Standard 1 42 – INTEGRATED MODULAR AVIONICS 19 ATA 44 – CABIN SYSTEMS 20 ATA 46 – INFORMATION SYSTEM 20 ATA 49 – APU 20 ATA 52 – DOOR 20 ATA 70 RR– POWERPLANT 20 ATA 70

AIRBUS A380 Standard 1.1 Malfunctions definition

LA_STD1.1_Malfunction_def_V1.1.doc February 5th, 2009 Page: 1 / 308

AIRBUS STANDARD A380 TRAINING DEVICE

M a l f u n c t i o n s D e s c r i p t i o n

S tandard 1 .1



1. TABLE OF CONTENT

1. TABLE OF CONTENT 2 2. SUMMARY 9 3. DOCUMENTATION MODIFICATION LIST 10 4. MALFUNCTIONS LIST 13

INTRODUCTION 13 ATA 21 – AIR COND / PRESS / VENT 14 ATA 22 – AUTO FLIGHT 14 ATA 23 – COMMUNICATIONS 14 ATA 24 – ELECTRICAL 15 ATA 26 – FIRE PROTECTION 15 ATA 27 – FLIGHT CONTROLS 16 ATA 28 – FUEL 16 ATA 29 – HYDRAULIC 17 ATA 30 – ICE & RAIN PROTECTION 17 ATA 31 – INDICATING/RECORDING SYSTEM 17 ATA 32 – LANDING GEAR 17 ATA 34 – NAVIGATION 18 ATA 35 – OXYGEN 19 ATA 36 – PNEUMATIC 19 ATA 42 – INTEGRATED MODULAR AVIONICS 19 ATA 44 – CABIN SYSTEMS 20 ATA 46 – INFORMATION SYSTEM 20 ATA 49 – APU 20 ATA 52 – DOOR 20 ATA 70 RR– POWERPLANT 20 ATA 70 EA – POWERPLANT 21

5. MALFUNCTIONS DESCRIPTIONS 23 ATA 21 – AIR CONDITIONING 24

MALFUNCTION : AIR PACK OVERHEAT 1 (2) 24 MALFUNCTION : AIR PACK FAULT 1 (2) 25 MALFUNCTION : COND DUCT OVERHEAT CABIN 26

ATA 21 – PRESSURIZATION 27 MALFUNCTION : CAB PRESS SYS FAULT ALL 27 MALFUNCTION : CAB PRESS AUTO CTL FAULT 28 MALFUNCTION : CAB PRESS OUTFLOW VALVE CTL FAULT 1 29 MALFUNCTION : CAB PRESS LDG ELEVATION FAULT 30 MALFUNCTION : CAB PRESS EXCESS CAB ALT 31 MALFUNCTION : CAB PRESS DOOR LEAK (INC/DEC) 1L 32

ATA 21 – VENTILATION 33 MALFUNCTION : VENT AVIONICS EXTRACT FAULT 33 MALFUNCTION : VENT AVIONICS BLOWING FAULT 34 MALFUNCTION : VENT AVIONICS OVBD VALVE FAULT 35

ATA 21 – AIR ADVISORY 36 MALFUNCTION : CABIN ALTITUDE INC/DEC 36 MALFUNCTION : CABIN DIFF PRESS INC/DEC 37

ATA 22 – AUTO FLIGHT 38 MALFUNCTION : AUTO FLT AP OFF 1 (2) 38 MALFUNCTION : AUTO FLT ENG A/THR OFF 1 (4) 39 MALFUNCTION : AUTO FLT A/THR OFF / THRUST LOCKED 40



MALFUNCTION : AUTO FLT FD FAULT 41 MALFUNCTION : AUTO FLT FCU FAULT 1 (2) (1+2) 42 MALFUNCTION : AUTO FLT FM FAULT A(B)(C) 43 MALFUNCTION : MAP SHIFT SLOW (QUICK) 45

ATA 22 – LOW VIS OPS / AUTOLAND 46 MALFUNCTION : LOC BEAM EXCESS DRIFT 46 MALFUNCTION : NO FLARE 47 MALFUNCTION : LONG FLARE 48 MALFUNCTION : LAND CAPABILITY DOWNGRADED TO CAT II 49 MALFUNCTION : NO ALT MODE 50 MALFUNCTION : NO LAND MODE 51 MALFUNCTION : ROLLOUT FAULT 52

ATA 23 – COMMUNICATIONS 53 MALFUNCTION : RMP FAULT 1 (2) (3) 53 MALFUNCTION : ACR DOWNLINK STBY 54 MALFUNCTION : COM DATALINK FAULT 55 MALFUNCTION : COM HF DATALINK FAULT 1 (2) 56 MALFUNCTION : COM VHF DATALINK FAULT 3 57 MALFUNCTION : COM SATCOM DATALINK FAULT 58

ATA 24 – ELECTRICAL (AC) 59 MALFUNCTION : GEN FAULT (EXCITATION) 1(2)(3)(4) 59 MALFUNCTION : APU GEN FAULT (EXCITATION) A (B) 60 MALFUNCTION : GEN FAULT (VOLTAGE INC/DEC) 1 61 MALFUNCTION : GEN FAULT (FREQUENCY INC/DEC) 4 62 MALFUNCTION : DRIVE OIL DISCONNECT 4 63 MALFUNCTION : DRIVE OIL PRESS LO 1 64 MALFUNCTION : DRIVE OIL LEVEL LO 3 65 MALFUNCTION : AC BUS FAULT 1 66 MALFUNCTION : AC BUS FAULT 2 67 MALFUNCTION : AC BUS FAULT 3 68 MALFUNCTION : AC BUS FAULT 4 69 MALFUNCTION : AC BUS FAULT ESS 70 MALFUNCTION : RAT FAULT 71 MALFUNCTION : EXTERNAL POWER FAULT 1 72

ATA 24 – ELECTRICAL (DC) 73 MALFUNCTION : DC BUS FAULT 1 73 MALFUNCTION : DC BUS FAULT 2 74 MALFUNCTION : DC BUS FAULT ESS 75 MALFUNCTION : BAT FAULT 1 (2) (APU) 76 MALFUNCTION : TR FAULT 2B 77 MALFUNCTION : TR FAULT 1 78 MALFUNCTION : TR FAULT 2A 79 MALFUNCTION : STATIC INVERTER FAULT 80 MALFUNCTION : C/B TRIPPED 81 MALFUNCTION : EMER CONFIG 82

ATA 26 – FIRE PROTECTION 83 MALFUNCTION : ENG FIRE (EXTING - FIRST AGENT) ENG 1(2) 83 MALFUNCTION : ENG FIRE (EXTING - SECOND AGENT) ENG 2(4) 84 MALFUNCTION : ENG FIRE (UNEXTING) ENG 1(3)(4) 85 MALFUNCTION : APU FIRE (EXTINGUISHABLE) 86 MALFUNCTION : APU FIRE (UNEXTINGUISHABLE) 87 MALFUNCTION : MLG BAY FIRE 88

ATA 26 – SMOKE 89 MALFUNCTION : AIR CONDITIONING SMOKE 89 MALFUNCTION : SMOKE MAIN AVIONIC LEFT 90



MALFUNCTION : SMOKE CARGO SMOKE AFT 91 MALFUNCTION : SMOKE LAVATORY MAIN DECK 92 MALFUNCTION : SMOKE IN-FLIGHT ENTERTAINMENT CENTER 93

ATA 27 – FLIGHT CONTROLS - EFCS 94 MALFUNCTION : PRIM 1 FAULT 94 MALFUNCTION : PRIM 2 FAULT 95 MALFUNCTION : PRIM 3 FAULT 96 MALFUNCTION : SEC 1 FAULT 97 MALFUNCTION : SEC 2 FAULT 98 MALFUNCTION : SEC 3 FAULT 99 MALFUNCTION : GYROMETER FAULT 1, 2 or 3 gyro failed 100 MALFUNCTION : SIDESTICK FAULT L(R) 101 MALFUNCTION : SIDE STICK FALSE ELEC INPUT L(R) 102 MALFUNCTION : SIDE STICK REVERSED INPUT L(R) 103 MALFUNCTION : RUDDER PEDAL FAULT 104 MALFUNCTION : RUDDER TRIM RUNAWAY (LEFT) 105 MALFUNCTION : RUDDER TRIM FAULT 1 (2) 106 MALFUNCTION : RUDDER FAULT UPR (LOW) 107 MALFUNCTION : ALTERNATE LOW DEMO (PROT LOST) 108 MALFUNCTION : DIRECT LAW DEMO (PROT LOST) 109

ATA 27 – FLIGHT CONTROLS - SURFACES 110 MALFUNCTION : SPEED BRAKES FAULT 110 MALFUNCTION : AILERON FAULT L INR 111 MALFUNCTION : AILERON ACTUATOR FAULT L OUTBD 112 MALFUNCTION : AILERON FAULT (DOWN) R OUTR 113 MALFUNCTION : STABILIZER FAULT 114 MALFUNCTION : SINGLE ELEVATOR FAULT R OUTB 115 MALFUNCTION : ELEVATOR ACTUATOR FAULT R INBD 116 MALFUNCTION : SINGLE ELEVATOR FAULT (DOWN) L OUTB 117

ATA 27 – FLIGHT CONTROLS - SLATS + FLAPS 118 MALFUNCTION : SLATS SYS FAULT 1 (2) 118 MALFUNCTION : FLAPS SYS FAULT 1 (2) 119 MALFUNCTION : SLATS SYS FAULT / FLAPS SYS FAULT 120 MALFUNCTION : SLATS LOCKED (WTB) 121 MALFUNCTION : FLAPS LOCKED (WTB) 122

ATA 28 – FUEL PUMPS 123 MALFUNCTION : FEED TANK MAIN PUMP FAULT 1(2)(3)(4) 123 MALFUNCTION : FEED TANK MAIN + STBY PUMPS FAULT 1(2)(3)(4) 124 MALFUNCTION : WING FEED PUMPS FAULT L (R) 125 MALFUNCTION : INR TANK FWD+AFT PUMPS FAULT R 126 MALFUNCTION : MID TANK FWD+AFT PUMPS FAULT L 127 MALFUNCTION : OUTR TANK PUMP FAULT L (R) 128 MALFUNCTION : TRIM TANK PUMP FAULT L (R) 129

ATA 28 – FUEL TANKS 130 MALFUNCTION : OUTR TANK XFR FAULT L (R) 130 MALFUNCTION : ENG LP VALVE FAULT 1(2)(3)(4) 131 MALFUNCTION : WINGS NOT BALANCED / LEAK DETECTED 1(2)(3)(4) 132 MALFUNCTION : HIDDEN FUEL LEAK ENG 1(4) 133 MALFUNCTION : CROSSFEED VALVE FAULT 1 134 MALFUNCTION : JETTISON FAULT/ VLV NOT CLOSED 135 MALFUNCTION : FQDC FAULT 1 (2) 136 MALFUNCTION : FEED TANK TEMP HIGH 2(3) 137

ATA 28 – FUEL CG 138 MALFUNCTION : AFT CG GW & CG BKUP/FQMS DISAGREE 138

ATA 29 – HYDRAULIC 139



MALFUNCTION : RSVR LOW LEVEL (FLUID QTY INC/DEC) GREEN 139 MALFUNCTION : RSVR LOW LEVEL (FLUID QTY INC/DEC) YELLOW 140 MALFUNCTION : SYSTEM OVERHEAT GREEN (YELLOW) 141 MALFUNCTION : RSVR AIR PRESS LO GREEN (YELLOW) 142 MALFUNCTION : ENG PUMP PRESS LO GREEN A(B) 1(2) 143 MALFUNCTION : ENG PUMP A+B OVERHEAT YELLOW 3 144 MALFUNCTION : ELEC PUMP FAULT (LO PRESS) GREEN A (B) 145 MALFUNCTION : ELEC PUMP FAULT (OVHT) YELLOW A (B) 146 MALFUNCTION : ELEC PUMP FAULT (POWER SUPPLY) G(Y) A(B) 147 MALFUNCTION : HYDRAULIC SYSTEM MONITORING FAULT GREEN (YELLOW) 148

ATA 30 – ICE AND RAIN PROTECTION 149 MALFUNCTION : ICE DETECTION FAULT 149 MALFUNCTION : WING VALVE CLOSED L (R) 150 MALFUNCTION : WING VALVE PRESS LOW L (R) 151 MALFUNCTION : ENG VALVE CLOSED / OPEN 1(4) 152 MALFUNCTION : WINDSHIELDS HEATG FAULT (NO HEAT) L (R) 153

