EASA Part-66 Module11 aeroplane systems foundations key terms

A design load associated with the maximum expected service condition, distinguished from an unrestricted promise that any repeated loading or damage is harmless.

A design and inspection approach considering the presence and growth of damage before it reaches a critical structural condition.

Control-surface mass distribution used to address inertial effects and flutter susceptibility, distinguished from aerodynamic assistance to the hinge moment.

A tab moving with a stabilator’s trailing-edge direction in the relevant design to increase control feel, rather than merely reduce every pilot force.

A braking-control function responding to wheel behavior to reduce a developing skid, without removing runway, tire or brake-energy limitations.

A device converting hydraulic pressure acting over an effective area into mechanical force or movement under the actual circuit conditions.

A system component storing hydraulic energy through a compressible element, with capacity and use determined by its charge and installation.

A device transferring mechanical power between suitable hydraulic circuits, distinguished from mixing their fluid or creating a new independent energy source.

A valve regulating cabin air escape as part of pressurization control, distinguished from a component directly setting aircraft geometric altitude.

An electrical conversion device producing AC from DC, distinguished from a rectifier that converts in the other direction.

The quantity available for the intended engine supply under the approved definition, distinguished from total capacity or an automatic legal reserve allowance.

A fuel-system path enabling an alternative engine-feed arrangement in the actual design, not necessarily a tank-transfer or equalization function.

The space above liquid fuel in a tank, whose gas composition is relevant to the purpose of a fuel-tank inerting system.

A protective method intended to prevent ice formation under specified conditions, distinguished from removing ice that has already accumulated.

An oxygen source using a chemical reaction after activation, with equipment-specific supply and heat characteristics unlike a simple stored-gas bottle.

Cabin internal pressure minus ambient external pressure, using consistent units and distinguished from the pressure-equivalent cabin altitude.

A protective function permitting the specified response when external pressure would otherwise exceed cabin pressure beyond the allowed difference.

A component controlling system pressure through its defined mechanism, distinguished from an accumulator storing energy or a simple nonreturn valve.

Introduction of unwanted biological, chemical or physical material into drinking-water equipment or supplies, including through incorrect servicing or cross-connections.

Pressure referenced to a vacuum, used in ideal gas-law ratios rather than an unqualified gauge reading referenced to ambient conditions.

A defect connected to the inspected surface, distinguished from a sealed internal defect that a penetrant method cannot independently reveal.

The ability of the specified technique and setup to reveal relevant defects, dependent on calibration, access and defect characteristics rather than method name alone.

The sequence of structural members carrying the specified loads, whose continuity and local stress effects matter when evaluating a repair.

The developed length associated with the bend along the stated neutral-axis model, distinguished from a straight flange length or setback.

The ratio of aerodynamic load to aircraft weight in the stated model, requiring the actual flight condition before inferring turning or stall relationships.

The separation of center of gravity from the aircraft neutral point in the defined convention, associated with longitudinal static stability rather than complete loading approval.

Power available beyond that required for the stated flight condition, associated with climb-rate capability in the relevant performance model.