Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) Category A. For each Category A rotorcraft, cooling must be shown duri ng t ake-off and subsequent climb as follows:
(1) Each temperature must be stabilised while hovering in ground effect with:
(i) The power necessary for hovering;
(ii) The appropriate cowl flap and shutter settings; and
(iii) The maximum weight.
(2) After the tem peratures have stabilised, a climb must be started at th e lowest practicable altitude and m ust be conducted with one engine inoperative.
(3) The operat ing engi nes m ust be at the greatest power for whi ch approval is sought (or at full throttle wh en above the critical altitude) for the same p eriod as th is p ower is used i n det ermining t he t ake-off cl imbout path under CS 29.59.
(4) At th e en d o f th e time interval prescribed in sub-paragraph (b)(3), t he power must be changed t o t hat used i n meeting CS 29.67(a)(2) and the cl imb m ust be cont inued for:
(i) 30 m inutes, i f 30-m inute OEI power is used; or
(ii) At least 5 m inutes after the occurrence of the highest tem perature recorded, i f cont inuous OEI power or maximum continuous power is used.
(5) The speeds m ust be those used in determining t he t ake-off fl ight pat h under CS 29.59.
(b) Category B. For each Category B rotorcraft, cooling must be shown duri ng t ake-off and subsequent climb as follows:
(1) Each temperature must be stabilised while hovering in ground effect with:
(i) The power necessary for hovering;
(ii) The appropriate cowl flap and shutter settings; and
(iii) The maximum weight.
(2) After the tem peratures have stabilised, a climb must be started at th e lowest practicable altitude with take-off power.
(3) Take-off power must be used for the same time in terval as tak e-off p ower is used in determining t he t ake-off fl ight pat h under CS 29.63.
(4) At th e en d o f th e time interval prescribed in sub-paragraph (a)(3), t he power must be reduced to maximum continuous power and the climb must be cont inued for at l east 5 minutes after the occurrence of the highest temperature recorded.
(5) The cooling t est m ust be conduct ed at an ai rspeed correspondi ng t o norm al operating pract ice for t he configuration being tested. However, i f t he cool ing provi sions are sensitive to rotorcraft sp eed, th e m ost critical airspeed must be used, but need not exceed the speed fo r b est rate of climb with maximum continuous power.
ED Decision 2003/016/RM · Source