ATA 31 – INDICATING/RECORDING 154 MALFUNCTION : CAPT PFD CDS UNIT FAULT 154 MALFUNCTION : F/O ND CDS UNIT FAULT 155 MALFUNCTION : UPPER ECAM CDS UNIT FAULT 156 MALFUNCTION : MFD CDS UNIT FAULT CAPT (F/O) 157 MALFUNCTION : ECP INTEGRATED CTL PANEL FAULT 158 MALFUNCTION : CDS CURSOR CTL+ KEYBOARD FAULT CAPT (F/O) 159 MALFUNCTION : CDS KEYBOARD FAULT CAPT (F/O) 160

ATA 32 – LANDING GEAR 161 MALFUNCTION : L/G NOT LOCKED DOWN LEFT BLG 161 MALFUNCTION : L/G NOT LOCKED UP NOSE GEAR 162 MALFUNCTION : L/G RETRACTION FAULT 163 MALFUNCTION : L/G DOORS NOT CLOSED LEFT BG 164 MALFUNCTION : L/G LEVER LOCKED (DOWN POS) 165 MALFUNCTION : L/G CONTROL INDICATION SYS FAULT 1 (2) 166

ATA 32 – STEERING 167 MALFUNCTION : STEER B/W STEER FAULT 167 MALFUNCTION : STEER TILLER FAULT CAPT (F/O) 168 MALFUNCTION : STEER N/W SYS FAULT NORMAL (ALTN) 169

ATA 32 – BRAKES 170 MALFUNCTION : ANTI SKID FAULT 170 MALFUNCTION : AUTO BRK FAULT 171 MALFUNCTION : EMER BRK FAULT 172 MALFUNCTION : NORM BRK FAULT 173 MALFUNCTION : ALTN + EMER BRK FAULT 174 MALFUNCTION : ALTN BRK FAULT 175 MALFUNCTION : LOSS OF BRAKING 176

ATA 32 – WHEELS 177 MALFUNCTION : TIRE PRESS LO (WLG BURST ON GND) L(R) 177 MALFUNCTION : TIRE PRESS LO (BLG BURST ON GND) L 178 MALFUNCTION : TIRE PRESS LO (BURST 90 KT) NOSE 179

ATA 34 – NAVIGATION - ADIRS 180 MALFUNCTION : IR1 FAULT 180 MALFUNCTION : IR2 FAULT 181 MALFUNCTION : IR3 FAULT 182 MALFUNCTION : ADR1 FAULT 183 MALFUNCTION : ADR2 FAULT 184 MALFUNCTION : ADR 3 FAULT 185



MALFUNCTION : CAPT & F/O ATT DISAGREE (PITCH) 1 (2) 186 MALFUNCTION : CAPT & F/O ATT DISAGREE (BANK) 1 (2) 187 MALFUNCTION : CAPT & F/O HDG DISAGREE 1 (2) 188 MALFUNCTION : ADR FAULT (AIRSPEED CHANNEL) 1 (2) (3) 189

ATA 34 – RADIO - NAVIGATION 190 MALFUNCTION : ILS LOC TRANSMITTER FAULT 190 MALFUNCTION : ILS G/S TRANSMITTER FAULT 191 MALFUNCTION : LS FAULT (MMR FUNCTION) 1 (2) 192 MALFUNCTION : VOR FAULT (RECEIVER) 1 193 MALFUNCTION : GPS FAULT (MMR FUNCTION) 1(2) 194 MALFUNCTION : MMR FAULT (RECEIVER) 1(2) 195 MALFUNCTION : RA SYS FAULT A(B)(C) 196 MALFUNCTION : ISIS FAULT 1 (2) 197

ATA 34 – NAVIGATION - SURVEILLANCE 198 MALFUNCTION : TAWS FAULT 1(2) 198 MALFUNCTION : TCAS FAULT 1(2) 199 MALFUNCTION : PWS FAULT 1(2) 200 MALFUNCTION : WXR FAULT 1(2) 201

ATA 34 – NAVIGATION - SENSORS 202 MALFUNCTION : BLOCKED PITOT PROBE ADR 1(2)(3), STBY 202 MALFUNCTION : BLOCKED L(R) STATIC PROBES ADR 1(2)(3) STBY 203 MALFUNCTION : LEFT STATIC PROBE HEATING FAULT ADR 1 204 MALFUNCTION : MULTI FUNCTION PROBE HEATG FAULT ADR1 205 MALFUNCTION : SIDE SLIP ANGLE PROBE HEATING FAULT ADR1 206 MALFUNCTION : STBY STATIC PROBE HEATG FAULT ISIS 1+2 207 MALFUNCTION : STBY PITOT PROBE HEATG FAULT ISIS 1+2 208 MALFUNCTION : FM / GPS POSITION DISAGREE 209 MALFUNCTION : GPS PRIMARY LOST 210

ATA 34 – NAVIGATION - OANS 211 MALFUNCTION : AIRPORT NAV FAULT 211

ATA 35 – OXYGEN 212 MALFUNCTION : CKPT BOTTLE PRESS LO 212

ATA 36 – PNEUMATIC 213 MALFUNCTION : BLEED FAULT / HP BLEED VLV NOT OPEN 1(3) 213 MALFUNCTION : BLEED FAULT / BLEED NOT CLOSED 1(4) 214 MALFUNCTION : BLEED TEMP LO 1 215 MALFUNCTION : INR WING LEAK LEFT (RIGHT) 216 MALFUNCTION : APU BLEED FAULT 217

ATA 42 – INTEGRATED MODULAR AVIONICS 218 MALFUNCTION : AVNCS CPIOM-A FAULT (BLEED) 1 (ALL) 218 MALFUNCTION : AVNCS CPIOM-B FAULT (COND) 1 (ALL) 219 MALFUNCTION : AVNCS CPIOM-C FAULT (COCKPIT) 1 (2) 220 MALFUNCTION : AVNCS CPIOM-D1 FAULT (ATC) 221 MALFUNCTION : AVNCS CPIOM-D3 FAULT (ACR) 222

ATA 42 – IMA – DEMONSTRATION FAULTS 223 MALFUNCTION : CAB PRESS AUTO CTL FAULT / BACKUP MODE 1(ALL) 223 MALFUNCTION : COND ZONE TEMP REGUL FAULT 224 MALFUNCTION : F/CTL FCDC FAULT 1 (2) 225 MALFUNCTION : AUTO FLT FCU BACKUP FAULT 1 (2) 226 MALFUNCTION : ELEC NETWORK MANAGEMENT UNIT (ENMU) FAULT 1 227 MALFUNCTION : FWS FAULT 1 (2) 228 MALFUNCTION : FUEL QUANTITY AND MANAGEMENT SYSTEM FAULT 1 (2) 229 MALFUNCTION : BRAKES SYS FAULT 1 (2) 230

ATA 44 – CABIN SYSTEMS 231



MALFUNCTION : CIDS CABIN COM FAULT 231 ATA 46 – INFORMATION SYSTEM 232

MALFUNCTION : COM OIS/AVNCS DATA XFR FAULT ALL 232 MALFUNCTION : OIS FAULT CAPT (F/O) 233

ATA 49 – APU 234 MALFUNCTION : APU FAULT (START/RUNNING) 234 MALFUNCTION : APU FAULT (N1 OVERSPEED) 235 MALFUNCTION : APU OIL QTY INC/DEC 236

ATA 52 - DOOR 237 MALFUNCTION : FWD CARGO DOOR NOT CLOSED 237 MALFUNCTION : MAIN SLIDE FAULT (NOT ARMED) 1L 238

ATA 70 RR – ENGINE FAILURES 239 MALFUNCTION : ENG FAIL (NO DAMAGE) ENG 1(2)(3)(4) 239 MALFUNCTION : ENG FAIL (DAMAGE) ENG 1(2)(3)(4) 240 MALFUNCTION : ENG FAIL (SERIOUS DAMAGE) ENG 1(2)(3)(4) 241 MALFUNCTION : BIRD INGESTION ENG 1(2)(3)(4) 242 MALFUNCTION : ENG STALL ENG 1(2)(3)(4) 243 MALFUNCTION : REVERSER LOCKED ENG 2 (3) 244 MALFUNCTION : REV UNLOCKED(DURING RETRACTION)-ON GROUND ENG 2(3) 245 MALFUNCTION : REV UNLOCKED ENG 2(3) 246 MALFUNCTION : REV INHIBITED ENG 2(3) 247 MALFUNCTION : REV FAULT ENG 2(3) 248

ATA 70 RR – ENGINE START 249 MALFUNCTION : START FAULT (ENG STALL) - HUNG START ENG 1(2) 249 MALFUNCTION : START FAULT (EGT OVER LIMIT) - HOT START ENG 3(4) 251 MALFUNCTION : IGN A+B FAULT ENG 1(2) 253 MALFUNCTION : START VLV FAULT (CLOSED/NOT CLOSED) ENG 1(2)(3)(4) 254 MALFUNCTION : ENG HP FUEL VALVE FAULT (HPV NOT OPEN / NOT CLOSED) ENG 3 (4) 255

ATA 70 RR – ENGINE CONTROLS 256 MALFUNCTION : FADEC FAULT ENG 1(4) 256 MALFUNCTION : NORM MODE FAULT – ALTN MODE ENG 2(3) 257 MALFUNCTION : EGT FAILED BLANKED ENG 1(2)(3)(4) 258

ATA 70 RR – ENGINE FLUIDS 259 MALFUNCTION : FUEL FILTER CLOGGED ENG 3 (4) 259 MALFUNCTION : OIL PRESS (INC/DEC) ENG 3 (4) 260 MALFUNCTION : OIL TEMP (INC/DEC) ENG 1(2) 261 MALFUNCTION : OIL FILTER CLOGGED ENG 2 262

ATA 70 RR – ENGINE PARAMETERS 263 MALFUNCTION : TURBINE OVHT ENG 1(2) 263 MALFUNCTION : EGT OVER LIMIT (INC/DEC) ENG 1(4) 264 MALFUNCTION : N1 OVER LIMIT (INC/DEC) ENG 3 265 MALFUNCTION : N2 OVER LIMIT (INC/DEC) ENG 4 267 MALFUNCTION : N3 OVER LIMIT (INC/DEC) ENG 4 269

ATA 70 RR – ENGINE ADVISORIES 271 MALFUNCTION : OIL QTY INC/DEC ENG 3(4) 271 MALFUNCTION : N1 VIBRATION INC/DEC ENG 1 272 MALFUNCTION : N2 VIBRATION INC/DEC ENG 4 273 MALFUNCTION : N3 VIBRATION INC/DEC ENG 4 274 MALFUNCTION : NAC TEMP INC/DEC ENG 4 275

ATA 70 EA – ENGINE FAILURES 276 MALFUNCTION : ENG FAIL (NO DAMAGE) ENG 1(2)(3)(4) 276 MALFUNCTION : ENG FAIL (DAMAGE) ENG 1(2)(3)(4) 277 MALFUNCTION : ENG FAIL (SERIOUS DAMAGE) ENG 1(2)(3)(4) 278



MALFUNCTION : BIRD INGESTION ENG 1(2)(3)(4) 279 MALFUNCTION : ENG STALL ENG 1(2)(3)(4) 280 MALFUNCTION : REVERSER LOCKED ENG 2 (3) 281 MALFUNCTION : REV UNLOCKED (DURING RETRACTION)-ON GROUND ENG 2(3) 282 MALFUNCTION : REV UNLOCKED ENG 2(3) 283 MALFUNCTION : REV INHIBITED ENG 2(3) 284 MALFUNCTION : REV FAULT ENG 2(3) 285

ATA 70 EA – ENGINE START 286 MALFUNCTION : START FAULT (ENG STALL) - HUNG START ENG 1(2) 286 MALFUNCTION : START FAULT (EGT OVER LIMIT) - HOT START ENG 3(4) 288 MALFUNCTION : IGN A+B FAULT ENG 1(2) 290 MALFUNCTION : START VLV FAULT (CLOSED/NOT CLOSED) ENG 1(2)(3)(4) 292 MALFUNCTION : ENG HP FUEL VALVE FAULT (HPV NOT OPEN / NOT CLOSED) ENG 3 (4) 293

ATA 70 EA – ENGINE CONTROLS 294 MALFUNCTION : FADEC FAULT ENG 1(4) 294

ATA 70 EA – ENGINE FLUIDS 295 MALFUNCTION : FUEL FILTER CLOGGED ENG 3 (4) 295 MALFUNCTION : OIL PRESS (INC/DEC) ENG 3 (4) 296 MALFUNCTION : OIL TEMP (INC/DEC) ENG 1(2) 297 MALFUNCTION : OIL FILTER CLOGGED ENG 2 298

