CS 29.1045 Climb cooling test procedures

• ED Decision 2003/16/RM found in: CS-29 Amdt 11 - Large Rotercraft (Feb 2023)

CS 29.1045 Climb cooling test procedures ED Decision 2003/16/RM (a) Climb cooling tests must be conducted under this paragraph for: (1) Category A rotorcraft; and (2) Multi-engine Category B rotorcraft for which certification is requested under the Category A powerplant installation requirements, and under the requirements of [CS 29.861(a)](#_DxCrossRefBm1178331973) at the steady rate of climb or descent established under [CS 29.67(b)](#_DxCrossRefBm1178331715). (b) The climb or descent cooling tests must be conducted with the engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components. (c) Each operating engine must: (1) For helicopters for which the use of 30-minute OEI power is requested, be at 30-minute OEI power for 30 minutes, and then at maximum continuous power (or at full throttle, when above the critical altitude); (2) For helicopters for which the use of continuous OEI power is requested, be at continuous OEI power (or at full throttle when above the critical altitude); and (3) For other rotorcraft, be at maximum continuous power (or at full throttle when above the critical altitude). (d) After temperatures have stabilised in flight, the climb must be: (1) Begun from an altitude not greater than the lower of: (i) 305 m (1000 ft) below the engine critical altitude; and (ii) 305 m (1000 ft) below the maximum altitude at which the rate of climb is 0.76 m/s (150 fpm); and (2) Continued for at least 5 minutes after the occurrence of the highest temperature recorded, or until the rotorcraft reaches the maximum altitude for which certification is requested. (e) For Category B rotorcraft without a positive rate of climb, the descent must begin at the all-engine-critical altitude and end at the higher of: (1) The maximum altitude at which level flight can be maintained with one engine operative; and (2) Sea-level. (f) The climb or descent must be conducted at an airspeed representing a normal operational practice for the configuration being tested. However, if the cooling provisions are sensitive to rotorcraft speed, the most critical airspeed must be used, but need not exceed the speeds established under [CS 29.67(a)(2)](#_DxCrossRefBm1178331715) or [29.67(b)](#_DxCrossRefBm1178331715). The climb cooling test may be conducted in conjunction with the take-off cooling test of [CS 29.1047](#_DxCrossRefBm1178332054). CS 29.1045 Climb cooling test procedures ED Decision 2003/16/RM (a) Climb cooling tests must be conducted under this paragraph for: (1) Category A rotorcraft; and (2) Multi-engine Category B rotorcraft for which certification is requested under the Category A powerplant installation requirements, and under the requirements of [CS 29.861(a)](#_DxCrossRefBm1513259572) at the steady rate of climb or descent established under [CS 29.67(b)](#_DxCrossRefBm1513259334). (b) The climb or descent cooling tests must be conducted with the engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components. (c) Each operating engine must: (1) For helicopters for which the use of 30-minute OEI power is requested, be at 30-minute OEI power for 30 minutes, and then at maximum continuous power (or at full throttle, when above the critical altitude); (2) For helicopters for which the use of continuous OEI power is requested, be at continuous OEI power (or at full throttle when above the critical altitude); and (3) For other rotorcraft, be at maximum continuous power (or at full throttle when above the critical altitude). (d) After temperatures have stabilised in flight, the climb must be: (1) Begun from an altitude not greater than the lower of: (i) 305 m (1000 ft) below the engine critical altitude; and (ii) 305 m (1000 ft) below the maximum altitude at which the rate of climb is 0.76 m/s (150 fpm); and (2) Continued for at least 5 minutes after the occurrence of the highest temperature recorded, or until the rotorcraft reaches the maximum altitude for which certification is requested. (e) For Category B rotorcraft without a positive rate of climb, the descent must begin at the all-engine-critical altitude and end at the higher of: (1) The maximum altitude at which level flight can be maintained with one engine operative; and (2) Sea-level. (f) The climb or descent must be conducted at an airspeed representing a normal operational practice for the configuration being tested. However, if the cooling provisions are sensitive to rotorcraft speed, the most critical airspeed must be used, but need not exceed the speeds established under [CS 29.67(a)(2)](#_DxCrossRefBm1513259334) or [29.67(b)](#_DxCrossRefBm1513259334). The climb cooling test may be conducted in conjunction with the take-off cooling test of [CS 29.1047](#_DxCrossRefBm1513259647). #### CS 29.1045 Climb cooling test procedures *ED Decision 2003/16/RM* (a) Climb cooling tests must be conducted under this paragraph for: (1) Category A rotorcraft; and (2) Multi-engine Category B rotorcraft for which certification is requested under the Category A powerplant installation requirements, and under the requirements of [CS 29.861(a)](#_DxCrossRefBm1685772438) at the steady rate of climb or descent established under [CS 29.67(b)](#_DxCrossRefBm1685772180). (b) The climb or descent cooling tests must be conducted with the engine inoperative that produces the most adverse cooling conditions for the remaining engines and powerplant components. (c) Each operating engine must: (1) For helicopters for which the use of 30-minute OEI power is requested, be at 30-minute OEI power for 30 minutes, and then at maximum continuous power (or at full throttle, when above the critical altitude); (2) For helicopters for which the use of continuous OEI power is requested, be at continuous OEI power (or at full throttle when above the critical altitude); and (3) For other rotorcraft, be at maximum continuous power (or at full throttle when above the critical altitude). (d) After temperatures have stabilised in flight, the climb must be: (1) Begun from an altitude not greater than the lower of: (i) 305 m (1000 ft) below the engine critical altitude; and (ii) 305 m (1000 ft) below the maximum altitude at which the rate of climb is 0.76 m/s (150 fpm); and (2) Continued for at least 5 minutes after the occurrence of the highest temperature recorded, or until the rotorcraft reaches the maximum altitude for which certification is requested. (e) For Category B rotorcraft without a positive rate of climb, the descent must begin at the all-engine-critical altitude and end at the higher of: (1) The maximum altitude at which level flight can be maintained with one engine operative; and (2) Sea-level. (f) The climb or descent must be conducted at an airspeed representing a normal operational practice for the configuration being tested. However, if the cooling provisions are sensitive to rotorcraft speed, the most critical airspeed must be used, but need not exceed the speeds established under [CS 29.67(a)(2)](#_DxCrossRefBm1685772180) or [29.67(b)](#_DxCrossRefBm1685772180). The climb cooling test may be conducted in conjunction with the take-off cooling test of [CS 29.1047](#_DxCrossRefBm1685772519).