EASA Part-66 Module11 aeroplane systems foundations cheat sheet
EASA Part-66 Module11 aeroplane systems foundations · Keep the key ideas within reach.
Structure, controls and landing gear
Trace loads and functions rather than identify a component from one keyword.
Fail-safe and damage tolerance are related but distinct concepts.
Mass balance and aerodynamic balance solve different problems.
Fly-by-wire does not imply identical protection in every mode or aircraft.
Gear, brake and emergency-extension procedures remain aircraft-specific.
Hydraulic, pneumatic and electrical power
Pressure, flow, voltage and current are different observations.
For a stated model, hydraulic force is pressure times effective area.
A PTU transfers available power rather than creating energy.
Inverter and rectifier conversions run in different directions.
Physical breaker reset capability does not authorize an operational reset.
Fuel, icing, fire and oxygen system concepts
Usable quantity, measured flow and derived FMS totals are distinct.
Crossfeed is not automatically tank-to-tank transfer or proof of balance.
Theoretical fuel-time calculations are not operational reserve authorizations.
Ice, fire and oxygen systems require their own equipment-specific procedures.
A test of detection is not a complete test of extinguishing capability.
Fluid power, cabin environment and water systems
Separate pressure, flow and stored energy.
Different valve types perform distinct circuit functions.
Gas-law models require absolute pressure and stated thermal assumptions.
Cabin altitude and differential pressure are different quantities.
Potable-water and waste servicing require effective contamination control.
Maintenance evidence, inspection and controlled work
Match inspection method to material, defect and approved technique.
A repair must restore the correct load path and acceptance criteria.
Cable tension, travel, direction, locking and mass balance are separate checks.
Torque corrections depend on the actual lever geometry.
Records and independent checks provide evidence without replacing the physical task.
Aerodynamics, loading and performance reasoning
State the flight condition before applying its force balance.
Stall depends on angle of attack and the relevant configuration.
Constant-altitude turning increases required lift and model stall speed.
Excess power and excess thrust describe different climb objectives.
Required performance is not proof of available aircraft capability.