КОМПОНЕНТИ НА ГОРИВНАТА СИСТЕМА

(a) Each fuel line must be installed and

supported to prevent excessive vibration and to

withstand loads due to fuel pressure 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) Flexible hose must be approved.

(d) Each flexible connection in fuel lines

that may be under pressure or subjected to axial

loading must use flexible hose assemblies.

(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.

(a) There must be a positive, quick-acting

valve to shut-off fuel to each engine

individually.

(b) The control for this valve must be

within easy reach of appropriate crew members.

(c) Where there is more than one source of

fuel supply there must be means for independent

feeding from each source.

(d) No shut-off valve may be on the engine

side of any firewall.

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 fuel system or engine fuel system

operation.

(d) Да осигурява средство за премахване всеки замърсител от горивото, който би представлявал заплаха за горивния поток през компонентите на роторкрафтната или двигателната горивна система, които са необходими за правилното функциониране на роторкрафтната или двигателната горивна система.

(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) of this paragraph must –

(1) Discharge clear of all parts of the

rotorcraft;

(2) Have manual or automatic means

to assure positive closure in the off position;

and

(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.

(a) Each engine must have an independent

oil system that can supply it with an appropriate

quantity of oil at a temperature not above that

safe for continuous operation.

(b) The usable oil capacity of each system

may not be less than the product of the

endurance of the rotorcraft under critical

operating conditions and the maximum oil

consumption of the engine under the same

conditions, plus a suitable margin to ensure

adequate circulation and cooling. Instead of a

rational analysis of endurance and consumption,

a usable oil capacity of 3.8 litres (0.83 Imperial

gallon /l US gallon) for each 151.4 litres (33.3

Imperial gallons/40 US gallons) of usable fuel

may be used.

(c) The oil cooling provisions for each

engine must be able to maintain the oil inlet

temperature to that engine at or below the

maximum established value. This must be

shown by flight tests.