(1)
The installation must comply with–

(i)
TheinstallationinstructionsprovidedunderSec.33.5 of this chapter; and

(ii)
The applicable provisions of this subpart;

(2)
The components of the installation must be constructed, arranged, and instal-led so as to ensure their continued safe operation between normal inspections or overhauls;

(3)
Theinstallation mustbe accessiblefor necessaryinspections andmaintenance; and

(4)
The major components of this installation must be electrically bonded to the other parts of the airplane.

(c)
For eachpowerplantand auxiliarypower unitinstallation,it mustbe establishedthat no singlefailure or malfunction orprobable combination offailures willjeopardize the safe operation of the airplane except that thefailure of structural elements need not be considered if the probability of such failure is extremely remote.

(d)
[Eachauxiliary power unit installation must meet the applicable provisions of this subpart.]

Amdt. 25-46, E.. 12/1/78
FAR 25.903 : Engines.
(a) Engine type certi.cate.
(1)
Each engine must have a type certi.cate and must meet the applicable requi-rements of Part 34 of this chapter.

(2)
[Eachturbine engine must comply with one of the following :

(i)
Sections 33.76, 33.77 and 33.78 of this chapter in e.ect on December 13,2000,or as subsequently amended; or

(ii)
Sections 33.77 and 33.78 of this chapter in e.ect on April 30, 1998, or as subsequently amended before December 13, 2000; or

(iii) Comply with Section 33.77 of this chapter in e.ect on October 31, 1974, or as subsequently amended prior to April 30, 1998, unless that engine’s foreign objectingestion servicehistoryhas resultedin an unsafe condition; or
(iv)
Be shown to have a foreign object ingestion service history in similar installation locations which has not resulted in any unsafe condition.]

(b)
Engine isolation. The powerplants must be arranged and isolated from each other to allow operation, in at least one con.guration, so that the failure or malfunction of any engine, or of any system that can a.ect the engine, will not–

(1)
Preventthe continued safe operation of the remaining engines; or

(2)
Require immediate action by any crewmember for continued safe operation.

(c)
Control of engine rotation. There must be means for stopping the rotation of any engineindividuallyin .ight,exceptthat,forturbineengineinstallations,themeans for stopping the rotation of any engine need be provided only where continued rotation couldjeopardizethe safety ofthe airplane.Each component ofthe stopping system on the engine side of the .rewall that might be exposed to .re must be at least .re-resistant. If hydraulic propeller feathering systems are used for this purpose, the feathering lines must be at least .re-resistant under the operating conditions that may be expected to exist during feathering.

(d)
Turbine engine installations. For turbine engine installations–

(1)
Design precautions must be taken to minimize the hazards to the airplane in the event of an engine rotor failure or of a .re originating within the engine which burns through the engine case.

(2)
The powerplant systems associated with engine control devices, systems, and instrumentation, must be designed to give reasonable assurance that those engine operating limitations that adversely a.ect turbine rotor structural in-tegrity will not be exceeded in service.

(e)
Restart capability.

(1)
Means to restart any engine in .ight must be provided.

(2)
An altitude and airspeed envelope must be established for in-.ight engine restarting, and each engine musthave a restart capability withinthat envelope.
　
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