(c) Radio and electronic equipment, controls, and wiring must be installed so that ope-ration of any one unit or system of units will not adversely a.ect the simultaneous operation of any other radio or electronic unit, or system of units, required by this chapter.
FAR 25.1433 : Vacuum systems.
[ There must be means, in addition to the normal pressure relief, to automatically relieve the pressure in the discharge lines from the vacuum air pump when the delivery temperature of the air becomes unsafe.] Amdt. 25-72, E.. 8/20/90
FAR 25.1435 : Hydraulic systems.
(a)
[Element design. Eachelement of the hydraulic system must be designed to :

(1)
Withstand the proof pressure without permanent deformation that would prevent it from performing its intended functions, and the ultimate pressure without rupture.Theproof and ultimatepressuresarede.nedintermsof the design operatingpressure(DOP) asfollows:

(2)
Withstand, without deformation that would prevent it from performing its intended function, the design operating pressure in combination with limit structural loads that may be imposed;

(3)
Withstand, without rupture, the design operating pressure multiplied by a factorof1.5incombinationwith ultimatestructuralload that canreasonably occur simultaneously;

(4)
Withstand the fatigue e.ects of all cyclic pressures, including transients, and associated externally induced loads, taking into account the consequences of elementfailure; and

(5)
Perform as intended under all environmental conditions for which the airplane is certi.cated.

(b)
System design. Each hydraulic system must :

(1)
Have means located at a .ightcrew station to indicate appropriate system parameters, if

(i)
It performs a function necessary for continued safe .ight and landing; or

(ii)
In the event of hydraulic system malfunction, corrective action by the crew to ensure continued safe .ight and landing is necessary;

(2)
Have means to ensure that system pressures, including transient pressures and pressures from .uid volumetric changes in elements that are likely to remain closed long enough for such changes to occur, are within the design

Element  Proof (xDOP)  Ultimate (xDOP) 
1. Tubes and .ttings  1.5  3.0 
2. Pressure vessels containinggas : High pressure (e.g., accumulators). Low pressure (e.g., reservoirs)  3.0 1.5  4.0 3.0 
3. Hoses  2.0  4.0 
4. All other elements.  1.5  2.0 

′
Elodie Roux. Septembre 2003
Subpart F : Equipment
capabilities of each element, such that they meet the requirements de.ned in Sec. 25.1435(a)(1) through(a)(5);
(3)
Have means to minimize the release of harmful or hazardous concentrations of hydraulic .uid or vapors into the crew and passenger compartments during .ight;

(4)
Meet the applicable requirements ofSecs.25.863,25.1183,25.1185,and25.1189 if a .ammablehydraulic .uidisused; and

(5)
Be designed to use any suitable hydraulic .uid speci.ed by the airplane ma-nufacturer, which must be identi.ed by appropriate markings as required by Sec. 25.1541.

(c) Tests. Tests must be conducted on the hydraulic system(s), and/ or subsystem(s) and elements, except that analysis may be used in place of or to supplement tes-ting, where the analysis is shown to be reliable and appropriate. All internal and external in.uences must be taken into account to an extent necessary to evaluate their e.ects, and to assure reliable system and elementfunctioning andintegration. Failure or unacceptable de.ciency of an element or system must be corrected and be su.ciently retested, where necessary.
(1)
The system(s), subsystem(s), or element(s) must be subjected toperformance, fatigue,and endurancetestsrepresentativeof airplaneground and .ightope-rations.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(30)