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545 

Federal Aviation Administration, DOT 

§ 27.1193 

means are used to prevent heat trans-
fer from each engine compartment to 
the flammable fluid. 

(d) Absorbent materials close to 

flammable fluid system components 
that might leak must be covered or 
treated to prevent the absorption of 
hazardous quantities of fluids. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–2, 33 FR 964, Jan. 26, 
1968; Amdt. 27–11, 41 FR 55470, Dec. 20, 1976; 
Amdt. 27–37, 64 FR 45095, Aug. 18, 1999] 

§ 27.1187

Ventilation and drainage. 

Each compartment containing any 

part of the powerplant installation 
must have provision for ventilation 
and drainage of flammable fluids. The 
drainage means must be— 

(a) Effective under conditions ex-

pected to prevail when drainage is 
needed, and 

(b) Arranged so that no discharged 

fluid will cause an additional fire haz-
ard. 

[Doc. No. 29247, 64 FR 45095, Aug. 18, 1999] 

§ 27.1189

Shutoff means. 

(a) There must be means to shut off 

each line carrying flammable fluids 
into the engine compartment, except— 

(1) Lines, fittings, and components 

forming an intergral part of an engine; 

(2) For oil systems for which all com-

ponents of the system, including oil 
tanks, are fireproof or located in areas 
not subject to engine fire conditions; 
and 

(3) For reciprocating engine installa-

tions only, engine oil system lines in 
installation using engines of less than 
500 cu. in. displacement. 

(b) There must be means to guard 

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

(c) Each shutoff valve and its control 

must be designed, located, and pro-
tected to function properly under any 
condition likely to result from an en-
gine fire. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–2, 33 FR 964, Jan. 26, 
1968; Amdt. 27–20, 49 FR 6850, Feb. 23, 1984; 
Amdt. 27–23, 53 FR 34214, Sept. 2, 1988] 

§ 27.1191

Firewalls. 

(a) Each engine, including the com-

bustor, turbine, and tailpipe sections of 
turbine engines must be isolated by a 
firewall, shroud, or equivalent means, 
from personnel compartments, struc-
tures, controls, rotor mechanisms, and 
other parts that are— 

(1) Essential to a controlled landing: 

and 

(2) Not protected under § 27.861. 
(b) Each auxiliary power unit and 

combustion heater, and any other com-
bustion equipment to be used in flight, 
must be isolated from the rest of the 
rotorcraft by firewalls, shrouds, or 
equivalent means. 

(c) In meeting paragraphs (a) and (b) 

of this section, account must be taken 
of the probable path of a fire as af-
fected by the airflow in normal flight 
and in autorotation. 

(d) Each firewall and shroud must be 

constructed so that no hazardous quan-
tity of air, fluids, or flame can pass 
from any engine compartment to other 
parts of the rotorcraft. 

(e) Each opening in the firewall or 

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

(f) Each firewall and shroud must be 

fireproof and protected against corro-
sion. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–2, 22 FR 964, Jan. 26, 
1968] 

§ 27.1193

Cowling and engine compart-

ment covering. 

(a) Each cowling and engine compart-

ment covering must be constructed and 
supported so that it can resist the vi-
bration, inertia, and air loads to which 
it may be subjected in operation. 

(b) There must be means for rapid 

and complete drainage of each part of 
the cowling or engine compartment in 
the normal ground and flight attitudes. 

(c) No drain may discharge where it 

might cause a fire hazard. 

(d) Each cowling and engine compart-

ment covering must be at least fire re-
sistant. 

(e) Each part of the cowling or engine 

compartment covering subject to high 
temperatures due to its nearness to ex-
haust system parts or exhaust gas im-
pingement must be fireproof. 

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