Performance (Aeroplanes)

All 241 learning objectives of EASA ATPL(A) subject 032, numbered per the 2020 syllabus as aligned with ECQB 2026. Objectives marked BK are basic knowledge, assessed at your ATO rather than in the central examination. Where a lesson link appears, our course teaches that objective — the map fills in as the course grows.

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032.01GENERAL

66 objectives

032.01.01Performance legislation
032.01.01.01Applicability of airworthiness requirements of CS-23 and CS-25
032.01.01.01.01Describe the application of certification specification (CSs) with regard to the different kinds of aeroplanes.BKlesson
032.01.01.01.02Describe the general differences between aeroplanes certified according to CS-23 and CS-25.BKlesson
032.01.01.02Operational regulations and safety
032.01.01.02.01Describe the basic concept that the applicable operational requirements differ depending on aeroplane performance.BKlesson
032.01.01.02.02Describe the performance classes for commercial air transport according to the applicable operational requirements.lesson
032.01.01.03Performance and safety
032.01.01.03.01State that aeroplane performance required for commercial air transport may limit the weight of a dispatched aeroplane in order to achieve a sufficient level of safety.BKlesson
032.01.01.03.02Describe that the minimum level of safety required for commercial air transport is ensured through the combination of airworthiness requirements and operational limitations, i.e. the more stringent airworthiness requirements of CS-25 enable a wider range of operating conditions for these aeroplanes.BKlesson
032.01.01.04Performance definitions and safety factors
032.01.01.04.01Describe measured performance and explain how it is determined.BKlesson
032.01.01.04.02Describe gross performance.lesson
032.01.01.04.03Describe net performance and safety factors.lesson
032.01.01.04.04Describe that the size of a safety factor depends on the likelihood of the event and the range of the measured performance data.BKlesson
032.01.01.04.05Describe the relationship between net and gross take-off and landing distances, and net and gross climb and descent gradients.lesson
032.01.02General performance theory
032.01.02.02Definitions and terms
032.01.02.02.01Define the terms ‘climb angle’ and ‘climb gradient’.BKlesson
032.01.02.02.02Define the terms ‘flight-path angle’ and ‘flight-path gradient’.BKlesson
032.01.02.02.03Define the terms ‘descent angle’ and ‘descent gradient’.BKlesson
032.01.02.02.04Explain the difference between climb/descent angle and flight-path angle.BKlesson
032.01.02.02.05Define ‘absolute ceiling’.BKlesson
032.01.02.02.06Describe ‘clearway’ and ‘stopway’ according to CS-Definitions.lesson
032.01.02.02.07Describe: take-off run available (TORA); take-off distance available (TODA); accelerate-stop distance available (ASDA); and determine each from given data or appropriate aerodrome charts.lesson
032.01.02.02.08Describe ‘screen height’ including its various values.lesson
032.01.02.02.09Define the terms ‘range’ and ‘endurance’.BKlesson
032.01.02.02.10Define an aeroplane’s ‘specific range’ (SR) in terms of nautical air miles (NAM) per unit of fuel, and ‘specific range over the ground’ (SRG) in terms of nautical ground miles (NGM) per unit of fuel.lesson
032.01.02.02.11Define the power available and power required.lesson
032.01.02.03Variables influencing performance
032.01.02.03.01Name the following factors that affect aeroplane performance: pressure altitude and temperature, wind, aeroplane weight, aeroplane configuration, aeroplane anti-skid status, aeroplane centre of gravity (CG), aerodrome runway surface, and aerodrome runway slope.BKlesson
032.01.02.03.02Describe how, for different density altitudes, the thrust and power available vary with speed for a propeller-driven aeroplane.BKlesson
032.01.02.03.03Describe how, for different density altitudes, the thrust and power available vary with speed for a turbojet aeroplane.BKlesson
032.01.02.03.04Describe how, for different density altitudes, the drag and power required vary with indicated airspeeds (IAS) and true airspeeds (TAS).lesson
032.01.02.03.05Describe how, for different aeroplane weights and configurations, the drag and power required vary with IAS and TAS.lesson
032.01.03Level flight, range and endurance
032.01.03.01Steady level flight
032.01.03.01.01Explain how drag (thrust) and power required vary with speed in straight and level flight.BKlesson
032.01.03.01.02Explain the effect of excess thrust and power on speed in level flight.BKlesson
032.01.03.01.03Interpret the ‘thrust/power required’ and ‘thrust/power available’ curves in straight and level flight.lesson
