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FAR 29.999 : Fuel system drains.
(a)
[There mustbe atleastone accessibledrain at thelowestpointin eachfuel sys-tem to completelydrain the system with the rotorcraftin anyground attitude to be expected in service.]
(b)
Eachdrainrequiredbyparagraph(a) of this sectionincluding thedrainspres-cribed in Sec. 29.971 must–
(1)
Discharge clear of all parts of the rotorcraft;
(2)
[Have manual or automatic means to ensure positive closure in 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 spillagein the vent of a landing with landing gear retracted.
Amdt. 29-26, E.. 10/3/88
FAR29.1001 :[Fueljettisoning.]
[Ifafueljettisoning systemisinstalled,thefollowing apply :
(a)
Fueljettisoning mustbesafeduring all .ightregimesforwhichjettisoningis to be authorized.
(b)
Inshowing compliancewithparagraph(a) ofthis section,itmustbe shown that–
(1) Thefueljettisoning systemanditsoperationarefreefrom .rehazard;
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(2)
No hazard results from fuel or fuel vapors which impinge on any part of the rotorcraftduring fueljettisoning; and
(3)
Controllability of the rotorcraft remains satisfactory throughout the fuel jettisoningoperation.
(c)
Means mustbeprovidedto automaticallypreventjettisoningfuelbelowthe level requiredfor an all-engine climb at maximum continuouspowerfrom sea level to 5,000 feet attitude and cruise thereafter for 30 minutes at maximum range engine power.
(d)
Thecontrolsforanyfueljettisoning systemmustbedesignedtoallow .ight personnel(minimum crew) to safelyinterruptfueljettisoning during anypart ofthejettisoning operation.
(e)
Thefueljettisoning system mustbedesigned to comply with thepowerplant installation requirements of Sec. 29.901(c).
(f)
An auxiliary fuel jettisoning system which meets the requirements of para-graphs(a),(b),(d), and(e) ofthis section may beinstalledtojettison addi-tional fuel provided it has separate and independent controls.]
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75.5 Oil System
FAR 29.1011 : Engines : General.
(a)
Each engine must have an independent oil system that can supply it with an appropriatequantity of oil at a temperature not above that safefor continuous operation.
(b)
[The usable oil capacityof each system may not be less than the product of the endurance of the rotorcraft under critical operating conditions and the maximum allowable 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 one gallon for each 40 gallons of usable fuel may be used for reciprocating engine installations.
(c)
Oil-fuel ratioslower than thoseprescribedinparagraph(b) of this section may be usedif they are substantiatedbydata on the oil consumption of the engine.
(d)
] The ability of the engine oil cooling provisions to maintain the oil tempe-rature at or below the maximum established value must be shown under the applicable requirements of Secs. 29.1041 through 29.1049.
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FAR 29.1013 : Oil tanks.
(a)
[Installation. Each oil tank installation must meet the requirements of Sec. 29.967.]
(b)
Expansion space. Oil tank expansion space must be provided so that–
(1)
[Eachoil tank used with a reciprocating engine has an expansion space of notlessthanthegreater of10percent of thetank capacity or0.5gallon, and each oil tank used with a turbine engine has an expansion space of not less than 10 percent of the tank capacity;]
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 5(72)
