Aircraft Systems

Front 1

Inside each collector cell

Back 1

2 boost pumps,

low level float switch,

quick drain outlet,

fuel capacitance probe,

level control valve,

sump drain

Front 2

Number of fuel drains and where they are in the aircraft

Back 2

Minimum 4 fuel drains, one in each collector cells and one in each transfer manifold

Front 3

Vents in each fuel cell and why vent the cell

Back 3

Two in each cell and to maintain a slight postive pressure in each cell to prevent collapse of the flexible tanks in case negative pressure existed.

Front 4

Boostpump output and pressure

Back 4

Nominal output of 450lbs/h @ a nominal pressure of 22 psi.

Front 5

Secondary function of boostpumps

Back 5

Transfer fuel from feeder cells to collector cell

Front 6

Two advantages of collector cell design

Back 6

1.changes in centre of gravity minimized because both in the center of the aircraft.

2. Possibility of uncovering the boost pump intake during turbulence or extreme nose up/down attitudes are minimized.

Front 7

Location of fuel filter

Back 7

Rear of the engine nacelle between the boostpump output and fuel flow transmitter.

Front 8

When is the automatic change over system initiated

Back 8

When the pressure @ #1 boostpump falls below 2 psi

Front 9

Maximum number of boostpumps that should be running @ the same time

Back 9

2