032.01.03.01.04Describe how the maximum achievable straight and level flight IAS and TAS vary with altitude.lesson
032.01.03.01.05Describe situations in which a pilot may elect to fly for ‘maximum endurance’ or ‘maximum range’.lesson
032.01.03.02Range
032.01.03.02.01Define a turbojet aeroplane’s specific fuel consumption (SFC) and describe how it affects fuel flow and specific range.lesson
032.01.03.02.02Define a propeller-driven aeroplane’s SFC and describe how it affects fuel flow and specific range.lesson
032.01.03.02.03Explain the optimum speed for maximum SR for a turbojet aeroplane in relation to the drag curve.lesson
032.01.03.02.04Explain the optimum speed to achieve maximum SR for a propeller-driven aeroplane in relation to the power required and drag graphs.lesson
032.01.03.02.05Explain the effect of aeroplane weight and CG position on fuel consumption, range and the optimum speed for maximum SR.lesson
032.01.03.02.06State how a turbojet engine’s SFC varies with temperature and thrust setting.lesson
032.01.03.02.07Explain how SR for a turbojet aeroplane varies with altitude and under different meteorological conditions.lesson
032.01.03.02.08Explain how SRG for a propeller-driven aeroplane varies with altitude and under different meteorological conditions.lesson
032.01.03.02.09Explain the effect of weight on the optimum altitude for maximum range.lesson
032.01.03.02.10Describe the effect of wind on SRG and the optimum speed for SRG , when compared to SR, and the optimum speed for SR.lesson
032.01.03.03Maximum endurance
032.01.03.03.01Explain fuel flow in relation to TAS and thrust for a turbojet aeroplane.lesson
032.01.03.03.02State the speed for maximum endurance for a turbojet aeroplane.lesson
032.01.03.03.03Explain fuel flow in relation to TAS and thrust for a propeller-driven aeroplane.lesson
032.01.03.03.04State the speed for maximum endurance for a propeller-driven aeroplane and the disadvantages of holding at this speed (e.g. high angle of attack (AoA) and lack of speed stability).lesson
032.01.03.03.05Explain the effect of wind and altitude on endurance, and the maximum endurance speed for a turbojet aeroplane.lesson
032.01.03.03.06Explain the effect of wind and altitude on endurance, and the maximum endurance speed for a propeller-driven aeroplane.lesson
032.01.03.03.07Describe the benefits of managing your en-route airspeed to reduce or avoid holding time, and the operational situations when it could be used (commanded by the pilot or air traffic control (ATC), when delays at arrival airport occur).lesson
032.01.04Climbing
032.01.04.01Climbing (climb performance)
032.01.04.01.01Resolve the forces during a steady climb.lesson
032.01.04.01.02Define and explain the following terms: critical engine; speed for best angle of climb (VX); speed for best rate of climb (VY).lesson
032.01.04.01.03Explain climb performance in relation to the thrust available and thrust required (angle of climb), and power available and power required (rate of climb).lesson
032.01.04.01.04Explain the meaning and effect of ‘excess thrust’ and ‘excess power’ in a steady climb.lesson
032.01.04.01.05Interpret the ‘thrust/power required’ and ‘thrust/power available’ curves in a steady climb.lesson
032.01.04.01.06State the difference between climb angle and gradient.lesson
032.01.04.01.07Explain the effect of weight on the climb angle and rate of climb, and the speed for best angle and best rate of climb.lesson
032.01.04.01.08Explain the effects of pressure altitude and temperature, including an inversion on climb performance (angle and rate of climb).lesson
032.01.04.01.09Explain the effect of configuration on climb performance (angle and rate of climb, and VX and VY).lesson
032.01.04.01.10Describe the effect of engine failure on climb performance (angle and rate of climb, and VX and VY).lesson
032.01.04.01.11Calculate the all-engine and one-engine-out climb gradient from given values of engine thrust and aeroplane drag and weight.lesson
032.01.05Descending
032.01.05.01Descending (descent performance)
032.01.05.01.01Resolve the forces during steady descent and in the glide.lesson
032.01.05.01.02Explain descent performance in relation to thrust available and thrust required (drag), and power available and power required.lesson
032.01.05.01.03Explain the meaning of ‘excess thrust required’ (excess drag) and ‘excess power required’ in a steady descent.lesson
032.01.05.01.04Interpret the ‘thrust/power required’ and ‘thrust/power available’ curves in a steady descent.lesson
032.01.05.01.05Explain the effect of mass, altitude, wind, speed and configuration on the glide descent.lesson
032.01.05.01.06Explain the effect of mass, altitude, wind, speed and configuration on the powered descent.lesson

