(2)
Three rigid metal tubes, each of them provided with a flange-mounted chromel-alumel thermocouple probe, that are permanently mounted to the secondary junction box.
B. The right-hand thermocouple harness segment consists of:
(1)
A flange-mounted secondary junction box with a receptacle connector for connection with right-hand harness segment extension lead.
(2)
Three rigid metal tubes, each of them provided with a flange-mounted chromel-alumel thermocouple probe, that are permanently mounted to the secondary junction box.
C. The main junction box and leads assembly consists of:
(1)
A main junction box with 2 receptacle connectors for connecting with the right-hand harness segment extension lead and the forward extension lead.
(2)
Two main junction box extension leads which are rigid metal tubes each permanently affixed to the main junction box on one end with a mobile connector on the other end for connection to the left-hand secondary junction boxes.
D. The right-hand harness segment extension lead is a rigid metal tube fitted with a mobile connector at each end: one for connection with the right-hand secondary junction box and the other for connection with the main junction box.
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GAS INLET
A-A
EGT ThermocoupleFigure 1
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SEEA
RIGHT HARNESS
PROBE NO. 8 EXTENSION LEAD
RIGHT PROBE NO. 7 LEFTJUNCTION JUNCTIONBOX RIGHT EGT
BOX HARNESS
PROBE NO. 6 PROBE NO. 5
LEFT EGT
HARNESS
PROBE NO. 9
MAIN EXTENSION CABLE JUNCTION BOX INTERFACE TERMINAL
FORWARD
PROBE NO. 4
LOWER
PROBE NO. 1
JUNCTION BOX LOWER HARNESSPROBE NO. 2 EXTENSION
PROBE NO. 3
LOWER EGT HARNESS
A
EGT Thermocouple Harness and Probes Figure 2
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E. The forward extension lead is a rigid metal tube with a mobile connector at one end for connection with the main junction box and a terminal block on the other end for airplane interface. The lead provides ease of access for engine removal and EGT system testing.
3. EGT Indicator (Fig. 3)
_____________
A. The EGT indicator responds to the varying voltage generated by the parallel-connected Chromel-Alumel thermocouples located in the engine exhaust section to display temperatures over the range of -50°C to 1150°C.
B. AIRPLANES WITHOUT EIS; The EGT indicator incorporates a cold-junction reference circuit to reference the incoming signals to 0°C and provides the following:
(1)
Display of EGT by means of a pointer positioned by a DC motor driven by a closed loop DC servo. The pointer is spring-loaded to return to the bottom stop position in the event of a power or signal failure.
(2)
Numeric display of EGT by means of a four digit LED dot matrix display which electronically simulates the action of a four-drum mechanical counter. Blanking this display indicates failure in the EGT indication system.
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