ED Decision 2003/18/RM
(a) The engine must be isolated from the rest of the aeroplane by a firewall, shroud or equivalent means.
(b) The firewall or shroud must be constructed so that no hazardous quantity of liquid, gas or flame can pass from the engine compartment to other parts of the aeroplane.
(c) Each opening in the firewall or shroud must be sealed with close fitting, fireproof grommets, bushings, or firewall fittings.
(d) The firewall and shroud must be fireproof and protected against corrosion.
(e) The following materials are accepted as fireproof, when used in firewalls or shrouds, without being tested:
(1) Stainless steel sheet, 0.38 mm thick;
(2) Mild steel sheet (coated with aluminium or otherwise protected against corrosion) 0.5 mm thick; and
(3) Steel or copper base alloy firewall fittings.
(f) Compliance with the criteria for fireproof materials or components must be shown as follows:
(1) The flame to which the materials or components are subjected must be 1100 ±25°C.
(2) Sheet materials approximately 64 cm2 must be subjected to the flame from a suitable burner.
(3) The flame must be large enough to maintain the required test temperature over an area approximately 13 mm square.
(4) Firewall materials and fittings must resist penetration for at least 15 minutes.
Loading collections...