032.02CS-23/APPLICABLE OPERATIONAL REQUIREMENTS PERFORMANCE CLASS B - THEORY

23 objectives

032.02.01Airworthiness requirements
032.02.01.01Airworthiness requirements and definitions
032.02.01.01.01Define the following speeds: stall speeds VS, VS0 and VS1; rotation speed VR; speed at 50 ft above the take-off surface level; reference landing speed VREF.BKlesson
032.02.01.01.02Describe the limitations on VR, on the speed at 50 ft above the take-off surface and on VREF, and given the appropriate stall speed, estimate the values based on these limitations for a single-engine, class B aeroplane.lesson
032.02.01.01.03Describe the limitations on VR, on the speed at 50 ft above the take-off surface and on VREF, and given the appropriate stall speed, estimate the values based on these limitations for a multi-engine, class B aeroplane.lesson
032.02.01.01.04Describe the European Union airworthiness requirements according to CS-23 relating to aeroplane performance (stall, take-off, climb, landing).BKlesson
032.02.01.01.05Define and identify the critical engine of a multi-engine propeller aeroplane.lesson
032.02.01.01.06Explain the effect of an engine failure on the power required, the total drag (thrust required) and climb performance of a multi-engine aeroplane.lesson
032.02.01.01.07Explain the effect of engine failure on the minimum control speed of a multi-engine aeroplane under given conditions (temperature and pressure altitude).lesson
032.02.03Take-off and landing
032.02.03.01Take-off and landing (definitions and effects)
032.02.03.01.01Define the following distances and masses: take-off distance; landing distance; ground-roll distance; maximum allowed take-off mass; maximum allowed landing mass.BKlesson
032.02.03.01.02Explain the effect of flap-setting on the take-off, landing and ground-roll distances.lesson
032.02.03.01.03Explain the effects of the following runway (RWY) variables on take-off distances: RWY slope; RWY surface conditions: dry, wet and contaminated; RWY elevation.lesson
032.02.03.01.04For both fixed-pitch and constant-speed propeller aeroplanes, explain the effect of airspeed on thrust during the take-off run.lesson
032.02.03.01.05Describe the effects of brake release before take-off power is set on the TOD and ASD.lesson
032.02.03.01.06Explain the effect of wind on take-off and landing distances, and determine the actual headwind/tailwind component given the runway direction, wind speed and direction, by use of wind component graphs, mathematical calculations, and rule of thumb.lesson
032.02.03.01.07Explain why an aeroplane has maximum crosswind limit(s) and determine the crosswind component given the runway direction, wind speed and direction, by use of wind component graphs, mathematical calculations, and rule of thumb.lesson
032.02.03.01.08Explain the percentage of accountability for headwind and tailwind components during take-off and landing calculations.lesson
032.02.03.01.09Explain the effect of runway conditions on the landing distance.lesson
032.02.03.01.10Explain the effects of pressure altitude and temperature on the take-off distance, take-off climb, landing distance and approach climb.lesson
032.02.03.01.11Describe the landing airborne distance and ground-roll distance and estimate the effect on the landing distance when the aeroplane is too fast or too high at the screen.lesson
032.02.03.01.12Describe the take-off flight path for a multi-engine, class B aeroplane.lesson
032.02.03.01.13Describe the dimensions of the take off flight path accountability area (domain).lesson
032.02.04Climb, cruise and descent
032.02.04.01Climb, cruise and descent (requirements and calculations)
032.02.04.01.01Describe the climb and en-route requirements according to the applicable operational requirements.lesson
032.02.04.01.02For a single-engine aeroplane, calculate the expected obstacle clearance (in visual meteorological conditions (VMC)) given gross climb performance, obstacle height and distance from reference zero.lesson
032.02.04.01.03For a single-engine aeroplane, calculate the net glide gradient and net glide distance, given aeroplane altitude, terrain elevation, gross gradient or lift/drag ratio (L/D ratio), and headwind or tailwind component.lesson

