Section 29.1337

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

mode of operation. Selector switch position is not acceptable as a means of
indication.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c), Dept.
of Transportation Act (49 U.S.C. 1655(c)))
[Amdt. 29-14, 42 FR 36973, July 18, 1977]

spaschal on DSK3GDR082PROD with CFR

Section 29.1337

Powerplant instruments.

(a) Instruments and instrument lines.
(1) Each powerplant and auxiliary
power unit instrument line must meet
the requirements of SectionSection 29.993 and 29.1183.
(2) Each line carrying flammable
fluids under pressure must - 
(i) Have restricting orifices or other
safety devices at the source of pressure
to prevent the escape of excessive fluid
if the line fails; and
(ii) Be installed and located so that
the escape of fluids would not create a
hazard.
(3) Each powerplant and auxiliary
power unit 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. There
must be means to indicate to the flight
crew members the quantity, in gallons
or equivalent units, of usable fuel in
each tank during 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 29.959;
(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;
(3) Tanks with interconnected outlets
and airspaces may be treated as one
tank and need not have separate indicators; and
(4) 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 a stick gauge or equivalent means
to indicate the quantity of oil - 
(1) In each tank; and
(2) In each transmission gearbox.
(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
within the transmission or gearbox.
Each chip detector must - 
(1) Be designed to provide a signal to
the
indicator
required
by
Section 29.1305(a)(22); and
(2) Be provided with a means to allow
crewmembers to check, in flight, the
function of each detector electrical circuit and signal.
(Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49
U.S.C. 1655(c))
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-13, 42 FR 15047, Mar. 17,
1977; Amdt. 29-26, 53 FR 34219, Sept. 2, 1988]

ELECTRICAL SYSTEMS AND EQUIPMENT
Section 29.1351 General.
(a) Electrical system capacity. The required generating capacity and the
number and kind of power sources
must - 
(1) Be determined by an electrical
load analysis; and
(2) Meet the requirements of Section 29.1309.
(b) Generating system. The generating
system
includes
electrical
power
sources, main power busses, transmission cables, and associated control,
regulation, and protective devices. It
must be designed so that - 
(1) Power sources function properly
when independent and when connected
in combination;
(2) No failure or malfunction of any
power source can create a hazard or
impair the ability of remaining sources
to supply essential loads;
(3) The system voltage and frequency
(as applicable) at the terminals of essential load equipment can be maintained within the limits for which the
equipment is designed, during any
probable operating condition;
(4) System transients due to switching, fault clearing, or other causes do
not make essential loads inoperative,

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