801 

Federal Aviation Administration, DOT 

§ 29.1303 

§ 29.1201

Fire extinguishing system 

materials. 

(a) No materials in any fire extin-

guishing system may react chemically 
with any extinguishing agent so as to 
create a hazard. 

(b) Each system component in an en-

gine compartment must be fireproof. 

§ 29.1203

Fire detector systems. 

(a) For each turbine engine powered 

rotorcraft and Category A recipro-
cating engine powered rotorcraft, and 
for each Category B reciprocating en-
gine powered rotorcraft with engines of 
more than 900 cubic inches displace-
ment, there must be approved, quick- 
acting fire detectors in designated fire 
zones and in the combustor, turbine, 
and tailpipe sections of turbine instal-
lations (whether or not such sections 
are designated fire zones) in numbers 
and locations ensuring prompt detec-
tion of fire in those zones. 

(b) Each fire detector must be con-

structed and installed to withstand any 
vibration, inertia, and other loads to 
which it would be subjected in oper-
ation. 

(c) No fire detector may be affected 

by any oil, water, other fluids, or 
fumes that might be present. 

(d) There must be means to allow 

crewmembers to check, in flight, the 
functioning of each fire detector sys-
tem electrical circuit. 

(e) The writing and other components 

of each fire detector system in an en-
gine compartment must be at least fire 
resistant. 

(f) No fire detector system compo-

nent for any fire zone may pass 
through another fire zone, unless— 

(1) It is protected against the possi-

bility of false warnings resulting from 
fires in zones through which it passes; 
or 

(2) The zones involved are simulta-

neously protected by the same detector 
and extinguishing systems. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 970, Jan. 26, 
1968] 

Subpart F—Equipment 

G

ENERAL

 

§ 29.1301

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. 

§ 29.1303

Flight and navigation instru-

ments. 

The following are required flight and 

navigational instruments: 

(a) An airspeed indicator. For Cat-

egory A rotorcraft with V

NE

less than a 

speed at which unmistakable pilot cues 
provide overspeed warning, a maximum 
allowable airspeed indicator must be 
provided. If maximum allowable air-
speed varies with weight, altitude, 
temperature, or r.p.m., the indicator 
must show that variation. 

(b) A sensitive altimeter. 
(c) A magnetic direction indicator. 
(d) A clock displaying hours, min-

utes, and seconds with a sweep-second 
pointer or digital presentation. 

(e) A free-air temperature indicator. 
(f) A non-tumbling gyroscopic bank 

and pitch indicator. 

(g) A gyroscopic rate-of-turn indi-

cator combined with an integral slip- 
skid indicator (turn-and-bank indi-
cator) except that only a slip-skid indi-
cator is required on rotorcraft with a 
third attitude instrument system 
that— 

(1) Is usable through flight attitudes 

of 

±

80 degrees of pitch and 

±

120 degrees 

of roll; 

(2) Is powered from a source inde-

pendent of the electrical generating 
system; 

(3) Continues reliable operation for a 

minimum of 30 minutes after total fail-
ure of the electrical generating system; 

(4) Operates independently of any 

other attitude indicating system; 

(5) Is operative without selection 

after total failure of the electrical gen-
erating system; 

VerDate Mar<15>2010 

10:12 Mar 18, 2014

Jkt 232046

PO 00000

Frm 00811

Fmt 8010

Sfmt 8010

Y:\SGML\232046.XXX

232046

pmangrum on DSK3VPTVN1PROD with CFR