(c)
Flexible hose must be approved.
(d)
[Each .exible connection in fuel lines that may be under pressure or subjected to axial loading must use .exible hose assemblies.
(e)
No .exible hose that might be adversely a.ected by high temperatures may be used where excessive temperatures will existduring operation or after engine shutdown.]
Amdt. 27-2, E.. 2/25/68
FAR 27.995 : Fuel valves
(a)
There must be a positive, quick-acting valve to shut o. fuel to each engine indivi-dually.
(b)
The control for this valve must be within easy reach of appropriate crewmembers.
(c)
Where there is more than one source of fuel supply there must be means for inde-pendent feeding from each source.
(d)
No shuto. valve may be on the engine side of any .rewall.
FAR 27.997 : Fuel strainer or .lter
[There must be a fuel strainer or .lter between the fuel tank outlet and the inlet of the .rst 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 .lter 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 .lter 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 .lter itself, unless adequate strength margins under allloading conditions areprovidedin the lines and connections; and
(d)
[Provide a meansto removefromthefuelany contaminant which wouldjeopardize the .ow of fuel through rotorcraft or engine fuel system components required for proper rotorcraft fuel system or engine fuel system operation.]
Amdt. 27-23, E.. 10/3/88
FAR 27.999 : Fuel system drains
(a)
[There must be at least one accessible drain at the lowest point in each fuelsystem to completely drain the system with the rotorcraft in any ground attitude to be expected in service.]
(b)
Eachdrain requiredbyparagraph(a) ofthis section must–
(1)
Discharge clear of all parts of the rotorcraft;
(2)
[Have manualor automatic means to assurepositive closurein the o.position; and]
(3)
Have a drain valve–
(i)
That is readily accessible and which can be easily opened and closed; and
(ii)
Thatis eitherlocated orprotected topreventfuel spillageinthe eventof a landing with landing gear retracted.
Amdt. 27-23, E.. 10/3/88
65.5 Oil System
FAR27.1011 :[Engines :] general
(a)
Each engine must have an independent oil system that can supply it with an appro-priatequantityof oil at a temperature not above that safefor 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 underthe sameconditions,plus a suitable marginto ensure adequate circulation and cooling.Instead of a rational analysis of endurance and consumption, a usable oil capacity of one gallon for each 40 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 .ight tests.
Amdt. 27-23, E.. 10/3/88
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 27.1013 : Oil tanks
Each oil tank must be designed and installed so that–
(a)
It can withstand, without failure, each vibration, inertia, .uid, and structural load expected in operation;
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(112)
