Spark Ignition Aircraft Engine Endurance Test of Aviation ... - FAA

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Table A-7. Crankcase Main Bearing Bore Measurements. Bore Diameter Posttest (in.) Serviceable Limits Maximum (in.) New Limits Item (in.) No. 1 Front 2.5660 2.566-2.567 2.5685 Yes No. 1 Rear 2.5660 2.566-2.567 2.5685 Yes No. 2 Front 2.5665 2.566-2.567 2.5685 Yes No. 2 Rear 2.5670 2.566-2.567 2.5685 Yes No. 3 Front 2.5670 2.566-2.567 2.5685 Yes No. 3 Rear 2.5670 2.566-2.567 2.5685 Yes Table A-8. Piston Pin Bore Measurements Within New Limits? Pretest Posttest New Limits Max. Service Limits Max. Within New Item (in.) (in.) (in.) (in.) Limits? No. 1 Front—Top To Bottom 1.1249 1.1249 1.1249 1.1254 Yes No. 1 Front—Side To Side 1.1249 1.1249 1.1249 1.1254 Yes No. 1 Rear—Top To Bottom 1.1249 1.1249 1.1249 1.1254 Yes No. 1 Rear—Side To Side 1.1249 1.1249 1.1249 1.1254 Yes No. 2 Front—Top To Bottom 1.1250 1.1249 1.1249 1.1254 Yes No. 2 Front—Side To Side 1.1250 1.1249 1.1249 1.1254 Yes No. 2 Rear—Top To Bottom 1.1249 1.1249 1.1249 1.1254 Yes No. 2 Rear—Side To Side 1.1249 1.1249 1.1249 1.1254 Yes No. 3 Front—Top To Bottom 1.1249 1.1249 1.1249 1.1254 Yes No. 3 Front—Side To Side 1.1249 1.1249 1.1249 1.1254 Yes No. 3 Rear—Top To Bottom 1.1249 1.1249 1.1249 1.1254 Yes No. 3 Rear—Side To Side 1.1249 1.1249 1.1249 1.1254 Yes No. 4 Front—Top To Bottom 1.1250 1.1249 1.1249 1.1254 Yes No. 4 Front—Side To Side 1.1250 1.1249 1.1249 1.1254 Yes No. 4 Rear—Top To Bottom 1.1250 1.1249 1.1249 1.1254 Yes No. 4 Rear—Side To Side 1.1250 1.1249 1.1249 1.1254 Yes Table A-9. Piston Skirt Measurements Service Limits Minimum (in.) Item Pretest (in.) Posttest (in.) No. 1 5.1170 5.1130 5.1090 Yes No. 2 5.1170 5.1120 5.1090 Yes No. 3 5.1171 5.1130 5.1090 Yes No. 4 5.1171 5.1150 5.1090 Yes Within Service Limits? A-5
Table A-10. Top Piston Ring Side Clearance Measurements Item Pretest (in.) Posttest (in.) New Limits (in.) Service Limits Max. (in.) No. 1—Top 0.0025 0.0030 0.0025-0.0055 0.0080 No. 1—Front 0.0025 0.0025 0.0025-0.0055 0.0080 No. 1—Bottom 0.0025 0.0025 0.0025-0.0055 0.0080 No. 2—Top 0.0025 0.0040 0.0025-0.0055 0.0080 No. 2—Front 0.0025 0.0025 0.0025-0.0055 0.0080 No. 2—Bottom 0.0025 0.0025 0.0025-0.0055 0.0080 No. 3—Top 0.0025 0.0040 0.0025-0.0055 0.0080 No. 3—Front 0.0025 0.0025 0.0025-0.0055 0.0080 No. 3—Bottom 0.0025 0.0025 0.0025-0.0055 0.0080 No. 4—Top 0.0025 0.0040 0.0025-0.0055 0.0080 No. 4—Front 0.0025 0.0025 0.0025-0.0055 0.0080 No. 4—Bottom 0.0025 0.0025 0.0025-0.0055 0.0080 Table A-11. Middle Piston Ring Side Clearance Measurements Item Pretest (in.) Posttest (in.) New Limits (in.) Service Limits Max. (in.) No. 1—Top - 0.0015 0.0000-0.0040 0.0060 No. 1—Front - 0.0015 0.0000-0.0040 0.0060 No. 1—Bottom - 0.0015 0.0000-0.0040 0.0060 No. 2—Top - 0.0010 0.0000-0.0040 0.0060 No. 2—Front - 0.0010 0.0000-0.0040 0.0060 No. 2—Bottom - 0.0010 0.0000-0.0040 0.0060 No. 3—Top - 0.0010 0.0000-0.0040 0.0060 No. 3—Front - 0.0010 0.0000-0.0040 0.0060 No. 3—Bottom - 0.0010 0.0000-0.0040 0.0060 No. 4—Top - 0.0010 0.0000-0.0040 0.0060 No. 4—Front - 0.0010 0.0000-0.0040 0.0060 No. 4—Bottom - 0.0010 0.0000-0.0040 0.0060 A-6
Page 1 and 2:
DOT/FAA/AR-06/43 Office of Aviation
Page 3 and 4:
1. Report No. DOT/FAA/AR-06/43 4. T
Page 5 and 6:
LIST OF FIGURES Figure Page 1 Oil F
Page 7 and 8:
46 Posttest Connecting Rod Bearing
Page 9 and 10: LIST OF ACRONYMS 100 low-lead 100LL
Page 11 and 12: more fuel volume flow. Future tests
Page 13 and 14: At the completion of the test, the
Page 15 and 16: The engine was installed in a test
Page 17 and 18: Table 4. Parameter Settings for End
Page 19 and 20: Figure 1. Oil Filter Inspection Fig
Page 21 and 22: Figure 4. Corrected Power at 2700 r
Page 23 and 24: Figure 8. Corrected Power at 2300 r
Page 25 and 26: Figure 10. Corrected BSFC vs Fuel M
Page 27 and 28: Figure 12. Corrected Power and Aver
Page 31 and 32: Table 8 provides a summary of the e
Page 37 and 38: output from all six cylinders. Pist
Page 39 and 40: The oil filter was cut open and the
Page 41 and 42: Figure 29. Top of Piston Face of Cy
Page 43 and 44: Figure 33. Bottom of Piston Face an
Page 45 and 46: Figure 39. Posttest Crankshaft Conn
Page 47 and 48: The camshaft lobes, shown in figure
Page 49 and 50: Figure 59 shows a combustion chambe
Page 51 and 52: Figure 63. Posttest Rocker Arm Show
Page 53 and 54: Visual observation of the intake tu
Page 55 and 56: Future testing should address effec
Page 57 and 58: Table A-2. Middle and Rear Main Cra
Page 59: Table A-4. Valve Tappet Outer Diame
Page 63: Table A-14. Intake Valve Seat Width
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Spark Ignition Aircraft Engine Endurance Test of Aviation ... - FAA

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