ATA 70 EA – ENGINE PARAMETERS 299 MALFUNCTION : EGT OVER LIMIT (INC/DEC) ENG 1(4) 299 MALFUNCTION : N1 OVER LIMIT (INC/DEC) ENG 3 300 MALFUNCTION : N2 OVER LIMIT (INC/DEC) ENG 4 302

ATA 70 EA – ENGINE ADVISORIES 304 MALFUNCTION : OIL QTY INC/DEC ENG 3(4) 304 MALFUNCTION : N1 VIBRATION INC/DEC ENG 1 305 MALFUNCTION : N2 VIBRATION INC/DEC ENG 4 306 MALFUNCTION : NAC TEMP INC/DEC ENG 4 307



2. SUMMARY

1 - List of malfunctions Malfunctions are designated according to their FWC warning message, if applicable. A meaningful name has been determined for malfunctions without FWC message. Malfunctions are grouped in accordance with the FCOM/ECAM breakdown. For example all APU or ENG fires are in the ATA 26 chapter and not in ATA 49 or 70 chapters. 2 - Descriptions For each malfunction, the most common behavior is briefly summarized. All system specification and behavior are described within AIRBUS GO5 delivered Data Package. This document does not present a referenced design of A/C systems. Consequences of malfunctions associated with FWC warning message detailed on the Vol. 3 of the FCOM are not re-written in this document. 3 - Malfunction reset As mentioned in the A380 simulator specification, “When the malfunction is cancelled, the corresponding cause is cleared and each system that has been affected returns instantaneously to nominal operation as if malfunction was never selected, unless additional action is defined in the malfunction description document”. Cockpit mechanical controls (push-buttons, rotary selectors, handles, …) have to be manually reset, if their position was modified during malfunction exercise. 4 - Malfunction VALIDITY When VALIDITY field is not present at the end of the malfunction, the corresponding malfunction is valid for ALL Training Devices (Full Flight Simulators and M/FTD).



3. DOCUMENTATION MODIFICATION LIST

Date Rev Description ATA

15/08/08 V1.0 Document creation based on Std 1.0 document Modifications: - CAB PRESS EXCESS CAB ALT: note is added for EXCESS NEGATIVE

DIFF PRESS procedure - ROLLOUT FAULT: defined as per FCOM procedure - NO G/S MODE: GO5 DIR. - GND SPLRs FAULT: malfunction removed at AIRBUS Training policy request - TERR SYS FAULT replaced by TAWS SYS FAULT - IR 1, IR 2 and IR 3 FAULT updated - ADR 1, ADR 2 and ADR 3 FAULT updated - ADR FAULT (AIRSPEED CHANNEL) updated. ADR 3 is added - ADR FAULT (AIRSPEED CHANNEL) 3 removed - ILS LOC TRANSMITTER FAULT: updated - ILS G/S TRANSMITTER FAULT: updated - ILS FAULT (RECEIVER) 1(2) renamed LS FAULT (MMR FUNCTION) 1(2)

and updated (cause and description) - GPS FAULT (RECEIVER) 1(2) renamed GPS FAULT (MMR function) 1(2) - MMR FAULT (RECEIVER) 1(2): cause and description updated - RA SYS FAULT A(B)(C): updated - ISIS FAULT 1(2): updated - TCAS FAULT 1(2): cause and description updated - WXR FAULT 1(2) renamed PWS FAULT 1(2) and updated (cause and

description) - WXR RADAR FAULT 1(2) renamed WXR FAULT 1(2) and updated (cause

and description) - BLOCKED PITOT CAPT(F/O)(STBY) renamed BLOCKED PITOT PROBE

ADR 1(2)(3)(STBY) and updated (cause and description) - BLOCKED STATIC PROBES CAPT(F/O)(STBY) renamed BLOCKED L(R)

STATIC PROBES ADR 1(2)(3)(STBY) - ADR1 LEFT ISP (INTEGRATED STATIC PROBE) HEATER renamed LEFT

STATIC PROBE HEATING FAULT ADR 1 and updated (cause and description)

- ADR1 MFP (MULTI FUNCTION PROBE) HEATER renamed MULTI FUNCTION PROBE HEATG FAULT ADR1and updated (cause and description)

- ADR1 SSA (SIDE SLIP ANGLE) PROBE HEATER renamed SIDE SLIP ANGLE PROBE HEATING FAULT ADR1 and updated (cause and description)

- ISIS 1&2 ISP (INTEGRATED STATIC PROBE) HEATER renamed STBY STATIC PROBE HEATG FAULT ISIS 1+2 and updated (cause and description)

- ISIS 1&2 PITOT HEATER renamed STBY PITOT PROBE HEATG FAULT ISIS 1+2 and updated (cause and description)

- FM / GPS POSITION DISAGREE: cause updated - GPS PRIMARY LOST: updated - AIRPORT NAV FAULT: updated - All Engines malfunctions review (new EEC) - START FAULT (TIME EXCEEDED) ENG 1 removed

21

22 22 27 34 34 34 34 34 34 34 34

34 34 34 34 34 34

34

34

34

34

34

34

34

34

34 34 34 70 70

05/02/09 V1.1 Update

ROLLOUT FAULT Updated 22




LAND CAPABILITY DOWNGRADED Renamed LAND CAPABILITY DOWNGRADED TO CAT II Updated

22

APU GEN FAULT (EXCITATION) A (B) FWS generated if A/C alt below 23000ft 24

GEN FAULT (FREQUENCY INC/DEC) 4 Parameter min value set to 350Hz for automatic disconnection 24

AC BUS FAULT 1 Updated (AC ESS BUS and “after 3 sec” case removed) 24

EXTERNAL POWER FAULT 1 EXT 1 P/B light state added if EXT PWR 1 not in use 24

DRIVE OIL OVERHEAT 4 Renamed DRIVE OIL DISCONNECT 4 Wording DISC instead of Disc

24

DRIVE OIL LEVEL LO 3 FWS message updated 24

TR FAULT 1 In consequences, TR1 is displayed amber on SD (instead of TR1A) 24

SPD BRKS FAULT Renamed SPEED BRAKES FAULT 27

GYROMETER FAULT 1, 2 OR 3 GYRO FAILED FWS messages updated for two and three gyrometers failures 27

OUTR TANK XFR FAULT L(R) Cause: “valves” added FWS updated for right effects

28

FEED TANK MAIN + STBY PUMPS FAULT 1(2)(3)(4) Added MAIN pumps effects 28

OUTR TANK PUMP FAULT L (R) SD and FWS messages updated 28

NORM BRK FAULT Updated with “A/C on ground” condition 32

LOSS OF BRAKING Emergency braking available instead of alternate (A/SKID off) 32

STEER N/W SYS FAULT NORMAL (ALTN) Updated 32

LS FAULT (MMR FUNCTION) 1(2) LS display on PFD and ND updated 34

BLEED FAULT / HP BLEED VLV NOT OPEN 1(3) HPV stuck open: HP valve is displayed closed amber on SD 36

BLEED FAULT / BLEED NOT CLOSED 1(4) Updated condition for ENG BLEED NOT CLOSED 36

ELEC NETWORK MANAGEMENT UNIT (ENMU) FAULT 1 FWS message updated 42

ENG FAIL (SERIOUS DAMAGE) 1(4) ENG BIRD INGESTION 1(4) ENG STALL 1(4) Renamed 1(2)(3)(4) Malfunction shall be available for engines 2 and 3

70-RR

ENG FAIL (SERIOUS DAMAGE) 1(4) ENG STALL 1(4) Renamed 1(2)(3)(4) Malfunction shall be available for engines 2 and 3

70-EA




REMOVED MALFUNCTION: NO G/S MODE NO F-GS TRK MODE COM VHF DATALINK FAULT 3: available on VHF2 only

22 22 23



4. MALFUNCTIONS LIST

INTRODUCTION Malfunctions are listed here as they will be displayed on the simulator IOS. Each IOS page corresponds to an ATA chapter: 21, 22, 23, 24, … On a page, the malfunctions will be regrouped in separate areas according to sub-chapters: Pressurization, Air Conditioning, Ventilation, … Each line corresponds to a malfunction selection: SYS FAULT 1(2), LDG ELEVATION FAULT… Malfunctions are named according to the IOS title, which is either the ECAM message(s) that they trigger, or the event title: CAB DIFF PRESS INC/DEC Supplementary definition will be displayed next to the title of a malfunction in a different font and size. A sub-menu enables activation of the malfunction. It includes as many selection boxes as indicated in the Element column: 1, 2, …



ATA 21 – AIR COND / PRESS / VENT

IOS Title Sup. Def. Element Validity ATA 21- AIR COND

AIR PACK OVERHEAT 1 (2) AIR PACK FAULT 1 (2) COND DUCT OVEHHEAT CABIN

ATA 21- PRESS CAB PRESS SYS FAULT ALL CAB PRESS AUTO CTL FAULT CAB PRESS OUTFLOW VALVE CTL FAULT 1 CAB PRESS LDG ELEVATION FAULT

CAB PRESS EXCESS CAB ALT EXPLOSIVE DECOMPRESSION

CAB PRESS DOOR LEAK (INC/DEC) 1L ATA 21- VENT

VENT AVIONICS EXTRACT FAULT FAN VENT AVIONICS BLOWING FAULT SENSORS VENT AVIONICS OVBD VALVE FAULT

ATA 21- ADVISORIES CAB ALT INC/DEC CAB DIFF PRESS INC/DEC

ATA 22 – AUTO FLIGHT

IOS Title Sup. Def. Element Validity ATA 22 – AUTO FLT

AUTO FLT AP OFF 1 (2) AUTO FLT ENG A/THR OFF 1 (4) AUTO FLT A/THR OFF / THRUST LOCKED AUTO FLT FD FAULT AUTO FLT FCU FAULT 1(2)(1+2) AUTO FLT FM FAULT A(B)(C) MAP SHIFT SLOW (QUICK)

ATA 22 – LOW VIS OPS / AUTOLAND LOC BEAM EXCESS DRIFT NO FLARE LONG FLARE LAND CAPABILITY DOWNGRADED TO CAT II NO ALT MODE NO LAND MODE ROLLOUT FAULT

ATA 23 – COMMUNICATIONS

IOS Title Sup. Def. Element Validity RMP FAULT 1 (2)(3) ACR DOWNLINK STBY VHF, HF, SATCOM FFS COM DATALINK FAULT VHF, HF, SATCOM FFS



COM HF DATALINK FAULT 1 (2) FFS COM VHF DATALINK FAULT 3 FFS COM SATCOM DATALINK FAULT FFS

ATA 24 – ELECTRICAL

IOS Title Sup. Def. Element Validity ATA 24 – ELEC (AC)

GEN FAULT EXCITATION 1(2)(3)(4) APU GEN FAULT EXCITATION A (B) GEN FAULT VOLTAGE INC/DEC 1 GEN FAULT FREQUENCY INC/DEC 4 DRIVE OIL DISCONNECT 4 DRIVE OIL PRESS LO 1 DRIVE OIL LEVEL LO 3 AC BUS FAULT 1 AC BUS FAULT 2 AC BUS FAULT 3 AC BUS FAULT 4 AC BUS FAULT ESS RAT FAULT EXTERNAL POWER FAULT 1

ATA 24 – ELEC (DC) DC BUS FAULT 1 DC BUS FAULT 2 DC BUS FAULT ESS BAT FAULT 1 (2) (APU) TR FAULT 2B TR FAULT 1 TR FAULT 2A STATIC INVERTER FAULT C/B TRIPPED EMER CONFIG

ATA 26 – FIRE PROTECTION

IOS Title Sup. Def. Element Validity ATA 26 - FIRE

ENG FIRE EXTING - FIRST AGENT 1(2) ENG FIRE EXTING - SECOND AGENT 2(4) ENG FIRE UNEXTINGUISHABLE 1(3)(4) APU FIRE EXTINGUISHABLE APU FIRE UNEXTINGUISHABLE MLG BAY FIRE

ATA 26 - SMOKE AIR CONDITIONING SMOKE PACK FIRE – NO WARNING FFS SMOKE MAIN AVNCS SMOKE LEFT SMOKE CARGO SMOKE AFT SMOKE LAVATORY SMOKE MAIN DECK SMOKE IN-FLIGHT ENTERTAINMENT CENTER



