Federal Aviation Administration, DOT

Section 27.75

(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 distance required to take off and climb
over a 50-foot obstacle is determined
for each weight, altitude, and temperature within the range for which certification is requested; or
(ii) At least 1:6 under standard sea
level conditions.
(b) Each helicopter must meet the
following requirements:
(1) VY 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 VNE;
(ii) Within the range from sea level
up to the maximum altitude for which
certification is requested;
(iii) For the weights and temperatures 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 Federal 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)))

spaschal on DSK3GDR082PROD with CFR

[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]

Section 27.67 Climb: one engine inoperative.
For multiengine helicopters, the
steady rate of climb (or descent), at Vy
(or at the speed for minimum rate of
descent), must be determined with - 
(a) Maximum weight;
(b) The critical engine inoperative
and the remaining engines at either - 
(1) Maximum continuous power and,
for helicopters for which certification
for the use of 30-minute OEI power is
requested, at 30-minute OEI power; or

(2) Continuous OEI power for helicopters for which certification for the
use of continuous OEI power is requested.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal 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. 27-23, 53 FR 34210, Sept. 2,
1988]

Section 27.71

Autorotation performance.

For single-engine helicopters and
multiengine helicopters that do not
meet the Category A engine isolation
requirements of Part 29 of this chapter,
the minimum rate of descent airspeed
and the best angle-of-glide airspeed
must be determined in autorotation
at - 
(a) Maximum weight; and
(b) Rotor speed(s) selected by the applicant.
[Amdt. 27-21, 49 FR 44433, Nov. 6, 1984]

Section 27.75

Landing.

(a) The rotorcraft must be able to be
landed with no excessive vertical acceleration, no tendency to bounce, nose
over, ground loop, porpoise, or water
loop, and without exceptional piloting
skill or exceptionally favorable conditions, with - 
(1) Approach or autorotation speeds
appropriate to the type of rotorcraft
and selected by the applicant;
(2) The approach and landing made
with - 
(i) Power off, for single engine rotorcraft and entered from steady state
autorotation; or
(ii) One-engine inoperative (OEI) for
multiengine rotorcraft, with each operating engine within approved operating
limitations, and entered from an established OEI approach.
(b) Multiengine rotorcraft must be
able to be landed safely after complete
power failure under normal operating
conditions.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-14, 43 FR 2324, Jan. 16,
1978; Amdt. 27-44, 73 FR 10999, Feb. 29, 2008]

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