(SAL) 25.5 Safe operational and flight characteristics

• ED Decision 2018/005/R found in: CS-25 Amdt 27 - Large Aeroplanes (Jan 2023)

(SAL) 25.5 Safe operational and flight characteristics ED Decision 2018/005/R (a) It must be demonstrated that it is possible to complete a stabilised approach in calm air down to the commencement of the landing flare, followed by a touchdown and landing without displaying any hazardous characteristics for the following conditions (see [AMC to Appendix Q, (SAL) 25.5](#_DxCrossRefBm1709822011)): (1) The selected approach path angle at VREF(SAL) or VREF(SAL)-1 as appropriate; (2) An approach path angle 2° steeper than the selected approach path angle, at VREF(SAL) or VREF(SAL)-1 as appropriate; and (3) The selected approach path angle at VREF(SAL) minus 5 knots or VREF(SAL)-1 minus 5 knots as appropriate. (b) For conditions (a)(1), (a)(2), and (a)(3): (1) The demonstration must be conducted at the most critical weight and centre of gravity, either with all-engines-operating or with the critical engine inoperative, as appropriate; (2) The rate of descent must be reduced to 3 feet per second or less before touchdown; (3) Below a height of 200 ft no action shall be taken to increase power or thrust apart from those small changes which are necessary to maintain an accurate approach; (4) No nose depression by use of longitudinal control shall be made after initiating the flare other than those small changes necessary to maintain a continuous and consistent flare flight path; and (5) The flare, touchdown and landing may not require exceptional piloting skill or alertness. (c) For conditions (a)(1) and (a)(3), the flare must not be initiated above the screen height. (d) For condition (a)(2), it must be possible to achieve an approach path angle 2° steeper than the selected approach path angle in all configurations which exist down to the initiation of the flare, which must not occur above 150 % of the screen height. The flare technique used must be substantially unchanged from that recommended for use at the selected approach path angle. (e) All-engines-operating steep approach. It must be demonstrated that the aeroplane can safely transition from the all-engines-operating steep landing approach to: (1) the all-engines-operating go-around as per standard procedure; and (2) the one-engine- inoperative approach climb configuration with one engine having been made inoperative, for the following conditions: (i) The selected steep approach angle; (ii) An approach speed of VREF(SAL); (iii) The most critical weight and centre of gravity; and (iv) For propeller-powered aeroplanes, the propeller of the inoperative engine shall be at the position it automatically assumes following an engine failure at high power. (f) In addition, for propeller-powered aeroplanes, it must be demonstrated that controllability is maintained following an engine failure at approach power and with the propeller at the position it automatically assumes. (g) The height loss during the manoeuvre required by subparagraph (SAL) 25.5(e) must be determined. (h) It must be demonstrated that the aeroplane is safely controllable during a landing with one engine having been made inoperative during the final stages of an all-engines-operating steep approach for the following conditions: (1) The selected steep approach angle; (2) An approach speed of VREF(SAL); (3) The most critical weight and centre of gravity; and (4) For propeller-powered aeroplanes, the propeller of the inoperative engine shall be at the position it automatically assumes following an engine failure at approach power. (i) One-engine-inoperative steep approach. It must be demonstrated that the aeroplane can safely transition from the one-engine-inoperative steep landing approach to the approach climb configuration for the following conditions: (1) The selected steep approach angle; (2) An approach speed of VREF(SAL)-1; (3) The most critical weight and centre of gravity; and (4) For propeller-powered aeroplanes, the propeller of the inoperative engine may be feathered. [Amdt 25/13] [Amdt 25/21]