CS-E 800 Bird Strike and Ingestion

• ED Decision 2018/014/R found in: CS-E Amdt 5 - Engines (Dec 2018)

CS-E 800 Bird Strike and Ingestion ED Decision 2018/014/R (See [AMC E 800](#_DxCrossRefBm1371447815)) (a) *Objective*. To demonstrate that the Engine will respond in a safe manner following specified encounters with birds, as part of the compliance with [CS-E 540](#_DxCrossRefBm1371447741). The demonstration will address the ingestion of large, medium and small birds, and also the effect of the impact of such birds upon the front of the Engine. (b) Single large bird ingestion test. An Engine ingestion test must be carried out using a large bird as specified below. Alternative evidence may be acceptable as provided under CS-E 800(g)(1). (1) Test conditions. (i) The Engine operating conditions must be stabilised prior to ingestion at not less than 100% of the Take-off Power or Thrust at the test day ambient conditions. In addition, the demonstration of compliance must account for Engine operation at sea level take-off conditions on the hottest day that a minimum Engine can achieve maximum rated Take-off Power or Thrust. (ii) The bird to be used must be of a minimum mass of:- (A) 1.85 kg for Engine inlet throat areas of less than 1.35 m2 unless a smaller bird is determined to be a more severe demonstration; (B) 2.75 kg for Engine inlet throat areas of less than 3.90 m2 but equal to or greater than 1.35 m2; (C) 3.65 kg for Engine inlet throat areas equal to or greater than 3.90 m2. (iii) The bird must be aimed at the most critical exposed location on the first stage rotor blades. (iv) A bird speed of 200 knots for Engines to be installed on aeroplanes or the maximum airspeed for normal flight operations for Engines to be installed on Rotorcraft. (v) Power lever movement is not permitted within 15 seconds following the ingestion. (2) *Acceptance criteria*. Ingestion of this single large bird must not result in a Hazardous Engine Effect. (c) *Large flocking bird*. An engine test using a single bird must be carried out at the conditions specified below for Engines with an inlet throat area equal to or greater than 2.5 m2. Alternative evidence may be acceptable as provided under CS-E 800(g)(1). (1) Test conditions. (i) The Engine operating conditions must be stabilised prior to ingestion at not less than the mechanical rotor speed of the first exposed stage(s) that, on an ISA standard day, would produce 90% of the sea level static Rated Take-off Thrust. (ii) The bird speed must be 200 knots. (iii) The bird mass must be at least as defined below: <table border="1" cellpadding="0" cellspacing="0" width="491"><tr><td valign="top" width="245"><p><b>Engine Inlet Throat Area (A) m²</b></p></td><td valign="top" width="245"><p><b>Mass of Bird kg </b></p></td></tr><tr><td valign="top" width="245"><p>A &lt; 2.50 </p></td><td valign="top" width="245"><p>Not applicable </p></td></tr><tr><td valign="top" width="245"><p>2.50 ≤ A &lt; 3.50</p></td><td valign="top" width="245"><p>1.85 </p></td></tr><tr><td valign="top" width="245"><p>3.50 ≤ A &lt; 3.90</p></td><td valign="top" width="245"><p>2.10 </p></td></tr><tr><td valign="top" width="245"><p>3.90 ≤ A </p></td><td valign="top" width="245"><p>2.50 </p></td></tr></table> (iv) The bird must be targeted on the first exposed rotating stage(s) at a blade aerofoil height of not less than 50%, measured at the leading edge. (v) The following test schedule must be used: <table border="0" cellpadding="0" cellspacing="0" width="499"><tr><td valign="top" width="62"><p>Step 1 - </p></td><td valign="top" width="437"><p>Ingestion followed by 1 minute without power lever movement. </p></td></tr><tr><td valign="top" width="62"><p>Step 2 - </p></td><td valign="top" width="437"><p>13 minutes at not less than 50% of Rated Take-off Thrust. </p></td></tr><tr><td valign="top" width="62"><p>Step 3 - </p></td><td valign="top" width="437"><p>2 minutes at a thrust set between 30 and 35% of Rated Take-off Thrust. </p></td></tr><tr><td valign="top" width="62"><p>Step 4 - </p></td><td valign="top" width="437"><p>1 minute at a thrust increased from that set in step 3 by between 5 and 10% of Rated Take-off Thrust. </p></td></tr><tr><td