802 

14 CFR Ch. I (1–1–14 Edition) 

§ 29.1305 

(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, 
including gearboxes necessary for rotor 
phasing; 

(11) A gas temperature indicator for 

each turbine engine; 

(12) A gas producer rotor tachometer 

for each turbine engine; 

(13) A tachometer for each engine 

that, if combined with the applicable 
instrument required by paragraph 
(a)(14) of this section, indicates rotor 
r.p.m. during autorotation. 

(14) At least one tachometer to indi-

cate, as applicable— 

(i) The r.p.m. of the single main 

rotor; 

(ii) The common r.p.m. of any main 

rotors whose speeds cannot vary appre-
ciably with respect to each other; and 

(iii) The r.p.m. of each main rotor 

whose speed can vary appreciably with 
respect to that of another main rotor; 

(15) A free power turbine tachometer 

for each turbine engine; 

(16) A means, for each turbine engine, 

to indicate power for that engine; 

(17) For each turbine engine, an indi-

cator to indicate the functioning of the 
powerplant ice protection system; 

(18) An indicator for the filter re-

quired by § 29.997 to indicate the occur-
rence of contamination of the filter to 
the degree established in compliance 
with § 29.955; 

(19) For each turbine engine, a warn-

ing means for the oil strainer or filter 
required by § 29.1019, if it has no bypass, 
to warn the pilot of the occurrence of 
contamination of the strainer or filter 
before it reaches the capacity estab-
lished in accordance with § 29.1019(a)(2); 

(20) An indicator to indicate the func-

tioning of any selectable or control-
lable heater used to prevent ice clog-
ging of fuel system components; 

(21) An individual fuel pressure indi-

cator for each engine, unless the fuel 
system which supplies that engine does 

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