Section 27.87
Section 27.87

14 CFR Ch. I (1-1-19 Edition)
Height-speed envelope.

(a) If there is any combination of
height and forward speed (including
hover) under which a safe landing cannot be made under the applicable power
failure condition in paragraph (b) of
this section, a limiting height-speed
envelope must be established (including all pertinent information) for that
condition, throughout the ranges of - 
(1) Altitude, from standard sea level
conditions to the maximum altitude
capability of the rotorcraft, or 7000 feet
density altitude, whichever is less; and
(2) Weight, from the maximum
weight at sea level to the weight selected by the applicant for each altitude covered by paragraph (a)(1) of this
section. For helicopters, the weight at
altitudes above sea level may not be
less than the maximum weight or the
highest weight allowing hovering outof-ground effect, whichever is lower.
(b) The applicable power failure conditions are - 
(1) For single-engine helicopters, full
autorotation;
(2) For multiengine helicopters, OEI
(where engine isolation features ensure
continued operation of the remaining
engines), and the remaining engine(s)
within approved limits and at the minimum installed specification power
available for the most critical combination of approved ambient temperature and pressure altitude resulting in
7000 feet density altitude or the maximum altitude capability of the helicopter, whichever is less, and
(3) For other rotorcraft, conditions
appropriate to the type.
(Secs. 313(a), 601, 603, 604, Federal Aviation
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424),
sec. 6(c), 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. 27-21, 49 FR 44433, Nov. 6, 1984;
Amdt. 27-44, 73 FR 10999, Feb. 29, 2008]

FLIGHT CHARACTERISTICS

spaschal on DSK3GDR082PROD with CFR

Section 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 condition within the range of weights and
centers of gravity for which certification 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 exceptional piloting skill, alertness, or
strength, and without danger of exceeding the limit load factor under any
operating condition probable for the
type, including - 
(1) Sudden failure of one engine, for
multiengine rotorcraft meeting Transport Category A engine isolation requirements of Part 29 of this chapter;
(2) Sudden, complete power failure
for other rotorcraft; and
(3) Sudden, complete control system
failures specified in Section 27.695 of this part;
and
(c) Have any additional characteristic required for night or instrument operation, if certification for
those kinds of operation is requested.
Requirements for helicopter instrument 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]

Section 27.143 Controllability and maneuverability.
(a) The rotorcraft must be safely controllable 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;

494

VerDate Sep<11>2014

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00504

Fmt 8010

Sfmt 8010

Y:\SGML\247046.XXX

247046