INTRODUCTION This Item provides a method to obtain the increment in pitching moment coefficient at zero angle of attack@ due to deployment of trailing-edge single-slotted flaps at low speeds@ either on an aerofoil or on a wing. For aerofoils the method predicts the centre of lift position@h2@ due to single-slotted flap deployment@ based on the thin-aerofoil theory of Derivation 26 and modified to obtain correlation with the experimental data of Derivations 3@ 4@ 5@ 7@ 8@ 11@ 12@ 14@ 15 and 21. This is combined with the increment in aerofoil lift coefficient calculated from Item No. 94030 (Derivation 2) to estimate the pitching moment coefficient increment. For wings with full-span flaps@ factors@ dependent on planform geometry@ are applied to the pitching moment coefficient increment on a section that is representative of the wing@ to allow for three-dimensional effects. Derivations 27 and 28 were used as the basis for these factors@ with some adjustment to the simple theoretical assumptions. For wings with part-span flaps@ additional factors are introduced that are dependent on taper ratio@ aspect ratio@ sweep and spanwise extent of the flap. Section 3 describes the prediction method and Section 4 discusses Mach number and Reynolds number effects. The applicability and accuracy of the method are addressed in Section 5. The Derivation and References are given in Section 6. Section 7 provides worked examples illustrating the use of the Item for an aerofoil and a wing.