643 

Federal Aviation Administration, DOT 

§ 27.87 

§ 27.67

Climb: one engine inoperative. 

For multiengine helicopters, the 

steady rate of climb (or descent), at 

V

y

 

(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 heli-

copters for which certification for the 
use of continuous OEI power is re-
quested. 

(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. 27–23, 53 FR 34210, Sept. 2, 
1988] 

§ 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 ap-

plicant. 

[Amdt. 27–21, 49 FR 44433, Nov. 6, 1984] 

§ 27.75

Landing. 

(a) The rotorcraft must be able to be 

landed with no excessive vertical accel-
eration, no tendency to bounce, nose 
over, ground loop, porpoise, or water 
loop, and without exceptional piloting 
skill or exceptionally favorable condi-
tions, 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 rotor-

craft and entered from steady state 
autorotation; or 

(ii) One-engine inoperative (OEI) for 

multiengine rotorcraft, with each oper-
ating engine within approved operating 

limitations, and entered from an estab-
lished 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] 

§ 27.87

Height-speed envelope. 

(a) If there is any combination of 

height and forward speed (including 
hover) under which a safe landing can-
not be made under the applicable power 
failure condition in paragraph (b) of 
this section, a limiting height-speed 
envelope must be established (includ-
ing 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 se-
lected by the applicant for each alti-
tude 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 out- 
of-ground effect, whichever is lower. 

(b) The applicable power failure con-

ditions 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 min-
imum installed specification power 
available for the most critical com-
bination of approved ambient tempera-
ture and pressure altitude resulting in 
7000 feet density altitude or the max-
imum altitude capability of the heli-
copter, 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] 

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