032.03CS-23/APPLICABLE OPERATIONAL REQUIREMENTS PERFORMANCE CLASS B - USE OF AEROPLANE PERFORMANCE DATA FOR SINGLE- AND MULTI-ENGINE AEROPLANES

16 objectives

032.03.03Use of aeroplane performance data
032.03.03.01Take-off
032.03.03.01.01Determine the field-length-limited take-off mass and take-off speeds given defactored distance, configuration, pressure altitude, temperature and headwind/tailwind component.lesson
032.03.03.01.02Determine the accelerate-go distance and accelerate-stop distance data.lesson
032.03.03.01.03Determine the ground-roll distance and take-off distance from graphs.lesson
032.03.03.01.04Determine the all-engine-out and critical-engine-out take-off climb data.lesson
032.03.03.01.05Determine take off flight path for a MEP aeroplane of given mass and given airfield conditions, and calculate the obstacle clearance based on the take off flight path.lesson
032.03.03.01.06Determine the minimum headwind or maximum tailwind component required for take-off for a given mass and given airfield conditions.lesson
032.03.03.01.07Given take-off run available (TORA), TODA and ASDA, slope and surface conditions, calculate the defactored distance to be used for commercial air transport using the appropriate take-off graphs.lesson
032.03.03.01.08Calculate the minimum TORA or TODA for commercial air transport given the defactored take-off distance or run, runway surface and slope.lesson
032.03.03.02Climb
032.03.03.02.01Determine rate of climb.lesson
032.03.03.02.02Calculate obstacle clearance climb data.lesson
032.03.03.02.03Determine the still-air and flight-path gradients for given IAS, altitude, temperature, aeroplane weight and, if relevant, wind component.lesson
032.03.03.04Landing
032.03.03.04.01Determine the field-length-limited landing mass and landing speeds given defactored distance, configuration, pressure altitude, temperature and headwind or tailwind component.lesson
032.03.03.04.02Determine landing climb data in the event of balked landing.lesson
032.03.03.04.03Determine landing distance and ground-roll distance for given flap position, aeroplane weight and airfield data.lesson
032.03.03.04.04Calculate, given the landing distance available (LDA), slope and surface type and condition, the defactored distance to be used for commercial air transport using the appropriate landing graphs.lesson
032.03.03.04.05Calculate the minimum landing distance (LD) that must be available for commercial air transport given the defactored landing distance, runway surface and slope.lesson

