Text in force at CS29-12: from CS29-0, effective 14 Nov 2003.
(a) For each turbine engine powered rotorcraft and Category A reci procating engi ne powered rotorcraft, and for each Category B reciprocating engi ne powered rotorcraft with engines of m ore t han 14 748 cm3 (900 cubi c inches) displacem ent there m ust be approved, quick-acting fire detectors in designated fire zones and in th e co mbustor, tu rbine, and tailpipe sections of turbine i nstallations (whet her or not such sect ions are desi gnated fi re zones) in numbers and l ocations ensuri ng prompt detection of fire in those zones.
(b) Each fi re det ector m ust be const ructed and in stalled to with stand any vibration, inertia and other loads to which it would be subject ed in operation.
(c) No fire detector m ay be affected by any oil, water, other fluids, or fum es t hat m ight be present.
(d) There must be m eans to allow crew members to check, in fl ight, t he funct ioning of each fire detector system electrical circuit.
(e) The wiring and othe r components of each fire detector system in an engine com partment must be at least fire resistant.
(f) No fire detector system com ponent for any fire zone m ay pass t hrough another fire zone, unless –
(1) It is protected against the possibility of false warnings resu lting from fires in zones through which it passes; or
(2) The zones i nvolved are simultaneously prot ected by t he sam e detector and extinguishing systems.
ED Decision 2003/016/RM · Source