Federal Aviation Administration, DOT

Section 27.1305

(f) A means of retaining each openable or readily removable panel, cowling, 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]

Section 27.1194

Other surfaces.

All surfaces aft of, and near, powerplant compartments, other than tail
surfaces not subject to heat, flames, or
sparks emanating from a powerplant
compartment, must be at least fire resistant.
[Amdt. 27-2, 33 FR 964, Jan. 26, 1968]

Section 27.1195

Fire detector systems.

Each turbine engine powered rotorcraft 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
GENERAL
Section 27.1301

Function and installation.

Each item of installed equipment
must - 
(a) Be of a kind and design appropriate 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 limitations specified for that equipment; and
(d) Function properly when installed.

spaschal on DSK3GDR082PROD with CFR

Section 27.1303 Flight and navigation instruments.
The following are the required flight
and navigation instruments:
(a) An airspeed indicator.
(b) An altimeter.
(c) A magnetic direction indicator.

Section 27.1305

Powerplant instruments.

The following are the required powerplant instruments:
(a) A carburetor air temperature indicator, for each engine having a preheater that can provide a heat rise in
excess of 60 SectionF.
(b) A cylinder head temperature indicator, for each - 
(1) Air cooled engine;
(2) Rotorcraft with cooling shutters;
and
(3) Rotorcraft for which compliance
with Section 27.1043 is shown in any condition
other than the most critical flight condition 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 manifold pressure indicator, for
each altitude engine.
(f) An oil temperature warning device
to indicate when the temperature exceeds 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 phasing) 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) At least one tachometer to indicate the r.p.m. of each engine and, as
applicable - 
(1) The r.p.m. of the single main
rotor;
(2) The common r.p.m. of any main
rotors whose speeds cannot vary appreciably 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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