title-14-part-27-sec27-1305

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

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;

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

(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.

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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§ 27.1309

(1) Provide a warning to the

flightcrew when approximately 10 min-
utes of usable fuel remains in the tank;
and

(2) Be independent of the normal fuel

quantity indicating system.

(m) Means to indicate to the

flightcrew the failure of any fuel pump
installed to show compliance with
§ 27.955.

(n) A means to indicate the gas tem-

perature for each turbine engine.

(o) A means to enable the pilot to de-

termine the torque of each turbine en-
gine, if a torque limitation is estab-
lished for that engine under § 27.1521(e).

(p) For each turbine engine, an indi-

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

(q) An indicator for the fuel filter re-

quired by § 27.997 to indicate the occur-
rence of contamination of the filter at
the degree established by the applicant
in compliance with § 27.955.

(r) For each turbine engine, a warn-

ing means for the oil strainer or filter
required by § 27.1019, 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 § 27.1019(a)(2).

(s) An indicator to indicate the func-

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

(t) For rotorcraft for which a 30-sec-

ond/2-minute OEI power rating is re-
quested, a means must be provided to
alert the pilot when the engine is at
the 30-second and the 2-minute OEI
power levels, when the event begins,
and when the time interval expires.

(u) For each turbine engine utilizing

30-second/2-minute OEI power, a device
or system must be provided for use by
ground personnel which—

(1) Automatically records each usage

and duration of power at the 30-second
and 2-minute OEI levels;

(2) Permits retrieval of the recorded

data;

(3) Can be reset only by ground main-

tenance personnel; and

(4) Has a means to verify proper oper-

ation of the system or device.

(v) Warning or caution devices to sig-

nal to the flight crew when ferromag-

netic particles are detected by the chip
detector required by § 27.1337(e).

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–9, 39 FR 35462, Oct. 1,
1974; Amdt. 27–23, 53 FR 34214, Sept. 2, 1988;
Amdt. 27–29, 59 FR 47767, Sept. 16, 1994; Amdt.
27–37, 64 FR 45095, Aug. 18, 1999; 64 FR 47563,
Aug. 31, 1999; Amdt. 27–51, 88 FR 8737, Feb. 10,
2023]

§ 27.1307

Miscellaneous equipment.

The following is the required mis-

cellaneous equipment:

(a) An approved seat for each occu-

pant.

(b) An approved safety belt for each

occupant.

energy, where electrical energy is nec-
essary for operation of the rotorcraft.

(e) Electrical protective devices.

§ 27.1309

Equipment, systems, and in-

stallations.

The equipment, systems, and instal-

lations whose functioning is required
by this subchapter must be designed
and installed to ensure that they per-
form their intended functions under
any foreseeable operating condition.
For any item of equipment or system
whose failure has not been specifically
addressed by another requirement in
this chapter, the following require-
ments also apply:

(a) The design of each item of equip-

ment, system, and installation must be
analyzed separately and in relation to
other rotorcraft systems and installa-
tions to determine and identify any
failure that would affect the capability
of the rotorcraft or the ability of the
crew to perform their duties in all op-
erating conditions.

(b) Each item of equipment, system,

and installation must be designed and
installed so that:

(1) The occurrence of any cata-

strophic failure condition is extremely
improbable;

(2) The occurrence of any major fail-

ure condition is no more than improb-
able; and

(3) For the occurrence of any other

failure condition between major and
catastrophic, the probability of the
failure condition must be inversely
proportional to its consequences.