R Auxiliary Power System - Operating Envelope R Figure 008A (SHEET 1)
 EFF : 401-499, 49-00-00Page 20 Config-1 Aug 01/05
 CES R Auxiliary Power System - Operating Envelope R Figure 008A (SHEET 2)

 EFF : 401-499, 49-00-00Page 21 Config-1 Aug 01/05
 CES  AIRBORNE AUXILIARY POWER - GENERAL - DESCRIPTION AND OPERATION

______________________________________________________________
 1. General
_______
 A. Function of the Auxiliary Power System In order to permit A/C ground operation independent of electric and pneumatic ground power, the A/C is equipped with an auxiliary power system. The A/C thus can be powered up autonomously, allowing the operator to service airports without adequate ground power facilities. In-flight availability of the auxiliary power system permits A/C operation under MMEL-conditions and under ETOPS.
 B. System Capabilities The gas turbine engine (the APU), which is used as the systems power source, is equipped to supply 115VAC for operation of the A/C electrical systems. It also supplies pneumatic power to permit main engine start (MES) and environmental control system (ECS) operation.
 C. APU Supplier The APU, fully designated 131-9 (A), is supplied by the AlliedSignal Aerospace Company - Engines.
 2. Component Location
__________________
 A. Tailcone
 (Ref. Fig. 001)

 B. Cockpit
 (Ref. Fig. 002, 003, 004)

 C. Avionics Compartment/Aft Cargo Compartment
 (Ref. Fig. 005)

 3. System Description
__________________
 A. Power Plant (Ref. 49-10-00) The power plant is installed in the rear fuselage aft of the passenger compartment. It occupies the tailcone, the rearmost portion of the fuselage. The tailcone has been fitted with a fireproof compartment to house the APU. Peripheral systems are installed both in the APU compartment as well as to the front and rear of it. Doors permit access to all components of the power plant.

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-00-00Page 1 201-210, Config-2 Aug 01/05
 CES

 Power Plant - Component Location
 Figure 001

 CES

 Auxiliary Power System - Component Location (Flight Deck) Figure 002

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-00-00Page 3 201-210, Config-2 Aug 01/05
 CES

 Auxiliary Power System - Component Location (ECAM System) Figure 003

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-00-00Page 4 201-210, Config-2 Aug 01/05
 CES

 Auxiliary Power System - Component Location (Maintenance System) Figure 004

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-00-00Page 5 201-210, Config-2 Aug 01/05
 CES

 Auxiliary Power System - Component Location (Avionics Compartment/Aft Cargo
 Compartment)
 Figure 005

 CES

 B. Engine (Ref. 49-20-00) The engine supplies:
 -pneumatic power,
 -electrical power, and

 -cooling air.
 To fulfill these requirements, the engine consists essentially of a power
 section to generate shaft power. A load compressor is flanged to this
 shaft to generate pneumatic power. The same shaft also drives a gearbox.
 A generator is attached to this gearbox to generate electrical power. A
 fan to provide cooling air is also attached to the gearbox.

 C. Engine Fuel and Control (Ref. 49-30-00) The APU system receives fuel from the A/C APU fuel supply system (Ref. 28-22-00). Incoming fuel is metered by the fuel control unit (FCU) and delivered to the flow divider assy. From there it is routed via 2 fuel manifolds to the fuel nozzles, located in the combustion chamber.
 D. Ignition and Starting (Ref. 49-40-00) The APU is fitted with a DC starter motor, which draws its power from the electrical system battery bus. It turns the engine to such speed that self-sustained engine operation becomes possible. The fuel-air mixture in the combustion chamber is ignited by the ignition system, also fitted to the APU. Electrical power to the ignition system is supplied through the ECB.
 E. Air (Ref. 49-50-00) The engine is equipped to provide 2 separate air sources:
 -pneumatic power (bleed air) for main engine start (MES) and the
 environmental control system (ECS),

 -cooling air for ventilation of the APU compartment and cooling of the APU lubrication system.
 F. Engine Controls (Ref. 49-60-00) In order to start, control its performance and to shut off the auxiliary power system, manual and automatic controls are provided. Manual control of the APU is possible through the crew interfaces in the cockpit. Automatic control is accomplished through the ECB.
　
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