DOC AIRBUS | AMM A320FELECTRICAL HARNESS - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
The engine electrical harnesses connect the electrical components installed in the nacelle to the aircraft electrical systems.
The harnesses have two primary assemblies. The fan zone harness and the core zone harness. Each of these primary assemblies has smaller harness assemblies
The core zone harnesses are connected to the fan zone harnesses at the bifurcation panel. The harnesses are installed around the engine and go up to the pylon break points. Here they interface with the aircraft electrical systems. The harnesses are attached to the engine with brackets, raceways, clips and clamps.
** ON A/C NOT FOR ALL The engine electrical harnesses connect the electrical components installed in the nacelle to the aircraft electrical systems.
The harnesses have two primary assemblies. The fan zone harness and the core zone harness. Each of these primary assemblies has smaller harness assemblies
The core zone harnesses are connected to the fan zone harnesses at the bifurcation panel. The harnesses are installed around the engine and go up to the pylon break points. Here they interface with the aircraft electrical systems. The harnesses are attached to the engine with brackets, raceways, clips and clamps.
Electrical Harnesses - Left Side of Engine2. Description
A. The harness assemblies
(1) that are part of the fan zone harness are:
(a) The Electronic Engine Control (EEC) harness.
(b) The EEC and ignition supply harness.
(c) The general supply harness.
(2) These harness assemblies are connected to the following engine components:
(a) The EDA.
(b) The ACOC modulating valve.
(c) The stage 10 solenoid valve.
(d) The pneumatic starter valve.
(e) The stage 7 solenoid valves.
(f) The ACOC oil temperature thermocouple.
(g) The relay box.
(h) The EEC.
(i) The Fuel Metering Unit (FMU).
(j) The fuel flow transmitter.
(k) The Integrated Drive Generator (IDG) fuel temperature thermocouple.
(l) The FCOC fuel temperature thermocouple.
(m) The fuel diverter and return valve.
(3) that are part of the core zone harness are:
(a) The fire detection (system A), cabin services and nacelle overtemperature harness.
(b) The fire detection (system B) harness.
(c) The EEC harness.
(d) The EEC link harness.
(e) The Exhaust Gas Temperature (EGT) harness.
(f) The ignition harness.
(4) These harness assemblies are connected to the following engine components:
(a) The Active Clearance Control (ACC) actuator.
(b) The Variable Stator Vane (VSV) actuator.
(c) The Low Pressure Control (LPC) bleed master actuator.
(d) The T2.5 CM terminal.
(e) The terminal block.
(f) The igniter boxes.
(g) The 10th stage valve.
(h) The T3 sensor.
(i) The EGT thermocouples.
3. Operation
The engine electrical harness supply the power that is necessary for the electrical systems. They also transmit the signals for the nacelle sub-systems and the engine control and monitoring functions.
The engine electrical harness supply the power that is necessary for the electrical systems. They also transmit the signals for the nacelle sub-systems and the engine control and monitoring functions.