642
14 CFR Ch. I (1–1–14 Edition)
§ 27.51
(1) The hovering ceiling must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested, with—
(i) Takeoff power;
(ii) The landing gear extended; and
(iii) The helicopter in-ground effect
at a height consistent with normal
takeoff procedures; and
(2) The hovering ceiling determined
under paragraph (a)(1) of this section
must be at least—
(i) For reciprocating engine powered
helicopters, 4,000 feet at maximum
weight with a standard atmosphere;
(ii) For turbine engine powered heli-
copters, 2,500 feet pressure altitude at
maximum weight at a temperature of
standard plus 22
°
C (standard plus 40
°
F).
(3) The out-of-ground effect hovering
performance must be determined over
the ranges of weight, altitude, and
temperature for which certification is
requested, using takeoff power.
(b) 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.
[Amdt. 27–44, 73 FR 10998, Feb. 29, 2008]
§ 27.51
Takeoff.
The takeoff, with takeoff power and
r.p.m. at the most critical center of
gravity, and with weight from the max-
imum weight at sea level to the weight
for which takeoff certification is re-
quested for each altitude covered by
this section—
(a) May not require exceptional pilot-
ing skill or exceptionally favorable
conditions throughout the ranges of al-
titude from standard sea level condi-
tions to the maximum altitude for
which takeoff and landing certification
is requested, and
(b) Must be made in such a manner
that a landing can be made safely at
any point along the flight path if an
engine fails. This must be dem-
onstrated up to the maximum altitude
for which takeoff and landing certifi-
cation is requested or 7,000 feet density
altitude, whichever is less.
[Amdt. 27–44, 73 FR 10999, Feb. 29, 2008]
§ 27.65
Climb: all engines operating.
(a) For rotorcraft other than heli-
copters—
(1) The steady rate of climb, at
V
Y,
must be determined—
(i) With maximum continuous power
on each engine;
(ii) With the landing gear retracted;
and
(iii) For the weights, altitudes, and
temperatures for which certification is
requested; and
(2) The climb gradient, at the rate of
climb determined in accordance with
paragraph (a)(1) of this section, must
be either—
(i) At least 1:10 if the horizontal dis-
tance required to take off and climb
over a 50-foot obstacle is determined
for each weight, altitude, and tempera-
ture within the range for which certifi-
cation is requested; or
(ii) At least 1:6 under standard sea
level conditions.
(b) Each helicopter must meet the
following requirements:
(1) V
Y
must be determined—
(i) For standard sea level conditions;
(ii) At maximum weight; and
(iii) With maximum continuous
power on each engine.
(2) The steady rate of climb must be
determined—
(i) At the climb speed selected by the
applicant at or below V
NE
;
(ii) Within the range from sea level
up to the maximum altitude for which
certification is requested;
(iii) For the weights and tempera-
tures that correspond to the altitude
range set forth in paragraph (b)(2)(ii) of
this section and for which certification
is requested; and
(iv) With maximum continuous power
on each engine.
(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. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–14, 43 FR 2324, Jan. 16,
1978; Amdt. 27–33, 61 FR 21907, May 10, 1996]
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