(vi)
That is either located or protected to prevent fuel spillage in the event of a landing with landing gear retracted.]

Amdt. 23-43, E.. 05/10/93
FAR23.1001 :Fueljettisoning system.
(a)
If the design landing weight is less than that permitted under the requirements of Sec. 23.473(b), the airplane must have a fuel jettisoning system installed that is able to jettison enough fuel to bring the maximum weight down to the design landing weight.The average rate offueljettisoning mustbe atleast1percent of the maximum weightper minute, exceptthatthetime required tojettisonthefuel need not be less than 10 minutes.

(b)
Fueljettisoning mustbedemonstrated atmaximumweightwith .apsandlanding gear up and in–

(1)
Apower-o.glide at1.4VS1 ;

(2)
[Aclimb, at the speed at which the one-engine-inoperative enroute climb data havebeen establishedin accordance withSec.23.69(b), withthe criticalengine inoperative and the remaining engines at maximum continuouspower; and]

(3)
Level .ight at 1.4VS1, if the results of the tests in the conditions speci.ed in paragraphs(b)(1) and(2) ofthis section showthatthis condition couldbe critical.

(c)
During the .ighttestsprescribedinparagraph(b) 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.

(d)
For reciprocatingenginepowered airplanes, thejettisoning system mustbe designed so thatitis notpossible tojettison thefuelin the tanks usedfor takeo. andlanding belowthelevelallowing45 minutes .ight at75percent maximumcontinuouspower. However,ifthereis an auxiliary controlindependent ofthe mainjettisoning control, the system may bedesigned tojettison all thefuel.

(e)
For turbine engine powered airplanes, the jettisoning system must be designed so thatis notpossibletojettisonfuelinthetanks usedfortakeo. andlanding below the level allowing from sea level to 10,000 feet and thereafter allowing 45 minutes cruise at a speed for maximum range.

(f)
Thefueljettisoning valvemustbedesigned toallow .ightcrewmemberstoclosethe valveduring anypart of thejettisoning operation.

(g)
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.

′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(h) Thefueljettisoning systemmustbedesigned sothat any reasonableprobablesingle malfunction in the system will not result in a hazardous condition due to unsym-metricaljettisoning of, orinability tojettison,fuel.
Amdt. 23-51, E.. 03/11/96
32.4 Oil System
FAR 23.1011 : General.
(a)
[For oilsystems and components that have been approved under the engine airwor-thiness requirements and where those requirements are equalto or more severethan the corresponding requirements of subpart E of this part, that approval need not be duplicated. Where the requirements of subpart E of this part are more severe, substantiation must be shown to the requirements of subpart E of this part.

(b)
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.

(c)
The usable oil tank capacity may not be less than the product of the endurance of the airplane under critical operating conditions and the maximum oil consumption of the engineunderthe sameconditions,plus asuitablemargintoensureadequate circulation and cooling.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(64)