The immediate actions and the technique for identifying the failed engine are:Lowering leading-edge flap differs from lowering trailing-edge flap in that:The centre of gravity (centre of mass) of a body is:The purpose of the constant-speed (variable-pitch) propeller is to:The factors affecting the radius of a looping manoeuvre are:For a body moving on a curved path, centripetal force and centrifugal reaction are:The basic principles of trailing-edge and leading-edge flaps are:The SI units for length, mass, time and temperature are:Weight, load factor, power, altitude, flaps and slats, and contamination affect stalling speed as follows:With increasing altitude in the lower atmosphere, pressure, temperature and density normally:The standard recovery from a stalled condition is:The forces acting in a steady climb are:Control in pitch, roll and yaw is achieved by:The lift formula and the three basic functions within it are:The components lift and drag of the total reaction are defined as:The forces on a propeller blade, the rpm/airspeed relationship and the most effective blade sections are:The principle of airspeed indication and the relationship between IAS, CAS, EAS and TAS are:As the point of stall is reached, the airflow, centre of pressure and attitude change such that:Power absorption and propeller solidity are:A wind of 30 kt blows at 60 degrees to the runway. Resolved into components along and across the runway it is:On a constant-speed propeller aircraft, opening the throttle in cruise with the propeller lever untouched results in:Compared with the flight manual stall speed (maximum weight, power off, flaps up), the stall speed will be lower if:Asymmetric blade effect (P-factor) is:Airspeed and slipstream affect control effectiveness in that:An aircraft stalls at 55 kt IAS at a weight of 1600 kg. At 1900 kg (same configuration) it will stall at approximately:Trim tabs work, and are correctly used, by:The factors affecting lift in low-subsonic flow are:In level flight at a TAS of 120 kt the total drag is 1800 N. The power required is approximately:Lateral and directional stability must be matched because:Streamlining reduces form drag because:Spiral instability, Dutch roll and snaking are:Aspect ratio (AR) is defined as, and affects CL in that:The three aircraft axes, the movements about them and the primary controls are:Absolute ceiling and service ceiling are defined as:The conditions that encourage a wing-drop at the stall are:The forecast temperature at 3000 ft pressure altitude is ISA -8. The ambient temperature is:The effect of induced downwash on angle of attack is that:Runway 20 (magnetic), surface wind 240/28 kt (magnetic). The headwind and crosswind components are approximately:The connection between load factor and the increase in stalling speed is that:The four forces and the conditions for steady straight and level flight are:In level flight at a TAS of 150 kt the total drag is 2200 N. The power required is approximately:Speed, velocity and acceleration are defined as:Runway 16 (magnetic), surface wind 120/18 kt (magnetic). The headwind and crosswind components are approximately:At a TAS of 130 kt in a level turn at 40 degrees of bank, the radius and rate of turn are approximately:Crosswind take-off and landing techniques are:The graphs of CD (against angle of attack) and total drag (against IAS) differ in that:The main methods of achieving aerodynamic control balance are:Control surfaces are aerodynamically balanced because:The drag formula and the three basic functions within it are:An aircraft stalls at 50 kt IAS at a weight of 1100 kg. At 1350 kg (same configuration) it will stall at approximately:Air density is, and is affected by temperature, pressure and humidity in that:The secondary effect of aileron, adverse yaw and its counter-measures, and the secondary effect of rudder are:Skin-friction drag is, and is affected by:Vx, Vy and the normal climb speed are:The power and attitude relationships at various airspeeds in straight and level flight are:A balance tab and an anti-balance tab differ in that:The standard recovery technique from a stall with a wing-drop, and at the onset of the stall, is:The trigonometric functions sine, cosine and tangent of an angle in a right-angled triangle are:At a pressure altitude of 6500 ft the ambient temperature is +20 degrees C. Expressed as a deviation from ISA this is:The general conditions for achieving maximum specific air range are:TODA and clearway, TORA, and ASDA and stopway are defined as:Upwash and downwash in the airflow around a wing are:A wind of 20 kt blows at 40 degrees to the runway. Resolved into components along and across the runway it is:Ground effect is, and relates to take-off and landing in that:In a 60 degree banked level turn the lift vector of 2 units resolves into vertical and horizontal components of:An aircraft climbs at 300 ft/min with a groundspeed of 100 kt. Its climb gradient over the ground is approximately:Bernoulli's theorem and its application to streamline flow around an aerofoil are:The centripetal force required for a turn is generated by:Induced drag originates from, is affected by, and is reduced by:The connection between L/D ratio, glide angle, airspeed and gliding range is that:In straight and level flight the curves of induced drag, parasite ('all other') drag and total drag against IAS are:The approximate bank angle for a rate one turn (3 degrees per second) at a TAS of 120 kt is:
Home / CPL exams / PoF & Performance
Commercial Pilot Licence · Subject 22, AC61-5
NZ CPL Principles of Flight & Performance exam.
PoF and Performance is 45 questions in two hours, and it is the CPL exam where the formulas matter most: the lift equation, load factor in the turn, stall speed with bank, power required, glide range, and the performance charts for take-off, climb, cruise and landing. Our bank of 250 questions covers all 17 sub-topics of Subject 22 of AC61-5, with the working shown for every calculation.
45questions120minutes70%pass mark250in the bank
150syllabus items tested · the questions in the background are from the bank