(2)
At the highest speed of the following, as applicable :

(i)
120percentofits maximumpermissible r.p.m.if tested on a rig and equip-ped with blades or blade weights.

(ii)
115percent ofits maximumpermissible r.p.m.if tested on an engine.

(iii) 115 percent of its maximum permissible r.p.m. if tested on turbosuper-charger driven by a hot gas supply from a special burner rig.
(iv)
120 percent of the r.p.m. at which, while cold spinning, it is subject to operating stresses that are equivalent to those induced at the maximum operating temperature and maximum permissible r.p.m.

(v)
105 percent of the highest speed that would result from failure of the most critical component or system in a representative installation of the engine.

(vi)
Thehighestspeed that would resultfrom thefailure of any component or system in a representative installation of the engine, in combination with anyfailure of a component or system that would not normallybedetected during a routine pre.ight check or during normal .ight operation.]

Following the test, each rotor must be within approved dimensional limits for an overspeed condition and may not be cracked.
Amdt. 33-10, E.. 3/26/84
FAR33.28:[Electricalandelectroniccontrol systems.]
[Eachcontrol system which relies on electrical and electronic means for normal ope-ration must :
(a)
Have the controlsystemdescription, thepercent of availablepower or thrust control-ledinbothnormal operation andfailure conditions, andthe range of control of other controlled functions, speci.ed in the instruction manual required by Sec. 33.5 for the engine;

(b)
Be designed and constructed so that any failure of aircraft-supplied power or data will not resultin an unacceptable changeinpower orthrust, orprevent continued safe operation of the engine;

(c)
Be designed and constructed so that no single failure or malfunction, or probable combination of failures of electrical or electronic components of the control system, resultsin an unsafe condition;

(d)
Have environmentallimits,including transients causedbylightning strikes, speci.ed in the instruction manual; and

(e) Haveall associated softwaredesigned andimplemented topreventerrorsthat would result in an unacceptable loss of power or thrust, or other unsafe condition, and have the method used to design and implement the software approved by the Ad-ministrator.]
Amdt. 33-15, E.. 8/16/93
FAR 33.29 : Instrument connection.
(a)
Unless it is constructed to prevent its connection to an incorrect instrument, each connection provided for powerplant instruments required by aircraft airworthiness regulations or necessary to insure operation of the engine in compliance with any engine limitation must be marked to identify it with its corresponding instrument.

(b)
A connection must be provided on each turbojet engine for an indicator system to indicate rotor system unbalance.

(c)
[Eachrotorcraft turbine engine having a 30-second OEI rating and a 2-minute OEI rating must have a provision for a means to :

(1)
Alertthepilot whenthe engineis atthe30-secondOEI and the2-minuteOEI power levels, when the event begins, and when the time interval expires;

(2)
Determine, in a positive manner, that the engine has been operated at each rating; and

(3)
Automatically record each usage and duration of power at each rating.] Amdt. 33-18, E.. 8/19/96

′
Elodie Roux. Septembre 2003
SubpartB :Design andConstruction;General
Chapitre 90
Subpart C : Design and Construction; Reciprocating Aircraft Engines
Sommaire
FAR33.31:Applicability. . . . . . . . . . . . . . . . . . . . . 1138 FAR33.33:Vibration.. . . . . . . . . . . . . . . . . . . . . . 1138 FAR33.35:Fuel andinductionsystem. . . . . . . . . . . . . 1138 FAR33.37:Ignitionsystem. .................. 1138 FAR33.39:Lubricationsystem. . . . . . . . . . . . . . . . . 1138
　
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