ATA 27 – FLIGHT CONTROLS

IOS Title Sup. Def. Element Validity ATA 27 – F/CTL EFCS

PRIM FAULT DIRECT LAW (triple failure) 1 PRIM FAULT DIRECT LAW (triple failure) 2 PRIM FAULT DIRECT LAW (triple failure) 3 SEC FAULT 1 SEC FAULT 2 SEC FAULT 3

GYROMETER FAULT 1, 2 OR 3 GYRO FAILED

SIDE STICK FAULT L(R) FFS SIDE STICK FALSE ELEC INPUT L(R) FFS SIDE STICK REVERSED INPUT L(R) FFS RUDDER PEDAL FAULT PFTU FFS RUDDER TRIM RUNAWAY STUCK FULL LEFT FFS RUDDER TRIM FAULT 1 (2) FFS RUDDER FAULT UPR (LOW) FFS ALTERNATE LAW DEMO PROT LOST FFS DIRECT LAW DEMO PROT LOST FFS

ATA 27 – F/CTL SURFACES SPEED BRAKES FAULT AILERON FAULT L INR FFS AILERON ACTUATOR FAULT L OUTBD FFS AILERON FAULT DOWN R OUTR FFS STABILIZER FAULT FFS SINGLE ELEVATOR FAULT R OUTB FFS ELEVATOR ACTUATOR FAULT R INBD FFS SINGLE ELEVATOR FAULT DOWN L OUTB FFS

ATA 27 – F/CTL SLATS + FLAPS SLATS SYS FAULT 1 (2) FLAPS SYS FAULT 1 (2) SLATS SYS FAULT / FLAPS SYS FAULT SLATS LOCKED WTB FLAPS LOCKED WTB

ATA 28 – FUEL

IOS Title Sup. Def. Element Validity ATA 28 – FUEL PUMPS

FEED TANK MAIN PUMP FAULT 1(2)(3)(4) FEED TANK MAIN+STBY PUMPS FAULT 1(2)(3)(4) WING FEED PUMPS FAULT L (R) INR TANK FWD+AFT PUMPS FAULT R MID TANK FWD+AFT PUMPS FAULT L OUTR TANK PUMP FAULT L (R) TRIM TANK PUMP FAULT XFR L (R)

ATA 28 – FUEL TANKS OUTR TANK XFR FAULT L (R)



ENG LP VALVE FAULT 1(2)(3)(4) WINGS NOT BALANCED / LEAK DETECTED FEED TANK LEAK 1(2)(3)(4) HIDDEN FUEL LEAK ENG 1(4) CROSSFEED VALVE FAULT 1 JETTISON FAULT / VLV NOT CLOSED VALVE STUCK FQDC FAULT 1 (2) FEED TANK TEMP HIGH 2 (3)

ATA 28 – FUEL CG AFT CG GW & CG BKUP/ FQMS DISAGREE EXCESS AFT CG

ATA 29 – HYDRAULIC

IOS Title Sup. Def. Element Validity RSVR LOW LEVEL FLUID QTY INC/DEC G RSVR LOW LEVEL FLUID QTY INC/DEC Y SYSTEM OVERHEAT G (Y) RSVR AIR PRESS LO G (Y) ENG PUMP PRESS LO G A(B) 1(2) ENG PUMP A + B OVHT Y 3 ELEC PUMP FAULT LO PRESS G A(B) ELEC PUMP FAULT OVHT Y A(B) ELEC PUMP FAULT POWER SUPPLY G(Y) A(B) HYDRAULIC SYSTEM MONITORING FAULT G (Y)

ATA 30 – ICE & RAIN PROTECTION

IOS Title Sup. Def. Element Validity ICE DETECTION FAULT WING VALVE CLOSED VALVES STUCK L (R) WING VALVE PRESS LOW L (R) ENG VALVE CLOSED / OPEN 1 (4) WINDSHIELDS HEATG FAULT NO HEAT L (R)

ATA 31 – INDICATING/RECORDING SYSTEM

IOS Title Sup. Def. Element Validity ATA 31 - EIS

CAPT PFD CDS UNIT FAULT F/O ND CDS UNIT FAULT UPPER ECAM CDS UNIT FAULT MFD CDS UNIT FAULT CAPT (F/O) ECP INTEGRATED CTL PANEL FAULT CDS CURSOR CTL + KEYBOARD FAULT CAPT (F/O) CDS KEYBOARD FAULT CAPT (F/O)

ATA 32 – LANDING GEAR

IOS Title Sup. Def. Element Validity



ATA 32 – LANDING GEAR L/G NOT LOCKED DOWN L BLG L/G NOT LOCKED UP NOSE L/G RETRACTION FAULT L/G DOORS NOT CLOSED LEFT BG L/G LEVER LOCKED (DOWN POS) L/G CONTROL INDICATION SYS FAULT 1 (2)

ATA 32 – STEERING STEER B/W STEER FAULT STEER TILLER FAULT CAPT (F/O) STEER N/W SYS FAULT NORM (ALTN)

ATA 32 – BRAKES ANTI SKID FAULT AUTO BRK FAULT EMER BRK FAULT NORM BRK FAULT ALTN + EMER BRK FAULT ALTN BRK FAULT LOSS OF BRAKING NO WARNING

ATA 32 – WHEEL TIRE PRESS LO WLG BURST ON GND L (R) TIRE PRESS LO BLG BURST ON GND L TIRE PRESS LO BURST 90 KT NOSE

ATA 34 – NAVIGATION

IOS Title Sup. Def. Element Validity ATA 34 – ADIRS

IR1 FAULT IR2 FAULT IR3 FAULT ADR1 FAULT ADR2 FAULT ADR3 FAULT CAPT & F/O ATT DISAGREE PITCH 1 (2) CAPT & F/O ATT DISAGREE BANK 1 (2) CAPT & F/O HDG DISAGREE 1 (2) ADR FAULT AIRSPEED CHANNEL 1 (2) ADR FAULT AIRSPEED CHANNEL 3

ATA 34 – RAD NAV ILS LOC TRANSMITTER FAULT ILS G/S TRANSMITTER FAULT LS FAULT MMR FUNCTION 1 (2) VOR FAULT RECEIVER 1 GPS FAULT MMR FUNCTION 1 (2) MMR FAULT RECEIVER 1 (2) RA SYS FAULT A (B) (C) ISIS FAULT 1(2)

ATA 34 – NAVIGATION SURVEILLANCE TAWS FAULT 1 (2) TCAS FAULT 1 (2)



PWS FAULT 1 (2) WX FAULT 1 (2) FFS

ATA 34 – NAVIGATION SENSORS

BLOCKED PITOT PROBE ADR 1(2)(3)(STBY)

BLOCKED STATIC PROBES L(R) ADR

1(2)(3)(STBY)

LEFT STATIC PROBE HEATING FAULT ADR 1 MULTI FUNCTION PROBE HEATG FAULT ADR 1 SIDE SLIP ANGLE PROBE HEATING FAULT ADR 1 STBY STATIC PROBE HEATG FAULT ISIS 1+2 STBY PITOT PROBE HEATG FAULT ISIS 1+2 FM/GPS POSITION DISAGREE GPS PRIMARY LOST

ATA 34 – NAVIGATION OANS AIRPORT NAV FAULT FFS

ATA 35 – OXYGEN

IOS Title Sup. Def. Element Validity CKPT BOTTLE PRESS LO LEAK

ATA 36 – PNEUMATIC

IOS Title Sup. Def. Element Validity ATA 36 – AIR

BLEED FAULT / HP BLEED VLV NOT OPEN HP VALVE STUCK 1(3) BLEED FAULT / BLEED NOT CLOSED PR VALVE OPEN 1(4) BLEED TEMP LO 1 INR WING LEAK L (R) APU BLEED FAULT VALVE STUCK CLOSED

ATA 42 – INTEGRATED MODULAR AVIONICS

IOS Title Sup. Def. Element Validity ATA 42 – INTEGRATED MODULAR AVIONICS

AVNCS CPIOM-A FAULT BLEED 1(ALL) FFS AVNCS CPIOM-B FAULT COND 1(ALL) FFS AVNCS CPIOM-C FAULT COCKPIT 1(2) FFS AVNCS CPIOM-D1 FAULT ATC FFS AVNCS CPIOM-D3 FAULT ACR FFS

ATA 42 – IMA - DEMONSTRATION FAULTS CAB PRESS AUTO CTL FAULT/BACKUP MODE 1(ALL) FFS COND ZONE TEMP REGUL FAULT FFS F/CTL FCDC FAULT 1(2) FFS AUTO FLT FCU BACKUP FAULT 1(2) FFS ELEC NETWORK MANAGEMENT UNIT FAULT 1 FFS FWS FAULT 1(2) FFS FUEL QUANTITY MANAGEMENT SYS FAULT 1(2) FFS BRAKES SYS FAULT 1(2) FFS



ATA 44 – CABIN SYSTEMS

IOS Title Sup. Def. Element Validity CIDS CABIN COM FAULT UPR DECK

ATA 46 – INFORMATION SYSTEM

IOS Title Sup. Def. Element Validity COM OIS/AVNCS DATA XFR FAULT ALL FFS OIS FAULT CPT (F/O) FFS

ATA 49 – APU

IOS Title Sup. Def. Element Validity APU FAULT START / RUNNING APU FAULT N1 OVERSPEED APU OIL QTY INC/DEC

ATA 52 – DOOR

IOS Title Sup. Def. Element Validity FWD DOOR CARGO NOT CLOSED SWITCH FAULT FWD MAIN SLIDE FAULT NOT ARMED (switch) 1L

ATA 70 RR– POWERPLANT

IOS Title Sup. Def. Element Validity ATA 70 RR– ENGINE FAILURES

ENG FAIL NO DAMAGE ENG 1(2)(3)(4) ENG FAIL DAMAGE ENG 1(2)(3)(4) ENG FAIL SERIOUS DAMAGE ENG 1(2)(3)(4) BIRD INGESTION ENG 1(2)(3)(4) ENG STALL ENG 1(2)(3)(4) REVERSER LOCKED ENG 2(3) REV UNLOCKED - ON GROUND DURING RETRACTION ENG 2(3) REV UNLOCKED ENG 2(3)

ATA 70 RR– ENGINE START START FAULT TIME EXCEEDED ENG 1 START FAULT – HUNG START ENG STALL ENG 1(2) START FAULT – HOT START EGT OVER LIMIT ENG 3(4) IGN A+B FAULT ENG 1(2) START VLV FAULT CLOSED/NOT CLOSED ENG 1(2)(3)(4)

ENG HP FUEL VALVE FAULT HPV NOT OPEN / NOT CLOSED ENG 3(4)

ATA 70 RR – ENGINE CONTROLS FADEC FAULT ENG 1(4) NORM MODE FAULT – ALTN MODE ENG 2(3)

ATA 70 RR – ENGINE FLUIDS FUEL FILTER CLOGGED ENG 3(4)



OIL PRESS INC/DEC ENG 3(4) OIL TEMP INC/DEC ENG 1(2) OIL FILTER CLOGGED ENG 2

ATA 70 RR – ENG PARAMETERS TURBINE OVHT ENG 1(2) EGT OVER LIMIT INC/DEC ENG 1(4) N1 OVER LIMIT INC/DEC ENG 3 N2 OVER LIMIT INC/DEC ENG 4 N3 OVER LIMIT INC/DEC ENG 4

ATA 70 RR – ENG ADVISORIES OIL QTY INC/DEC ENG 3 (4) N1 VIBRATION INC/DEC ENG 1 N2 VIBRATION INC/DEC ENG 4 N3 VIBRATION INC/DEC ENG 4 NAC TEMP INC/DEC ENG 4

ATA 70 EA – POWERPLANT

IOS Title Sup. Def. Element Validity ATA 70 EA – ENGINE FAILURES

ENG FAIL NO DAMAGE ENG 1(2)(3)(4) ENG FAIL DAMAGE ENG 1(2)(3)(4) ENG FAIL SERIOUS DAMAGE ENG 1(2)(3)(4) ENG STALL ENG 1(2)(3)(4) REVERSER LOCKED ENG 2(3) REV UNLOCKED - ON GROUND DURING RETRACTION ENG 2(3) REV UNLOCKED ENG 2(3)

ATA 70 EA – ENGINE START START FAULT TIME EXCEEDED ENG 1 START FAULT – HUNG START ENG STALL ENG 1(2) START FAULT – HOT START EGT OVER LIMIT ENG 3(4) IGN A+B FAULT ENG 1(2) START VLV FAULT CLOSED/NOT CLOSED ENG 1(2)(3)(4)

ENG HP FUEL VALVE FAULT HPV NOT OPEN / NOT CLOSED ENG 3(4)

ATA 70 EA – ENGINE CONTROLS FADEC FAULT ENG 1(4)

ATA 70 EA – ENGINE FLUIDS FUEL FILTER CLOGGED ENG 3(4) OIL PRESS INC/DEC ENG 3(4) OIL TEMP INC/DEC ENG 1(2) OIL FILTER CLOGGED ENG 2

ATA 70 EA – ENG PARAMETERS EGT OVER LIMIT INC/DEC ENG 1(4) N1 OVER LIMIT INC/DEC ENG 3 N2 OVER LIMIT INC/DEC ENG 4

ATA 70 EA – ENG ADVISORIES OIL QTY INC/DEC ENG 3 (4) N1 VIBRATION INC/DEC ENG 1 N2 VIBRATION INC/DEC ENG 4



NAC TEMP INC/DEC ENG 4



5. MALFUNCTIONS DESCRIPTIONS



ATA 21 – AIR CONDITIONING

MALFUNCTION : AIR PACK OVERHEAT 1 (2) AIRCRAFT : A380 CAUSE : Pack compressor overheat detected by both sensors CONSEQUENCES:

• Pack 1 (2) discharge temperature increases,

10s after temperature reaches 88 deg C: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of PACK 1(2) P/B SW illuminates, • E/WD displays message: AIR PACK 1 (2) OVHT • SD displays BLEED page:

- Pack 1(2) discharge temperature is displayed in amber, - OVHT indication is displayed (in amber) while pack temperature is above 60°C

• During the ECAM procedure: After PACK 1 (2) P/B SW has been switched off:

FAULT light of the PACK 1(2) P/B SW remains illuminated while overheat condition is valid, OFF light of the PACK 1(2) P/B SW illuminates.

