Amdt. 25-57, E.. 3/26/84
FAR 25.999 : Fuel system drains.
(a)
Drainage of the fuel system must be accomplished by the use of fuel strainer and fuel tank sump drains.

(b)
[Eachdrain requiredbyparagraph(a)ofthis section must–

(1)
Discharge clear of all parts of the airplane :

(2)
Have manual or automatic meansforpositivelockingin the closedposition; 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. 25-38, E.. 2/1/77
FAR25.1001 :Fueljettisoning system.
(a)
Afueljettisoning system mustbeinstalled on each airplane unlessitis shownthat the airplane meets the climb requirements of Secs. 25.119 and 25.121(d) at maxi-mum takeo. weight, less the actual or computed weight of fuel necessary for a 15-minute .ight comprised of a takeo., go-around, and landing at the airport of departure with the airplane con.guration, speed, power, and thrust the same as that used in meeting the applicable takeo., approach, and landing climb perfor-mance requirements of this Part.

(b)
If afueljettisoning systemis requiredit mustbe capable ofjettisoning enoughfuel within15 minutes, starting withthe weightgiveninparagraph(a) ofthis section, to enable the airplane to meet the climb requirements ofSecs.25.119 and25.121(d), assumingthat thefuelisjettisoned under the conditions, except weight,foundleast favorableduring the .ighttestsprescribedinparagraph(c) ofthissection.

(c)
Fueljettisoning mustbedemonstratedbeginning at maximum takeo. weight with .aps and landing gear up and in–

(1)
[Apower-o.glide at1.3VSR1 ;]

(2)
Aclimb at the one-engineinoperativebest rate-of-climb speed, withthe critical engine inoperative and the remaining engines at maximum continuouspower; and

(3)
[Level .ight at 1.3VSR1, if the results of the tests in the conditions speci.ed inparagraphs(c)(1) and(2) of this section showthatthis condition couldbe critical.]

(d)
During the .ighttestsprescribedinparagraph(c) of thissection,itmustbeshown that–

(1)
Thefueljettisoning systemanditsoperationarefreefrom .rehazard;

(2)
Thefueldischarges clear of anypart of the airplane;

(3)
Fuel or fumes do not enter any parts of the airplane; and

(4)
The jettisoning operation does not adversely a.ect the controllability of the airplane.

(e)
For reciprocating engine powered airplanes, means must be provided to prevent jettisoningthefuelin the tanks usedfor takeo. andlandingbelow thelevelallowing 45 minutes .ight at 75 percent maximum continuous power. However, if there is an auxiliary controlindependent of the mainjettisoning control, the system may be designed to jettison the remaining fuel by means of the auxiliary jettisoning control.

(f)
For turbine enginepoweredairplanes, means mustbeprovided topreventjettisoning the fuel in the tanks used for takeo. and landing below the level allowing climb from sea level to 10,000 feet and thereafter allowing 45 minutes cruise at a speed for maximum range. However, if there is an auxiliary control independent of the mainjettisoning control, the system maybe designed tojettison the remainingfuel by means ofthe auxiliaryjettisoning control.

(g)
The fuel jettisoning valve must be designed to allow .ight personnel to close the valveduring anypart of thejettisoning operation.

(h)
Unlessitisshownthatusing any means(including .aps,slots,and slats) forchan-gingthe air.ow across or aroundthe wingsdoes notadversely a.ectfueljettisoning, theremustbeaplacard,adjacenttothejettisoning control,towarn .ightcrew-membersagainstjettisoningfuel whilethe meansthatchangethe air.owarebeing used.
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 3(120)