(e)
Each turbine engine ignition system must be independent of any electrical circuit thatis not usedfor assisting, controlling, or analyzingthe operation of that system.
(f)
[In addition, for commuter categoryairplanes, each turbopropeller ignition system must be an essential electrical load.]
Amdt. 23-34, E. 02/17/87
32.10 Powerplant Fire Protection
FAR23.1181:Designated .rezones; regionsincluded.
Designated .re zones are–
(a)
For reciprocating engines–
(1)
Thepower section;
(2)
The accessory section;
(3)
Any completepowerplantcompartmentin which thereis noisolationbetween the power section and the accessory section.
(b)
For turbine engines–
(1)
The compressor and accessory sections;
(2)
Thecombustor,turbineand tailpipe sectionsthat containlinesorcomponents carrying .ammable .uids or gases.
(3)
[Anycompletepowerplant compartmentin which thereis noisolationbetween compressor, accessory, combustor, turbine, and tailpipe sections.]
(c)
Any auxiliarypower unit compartment; and
(d)
Any fuel-burning heater, and other combustion equipment installation described in Sec. 23.859.
Amdt. 23-51, E.. 03/11/96
FAR23.1182:[Nacelleareasbehind .rewalls.]
[Components,lines,and.ttings,exceptthosesubjecttotheprovisionsofSec.23.1351(e), located behind the engine-compartment .rewall must be constructed of such materials andlocated atsuchdistancesfromthe .rewall thatthey will notsu.erdamagesu.cient to endanger the airplane if a portion of the engine side of the .rewall is subjected to a .ame temperature of not less than 2000'F for 15 minutes.] Amdt. 23-14, E.. 12/20/73
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.1183 : Lines, .ttings and components.
(a)
Exceptasprovidedinparagraph(b) ofthissection,each component,line,and.tting carrying .ammable .uids, gas, or air in any area subject to engine .re conditions must be at least .re resistant, except that .ammable .uid tanks and supports which are part of and attached to the engine must be .reproof or be enclosed by a .reproof shield unless damage by .re to any non-.reproof part will not cause leakage or spillage of .ammable .uid. Components must be shielded or located so as to safeguard against the ignition of leaking .ammable .uid. Flexible hose assemblies(hoseand end .ttings) mustbe[showntobesuitablefortheparticular application.]Anintegral oil sump oflessthan25quartcapacity on a reciprocating engine need not be .reproof nor be enclosed by a .reproof shield.
(b)
Paragraph(a) of this sectiondoes not apply to–
(1)
Lines, .ttings,and componentswhich arealready approved aspart of thetype certi.cated engine; and
(2)
Vent and drain lines, and their .ttings, whose failure will not result in, or add to, a .re hazard.
Amdt. 23-51, E.. 03/11/96
FAR 23.1189 : Shuto. means.
(a)
[For eachmultiengine airplane, the following apply :]
(1)
Each engine installation must have means to shut o. or otherwise prevent hazardous quantities of fuel, oil, deicing .uid, and other .ammable liquids from .owinginto,within,orthroughany enginecompartment,exceptinlines, .ttings, and componentsforming anintegralpart of an engine.
(2)
The closing of the fuel shuto. valve for any engine may not make any fuel unavailable to the remaining engines that would be available to those engines with that valve open.
(3)
Operation of any shuto. means may not interfere with the later emergency operation of other equipment such aspropellerfeathering devices.
(4)
Eachshuto. mustbe outside of the engine compartment unless an equaldegree of safety is provided with the shuto. inside the compartment.
