EASA Part-66 Module12 helicopter systems foundations cheat sheet
EASA Part-66 Module12 helicopter systems foundations · Keep the key ideas within reach.
Rotary-wing airflow, loads and hub behavior
Declare rotation direction and viewing reference before using left/right rules.
Dissymmetry, flapping and lead-lag are related but distinct concepts.
Autorotation uses airflow rather than engine shaft power to drive the rotor.
Vortex ring state and insufficient available power are different mechanisms.
Response phase and actual operating limits depend on the rotor design.
Controls, power transmission and anti-torque
Collective and cyclic commands change pitch in different patterns.
Stationary and rotating swashplate functions must be distinguished.
Feel, trim, SAS and broader automatic-flight functions have distinct roles.
A hydraulic failure response cannot be inferred from one generic architecture.
Reduction, overrun, shaft support and anti-torque each have separate functions.
Airframe, electrical, fluid and protection systems
Assess the actual helicopter installation and energy sources.
Separate pressure, flow and stored energy.
Electrical indications and system capability are different evidence.
Use the specified fluid, contamination controls and protection procedures.
A theory example does not authorize servicing or release.
Rotor inspection, vibration and usage evidence
Tracking, mass balance and dynamic vibration are distinct checks.
Retain the frequency reference for the actual rotor or component.
Inspection method and acceptance criteria depend on material and defect.
Life status and event history remain relevant even with a clean exterior.
HUMS and chip detection support evidence without guaranteeing every failure is absent.