Global 7500 Flashcards - Technical Systems Review

Practice flashcards covering Global 7500 systems including hydraulics, electrical, fire protection, and fuel management based on instructor notes.

RAT/bootstrap accumulator pre-charge pressure (15°C)

$1,100 \pm 100\,psi$ when the hydraulic system is depressurized.

Brake accumulators pre-charge pressure

$650 \pm 100\,psi$ when the hydraulic system is depressurized.

Hydraulic fluid cooling method

Heat exchangers located in the fuel tanks.

Single generator hydraulic power (flight)

Operating engine hydraulic pumps (EDP) and a maximum of 2 ACMPs; above $43,000\,ft$, only one ACMP can be powered by the APU generator.

Airplane generated AC power sources

Two $115\,VAC$, $60\,kVA$ engine driven variable frequency generators (VFG), one $115\,VAC$, $60\,kVA$ APU generator, and one $115\,VAC$, $9\,kVA$ Ram air turbine.

Single generator bus shedding

None; a single generator supplies power to all three AC buses, though some high load users (like certain hydraulic pumps) are load shed.

EXT AC AVAIL Annunciator

Indicates external AC power is connected, the power is the correct voltage and frequency, and external power is not on line.

External ground power panel location

Lower body fairing below the right engine.

EXT AC (Normal Mode) powered buses

All AC and DC buses are powered.

AC BUS 1 and 2 priority source

1. Onside engine VFG, 2. APU Generator, 3. External AC Power, 4. Opposite side engine VFG.

Battery rating

$24\,VDC$, $28\,Ah$.

Minimum battery voltage for start

$22\,VDC$.

APU and Main Battery locations

APU battery is in the belly fairing compartment below the baggage bay door; Main battery is in the forward equipment bay in the nose.

Main battery endurance (sole power source)

Minimum of $5\,minutes$.

Battery DISCHARGING indications

Cyan DISCHARGING indication on the ELEC synoptic, cyan BATT DISCHARGING CAS message, or voltage at $24\,VDC$ or less and decreasing.

DC Bus shedding (Single TRU failure)

None; all remain powered.

DC Bus shedding (TRU 1 and 2 failure)

DC BUS 1 and 2 are shed.

Thermal circuit breaker reset (ECB)

No, affected circuit breakers cannot be reset from the Electronic Circuit Breaker Application; they must be manually reset at their location.

CB TRIP CAS message

A cyan CAS message generated when a physical circuit breaker trips.

RAT automatic deployment trigger

In the event of a complete loss of AC power in flight.

RAT stowage

On the ground only by maintenance.

RAT Generator reset

Moving the RAT deployment handle to stow and back to the deploy position.

RAT generator off line speed

Below $147\,kt$.

RAT hydraulic pressure loss speed

$102\,kt$.

RAT powered buses (after generator reset)

AC ESS Bus.

Engine fire detection sensing locations

Accessory gear box, Engine core, and Fixed cowl.

Fire warning system activation

Both paired loops in a section must sense heat, or only one loop if the other is inoperative.

Fire bottle extinguishing agent

Halon.

Engine fire warning indications

L/R ENG FIRE PBA illumination, Red L/R ENG FIRE CAS, FIRE icon in the N1 gauge, aural voice message, and Master Warning PBA flashing red.

L/R ENG FIRE PBA pressed effects

Firewall fuel SOV closes, Engine PRSOV closes, Hydraulic SOV closes, Generator offline, BTL 1 and 2 PBAs arm (AVAIL), and Ignition is disabled.

APU FIRE PBA pressed effects

APU firewall fuel SOV closes, APU fuel control unit shuts off, APU generator offline, APU Bleed Control Valve closes, and BTL 2 squib arms.

Engine shutdown via FIRE PBA

The engine will run for up to $20\,seconds$ to empty the fuel line after the firewall SOV closes; immediate shutdown requires the ENGINE RUN switch.

Ground APU fire auto-shutdown sequence

APU fire warning horn sounds, APU BCV closes, and FIDEEX triggers APU shutdown.

Baggage compartment fire suppression

Smoke detectors provide detection and BTL 1 can be discharged into the compartment.

Max fuel imbalance (Gnd/TO/Lnd)

$600\,lb$ ($266\,kg$).

Max fuel imbalance (Flight)

$1,100\,lb$ ($488\,kg$).

Auto transfer system activation thresholds

$340\,lb$ on the ground; $510\,lb$ in flight when total fuel volume is over $16,000\,lb$.

Refueling limits (Pressure)

Wings: $17,550\,lb$ each; Center: $14,200\,lb$; Aft: $2,550\,lb$; Total: $51,850\,lb$.

Wide cut fuels limitation

Prohibited.

Min fuel for manual wing-to-wing transfer

$2,500\,lb$ per wing tank.

Fuel cross-feed OFF requirements

Selected OFF for Takeoff and Landing, and for normal operations below $10,000\,ft$.

Gravity refueling restrictions

Center and aft tanks cannot be gravity refueled.

Positive fuel tank pressure maintenance

Ram air via NACA scoops on the bottom of each surge tank at the wing tips.

PRV handle pull limit (to avoid spillage)

Do not pull if wing tank quantity is more than $11,300\,lb$ or center tank is more than $12,000\,lb$.

FUEL QTY MISCOMPARE CAS

Amber message indicating a mismatch between FMS calculated fuel and sensed fuel on board.

FRTT (fuel-return-to-tank) automation

Operates above $30,000\,ft$ when wing fuel temperatures are colder than $-20^{\circ}C$; closes when any sensor is $-5^{\circ}C$ or higher or altitude is below $30,000\,ft$.

Primary AC fuel pump operation

When ENGINE RUN switches are ON or the XFEED SOV is selected open.

Auxiliary DC fuel pump operation

Automatically when low pressure is sensed at the AC fuel pump outlet.

Engine fuel SOV location and closure

Located in the engine feed line at the firewall; closed by pressing the associated engine FIRE PBA.