valign="top" width="62"><p>Step 5 - </p></td><td valign="top" width="437"><p>2 minutes at a thrust decreased from that set in step 4 by between 5 and 10% of Rated Take-off Thrust. </p></td></tr><tr><td valign="top" width="62"><p>Step 6 - </p></td><td valign="top" width="437"><p>At least 1 minute at ground idle followed by Engine shutdown. </p></td></tr></table> Each specified step duration is the time at the defined step conditions. The power lever movement between each step will be 10 seconds or less in duration, except that power lever movement for setting theconditions of step 3 will be 30 seconds or less. Within step 2, power lever movements are allowed and are not limited. Run-on For Large Flocking Bird Rule  (2) Acceptance criteria. The test of CS-E 800(c)(1)(v) must not cause: — the Engine to be unable to complete the required test schedule; — the Engine to be shut down before end of step 6; — a sustained reduction in thrust to less than 50% Rated Take-off Thrust during step 1; — a Hazardous Engine Effect. (d) *Medium and small birds ingestion tests*. Engine ingestion tests and analysis with medium- and small-sized birds must be carried out as specified below. Alternative evidence may be acceptable as provided under CS-E 800(g)(1). The small-birds test will not be required if the prescribed number of medium-bird(s) pass into the Engine rotor blades during the medium bird test. (1) Test Conditions. (i) The Engine operating conditions must be stabilised prior to ingestion at not less than 100% of the Take-off Power or Thrust at the test day ambient conditions. In addition, the demonstration of compliance must account for Engine operation at sea level take-off conditions on the hottest day at which a minimum Engine can achieve maximum rated Takeoff Power or Thrust. (ii) The critical ingestion parameters that affect power loss and damage must be determined by analysis or component tests or both. They must include but are not limited to the effects of the bird speed, the critical target location and the first stage rotor speed. The critical bird ingestion speed must reflect the most critical condition within the range of airspeeds for normal flight operations up to 450 m (1 500 ft) above ground level, but not less than the V1 minimum for Engines to be installed on aeroplanes. (iii) Except for Rotorcraft Engines, the following test schedule must be used: — Perform an ingestion to simulate a flock encounter within 1 second; — 2 minutes without any power lever movement; — 3 minutes at 75% of the test conditions of CS-E 800(d)(1)(i); — 6 minutes at 60% of the test conditions of CS-E 800(d)(1)(i); — 6 minutes at 40% of the test conditions of CS-E 800(d)(1)(i); — 1 minute at approach idle; — 2 minutes at 75% of the test conditions of CS-E 800(d)(1)(i); — Stabilise the Engine at idle and then shut the Engine down. These durations are times at the defined conditions, the power lever being moved between each condition in less than 10 seconds. (iv) For Rotorcraft Engines, the following test schedule must be used: — Perform an ingestion to simulate a flock encounter within 1 second; — 3 minutes at 75% of the test conditions of CS-E 800(d)(1)(i); — 90 seconds at minimum test bed idle; — 30 seconds at 75% of the test conditions of CS-E 800(d)(1)(i); — Stabilise the Engine at idle and then shut the Engine down. These durations are times at the defined conditions, the power lever being moved between each condition in less than 10 seconds. (v) (A) *Medium birds*. The masses and quantities of birds will be determined from the second column of Table A. When only one bird is specified, it must be aimed at the Engine core primary flow path; the other critical locations on the Engine face area must be addressed by appropriate tests or analysis or both. When two or more birds are specified, the largest must be aimed at the Engine core primary flow path and a second bird must be aimed at the most critical exposed location on the first stage rotor blades. Any remaining birds must be evenly distributed over the Engine face area. (B) *Small birds*. One 85-g bird for each 0.032 m2 of the inlet throat area or fraction thereof with a maximum of 16 birds, distributed