Airbus A318 A319 A320 A321 Chapter 24 Electrical Power Aircraft Maintenance Manual AES Rev 40 (2012)

Description

Airbus A318 A319 A320 A321 Chapter 24 Electrical Power Aircraft Maintenance Manual AES Rev 40 (2012)

This download is ATA Chapter 24 of the A318/A319/A320/A321 Aircraft Maintenance Manual as issued under AES Revision n˚ 40 dated May 01/12. It is the electrical-power chapter only: generation, conversion, emergency supply, ground power, bus switching, galley load, battery charging and electrical routing/EWIS inspection. Effectivity notes in the text distinguish On A/C ALL, On A/C 003-004, On A/C 005-099 and selected zone differences such as APU generator location on 003-007 versus 008-099.

File Details

• Manual type: Aircraft Maintenance Manual – Chapter 24 Electrical Power
• Brand / models: Airbus A318, A319, A320, A321
• Language: English
• Page count: 1442
• File format: PDF
• Publisher mark: AES
• Revision: n˚ 40
• Date: May 01/12

How the Electrical Network Is Built

The Airbus A318 A319 A320 A321 Chapter 24 Electrical Power Aircraft Maintenance Manual AES Rev 40 (2012) opens with the general arrangement used on the family. Two Integrated Drive Generators normally supply the aircraft in flight; each engine HP rotor drives one IDG through the accessory gearbox. An APU-driven third generator can replace GEN 1 or GEN 2 in flight and can power the network on the ground when a GPU is not connected. Two Transformer Rectifiers convert AC to DC in normal configuration. After a major generation loss a hydraulically driven Constant Speed Motor/Generator (CSM/G) supplies the systems needed for aircraft control. On the ground a Ground Power Unit can feed the network through the external-power receptacle and GPCU.

Each IDG produces 115/200 VAC, 3-phase, 400 Hz. Leading particulars of the main generator and APU generator are given as 90 KVA at the Point of Regulation (POR) with the same 115 V/200 V three-phase 400 Hz output. The IDG combines a hydromechanical Constant-Speed Drive with the generator so variable engine speed becomes constant generator speed. The APU generator is driven at a nominal 24000 rpm constant speed and is a brushless oil-cooled machine. The CSM/G is listed at 5 KVA at POR, 115/200 VAC, three-phase, 400 Hz, speed-regulated from Blue hydraulic oil. In normal conditions an electric pump supplies Blue; in emergency the RAT supplies Blue. Loss of AC BUS 1 and AC BUS 2 automatically commands the RAT and CSM/G; a guarded MAN ON pushbutton on the EMER ELEC PWR panel provides a manual path that is redundant with automatic RAT logic.

The two IDGs are never electrically coupled. Network 1 comprises AC BUS 1, AC ESS BUS and AC SHED ESS BUS. Network 2 is AC BUS 2. TR1, fed from AC BUS 1, supplies DC BUS 1, DC BAT BUS, DC ESS BUS and DC SHED ESS BUS. Two batteries sit on the DC BAT BUS. TR2, fed from AC BUS 2, supplies DC BUS 2. If TR1 or TR2 fails, the Essential Transformer Rectifier (ESS TR) takes DC ESS and DC SHED ESS. Transfer contactors (BTC 1/2) can feed either AC network from GEN 1, GEN 2, APU GEN or EXT PWR according to source priority: own generator, ground power, APU GEN, then the opposite generator. A BUS TIE pushbutton can lock both BTCs and isolate the channels.

Batteries 2PB1 and 2PB2 are nickel-cadmium packs of twenty cells in a stainless-steel case: 24 V nominal, 23 Ah, 60 cm³ electrolyte reserve and two ventilation ducts. They start the APU in flight and on the ground and back the essential network during RAT deployment and when the emergency generator is not available. Each pack has a Battery Charge Limiter and a shunt. BCL logic includes charge-cycle close/open thresholds (VBAT < 26.5 V with V3PP > 27 V; end of charge when ICH < 4 A), thermal-runaway opening, APU-start closing and hot-bus integrity opening. The static-inverter section describes a unit that converts battery DC into single-phase 115 VAC/400 Hz; the general chapter also records a 350 VA inverter fed from the BAT BUS for loss of both AC buses, while the dedicated 24-28 task block describes a 1000 VA inverter fed from battery 1.

Galley supply is 115 VAC with 50 KVA available for all galleys, split as 30 KVA aft and 20 KVA forward. Automatic and manual galley and bus shedding, commercial-load shedding and C/B TRIPPED warning inhibit/reactivate tasks sit in the distribution ATA blocks. Ground-service AC and DC buses can be energized from external power independently of the full flight network.

