Federal Aviation Administration, DOT

Section 29.1305

spaschal on DSK3GDR082PROD with CFR

(c) Be installed according to limitations specified for that equipment; and
(d) Function properly when installed.
Section 29.1303 Flight and navigation instruments.
The following are required flight and
navigational instruments:
(a) An airspeed indicator. For Category A rotorcraft with VNE less than a
speed at which unmistakable pilot cues
provide overspeed warning, a maximum
allowable airspeed indicator must be
provided. If maximum allowable airspeed 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, minutes, 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 indicator combined with an integral slipskid indicator (turn-and-bank indicator) except that only a slip-skid indicator is required on rotorcraft with a
third attitude instrument system
that - 
(1) Is usable through flight attitudes
of Section80 degrees of pitch and Section120 degrees
of roll;
(2) Is powered from a source independent of the electrical generating
system;
(3) Continues reliable operation for a
minimum of 30 minutes after total failure 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 generating system;
(6) Is located on the instrument panel
in a position acceptable to the Administrator that will make it plainly visible 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) indicator.
(j) For Category A rotorcraft, a speed
warning device when VNE 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 (differing distinctively from aural warnings used for other purposes) to the pilots whenever the indicated speed exceeds VNE plus 3 knots and must operate satisfactorily throughout the approved range of altitudes and temperatures.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal 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]

Section 29.1305

Powerplant instruments.

The following are required powerplant instruments:
(a) For each rotorcraft - 
(1) A carburetor air temperature indicator for each reciprocating engine;
(2) A cylinder head temperature indicator for each air-cooled reciprocating
engine, and a coolant temperature indicator for each liquid-cooled reciprocating 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 usable 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 altitude type;
(6) An oil pressure indicator for each
pressure-lubricated gearbox.
(7) An oil pressure warning device for
each pressure-lubricated gearbox to indicate 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 device to indicate unsafe oil temperatures in each main rotor drive gearbox,

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