Federal Aviation Administration, DOT

Section 29.1091

normal operational 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 speeds established under
Section 29.67(a)(2) or Section 29.67(b). The climb cooling test may be conducted in conjunction with the takeoff cooling test of
Section 29.1047.

spaschal on DSK3GDR082PROD with CFR

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-26, 53 FR 34218, Sept. 2,
1988]

Section 29.1047 Takeoff cooling test procedures.
(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 Section 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 Section 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 Section 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 Section 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 occurance 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.
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-1, 30 FR 8778, July 13,
1965; Amdt. 29-26, 53 FR 34219, Sept. 2, 1988]

Section 29.1049 Hovering cooling test procedures.
The hovering cooling provisions must
be shown - 
(a) At maximum weight or at the
greatest weight at which the rotorcraft
can hover (if less), at sea level, with
the power required to hover but not
more
than
maximum
continuous
power, in the ground effect in still air,
until at least five minutes after the occurrence of the highest temperature recorded; and
(b) With maximum continuous power,
maximum weight, and at the altitude
resulting in zero rate of climb for this
configuration, until at least five minutes after the occurrence of the highest
temperature recorded.
INDUCTION SYSTEM
Section 29.1091

Air induction.

(a) The air induction system for each
engine and auxiliary power unit must
supply the air required by that engine

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