032.04CS-25/APPLICABLE OPERATIONAL REQUIREMENTS PERFORMANCE CLASS A - THEORY

119 objectives

032.04.01Take-off
032.04.01.01Take-off performance, definitions of and relationships between terms
032.04.01.01.01Explain the forces affecting the aeroplane during the take-off run.BKlesson
032.04.01.01.02State the effects of thrust-to-weight ratio and flap-setting on ground roll.BKlesson
032.04.01.01.03Describe the European Union airworthiness requirements according to CS-25 relating to large aeroplane performance (General and Take-off).lesson
032.04.01.01.04Describe the terms ‘aircraft classification number’ (ACN) and ‘pavement classification number’ (PCN), and the requirements and hazards of operating on aerodrome surfaces with PCNs smaller than the ACNs.lesson
032.04.01.01.05Define and explain the following speeds in accordance with CS-25 or CS-Definitions: reference stall speed (VSR); reference stall speed in a specific configuration (VSR1); 1-g stall speed at which the aeroplane can develop a lift force (normal to the flight path) equal to its weight (VS1g); minimum control speed with critical engine inoperative (VMC); minimum control speed on or near the ground (VMCG); minimum control speed at take-off climb (VMCA); engine failure speed (VEF); take-off decision speed (V1); rotation speed (VR); take-off safety speed (V2); minimum take-off safety speed (V2MIN); minimum unstick speed (VMU); lift-off speed (VLOF); maximum brake energy speed (VMBE); maximum tyre speed (VMax Tyre).lesson
032.04.01.01.06Explain the interdependence between the above-mentioned speeds where relevant.lesson
032.04.01.01.07Define the following distances in accordance with CS-25: take-off run with all engines operating and one-engine- inoperative; take-off distance with all engines operating and one-engine-inoperative; accelerate-stop distance with all engines operating and one-engine-inoperative.lesson
032.04.01.01.08Explain how loss of TORA due to alignment is accounted for.lesson
032.04.01.01.09Explain the effect of the interdependency of relevant speeds in 032 04 01 01 (05) and the situations in which these interdependencies can cause speed and performance restrictions.lesson
032.04.01.02Take-off distances
032.04.01.02.01Explain the effects of the following runway (RWY) variables on take-off distances: RWY slope; RWY surface conditions: dry, wet and contaminated; RWY elevation.lesson
032.04.01.02.02Explain the effects of the following aeroplane variables on take-off distance: aeroplane mass; take-off configuration; bleed-air configurations.lesson
032.04.01.02.03Explain the effects of the following meteorological variables on take-off distances: wind; temperature; pressure altitude.lesson
032.04.01.02.04Explain the consequence of errors in rotation technique on take-off distance: early and late rotation; too high and too low rotation angle; too high and too low rotation rate.lesson
032.04.01.02.05Compare the take-off distance for specified conditions and configuration for all engines operating and one-engine-inoperative.lesson
032.04.01.02.06Explain the effect of using clearway on the field-length-limited take-off mass.lesson
032.04.01.02.07Explain the influence of aeroplane mass, air density and flap settings on V1, V2 and V2MIN and thereby on take-off distance.lesson
032.04.01.02.08Explain the effect of an error in V1 on the resulting one-engine-out take-off distance.lesson
032.04.01.03Accelerate-stop distance
032.04.01.03.01Explain how the accelerate-stop distance is affected by given conditions and configuration for all engines operating and one-engine-inoperative.lesson
032.04.01.03.02Explain the effect of using a stopway on the field-length-limited take-off mass.lesson
032.04.01.03.03Explain the effect of an error in V1 on the resulting accelerate-stop distance.lesson
032.04.01.03.04Explain the effect of runway slope or wind component on the accelerate-stop distance.lesson
032.04.01.03.05Explain how the accelerate-stop distance is determined and discuss the deceleration procedure.lesson
032.04.01.03.06Explain how the accelerate-stop distance is affected by the use of brakes, anti-skid, reverse thrust, ground spoilers (lift dumpers) and by brake energy absorption limits, delayed temperature rise and brake temperature indication.lesson
032.04.01.03.07Explain the hazards of rejecting a take-off from high ground speed or high take-off mass, and how to manage these hazards.BKlesson
032.04.01.04Balanced field length concept
032.04.01.04.01Define the term ‘balanced field length’.BKlesson
032.04.01.04.02Describe the relationship between take-off distance and accelerate-stop distance, and identify on a diagram the balanced field length and balanced V1.lesson
032.04.01.04.03Describe the applicability of a balanced field length.BKlesson
032.04.01.05Unbalanced field length concept
032.04.01.05.01Describe the applicability of an unbalanced field length.BKlesson
032.04.01.05.02Explain the effect of additional stopway on the allowed take-off mass and appropriate V1 when using an unbalanced field.lesson
032.04.01.05.03Explain the effect of additional clearway on the allowed take-off mass and appropriate V1 when using an unbalanced field.lesson
032.04.01.06Field-length-limited take-off mass (FLLTOM)
032.04.01.06.01Explain the factors that affect the FLLTOM.lesson
032.04.01.06.02Explain the concept of a ‘range of V1’ and explain reasons for the placement of the designated V1 towards the faster or slower end of the range.lesson
032.04.01.07Contaminated runways
Remark: See 010 09 02 04 and 071 02 13 02
032.04.01.07.01Define a ‘contaminated runway’, ‘wet runway’, and a ‘dry runway’.lesson
