a380-Level II - Ata 49 Apu Systems

A380 TECHNICAL TRAINING MANUAL MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 49 APU Systems

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A380 TECHNICAL TRAINING MANUAL

LEVEL II - AT ATA 49 APU SYSTEMS APU Engine System System Description Description (2) . . . . . . . . . . . . . . . . . . . . . . . . . . 2 APU Bays Lights & Power Power Outlets Description Description (2) . . . . . . . . . . . . . . 8 APU Engine System System Operation, Operation, Control & Indicating Indicating (2) . . . . . . . . 12 APU Engine System System Component Component Location (2) . . . . . . . . . . . . . . . . . 30

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MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 49 APU Systems

TABLE OF CONTENTS

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APU ENGINE SYSTEM DESCRIPTION (2)

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System Architecture Auxiliary Power Unit (APU) load gearbox and Accessory GearBox (AGB) are key elements of both APU lubrication and starting systems. The load gearbox drives the two generators and the dedicated oil pump for generator lubrication. The AGB is driven by the starter and drives the engine oil pumps. The APU starting system can be energized by the APU battery or from the A/C DC network (external power for ground operations). A single APU P/BSW, P/BSW, located on the overhead panel, is used fo r normal start and shutdown. An emergency shutdown may be selected at either the Nose Landing Gear (NLG) control panel or the Integrated Refuel Panel (IRP). The APU FIRE P/BSW on the overhead p anel would also cause an APU shutdown, in addition to arming the APU fire extinguisher. The Electronic Control Box (ECB) controls and monitors APU start, operation and shutdown (normal and emergency). During the start sequence, the DC starter will drive the HP shaft of the APU. The same drive through the AGB will also operate the Fuel Control Unit (FCU) and the engine oil pump. The st arter drive will be maintained up to 40 % and then, the supply to the ignition system is removed. The APU has two igniter plugs which are used alternatively for each APU start, and are supplied by a high energy ignition unit. The APU shutdown can be classified as normal, automatic or emergency. emergency. During a normal shutdown, the ECB will immediately close the APU bleed valve, and initiate a cooling period of 60 seconds. The shutdown sequence is controlled based on time. It controls N1 speed reduction and Inlet Guide Vanes (IGVs) opening. An automatic shutdown occurs following a fault condition. In this case, ECB has determined that a monitored parameter is outside the acceptable limits or an APU component operation is not in the required configuration. On ground, an emergency shutdown will occur immediately following an APU fire detection. In this case, all APU suppli es (fuel and bleed ai r) MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 49 APU Systems

are shut immediately. In flight, the APU shutdown is selected by the flight crew. crew. During an automatic or an emergency shutdown, there is no cool down period.


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APU ENGINE SYSTEM DESCRIPTION (2) APU Oil System The APU has two oil sub-systems: - the main engine section lubrication, - and the APU generators lubrication. Oil for both systems is stored in a single tank, which has separate compartments for the generator section and the main engine section. The tank has common filler, which lets the generator section be filled first, and then the oil flows into the main engine section. In addition, the oil tank h as two external oil level indicators: a sigh gl ass for the main engine section and a bulls-eye for the generator section. NOTE: NOTE:

Note: When checking checking or replenishing replenishing the the APU APU oil system, system, it it is important to refer to the AMM graph to est ablish if the oil level usage against flight hours is within acceptable limits. The APU is certified for either type 1 or type 2 oils. An oil filling tool is available for use at the tank. Note: The oil level level may may also be reported reported through the service service report, and can be checked as correct through the Central Maintenance System (CMS). The APU oil system has filters for both sub-systems. The main engine section filter is at the AGB and the generator system filter is at the load gearbox. Both filters have a by-pass and are monitored for clogging.

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NOTE: NOTE:

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APU ENGINE SYSTEM DESCRIPTION (2) APU Drain System An APU overboard drain outlet is installed on the APU door. It is connected to: - the AGB drain to collect fuel and oil, - the starter drain pad for oil, - the IGV actuator, surge control valve actuator, gas generator and eductor drains for fuel. Drains are also installed to drain water from the inlet plenum and the APU exhaust. NOTE: NOTE: Note: Acceptable Acceptable drain drain limits are given given in the AMM. Following two or three successive APU shutdown sequences, it is possible that some drainage can be seen at the APU overboard drain outlet. After an APU auto-shutdown, the drains should be checked for fuel drainage. Refer to AMM or TSM for follow-up procedures.

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APU BAYS LIGHTS & POWER OUTLETS DESCRIPTION (2) System Overview The APU bays have two service lights: - one High Intensity Dis charge (HID) light installed in the tail cone APU compartment, - one Light Emitting Diod e (LED) light installed in t he air intake area of the APU and its above fireproof compartment. Each light is composed of: - a stainless steel housing, - a glass lens with steel grid cover, - one electrical connector and, - two halogen/LED bulbs. The service light for the tail cone APU compartment is controlled from a single toggle switch ins talled on the APU firewall. Whereas the service light for the air intake area of the APU and its above fireproof compartment is controlled from a single toggle switch installed in the fuselage floor of the aircraft section 19, on the LH of the bay access door (311AB). The system also includes on e 28 VDC power outlets to enable performance of the maintenance tasks in this area. The service lights and the power outlets are energized from the 28 VDC GND SVCE BUS. Human factor points: 2

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WARNI ARNING: NG: - BE CAREFUL WITH HOT COMPONENTS AND SURFACES, SURFACES, THERE IS A RISK OF BURNING, - BE CAREFUL WITH MOVING SURFACES. U

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CAUTION: CAUTION: - MAKE SURE THAT THAT YOU YOU INSTALL INSTALL THE CORRECT LAMPS IN THE APU COMPARTMENT, COMPARTMENT, DO NOT INSTALL LED TYPE LAMPS BECAUSE THEY ARE NOT RESISTANT TO HEAT. L

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APU AP U BA BAYS LI LIGH GHTS TS & POW POWER ER OU OUTL TLET ETS S DES DESCR CRIP IPTI TION ON (2 (2))

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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) General

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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2)

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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Start




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Running Bleed Air Supply




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Running GEN Supply




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Shutdown




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Abnormal Shutdown




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Emergency Shutdown




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APU ENGINE SYSTEM OPERATION, CONTROL & INDICATING (2) APU Low Oil Level




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APU ENGINE SYSTEM COMPONENT LOCATION (2) APU Zone 310 Zone 315

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APU EN ENGINE SY SYSTEM CO COMPONENT LO LO CA CATION (2 (2)

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APU EN ENGINE SY SYSTEM CO COMPONENT LO LO CA CATION (2 (2)

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AIRBUS S.A.S. 31707 BLAGNAC cedex, FRANCE STM REFERENCE L0Y06082 MARCH 2006 PRINTED IN FRANCE AIRBUS S.A.S. 2006 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

a380-Level II - Ata 49 Apu Systems

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