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14 CFR Ch. I (1–1–19 Edition)

§ 27.1307

(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 gas temperature indicator for

each turbine engine.

(o) Means to enable the pilot to de-

termine the torque of each turboshaft
engine, 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]

§ 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.

(a) The equipment, systems, and in-

stallations whose functioning is re-
quired by this subchapter must be de-
signed and installed to ensure that
they perform their intended functions
under any foreseeable operating condi-
tion.

(b) The equipment, systems, and in-

stallations of a multiengine rotorcraft
must be designed to prevent hazards to
the rotorcraft in the event of a prob-
able malfunction or failure.

stallations of single-engine rotorcraft
must be designed to minimize hazards
to the rotorcraft in the event of a prob-
able malfunction or failure.

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–21, 49 FR 44435, Nov. 6,
1984; Amdt. 27–46, 76 FR 33135, June 8, 2011]

§ 27.1316

Electrical and electronic sys-

tem lightning protection.

(a) Each electrical and electronic

system that performs a function, for
which failure would prevent the contin-
ued safe flight and landing of the rotor-
craft, must be designed and installed so
that—

(1) The function is not adversely af-

fected during and after the time the
rotorcraft is exposed to lightning; and

(2) The system automatically recov-

ers normal operation of that function

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