CS-E 270 Lubrication System

(a)It shall not be possible for oil to drain into the Engine when it is not running, in such quantities as to introduce a risk of ‘hydraulicing’ or in any way adversely to affect the mechanical reliability of the Engine.

(b)The oil flow between the Engine lubrication system and the Propeller control system or other system utilising oil supplied by the Engine, shall not prevent oil pressure being maintained within approved limits at all operating conditions within the flight envelope, allowance being made for deterioration of the Engine.

(c)All parts of the oil system that are not inherently capable of accepting contaminants likely to be present in the oil or otherwise introduced into the oil system shall be protected by suitable filter(s) or strainer(s). These shall provide a degree of filtration sufficient to preclude damage to the Engine and Engine equipment and have adequate capacity to accommodate contaminants in relation to the specified servicing intervals. These filters or strainers may be provided as part of the aircraft; in such cases, their characteristics will be specified in the instructions for installation

(d)Adequate oil cooling shall be provided, or the required oil cooling means shall be defined in the instructions for installation, to ensure that temperature limits are not exceeded in any normal operating condition within the flight envelope.

(e)Each type of oil, and brand if appropriate, must be declared and substantiated, along with any associated limitations.

(f)Any oil characteristic which is likely to be critical for Engine functioning or durability must be identified. Where necessary, Engine or rig testing using appropriate oil shall be conducted.