OIL FUEL FILTER IMPENDING FUEL PRESSURE INLET PARTICLE Np
COOLER BYPASS BUTTON SENSOR SEPARATOR (%RPM)
BLOWER SENSOR
OIL LEVEL BLEED.AIR PORT ANTI.ICING AND MAIN FUEL IGNITER PLUG PRIMER FUEL INDICATOR START BLEED VALVE NOZZLE NOZZLE
LEFT SIDE
ALTERNATOR OIL FILTER OIL FILTER
BYPASS SENSOR BYPASS BUTTON
CHIP DETECTOR
FUEL BOOST
OIL TEMPERATURE PUMP
SENSOR
FUEL FILTER
SWIRL VANES
OIL PRESSURE
SENSOR
OIL DRAIN PLUG
AA9916_1
FRONT VIEW
SA
Figure 2-9. Engine T700 (Sheet 1 of 2)
ACCESSORY SECTION MODULE
THERMOCOUPLE
HARNESS OIL FILLER
HYDROMECHANICAL UNIT CAP HISTORY RECORDER
IGNITOR STARTER
PLUG
TORQUE AND
OVERSPEED SENSOR
HOT SECTION MODULE (INTERNAL) ECU IGNITION EXCITER OIL LEVEL INDICATOR
POWER TURBINE MODULE COLD SECTION MODULE
RIGHT SIDE SA AA9916_2
Figure 2-9. Engine T700 (Sheet 2 of 2)
HMU and in.uence fuel .ow, variable geometry position, and engine anti-ice start bleed valve operation. Fuel from the HMU .ows to a POU.
2.15.4.1 Pressurizing and Overspeed Unit. The POU sends some of the fuel through the fuel start manifold tube to the primer nozzles and allows back .ow of high pressure air for purging. The rest of the fuel is sent through the main fuel manifold to the injectors for starting accelera-tion and engine operation. It purges fuel from the primer nozzles after light off. It purges fuel from the primer nozzle and main fuel manifold on shutdown. It also reduces fuel .ow to prevent an engine overspeed when the overspeed system is tripped as sensed by the ECU.
2.16 ENGINE ALTERNATOR.
2.16.1 Engine Alternator. The engine alternator (Fig-ure 2-9) supplies ac power to the ignition exciter and elec-trical control unit (ECU). It also supplies a signal to the Ng SPEED cockpit indicator. All essential engine electrical functions are powered by the alternator.
a. When the alternator power supply to the ECU is in-terrupted, a loss of % RPM 1 or 2 and % TRQ indications will occur, with corresponding engine(s) increasing to maximum power (high side).
Change 4 2-21
b.
When the alternator Ng signal is interrupted, a loss of Ng cockpit indication will occur with a corresponding ENG OUT warning light and audio.
c.
A complete loss of engine alternator power results in affected engine(s) increasing to maximum power (high side) with a loss of cockpit indications of % RPM 1 or 2, % TRQ, Ng SPEED; and ENG OUT warning light and audio will occur. Overspeed protection is still available.
2.17 IGNITION SYSTEM.
The engine ignition system is a noncontinuous ac pow-ered, capacitor discharge, low voltage system. It includes a dual exciter, two igniter plugs, ignition leads, and ENGINE IGNITION keylock switch.
2.18 HISTORY RECORDER.
The engine history recorder is mounted on the right side of the swirl frame (Figure 2-9). It displays four digital counters which records information for maintenance pur-poses only. The history recorder will only operate with an ECU.
2.19 THERMOCOUPLE HARNESS.
A seven probe harness measures the temperature of the gases at the power turbine inlet. It provides a signal to the ECU, that relays it to the history recorder through the sig-nal data converter (SDC) to the cockpit temperature gage.
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