to take account of any critical exposed locations on the first stage rotor blades, but otherwise evenly distributed over the Engine face area. TABLE A of CS-E 800 Medium (flocking) birds <table border="1" cellpadding="0" cellspacing="0" width="606"><thead><tr><td valign="top" width="208"><p><b>Engine test</b></p><p><b>(CS-E 800(d)(1)) </b></p></td><td valign="top" width="208"><p><b>Additional integrity assessment </b></p><p><b>(CS-E 800(d)(3))</b></p></td></tr><tr><td valign="top" width="190"><p><b>Engine inlet throat area (A) </b></p><p><b>m²</b></p></td><td valign="top" width="208"><p><b>Number of birds x mass of birds </b></p><p><b>kg </b></p></td><td valign="top" width="208"><p><b>Number x mass of birds </b></p><p><b>kg </b></p></td></tr></thead><tr><td valign="top" width="190"><p> A &lt; 0.05 </p></td><td valign="top" width="208"><p> none</p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>0.05 ≤ A &lt; 0.10 </p></td><td valign="top" width="208"><p>1 x 0.35 </p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>0.10 ≤ A &lt; 0.20 </p></td><td valign="top" width="208"><p>1x 0.45 </p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>0.20 ≤ A &lt; 0.40 </p></td><td valign="top" width="208"><p>2x 0.45 </p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>0.40 ≤ A &lt; 0.60 </p></td><td valign="top" width="208"><p>2x 0.70 </p></td><td valign="top" width="208"><p>none </p></td></tr><tr><td valign="top" width="190"><p>0.60 ≤ A &lt; 1.00 </p></td><td valign="top" width="208"><p>3x 0.70 </p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>1.00 ≤ A &lt; 1.35 </p></td><td valign="top" width="208"><p>4x 0.70 </p></td><td valign="top" width="208"><p>none</p></td></tr><tr><td valign="top" width="190"><p>1.35 ≤ A &lt; 1.70 </p></td><td valign="top" width="208"><p>1 x 1.15 + 3 x 0.70 </p></td><td valign="top" width="208"><p>1 x 1.15</p></td></tr><tr><td valign="top" width="190"><p>1.70 ≤ A &lt; 2.10 </p></td><td valign="top" width="208"><p>1 x 1.15 + 4 x 0.70 </p></td><td valign="top" width="208"><p>1 x 1.15</p></td></tr><tr><td valign="top" width="190"><p>2.10 ≤ A &lt; 2.50 </p></td><td valign="top" width="208"><p>1 x 1.15 + 5 x 0.70 </p></td><td valign="top" width="208"><p>1 x 1.15</p></td></tr><tr><td valign="top" width="190"><p>2.50 ≤ A &lt; 2.90</p></td><td valign="top" width="208"><p>1 x 1.15 + 6 x 0.70</p></td><td valign="top" width="208"><p>1 x 1.15</p></td></tr><tr><td valign="top" width="190"><p>2.90 ≤ A &lt; 3.90 </p></td><td valign="top" width="208"><p>1 x 1.15 + 6 x 0.70</p></td><td valign="top" width="208"><p>2x 1.15</p></td></tr><tr><td valign="top" width="190"><p>3.90 ≤ A &lt; 4.50</p></td><td valign="top" width="208"><p>3 x 1.15</p></td><td valign="top" width="208"><p>1 x 1.15 + 6 x 0.70</p></td></tr><tr><td valign="top" width="190"><p>4.50 ≤ A</p></td><td valign="top" width="208"><p>4 x 1.15</p></td><td valign="top" width="208"><p>1 x 1.15 + 6 x 0.70</p></td></tr></table> (2) *Acceptance criteria*. The ingestion must not cause: — more than a sustained 25% power or thrust loss; — the Engine to be shut down during the test. (3) In addition, except for Rotorcraft Engines, it must be substantiated by appropriate tests or analysis or both that, when the full first stage rotor assembly is subjected to the quantity and mass of medium birds from the third Column of Table A fired at the most critical locations on the first stage rotor, the effects will not be such as to make the Engine incapable of complying with the acceptance criteria of CS-E 800(d)(2). (e) *Core Engine flocking bird ingestion test*. For turbofan Engines, an ingestion test shall be performed as follows: (1) A core Engine flocking bird ingestion test shall be performed with one bird, using the heaviest bird specified in the second column of Table A above and ingested at a bird speed of 250 knots, unless it is shown by test or validated analysis that no bird material will be ingested into the core under the conditions of this subparagraph, in which case subparagraphs (e)(4), (5) and (6) should be applied. Prior to the ingestion, the Engine shall be stabilised at the mechanical rotor speed of the first exposed stage or stages that, on a standard day, would