671 

Federal Aviation Administration, DOT 

§ 29.1505 

(2) Equipment control devices, sys-

tems, and instrumentation must rea-
sonably ensure that no operating limi-
tations affecting the integrity of high 
energy rotors will be exceeded in serv-
ice. 

(c) It must be shown by test that 

equipment containing high energy ro-
tors can contain any failure of a high 
energy rotor that occurs at the highest 
speed obtainable with the normal speed 
control devices inoperative. 

(d) Equipment containing high en-

ergy rotors must be located where 
rotor failure will neither endanger the 
occupants nor adversely affect contin-
ued safe flight. 

[Amdt. 29–3, 33 FR 971, Jan. 26, 1968] 

Subpart G—Operating Limitations 

and Information 

§ 29.1501

General. 

(a) Each operating limitation speci-

fied in §§ 29.1503 through 29.1525 and 
other limitations and information nec-
essary for safe operation must be es-
tablished. 

(b) The operating limitations and 

other information necessary for safe 
operation must be made available to 
the crewmembers as prescribed in 
§§ 29.1541 through 29.1589. 

(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))) 

[Amdt. 29–15, 43 FR 2327, Jan. 16, 1978] 

O

PERATING

L

IMITATIONS

 

§ 29.1503

Airspeed limitations: general. 

(a) An operating speed range must be 

established. 

(b) When airspeed limitations are a 

function of weight, weight distribution, 
altitude, rotor speed, power, or other 
factors, airspeed limitations cor-
responding with the critical combina-
tions of these factors must be estab-
lished. 

§ 29.1505

Never-exceed speed. 

(a) The never-exceed speed, V

NE,

must 

be established so that it is— 

(1) Not less than 40 knots (CAS); and 
(2) Not more than the lesser of— 

(i) 0.9 times the maximum forward 

speeds established under § 29.309; 

(ii) 0.9 times the maximum speed 

shown under §§ 29.251 and 29.629; or 

(iii) 0.9 times the maximum speed 

substantiated for advancing blade tip 
mach number effects under critical al-
titude conditions. 

(b) V

NE

may vary with altitude, 

r.p.m., temperature, and weight, if— 

(1) No more than two of these vari-

ables (or no more than two instru-
ments integrating more than one of 
these variables) are used at one time; 
and 

(2) The ranges of these variables (or 

of the indications on instruments inte-
grating more than one of these vari-
ables) are large enough to allow an 
operationally practical and safe vari-
ation of V

NE

. 

(c) For helicopters, a stabilized 

power-off V

NE

denoted as V

NE

(power- 

off) may be established at a speed less 
than V

NE

established pursuant to para-

graph (a) of this section, if the fol-
lowing conditions are met: 

(1) V

NE

(power-off) is not less than a 

speed midway between the power-on 
V

NE

and the speed used in meeting the 

requirements of— 

(i) § 29.67(a)(3) for Category A heli-

copters; 

(ii) § 29.65(a) for Category B heli-

copters, except multi-engine heli-
copters meeting the requirements of 
§ 29.67(b); and 

(iii) § 29.67(b) for multi-engine Cat-

egory B helicopters meeting the re-
quirements of § 29.67(b). 

(2) V

NE

(power-off) is— 

(i) A constant airspeed; 
(ii) A constant amount less than 

power-on V

NE

´

or 

(iii) A constant airspeed for a portion 

of the altitude range for which certifi-
cation is requested, and a constant 
amount less than power-on V

NE

for the 

remainder of the altitude range. 

(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))) 

[Amdt. 29–3, 33 FR 971, Jan. 26, 1968, as 
amended by Amdt. 29–15, 43 FR 2327, Jan. 16, 
1978; Amdt. 29–24, 49 FR 44440, Nov. 6, 1984] 

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