547
Federal Aviation Administration, DOT
§ 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.
(c) A master switch arrangement.
(d) An adequate source of electrical
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.
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