Chapters Covered

• 24-00-00 Electrical Power – General: description and operation, general schematics, component and control/indicating locations, AC and DC generation/distribution schematics, Lower ECAM ELEC page, integrity test, inspection of circuits and equipment, opening and closing of circuit breakers with circuits de-energized
• 24-20-00 AC Generation: main-component and spare-fuse locations; AC main-generation maintenance condition; APU oil-consumption data for GTCP 36-300, APS 3200 and 131-9(A); RAT manual-extension check, RAT control and reactivation
• 24-21-00 Integrated Drive Generator System (IDG, GCU): gearbox attachment, nacelle location, interface accessories, ELEC control panel, fuel-cooled IDG oil cooler and cables, speed-regulation loop, oil-system and internal schematics, drive control and indicating, IDG oil low-pressure / overheat advisory / overheat and disconnect ECAM pages; preservation/storage; servicing after oil chemical contamination and with DPI extended; drain, discard filter and replenish; oil-type change; disconnect/reconnect tests engine static and in operation; frequency system test (P/N 766219); governor adjustment screw; filter-element inspection and oil-leak visual check
• 24-21-15 / 24-21-41 / 24-21-42 / 24-21-43 / 24-21-49 / 24-21-51: IDG oil-temperature thermocouple; QAD adapter removal/installation and tension-bolt torque check; fuel-cooled oil-cooler R&I and cleaning; IDG cables; cooler-oil tubing R&I and general check; IDG 1(2) removal/installation; oil-filter R&I; oil-level and DPI checks
• 24-22-00 AC Main Generation: component locations, normal-configuration schematics, zone of protection, EGIU schematic, flip-flop and SDAC communication, current-transformer block diagrams, Channel 1 schematic, GLC/BTC logic, GLC-1 and BTC supplies, GEN FAULT/OFF and AC BUS FAULT ECAM pages, smoke detection; GLC-1 opening in the smoke procedure and transfer-inhibition tests; AC current transformers, TDC AC sensors, EGIU, GCU, lightning-protection modules and contactors
• 24-23-00 AC Auxiliary Generation: APU generator configuration, current transformers, auxiliary-generation and APU GLC schematics, APU GEN FAULT ECAM; deactivation by substitution kit or quill-shaft removal and reactivation; APU GCU, APU generator 8XS (including minilift hoist) and APU GLC
• 24-24-00 AC Emergency Generation: component locations, emergency generating and switching schematics, EMER & AC ESS contactor logic, RAT extension and CSM/G control logic, GCU EMER MCDU test, emergency and smoke ECAM configurations, available functions in emergency configuration; operational tests of the emergency generation system and GCU from CFDS; CSM/G control unit, CSM/G 8XE, EMER GLC and AC ESS BUS contactors
• 24-25-00 AC Essential Generation Switching: loss-of-AC-BUS-1XP logic, operational test, AC essential bus switching contactor
• 24-26-00 / 24-27-00 / 24-28-00: galley supply control and overload ECAM; AC generation monitoring and indicating; GEN FAULT and automatic galley-shedding tests; static inverter schematic, operational tests from external power or APU, inverter and inverter-contactor R&I
• 24-30-00 / 24-32-00 / 24-34-00 / 24-35-00 DC generation family: TR1/TR2 loss diagrams, CFDS architecture with TRs and BCLs, battery charging cycle on the operative BCL, TR2 deactivation/reactivation, emergency generation with one normal TR failed; TR component description, contactor logic, TR fault ECAM and TR reset; DC generation switching test; essential TR and contactors; DC NORM BUS and DC ESS BUS supply logic
• 24-37-00 / 24-38-00 Batteries and indicating: battery and shunt locations, BCL cockpit schematics, BAT 1/2 FAULT ECAM, BCL operational tests with and without CFDS, visual battery inspection, BCL/battery/shunt/line-contactor R&I, batteries 1 and 2 removal for restoration
• 24-40-00 / 24-41-00 / 24-42-00 / 24-43-00 External and ground-service power: GPCU locations and schematics, EPC supply, Class 3 fault reading on MCDU, energize/de-energize from EXT PWR, APU or engine 1(2), receptacle inspection, GPCU CFDS check, receptacle and EPC R&I; AC and DC ground-service bus control, energize/de-energize of the ground-service network
• 24-50-00 through 24-56-00 AC load distribution: normal-flight, emergency and smoke configurations for the whole AC/DC network; C/B provisions on panels 49VU, 105/106VU, 121–125VU, 2000VU and 2001VU; galley-supply deactivation/reactivation; commercial-load shedding test; 115/26 VAC autotransformers; AC service and shed-essential contactors; galley power-supply schematics and panel-200VU contactors
• 24-60-00 / 24-61-00 / 24-62-00 / 24-67-00 DC load distribution: DC EMER CONFIG, CSM/G and landing-gear-extended supply pages; DC BUS 1/2, combined BUS and BAT BUS FAULT ECAM; DC service and shed-bus contactors and bus-1/bus-2 contactor modules; DC ESS BUS FAULT and SHED pages; refueling on battery schematic and refuel/defuel panel location
• 24-92-00 Electrical routing: IDG feeder removal/installation on pylon and wing; conduit end-fitting inspections from wing leading/trailing edges, wing tip, air-conditioning compartment, vertical and horizontal stabilizer, flap-track fairing, MLG well, dry bay and fuselage tail; harness GVI and detailed EWIS inspections in avionics bays, passenger and cargo compartments, fuel tank, vent surge tank, pylons, keel beam and bulk cargo; bonding-lead inspection on movable surfaces; loop-tester connector tightness check; EWIS cleaning tasks when contaminated

