DOC AIRBUS | AMM A320FPOWER PLANT - GENERAL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The aircraft is powered by two IAE V2500 turbo fan engines designed for subsonic commercial airline service.
Each engine is housed in a nacelle suspended from a pylon attached below the wing.
The right and left power plants are interchangeable except for the thrust reverser C ducts.
** ON A/C NOT FOR ALL The aircraft is powered by two IAE V2500 turbo fan engines designed for subsonic commercial airline service.
Component LocationEach engine is housed in a nacelle suspended from a pylon attached below the wing.
The right and left power plants are interchangeable except for the thrust reverser C ducts.
2. Component Location
** ON A/C NOT FOR ALL | ------------------------------------------------------------------------------- |
| FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA |
| I I I I DOOR I REF. |
| ------------------------------------------------------------------------------- |
| 1100KM1 COWL-AIR INTAKE, LEFT 431 71-11-11 |
| 1100KM2 COWL-AIR INTAKE, RIGHT 441 71-11-11 |
| 1400KM COWL-FAN, LEFT 430 71-13-11 |
| 1410KM COWL-FAN, RIGHT 440 71-13-16 |
| 1420KM ROD-FAN COWL DOOR HOLD OPEN 400 71-13-12 |
| - ACCESS PANEL-FAN COWL RIGHT 400 71-13-17 |
| - STRAKE-FAN COWL, LEFT 438 71-13-19 |
| - STRAKE-FAN COWL, RIGHT 447 71-13-19 |
| 1500KM MOUNT-FORWARD 400 451AL 71-21-12 |
| 1550KM MOUNT-AFT 400 451AL 71-22-11 |
| - DRAIN MAST 430 438AR 71-71-42 |
| 3400KM THRUST REVERSER HALF, LEFT 450 78-32-01 |
| 3410KM THRUST REVERSER HALF, RIGHT 460 78-32-03 |
| 3900KM1 CONE-ENGINE EXHAUST, LEFT 450 78-11-12 |
| 3900KM2 CONE-ENGINE EXHAUST, RIGHT 460 78-11-12 |
| 3850KM1 COLLECTOR-COMMON NOZZLE EXHAUST, LEFT 455 78-11-11 |
| 3850KM2 COLLECTOR-COMMON NOZZLE EXHAUST, RIGHT 465 78-11-11 |
3. Description
A. Engine
The V2500 is a two spool, axial flow, high by-pass ratio turbo fan engine. The design and configuration of the engine are based on obtaining long life high reliability and easy access for line maintenance.
The V2500 incorporates a Full Authority Digital Engine Control (FADEC). The control system governs all engine control functions including power plant management.
The main modules of the engine are: the Low Pressure (LP) compressor (fan and booster) assembly, the LP compressor/intermediate case, the No. 4 bearing and combustion section, the High Pressure (HP) compressor, the HP turbine section, the LP turbine section and the accessory drives (gearbox).
The V2500 is a two spool, axial flow, high by-pass ratio turbo fan engine. The design and configuration of the engine are based on obtaining long life high reliability and easy access for line maintenance.
The V2500 incorporates a Full Authority Digital Engine Control (FADEC). The control system governs all engine control functions including power plant management.
The main modules of the engine are: the Low Pressure (LP) compressor (fan and booster) assembly, the LP compressor/intermediate case, the No. 4 bearing and combustion section, the High Pressure (HP) compressor, the HP turbine section, the LP turbine section and the accessory drives (gearbox).
B. Cowling
The cowling assembly consists of:
The hinged fan reverser and fan cowls are attached to the pylon.
The fan cowls are hinged at the upper part by four hinges.
They are held open by hold-open rods providing access to the engine for:
The cowling assembly consists of:
- the air intake cowl,
- the fan cowl 437AL, 438AR, 447AL, 448AR,
- the thrust reverser 451AL, 452AR, 461AL, 462AR,
- the Common Nozzle Assembly (CNA).
The hinged fan reverser and fan cowls are attached to the pylon.
The fan cowls are hinged at the upper part by four hinges.
They are held open by hold-open rods providing access to the engine for:
- maintenance,
- rigging,
- trouble shooting.
- a conductive graphite material within the skin.
On the fan cowl further protection is provided by the addition of expanded copper foil on its airwashed surface.
C. Mounts
The engine is attached to the pylon by two damage tolerant mounts. The mounts are the main attaching structures (forward and aft).
The forward mount comprises five attach bolts that connect the engine directly to the pylon.
The aft mount consists of a link and beam system attaching the engine to the pylon.
The engine is attached to the pylon by two damage tolerant mounts. The mounts are the main attaching structures (forward and aft).
The forward mount comprises five attach bolts that connect the engine directly to the pylon.
The aft mount consists of a link and beam system attaching the engine to the pylon.
D. Attachment Fittings
The attachment fittings and support brackets ensure the attachment on the engine of:
The attachment fittings and support brackets ensure the attachment on the engine of:
- components,
- ducts,
- pipes,
- electrical cables.
- the engine core,
- the fan case,
- the accessories,
- the accessory gearbox.
E. Fire Seals
The fire walls and fire seals provide fire protection (to a fireproof standard) between the power plant designated fire zones (fan and core compartments).
The fire walls and fire seals provide fire protection (to a fireproof standard) between the power plant designated fire zones (fan and core compartments).
F. Electrical Harness
The engine electrical harness:
The engine electrical harness:
- distributes the power required by the aircraft electrical system,
- supplies the 115VAC or 28VAC power to the engine or nacelle systems.
- transmits signals for:
nacelle sub-systems
engine control
monitoring functions
G. Engine Drains
The drain and vent system consists of lines collecting and carrying waste fluids and vapors overboard through the system drain mast.
This system drains the gearbox mounted accessories and engine components
The drain and vent system consists of lines collecting and carrying waste fluids and vapors overboard through the system drain mast.
This system drains the gearbox mounted accessories and engine components