DOC AIRBUS | AMM A320FPOWER PLANT - GENERAL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
Power Plant2. Description
A. Nacelle Systems
(1) The nacelle systems provide the engine with an aerodynamic and protective enclosure for engine-mounted components, support and transfer loads to the pylon, and collects and discharges oil, fuel and hydraulic fluid from the engine and its components. Nacelle system components are mounted on the engine and on the pylon. They provide the engine with these capabilities:
- An aerodynamic and protective enclosure for engine mounted components
- Support and transfer of loads to the pylon
- Collection and discharge of oil, fuel and hydraulic fluid from the engine and its components.
B. Nacelle Systems and Components
(1) Engine Mounted Components
(a) Inlet Cowl
The inlet cowl's aerodynamic barrel smooths airflow, providing uniform pressure as air reaches the fan. The outer skin provides even airflow across the engine nacelle. The inner skin forms the engine inlet and acoustic treatment. The inlet cowl is secured to the engine fan case. The outer barrel is a two piece carbon epoxy assembly extending from the aluminum inlet lip skin interface to the leading edge of the fan cowl. The five piece segmented forward bulkhead and three-piece segmented aft bulkhead provide impact protection and structural support for the inlet assembly. An access panel is provided in the outer barrel for maintenance of the thermal anti-ice duct that supplies the inlet lip with hot air. A second panel serves the T2 probe and the wiring harness. A small flush NACA scoop is provided on the inlet outer barrel for the fan compartment cooling. The inner barrel has gravity drainage holes embedded within the honeycomb core. The ice buildup on the inlet lip of the inlet cowl is prevented via the RhorSwirl® Nozzle anti-ice system. The inlet is interchangeable.
The inlet cowl's aerodynamic barrel smooths airflow, providing uniform pressure as air reaches the fan. The outer skin provides even airflow across the engine nacelle. The inner skin forms the engine inlet and acoustic treatment. The inlet cowl is secured to the engine fan case. The outer barrel is a two piece carbon epoxy assembly extending from the aluminum inlet lip skin interface to the leading edge of the fan cowl. The five piece segmented forward bulkhead and three-piece segmented aft bulkhead provide impact protection and structural support for the inlet assembly. An access panel is provided in the outer barrel for maintenance of the thermal anti-ice duct that supplies the inlet lip with hot air. A second panel serves the T2 probe and the wiring harness. A small flush NACA scoop is provided on the inlet outer barrel for the fan compartment cooling. The inner barrel has gravity drainage holes embedded within the honeycomb core. The ice buildup on the inlet lip of the inlet cowl is prevented via the RhorSwirl® Nozzle anti-ice system. The inlet is interchangeable.
(b) Exhaust Nozzle Assembly
- Exhaust nozzle
- Forward and aft center body (exhaust plug).
(2) Pylon Mounted Components
(a) Fan Cowls
The fan cowls protect the engine fan case and the components. The panels provide aerodynamic smoothness and fire protection to the nacelle fan compartment. The fan cowls are made of lightweight carbon-epoxy laminate construction and have lightning strike protection. The cowls are manually opened and kept open by the Hold Open Rods (HORs). They provide access to the fan case mounted engine components. The fan cowls have three hinges at the top to the pylon and incorporate a latch system at the bottom. The axial locator blades and the grooves maintain interface gaps with the inlet and the thrust reverser. The provisions on the doors allow interchangeable strake mounting. A strake is mounted on the fan cowl outer surface for low speed, high angle of attack performance. The aerodynamic strake deflects airflow as required in certain maneuvers related to the aircraft performance. A fan cowl vent provides the overpressure protection in the event of a burst anti-ice duct. The drain holes at the bottom of the fan cowls provide fluid drainage.
The fan cowls protect the engine fan case and the components. The panels provide aerodynamic smoothness and fire protection to the nacelle fan compartment. The fan cowls are made of lightweight carbon-epoxy laminate construction and have lightning strike protection. The cowls are manually opened and kept open by the Hold Open Rods (HORs). They provide access to the fan case mounted engine components. The fan cowls have three hinges at the top to the pylon and incorporate a latch system at the bottom. The axial locator blades and the grooves maintain interface gaps with the inlet and the thrust reverser. The provisions on the doors allow interchangeable strake mounting. A strake is mounted on the fan cowl outer surface for low speed, high angle of attack performance. The aerodynamic strake deflects airflow as required in certain maneuvers related to the aircraft performance. A fan cowl vent provides the overpressure protection in the event of a burst anti-ice duct. The drain holes at the bottom of the fan cowls provide fluid drainage.
(b) Thrust Reverser
When stowed, the thrust reverser provides a smooth surface for the fan exhaust air to produce forward thrust. When deployed, the thrust reverser redirects the fan exhaust air to produce reverse thrust that assists in braking. Each thrust reverser door is attached to the pylon. The two thrust reverser halves open at the 6 o'clock location and rotate around the 12 o'clock hinge beam to give access to the engine for maintenance. For maintenance purposes, each cowl is hydraulically opened and closed by a cowl opening actuator and kept in the open position with the HORs. The access panels allow access to the engine components.
When stowed, the thrust reverser provides a smooth surface for the fan exhaust air to produce forward thrust. When deployed, the thrust reverser redirects the fan exhaust air to produce reverse thrust that assists in braking. Each thrust reverser door is attached to the pylon. The two thrust reverser halves open at the 6 o'clock location and rotate around the 12 o'clock hinge beam to give access to the engine for maintenance. For maintenance purposes, each cowl is hydraulically opened and closed by a cowl opening actuator and kept in the open position with the HORs. The access panels allow access to the engine components.
(3) Engine Mounts
- Front
- Aft (aft mount and thrust link assembly).
- Support the weight of the engine
- Transmit the thrust of the engine to the pylon
- Make sure that the engine does not turn around its axis
- Hold lateral loads.
(4) Engine Build-up Unit (EBU)
These are the necessary system components which are installed to the engine and the nacelle and connected to the pylon and the aircraft systems:
These are the necessary system components which are installed to the engine and the nacelle and connected to the pylon and the aircraft systems:
- Nacelle Anti-Icing (NAI)
- Environmental Control System (ECS)
- Hydraulic system
- Fuel supply
- Starter ducts
- Fire extinguishing
- Harnesses
- Drains.