produce the lowest expected power or thrust required during a climb through 3 000 ft above ground level in revenue service. The bird must be targeted on the first exposed rotating stage or stages at the blade aerofoil height measured at the leading edge that would maximise the bird material that is ingested into the Engine core. (2) Ingestion into the Engine core of a bird under the conditions prescribed in subparagraph (e)(1) shall not cause any of the following: (i) A sustained reduction in power or thrust to less than 50 % of the maximum rated Take-off Power or Thrust during the run-on specified under paragraph (e)(3)(iii) below, that cannot be restored only by movement of the power lever. (ii) A sustained reduction in power or thrust to less than flight idle power or thrust during the run-on segment specified under paragraph (e)(3) below. (iii) An Engine shutdown during the required run-on demonstration specified in paragraph (e)(3) below. (iv) The conditions specified in paragraph CS-E 800(b)(2). (3) The following test schedule shall be used: (i) Ingestion followed by 1 minute without any power lever movement. (ii) Followed by power lever movement to increase the power or thrust to not less than 50 % of the maximum rated Take-off Power or Thrust, if the initial bird ingestion resulted in a reduction in power or thrust below that level. (iii) Followed by 13 minutes at not less than 50 % of the maximum rated Take-off Power or Thrust. (iv) Followed by 2 minutes at between 30 and 35 % of the maximum rated Take-off Power or Thrust. (v) Followed by 1 minute with the power or thrust increased by between 5 and 10 % of the maximum rated Take-off Power or Thrust from that set in subparagraph (e)(3)(iv) of this paragraph. (vi) Followed by 2 minutes with the power or thrust reduced by between 5 and 10 % of maximum rated Take-off Power or Thrust from that set in subparagraph (e)(3)(v) of this paragraph. (vii) Followed by a minimum of 1 minute at ground idle, then an Engine shutdown. The durations specified are the times at the defined conditions. The power lever movement between each condition shall be 10 seconds or less in duration, except power lever movements that are allowed within subparagraph (e)(3)(iii), that are not limited, and those for setting power under subparagraph (e)(3)(iv), which shall be 30 seconds or less in duration. (4) If it is shown by test or analysis that no bird material will be ingested into the Engine core under the conditions of subparagraph (e)(1), then the core Engine ingestion test shall be performed with one bird, using the heaviest bird specified in the second column of Table A, and ingested at a bird speed of 200 knots. Prior to the ingestion, the Engine must be stabilised at the mechanical rotor speed of the first exposed stage or stages that is consistent with a minimum approach idle setting, on a standard day, at 3 000 ft above ground level. The bird must be targeted on the first exposed rotating stage or stages at the blade aerofoil height measured at the leading edge that would maximise the bird material being ingested into the Engine core. (5) Ingestion into the Engine core of a bird under the conditions prescribed in (e)(4) must not cause any of the following: (i) an Engine shutdown during the required run-on demonstration specified in paragraph (e)(6) below; (ii) the conditions specified in paragraph CS-E 800(b)(2). (6) The following test schedule must be used: (i) Ingestion followed by 1 minute without any power lever movement. (ii) Followed by 2 minutes at between 30 and 35 % of the maximum rated Take-off Power or Thrust. (iii) Followed by 1 minute with the power or thrust increased from that set in subparagraph (e)(6)(ii), by between 5 and 10 % of the maximum rated Take-off Power or Thrust. (iv) Followed by 2 minutes with the power or thrust reduced from that set in subparagraph (e)(6)(iii), by between 5 and 10 % of maximum rated Take-off Power or Thrust. (v) Followed by a minimum of 1 minute at ground idle, then an Engine shutdown. The durations specified are times at the defined conditions. The power lever movement between each condition shall be 10 seconds or less in duration, except power lever movements that are allowed within subparagraph (e)(6)(iii), that are not limited, and those for setting power under subparagraph (e)(6)(iv), which shall be 30 seconds or less in duration. (7) Applicants must show that no unsafe condition will result if any Engine operating limit is exceeded during the run-on demonstration. (8) The core Engine flocking bird ingestion test of subparagraph (e) may be combined with the medium flocking bird test of subparagraph (d), if the climb fan rotor speed calculated in subparagraph (e)(1) is within 1 % of the first stage rotor speed required by subparagraph (d)(1). (f) *Impact.