032.04.01.07.02Describe the different types of contamination: wet or water patches, frost-covered, dry snow, wet snow, slush, ice, compacted or rolled snow, frozen ruts or ridges.lesson
032.04.01.07.05Define the different types of hydroplaning.lesson
032.04.01.07.06Explain the difference between the two dynamic hydroplaning speeds and state which of them is the most limiting for an aircraft operating on a wet runway.lesson
032.04.01.07.07State that some wind limitations may apply in case of contaminated runways. Those limitations are to be found in Part B of the Operations Manual - Limitations.lesson
032.04.01.07.08State that the procedures associated with take-off and landing on contaminated runways are to be found in Part B of the Operations Manual - Normal procedures.lesson
032.04.01.07.09State that the performance associated with contaminated runways is to be found in Part B of the Operations Manual - Performance.lesson
032.04.01.08Take-off climb
032.04.01.08.01Explain the difference between the flat-rated and non-flat-rated part in performance charts.lesson
032.04.01.08.02State the differences in climb-gradient requirements for two-, three- and four-engined aeroplanes.lesson
032.04.01.08.03Explain the effects of aeroplane configuration and meteorological conditions on the take-off climb.lesson
032.04.01.08.04Determine the climb-limited take-off mass.lesson
032.04.01.09Obstacle-limited take-off
032.04.01.09.01Describe the operational regulations for obstacle clearance in the net take-off flight path (NTOFP).lesson
032.04.01.09.02Define the actual and NTOFP with one-engine-inoperative in accordance with CS-25.lesson
032.04.01.09.03Explain the effects of aeroplane configuration and meteorological conditions on the obstacle-limited take-off mass.lesson
032.04.01.09.04Describe the segments of the actual take-off flight path.lesson
032.04.01.09.05Describe the changes in the configuration, power, thrust and speed in the NTOFP climb segments.lesson
032.04.01.09.06State the standard maximum bank angle(s) in the first and second segment, and determine the effect on the stall speed and implication on V2.lesson
032.04.01.09.07Explain the influence of airspeed selection, acceleration and turns on the climb gradient.lesson
032.04.01.09.08Describe the European Union airworthiness requirements according to CS-25 relating to aeroplane performance take-off climb and flight path.lesson
032.04.01.10Performance-limited take-off mass (PLTOM) and regulated take-off mass (RTOM) tables
032.04.01.10.01Define PLTOM and RTOM.lesson
032.04.01.10.02Describe the use of RTOM tables or similar to find PLTOM and how this can also be done using an EFB.BKlesson
032.04.01.10.03Interpret what take-off limitation (field length, obstacle, climb, structural, etc.) is restricting a particular RTOM as it is presented in RTOM tables or similar.lesson
032.04.01.10.04Describe why data from an EFB can differ from data derived from RTOM tables or similar.lesson
032.04.01.11Take-off performance on wet and contaminated runways
032.04.01.11.01Explain the differences between the take-off performance determination on a wet or contaminated runway and on a dry runway.lesson
032.04.01.11.02Describe a wet V1 and explain the consequences of using a wet V1.lesson
032.04.01.11.03Describe the hazards, effects and management of operating from a contaminated runway.lesson
032.04.01.11.04Describe displacement drag, impingement drag, and the methods to monitor acceleration.lesson
032.04.01.11.05Explain the benefits and implications of using a derated take-off on a contaminated runway.lesson
032.04.01.12Use of reduced (flexible or flex) and derated thrust
032.04.01.12.01Explain the advantages and disadvantages of using reduced (flex) and derated thrust.lesson
032.04.01.12.02Explain the difference between and principles behind reduced (flex) and derated thrust.lesson
032.04.01.12.03Explain when reduced (flex) and derated thrust may and may not be used.lesson
032.04.01.12.04Explain the effect of using reduced (flex) and derated thrust on take-off performance including take-off speeds, take-off distance, climb performance and obstacle clearance.lesson
032.04.01.12.05Explain the assumed temperature method for determining reduced (flex) thrust performance.lesson
032.04.01.13Take-off performance using different take-off flap settings
032.04.01.13.01Explain the advantages and disadvantages of using different take-off flap settings to optimise the performance-limited take-off mass (PLTOM).lesson
032.04.01.13.02Determine the optimum flap position and PLTOM from given figures.lesson
032.04.01.14Take-off performance using increased V2 speeds (‘improved climb performance’)
032.04.01.14.01Explain the advantages and disadvantages of the increased V2 procedure.lesson
032.04.01.14.02Explain under what circumstances this procedure can be used.lesson
032.04.01.14.03Explain the hazards of the fast V1 and VLOF speeds associated with the increased V2 procedure and how they can be managed.lesson
032.04.01.15Brake-energy and tyre-speed limit
032.04.01.15.01Explain the effects on take-off performance of brake-energy and tyre-speed limits.lesson
032.04.01.15.02Explain under what conditions they are more likely to become limiting.lesson
032.04.02Climb
032.04.02.01Climb techniques
032.04.02.01.01Explain the effect of climbing at constant IAS on: TAS; Mach number; climb gradient; rate of climb.lesson
032.04.02.01.02Explain the effect of climbing at constant Mach number on: TAS; IAS; climb gradient; rate of climb.lesson
032.04.02.01.03Explain the correct sequence of climb speeds for turbojet transport aeroplanes.lesson
032.04.02.01.04Determine the effect on TAS when climbing in and above the troposphere at constant Mach number.lesson
