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14 CFR Ch. I (1–1–24 Edition) 

§ 27.1194 

(f) A means of retaining each open-

able or readily removable panel, cowl-
ing, or engine or rotor drive system 
covering must be provided to preclude 
hazardous damage to rotors or critical 
control components in the event of 
structural or mechanical failure of the 
normal retention means, unless such 
failure is extremely improbable. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–23, 53 FR 34214, Sept. 2, 
1988] 

§ 27.1194

Other surfaces. 

All surfaces aft of, and near, power-

plant compartments, other than tail 
surfaces not subject to heat, flames, or 
sparks emanating from a powerplant 
compartment, must be at least fire re-
sistant. 

[Amdt. 27–2, 33 FR 964, Jan. 26, 1968] 

§ 27.1195

Fire detector systems. 

Each turbine engine powered rotor-

craft must have approved quick-acting 
fire detectors in numbers and locations 
insuring prompt detection of fire in the 
engine compartment which cannot be 
readily observed in flight by the pilot 
in the cockpit. 

[Amdt. 27–5, 36 FR 5493, Mar. 24, 1971] 

Subpart F—Equipment 

G

ENERAL

 

§ 27.1301

Function and installation. 

Each item of installed equipment 

must— 

(a) Be of a kind and design appro-

priate to its intended function; 

(b) Be labeled as to its identification, 

function, or operating limitations, or 
any applicable combination of these 
factors; 

(c) Be installed according to limita-

tions specified for that equipment; and 

(d) Function properly when installed. 

§ 27.1303

Flight and navigation instru-

ments. 

The following are the required flight 

and navigation instruments: 

(a) An airspeed indicator. 
(b) An altimeter. 
(c) A magnetic direction indicator. 

§ 27.1305

Powerplant instruments. 

The following are the required power-

plant instruments: 

(a) A carburetor air temperature in-

dicator, for each engine having a pre-
heater that can provide a heat rise in 
excess of 60 

°

F. 

(b) A cylinder head temperature indi-

cator, for each— 

(1) Air cooled engine; 
(2) Rotorcraft with cooling shutters; 

and 

(3) Rotorcraft for which compliance 

with § 27.1043 is shown in any condition 
other than the most critical flight con-
dition with respect to cooling. 

(c) A fuel pressure indicator, for each 

pump-fed engine. 

(d) A fuel quantity indicator, for each 

fuel tank. 

(e) A means to indicate manifold 

pressure for each altitude engine. 

(f) An oil temperature warning device 

to indicate when the temperature ex-
ceeds a safe value in each main rotor 
drive gearbox (including any gearboxes 
essential to rotor phasing) having an 
oil system independent of the engine 
oil system. 

(g) An oil pressure warning device to 

indicate when the pressure falls below 
a safe value in each pressure-lubricated 
main rotor drive gearbox (including 
any gearboxes essential to rotor phas-
ing) having an oil system independent 
of the engine oil system. 

(h) An oil pressure indicator for each 

engine. 

(i) An oil quantity indicator for each 

oil tank. 

(j) An oil temperature indicator for 

each engine. 

(k) A means to indicate the r.p.m. of 

each engine and at least one tachom-
eter, as applicable, for: 

(1) The r.p.m. of the single main 

rotor; 

(2) The common r.p.m. of any main 

rotors whose speeds cannot vary appre-
ciably with respect to each other; or 

(3) The r.p.m. of each main rotor 

whose speed can vary appreciably with 
respect to that of another main rotor. 

(l) A low fuel warning device for each 

fuel tank which feeds an engine. This 
device must— 

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