A. Temperature (continued)
1. InterTurbine Temperature Sensing System (ITT) (continued)
CHART 2
THERMOELECTRIC VOLTAGE IN ABSOLUTE MILLIVOLTS

Deg CentigradeGraph Deg
° 2°4° 6° 7°8° °
C 0 1 3° 5° 9°10 C
-40 1.527 1.563 1.600 1.636 1.673 1.709 1.745 1.781 1.817 1.853 1.889 -40 -30 1.156 1.193 1.231 1.268 1.305 1.342 1.379 1.416 1.453 1.490 1.527 -30 -20 0.777 0.816 0.854 0.892 0.930 0.968 1.005 1.043 1.081 1.118 1.156 -20 -10 0.392 0.431 0.469 0.508 0.547 0.585 0.624 0.662 0.701 0.739 0.777 -10
0 0.000 0.039 0.079 0.118 0.157 0.197 0.236 0.275 0.314 0.353 0.392 0
0 0.000 0.039 0.079 0.119 0.158 0.198 0.238 0.277 0.317 0.357 0.397 0
10 0.397 0.437 0.477 0.517 0.557 0.597 0.637 0.677 0.718 0.758 0.798 10
20 0.798 0.838 0.879 0.919 0.960 1.000 1.041 1.081 1.122 1.162 1.203 20
30 1.203 1.244 1.285 1.325 1.366 1.407 1.448 1.489 1.529 1.570 1.611 30
40 1.611 1.652 1.693 1.734 1.776 1.817 1.858 1.899 1.940 1.981 2.022 40
50 2.022 2.064 2.105 2.146 2.188 2.229 2.270 2.312 2.353 2.394 2.436 50
60 2.436 2.477 2.519 2.560 2.601 2.643 2.684 2.726 2.767 2.809 2.850 60
70 2.850 2.892 2.933 2.975 3.016 3.058 3.100 3.141 3.183 3.224 3.266 70
80 3.266 3.307 3.349 3.390 3.432 3.473 3.515 3.556 3.598 3.639 3.681 80
90 3.681 3.722 3.764 3.805 3.847 3.888 3.930 3.971 4.012 4.054 4.095 90
Deg Fahrenheit Graph Deg
F0 1 2° 3° 4° 5° 6° 7° 8° 9°10° F

-40 1.527 1.547 1.567 1.588 1.608 1.628 1.648 1.669 1.689 1.709 1.729 -40 -30 1.322 1.342 1.363 1.383 1.404 1.424 1.445 1.465 1.486 1.506 1.527 -30 -20 1.114 1.135 1.156 1.177 1.197 1.218 1.239 1.260 1.280 1.301 1.322 -20 -10 0.904 0.925 0.946 0.968 0.989 1.010 1.031 1.051 1.072 1.093 1.114 -10
0 0.692 0.714 0.735 0.756 0.777 0.799 0.820 0.841 0.862 0.883 0.904 0
0 0.692 0.671 0.650 0.628 0.607 0.585 0.564 0.543 0.521 0.500 0.478 0
10 0.478 0.457 0.435 0.413 0.392 0.370 0.349 0.327 0.305 0.284 0.262 10
20 0.262 0.240 0.218 0.197 0.175 0.153 0.131 0.109 0.088 0.066 0.044 20
30 0.044 0.022 0.000 0.022 0.044 0.066 0.088 0.110 0.132 0.154 0.176 30
40 0.176 0.198 0.220 0.242 0.264 0.286 0.308 0.331 0.353 0.375 0.397 40
50 0.397 0.419 0.441 0.464 0.486 0.508 0.530 0.553 0.575 0.597 0.619 50
60 0.619 0.642 0.664 0.686 0.709 0.731 0.753 0.776 0.798 0.821 0.843 60
70 0.843 0.865 0.888 0.910 0.933 0.955 0.978 1.000 1.023 1.045 1.068 70
80 1.068 1.090 1.113 1.135 1.158 1.181 1.203 1.226 1.248 1.271 1.294 80
90 1.294 1.316 1.339 1.362 1.384 1.407 1.430 1.452 1.475 1.498 1.520 90
100 1.520 1.543 1.566 1.589 1.611 1.634 1.657 1.680 1.703 1.725 1.748 100 110 1.748 1.771 1.794 1.817 1.839 1.862 1.885 1.908 1.931 1.954 1.977 110 120 1.977 2.000 2.022 2.045 2.068 2.091 2.114 2.137 2.160 2.183 2.206 120 130 2.206 2.229 2.252 2.275 2.298 2.321 2.344 2.367 2.390 2.413 2.436 130 140 2.436 2.459 2.482 2.505 2.528 2.551 2.574 2.597 2.620 2.643 2.666 140
EFFECTIVITY:
040-999
77-20-00 Feb 1/98
77-20-00 PAGE5

PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

A. Temperature (continued)
1. InterTurbine Temperature Sensing System (ITT) (continued)
On-OffSwitch  BARFIELD  DisplayWindow 
ON 
SystemResistance Selector  SYSTEMRES TEMPADJ SHOT TEST LEAD AND PUSH TO SET SYSTEMRES RX INSULATION RESISTANCE TEMPMEASURE  FunctionSelectedSwitch 
RANGE  ACFT  LEADSRES 
Set SystemResistanceSwitch ResistanceMeasurementSwitch ResistanceRangeSelector 

Barfield TT-1000Test Set Controls Figure 501
EFFECTIVITY:
040-999

PAGE
6 77-20-00
Jan 10/90 77 -20-00
PIPER AIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCE MANUAL

A. Analyzers
1. EngineConditionTrendMonitoringSystem
(a) General
Contemporarygas turbine/turbo prop engine maintenance systemsfrequentlyincludeinflight
engine performance monitoring,as a meansof detecting mechanicaldeteriorationin engine
gaspaths. A simple system requiring almostno arithmetic calculationhas been devised for
PT6 engines to aid in planning indicatedrectificationsearly, and so reduce primary and
secondarydamagecostsresultingfromfully developed failures,and risks of inflight shutdowns
andflight cancellations.
The turbine engine characteristic of repeatedly producingits output at, or very close to, charted gas generator parametervalues provides the basis for the PT6 trend monitoring system.Thus, under known conditions of pressure altitude(PA) and indicated outside air temperature (IOAT), the gas generator parameter temperature speed (Ng),
values of inter-turbine (ITT), compressor and fuel flow (Wf), for particular outputshaft speeds (Np) and torques are predictable within reasonablelimits.
　
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