(a) Category A. For each category A rotorcraft, cooling must be
shown during takeoff and subsequent climb as follows:
(1) Each temperature must be stabilized 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 temperatures have stabilized, a climb must be started at
the lowest practicable altitude and must be conducted with one engine
inoperative.
(3) The operating engines must be at the greatest power for which
approval is sought (or at full throttle when above the critical altitude)
for the same period as this power is used in determining the takeoff
climbout path under §29.59.
(4) At the end of the time interval prescribed in paragraph (b)(3) of
this section, the power must be changed to that used in meeting
§29.67(a)(2) and the climb must be continued for --
(i) Thirty minutes, if 30-minute OEI power is used; or
(ii) At least 5 minutes after the occurrence of the highest temperature
recorded, if continuous OEI power or maximum continuous power is used.
(5) The speeds must be those used in determining the takeoff flight
path under §29.59.
(b) Category B. For each category B rotorcraft, cooling must be
shown during takeoff and subsequent climb as follows:
(1) Each temperature must be stabilized 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 temperatures have stabilized, a climb must be started at
the lowest practicable altitude with takeoff power.
(3) Takeoff power must be used for the same time interval as takeoff
power is used in determining the takeoff flight path under §29.63.
(4) At the end of the time interval prescribed in paragraph (a)(3) of
this section, the power must be reduced to maximum continuous power and
the climb must be continued for at least five minutes after the occurence
of the highest temperature recorded.
(5) The cooling test must be conducted at an airspeed corresponding to
normal operating 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 speed for best
rate of climb with maximum continuous power.