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25 Cards in this Set
- Front
- Back
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Vs1 |
48KIAS |
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Vs0 |
40KIAS |
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Max ramp weight |
2558Ibs |
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Max take off weight |
2550Ibs |
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Maximum baggage allowance |
120Ibs |
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Engine |
Textron Lycoming IO-360-L2A 180BHP@2700RPM Normally aspirated, direct drive, air cooled, horizontally opposed, fuel inject, four cylinder |
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Va |
Maximum speed at which full or abrupt movements may be used without over stressing the airframe |
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Vne |
163KIAS |
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Vno |
129KIAS |
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Va (2550Ibs) |
105KIAS |
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Static RPM range |
2300-2400RPM |
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Power system |
one battery 24V but 28V electrical system Powered by alternator |
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Purpose of the fuel pump |
Prime the engine before start, provide fuel vapour suppression at high altitudes and serve as a back up |
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3 bottom fuel drains |
Fuel selector, fuel reservoir, fuel strainer |
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Where does the excess fuel go? |
Back into the fuel reservoir |
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Oil system |
Wet sump lubrication system |
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How is the alternator driven? |
Belt driven. |
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Which magneto starts the engine? |
L mag |
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Fuel pump |
Engine driven |
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How many fuel vents are there |
3 - fuel caps + behind |
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How many total quartz of oil in the aircraft? |
9. Sump max 8 + additional quart in engine oil filter |
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How many spark plugs per cylinder? |
Two. |
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Normal operation |
Both magnetos due to the more complete burning of the mixture |
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Fuel pump |
Gravity feed down to the three position fuel selector valve, onto the reservoir tank. From there, fuel flows through the electrically driven auxiliary fuel pump, through the fuel shutoff valve, the fuel strainer, and to the engine driven fuel pump. From the engine driven fuel pump, fuel is delivered to the fuel/air control unit on the bottom of the engine. The fuel/air control unit meters fuel flow in proportion to induction air flow. After passing through the control unit, metered fuel goes to a fuel distribution valve (flow divider) located on the top of the engine. From there, individual fuel lines are touted to air bleed type injector nozzles. |
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Battery |
24V main storage battery located inside the engine cowling. |
