the reverse flow of the fuel there is an anti shiphon valve on each wing that prevents fuel from coming out in flight you can over wing fill the tanks and the AUX tanks must be filled first before the main wings to prevent frozen fuel there is a oil heated fuel heater the fuel is passed by before entering the center nacelle for consumption in the event the fuelXFR caution lights come on its because the center nacelle is low on fuel and must be put into the AUX override to fill the tank back up to an acceptable level if the nacelle is too full the extra fuel will be returned to the wing they the vent line to be used again the total system is 539 gallons and uses 100LL 89 87 purple green red and JP4,5,6 these are limited to 150 hours and 20000 ft with both standby pumps operational.
