[IAE] V2500 line&base maintenance manual 航线和基地维护培训手册

SECTION 2
PROPULSION SYSTEM (Chapter 71)
FIRE PROTECTION (Chapter 26)
COOLING &VENTILATION (Chapter 75)
IAE V2500 Line and Base Maintenance Propulsion System
Propulsion System Introduction
Purpose
The propulsion system encloses the powerplant.
It provides the ducting for the fan bypass air and for an aerodynamic exterior to the engine.
Description
The propulsion system comprises of the engine and the following nacelle units:
• Intake cowl assembly.
• The Left and Right Hand hinged fan cowl doors.
• The thrust reverser ‘C’-ducts.
• The common nozzle assembly (CNA).
• Engine mounts for the front and rear of the engine.
• Fire protection and ventilation system.
Airframe Interfaces
Purpose
The airframe interfaces provide a link between the engine and aircraft systems.
Description
The following units form the interface between the aircraft and engine:
• The front and rear engine mounts.
• The bleed air off-takes.
• The starter motor air supply.
• Integrated Drive Generator (IDG) electrical power.
• Fuel supplies.
• Hydraulic fluid supplies.
• FADEC system interfaces.
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Nacelle Air Temperature (NAC)
Purpose
The nacelle air temperature gives an advisory indication to the lower ECAM CRT if a temperature exceedance has been experienced.
Location
The NAC sensor is located by the bifurcation panel at bottom dead centre between the two thrust reverser C duct halves.
The NAC is in zone 2.
Description
Under normal conditions the NAC indication is not displayed on the lower ECAM CRT.
When a temperature exceedance of 320 deg.c has occurred the indication will appear to the lower ECAM CRT.
This indication is displayed if;
The system is not in engine starting mode and one of the two temperatures reaches the advisory threshold.