Canceling the malfunction restores normal pack operation.




MALFUNCTION : AIR PACK FAULT 1 (2) AIRCRAFT : A380 CAUSE : AGU Controller (FDAC) channel 1+2 fault CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of PACK 1(2) P/B SW illuminates, • E/WD displays message: AIR PACK 1 (2) FAULT • SD displays BLEED page.

- CTL indication is displayed in white - 1 and 2 indications are displayed in amber - FCV 1 and 2 (3 and 4) are displayed XX amber - FCV needles 1 and 2 (3 and 4) are displayed XX amber

Canceling the malfunction restores normal pack operation.




MALFUNCTION : COND DUCT OVERHEAT CABIN

AIRCRAFT : A380 CAUSE : Cabin Trim air valve full open order (trim air valve fails) CONSEQUENCES:

• Cabin duct temperature increases,

10 seconds after duct temperature reaches 80 deg C: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of the HOT AIR 1 P/B SW illuminates, • E/WD displays message: COND DUCT OVHT • SD displays COND page:

- Hot air 1 valve closes and is displayed in amber, - OVHT is displayed in amber in each affected cabin zone while overheat condition is valid,

• During the ECAM procedure: After HOT AIR 1 P/B SW has been switched off:

OFF light of the HOT AIR 1 P/B SW illuminates. FAULT light of the HOT AIR 1 P/B SW remains on.

Note: HOT AIR 1P/B Fault light goes off once the affected duct temp is < 70°C and the HOT AIR 1 P/B is switched on.

Canceling the malfunction restores normal air conditioning parameters.



ATA 21 – PRESSURIZATION

MALFUNCTION : CAB PRESS SYS FAULT ALL AIRCRAFT : A380 CAUSE : Outflow valve Control and Sensor Module 1 to 4 failure CONSEQUENCES:

• Single Chime sounds, • MASTER CAUTION lights illuminate, • E/WD displays message: CAB PRESS SYS FAULT • SD displays PRESS page.

- SYS 1, 2, 3, 4 indications are displayed in amber, - All outflow valves are displayed amber

Canceling the malfunction restores normal cabin pressure operation.




MALFUNCTION : CAB PRESS AUTO CTL FAULT AIRCRAFT : A380 CAUSE : Total loss of ambient pressure information from PRIMs CONSEQUENCES:

If aircraft is in flight phase 8: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: CAB PRESS AUTO CTL FAULT • SD displays CAB PRESS page

If a/c altitude is ABOVE 7500ft • CPCS automatically control the CABIN ALT to 7500ft

If a/c altitude is BELOW 7500ft • CPCS automatically control the CABIN V/S to AIRCRAFT V/S

Canceling the malfunction restores normal cabin pressure operation.




MALFUNCTION : CAB PRESS OUTFLOW VALVE CTL FAULT 1 AIRCRAFT : A380 CAUSE : Outflow valve flap mechanically stuck in current position CONSEQUENCES:

• Outflow valve 1 remains stuck in its current position, • Others outflow valves attempt to provide correct Cabin Pressure.

• E/WD displays message: CAB PRESS OUTFLW VLV CTL 1 FAULT • SD displays CAB PRESS page:

- Outflow valve 1 is displayed in amber,

Canceling the malfunction restores normal outflow valve operation and pressurization parameters according to flight conditions.




MALFUNCTION : CAB PRESS LDG ELEVATION FAULT AIRCRAFT : A380 CAUSE : Invalid landing elevation data from FMS CONSEQUENCES:

If the aircraft is in cruise (flight phase 8) and CABIN ALT push-button is in AUTO position: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: CAB PRESS LDG ELEVN FAULT • SD displays CAB PRESS page:

- Landing elevation data is replaced by XX amber.

Canceling the malfunction restores normal operation.




MALFUNCTION : CAB PRESS EXCESS CAB ALT AIRCRAFT : A380 CAUSE : Explosive decompression (window blown out) CONSEQUENCES:

• Sound effects take place.

If the aircraft is in cruise above 10000ft: • On SD CAB PRESS page:

- All outflow valves move to close, - Cabin vertical speed increases rapidly (display limit is reached: 6350 ft/min), - Delta press decreases, - Cabin altitude increases,

If cabin altitude reaches 9550 ft: • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: CAB PRESS EXCESS CAB ALT • SD displays CAB PRESS page

- Cabin altitude value is displayed in RED

Note: During an EMER DESCENT (required in EXCESS CAB ALT procedure), a CAB ALT EXCESS NEGATIVE DIFF PRESS can be obtained. This procedure shall be applied and then go back to EXCESS CAB ALT alert procedure)

Canceling the malfunction restores cabin altitude, Delta press and all pressurization parameters as a function of current aircraft altitude operation.




MALFUNCTION : CAB PRESS DOOR LEAK (INC/DEC) 1L AIRCRAFT : A380 CAUSE : Defective seal PARAMETER : min value max value

CAB V/S 500 ft/min 2500 ft/min CONSEQUENCES:

If aircraft is in flight: • On PRESS system page:

- Parameters V/S, CAB ALT increase and ΔP decrease, - All outflow valves close

- If V/S grows over 1800 AND is lower than 6350:

The V/S needle start pulsing in green (needle stop pulsing if V/S drops below 1600 ft/min),

When CAB ALT reaches 9550 ft: • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • EWD displays message: CAB PRESS EXCESS CAB ALT • SD displays CAB PRESS page.

Canceling the malfunction restores normal doors, cabin altitude, ΔP and all pressurization parameters as a function of current aircraft altitude operation.



ATA 21 – VENTILATION

MALFUNCTION : VENT AVIONICS EXTRACT FAULT AIRCRAFT : A380 CAUSE : Extract fan fails CONSEQUENCES:

After 40 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of the EXTRACT P/B illuminates, • E/WD displays message: VENT AVNCS EXTRACT FAULT • SD displays COND page,

- Extract fan symbol is displayed amber, - VENT is displayed amber

• If aircraft is on ground with engines 2 and 3 not running:

- The mechanic call horn sounds.

• During the ECAM procedure: After EXTRACT P/B SW has been switched to OVRD:

- OVRD light of the EXTRACT P/B SW illuminates, - If A/C is in flight, FAULT light of the EXTRACT P/B SW extinguishes, - The mechanic call horn stops (if applicable).

Canceling the malfunction restores normal ventilation operation.




MALFUNCTION : VENT AVIONICS BLOWING FAULT AIRCRAFT : A380 CAUSE : Both sensors fail CONSEQUENCES:

After 180 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: VENT AVNCS BLOWING FAULT • SD displays COND page

- VENT indication is displayed in amber, - Ducts L and R are amber





MALFUNCTION : VENT AVIONICS OVBD VALVE FAULT AIRCRAFT : A380 CAUSE : Overboard extract valve stuck in current position CONSEQUENCES:

If the overboard extract valve is stuck open and a closure demand occurs (ground engine start or a/c in flight), after 45 seconds:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of the EXTRACT P/B SW illuminates, • E/WD displays message: VENT AVNCS OVBD VLV FAULT • SD displays PRESS page:

- Overboard extract valve is open and displayed in amber. • During the ECAM procedure:

After VENT EXTRACT P/B SW has been switched to OVRD: OVRD light of the EXTRACT P/B SW illuminates, FAULT light of the EXTRACT P/B SW extinguishes.

If the overboard valve is stuck closed and VENT EXTRACT P/B SW is set to OVRD, after 45 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of the EXTRACT P/B SW illuminates, • E/WD displays message: VENT AVNCS OVBD VLV FAULT • SD displays PRESS page:

- Overboard extract valve is closed and displayed in amber.




ATA 21 – AIR ADVISORY

MALFUNCTION : CABIN ALTITUDE INC/DEC AIRCRAFT : A380 CAUSE : Wrong target altitude computation PARAMETER : min value max value rate

CAB ALT - 625 ft 12 000 ft 2000 ft/min CONSEQUENCES:

If the aircraft is in cruise above 10000ft:

If Cabin Altitude is below advisory level (8300ft): • Cabin Altitude indication and needle are green.

If Cabin Altitude advisory level is reached (8300ft to 9550 ft): • SD displays PRESS page:

- Cabin Altitude indication and needle pulse green on the SD after 5 seconds.

If Cabin Altitude warning level is reached (above 9.550 ft): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: CAB PRESS EXCESS CAB ALT • SD displays PRESS page:

- Cabin Altitude indication and needle are red.




ATA 21 – AIR ADVISORY

MALFUNCTION : CABIN DIFF PRESS INC/DEC AIRCRAFT : A380 CAUSE : Wrong CPC Automatic Control Partition (ACP) pressure sensor

information PARAMETER : min value max value rate ∆P (Diff Press) - 0.5 psi 9.2 psi 1.0 psi/min

CONSEQUENCES:

If the aircraft is in cruise above 10000ft: If Differential Pressure is below advisory level:

• ΔP value and needle are green. If Differential Pressure value is ΔP>8.91 psi:

• On SD CAB PRESS, ΔP value and needle are amber. When ΔP>8.99psi (or ΔP will soon exceed 8.99psi), then after 30s:

Single Chime sounds, MASTER CAUT lights illuminate, E/WD displays message: CAB PRESS DIFF PRESS HI SD displays CAB PRESS page:

- ΔP value and needle are amber.

Note: when ΔP is below 8.99psi, DIFF PRESS HI message remains set for at least 10s

Only during a fast a/c descent if Differential Pressure value is ΔP< -0.2 psi, then after 26s: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: CAB PRESS DIFF PRESS LO • SD displays CAB PRESS page:

- ΔP value and needle are amber

Note: DIFF PRESS LO is inhibited by EXCESS CAB ALT or EXCESS NEGATIVE DIFF PRESS alarm

In flight phase 9: If Differential Pressure advisory level is reached (1.5 psi < ΔP < 8.85 psi), then after 5 seconds:

• ΔP value pulses green on SD. When ΔP drops below 1.0 psi

• ΔP value stops pulsing green on SD.





MALFUNCTION : AUTO FLT AP OFF 1 (2) AIRCRAFT : A380 CAUSE : Detection of FCU AP p/b fault CONSEQUENCES:

If AP 1(2) was engaged and FCU-BACKUP was not engaged: • AP 1(2) disengages and cannot be engaged, • Cavalry Charge sound, • MASTER WARN lights flash, • E/WD displays message: AUTO FLT AP OFF

Canceling the malfunction restores normal AP operation. E/WD message remains until AP is engaged.




