ED Decision 2003/16/RM
(a) Compliance with CS 29.955 must not be jeopardised by failure of:
(1) Any one pump except pumps that are approved and installed as parts of a type certificated engine; or
(2) Any component required for pump operation except the engine served by that pump.
(b) The following fuel pump installation requirements apply:
(1) When necessary to maintain the proper fuel pressure:
(i) A connection must be provided to transmit the carburettor air intake static pressure to the proper fuel pump relief valve connection; and
(ii) The gauge balance lines must be independently connected to the carburettor inlet pressure to avoid incorrect fuel pressure readings.
(2) The installation of fuel pumps having seals or diaphragms that may leak must have means for draining leaking fuel.
(3) Each drain line must discharge where it will not create a fire hazard.
CS 29.993 Fuel system lines and fittings
ED Decision 2003/16/RM
(a) Each fuel line must be installed and supported to prevent excessive vibration and to withstand loads due to fuel pressure, valve actuation, and accelerated flight conditions.
(b) Each fuel line connected to components of the rotorcraft between which relative motion could exist must have provisions for flexibility.
(c) Each flexible connection in fuel lines that may be under pressure or subjected to axial loading must use flexible hose assemblies.
(d) Flexible hose must be approved.
(e) No flexible hose that might be adversely affected by high temperatures may be used where excessive temperatures will exist during operation or after engine shutdown.
ED Decision 2003/16/RM
In addition to meeting the requirements of CS 29.1189, each fuel valve must:
(a) Reserved.
(b) Be supported so that no loads resulting from their operation or from accelerated flight conditions are transmitted to the lines attached to the valve.
CS 29.997 Fuel strainer or filter
ED Decision 2003/16/RM
There must be a fuel strainer or filter between the fuel tank outlet and the inlet of the first fuel system component which is susceptible to fuel contamination, including but not limited to the fuel metering device or an engine positive displacement pump, whichever is nearer the fuel tank outlet. This fuel strainer or filter must:
(a) Be accessible for draining and cleaning and must incorporate a screen or element which is easily removable;
(b) Have a sediment trap and drain, except that it need not have a drain if the strainer or filter is easily removable for drain purposes;
(c) Be mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or filter itself, unless adequate strength margins under all loading conditions are provided in the lines and connections; and
(d) Provide a means to remove from the fuel any contaminant which would jeopardise the flow of fuel through rotorcraft or engine fuel system components required for proper rotorcraft or engine fuel system operation.
ED Decision 2003/16/RM
(a) There must be at least one accessible drain at the lowest point in each fuel system to completely drain the system with the rotorcraft in any ground attitude to be expected in service.
(b) Each drain required by sub-paragraph (a) including the drains prescribed in CS 29.971 must:
(1) Discharge clear of all parts of the rotorcraft;
(2) Have manual or automatic means to ensure positive closure in the off position; and
(3) Have a drain valve:
(i) That is readily accessible and which can be easily opened and closed; and
(ii) That is either located or protected to prevent fuel spillage in the event of a landing with landing gear retracted.
ED Decision 2003/16/RM
If a fuel jettisoning system is installed, the following apply:
(a) Fuel jettisoning must be safe during all flight regimes for which jettisoning is to be authorised.
(b) In showing compliance with sub-paragraph (a), it must be shown that:
(1) The fuel jettisoning system and its operation are free from fire hazard;
(2) No hazard results from fuel or fuel vapours which impinge on any part of the rotorcraft during fuel jettisoning; and
(3) Controllability of the rotorcraft remains satisfactory throughout the fuel jettisoning operation.
(c) Means must be provided to automatically prevent jettisoning fuel below the level required for an all-engine climb at maximum continuous power from sea-level to 1524 m (5000 ft) altitude and cruise thereafter for 30 minutes at maximum range engine power.
(d) The controls for any fuel jettisoning system must be designed to allow flight personnel (minimum crew) to safely interrupt fuel jettisoning during any part of the jettisoning operation.
(e) The fuel jettisoning system must be designed to comply with the powerplant installation requirements of CS 29.901(c).
(f) An auxiliary fuel jettisoning system which meets the requirements of sub-paragraphs (a), (b), (d) and (e) may be installed to jettison additional fuel provided it has separate and independent controls.