Federal Aviation Administration, DOT

Section 29.1013

(e) The fuel jettisoning system must
be designed to comply with the powerplant installation requirements of
Section 29.901(c).
(f) An auxiliary fuel jettisoning system which meets the requirements of
paragraphs (a), (b), (d), and (e) of this
section may be installed to jettison additional fuel provided it has separate
and independent controls.
[Amdt. 29-26, 53 FR 34218, Sept. 2, 1988]

OIL SYSTEM
Section 29.1011 Engines: general.
(a) Each engine must have an independent oil system that can supply it
with an appropriate quantity of oil at a
temperature not above that safe for
continuous operation.
(b) The usable oil capacity of each
system may not be less than the product of the endurance of the rotorcraft
under critical operating conditions and
the maximum allowable oil consumption of the engine under the same conditions, plus a suitable margin to ensure adequate circulation and cooling.
Instead of a rational analysis of endurance and consumption, a usable oil capacity of one gallon for each 40 gallons
of usable fuel may be used for reciprocating engine installations.
(c) Oil-fuel ratios lower than those
prescribed in paragraph (c) of this section may be used if they are substantiated by data on the oil consumption
of the engine.
(d) The ability of the engine and oil
cooling provisions to maintain the oil
temperature at or below the maximum
established value must be shown under
the applicable requirements of SectionSection 29.1041
through 29.1049.

spaschal on DSK3GDR082PROD with CFR

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-26, 53 FR 34218, Sept. 2,
1988]

Section 29.1013 Oil tanks.
(a) Installation. Each oil tank installation must meet the requirements of
Section 29.967.
(b) Expansion space. Oil tank expansion space must be provided so that - 
(1) Each oil tank used with a reciprocating engine has an expansion space of
not less than the greater of 10 percent
of the tank capacity or 0.5 gallon, and
each oil tank used with a turbine en-

gine has an expansion space of not less
than 10 percent of the tank capacity;
(2) Each reserve oil tank not directly
connected to any engine has an expansion space of not less than two percent
of the tank capacity; and
(3) It is impossible to fill the expansion space inadvertently with the
rotorcraft in the normal ground attitude.
(c) Filler connections. Each recessed
oil tank filler connection that can retain any appreciable quantity of oil
must have a drain that discharges clear
of the entire rotorcraft. In addition - 
(1) Each oil tank filler cap must provide an oil-tight seal under the pressure expected in operation;
(2) For category A rotorcraft, each
oil tank filler cap or filler cap cover
must incorporate features that provide
a warning when caps are not fully
locked or seated on the filler connection; and
(3) Each oil filler must be marked
under Section 29.1557(c)(2).
(d) Vent. Oil tanks must be vented as
follows:
(1) Each oil tank must be vented
from the top part of the expansion
space to that venting is effective under
all normal flight conditions.
(2) Oil tank vents must be arranged
so that condensed water vapor that
might freeze and obstruct the line cannot accumulate at any point;
(e) Outlet. There must be means to
prevent entrance into the tank itself,
or into the tank outlet, of any object
that might obstruct the flow of oil
through the system. No oil tank outlet
may be enclosed by a screen or guard
that would reduce the flow of oil below
a safe value at any operating temperature. There must be a shutoff valve at
the outlet of each oil tank used with a
turbine engine unless the external portion of the oil system (including oil
tank supports) is fireproof.
(f) Flexible liners. Each flexible oil
tank liner must be approved or shown
to be suitable for the particular installation.
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-10, 39 FR 35462, Oct. 1,
1974]

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