§29.1045 Climb cooling test procedures

(a) Climb cooling tests must be conducted under this paragraph for: (1) Category A rotorcraft; and (2) Multi-engine Categ ory B ro torcraft for whi ch cert ification i s request ed under the Category A powerpl ant installation require-ments, and under t he requi rements of CS 29.861(a) at the steady rate of cl imb or descent established under CS 29.67(b). (b) The cl imb or descent cool ing t ests must be conduct ed wi th t he engi ne i noperative t hat produces t he m ost adverse cool ing condi tions for the rem aining engi nes and powerplant components. (c) Each operating engine must: (1) For helicopters for which the use of 30-minute OEI power i s request ed, be at 30- minute OEI power for 30 m inutes, 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 i s requested, be at continuous OEI power (or at full throttle when above the critical altitude); and (3) For other rotorcra ft, be at maximum continuous power (or at full throttle when above the critical altitude). (d) After tem peratures h ave stab ilised in flight, the climb must be: (1) Begun from an altitude not greater than the lower of: (i) 305 m (1000 ft ) bel ow t he engine critical altitude; and (ii) 305 m (1000 ft ) bel ow t he maximum altitude at wh ich th e rate o f climb is 0.76 m/s (150 fpm); and (2) Continued for at l east 5 m inutes after the occurrence of the highest tem perature recorded, or until the ro torcraft reaches the maximum altitude for wh ich certificatio n is requested. (e) For Category B rot orcraft wi thout a positive rate of clim b, th e d escent m ust b egin at the all-engine-critical altitu de an d en d at th e higher of: (1) The m aximum altitu de at wh ich level flight can b e m aintained with o ne en gine operative; and (2) Sea-level. (f) The clim b or descent m ust be conducted at an ai rspeed represent ing a norm al operat ional practice for t he confi guration bei ng t ested. 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) or 29.67(b). The cl imb cooling test may be conducted in conjunction with the take-off cooling test of CS 29.1047.