spaschal on DSK3GDR082PROD with CFR

Section 33.87

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

(d), (e) or (g) of this section, the prescribed 6-hour test sequence must be
conducted 25 times to complete the required 150 hours of operation. Engines
for which the 30-second OEI and 2minute OEI ratings are desired must be
further tested under paragraph (f) of
this section. The following test requirements apply:
(1) The runs must be made in the
order found appropriate by the FAA for
the particular engine being tested.
(2) Any automatic engine control
that is part of the engine must control
the engine during the endurance test
except for operations where automatic
control is normally overridden by manual control or where manual control is
otherwise specified for a particular test
run.
(3) Except as provided in paragraph
(a)(5) of this section, power or thrust,
gas temperature, rotor shaft rotational
speed, and, if limited, temperature of
external surfaces of the engine must be
at least 100 percent of the value associated with the particular engine operation being tested. More than one test
may be run if all parameters cannot be
held at the 100 percent level simultaneously.
(4) The runs must be made using fuel,
lubricants and hydraulic fluid which
conform to the specifications specified
in complying with Section 33.7(c).
(5) Maximum air bleed for engine and
aircraft services must be used during
at least one-fifth of the runs, except for
the test required under paragraph (f) of
this section, provided the validity of
the test is not compromised. However,
for these runs, the power or thrust or
the rotor shaft rotational speed may be
less than 100 percent of the value associated with the particular operation
being tested if the FAA finds that the
validity of the endurance test is not
compromised.
(6) Each accessory drive and mounting attachment must be loaded in accordance with paragraphs (a)(6)(i) and
(ii) of this section, except as permitted
by paragraph (a)(6)(iii) of this section
for the test required under paragraph
(f) of this section.
(i) The load imposed by each accessory used only for aircraft service must
be the limit load specified by the applicant for the engine drive and attach-

ment point during rated maximum continuous power or thrust and higher
output.
(ii) The endurance test of any accessory drive and mounting attachment
under load may be accomplished on a
separate rig if the validity of the test
is confirmed by an approved analysis.
(iii) The applicant is not required to
load the accessory drives and mounting
attachments when running the tests
under paragraphs (f)(1) through (f)(8) of
this section if the applicant can substantiate that there is no significant
effect on the durability of any accessory drive or engine component. However, the applicant must add the equivalent engine output power extraction
from the power turbine rotor assembly
to the engine shaft output.
(7) During the runs at any rated
power or thrust the gas temperature
and the oil inlet temperature must be
maintained at the limiting temperature except where the test periods are
not longer than 5 minutes and do not
allow stabilization. At least one run
must be made with fuel, oil, and hydraulic fluid at the minimum pressure
limit and at least one run must be
made with fuel, oil, and hydraulic fluid
at the maximum pressure limit with
fluid temperature reduced as necessary
to allow maximum pressure to be attained.
(8) If the number of occurrences of either transient rotor shaft overspeed,
transient gas overtemperature or transient engine overtorque is limited, that
number of the accelerations required
by paragraphs (b) through (g) of this
section must be made at the limiting
overspeed, overtemperature or overtorque. If the number of occurrences is
not limited, half the required accelerations must be made at the limiting
overspeed, overtemperature or overtorque.
(9) For each engine type certificated
for use on supersonic aircraft the following additional test requirements
apply:
(i) To change the thrust setting, the
power control lever must be moved
from the initial position to the final
position in not more than one second
except for movements into the fuel

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