Taken together, the chapter gives a line technician the description-and-operation baseline, the ECAM electrical pages, the R&I and servicing tasks for generators, coolers, filters, contactors, TRs, batteries and the GPCU, plus the EWIS inspection map that occupies the last several hundred pages. Configuration notes keep the reader on the correct schematic when an aircraft falls in the 003-004 versus 005-099 group.

IDG Servicing, Tests and Hardware Tasks

Practices inside 24-21 go well beyond theory. Oil chemical-contamination servicing covers both the standard case and the case with the oil-filter Differential Pressure Indicator extended. Drain-and-replenish, filter discard, oil-type change and filter-element inspection are written as stand-alone tasks. Disconnect and reconnect (reset) is tested with the engine static and with the engine running. A frequency system test is listed for IDG P/N 766219, and a governor adjustment-screw figure supports that test. Visual leak checks distinguish engine-static inspection from the general oil-leak and electrical-circuit check. QAD adapter tension-bolt torque, thermocouple R&I, cooler cleaning, cooler-oil tubing torque values (examples printed in the tubing task include 85–105 lbf.in on cooler bolts and several hundred lbf.in on IDG inlet/outlet tubes) and oil-level/DPI checks sit next to the generator R&I for IDG 1(2).

APU-side work includes flight without an APU generator installed (substitution kit), quill-shaft removal, safety-cable handling and hoist-assisted generator R&I. Emergency-side work includes CSM/G control-unit and 8XE generator R&I, EMER GLC and AC ESS BUS contactors, and an operational test of the emergency generation system plus a CFDS test of the emergency GCU. Lightning-protection modules have both R&I and an inspection/check task.

Monitoring, Fault Pages and Ground Power

ECAM coverage is extensive: IDG oil low pressure, overheat advisory, overheat and disconnect; GEN 1 FAULT, GEN 1/2 OFF, AC BUS 1/2 FAULT, APU GEN FAULT; electrical emergency configuration during RAT deployment and with landing gear extended; ESS BUSES ON BAT; smoke detection and electrical smoke configuration; TR1 fault; BAT 1/2 FAULT; DC BUS and DC ESS/SHED pages; galley overload. Integrity testing of electrical power walks through circuit-breaker actions on panels such as 122VU, 123VU and 125VU and records expected TR voltage in the 29–31 V band after breaker reset. External-power practices tell the reader how to energize or de-energize the aircraft from the receptacle, from the APU or from engine 1(2), how to inspect the receptacle, and how to interrogate the GPCU through CFDS.

What This Chapter Lets You Do

Use the Airbus A318 A319 A320 A321 Chapter 24 Electrical Power Aircraft Maintenance Manual AES Rev 40 (2012) to locate IDG, GCU, EGIU, GPCU, TR, BCL, CSM/G, static inverter, contactors and feeders by FIN, panel and zone; to service and replace the IDG oil system and QAD hardware; to test GLC opening in the smoke procedure, transfer inhibition, emergency generation, DC switching, galley shedding and BCL charge cycles; and to inspect or clean EWIS routes from the pylons through the fuel tanks, avionics bays and cabin overheads. Following the printed torque figures, oil-servicing steps, contactor logic and ECAM expected results keeps generation and distribution work aligned with this AES Rev 40 issue. The file is delivered as an instant PDF after payment—no shipping—so it can be opened on a laptop, tablet or workshop PC and printed for the job card in the hangar.