MALFUNCTION : AUTO FLT ENG A/THR OFF 1 (4) AIRCRAFT : A380 CAUSE : A/THR mode not available on Engine CONSEQUENCES:

SINGLE FAILURE

If A/THR was engaged: • A/THR disengages on ENG 1(4) but remains engaged and active on all other engines • Engine 1(4) thrust is frozen, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AUTO FLT ENG 1(4) A/THR OFF

DOUBLE FAILURE

If A/THR was engaged: • A/THR disengages on all engines and cannot be re-engaged, • All engines thrust is frozen, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AUTO FLT A/THR OFF

Every 5s ENG THRUST LOCKED

Canceling the malfunction restores normal A/THR system behavior. A/THR shall be manually reengaged if needed.




MALFUNCTION : AUTO FLT A/THR OFF / THRUST LOCKED AIRCRAFT : A380 CAUSE : Failure detected on the FCU ATHR push-button CONSEQUENCES:

If A/THR was engaged: • A/THR disengages, • Single Chime sounds, • MASTER CAUT lights illuminate, • Amber “THR LK” blinks on FMA, • E/WD displays message: AUTO FLT A/THR OFF

Every 5s ENG THRUST LOCKED

If A/THR was not engaged: • A/THR cannot be engaged

Canceling the malfunction restores normal A/THR system. A/THR OFF message remains until A/THR is engaged.




MALFUNCTION : AUTO FLT FD FAULT AIRCRAFT : A380 CAUSE : permanent FD P/B activation in input of PRIM. CONSEQUENCES:

If FD was engaged: • FD disengages.

If FD is disengaged: • FD cannot be engaged or re-engaged.

Canceling the malfunction restores normal FD operation.




MALFUNCTION : AUTO FLT FCU FAULT 1 (2) (1+2) AIRCRAFT : A380 CAUSE : internal channel PSU(s) fault. CONSEQUENCES:

If one channel is failed: • AP part of FCU remains controlled by opposite channel, • Associated EFIS/ND-CP blanks, • Associated EFIS/ND-CP controls are inoperative, • EFIS CTL BACKUP function on MFD is activated,, • E/WD displays message: CDS CAPT (F/O) EFIS CTL PNL FAULT

If both channels are failed: • All FCU displays and lights are blanked. • All FCU functions are lost, • EFIS CTL and FCU BACKUP on MFD are automatically activated, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AUTO FLT AFS CTL PNL FAULT

CDS CAPT+F/O EFIS CTL PNLS FAULT

Note: Due to constant FCU BACKUP function synchronization with real FCU, there is no AP or A/THR disconnection when switching to FCU BACKUP control.

Canceling the malfunction restores normal FCU operation. FCU is initialized as per its own reset logic.




MALFUNCTION : AUTO FLT FM FAULT A(B)(C) AIRCRAFT : A380 CAUSE : Loss of FMC A(B)(C) CONSEQUENCES: SINGLE FAILURE:

• The faulty FMC is replaced by the standby unit (automatic reconfiguration), • E/WD displays message: AUTO FLT FMC-A(B)(C) FAULT

If the faulty FMC was the Master FMC with related AP engaged in managed mode: • The managed mode of the AP disengages, • Triple click aural warning sounds, • New guidance modes are displayed on FMA, • Managed mode can be re-engaged.

DOUBLE FAILURE:

• The faulty FMC’s are replaced by the remaining unit in single mode operation (manual reconfiguration),

• Single Chime sounds, • MASTER CAUT lights illuminates, • E/WD displays messages according to FMC configuration: AUTO FLT FMS 1 (2) FAULT

• If FMS 1 FAULT: FMC A+C (A+B) (A) FAULT

• If FMS 2 FAULT:

FMC B+C (A+B) (B) FAULT

If one of the faulty FMC’s was the Master FMC with related AP engaged in managed mode: • The managed mode of the AP disengages, • Triple click aural warning sounds, • New guidance modes are displayed on FMA, • Managed mode can be re-engaged.

TRIPLE FAILURE:

• Single Chime sounds, • MASTER CAUT lights illuminates, • E/WD displays message: AUTO FLT FMS 1+2 FAULT

ALL FMCs FAULT

If the AP was engaged in managed mode: • The managed mode of the AP disengages,



• Triple click aural warning sounds, • New guidance modes are displayed on FMA, Managed mode cannot be re-engaged.

Canceling the malfunction restores FMC normal operation.




MALFUNCTION : MAP SHIFT SLOW (QUICK) AIRCRAFT : A380 CAUSE : Wrong internal FM position computation (IRS FM drift) CONSEQUENCES:

GPS primary must be lost before malfunction activation: • Slow (quick) map shift perpendicular to A/C track on both NDs, • IRS data displayed on MFD POSITION/IRS page are not altered and remain consistent with

aircraft real position, • At the same time, IRS FM is modified and consequently, the FM position is shifted with typical

values: 2 Nm/min, 10 Nm max (slow) 10 Nm/min, 10 Nm max (quick)

Canceling the malfunction restores instantaneously correct FM position.



ATA 22 – LOW VIS OPS / AUTOLAND

MALFUNCTION : LOC BEAM EXCESS DRIFT AIRCRAFT : A380 CAUSE : LOC deviation seen by PRIM1, 2, 3 from ILS1 and ILS2 has a

drift.

(Failure designed for specific training scenario) CONSEQUENCES:

When fault is activated above 200ft RA: • AP/FD drifts off the localizer beam.

If RA below 200 ft and above 15ft, as soon as LOC deviation exceeds an internal drift limit (0.020 DDM or 20µA):

• AUTOLAND WARNING lights illuminate on the CAPT and F/O glareshields, • If RA above 15ft, LOC scale and the associated indications flash on the CAPT and F/O PFD and

ND.

Canceling the malfunction restores normal LOC signal.




MALFUNCTION : NO FLARE AIRCRAFT : A380 CAUSE : Error in the radio height seen by PRIM1, 2, 3 from RA1, 2, and 3

(RA = true RA + 100 ft)


• The aircraft lands without flare phase (Align mode and retard cannot be engaged by PRIM), • There is no warning message or indication, • The FLARE mode is not annunciated on the FMA.





MALFUNCTION : LONG FLARE AIRCRAFT : A380 CAUSE : Error in the radio height seen by PRIM 1, 2, 3 from RA1, 2 and 3

(RA = true RA - 25 ft)


• FLARE phase duration is increased.





MALFUNCTION : LAND CAPABILITY DOWNGRADED TO CAT II AIRCRAFT : A380 CAUSE : Dual RA fault seen by all PRIM


During ILS CAT 3 SINGLE/DUAL approach: • Triple click aural warning sounds, • CAT 3 SINGLE/DUAL is lost, • CAT 2 appears on the FMA

Canceling the malfunction restores normal landing capabilities.




MALFUNCTION : NO ALT MODE AIRCRAFT : A380 CAUSE : erroneous ZBI from three ADIRS at PRIM input.


IF ALT mode was not armed: • ALT mode can be armed (ALT in cyan on the FMA) but A/C does not capture target altitude (FCU

selected altitude or altitude provided by FM).

IF ALT mode was armed (ALT in cyan on the FMA): • ALT remains armed but A/C does not capture target altitude (FCU selected altitude or altitude

provided by FM).

IF ALT*/ALT CRZ*/ALT CST* (capture phase of FCU selected altitude or altitude provided by FM) mode was engaged:

• ALT*/ ALT CRZ*/ALT CST* mode stays engaged and A/C does not capture altitude when reaching target altitude.

IF ALT mode was engaged: • ALT mode disengages. • AP/FD/ATHR disengages

Canceling the malfunction restores normal ALT engagement.

NOTE: available on FFS if PRIM software package simulation is fitted




MALFUNCTION : NO LAND MODE AIRCRAFT : A380 CAUSE : Radio altitude of radio altimeter 1 and 2 received by PRIM 1, 2, 3

always above 400 ft (only values transmitted to PRIM 1, 2, 3 are altered).

(Failure designed for specific training scenario)

CONSEQUENCES:

IF LAND mode was not engaged: • When A/C reaches 400fts, LAND mode does not engage (LAND green not displayed on FMA), • The aircraft lands without FLARE phase.

IF LAND mode was engaged: • LAND mode remains engaged, • The aircraft lands without FLARE phase.

Canceling the malfunction restores normal LAND mode engagement.




MALFUNCTION : ROLLOUT FAULT AIRCRAFT : A380 CAUSE : No wheel steering data at input of PRIM.


When fault is activated above 200ft RA: • Single Chime sounds, • MASTER CAUT lights illuminate, • EWD displays messages: AUTO FLT ROLL OUT FAULT Note: guidance is still active on ground.

Canceling the malfunction restores normal ROLLOUT mode engagement.




MALFUNCTION : RMP FAULT 1 (2) (3) AIRCRAFT : A380 CAUSE : RMP internal failure CONSEQUENCES:

If one RMP is failed: • The affected RMP screen is blanked, • The affected RMP keyboard is unusable, • There is no communication between the affected RMP and other A/C systems (RMP controls

switch to its OFF configuration). • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: COM RMP 1(2)(3) FAULT

If RMP 1 & 2, (1&3), (2&3) are failed: • The affected RMP screens are blanked, • The affected RMP keyboards are unusable, • There is no communication between the affected RMPs and other A/C systems (RMP controls

switch to its OFF configuration). • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: COM RMP 1+2 (1+3) (2+3) FAULT

If RMP 1, 2 & 3 are failed: • All RMP screens are blanked, • All RMP keyboards are unusable, • There is no communication between the RMPs and other A/C systems (RMP controls switch to its

OFF configuration). • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: COM RMP 1+2+3 FAULT

Canceling the malfunction restores normal RMP functions.




MALFUNCTION : ACR DOWNLINK STBY AIRCRAFT : A380 CAUSE : All VHF, HF, SATCOM units simultaneously switch to standby

mode CONSEQUENCES:

• Data radio links are no more alive. • All datalink controller within each transceiver switches to standby mode,, • Only voice communication mode remains available, • DATALINK STANDBY green memo is displayed.

Canceling the malfunction restores normal transceivers datalink functions. All connections are lost. VALIDITY: FFS




MALFUNCTION : COM DATALINK FAULT AIRCRAFT : A380 CAUSE : VHF, HF, SATCOM data not available from ACR side. CONSEQUENCES:

• All datalink communication functions are inhibited • E/WD displays message: COM DATALINK FAULT

VHF & HF & SATCOM DATA NOT AVAIL

Canceling the malfunction restores normal ACR behavior. All previously established connections are lost. VALIDITY: FFS




MALFUNCTION : COM HF DATALINK FAULT 1 (2) AIRCRAFT : A380 CAUSE : HF datalink internal module fails CONSEQUENCES:

• The affected HF is only capable of voice communication, • If the affected HF is being used by the ACR for datalink communication, the ACR shall switch to

another communication means. • E/WD displays message: COM HF 1(2) DATALINK FAULT

Canceling the malfunction restores normal HF datalink functions. VALIDITY: FFS




MALFUNCTION : COM VHF DATALINK FAULT 3 AIRCRAFT : A380 CAUSE : VHF datalink internal module fails CONSEQUENCES:

• The affected VHF is only capable of voice communication, • If the affected VHF is being used by the ACR for datalink communication, the ACR shall switch to

another communication means. • E/WD displays message: COM VHF 3 DATALINK FAULT

Canceling the malfunction restores normal VHF datalink functions. VALIDITY: FFS




MALFUNCTION : COM SATCOM DATALINK FAULT AIRCRAFT : A380 CAUSE : SATCOM datalink internal module fails CONSEQUENCES:

• The affected SATCOM is only capable of voice communication, • If the affected SATCOM is being used by the ACR for datalink communication, the ACR shall

switch to another communication means. • E/WD displays message: COM SATCOM DATALINK FAULT

Canceling the malfunction restores normal SATCOM datalink functions. VALIDITY: FFS



ATA 24 – ELECTRICAL (AC)

MALFUNCTION : GEN FAULT (EXCITATION) 1(2)(3)(4) AIRCRAFT : A380 CAUSE : Generator excitation circuit fails CONSEQUENCES:

If engine 1(2)(3)(4) is running: • Single Chime sounds, • MAST CAUT lights illuminate, • FAULT light of the affected GEN P/B SW illuminates, • E/WD displays message: ELEC GEN 1(2)(3)(4) FAULT • SD displays ELEC AC page,

- The voltage indication is displayed in amber and lower than the normal value • During the ECAM procedure:

After GEN 1(2)(3)(4) P/B SW has been switched off: - FAULT light of GEN P/B SW extinguishes, - OFF light of GEN P/B SW illuminates.

Canceling the malfunction restores normal electrical generation. System operates as per switch positions following ECAM actions.




