a330 Emergency Electrical Configuration

Cargo smoke detectors CVR HF1 Cargo vent All MCDU All FMGC

A330 EMERGENCY ELECTRICAL CONFIGURATION 3 LEVELS - emergency generator running with source: green hydraulic system - emergency generator running with source: RAT hydraulic power  - batteries only (emergency generator not running)

CHECKLIST MANAGEMENT Since the ECAM SD (lower screen) is lost the checklist has to completed using the EWD (upper screen); this ECP control panel switching to bring up different displays.

EMERGENCY ELECTRICAL GENERATOR Comes online when both AC buses are lost due to double engine failure and APU (gen) not running or due to major electrical fault (eg. Short circuit ON AC bus 1 & 2). Note that the APU is unlikely to restore power to both main AC buses if  the latter is the case (-buses, themselves faulty). The emergen is driven by the green hydraulic system if it is available. Otherwise driven by the RAT – which deploys in the case of a double engine failure. The emergen is a 115/200 Volt, 3-phase generator with 8.6 kVA capacity (only 3.5 kVA if powered by the RAT and below 260 kts IAS – further  load-shedding occurs). occurs). Note the main engine generators are 115 kVA.

LAND RECOVERY SWITCH ON Reconnects certain AC and DC busbars ( AC LAND RECOVERY and DC LAND RECOVERY) RECOVERY) which were shed when the emergency electrical generator started. This results in shedding some equipment now not useful and connecting equipment which relates to the approach and landing. SYSTEMS WHICH ARE SHED WITH LAND RECOVERY ON - HF 1 - AP 1 - ADR 3 - the remaining fuel pump (L PUMP 2 or R PUMP 2) - flaps are lost if engine 2 has failed and IDG 1 has failed. - no autobrake (as only 1 PRIM is available) - radar  - APU aft fuel pump

The emergen feeds the: AC ESSENTIAL BUS and DC ESSENTIAL BUS plus, if powered by the green hydraulic system, the: AC ESS SHED BUS and DC ESS SHED BUS is also powered. The emergen cannot be manually switched off. The aircraft automatically disconnects it on final approach when the slats are out of UP. Activation of the emergen is a major emergency and a mayday is required. The ECAM displays LAND ASAP in RED. Prolonged flight in the emergency electrical configuration is not recommended. Though neither is rushing a landing, especially in marginal weather.

SYSTEMS WHICH COME ONLINE WITH LAND RECOVERY ON - SFCC (slats only) (slat/flaps slow) - LGCIU 1 - ILS 1 The landing gear is manually extended (gravity drop) so that there is no spurious load on the green hydraulic system (which may cause the emergen to trip off). The gear doors remain open. The landing cannot be retracted. The flight law is DIRECT LAW. The landing is in FLAP3 w ith a 5 kt increment. A small increment in landing distance. Engine anti-ice is on regardless of cockpit switch position – a fuel flow increase of 1.5% applies. The landing is with pedal braking and no antiskid.

LOST SYSTEMS WITH EMERGEN RUNNINNG F/CTRL = ALT LAW PRIM 2 + 3 (remaining is PRIM 1, SEC 1 and SEC 2) RA 1 + 2 AP 2 VHF 2 + 3 Half spoilers Reversers ADR 2 CAT 2 R rain repellent DME 2 VOR 2 (VOR 1 and ADF 1 are only on the DDRMI) GPS 2 RMP 2 ADF 2 ATC 2 Selcal RADAR 2 PFD 2 ND 2 R FMGC R MCDU Lower ECAM screen Pitch trim Rudder trim R windshield anti-ice R landing light Manual pressurisation control Nosewheel steering Most fuel pumps IR 2 only runs for 5 more minutes The AP drops out but AP 1 may be re-engaged FD’s may or may not be available.

In addition, when the emergen is powered by the green hydraulic system (not the RAT) the following systems come online: - BSCU 1 - WHC - Left landing light - Left windshield anti-ice - the flight control system is in DIRECT LAW when the landing gear extends The landing is with pedal braking with antiskid - ANYTIME: When the emergen is powered by the RAT only there is: No AP No pitch trim No rudder trim A right roll tendency due to the R outboard aileron floating up. At slat extension the emergen disconnects and the landing is completed on batteries – so getting on the ground is a priority. This leaves the RAT to hydraulically power the flight controls only. The emergen cannot be reactivated after this disconnection except by: * on the ground after engines shutdown * in flight after slat retraction and then pressing the MAN ON switch (ie. after a go-round).

The captain has to be pilot flying (no instruments on the F/O’s side). Flying the aircraft is a full time task. ENGINE ANTI-ICE COMES ON AND STAYS ON

The standby airspeed probe is not heated so if there is discrepancy between it and the C aptain’s airspeed – use PFD 1 airspeed.

If the emergen is powered by the RAT only then the following systems are also lost:Wing anti-ice WHC 1 CAPT AOA & STBY AOA ND1 Autobrake and anti-skid L landing light All DME, all ATC and all radar  Standby altimeter  FCMC FCDC 1

AC POWER RESTORATION In the unlikely event that main AC power is restored, the emergen will continue to run. The LAND RECOVERY switch must still be selected on to restore the shed AC and DC busbars which were lost when the emergen first started. QRH SUMMARY The SUMMARY of affected systems is available in the QRH. Page 1.01 and 1.02 Basically the pilot puts the gear` down and runs the slats then lands.

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