ADVOKS GLOBAL · KENYA
The Civil Aviation (Environmental Protection Aircraft Noise) Regulations, 2025
78. Test procedures
Edition: 2026-03-03 · In force
78. Test procedures
(1)The test procedures shall be acceptable to the Authority.(2)The test procedures and noise measurements shall be conducted and processed in an approved manner to yield the noise evaluation measure in accordance to subregulation (2)(3)Test conditions and procedures shall be similar to reference conditions and procedures or the acoustic data shall be adjusted, by the methods outlined in the Third Schedule of these regulations for helicopters, to the reference conditions and procedures specified in this chapter.(4)Adjustments for differences between test and reference flight procedures shall not exceed—(a)for take-off: 4.0 EPNdB, of which the arithmetic sum of ∆1 and the term −7.5 log QK/QrKr from ∆2 shall not in total exceed 2.0 EPNdB; and(b)for overflight or approach: 2.0 EPNdB.(5)During the test the average rotor rpm shall not vary from the normal maximum operating rpm by more than ±1.0 per cent throughout the 10 dB-down period.(6)The airspeed of the tilt-rotor shall not vary from the reference airspeed appropriate to the flight demonstration by more than ±9 km/h (±5 kt) throughout the 10 dB-down period.(7)The number of level overflights made with a headwind component shall be equal to the number of level overflights made with a tailwind component.(8)The tilt-rotor shall fly within ±10° or ±20 m (±65 ft), whichever is greater, from the vertical above the reference track throughout the 10 dB-down period (see Figure 8-1).(9)The height of the tilt-rotor shall not vary during overflight from the reference height throughout the 10 dB-down period by more than ±9 m (±30 ft).(10)During the approach noise demonstration the tilt-rotor shall be established on a stabilized constant speed approach within the airspace contained between approach angles of 5.5° and 6.5° throughout the 10 dB-down period.(11)Tests shall be conducted at a tilt-rotor mass not less than 90 per cent of the relevant maximum certificated mass and may be conducted at a mass not exceeding 105 per cent of the relevant maximum certificated mass. For each of the flight conditions, at least one test shall be completed at or above this maximum certificated mass.