MALFUNCTION : APU GEN FAULT (EXCITATION) A (B) AIRCRAFT : A380 CAUSE : APU generator excitation circuit fails CONSEQUENCES:

If APU is running: • Single Chime sounds, • MAST CAUT lights illuminate, • FAULT light of APU GEN P/B SW illuminates, • If A/C altitude is below 23000 feet

- E/WD displays message: ELEC APU GEN A (B) FAULT • SD displays ELEC AC page,

- The voltage indication is displayed in amber and lower than the normal value (0 volt displayed) • During the ECAM procedure:

- After APU GEN P/B SW has been switched off: - FAULT light of APU GEN P/B SW extinguishes, - OFF light of APU GEN P/B SW illuminates.

Canceling the malfunction restores normal electrical generation. System operates as per switch positions following ECAM actions.




MALFUNCTION : GEN FAULT (VOLTAGE INC/DEC) 1 AIRCRAFT : A380 CAUSE : Generator 1 excitation fails PARAMETER : min value max value rate

Generator 1 voltage 60 V 180 V 1 V/s CONSEQUENCES:

Over 130V • Single Chime sounds, • MAST CAUT lights illuminate, • FAULT light of GEN 1 P/B SW illuminates, • E/WD displays message: ELEC GEN 1 FAULT • SD displays ELEC AC page,

- On ELEC AC system page: - Generator 1 is disconnected from the network (generator control line open).

• During the ECAM procedure: - After GEN 1 P/B SW has been switched off:

- FAULT light of GEN 1 P/B SW extinguishes, - OFF light of GEN 1 P/B SW illuminates.

Canceling the malfunction restores normal voltage. System operates as per switch positions following ECAM actions.




MALFUNCTION : GEN FAULT (FREQUENCY INC/DEC) 4 AIRCRAFT : A380 CAUSE : Speed drive fails PARAMETER : min value max value

Gen 4 frequency 350 Hz 1000 Hz CONSEQUENCES:

Over 775Hz: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of GEN 4 P/B SW illuminates, • E/WD displays message: ELEC GEN 4 FAULT • SD displays ELEC AC page,

Generator 4 is disconnected from the network (generator control line open). • During the ECAM procedure:

After GEN P/B SW has been switched off: FAULT light of GEN P/B SW extinguishes, OFF light of GEN P/B SW illuminates.

Under 370Hz • No warning • Automatic disconnection

Canceling the malfunction restores normal frequency.




MALFUNCTION : DRIVE OIL DISCONNECT 4 AIRCRAFT : A380 CAUSE : Abnormal friction in gearbox CONSEQUENCES:

When, the DRIVE oil temperature is around 193(for EA) or 183 (for RR) deg C: • FAULT light of DRIVE P/B SW illuminates, • SD displays ELEC AC page,

- OVHT indication is displayed in amber, - DRIVE disconnects automatically.

After automatic disconnection:

- Single Chime sounds, - MASTER CAUT light illuminates, - DISC light of the drive P/B switch illuminates, - Fault light of GEN 4 P/B illuminates. - DISC is displayed in amber on ELEC AC page - EWD displays message: ELEC DRIVE 4 DISCONNECTED

Canceling the malfunction restores initial DRIVE oil temperature and DRIVE reconnect.




MALFUNCTION : DRIVE OIL PRESS LO 1 AIRCRAFT : A380 CAUSE : Oil low press switch fails CONSEQUENCES:

If engine is running: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of DRIVE P/B SW illuminates, • E/WD displays message: ELEC DRIVE 1 OIL PRESS LO • During the ECAM procedure:

After DRIVE P/B SW has been switched to disc: - FAULT light of GEN P/B SW illuminates, - DISC light of DRIVE P/B SW illuminates, - FAULT light of DRIVE P/B SW extinguishes, - On ELEC AC system page, DISC indication is displayed in amber.

If the procedure is not followed and the DRIVE oil pressure stays faulty for 5 min, then the disconnection will be done automatically.

Canceling the malfunction restores DRIVE oil temperature to normal value. ECAM warning message is reset in flight phase 1




MALFUNCTION : DRIVE OIL LEVEL LO 3 AIRCRAFT : A380 CAUSE : Oil low level CONSEQUENCES:

On ground, if engine is not running: • Single Chime sounds, • MASTER CAUT light illuminates. • E/WD displays message: ELEC DRIVE 3 OIL LEVEL LO

Canceling the malfunction restores normal DRIVE operation.




MALFUNCTION : AC BUS FAULT 1 AIRCRAFT : A380 CAUSE : Wiring between contactors GLC 1, BTC 1, EPC 1 and 100XP1 cut CONSEQUENCES:

• AC BUS 1 (100XP1) is lost, • FAULT light of AC ESS FEED P/B SW indicator illuminates, • On ELEC AC system page, AC 1 bus bar indication is displayed in amber, • The supply of AC ESS BUS (400XP) is switched automatically on AC BUS 4 (200XP4), • FAULT light of AC ESS FEED P/B SW indicator extinguishes.

After 2 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC AC BUS 1 FAULT • SD displays ELEC AC page.

- AC 1 bus bar indication is amber - AC 4 supplies AC ESS bus bar.

Canceling the malfunction restores normal electrical supply. System operates as per switch positions following ECAM actions.




MALFUNCTION : AC BUS FAULT 2 AIRCRAFT : A380 CAUSE : Wiring between contactors GLC 2, BTC 2, EPC 2, BTC 5 and

100XP2 cut CONSEQUENCES:

• AC BUS 2 (100XP2) is lost, • TR 1 is lost, • On ELEC AC system page, AC 2 bus bar indication is displayed in amber






MALFUNCTION : AC BUS FAULT 3 AIRCRAFT : A380 CAUSE : Wiring between contactors GLC 3, BTC 3, EPC 3, BTC 6 and

200XP3 cut CONSEQUENCES:

• AC BUS 3 (200XP3) is lost, • TR 2 is lost, • On ELEC AC system page, AC 3 bus bar indication is displayed in amber






MALFUNCTION : AC BUS FAULT 4 AIRCRAFT : A380 CAUSE : Wiring between contactors GLC 4, BTC 4, EPC 4 and 200XP4 cut CONSEQUENCES:

• AC BUS 4 (200XP4) is lost, • TR APU is lost, display in white • On ELEC AC system page, AC 4 bus bar indication is displayed in amber.






MALFUNCTION : AC BUS FAULT ESS AIRCRAFT : A380 CAUSE : Wire between contactor 3XC and AC ESS BUS cut CONSEQUENCES:

• AC ESS BUS (400XP) is lost, whatever the AC ESS FEED P/B SW position is, • ESS TR is lost, • FAULT light of AC ESS FEED P/B SW illuminates, • On ELEC AC system page, AC ESS and AC EMER bus bar indication are displayed in amber.

After 5 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC AC ESS BUS FAULT • SD displays ELEC AC page,





MALFUNCTION : RAT FAULT AIRCRAFT : A380 CAUSE : Automatic extension logic fail CONSEQUENCES:

If emergency conditions are present: • RAT fails to connect to AC ESS BUS, • Static inverter supplies AC ESS BUS, • During the ECAM procedure:

After MAN RAT PB S/W is pressed: The RAT supplies the AC ESS BUS after a delay, FAULT light of RAT P/B SW extinguishes,

Canceling the malfunction restores automatic extension logic And rat has to be stowed if manual extension has been done




MALFUNCTION : EXTERNAL POWER FAULT 1 AIRCRAFT : A380 CAUSE : Under-voltage (below 110 V) CONSEQUENCES:

If external power 1 is not in use: • Connection to AC BUS 1 (100XP1) is not possible, • EXT 1 P/B AVAIL light will be extinguished

If external power 1 is in use: • Connection between EXT PWR 1 and AC BUS 100XP1 is lost, • AC BUS 100XP1 is supplied by the remaining power source, according to priorities order definition. • E/WD displays message: ELEC EXT PWR 1 FAULT




ATA 24 – ELECTRICAL (DC)

MALFUNCTION : DC BUS FAULT 1 AIRCRAFT : A380 CAUSE : Wiring between contactors BLC 1, IBLC2, BATLC1 and 100PP cut CONSEQUENCES:

• DC BUS 100PP is lost. • On ELEC DC system page

- DC 1 bus bar is displayed in amber.

After 5 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC DC BUS 1 FAULT • SD displays ELEC DC page.





MALFUNCTION : DC BUS FAULT 2 AIRCRAFT : A380 CAUSE : Wiring between contactors BLC 2, IBLC2, TRLC2, BATLC2 and

200PP cut CONSEQUENCES:

• DC BUS 200PP is lost. • On ELEC DC system page

- DC 2 bus bar is displayed in amber, - TR 2A or TR 2B are displayed in amber.

After 5 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC DC BUS 2 FAULT • SD displays ELEC DC page.





MALFUNCTION : DC BUS FAULT ESS AIRCRAFT : A380 CAUSE : Wiring between contactors BLCESS, IBLC1, STAT.INV,

DSLC1,BATLCESS and 400PP cut CONSEQUENCES:

• DC BUS 400PP is lost, • On ELEC DC system page:

- DC ESS bus bar are displayed in amber

After 5 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC DC ESS BUS FAULT • SD displays ELEC DC page after switching.





MALFUNCTION : BAT FAULT 1 (2) (APU) AIRCRAFT : A380 CAUSE : Faulty BAT 1 (2) (APU) overheat detection CONSEQUENCES:

• Relevant FAULT light of the BAT P/B SW illuminates, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ELEC (APU) BAT 1(2) FAULT • SD displays: ELEC DC page,

- BAT indication is displayed in amber. • During the ECAM procedure:

After relevant BAT P/B SW has been switched off: The OFF light of the BAT P/B SW illuminates, The FAULT light of the BAT P/B SW extinguishes.

Canceling the malfunction and resetting of FWC restore normal battery operation.




MALFUNCTION : TR FAULT 2B AIRCRAFT : A380 CAUSE : Control of TRLC2 contactor fail (wiring cut) CONSEQUENCES:

If TRU 2 is requested to supply DC BUS 2 (TR 2A is failed): • TRU 2 fails to connect • E/WD displays message: ELEC TR 2B FAULT • SD displays: ELEC DC page

- TR 2A & B are displayed in amber





MALFUNCTION : TR FAULT 1 AIRCRAFT : A380 CAUSE : TR internal failure CONSEQUENCES:

• TR fails to supply DC BUS 100 PP, • DC BUS 100PP is supplied by DC BUS 200PP, • On ELEC DC system page, TR1 is displayed in amber.

After 2 seconds: • E/WD displays message: ELEC TR 1 FAULT • SD displays ELEC DC page,





MALFUNCTION : TR FAULT 2A AIRCRAFT : A380 CAUSE : TR 2A internal failure CONSEQUENCES:

• TR 2A fails to supply DC BUS 200 PP, • DC BUS 200PP is supplied by TRU 2B, • On ELEC DC system page, TR 2A is displayed in amber.

After 2 seconds: • E/WD displays message: ELEC TR 2A FAULT • SD displays ELEC DC page,





MALFUNCTION : STATIC INVERTER FAULT AIRCRAFT : A380 CAUSE : Static inverter internal failure CONSEQUENCES:

If the batteries are the only power source: • All AC busses are lost.

On ground with at least on AC SPLY • E/WD displays message: ELEC STATIC INV FAULT • Static inv displayed in amber on SD ELEC AC page





MALFUNCTION : C/B TRIPPED AIRCRAFT : A380 CAUSE : Electrical overload on CB8XB circuit breaker (short circuit of the

charge) CONSEQUENCES:

• E/WD displays message: ELEC C/B TRIPPED • On ELEC C/B system page, C/B 8XB-400XP CTL is displayed.





MALFUNCTION : EMER CONFIG AIRCRAFT : A380 CAUSE : All main AC BUS bars are lost Wiring between contactors EPC 1 to 4, GLC 1 to 4, BTC 1 to 4

wiring cut. CONSEQUENCES:

• Static inverter supply AC ESS bus before RAT connect, • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • FAULT light on RAT P/B SW illuminates until RAT is connected, during 2 seconds, • E/WD displays message: ELEC EMER CONFIG • SD displays: ELEC AC page

Canceling the malfunction restores normal generation distribution. System operates as per switch positions following ECAM actions.




