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14 CFR Ch. I (1–1–14 Edition) 

§ 23.1189 

fluids, gas, or air in any area subject to 
engine fire conditions must be at least 
fire resistant, except that flammable 
fluid tanks and supports which are part 
of and attached to the engine must be 
fireproof or be enclosed by a fireproof 
shield unless damage by fire to any 
non-fireproof part will not cause leak-
age or spillage of flammable fluid. 
Components must be shielded or lo-
cated so as to safeguard against the ig-
nition of leaking flammable fluid. 
Flexible hose assemblies (hose and end 
fittings) must be shown to be suitable 
for the particular application. An inte-
gral oil sump of less than 25–quart ca-
pacity on a reciprocating engine need 
not be fireproof nor be enclosed by a 
fireproof shield. 

(b) Paragraph (a) of this section does 

not apply to— 

(1) Lines, fittings, and components 

which are already approved as part of a 
type certificated engine; and 

(2) Vent and drain lines, and their fit-

tings, whose failure will not result in, 
or add to, a fire hazard. 

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as 
amended by Amdt. 23–5, 32 FR 6912, May 5, 
1967; Amdt. 23–15, 39 FR 35460, Oct. 1, 1974; 
Amdt. 23–29, 49 FR 6847, Feb. 23, 1984; Amdt. 
23–51, 61 FR 5138, Feb. 9, 1996] 

§ 23.1189

Shutoff means. 

(a) For each multiengine airplane the 

following apply: 

(1) Each engine installation must 

have means to shut off or otherwise 
prevent hazardous quantities of fuel, 
oil, deicing fluid, and other flammable 
liquids from flowing into, within, or 
through any engine compartment, ex-
cept in lines, fittings, and components 
forming an integral part of an engine. 

(2) The closing of the fuel shutoff 

valve for any engine may not make any 
fuel unavailable to the remaining en-
gines that would be available to those 
engines with that valve open. 

(3) Operation of any shutoff means 

may not interfere with the later emer-
gency operation of other equipment 
such as propeller feathering devices. 

(4) Each shutoff must be outside of 

the engine compartment unless an 
equal degree of safety is provided with 
the shutoff inside the compartment. 

(5) Not more than one quart of flam-

mable fluid may escape into the engine 

compartment after engine shutoff. For 
those installations where the flam-
mable fluid that escapes after shut-
down cannot be limited to one quart, it 
must be demonstrated that this greater 
amount can be safely contained or 
drained overboard. 

(6) There must be means to guard 

against inadvertent operation of each 
shutoff means, and to make it possible 
for the crew to reopen the shutoff 
means in flight after it has been closed. 

(b) Turbine engine installations need 

not have an engine oil system shutoff 
if— 

(1) The oil tank is integral with, or 

mounted on, the engine; and 

(2) All oil system components exter-

nal to the engine are fireproof or lo-
cated in areas not subject to engine 
fire conditions. 

(c) Power operated valves must have 

means to indicate to the flight crew 
when the valve has reached the se-
lected position and must be designed so 
that the valve will not move from the 
selected position under vibration con-
ditions likely to exist at the valve lo-
cation. 

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as 
amended by Amdt. 23–7, 34 FR 13096, Aug. 13, 
1969; Amdt. 23–14, 38 FR 31823, Nov. 19, 1973; 
Amdt. 23–29, 49 FR 6847, Feb. 23, 1984; Amdt. 
23–43, 58 FR 18975, Apr. 9, 1993] 

§ 23.1191

Firewalls. 

(a) Each engine, auxiliary power 

unit, fuel burning heater, and other 
combustion equipment, must be iso-
lated from the rest of the airplane by 
firewalls, shrouds, or equivalent 
means. 

(b) Each firewall or shroud must be 

constructed so that no hazardous quan-
tity of liquid, gas, or flame can pass 
from the compartment created by the 
firewall or shroud to other parts of the 
airplane. 

(c) Each opening in the firewall or 

shroud must be sealed with close fit-
ting, fireproof grommets, bushings, or 
firewall fittings. 

(d) [Reserved] 
(e) Each firewall and shroud must be 

fireproof and protected against corro-
sion. 

(f) Compliance with the criteria for 

fireproof materials or components 
must be shown as follows: 

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