Aircraft Reciprocating-Engine Failure - Pilot und Flugzeug

More documents

Recommendations

Info

Figure 8.10: Piston surface condition, 2000/2157, VH-MZK (right engine) While the piston crown surfaces from this engine were affected by immersion in seawater, it is evident from the residual deposits on the pistons that the engine was operating <strong>und</strong>er very different combustion conditions to the left engine (MZK) prior to engine failure, see figures 8.6 and 8.7, and other Lycoming TIO-540 engines, see for example figures 8.12 – 8.14. – 138 –
Figure 8.11: Cylinder head surface condition, 2001/5866, VH-JCH (right engine) – 139 –
Page 1:
ATSB TRANSPORT SAFETY INVESTIGATION
Page 4 and 5:
Published by: Australian Transport
Page 6 and 7:
4.4 Powertrain component failure co
Page 8 and 9:
8.3 Factors associated with bearing
Page 10 and 11:
THE AUSTRALIAN TRANSPORT SAFETY BUR
Page 12 and 13:
stresses in the component during en
Page 14 and 15:
• a combined reduction in compone
Page 16 and 17:
Figure 1.1: High-power reciprocatin
Page 18 and 19:
- 4 -
Page 20 and 21:
from human behaviour and the behavi
Page 22 and 23:
Risk in the context of public trans
Page 24 and 25:
and certificated against a simpler
Page 26 and 27:
3.3 Reciprocating-engine reliabilit
Page 28 and 29:
3.3.1 The impact of structural effi
Page 30 and 31:
Between 1972 and 1976, the NTSB inv
Page 32 and 33:
feather position. He set maximum po
Page 34 and 35:
79 (8% of the accidents, 15% of the
Page 36 and 37:
4.2 Powertrain component design An
Page 38 and 39:
2 2 T. n P. D. K. N P. D. n. S. N b
Page 40 and 41:
powertrain components affected by c
Page 42 and 43:
Figure 4.3: Schematic illustration
Page 44 and 45:
that variations from a norm do occu
Page 46 and 47:
4.5 References Repco 1980, Repco En
Page 48 and 49:
5.3 Information gathering Informati
Page 50 and 51:
5.3.4 Evaluating Evidence associate
Page 52 and 53:
- 38 -
Page 54 and 55:
Figure 6.1: Timeline of powertrain
Page 56 and 57:
6.2.1 Occurrence 2000/2157 VH-MZK (
Page 58 and 59:
Examination of the remaining five p
Page 60 and 61:
Figure 6.6: Ground tracks, radar da
Page 62 and 63:
• the separation of the destructi
Page 64 and 65:
Figure 6.10: Cracking in the fillet
Page 66 and 67:
6.2.4 Occurrence 2001/3357 VH-RNG R
Page 68 and 69:
6.2.5 Occurrence 2001/3251 VH-FIA R
Page 70 and 71:
Figure 6.17: The No.3 piston and cy
Page 72 and 73:
6.2.8 Occurrence 2003/3532 VH-HJS R
Page 74 and 75:
6.3.2 Occurrence 2000/90 VH-MZK (le
Page 76 and 77:
Figure 6.23: Galling (adhesive wear
Page 78 and 79:
earing alloy layer from the steel b
Page 80 and 81:
It is evident that the initial frac
Page 82 and 83:
Figure 6.27: Detailed views of the
Page 84 and 85:
6.3.6 Occurrence 200303701 VH-OCF R
Page 86 and 87:
Figure 6.31: The condition of littl
Page 88 and 89:
6.4.2 Occurrence 2000/2157 VH-MZK (
Page 90 and 91:
Figure 6.35: The No.6 connecting ro
Page 92 and 93:
Figure 6.39: No.6 connecting rod, b
Page 94 and 95:
Figure 6.42: The initiation site of
Page 96 and 97:
6.4.3 Occurrence 2000/2276 VH-ODE R
Page 98 and 99:
6.4.4 Occurrence 2001/2544 VH-TTX R
Page 100 and 101:
Figure 6.48: Crankshaft secondary f
Page 102 and 103: Figure 6.50: Detailed views of the
Page 104 and 105: Figure 6.52: Pneumatic pump couplin
Page 106 and 107: Figure 6.55: The No.6 connecting ro
Page 108 and 109: It is evident that with continued e
Page 110 and 111: Figure 6.61: Views of the fatigue f
Page 112 and 113: The engine had been operated under
Page 114 and 115: 6.4.8 Occurrence 2005/02231 VH-IGW
Page 116 and 117: Figure 6.70: Crankshaft web fractur
Page 118 and 119: 6.5 Crankshaft bearing, reported se
Page 120 and 121: Figure 6.74: Back surface of the bi
Page 123 and 124: 7 EVALUATION OF POWERTRAIN COMPONEN
Page 125 and 126: 7.2 Cylinder head fatigue fracture
