579
Federal Aviation Administration, DOT
§ 29.51
silence the audible warning before the
low-speed condition is corrected.
(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c) of the
Dept. of Transportation Act (49 U.S.C.
1655(c)))
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 965, Jan. 26,
1968; Amdt. 29–15, 43 FR 2326, Jan. 16, 1978]
P
ERFORMANCE
§ 29.45
General.
(a) The performance prescribed in
this subpart must be determined—
(1) With normal piloting skill and;
(2) Without exceptionally favorable
conditions.
(b) Compliance with the performance
requirements of this subpart must be
shown—
(1) For still air at sea level with a
standard atmosphere and;
(2) For the approved range of atmos-
pheric variables.
(c) The available power must cor-
respond to engine power, not exceeding
the approved power, less—
(1) Installation losses; and
(2) The power absorbed by the acces-
sories and services at the values for
which certification is requested and ap-
proved.
(d) For reciprocating engine-powered
rotorcraft, the performance, as affected
by engine power, must be based on a
relative humidity of 80 percent in a
standard atmosphere.
(e) For turbine engine-powered rotor-
craft, the performance, as affected by
engine power, must be based on a rel-
ative humidity of—
(1) 80 percent, at and below standard
temperature; and
(2) 34 percent, at and above standard
temperature plus 50
°
F.
Between these two temperatures, the
relative humidity must vary linearly.
(f) For turbine-engine-power rotor-
craft, a means must be provided to per-
mit the pilot to determine prior to
takeoff that each engine is capable of
developing the power necessary to
achieve the applicable rotorcraft per-
formance prescribed in this subpart.
(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c), Dept.
of Transportation Act (49 U.S.C. 1655(c)))
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–15, 43 FR 2326, Jan. 16,
1978; Amdt. 29–24, 49 FR 44436, Nov. 6, 1984]
§ 29.49
Performance at minimum oper-
ating speed.
(a) For each Category A helicopter,
the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which
takeoff data are scheduled—
(1) With not more than takeoff
power;
(2) With the landing gear extended;
and
(3) At a height consistent with the
procedure used in establishing the
takeoff, climbout, and rejected takeoff
paths.
(b) For each Category B helicopter,
the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested, with—
(1) Takeoff power;
(2) The landing gear extended; and
(3) The helicopter in ground effect at
a height consistent with normal take-
off procedures.
(c) For each helicopter, the out-of-
ground effect hovering performance
must be determined over the ranges of
weight, altitude, and temperature for
which certification is requested with
takeoff power.
(d) For rotorcraft other than heli-
copters, the steady rate of climb at the
minimum operating speed must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested with—
(1) Takeoff power; and
(2) The landing gear extended.
[Doc. No. 24802, 61 FR 21898, May 10, 1996; 61
FR 33963, July 1, 1996]
§ 29.51
Takeoff data: general.
(a) The takeoff data required by
§§ 29.53, 29.55, 29.59, 29.60, 29.61, 29.62,
29.63, and 29.67 must be determined—
(1) At each weight, altitude, and tem-
perature selected by the applicant; and
VerDate Sep<11>2014
09:06 Jun 28, 2024
Jkt 262046
PO 00000
Frm 00589
Fmt 8010
Sfmt 8010
Y:\SGML\262046.XXX
262046
jspears on DSK121TN23PROD with CFR
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
VerDate Sep<11>2014
09:06 Jun 28, 2024
Jkt 262046
PO 00000
Frm 00590
Fmt 8010
Sfmt 8010
Y:\SGML\262046.XXX
262046
jspears on DSK121TN23PROD with CFR