* The impact against the front of the Engine of the largest medium bird required by CS-E 800(d)(1)(v)(A) and of the large bird required by CS-E 800(b)(1)(ii) must be evaluated for compliance with [CS-E 540](#_DxCrossRefBm1371447741) under the Engine conditions specified for the ingestion tests. The bird speed must be the critical bird ingestion speed for the critical locations within the range of airspeeds for normal flight operations up to 450 m (1 500 ft) above ground level, but not less than V1 minimum for Engines to be installed on aeroplanes or higher than the speeds for the ingestion tests. The impact evaluation may be carried out separately from the ingestion evaluation; however, any damage resulting from the impact on the front of the Engine must be assessed in relation to consequential damage on the rotating blades. (g) *General* (1) Engine tests must be performed as required under CS-E 800(b), (c), (d) and (e) unless it is agreed that alternative evidence such as from Engine tests, rig tests, analysis or an appropriate combination of these, may come from the spplicant’s experience with engines of comparable size, design, construction, performance and handling characteristics, obtained during development, certification or operation. (2) The Engine test described in CS-E 800(b)(1), with regard to the single large bird, may be waived if it can be shown by test or analysis that the specifications of [CS-E 810(a)](#_DxCrossRefBm1371447727) are more severe. (3) Compliance with CS-E 800(c), in place of an Engine test, may be shown by: (i) incorporating the run-on specifications of CS-E 800(c)(1)(v) into the Engine test demonstration specified in CS-E 800(b)(1); or (ii) using a component test at the conditions of CS-E 800(b)(1) or (c)(1), subject to the following additional conditions: (A) All components that are critical to achieving the run-on criteria of CS-E 800(c) are included in the component test; and (B) The components tested under (A) above are subsequently installed in a representative Engine for a run-on demonstration in accordance with CS-E 800(c)(1)(v), except that steps 1 and 2 of CS-E 800(c)(1)(v) are replaced by a unique 14-minutes step at a thrust not less than 50% of Rated Take-off Thrust after the Engine is started and stabilized; and (C) Dynamic effects that would have been experienced during a full Engine test can be shown to be negligible with respect to meeting the specifications of CS-E 800(c). (4) Limit exceedances may be permitted to occur during the tests of CS-E 800(c), (d) and (e). Any limit exceedance must be recorded and shown to be acceptable under [CS-E 700](#_DxCrossRefBm1371447774). (5) For an Engine that incorporates an inlet protection device, compliance with CS-E 800 must be established with the device functioning and the Engine approval must be endorsed accordingly. (6) If compliance with all of the specifications of CS-E 800 is not established, the Engine approval will be endorsed accordingly by restricting the Engine installations to those where birds cannot strike the Engine or be ingested by the Engine or adversely restrict the airflow into the Engine. (7) An Engine to be installed in a multi-Engine Rotorcraft does not need to comply with the medium- or small-bird specifications of CS-E 800(d), but the Engine approval will be endorsed accordingly. (8) The Engine inlet throat area, as used in CS-E 800 to determine the bird quantity and mass, must be established and identified as a limitation on the inlet throat area in the instructions for installation. [Amdt No: E/1] [Amdt No: E/5]