643
Federal Aviation Administration, DOT
§ 29.1091
normal operational practice for the
configuration being tested. However, if
the cooling provisions are sensitive to
rotorcraft speed, the most critical air-
speed must be used, but need not ex-
ceed the speeds established under
§ 29.67(a)(2) or § 29.67(b). The climb cool-
ing test may be conducted in conjunc-
tion with the takeoff cooling test of
§ 29.1047.
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–26, 53 FR 34218, Sept. 2,
1988]
§ 29.1047
Takeoff cooling test proce-
dures.
(a)
Category A.
For each category A
rotorcraft, cooling must be shown dur-
ing takeoff and subsequent climb as
follows:
(1) Each temperature must be sta-
bilized 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 sta-
bilized, 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 de-
termining 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 oc-
currence of the highest temperature re-
corded, 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 dur-
ing takeoff and subsequent climb as
follows:
(1) Each temperature must be sta-
bilized 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 sta-
bilized, a climb must be started at the
lowest practicable altitude with take-
off power.
(3) Takeoff power must be used for
the same time interval as takeoff
power is used in determining the take-
off 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 occurance of the
highest temperature recorded.
(5) The cooling test must be con-
ducted at an airspeed corresponding to
normal operating practice for the con-
figuration being tested. However, if the
cooling provisions are sensitive to
rotorcraft speed, the most critical air-
speed must be used, but need not ex-
ceed 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]
§ 29.1049
Hovering cooling test proce-
dures.
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 oc-
currence of the highest temperature re-
corded; 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 min-
utes after the occurrence of the highest
temperature recorded.
I
NDUCTION
S
YSTEM
§ 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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