580
14 CFR Ch. I (1–1–24 Edition)
§ 29.53
(2) With the operating engines within
approved operating limitations.
(b) Takeoff data must—
(1) Be determined on a smooth, dry,
hard surface; and
(2) Be corrected to assume a level
takeoff surface.
(c) No takeoff made to determine the
data required by this section may re-
quire exceptional piloting skill or
alertness, or exceptionally favorable
conditions.
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–39, 61 FR 21899, May 10,
1996]
§ 29.53
Takeoff: Category A.
The takeoff performance must be de-
termined and scheduled so that, if one
engine fails at any time after the start
of takeoff, the rotorcraft can—
(a) Return to, and stop safely on, the
takeoff area; or
(b) Continue the takeoff and
climbout, and attain a configuration
and airspeed allowing compliance with
§ 29.67(a)(2).
[Doc. No. 24802, 61 FR 21899, May 10, 1996; 61
FR 33963, July 1, 1996]
§ 29.55
Takeoff decision point (TDP):
Category A.
(a) The TDP is the first point from
which a continued takeoff capability is
assured under § 29.59 and is the last
point in the takeoff path from which a
rejected takeoff is assured within the
distance determined under § 29.62.
(b) The TDP must be established in
relation to the takeoff path using no
more than two parameters; e.g., air-
speed and height, to designate the
TDP.
(c) Determination of the TDP must
include the pilot recognition time in-
terval following failure of the critical
engine.
[Doc. No. 24802, 61 FR 21899, May 10, 1996]
§ 29.59
Takeoff path: Category A.
(a) The takeoff path extends from the
point of commencement of the takeoff
procedure to a point at which the
rotorcraft is 1,000 feet above the take-
off surface and compliance with
§ 29.67(a)(2) is shown. In addition—
(1) The takeoff path must remain
clear of the height-velocity envelope
established in accordance with § 29.87;
(2) The rotorcraft must be flown to
the engine failure point; at which
point, the critical engine must be made
inoperative and remain inoperative for
the rest of the takeoff;
(3) After the critical engine is made
inoperative, the rotorcraft must con-
tinue to the takeoff decision point, and
then attain V
TOSS
;
(4) Only primary controls may be
used while attaining V
TOSS
and while
establishing a positive rate of climb.
Secondary controls that are located on
the primary controls may be used after
a positive rate of climb and V
TOSS
are
established but in no case less than 3
seconds after the critical engine is
made inoperative; and
(5) After attaining V
TOSS
and a posi-
tive rate of a climb, the landing gear
may be retracted.
(b) During the takeoff path deter-
mination made in accordance with
paragraph (a) of this section and after
attaining V
TOSS
and a positive rate of
climb, the climb must be continued at
a speed as close as practicable to, but
not less than, V
TOSS
until the rotorcraft
is 200 feet above the takeoff surface.
During this interval, the climb per-
formance must meet or exceed that re-
quired by § 29.67(a)(1).
(c) During the continued takeoff, the
rotorcraft shall not descend below 15
feet above the takeoff surface when the
takeoff decision point is above 15 feet.
(d) From 200 feet above the takeoff
surface, the rotorcraft takeoff path
must be level or positive until a height
1,000 feet above the takeoff surface is
attained with not less than the rate of
climb required by § 29.67(a)(2). Any sec-
ondary or auxiliary control may be
used after attaining 200 feet above the
takeoff surface.
(e) Takeoff distance will be deter-
mined in accordance with § 29.61.
[Doc. No. 24802, 61 FR 21899, May 10, 1996; 61
FR 33963, July 1, 1996, as amended by Amdt.
29–44, 64 FR 45337, Aug. 19, 1999]
§ 29.60
Elevated heliport takeoff path:
Category A.
(a) The elevated heliport takeoff path
extends from the point of commence-
ment of the takeoff procedure to a
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