869
Federal Aviation Administration, DOT
§ 33.76
T
ABLE
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TO
§ 33.76—A
DDITIONAL
I
NTEGRITY
A
SSESSMENT
Engine Inlet Throat Area (A)—
square-meters (square-inches)
Bird
quantity
Bird weight
kg. (lb.)
1.35 (2,092)>A .................................
none .....
1.35 (2,092)
≤
A <2.90 (4,495) ..........
1 ...........
1.15 (2.53)
2.90 (4,495)
≤
A <3.90 (6,045) ..........
2 ...........
1.15 (2.53)
3.90 (6,045)
≤
A .................................
1 ...........
1.15 (2.53)
plus 6 ...
0.70 (1.54)
(d)
Large flocking bird. An engine test
will be performed as follows:
(1) Large flocking bird engine tests
will be performed using the bird mass
and weights in Table 4, and ingested at
a bird speed of 200 knots.
(2) Prior to the ingestion, the engine
must be stabilized at no less than the
mechanical rotor speed of the first ex-
posed stage or stages that, on a stand-
ard day, would produce 90 percent of
the sea level static maximum rated
takeoff power or thrust.
(3) The bird must be targeted on the
first exposed rotating stage or stages
at a blade airfoil height of not less
than 50 percent measured at the lead-
ing edge.
(4) Ingestion of a large flocking bird
under the conditions prescribed in this
paragraph must not cause any of the
following:
(i) A sustained reduction of power or
thrust to less than 50 percent of max-
imum rated takeoff power or thrust
during the run-on segment specified
under paragraph (d)(5)(i) of this sec-
tion.
(ii) Engine shutdown during the re-
quired run-on demonstration specified
in paragraph (d)(5) of this section.
(iii) The conditions specified in para-
graph (b)(3) of this section.
(5) The following test schedule must
be used:
(i) Ingestion followed by 1 minute
without power lever movement.
(ii) Followed by 13 minutes at not
less than 50 percent of maximum rated
takeoff power or thrust.
(iii) Followed by 2 minutes between
30 and 35 percent of maximum rated
takeoff power or thrust.
(iv) Followed by 1 minute with power
or thrust increased from that set in
paragraph (d)(5)(iii) of this section, by
between 5 and 10 percent of maximum
rated takeoff power or thrust.
(v) Followed by 2 minutes with power
or thrust reduced from that set in
paragraph (d)(5)(iv) of this section, by
between 5 and 10 percent of maximum
rated takeoff power or thrust.
(vi) Followed by a minimum of 1
minute at ground idle then engine
shutdown. The durations specified are
times at the defined conditions. Power
lever movement between each condi-
tion will be 10 seconds or less, except
that power lever movements allowed
within paragraph (d)(5)(ii) of this sec-
tion are not limited, and for setting
power under paragraph (d)(5)(iii) of this
section will be 30 seconds or less.
(6) Compliance with the large flock-
ing bird ingestion requirements of this
paragraph (d) may also be dem-
onstrated by:
(i) Incorporating the requirements of
paragraph (d)(4) and (d)(5) of this sec-
tion, into the large single bird test
demonstration specified in paragraph
(b)(1) of this section; or
(ii) Use of an engine subassembly test
at the ingestion conditions specified in
paragraph (b)(1) of this section if:
(A) All components critical to com-
plying with the requirements of para-
graph (d) of this section are included in
the subassembly test;
(B) The components of paragraph
(d)(6)(ii)(A) of this section are installed
in a representative engine for a run-on
demonstration in accordance with
paragraphs (d)(4) and (d)(5) of this sec-
tion; except that section (d)(5)(i) is de-
leted and section (d)(5)(ii) must be 14
minutes in duration after the engine is
started and stabilized; and
(C) The dynamic effects that would
have been experienced during a full en-
gine ingestion test can be shown to be
negligible with respect to meeting the
requirements of paragraphs (d)(4) and
(d)(5) of this section.
(7) Applicants must show that an un-
safe condition will not result if any en-
gine operating limit is exceeded during
the run-on period.
T
ABLE
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TO
§ 33.76—L
ARGE
F
LOCKING
B
IRD
M
ASS AND
W
EIGHT
Engine inlet throat area
(square meters/square inches)
Bird
quan-
tity
Bird mass
and weight
(kg (lbs))
A <2.50 (3875) ................................
none
2.50 (3875)
≤
A <3.50 (5425) ...........
1
1.85 (4.08)
3.50 (5425)
≤
A <3.90 (6045) ...........
1
2.10 (4.63)
3.90 (6045)
≤
A .................................
1 2.50
(5.51)
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