653 

Federal Aviation Administration, DOT 

§ 29.1305 

(c) Be installed according to limita-

tions specified for that equipment; and 

(d) Function properly when installed. 

§ 29.1303

Flight and navigation instru-

ments. 

The following are required flight and 

navigational instruments: 

(a) An airspeed indicator. For Cat-

egory A rotorcraft with V

NE

less than a 

speed at which unmistakable pilot cues 
provide overspeed warning, a maximum 
allowable airspeed indicator must be 
provided. If maximum allowable air-
speed varies with weight, altitude, 
temperature, or r.p.m., the indicator 
must show that variation. 

(b) A sensitive altimeter. 
(c) A magnetic direction indicator. 
(d) A clock displaying hours, min-

utes, and seconds with a sweep-second 
pointer or digital presentation. 

(e) A free-air temperature indicator. 
(f) A non-tumbling gyroscopic bank 

and pitch indicator. 

(g) A gyroscopic rate-of-turn indi-

cator combined with an integral slip- 
skid indicator (turn-and-bank indi-
cator) except that only a slip-skid indi-
cator is required on rotorcraft with a 
third attitude instrument system 
that— 

(1) Is usable through flight attitudes 

of 

±

80 degrees of pitch and 

±

120 degrees 

of roll; 

(2) Is powered from a source inde-

pendent of the electrical generating 
system; 

(3) Continues reliable operation for a 

minimum of 30 minutes after total fail-
ure of the electrical generating system; 

(4) Operates independently of any 

other attitude indicating system; 

(5) Is operative without selection 

after total failure of the electrical gen-
erating system; 

(6) Is located on the instrument panel 

in a position acceptable to the Admin-
istrator that will make it plainly visi-
ble to and useable by any pilot at his 
station; and 

(7) Is appropriately lighted during all 

phases of operation. 

(h) A gyroscopic direction indicator. 
(i) A rate-of-climb (vertical speed) in-

dicator. 

(j) For Category A rotorcraft, a speed 

warning device when V

NE

is less than 

the speed at which unmistakable over-

speed warning is provided by other 
pilot cues. The speed warning device 
must give effective aural warning (dif-
fering distinctively from aural warn-
ings used for other purposes) to the pi-
lots whenever the indicated speed ex-
ceeds V

NE

plus 3 knots and must oper-

ate satisfactorily throughout the ap-
proved range of altitudes and tempera-
tures. 

(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. 29–12, 41 FR 55474, Dec. 20, 
1976; Amdt. 29–14, 42 FR 36972, July 18, 1977; 
Amdt. 29–24, 49 FR 44438, Nov. 6, 1984; 70 FR 
2012, Jan. 12, 2005] 

§ 29.1305

Powerplant instruments. 

The following are required power-

plant instruments: 

(a) For each rotorcraft— 
(1) A carburetor air temperature indi-

cator for each reciprocating engine; 

(2) A cylinder head temperature indi-

cator for each air-cooled reciprocating 
engine, and a coolant temperature indi-
cator for each liquid-cooled recipro-
cating engine; 

(3) A fuel quantity indicator for each 

fuel tank; 

(4) A low fuel warning device for each 

fuel tank which feeds an engine. This 
device must— 

(i) Provide a warning to the crew 

when approximately 10 minutes of usa-
ble fuel remains in the tank; and 

(ii) Be independent of the normal fuel 

quantity indicating system. 

(5) A manifold pressure indicator, for 

each reciprocating engine of the alti-
tude type; 

(6) An oil pressure indicator for each 

pressure-lubricated gearbox. 

(7) An oil pressure warning device for 

each pressure-lubricated gearbox to in-
dicate when the oil pressure falls below 
a safe value; 

(8) An oil quantity indicator for each 

oil tank and each rotor drive gearbox, 
if lubricant is self-contained; 

(9) An oil temperature indicator for 

each engine; 

(10) An oil temperature warning de-

vice to indicate unsafe oil tempera-
tures in each main rotor drive gearbox, 

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