spaschal on DSK3GDR082PROD with CFR

Section 27.1307

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

(1) Provide a warning to the
flightcrew when approximately 10 minutes 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
Section 27.955.
(n) A gas temperature indicator for
each turbine engine.
(o) Means to enable the pilot to determine the torque of each turboshaft
engine, if a torque limitation is established for that engine under Section 27.1521(e).
(p) For each turbine engine, an indicator to indicate the functioning of the
powerplant ice protection system.
(q) An indicator for the fuel filter required by Section 27.997 to indicate the occurrence of contamination of the filter at
the degree established by the applicant
in compliance with Section 27.955.
(r) For each turbine engine, a warning means for the oil strainer or filter
required by Section 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 established in accordance with Section 27.1019(a)(2).
(s) An indicator to indicate the functioning of any selectable or controllable heater used to prevent ice clogging of fuel system components.
(t) For rotorcraft for which a 30-second/2-minute OEI power rating is requested, 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 maintenance personnel; and
(4) Has a means to verify proper operation of the system or device.
(v) Warning or caution devices to signal to the flight crew when ferromag-

netic particles are detected by the chip
detector required by Section 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]

Section 27.1307

Miscellaneous equipment.

The following is the required miscellaneous equipment:
(a) An approved seat for each occupant.
(b) An approved safety belt for each
occupant.
(c) A master switch arrangement.
(d) An adequate source of electrical
energy, where electrical energy is necessary for operation of the rotorcraft.
(e) Electrical protective devices.
Section 27.1309 Equipment, systems, and installations.
(a) The equipment, systems, and installations whose functioning is required by this subchapter must be designed and installed to ensure that
they perform their intended functions
under any foreseeable operating condition.
(b) The equipment, systems, and installations of a multiengine rotorcraft
must be designed to prevent hazards to
the rotorcraft in the event of a probable malfunction or failure.
(c) The equipment, systems, and installations of single-engine rotorcraft
must be designed to minimize hazards
to the rotorcraft in the event of a probable 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]

Section 27.1316 Electrical and electronic system lightning protection.
(a) Each electrical and electronic
system that performs a function, for
which failure would prevent the continued safe flight and landing of the rotorcraft, must be designed and installed so
that - 
(1) The function is not adversely affected during and after the time the
rotorcraft is exposed to lightning; and
(2) The system automatically recovers normal operation of that function

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