578 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.45 

when the speed of a main rotor ap-
proaches a value that can jeopardize 
safe flight. 

(2) The warning may be furnished ei-

ther through the inherent aerodynamic 
qualities of the helicopter or by a de-
vice. 

(3) The warning must be clear and 

distinct under all conditions, and must 
be clearly distinguishable from all 
other warnings. A visual device that 
requires the attention of the crew 
within the cockpit is not acceptable by 
itself. 

(4) If a warning device is used, the de-

vice must automatically deactivate 
and reset when the low-speed condition 
is corrected. If the device has an audi-
ble warning, it must also be equipped 
with a means for the pilot to manually 
silence the audible warning before the 
low-speed condition is corrected. 

(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. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 965, Jan. 26, 
1968; Amdt. 29–15, 43 FR 2326, Jan. 16, 1978] 

P

ERFORMANCE

 

§ 29.45

General. 

(a) The performance prescribed in 

this subpart must be determined— 

(1) With normal piloting skill and; 
(2) Without exceptionally favorable 

conditions. 

(b) Compliance with the performance 

requirements of this subpart must be 
shown— 

(1) For still air at sea level with a 

standard atmosphere and; 

(2) For the approved range of atmos-

pheric variables. 

(c) The available power must cor-

respond to engine power, not exceeding 
the approved power, less— 

(1) Installation losses; and 
(2) The power absorbed by the acces-

sories and services at the values for 
which certification is requested and ap-
proved. 

(d) For reciprocating engine-powered 

rotorcraft, the performance, as affected 
by engine power, must be based on a 
relative humidity of 80 percent in a 
standard atmosphere. 

(e) For turbine engine-powered rotor-

craft, the performance, as affected by 
engine power, must be based on a rel-
ative humidity of— 

(1) 80 percent, at and below standard 

temperature; and 

(2) 34 percent, at and above standard 

temperature plus 50 

°

F. 

Between these two temperatures, the 
relative humidity must vary linearly. 

(f) For turbine-engine-power rotor-

craft, a means must be provided to per-
mit the pilot to detemine prior to take-
off that each engine is capable of devel-
oping the power necessary to achieve 
the applicable rotorcraft performance 
prescribed in this subpart. 

(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), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–15, 43 FR 2326, Jan. 16, 
1978; Amdt. 29–24, 49 FR 44436, Nov. 6, 1984] 

§ 29.49

Performance at minimum oper-

ating speed. 

(a) For each Category A helicopter, 

the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which 
takeoff data are scheduled— 

(1) With not more than takeoff 

power; 

(2) With the landing gear extended; 

and 

(3) At a height consistent with the 

procedure used in establishing the 
takeoff, climbout, and rejected takeoff 
paths. 

(b) For each Category B helicopter, 

the hovering performance must be de-
termined over the ranges of weight, al-
titude, and temperature for which cer-
tification is requested, with— 

(1) Takeoff power; 
(2) The landing gear extended; and 
(3) The helicopter in ground effect at 

a height consistent with normal take-
off procedures. 

(c) For each helicopter, the out-of- 

ground effect hovering performance 
must be determined over the ranges of 
weight, altitude, and temperature for 
which certification is requested with 
takeoff power. 

(d) For rotorcraft other than heli-

copters, the steady rate of climb at the 

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