Section 25.1305

14 CFR Ch. I (1-1-19 Edition)

(4) 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 large airplanes
with a third attitude instrument system useable through flight attitudes of
360Section of pitch and roll and installed in
accordance with Section 121.305(k) of this
title.
(5) A bank and pitch indicator (gyroscopically stabilized).
(6) A direction indicator (gyroscopically stabilized, magnetic or nonmagnetic).
(c) The following flight and navigation instruments are required as prescribed in this paragraph:
(1) A speed warning device is required
for turbine engine powered airplanes
and for airplanes with VMO/MMO greater
than 0.8 VDF/MDF or 0.8 V D/MD. The
speed warning device must give effective aural warning (differing distinctively from aural warnings used for
other purposes) to the pilots, whenever
the speed exceeds VMO plus 6 knots or
MMO + 0.01. The upper limit of the production tolerance for the warning device may not exceed the prescribed
warning speed.
(2) A machmeter is required at each
pilot station for airplanes with compressibility limitations not otherwise
indicated to the pilot by the airspeed
indicating system required under paragraph (b)(1) of this section.
[Amdt. 25-23, 35 FR 5678, Apr. 8, 1970, as
amended by Amdt. 25-24, 35 FR 7108, May 6,
1970; Amdt. 25-38, 41 FR 55467, Dec. 20, 1976;
Amdt. 25-90, 62 FR 13253, Mar. 19, 1997]

spaschal on DSK3GDR082PROD with CFR

Section 25.1305

Powerplant instruments.

The following are required powerplant instruments:
(a) For all airplanes. (1) A fuel pressure warning means for each engine, or
a master warning means for all engines
with provision for isolating the individual warning means from the master
warning means.
(2) A fuel quantity indicator for each
fuel tank.
(3) An oil quantity indicator for each
oil tank.
(4) An oil pressure indicator for each
independent pressure oil system of
each engine.

(5) An oil pressure warning means for
each engine, or a master warning
means for all engines with provision
for isolating the individual warning
means from the master warning means.
(6) An oil temperature indicator for
each engine.
(7) Fire-warning devices that provide
visual and audible warning.
(8) An augmentation liquid quantity
indicator (appropriate for the manner
in which the liquid is to be used in operation) for each tank.
(b) For reciprocating engine-powered
airplanes. In addition to the powerplant
instruments required by paragraph (a)
of this section, the following powerplant instruments are required:
(1) A carburetor air temperature indicator for each engine.
(2) A cylinder head temperature indicator for each air-cooled engine.
(3) A manifold pressure indicator for
each engine.
(4) A fuel pressure indicator (to indicate the pressure at which the fuel is
supplied) for each engine.
(5) A fuel flowmeter, or fuel mixture
indicator, for each engine without an
automatic altitude mixture control.
(6) A tachometer for each engine.
(7) A device that indicates, to the
flight crew (during flight), any change
in the power output, for each engine
with - 
(i) An automatic propeller feathering
system, whose operation is initiated by
a power output measuring system; or
(ii) A total engine piston displacement of 2,000 cubic inches or more.
(8) A means to indicate to the pilot
when the propeller is in reverse pitch,
for each reversing propeller.
(c) For turbine engine-powered airplanes. In addition to the powerplant
instruments required by paragraph (a)
of this section, the following powerplant instruments are required:
(1) A gas temperature indicator for
each engine.
(2) A fuel flowmeter indicator for
each engine.
(3) A tachometer (to indicate the
speed of the rotors with established
limiting speeds) for each engine.
(4) A means to indicate, to the flight
crew, the operation of each engine
starter that can be operated continuously but that is neither designed for

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