032.04.02.02Influence of variables on climb performance
032.04.02.02.01Explain the effect on the operational speed limit when climbing at constant IAS and at constant Mach number.lesson
032.04.02.02.02Explain the term ‘crossover altitude’ which occurs during the climb speed schedule (IAS–Mach number).lesson
032.04.03Cruise
032.04.03.04Long-range cruise
032.04.03.04.01Define the term ‘long-range cruise’.lesson
032.04.03.04.02Explain the differences between flying at long-range speed and maximum-range speed with regard to fuel-flow and speed stability.lesson
032.04.03.06Cruise altitudes
032.04.03.06.01Define the term ‘optimum cruise altitude’.BKlesson
032.04.03.06.02Explain the factors that affect optimum cruise altitude.lesson
032.04.03.06.03Explain the factors that can affect or limit the maximum operating cruise altitude.lesson
032.04.03.06.04Explain the purpose of, and operational reasons for, a step climb and when such a climb would be initiated for optimum range.lesson
032.04.03.06.05Describe the buffet onset boundary (BOB) and determine the high- and low-speed buffet (speed/Mach number only).lesson
032.04.03.06.06Analyse the influence of bank angle, mass and the 1.3g buffet margin on a step climb.lesson
032.04.03.06.07Describe that the high-speed buffet can occur at speeds slower or faster than MMO.lesson
032.04.03.06.08Explain the reasons why a step climb may not be used (e.g. for short sectors, advantageous winds, avoiding turbulence, and due to air traffic restrictions).lesson
032.04.03.07Cost index (CI)
032.04.03.07.01Describe ‘cost index’.lesson
032.04.03.07.02Describe the reason for economical cruise speed.lesson
032.04.03.07.03Describe the effect of cost index on climb, cruise and descent speeds.lesson
032.04.04En-route one-engine-inoperative
032.04.04.01Drift-down
032.04.04.01.01Describe the determination of en-route flight-path data with one-engine-inoperative in accordance with the CS-25 provision on en-route flight paths.lesson
032.04.04.01.02Describe the minimum obstacle-clearance height prescribed in the applicable operational requirements.lesson
032.04.04.01.03Describe the optimum speed that the pilot should select during drift-down.lesson
032.04.04.01.04Explain the influence of deceleration on the drift-down profiles.lesson
032.04.04.02Influence of variables on the en-route one-engine-inoperative performance
032.04.04.02.01Describe and explain the factors which affect the en-route net drift-down flight path.lesson
032.04.05Descent
032.04.05.01Descent techniques
032.04.05.01.01Explain the effect of descending at constant Mach number.lesson
032.04.05.01.02Explain the effect of descending at constant IAS.lesson
032.04.05.01.03Explain the correct sequence of descent speeds for turbojet transport aeroplanes.lesson
032.04.05.01.04Determine the effect on TAS when descending in and above the troposphere at constant Mach number.lesson
032.04.05.01.05Describe the following limiting speeds for descent: maximum operating speed (VMO); maximum Mach number (MMO).lesson
032.04.05.01.06Explain the effect of a descent at constant Mach number on the margin to low- and high-speed buffet.lesson
032.04.05.02Energy management in the descent
032.04.05.02.01Explain the advantages and principle of a continuous descent.lesson
032.04.05.02.02Describe energy management in terms of chemical, potential and kinetic energy.BKlesson
032.04.05.02.03Describe the effect of increasing/decreasing headwind and tailwind on profile management.lesson
032.04.05.02.04Describe the effect of the Mach number to IAS transition (speed conversion) on profile management.lesson
032.04.05.02.05Describe situations during the descent and approach in which a pilot could find that an aeroplane flies high or fast, and explain how the pilot can manage descent angle/excess energy.lesson
032.04.06Approach and landing
032.04.06.01Approach requirements
032.04.06.01.01Describe the CS-25 requirements for the approach climb (one-engine-inoprative).lesson
032.04.06.01.02Describe the CS-25 requirements for the landing climb.lesson
032.04.06.01.03Explain the effect of temperature and pressure altitude on approach and landing-climb performance.lesson
032.04.06.02Landing-field-length and landing-speed requirements
032.04.06.02.01Describe the landing distance determined according to CS 25 (‘demonstrated’ landing distance).BKlesson
032.04.06.02.02Describe the landing-field-length requirements for dry, wet and contaminated runways and the applicable operational requirements.lesson
032.04.06.02.03Define the ‘landing distance available’ (LDA).BKlesson
032.04.06.02.04Define and explain the following speeds in accordance with CS-25 or CS-Definitions: reference stall speed in the landing configuration (VSR0); reference landing speed (VREF); minimum control speed, approach and landing (VMCL).lesson
032.04.06.03Influence of variables on landing performance
032.04.06.03.01Explain the effect of runway slope, surface conditions and wind on the maximum landing mass for a given landing distance available in accordance with the applicable operational requirements.lesson
032.04.06.03.02Explain the effect on landing distance and maximum allowable landing mass of the following devices affecting deceleration: reverse; anti-skid; ground spoilers or lift dumpers; autobrakes.lesson
032.04.06.03.03Explain the effect of temperature and pressure altitude on the maximum landing mass for a given landing distance available.lesson
032.04.06.03.04Explain the effect of hydroplaning on landing distance required and methods of managing landing on contaminated or wet runways.lesson
032.04.06.04Quick turnaround limit
032.04.06.04.01Describe how brake temperature limits the turnaround times.lesson

