658 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.1322 

(4) The instrument that most effec-

tively indicates altitude or is most fre-
quently utilized in control of altitude 
must be adjacent to and to the right of 
the attitude instrument. 

(c) Other required powerplant instru-

ments must be closely grouped on the 
instrument panel. 

(d) Identical powerplant instruments 

for the engines must be located so as to 
prevent any confusion as to which en-
gine each instrument relates. 

(e) Each powerplant instrument vital 

to safe operation must be plainly visi-
ble to appropriate crewmembers. 

(f) Instrument panel vibration may 

not damage, or impair the readability 
or accuracy of, any instrument. 

(g) If a visual indicator is provided to 

indicate malfunction of an instrument, 
it must be effective under all probable 
cockpit lighting conditions. 

(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. 29–14, 42 FR 36972, July 18, 
1977; Amdt. 29–21, 48 FR 4391, Jan. 31, 1983] 

§ 29.1322

Warning, caution, and advi-

sory lights. 

If warning, caution or advisory lights 

are installed in the cockpit they must, 
unless otherwise approved by the Ad-
ministrator, be— 

(a) Red, for warning lights (lights in-

dicating a hazard which may require 
immediate corrective action); 

(b) Amber, for caution lights (lights 

indicating the possible need for future 
corrective action); 

(c) Green, for safe operation lights; 

and 

(d) Any other color, including white, 

for lights not described in paragraphs 
(a) through (c) of this section, provided 
the color differs sufficiently from the 
colors prescribed in paragraphs (a) 
through (c) of this section to avoid pos-
sible confusion. 

[Amdt. 29–12, 41 FR 55474, Dec. 20, 1976] 

§ 29.1323

Airspeed indicating system. 

For each airspeed indicating system, 

the following apply: 

(a) Each airspeed indicating instru-

ment must be calibrated to indicate 
true airspeed (at sea level with a stand-

ard atmosphere) with a minimum prac-
ticable instrument calibration error 
when the corresponding pitot and stat-
ic pressures are applied. 

(b) Each system must be calibrated 

to determine system error excluding 
airspeed instrument error. This cali-
bration must be determined— 

(1) In level flight at speeds of 20 

knots and greater, and over an appro-
priate range of speeds for flight condi-
tions of climb and autorotation; and 

(2) During takeoff, with repeatable 

and readable indications that ensure— 

(i) Consistent realization of the field 

lengths specified in the Rotorcraft 
Flight Manual; and 

(ii) Avoidance of the critical areas of 

the height-velocity envelope as estab-
lished under § 29.87. 

(c) For Category A rotorcraft— 
(1) The indication must allow con-

sistent definition of the takeoff deci-
sion point; and 

(2) The system error, excluding the 

airspeed instrument calibration error, 
may not exceed— 

(i) Three percent or 5 knots, which-

ever is greater, in level flight at speeds 
above 80 percent of takeoff safety 
speed; and 

(ii) Ten knots in climb at speeds from 

10 knots below takeoff safety speed to 
10 knots above V

Y

. 

(d) For Category B rotorcraft, the 

system error, excluding the airspeed 
instrument calibration error, may not 
exceed 3 percent or 5 knots, whichever 
is greater, in level flight at speeds 
above 80 percent of the climbout speed 
attained at 50 feet when complying 
with § 29.63. 

(e) Each system must be arranged, so 

far as practicable, to prevent malfunc-
tion or serious error due to the entry of 
moisture, dirt, or other substances. 

(f) Each system must have a heated 

pitot tube or an equivalent means of 
preventing malfunction due to icing. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 970, Jan. 26, 
1968; Amdt. 29–24, 49 FR 44439, Nov. 6, 1984; 
Amdt. 29–39, 61 FR 21901, May 10, 1996; Amdt. 
29–44, 64 FR 45338, Aug. 19, 1999] 

§ 29.1325

Static pressure and pressure 

altimeter systems. 

(a) Each instrument with static air 

case connections must be vented to the 

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