546
14 CFR Ch. I (1–1–24 Edition)
§ 27.1194
(f) A means of retaining each open-
able or readily removable panel, cowl-
ing, or engine or rotor drive system
covering must be provided to preclude
hazardous damage to rotors or critical
control components in the event of
structural or mechanical failure of the
normal retention means, unless such
failure is extremely improbable.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–23, 53 FR 34214, Sept. 2,
1988]
§ 27.1194
Other surfaces.
All surfaces aft of, and near, power-
plant compartments, other than tail
surfaces not subject to heat, flames, or
sparks emanating from a powerplant
compartment, must be at least fire re-
sistant.
[Amdt. 27–2, 33 FR 964, Jan. 26, 1968]
§ 27.1195
Fire detector systems.
Each turbine engine powered rotor-
craft must have approved quick-acting
fire detectors in numbers and locations
insuring prompt detection of fire in the
engine compartment which cannot be
readily observed in flight by the pilot
in the cockpit.
[Amdt. 27–5, 36 FR 5493, Mar. 24, 1971]
Subpart F—Equipment
G
ENERAL
§ 27.1301
Function and installation.
Each item of installed equipment
must—
(a) Be of a kind and design appro-
priate to its intended function;
(b) Be labeled as to its identification,
function, or operating limitations, or
any applicable combination of these
factors;
(c) Be installed according to limita-
tions specified for that equipment; and
(d) Function properly when installed.
§ 27.1303
Flight and navigation instru-
ments.
The following are the required flight
and navigation instruments:
(a) An airspeed indicator.
(b) An altimeter.
(c) A magnetic direction indicator.
§ 27.1305
Powerplant instruments.
The following are the required power-
plant instruments:
(a) A carburetor air temperature in-
dicator, for each engine having a pre-
heater that can provide a heat rise in
excess of 60
°
F.
(b) A cylinder head temperature indi-
cator, for each—
(1) Air cooled engine;
(2) Rotorcraft with cooling shutters;
and
(3) Rotorcraft for which compliance
with § 27.1043 is shown in any condition
other than the most critical flight con-
dition with respect to cooling.
(c) A fuel pressure indicator, for each
pump-fed engine.
(d) A fuel quantity indicator, for each
fuel tank.
(e) A means to indicate manifold
pressure for each altitude engine.
(f) An oil temperature warning device
to indicate when the temperature ex-
ceeds a safe value in each main rotor
drive gearbox (including any gearboxes
essential to rotor phasing) having an
oil system independent of the engine
oil system.
(g) An oil pressure warning device to
indicate when the pressure falls below
a safe value in each pressure-lubricated
main rotor drive gearbox (including
any gearboxes essential to rotor phas-
ing) having an oil system independent
of the engine oil system.
(h) An oil pressure indicator for each
engine.
(i) An oil quantity indicator for each
oil tank.
(j) An oil temperature indicator for
each engine.
(k) A means to indicate the r.p.m. of
each engine and at least one tachom-
eter, as applicable, for:
(1) The r.p.m. of the single main
rotor;
(2) The common r.p.m. of any main
rotors whose speeds cannot vary appre-
ciably with respect to each other; or
(3) The r.p.m. of each main rotor
whose speed can vary appreciably with
respect to that of another main rotor.
(l) A low fuel warning device for each
fuel tank which feeds an engine. This
device must—
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