§3.587 Cooling test procedure for multiengine airplanes—.

(a) Airplanes which meet the minimum one-engine-inoperative climb performance specified in § 3.85 (b). The engine cooling test for these airplanes shall be conducted with the airplane in the configuration specified in § 3.85 (b), except that the operating engine(s) shall be operated at maximum continuous power or at full throttle when above the critical altitude. After stabilizing temperatures in flight, the climb shall be started at the lower of the two following altitudes and shall be continued until at least 5 minutes after the highest temperature has been recorded: (1) 1,000 feet below the engine critical altitude or at the lowest practicable altitude (when applicable). (2) 1,000 feet below the altitude at which the single-engine-inoperative rate of climb is 0.02 Vso2. The climb shall be conducted at a speed not in excess of the highest speed at which compliance with the climb requirement of § 3.85 (b) can be shown. However, if the speed used exceeds the speed for best rate of climb with one engine inoperative, a cylinder head temperature indicator shall be provided as specified in § 3.675. (b) Airplanes which cannot meet the minimum one-engine-inoperative climb performance specified in § 3.85 (b). The engine cooling test for these airplanes shall be the same as in paragraph (a) of this section, except that after stabilizing temperatures in flight, the climb (or descent, in the case of airplanes with zero or negative one-engine-inoperative rate of climb) shall be commenced at as near sea level as practicable and shall be conducted at the best rate-of-climb speed (or the speed of minimum rate of descent, in the case of airplanes with zero or negative one-engine-inoperative rate of climb). LIQUID COOLING SYSTEMS