(1)
Forreciprocating enginepowered airplanes,the enginesmust operateatmaxi-mum continuous power, except that takeo. power must be used for the alti-tudes from 1,000 feet below the critical altitude through the critical altitude. The time interval during which takeo.poweris used may notbe less than the takeo. time limitation.

(2)
For turbine engine powered airplanes, the engines must operate at takeo. po-wer for the time interval selected for showing the takeo. .ight path, and at maximum continuouspowerforthe rest of the climb.

(3)
The weight of the airplane must be the weight with full fuel tanks, minimum crew, and the ballast necessary to maintain the center of gravity within allo-wable limits.

(4)
The climb airspeed may not exceed–

(i)
[For reciprocatingengine powered airplanes, the maximum airspeed esta-blishedfor climbingfrom takeo. to the maximum operating altitude with the airplane in the following con.guration :

(A)
Landing gear retracted.

(B)
Wing .apsinthemostfavorableposition.

(C)
Cowl .aps(orothermeansof controlling theenginecooling supply) in the position that provides adequate cooling in the hot-day condi-tion.

(D)
Engine operatingwithin the maximum continuouspowerlimitations.

(E)
Maximum takeo. weight; and]

(ii)
Forturbine enginepowered airplanes,the maximumairspeed established for climbing from takeo. to the maximum operating altitude.

(5)
The fuel temperature must be at least 110'F.

(b)
Thetestprescribedinparagraph(a) ofthissectionmaybeperformedin .ightor ontheground underclosely simulated .ight conditions.If a .ighttestisperformed in weather cold enough to interfere with the proper conduct of the test, the fuel tank surfaces, fuel lines, and other fuel system parts subject to cold air must be insulated to simulate, insofar as practicable, .ight in hot weather.

Amdt. 25-57, E.. 3/26/84
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 25.963 : Fuel tanks : general.
(a)
Each fuel tank must be able to withstand, without failure, the vibration, inertia, .uid, and structural loads that it may be subjected to in operation.

(b)
Flexible fuel tank liners must be approved or must be shown to be suitable for the particular application.

(c)
Integral fuel tanks must have facilities for interior inspection and repair.

(d)
Fuel tanks within the fuselage contour must be able to resist rupture, and to retain fuel, under theinertiaforcesprescribedfor the emergencylandingconditionsinSec.

25.561. In addition, these tanks must be in a protected position so that exposure of the tanks to scraping action with the ground is unlikely.

(e)
[Fuel tank access covers must comply with the following criteria in order to avoid loss ofhazardousquantities offuel:

(1)
All covers located in an area where experience or analysis indicates a strike is likely must be shown by analysis or tests to minimize penetration and deformationby tirefragments,low energy enginedebris, or otherlikelydebris.

(2)
All covers must be .re resistant as de.ned in Part 1 of this chapter.]

(f)
Forpressurizedfueltanks,a means withfail-safefeatures mustbeprovidedtoprevent the buildup of an excessive pressure di.erence between the inside and the outside of the tank.

Amdt. 25-69, E.. 10/30/89
FAR 25.965 : Fuel tank tests.
(a)
It must be shown by tests that the fuel tanks, as mounted in the airplane can withstand, without failure or leakage, the more critical of the pressures resulting fromthe conditions speci.edin subparagraphs(1) and(2) ofthisparagraph.In addition, it must be shown by either analysis or tests, that tank surfaces subjected to more criticalpressuresresulting fromthe condition of subparagraph(3) and(4) of thisparagraph, are ableto withstandthefollowingpressures:
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(115)