CS 29.1587 Performance information

• ED Decision 2018/007/R found in: CS-29 Amdt 11 - Large Rotercraft (Feb 2023)

CS 29.1587 Performance information ED Decision 2018/007/R Flight manual performance information which exceeds any operating limitation may be shown only to the extent necessary for presentation clarity or to determine the effects of approved optional equipment or procedures. When data beyond operating limits are shown, the limits must be clearly indicated. The following must be provided: (a) Category A. For each Category A rotorcraft, the rotorcraft flight manual must contain a summary of the performance data, including data necessary for the application of any applicable operating rule, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain – (1) The indicated airspeeds corresponding with those determined for take-off and the procedures to be followed if the critical engine fails during take-off; (2) The airspeed calibrations; (3) The techniques, associated airspeeds, and rates of descent for autorotative landings; (4) The rejected take-off distance determined under [CS 29.62](#_DxCrossRefBm1178331728) and the take-off distance determined under [CS 29.61](#_DxCrossRefBm1178331729); (5) The landing data determined under [CS 29.81](#_DxCrossRefBm1178331749) and [29.85](#_DxCrossRefBm1178331747); (6) The steady gradient of climb for each weight, altitude, and temperature for which take- off data are to be scheduled, along the take-off path determined in the flight conditions required in [CS 29.67(a)(1) and (a)(2)](#_DxCrossRefBm1178331715): (i) In the flight conditions required in [CS 29.67(a)(1)](#_DxCrossRefBm1178331715) between the end of the take-off distance and the point at which the rotorcraft is 61 m (200 ft) above the take-off surface (or 61 m (200 ft) above the lowest point of the take-off profile for elevated heliports). (ii) In the flight conditions required in [CS 29.67(a)(2)](#_DxCrossRefBm1178331715) between the points at which the rotorcraft is 61 m (200 ft) and 305 m (1000 ft) above the take-off surface (or 61 m (200 ft) and 305 m (1000 ft) above the lowest point of the take-off profile for elevated heliports). (7) Hover performance determined under [CS 29.49](#_DxCrossRefBm1178331725) and the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts. (b) Category B. For each Category B rotorcraft, the Rotorcraft Flight Manual must contain: (1) The take-off distance and the climbout speed together with the pertinent information defining the flight path with respect to autorotative landing if an engine fails, including the calculated effects of altitude and temperature; (2) The steady rates of climb and hovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated effects of altitude and temperature; (3) The landing distance, appropriate airspeed and type of landing surface, together with any pertinent information that might affect this distance, including the effects of weight, altitude and temperature; (4) The maximum safe wind for operation near the ground; (5) The airspeed calibrations; (6) The height-speed envelope except for rotorcraft incorporating this as an operating limitation; (7) Glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide angle, as determined in [CS 29.71](#_DxCrossRefBm1178331745); (8) Hover performance determined under [CS 29.49](#_DxCrossRefBm1178331725) and the maximum safe wind demonstrated under the ambient conditions for data presented. In addition, the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts; and (9) Any additional performance data necessary for the application of any applicable operating rule. (c) The RFM must contain the substantiated sea conditions and any associated information relating to the certification obtained with ditching or emergency flotation provisions. [Amdt No: 29/1] [Amdt No: 29/2] [Amdt No: 29/5] CS 29.1587 Performance information ED Decision 2018/007/R Flight manual performance information which exceeds any operating limitation may be shown only to the extent necessary for presentation clarity or to determine the effects of approved optional equipment or procedures. When data beyond operating limits are shown, the limits must be clearly indicated. The following must be provided: (a) Category A. For each Category A rotorcraft, the rotorcraft flight manual must contain a summary of the performance data, including data necessary for the application of any applicable operating rule, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain – (1) The indicated airspeeds corresponding with those determined for take-off and the procedures to be followed if the critical engine fails during take-off; (2) The airspeed calibrations; (3) The techniques, associated airspeeds, and rates of descent for autorotative landings; (4) The rejected take-off distance determined under [CS 29.62](#_DxCrossRefBm1513259347) and the take-off distance determined under [CS 29.61](#_DxCrossRefBm1513259348); (5) The landing data determined under [CS 29.81](#_DxCrossRefBm1513259368) and [29.85](#_DxCrossRefBm1513259366); (6) The steady gradient of climb for each weight, altitude, and temperature for which take- off data are to be scheduled, along the take-off path determined in the flight conditions required in [CS 29.67(a)(1) and (a)(2)](#_DxCrossRefBm1513259334): (i) In the flight conditions required in [CS 29.67(a)(1)](#_DxCrossRefBm1513259334) between the end of the take-off distance and the point at which the rotorcraft is 61 m (200 ft) above the take-off surface (or 61 m (200 ft) above the lowest point of the take-off profile for elevated heliports). (ii) In the flight conditions required in [CS 29.67(a)(2)](#_DxCrossRefBm1513259334) between the points at which the rotorcraft is 61 m (200 ft) and 305 m (1000 ft) above the take-off surface (or 61 m (200 ft) and 305 m (1000 ft) above the lowest point of the take-off