Page 127 and 128: Figure 7.4: Cause-and-effect diagra
Page 129 and 130: 7.4 Cylinder attachment fastener fa
Page 131 and 132: 7.5.2 Connecting rod little-end fat
Page 133 and 134: Figure 7.9: Cause-and-effect diagra
Page 135 and 136: Inherent points of stress concentra
Page 137 and 138: friction is relatively small, so be
Page 139 and 140: speeds that exceed the design allow
Page 141 and 142: 8 ANALYSIS OF POWERTRAIN STRUCTURAL
Page 143 and 144: shockwaves through the gas in the c
Page 145 and 146: The relationship between engine pow
Page 147 and 148: Figure 8.5: Cylinder head surface c
Page 149 and 150: Figure 8.7: Piston surface conditio
Page 151: Figure 8.9: Cylinder head surface c
Page 155 and 156: Figure 8.13: Piston surface conditi
Page 159 and 160: Figure 8.17: Cylinder head surface
Page 161 and 162: Figure 8.19: Cylinder head surface
Page 165 and 166: Lead oxybromide deposits may also f
Page 167 and 168: The extent of detonation; light, me
Page 169 and 170: Combustion chamber component temper
Page 171 and 172: 8.3 Factors associated with bearing
Page 173 and 174: Any increase in oil-film temperatur
Page 175 and 176: Figure 8.37: Examples of trimetal b
Page 177 and 178: phase, in bearings manufactured wit
Page 179 and 180: emains attached to the aluminium al
Page 181 and 182: Bearing clearance Bearing clearance
Page 183 and 184: Figure 8.48: Detailed view of the n
Page 185 and 186: The available connecting-rod bearin
Page 187 and 188: Figure 8.52: Detailed view showing
Page 189 and 190: 8.4 Factors associated with the ret
Page 191 and 192: Figure 8.57 Example of insert-locat
Page 193 and 194: 8.4.3 Crankshaft main-bearing reten
Page 195 and 196: Figure 8.62: Detailed view of the m
Page 197 and 198: 8.5 Factors associated with fatigue
Page 199 and 200: • a change in the component has o
Page 201 and 202: Figure 8.68: Detailed view of the p
Page 203 and 204:
8.5.4 Crankshaft fatigue failure Cr
Page 205 and 206:
Figure 8.74: Schematic showing the
Page 207 and 208:
8.5.5 Crankshaft fatigue failure -
Page 209 and 210:
Figure 8.80: Metallographic section
Page 211 and 212:
Example 2: Teledyne Continental TSI
Page 213 and 214:
Figure 8.86: Metallographic section
Page 215 and 216:
Example 4: The Federal Aviation Adm
Page 217 and 218:
Example 6: Lycoming TIO-540-J2B, oc
Page 219 and 220:
Figure 8.94: Detailed view of the f
Page 221 and 222:
Examination of the connecting rod e
Page 223 and 224:
Planar defects created by journal g
Page 225 and 226:
Example 10: Lycoming TIO-540-J2BD,
Page 227 and 228:
Example 11: Lycoming TIO-540-J2BD,
Page 229 and 230:
Example 13: Lycoming IO-360-A1B6, m
Page 231 and 232:
Figure 8.114: Detailed views of the
Page 233 and 234:
Fatigue crack initiation, occurrenc
Page 235 and 236:
evident, from these sections, that
Page 237 and 238:
Figure 8.121: Detailed view, sectio
Page 239 and 240:
Figure 8.124: Fatigue crack initiat
Page 241 and 242:
8.6 Multiple event sequences It is
Page 243 and 244:
GAMI, General Aviation Modification
Page 245 and 246:
9 ANALYSIS OF AIRWORTHINESS ASSURAN
Page 247 and 248:
Engine reliability (issued December
Page 249 and 250:
In your letter of 5 August 2002, yo
Page 251 and 252:
Since August 2001, CASA has receive
Page 253 and 254:
Lycoming has received several field
Page 255 and 256:
1. Engines that have complied with
Page 257 and 258:
ACTION: Final rule. Date: October 2
Page 259 and 260:
Aggressive leaning: Aggressive lean
Page 261 and 262:
Feedback is an important component
Page 263 and 264:
feedback, in response to system mal
Page 265 and 266:
10 CONCLUSIONS The reliability of r
Page 267 and 268:
adial-engine combustion chamber (du
Page 269:
complete certainty, the consequence
show all

Aircraft Reciprocating-Engine Failure - Pilot und Flugzeug

Create successful ePaper yourself

Delete template?

Save as template?