Commission Directive (EU) 2015/996 of 19 May 2015 establishing common noise assessment methods according to Directive 2002/49/EC of the European Parliament and of the Council (Text with EEA relevance) (c. 996)

ANNEX U.K.

Appendix B Flight performance calculations

B11 LANDING APPROACH U.K.

The landing approach calibrated airspeed, V_CA , is related to the landing gross weight by an equation of the same form as equation B-11, namely

(B-24)

where the coefficient D (kt/√lbf) corresponds to the landing flap setting.

The corrected net thrust per engine during descent along the approach glideslope is calculated by solving equation B-12 for the landing weight W and a drag-to-lift ratio R appropriate for the flap setting with landing gear extended. The flap setting should be that typically used in actual operations. During landing approach, the glideslope descent angle γ may be assumed constant. For jet-powered and multi-engine propeller aeroplanes, γ is typically – 3°. For single-engine, propeller-powered aeroplanes, γ is typically – 5°.

The average corrected net thrust is calculated by inverting equation B-12 using K = 1,03 to account for the deceleration inherent in flying a descending flight path into an 8-knot reference headwind at the constant calibrated airspeed given by equation B-24, i.e.

(B-25)

For headwinds other than 8 kt, average corrected net thrust becomes

(B-26)

The horizontal distance covered is calculated by:

(B-27)

(positive since h₁ > h₂ and γ is negative).