profile for elevated heliports). (7) Hover performance determined under [CS 29.49](#_DxCrossRefBm1513259344) and the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts. (b) Category B. For each Category B rotorcraft, the Rotorcraft Flight Manual must contain: (1) The take-off distance and the climbout speed together with the pertinent information defining the flight path with respect to autorotative landing if an engine fails, including the calculated effects of altitude and temperature; (2) The steady rates of climb and hovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated effects of altitude and temperature; (3) The landing distance, appropriate airspeed and type of landing surface, together with any pertinent information that might affect this distance, including the effects of weight, altitude and temperature; (4) The maximum safe wind for operation near the ground; (5) The airspeed calibrations; (6) The height-speed envelope except for rotorcraft incorporating this as an operating limitation; (7) Glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide angle, as determined in [CS 29.71](#_DxCrossRefBm1513259364); (8) Hover performance determined under [CS 29.49](#_DxCrossRefBm1513259344) and the maximum safe wind demonstrated under the ambient conditions for data presented. In addition, the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts; and (9) Any additional performance data necessary for the application of any applicable operating rule. (c) The RFM must contain the substantiated sea conditions and any associated information relating to the certification obtained with ditching or emergency flotation provisions. [Amdt No: 29/1] [Amdt No: 29/2] [Amdt No: 29/5] #### CS 29.1587 Performance information *ED Decision 2018/007/R* Flight manual performance information which exceeds any operating limitation may be shown only to the extent necessary for presentation clarity or to determine the effects of approved optional equipment or procedures. When data beyond operating limits are shown, the limits must be clearly indicated. The following must be provided: (a) *Category A.* For each Category A rotorcraft, the rotorcraft flight manual must contain a summary of the performance data, including data necessary for the application of any applicable operating rule, together with descriptions of the conditions, such as airspeeds, under which this data was determined, and must contain – (1) The indicated airspeeds corresponding with those determined for take-off and the procedures to be followed if the critical engine fails during take-off; (2) The airspeed calibrations; (3) The techniques, associated airspeeds, and rates of descent for autorotative landings; (4) The rejected take-off distance determined under [CS 29.62](#_DxCrossRefBm1685772193) and the take-off distance determined under [CS 29.61](#_DxCrossRefBm1685772194); (5) The landing data determined under [CS 29.81](#_DxCrossRefBm1685772214) and [29.85](#_DxCrossRefBm1685772212); (6) The steady gradient of climb for each weight, altitude, and temperature for which take- off data are to be scheduled, along the take-off path determined in the flight conditions required in [CS 29.67(a)(1) and (a)(2)](#_DxCrossRefBm1685772180): (i) In the flight conditions required in [CS 29.67(a)(1)](#_DxCrossRefBm1685772180) between the end of the take-off distance and the point at which the rotorcraft is 61 m (200 ft) above the take-off surface (or 61 m (200 ft) above the lowest point of the take-off profile for elevated heliports). (ii) In the flight conditions required in [CS 29.67(a)(2)](#_DxCrossRefBm1685772180) between the points at which the rotorcraft is 61 m (200 ft) and 305 m (1000 ft) above the take-off surface (or 61 m (200 ft) and 305 m (1000 ft) above the lowest point of the take-off profile for elevated heliports). (7) Hover performance determined under [CS 29.49](#_DxCrossRefBm1685772190) and the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts. (b) *Category B.* For each Category B rotorcraft, the Rotorcraft Flight Manual must contain: (1) The take-off distance and the climbout speed together with the pertinent information defining the flight path with respect to autorotative landing if an engine fails, including the calculated effects of altitude and temperature; (2) The steady rates of climb and hovering ceiling, together with the corresponding airspeeds and other pertinent information, including the calculated effects of altitude and temperature; (3) The landing distance, appropriate airspeed and type of landing surface, together with any pertinent information that might affect this distance, including the effects of weight, altitude and temperature; (4) The maximum safe wind for operation near the ground; (5) The airspeed calibrations; (6) The height-speed envelope except for rotorcraft incorporating this as an operating limitation; (7) Glide distance as a function of altitude when autorotating at the speeds and conditions for minimum rate of descent and best glide angle, as determined in [CS 29.71](#_DxCrossRefBm1685772210); (8) Hover performance determined under [CS 29.49](#_DxCrossRefBm1685772190) and the maximum safe wind demonstrated under the ambient conditions for data presented. In addition, the maximum weight for each altitude and temperature condition at which the rotorcraft can safely hover in-ground effect and out-of-ground effect in winds of not less than 31 km/h (17 knots) from all azimuths. This data must be clearly referenced to the appropriate hover charts; and (9) Any additional performance data necessary for the application of any applicable operating rule. (c) The RFM must contain the substantiated sea conditions and any associated information relating to the certification obtained with ditching or emergency flotation provisions. [Amdt No: 29/1] [Amdt No: 29/2] [Amdt No: 29/5]