(b)
Thedynamic e.ects of the operation of these(including consideration ofprobable malfunctions) upon the aerodynamic control of the airplane may not result in any condition that would require exceptional skill, alertness, or strength on the part of thepilotto avoid exceeding anoperational orstructurallimitation of the airplane; and

(c)
In showingcompliance withparagraph(b) of this section, thepilot strength required may not exceed the limits set forth in Sec. 25.143(c), subject to the conditions set forthinparagraph(d) and(e) ofSec.25.143.]

Amdt. 25-38, E.. 2/1/77
FAR25.943 :[Negative acceleration.]
[No hazardous malfunction ofan engine, an auxiliary power unit approved for use in .ight, or any component or system associated with the powerplant or auxiliary power unit may occur when the airplane is operated at the negative accelerations within the .ight envelopesprescribedinSec.25.333.This mustbe shownforthegreatestduration expected for the acceleration.] Amdt. 25-40, E.. 5/2/77
FAR 25.945 : Thrust or power augmentation system.
(a)
General. Each .uid injection system must provide a .ow of .uid at the rate and pressure established for proper engine functioning under each intended operating condition. If the .uid can freeze, .uid freezing may not damage the airplane or adversely a.ect airplane performance.

(b)
Fluid tanks. Each augmentation system .uid tank must meet the following require-ments :

(1)
Each tank must be able to withstand without failure the vibration, inertia, .uid, and structural loads that it may be subject to in operation.

(2)
The tanks as mountedin the airplane mustbe able to withstandwithoutfailure orleakage aninternalpressure1.5 timesthe maximum operatingpressure.

(3)
If a vent is provided, the venting must be e.ective under all normal .ight conditions.

(4)
[[Reserved.]]

(c)
Augmentation system drains must be designed and located in accordance with Sec. 25.1455 if–

(1)
The augmentation system .uid is subject to freezing; and

(2)
The .uid may be drained in .ight or during ground operation.

(d)
The augmentation liquid tank capacity available for the use of each engine must be large enough to allow operation of the airplane underthe approvedproceduresfor the use of liquid-augmented power. The computation of liquid consumption must bebased onthe maximumapproved rateappropriateforthedesired engineoutput and must include the e.ect of temperature on engine performance as well as any other factors that might vary the amount of liquid required.

(e)
This section does not apply to fuel injection systems. Amdt. 25-72, E.. 8/20/90

48.2 Fuel System
FAR 25.951 : General.
(a)
Eachfuel systemmustbe constructed and arranged toensurea .owoffuel at arate andpressure establishedforproper engine and auxiliarypower unitfunctioning un-der each likely operating condition, including any maneuver for which certi.cation is requested and during which the engine or auxiliary power unit is permitted to be in operation.

(b)
Each fuel system must be arranged so that any air which is introduced into the system will not result in–

(1)
Powerinterruptionfor morethan20 secondsfor reciprocating engines; or

(2)
Flameout for turbine engines.

(c)
Each fuel system for a turbine engine must be capable of sustained operation throu-ghout its .ow and pressure range with fuel initially saturated with water at 80'F and having 0.75cc of free water per gallon added and cooled to the most critical condition for icing likely to be encountered in operation.

(d)
[Each fuel system for a turbine engine powered airplane must meet the applicable

fuel venting requirements of Part 34 of this chapter.] Amdt. 25-73, E.. 9/10/90
　
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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(113)