Federal Aviation Administration, DOT

Section 33.89

spaschal on DSK3GDR082PROD with CFR

during the periods specified in paragraphs (g)(2)(ii) through (iv) of this section;
(ii) One period repeating the run
specified in paragraph (g)(2)(i) of this
section, except that it must be followed
by 10 minutes at the thrust obtained
with the power control lever set at the
position for 80 percent of rated maximum continuous augmented thrust;
(iii) One period repeating the run
specified in paragraph (g)(2)(i) of this
section, except that it must be followed
by 10 minutes at the thrust obtained
with the power control lever set at the
position for 60 percent of rated maximum continuous augmented thrust
and then 10 minutes at not more than
15 percent of rated takeoff thrust;
(iv) One period repeating the runs
specified in paragraphs (g)(2)(i) and (ii)
of this section; and
(v) One period of 30 minutes with 25
of the runs made at the thrust obtained
with the power control lever set at the
position for rated maximum continuous augmented thrust, each followed
by idle thrust and with the remaining
5 runs at the thrust obtained with the
power control lever set at the position
for rated maximum continuous augmented thrust for 25 minutes each, followed by subsonic operation at not
more than 15 percent or rated takeoff
thrust and accelerated to rated takeoff
thrust for 5 minutes using hot fuel.
(3) Starts. One hundred starts must be
made, of which 25 starts must be preceded by an engine shutdown of at
least 2 hours. There must be at least 10
false engine starts, pausing for the applicant-s specified minimum fuel drainage time before attempting a normal
start. At least 10 starts must be normal
restarts, each made no later than 15
minutes after engine shutdown. The
starts may be made at any time, including the period of endurance testing.
[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33-3, 32 FR 3737, Mar. 4,
1967; Amdt. 33-6, 39 FR 35468, Oct. 1, 1974;
Amdt. 33-10, 49 FR 6853, Feb. 23, 1984; Amdt.
33-12, 53 FR 34220, Sept. 2, 1988; Amdt. 33-18,
61 FR 31328, June 19, 1996; Amdt. 33-25, 73 FR
48123, Aug. 18, 2008; Amdt. 33-30, 74 FR 45311,
Sept. 2, 2009; Amdt. 33-32, 77 FR 22187, Apr.
13, 2012]

Section 33.88

Engine overtemperature test.

(a) Each engine must run for 5 minutes at maximum permissible rpm with
the gas temperature at least 75 SectionF (42
SectionC) higher than the maximum rating-s
steady-state operating limit, excluding
maximum values of rpm and gas temperature associated with the 30-second
OEI and 2-minute OEI ratings. Following this run, the turbine assembly
must be within serviceable limits.
(b) In addition to the test requirements in paragraph (a) of this section,
each engine for which 30-second OEI
and 2-minute OEI ratings are desired,
that incorporates a means for automatic temperature control within its
operating limitations in accordance
with Section 33.28(k), must run for a period of
4 minutes at the maximum power-on
rpm with the gas temperature at least
35 SectionF (19 SectionC) higher than the maximum
operating limit at 30-second OEI rating. Following this run, the turbine assembly may exhibit distress beyond the
limits for an overtemperature condition provided the engine is shown by
analysis or test, as found necessary by
the FAA, to maintain the integrity of
the turbine assembly.
(c) A separate test vehicle may be
used for each test condition.
[Doc. No. 26019, 61 FR 31329, June 19, 1996, as
amended by Amdt. 33-25, 73 FR 48124, Aug. 18,
2008; Amdt. 33-26, 73 FR 48285, Aug. 19, 2008]

Section 33.89

Operation test.

(a) The operation test must include
testing found necessary by the Administrator to demonstrate - 
(1) Starting, idling, acceleration,
overspeeding, ignition, functioning of
the propeller (if the engine is designated to operate with a propeller);
(2) Compliance with the engine response requirements of Section 33.73; and
(3) The minimum power or thrust response time to 95 percent rated takeoff
power or thrust, from power lever positions representative of minimum idle
and of minimum flight idle, starting
from stabilized idle operation, under
the following engine load conditions:
(i) No bleed air and power extraction
for aircraft use.
(ii) Maximum allowable bleed air and
power extraction for aircraft use.

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