Document ID: chunk:federal_register_of_legislation:F2005B00951:body:0:p6
Version: federal_register_of_legislation:F2005B00951
Segment Type: other
Provision Reference: 
Character Range: 12579–15410

tank sump arrangement is impracticable a separate sediment bowl may be accepted provided it can be clearly demonstrated that the capacity of the sediment bowl is adequate for the purpose and that water will automatically drain from all parts of the tank to the sediment bowl when the aeroplane is in the normal ground attitude.
3.20 Fuel system

 (1) Each fuel system shall be constructed and arranged to ensure that a fuel flow rate of at least 125% of the take-off fuel consumption of the engine(s) can be achieved under the most adverse conditions of aircraft attitude and fuel quantity.

 (2) The fuel system shall be free from inverted "U" bends and other possible causes of air and vapour locks.
3.21 Powerplant cooling

The powerplant cooling provisions shall be capable of maintaining the temperatures of the engines, components, equipment and engine fluids within the relevant manufacturer's established safe values for all conditions of flight and ground operation liable to occur within the limits of the ICAO intercontinental maximum standard climate.
3.22 Induction system icing protection

Engine air induction systems shall be designed and installed to prevent and eliminate icing.
3.23 Powerplant fire protection

 (1) Except as provided in subparagraph (2) following, all line and hose assemblies carrying flammable fluids in engine compartments shall be fire resistant and the hose assemblies shall be of an approved type. For this purpose such components may be deemed to comply if capable of withstanding, at maximum working pressure, exposure to flame at a temperature of 1 090 ±30C for 5 minutes without failure.
        Note: Flexible hose assemblies approved as 'fire resistant' by the CAA or approved for use in engine compartments by the CAA or the FAA are acceptable, as are rigid lines and fittings composed of steel or copper-base alloys. Wire-braided flexible hose assemblies Types C and D of the FAA Technical Standard Order C53a ('normal' or 'high' temperature as appropriate) are acceptable, but, Types A and B are not likewise acceptable unless either their working pressures are less than 210 kPa or they are protected by properly secured external fire sleeves.

 (2) The requirements of this subparagraph need not be applied to breather, vent and drain lines, the failure of which will not result in, or significantly add to, a fire hazard.

 (3) Each engine compartment firewall or shroud shall be constructed of fireproof material and all openings in such firewall or shroud shall be sealed with close-fitting fireproof grommets, bushings or fittings, except that fire resistant seals may be used where the openings concerned would not allow the passage of a hazardous amount of flame in the absence of seals.
EQUIPMENT
3.24 Instruments and indications

 (1) The scale graduations of airspeed