JAR 29.1047 Take-off cooling test
procedures
(a) Category A. For each Category A
rotorcraft, cooling must be shown during take-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
JAR 29.1043 (continued) JAR 29.1045(c) (continued)
JAR–29 SECTION 1
5.11.93 1–E–18 Reissued by Change 1
(iii) The maximum weight.
(2) After the temperatures have
stabilised, 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 take-off climbout path
under JAR 29.59.
(4) At the end of the time interval
prescribed in sub-paragraph (b) (3) of this
paragraph, the power must be changed to that
used in meeting JAR 29.67 (a) (2) and the
climb must be continued for –
(i) 30 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 take-off flight path under JAR
29.59.
(b) Category B. For each Category B
rotorcraft, cooling must be shown during take-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 temperatures have
stabilised, a climb must be started at the lowest
practicable altitude with take-off power.
(3) Take-off power must be used for
the same time interval as take-off power is used
in determining the take-off flight path under
JAR 29.63.
(4) At the end of the time interval
prescribed in sub-paragraph (a) (3) of this
paragraph, the power must be reduced to
maximum continuous power and the climb
must be continued for at least 5 minutes after
the occurrence 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.
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