spaschal on DSK3GDR082PROD with CFR

Section 27.1351

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

(ii) Be installed and located so that
the escape of fluids would not create a
hazard.
(3) Each powerplant instrument that
utilizes flammable fluids must be installed and located so that the escape
of fluid would not create a hazard.
(b) Fuel quantity indicator. Each fuel
quantity indicator must be installed to
clearly indicate to the flight crew the
quantity of fuel in each tank in flight.
In addition - 
(1) Each fuel quantity indicator must
be calibrated to read  - zero -  during
level flight when the quantity of fuel
remaining in the tank is equal to the
unusable fuel supply determined under
Section 27.959;
(2) When two or more tanks are closely interconnected by a gravity feed system and vented, and when it is impossible to feed from each tank separately, at least one fuel quantity indicator must be installed; and
(3) Each exposed sight gauge used as
a fuel quantity indicator must be protected against damage.
(c) Fuel flowmeter system. If a fuel
flowmeter system is installed, each
metering component must have a
means for bypassing the fuel supply if
malfunction of that component severely restricts fuel flow.
(d) Oil quantity indicator. There must
be means to indicate the quantity of
oil in each tank - 
(1) On the ground (including during
the filling of each tank); and
(2) In flight, if there is an oil transfer
system or reserve oil supply system.
(e) Rotor drive system transmissions
and gearboxes utilizing ferromagnetic
materials must be equipped with chip
detectors designed to indicate the presence of ferromagnetic particles resulting from damage or excessive wear.
Chip detectors must - 
(1) Be designed to provide a signal to
the device required by Section 27.1305(v) and
be provided with a means to allow
crewmembers to check, in flight, the
function of each detector electrical circuit and signal.

(2) [Reserved]
(Secs. 313(a), 601, and 603, 72 Stat. 752, 775, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c) 49
U.S.C. 1655(c))
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-12, 42 FR 15046, Mar. 17,
1977; Amdt. 27-23, 53 FR 34214, Sept. 2, 1988;
Amdt. 27-37, 64 FR 45095, Aug. 18, 1999]

ELECTRICAL SYSTEMS AND EQUIPMENT
Section 27.1351 General.
(a) Electrical system capacity. Electrical equipment must be adequate for
its intended use. In addition - 
(1) Electric power sources, their
transmission cables, and their associated control and protective devices
must be able to furnish the required
power at the proper voltage to each
load circuit essential for safe operation; and
(2) Compliance with paragraph (a)(1)
of this section must be shown by an
electrical load analysis, or by electrical measurements that take into account the electrical loads applied to
the electrical system, in probable combinations and for probable durations.
(b) Function. For each electrical system, the following apply:
(1) Each system, when installed,
must be - 
(i) Free from hazards in itself, in its
method of operation, and in its effects
on other parts of the rotorcraft; and
(ii) Protected from fuel, oil, water,
other detrimental substances, and mechanical damage.
(2) Electric power sources must function properly when connected in combination or independently.
(3) No failure or malfunction of any
source may impair the ability of any
remaining source to supply load circuits essential for safe operation.
(4) Each electric power source control
must allow the independent operation
of each source.
(c) Generating system. There must be
at least one generator if the system
supplies power to load circuits essential for safe operation. In addition - 
(1) Each generator must be able to
deliver its continuous rated power;
(2) Generator voltage control equipment must be able to dependably regulate each generator output within
rated limits;

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