ESDU Aero F.05.01.01 provides data for the estimation of air loads on flaps and controls. For flaps it is found that the maximum normal load coefficient is substantially independent of aerofoil incidence because it occurs at the maximum permissible speed with flaps fully extended when incidence is low. Therefore for each type of flap (split, slotted, and Fowler) a graph of the normal force coefficient plotted against flap deflection for various flap chord/wing chord ratios is adequate. However the maximum force on controls occurs in manoeuvring flight at high speed and small control deflections. Under those conditions the rate of change of normal force coefficient with control deflection is linear; therefore for controls a graph that plots that rate of change against control chord/wing chord ratio is appropriate. Data were only available for controls for a 9 per cent thick aerofoil. The values of maximum normal load coefficient for split and Fowler flaps are accurate to 0.1. For slotted flaps the data show significant scatter and are plotted for the specific aerofoil sections rather than correlated; there is a strong dependence on slot design that may introduce variations of 0.3. For a split flap with its trailing edge ahead or aft of the aerofoil trailing edge it is suggested a reduction of 5 per cent in normal force coefficient may be expected for a 10 per cent shift in chord in either direction.