032.05CS-25/APPLICABLE OPERATIONAL REQUIREMENTS PERFORMANCE CLASS A - USE OF AEROPLANE PERFORMANCE DATA

17 objectives

032.05.01Take-off
032.05.01.01Take-off (performance data)
032.05.01.01.01Determine from given graphs the field-lenght-limited take-off mass (FLLTOM) and describe situations in which this limitation could be most restrictive for take-off.lesson
032.05.01.01.02Determine from given graphs the climb-limited take-off mass and describe situations in which this limitation could be most restrictive for take-off.lesson
032.05.01.01.03Determine from given graphs the obstacle-limited mass and describe situations in which this limitation could be most restrictive for take-off.lesson
032.05.01.01.04Determine from given graphs the tyre-speed-limited take-off mass.lesson
032.05.01.01.05Determine from given graphs the maximum brake-energy-limited take-off mass.lesson
032.05.01.01.06Determine the take-off V speeds for the actual take-off mass.lesson
032.05.01.01.07Determine the maximum take-off mass using given RTOM tables.lesson
032.05.01.01.08Using RTOM tables, determine the take-off V speeds for the actual take-off weight using appropriate corrections.lesson
032.05.01.01.09Determine the assumed/flex temperature and take-off V speeds using the RTOM tables.lesson
032.05.01.01.10Calculate the break cooling time following a rejected take-off given appropriate data.lesson
032.05.02Drift-down and stabilising altitude
032.05.02.01Drift-down and stabilising altitude (performance data)
032.05.02.01.01Determine the one-engine-out net stabilising altitude (level-off altitude) from given graphs/tables.lesson
032.05.02.01.02Determine the maximum mass at which the net stabilising altitude with one-engine-out clears the highest relevant obstacle by the required clearance margin.lesson
032.05.02.01.03Determine, using drift-down graphs, fuel used, time and distance travelled in a descent from a cruise flight level to a given altitude.lesson
032.05.03Landing
032.05.03.01Landing (performance data)
032.05.03.01.01Determine the field length required for landing with a given landing mass from the aeroplane performance data sheets.lesson
032.05.03.01.02Determine the landing and approach climb-limited landing mass from the aeroplane performance data sheets.lesson
032.05.03.01.03Calculate the maximum allowable landing mass as the lowest of: approach-climb- and landing-climb-limited landing mass; landing-field-length-limited landing mass; structural-limited landing mass.lesson
032.05.03.01.04Determine the brake cooling time for different landing masses using the aeroplane performance data sheets.lesson