(b)
Eachpowerplantinstallation mustbe constructed and arranged to–

(1)
Ensure safe operationtothe maximum altitudefor whichapprovalis requested.

(2)
Be accessible for necessary inspections and maintenance.

(c)
Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for pre.ight checks.

(d)
Each turbine engine installation must be constructed and arranged to–

(1)
Result in carcass vibration characteristics thatdo not exceed those established during the type certi.cation of the engine.

(2)
[Ensure that the capabilityof the installed engine to withstand the ingestion of rain, hail, ice, and birds into the engine inlet is not less than the capability established for the engine itself under Sec. 23.903(a)(2).]

(e)
The installation must comply with–

(1)
The instructions provided under the engine type certi.cate and the propeller type certi.cate.

(2)
The applicable provisions of this subpart.

(f)
Eachauxiliarypower unitinstallation must meet the applicableportions of thispart. Amdt. 23-53, E.. 04/30/98

FAR 23.903 : 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 anditsinstallation mustcomply with one ofthefollowing:

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

(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) Section 33.77 of this chapter in e.ect on October 31, 1974, or as subse-quentlyamendedbeforeApril30,1998, unless that engine’sforeign object ingestion service history has resulted in 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.] Note : Sec. 33.77 of this chapter in e.ect on October 31, 1974, was published in 14 CFR parts 1 to 59, Revised as of January 1, 1975. See 39 FR 35467, October 1, 1974.
(b)
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 inside 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 operating limitations that adversely a.ect turbine rotor structural integrity will not be exceeded in service.

(c)
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 the failure or malfunction (including destruction by .re in the engine compartment) of any system that can a.ect an engine (other than a fuel tank if only one fuel tank is installed), will not–

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

(2)
Require immediate action by any crewmember for continued safe operation of the remaining engines.

(d)
Starting and stopping(piston engine).

(1)
The design of the installation must be such that risk of .re or mechanical damage to the engine or airplane, as a result of starting the engine in any conditionsin which startingis to bepermitted, is reduced to a minimum. Any techniques and associated limitations for engine starting must be established and included in the Airplane Flight Manual, approved manual material, or applicable operating placards. Means must be provided for–
　
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