spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 33.35

(1) Alert the pilot when the engine is
at the 30-second OEI and the 2-minute
OEI power levels, when the event begins, and when the time interval expires;
(2) Automatically record each usage
and duration of power at the 30-second
OEI and 2-minute OEI levels;
(3) Alert maintenance personnel in a
positive manner that the engine has
been operated at either or both of the
30-second and 2-minute OEI power levels, and permit retrieval of the recorded data; and
(4) Enable routine verification of the
proper operation of the above means.
(d) The means, or the provision for a
means, of paragraphs (c)(2) and (c)(3) of
this section must not be capable of
being reset in flight.
(e) The applicant must make provision for the installation of instrumentation necessary to ensure operation in
compliance with engine operating limitations. Where, in presenting the safety analysis, or complying with any
other requirement, dependence is
placed on instrumentation that is not
otherwise mandatory in the assumed
aircraft installation, then the applicant must specify this instrumentation
in the engine installation instructions
and declare it mandatory in the engine
approval documentation.
(f) As part of the System Safety Assessment of Section 33.28(e), the applicant
must assess the possibility and subsequent effect of incorrect fit of instruments, sensors, or connectors. Where
necessary, the applicant must take design precautions to prevent incorrect
configuration of the system.
(g) The sensors, together with associated wiring and signal conditioning,
must be segregated, electrically and
physically, to the extent necessary to
ensure that the probability of a fault
propagating from instrumentation and
monitoring functions to control functions, or vice versa, is consistent with
the failure effect of the fault.
(h) The applicant must provide instrumentation enabling the flight crew
to monitor the functioning of the turbine cooling system unless appropriate
inspections are published in the relevant manuals and evidence shows
that:

(1) Other existing instrumentation
provides adequate warning of failure or
impending failure;
(2) Failure of the cooling system
would not lead to hazardous engine effects before detection; or
(3) The probability of failure of the
cooling system is extremely remote.
[Amdt. 33-5, 39 FR 1831, Jan. 15, 1974, as
amended by Amdt. 33-6, 39 FR 35465, Oct. 1,
1974; Amdt. 33-18, 61 FR 31328, June 19, 1996;
Amdt. 33-25, 73 FR 48123, Aug. 18, 2008; Amdt.
33-26, 73 FR 48285, Aug. 19, 2008]

Subpart C - Design and Construction; Reciprocating Aircraft
Engines
Section 33.31 Applicability.
This subpart prescribes additional design and construction requirements for
reciprocating aircraft engines.
Section 33.33 Vibration.
The engine must be designed and constructed to function throughout its
normal operating range of crankshaft
rotational speeds and engine powers
without inducing excessive stress in
any of the engine parts because of vibration and without imparting excessive vibration forces to the aircraft
structure.
Section 33.34 Turbocharger rotors.
Each turbocharger case must be designed and constructed to be able to
contain fragments of a compressor or
turbine that fails at the highest speed
that is obtainable with normal speed
control devices inoperative.
[Amdt. 33-22, 72 FR 50860, Sept. 4, 2007]

Section 33.35 Fuel and induction system.
(a) The fuel system of the engine
must be designed and constructed to
supply an appropriate mixture of fuel
to the cylinders throughout the complete operating range of the engine
under all flight and atmospheric conditions.
(b) The intake passages of the engine
through which air or fuel in combination with air passes for combustion
purposes must be designed and constructed to minimize the danger of ice
accretion in those passages. The engine
must be designed and constructed to

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