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14 CFR Ch. I (1–1–14 Edition)
§ 33.76
and other similar equipment or proce-
dures. If items of a safety system are
outside the control of the engine manu-
facturer, the assumptions of the safety
analysis with respect to the reliability
of these parts must be clearly stated in
the analysis and identified in the in-
stallation instructions under § 33.5 of
this part.
(e) If the safety analysis depends on
one or more of the following items,
those items must be identified in the
analysis and appropriately substan-
tiated.
(1) Maintenance actions being carried
out at stated intervals. This includes
the verification of the serviceability of
items that could fail in a latent man-
ner. When necessary to prevent haz-
ardous engine effects, these mainte-
nance actions and intervals must be
published in the instructions for con-
tinued airworthiness required under
§ 33.4 of this part. Additionally, if er-
rors in maintenance of the engine, in-
cluding the control system, could lead
to hazardous engine effects, the appro-
priate 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 func-
tioning must be published in the appro-
priate manual.
(3) The provisions of specific instru-
mentation not otherwise required.
(4) Flight crew actions to be specified
in the operating instructions estab-
lished under § 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, overtempera-
ture, or topping limiters;
(8) Propeller control systems; and
(9) Engine or propeller thrust rever-
sal systems.
(g) Unless otherwise approved by the
FAA and stated in the safety analysis,
for compliance with part 33, the fol-
lowing failure definitions apply to the
engine:
(1) An engine failure in which the
only consequence is partial or com-
plete loss of thrust or power (and asso-
ciated engine services) from the engine
will be regarded as a minor engine ef-
fect.
(2) The following effects will be re-
garded 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 oppo-
site direction to that commanded by
the pilot;
(iv) Uncontrolled fire;
(v) Failure of the engine mount sys-
tem leading to inadvertent engine sep-
aration;
(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 be-
tween those effects covered in para-
graphs (g)(1) and (g)(2) of this section
will be regarded as a major engine ef-
fect.
[Amdt. 33–24, 72 FR 50867, Sept. 4, 2007]
§ 33.76
Bird ingestion.
(a)
General. Compliance with para-
graphs (b), (c), and (d) of this section
shall be in accordance with the fol-
lowing:
(1) Except as specified in paragraph
(d) of this section, all ingestion tests
must be conducted with the engine sta-
bilized at no less than 100-percent take-
off power or thrust, for test day ambi-
ent conditions prior to the ingestion.
In addition, the demonstration of com-
pliance must account for engine oper-
ation 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 es-
tablished by the applicant and identi-
fied as a limitation in the installation
instructions required under § 33.5.
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