Velocity Edge GX570 Manual de usuario descargar pdf (Pagina 11)

August 2011, Preliminary

respective FADEC to deliver high pressure fuel to the

engine. Some of that high pressure fuel from the FDU is

routed back to a motive flow ejector pump in each fuel

tank sump to generate the low pressure fuel supply

required by the FDU and by the one motive flow scav-

enge pump per tank located near each sump. Fuel may

be transferred from tank to tank as needed. A vented

surge tank is integrated near each wing tip.

Fuel levels are monitored by six passive capacitance

probes per wing and one dual channel signal conditioner for

accurate quantity indications which are shown on the multi-

function display. Refueling is accomplished through over

wing filler ports with flush mounted caps.

9.3 Hydraulic System

The hydraulic system is an open-center design providing

1,500 psi (103.4 bar) on demand to operate the landing

gear, speed brakes, and flaps. Two engine-driven

pumps, one located on each engine, supply hydraulic

pressure. Either pump can supply enough pressure and

flow to operate the system. An independent hydraulic

system, driven by an electric motor, operates the wheel

brakes and anti-skid system, and charges the emer-

gency accumulator.

9.4 Electrical System

The M2 electrical power generation and distribution sys-

tem features traditional parallel bus architecture designed

to provide 600 amperes at 29 volts DC from two engine

driven 300 ampere starter/generators. One 44 ampere-

hour nickel cadmium battery is used for initial engine starts

and serves as a limited backup to the generators.

Each generator is connected to a remote digital genera-

tor control unit (GCU) in the tailcone. The two GCUs are

connected to each other to allow proportionate load

sharing. If one generator becomes disabled in flight, the

vapor cycle air conditioning system, if in use, and the

interior electrical equipment, will automatically load shed

to prevent overloading the remaining generator. All other

systems are supplied by the remaining generator

through the respective main and crossfeed busses.

All system controls are located on the left-hand power

switch panel and the indications are displayed on the

MFD EIS window for voltage and generators amperage.

Left and right circuit breaker panels are positioned on

the cockpit sidewall within easy reach of each pilot. A

junction box is accessible through the aft baggage com-

partment. The battery, with quick disconnect, is posi-

tioned just left of the baggage compartment door behind

an easy access panel. An external power receptacle is

provided below the left engine pylon.

A sealed lead acid 24V, 16a-hr auxiliary battery is

installed in the nose over the landing gear well. During

normal operation the battery works in conjunction with

the primary ships battery to allow for all aircraft systems,

including avionics, to be powered on during engine

starts. The auxiliary battery is also used to provide addi-

tional battery capacity during emergency operation.

A 500 watt inverter supplies 110 volt AC power to three

outlets: one in the copilot's sidewall and two in the cabin.

9.5 Pressurization and Environmental Systems

Engine bleed air is tapped to pressurize the M2 cabin.

The pressurization control system automatically sched-

ules cabin altitude and change rate while maintaining a

nominal maximum pressure differential of 8.5 psi. Cabin

altitude and rate of change are automatically managed

by a digital, auto-schedule controller. A nominal maxi-

mum differential pressure of 8.5 psi (.59 bar) permits a

sea level cabin altitude up to 22,027 feet (6,714 m),

increasing to 8,000 feet (2,438 m) at the maximum

cruise altitude of 41,000 feet (12,497 m). The MFD dis-

plays all pressurization parameters and the GTCs pro-

vide pilot interface for entry of landing field elevation.

Engine bleed air is also used to heat the cabin and to

defog the windows. A vapor cycle air conditioning sys-

tem provides cooling and may be operated anytime in

the air, or on the ground when ground power is connect-

ed or when the right engine is running. In flight, the sys-

tem automatically shuts down if one generator falls off

line. A cockpit thermostat permits automatic temperature

control and a five-position flow divider allows proportion-

ing of the airflow.

9.6 Oxygen System

A 50 cubic foot (1.42 m

) oxygen bottle, located in the

nose, is provided with a high pressure gauge and bottle-

mounted pressure regulator. Quick-donning pressure

demand masks with microphones are provided at each

crew seat, while automatic dropout constant-flow oxygen

masks are provided at each passenger seat and above

the toilet. Oxygen flow to the cabin is controlled by a

sequencing regulator valve for optimal passenger usage.

9. SYSTEMS (Continued)

1 2 ... 6 7 8 9 10 11 12 13 14 15 16 ... 23 24

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