(d)
If installed communication equipment includes transmitter ”o.-on” switching, that switching meansmustbedesigned toreturnfromthe ”transmit” tothe ”o.” posi-tion whenitis released and ensurethatthetransmitter will returntothe o.(non transmitting) state.
(e)
Ifprovisionsfor the use ofcommunicationheadsets areprovided,it mustbedemons-trated that the .ightcrew members will receive all aural warnings under the actual cockpit noise conditions when the airplane is being operated when any headset is being used.]
Amdt. 23-49, E.. 03/11/96
FAR 23.1435 : Hydraulic systems.
(a) Design. Each hydraulic system must be designed as follows :
(1)
Eachhydraulicsystem andits elements must withstand, withoutyielding,the structural loads expected in addition to hydraulic loads.
(2)
A means to indicate the pressure in each hydraulic system which supplies two or more primary functions must be provided to the .ight crew.
(3)
There mustbe meansto ensurethatthepressure,including transient(surge) pressure,in anypartof the system will not exceed the safelimit abovedesign operating pressure and to prevent excessive pressure resulting from .uid vo-lumetric changes in all lines which are likely to remain closed long enough for such changes to occur.
(4)
The minimumdesignburstpressuremustbe2.5 timesthe operatingpressure.
(b)
Tests.Each system mustbe substantiatedbyproofpressuretests.Whenproof tes-ted, no part of any system may fail, malfunction, or experience a permanent set. The proof load of each system must be at least 1.5 times the maximum operating pressure of that system.
(c)
[Accumulators. A hydraulic accumulator or reservoir may be installed on the engine side of any .rewall, if–
(1)
Itis anintegralpart of an engine orpropeller system, or
(2)
The reservoir is nonpressurized and the total capacity of all such nonpressuri-zed reservoirs is one quart or less.]
Amdt. 23-49, E.. 03/11/96
FAR 23.1437 : Accessories for multiengine airplanes.
For multiengine airplanes, engine-driven accessories essential to safe operation must be distributed among two or more engines so that the failure of any one engine will not impair safe operation through the malfunctioning of these accessories.
FAR23.1438 :[Pressurization andpneumatic systems.]
(a)
[Pressurization system elements mustbeburstpressuretestedto2.0times, andproof pressure tested to 1.5 times, the maximum normal operating pressure.
(b)
Pneumatic system elements must be burst pressure tested to 3.0 times, and proof pressure tested to 1.5 times, the maximum normal operating pressure.
(c)
An analysis, or a combination of analysis and test, may be substituted for any testrequiredbyparagraph(a) or(b) ofthissectioniftheAdministrator .ndsit equivalent to the required test.]
Amdt. 23-20, E.. 09/01/77
FAR 23.1441 : Oxygen equipment and supply.
(a)
[If certi.cation with supplemental oxygen equipment is requested, or the airplane is approved for operations at or above altitudes where oxygen is required to be used by the operating rules, oxygen equipment must meet the requirements of this section andSecs.23.1443through23.1449.Portable oxygen equipment maybe used tomeetthe requirementsof thispartif theportableequipmentisshowntocomply with the applicable requirements, is identi.ed in the airplane type design, and its stowage provisions are found to be in compliance with the requirements of Sec. 23.561.]
(b)
The oxygen system must be free from hazards in itself, in its method of operation, and its e.ect upon other components.
(c)
There must be a means to allow the crew to readily determine, during the .ight, the quantity of oxygen available in each source of supply.
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Elodie Roux. Septembre 2003
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(96)
