spaschal on DSK3GDR082PROD with CFR

Section 33.76

14 CFR Ch. I (1-1-19 Edition)

items that could fail in a latent manner. When necessary to prevent hazardous engine effects, these maintenance actions and intervals must be
published in the instructions for continued airworthiness required under
Section 33.4 of this part. Additionally, if errors in maintenance of the engine, including the control system, could lead
to hazardous engine effects, the appropriate procedures must be included in
the relevant engine manuals.
(2) Verification of the satisfactory
functioning of safety or other devices
at pre-flight or other stated periods.
The details of this satisfactory functioning must be published in the appropriate manual.
(3) The provisions of specific instrumentation not otherwise required.
(4) Flight crew actions to be specified
in the operating instructions established under Section 33.5.
(f) If applicable, the safety analysis
must also include, but not be limited
to, investigation of the following:
(1) Indicating equipment;
(2) Manual and automatic controls;
(3) Compressor bleed systems;
(4) Refrigerant injection systems;
(5) Gas temperature control systems;
(6) Engine speed, power, or thrust
governors and fuel control systems;
(7) Engine overspeed, overtemperature, or topping limiters;
(8) Propeller control systems; and
(9) Engine or propeller thrust reversal systems.
(g) Unless otherwise approved by the
FAA and stated in the safety analysis,
for compliance with part 33, the following failure definitions apply to the
engine:
(1) An engine failure in which the
only consequence is partial or complete loss of thrust or power (and associated engine services) from the engine
will be regarded as a minor engine effect.
(2) The following effects will be regarded as hazardous engine effects:
(i) Non-containment of high-energy
debris;
(ii) Concentration of toxic products
in the engine bleed air intended for the
cabin sufficient to incapacitate crew or
passengers;

(iii) Significant thrust in the opposite direction to that commanded by
the pilot;
(iv) Uncontrolled fire;
(v) Failure of the engine mount system leading to inadvertent engine separation;
(vi) Release of the propeller by the
engine, if applicable; and
(vii) Complete inability to shut the
engine down.
(3) An effect whose severity falls between those effects covered in paragraphs (g)(1) and (g)(2) of this section
will be regarded as a major engine effect.
[Amdt. 33-24, 72 FR 50867, Sept. 4, 2007]

Section 33.76 Bird ingestion.
(a) General. Compliance with paragraphs (b), (c), and (d) of this section
shall be in accordance with the following:
(1) Except as specified in paragraph
(d) of this section, all ingestion tests
must be conducted with the engine stabilized at no less than 100-percent takeoff power or thrust, for test day ambient conditions prior to the ingestion.
In addition, the demonstration of compliance must account for engine operation at sea level takeoff conditions on
the hottest day that a minimum engine
can achieve maximum rated takeoff
thrust or power.
(2) The engine inlet throat area as
used in this section to determine the
bird quantity and weights will be established by the applicant and identified as a limitation in the installation
instructions required under Section 33.5.
(3) The impact to the front of the engine from the large single bird, the single largest medium bird which can
enter the inlet, and the large flocking
bird must be evaluated. Applicants
must show that the associated components when struck under the conditions prescribed in paragraphs (b), (c)
or (d) of this section, as applicable, will
not affect the engine to the extent that
the engine cannot comply with the requirements of paragraphs (b)(3), (c)(6)
and (d)(4) of this section.
(4) For an engine that incorporates
an inlet protection device, compliance
with this section shall be established
with the device functioning. The engine approval will be endorsed to show

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