644
14 CFR Ch. I (1–1–14 Edition)
§ 27.141
F
LIGHT
C
HARACTERISTICS
§ 27.141
General.
The rotorcraft must—
(a) Except as specifically required in
the applicable section, meet the flight
characteristics requirements of this
subpart—
(1) At the altitudes and temperatures
expected in operation;
(2) Under any critical loading condi-
tion within the range of weights and
centers of gravity for which certifi-
cation is requested;
(3) For power-on operations, under
any condition of speed, power, and
rotor r.p.m. for which certification is
requested; and
(4) For power-off operations, under
any condition of speed and rotor r.p.m.
for which certification is requested
that is attainable with the controls
rigged in accordance with the approved
rigging instructions and tolerances;
(b) Be able to maintain any required
flight condition and make a smooth
transition from any flight condition to
any other flight condition without ex-
ceptional piloting skill, alertness, or
strength, and without danger of ex-
ceeding the limit load factor under any
operating condition probable for the
type, including—
(1) Sudden failure of one engine, for
multiengine rotorcraft meeting Trans-
port Category A engine isolation re-
quirements of Part 29 of this chapter;
(2) Sudden, complete power failure
for other rotorcraft; and
(3) Sudden, complete control system
failures specified in § 27.695 of this part;
and
(c) Have any additional char-
acteristic required for night or instru-
ment operation, if certification for
those kinds of operation is requested.
Requirements for helicopter instru-
ment flight are contained in appendix
B of this part.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–2, 33 FR 962, Jan. 26,
1968; Amdt. 27–11, 41 FR 55468, Dec. 20, 1976;
Amdt. 27–19, 48 FR 4389, Jan. 31, 1983; Amdt.
27–21, 49 FR 44433, Nov. 6, 1984]
§ 27.143
Controllability and maneuver-
ability.
(a) The rotorcraft must be safely con-
trollable and maneuverable—
(1) During steady flight; and
(2) During any maneuver appropriate
to the type, including—
(i) Takeoff;
(ii) Climb;
(iii) Level flight;
(iv) Turning flight;
(v) Autorotation;
(vi) Landing (power on and power
off); and
(vii) Recovery to power-on flight
from a balked autorotative approach.
(b) The margin of cyclic control must
allow satisfactory roll and pitch con-
trol at V
NE
with—
(1) Critical weight;
(2) Critical center of gravity;
(3) Critical rotor r.p.m.; and
(4) Power off (except for helicopters
demonstrating compliance with para-
graph (f) of this section) and power on.
(c) Wind velocities from zero to at
least 17 knots, from all azimuths, must
be established in which the rotorcraft
can be operated without loss of control
on or near the ground in any maneuver
appropriate to the type (such as cross-
wind takeoffs, sideward flight, and
rearward flight)—
(1) With altitude, from standard sea
level conditions to the maximum take-
off and landing altitude capability of
the rotorcraft or 7000 feet density alti-
tude, whichever is less; with—
(i) Critical Weight;
(ii) Critical center of gravity;
(iii) Critical rotor r.p.m.;
(2) For takeoff and landing altitudes
above 7000 feet density altitude with—
(i) Weight selected by the applicant;
(ii) Critical center of gravity; and
(iii) Critical rotor r.p.m.
(d) Wind velocities from zero to at
least 17 knots, from all azimuths, must
be established in which the rotorcraft
can be operated without loss of control
out-of-ground-effect, with—
(1) Weight selected by the applicant;
(2) Critical center of gravity;
(3) Rotor r.p.m. selected by the appli-
cant; and
(4) Altitude, from standard sea level
conditions to the maximum takeoff
and landing altitude capability of the
rotorcraft.
(e) The rotorcraft, after (1) failure of
one engine in the case of multiengine
rotorcraft that meet Transport Cat-
egory A engine isolation requirements,
VerDate Mar<15>2010
10:12 Mar 18, 2014
Jkt 232046
PO 00000
Frm 00654
Fmt 8010
Sfmt 8010
Y:\SGML\232046.XXX
232046
pmangrum on DSK3VPTVN1PROD with CFR