MALFUNCTION : ENG FIRE (EXTING - FIRST AGENT) ENG 1(2) AIRCRAFT : A380 CAUSE : Engine fire CONSEQUENCES:

• On fire panel relevant engine 1(2) FIRE handle illuminates, • On central pedestal, engine 1(2) FIRE light illuminates, • Nacelle temperature increases and triggers the advisory. • SD displays ENGINE page, • Nacelle temperature maximum value remains just above the advisory value, • Oil temperature increases but does not reach the green advisory value, • Continuous repetitive chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 1(2) FIRE LAND ASAP • During the ECAM procedure:

After the first agent bottle has been discharged the fire extinguishes, ENG 1(2) FIRE warning message is cleared, Fire lights on fire handle and pedestal go out, Engine oil temperature and nacelle temperature decrease (nacelle temperature advisory disappears within a few seconds).

Canceling the malfunction reopens fire shut off valve and restores normal engine performance. Resetting the FIRE AGENT recharges the bottles. System operates as per switch positions following ECAM actions.




MALFUNCTION : ENG FIRE (EXTING - SECOND AGENT) ENG 2(4) AIRCRAFT : A380 CAUSE : Engine fire CONSEQUENCES:

• On fire panel relevant engine FIRE handle illuminates, • On central pedestal, relevant engine FIRE light illuminates, • Nacelle temperature increases and triggers the advisory. • SD displays ENGINE page, • Nacelle temperature maximum value remains just above the advisory value, • Oil temperature increases but does not reach the green advisory value, • Continuous repetitive chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 2(4) FIRE LAND ASAP • During the ECAM procedure:

After the two agents bottles has been discharged the fire extinguishes, ENG 2(4) FIRE warning message is cleared, Fire lights on fire handle and pedestal go out, Engine oil temperature and nacelle temperature decrease (nacelle temperature advisory disappears within a few seconds).





MALFUNCTION : ENG FIRE (UNEXTING) ENG 1(3)(4) AIRCRAFT : A380 CAUSE : Engine fire CONSEQUENCES:

• On fire panel relevant engine FIRE handle illuminates, • On center pedestal, relevant engine FIRE light illuminates, • Nacelle temperature increases and triggers the advisory. • SD displays ENGINE page, • Nacelle temperature maximum value remains just above the advisory value, • Oil temperature increases but does not reach the amber advisory value, • Continuous repetitive chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 1(3)(4) FIRE LAND ASAP • During the ECAM procedure:

After the two agents bottles have been discharged the fire does not extinguish.





MALFUNCTION : APU FIRE (EXTINGUISHABLE) AIRCRAFT : A380 CAUSE : APU Fire CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • APU FIRE light illuminates red on APU FIRE panel, • E/WD displays message: APU FIRE • SD displays APU page.

If the aircraft is on ground: • FAULT light of APU MASTER P/B SW illuminates, • After 3s, APU automatic shutdown, • 10s after shutdown, agent discharge occurs • Horn in the nose gear bay sounds, • DISCH light of APU AGENT P/B illuminates, • After 20s, fire extinguishes.

If the aircraft is in flight: • E/WD displays message: APU FIRE LAND ASAP • During the ECAM procedure:

After APU FIRE P/B has been pushed: FAULT light of APU MASTER P/B SW illuminates, APU FIRE P/B remains illuminated as long as fire is detected, After 20s, fire extinguishes,

Canceling the malfunction restores normal APU operation and resetting FIRE AGENT recharges the bottle. System operates as per switch positions following ECAM actions.




MALFUNCTION : APU FIRE (UNEXTINGUISHABLE) AIRCRAFT : A380 CAUSE : APU Fire CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • APU FIRE light illuminates red on APU FIRE panel, • E/WD displays message: APU FIRE • SD displays APU page.

If the aircraft is on ground: • FAULT light of APU MASTER P/B SW illuminates, • After 3s, APU automatic shutdown, • 10s after shutdown, agent discharge occurs • Horn in the nose gear bay sounds, • DISCH light of APU AGENT P/B illuminates.

If the aircraft is in flight: • During the ECAM procedure:

After APU FIRE P/B has been pushed: FAULT light of APU MASTER P/B SW illuminates, APU FIRE P/B remains illuminated,

Canceling the malfunction restores normal APU operation and resetting FIRE AGENT recharges the bottle. System operates as per switch positions following ECAM actions.




MALFUNCTION : MLG BAY FIRE AIRCRAFT : A380 CAUSE : Fire in the MLG BAY CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: MLG BAY FIRE LAND ASAP • SD displays WHEEL page

Canceling the malfunction extinguishes fire in the MLG BAY.



ATA 26 – SMOKE

MALFUNCTION : AIR CONDITIONING SMOKE AIRCRAFT : A380 CAUSE : Fire in a pack Smoke generator initialization: Smoke generator initialization - Push “Smoke” button on IOS services panel. Light in pushbutton will flash for 10 minutes, indicating the smoke generator is pre-heating. - When light is steady, smoke generator is ready for use.

CONSEQUENCES: There is no warning message or indication.

If the smoke generator is ready, smoke comes from air conditioning system. Canceling the malfunction stops the smoke generation. Smoke generator deactivation: Push the “Smoke” pushbutton on services panel to power off the smoke generator and extract fan starts. After end of smoke exercise, wait about 10 min for complete smoke extraction before opening the simulator door.

VALIDITY : FFS



ATA 26 – SMOKE

MALFUNCTION : SMOKE MAIN AVIONIC LEFT AIRCRAFT : A380 CAUSE : Fire in left hand area of main avionics CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • SMOKE light of AVNCS button illuminates on the ventilation panel, • E/WD displays message: SMOKE L MAIN AVNCS SMOKE LAND ASAP

Canceling the malfunction extinguishes the fire.



ATA 26 – SMOKE

MALFUNCTION : SMOKE CARGO SMOKE AFT AIRCRAFT : A380 CAUSE : Fire in the AFT GARGO compartment CONSEQUENCES: Camera image simulates a heavy smoke generation in the relevant compartment

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • SMOKE light of AGENT TO AFT P/B SW on cargo smoke panel illuminates, • E/WD displays message: SMOKE AFT/BULK CARGO SMOKE LAND ASAP • During the ECAM procedure:

After AGENT TO AFT P/B has been switched on: After about 60s, BTL 1 light of DISCH button illuminates, After 200s, BTL 2 light of DISCH button illuminates,

Canceling the malfunction extinguishes fire in the CARGO compartment and resetting the FIRE AGENT recharges bottles 1 and 2. System operates as per switch positions following ECAM actions.



ATA 26 – SMOKE

MALFUNCTION : SMOKE LAVATORY MAIN DECK AIRCRAFT : A380 CAUSE : Fire in main deck lavatory CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: SMOKE MAIN DECK LAVATORY SMOKE

Canceling the malfunction extinguishes the fire. System operates as per switch positions following ECAM actions



ATA 26 – SMOKE

MALFUNCTION : SMOKE IN-FLIGHT ENTERTAINMENT CENTER AIRCRAFT : A380 CAUSE : Fire in in-flight entertainment center CONSEQUENCES:

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • IFEC SMOKE P/B SW light illuminates • E/WD displays message: SMOKE IFE BAY SMOKE LAND ASAP

Canceling the malfunction extinguishes the fire.



ATA 27 – FLIGHT CONTROLS - EFCS

MALFUNCTION : PRIM 1 FAULT AIRCRAFT : A380 CAUSE : Flight Control and Guidance Unit (FCGU) 1 power supply unit fails. CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of PRIM 1 P/B SW illuminates, • E/WD displays message: F/CTL PRIM 1 FAULT, • SD displays F/CTL page,

- L&R Spoiler 6 indications show amber X, - PRIM 1 indication is X amber.

Note: In case of triple PRIM failure, aircraft reverts to DIRECT LAW.

Canceling the malfunction restores PRIM1 operation.






- L&R Spoiler 5 indications show amber X, - STAB elec motor is amber boxed, - G left & right outboard aileron actuators are amber boxed, - PRIM 2 indication is X amber.


Canceling the malfunction restores PRIM 2 operation.






- L&R Spoiler 4 indications show amber X, - Y left & right outboard aileron actuators are partially amber boxed - PRIM 3 indication is X amber.


Canceling the malfunction restores PRIM3 operation.




MALFUNCTION : SEC 1 FAULT AIRCRAFT : A380 CAUSE : SEC 1 power supply unit fails. CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of SEC 1 P/B SW illuminates, • E/WD displays message: F/CTL SEC 1 FAULT, • SD displays F/CTL page,

- L&R Spoiler 3 indications show amber X, - SEC 1 indication is X amber.

Note: In case of SEC 1 & 3 failure, RUDDER TRIM PEDAL deflection is lost.

Canceling the malfunction restores SEC 1 operation.





• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of SEC 2 P/B SW illuminates, • E/WD displays message: F/CTL SEC 2 FAULT, • SD displays F/CTL page:

- L&R Spoiler 2&7 indications show amber X, - SEC 2 indication is X amber.






• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of SEC 3 P/B SW illuminates, • E/WD displays message: F/CTL SEC 3 FAULT, • SD displays F/CTL page,

- L&R Spoiler 1&8 indications show amber X, - SEC 3 indication is X amber.

Note: In case of SEC 1 & 3 failure, RUDDER TRIM PEDAL deflection is lost.





MALFUNCTION : GYROMETER FAULT 1, 2 or 3 gyro failed AIRCRAFT : A380 CAUSE : Gyrometer internal fault CONSEQUENCES:

Single gyrometer fails:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AUTO FLT APPROACH CAPABILITY DOWNGRADED • CAT 3 DUAL capability is lost.

Two gyrometers fail:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AUTO FLT APPROACH CAPABILITY DOWNGRADED • E/WD displays message when engines are stopped: F/CTL TWO GYROMETERS FAULT • CAT 2 capability is lost. • GLS AUTOLAND capability is lost.

Three gyrometers fail:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL DIRECT LAW (PROT LOST) • E/WD displays message when engines are stopped: F/CTL TWO GYROMETERS FAULT • EFCS reverts to direct law.

Canceling the malfunction restores normal EFCS functions.




MALFUNCTION : SIDESTICK FAULT L(R) AIRCRAFT : A380 CAUSE : CAPT (F/O) side stick pitch and roll electrical signals fail CONSEQUENCES:

• CAPT (F/O) side stick is inoperative in pitch and in roll axis, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL L(R) SIDESTICK FAULT, • SD displays F/CTL page.

Canceling the malfunction restores normal CAPT (F/O) side stick operation.

VALIDITY: FFS




MALFUNCTION : SIDE STICK FALSE ELEC INPUT L(R) AIRCRAFT : A380 PARAMETER : Full right / full left / full up / full down CAUSE : Wrong side stick signal CONSEQUENCES:

• CAPT (F/O) side stick fails and sends Full right / full left / full up / full down order, • Crew action have no effect on the CAPT (F/O) side stick order, • No failure is detected by EFCS, nor announced by FWS.


VALIDITY: FFS




MALFUNCTION : SIDE STICK REVERSED INPUT L(R) AIRCRAFT : A380 CAUSE : CAPT (F/O) side stick inverted roll electrical signal CONSEQUENCES:

• CAPT (F/O) side stick roll orders are inverted on roll axis, • No failure is detected by EFCS, nor announced by FWS.


VALIDITY: FFS




MALFUNCTION : RUDDER PEDAL FAULT AIRCRAFT : A380 CAUSE : Pedal Feel and Trim Unit (PFTU) failed CONSEQUENCES: As soon as the failure is inserted:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL RUDDER PEDAL FAULT • SD displays F/CTL page, • Action on the pedals has no effect in flight or on ground.

Canceling the malfunction restores normal rudder pedals operation.

VALIDITY: FFS



ATA 27 – FLIGHT CONTROL - EFCS

MALFUNCTION : RUDDER TRIM RUNAWAY (LEFT) AIRCRAFT : A380 CAUSE : Rudder trim control selector stuck in left position CONSEQUENCES:

If auto pilot is engaged: • No effect

If auto pilot is not engaged: • As soon as pilot operates RUDDER trim selector to the left, rudder trim moves to full left position

Canceling the malfunction restores normal rudder trim operation. No pilot action is necessary on rudder trim reset pushbutton. The rudder trim position is also restored to 0 deg.

VALIDITY: FFS




MALFUNCTION : RUDDER TRIM FAULT 1 (2) AIRCRAFT : A380 CAUSE : Pedal Feel and Trim Unit (PFTU) actuator 1(2) fails CONSEQUENCES:

Single rudder trim fails: • E/WD displays message: F/CTL RUD TRIM 1(2) FAULT

Dual rudder trim fails: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL RUDDER TRIM FAULT • SD displays F/CTL page,

- Rudder trim position becomes X amber, • Rudder trim control selector becomes inoperative, • Rudder trim reset becomes inoperative, • Rudder trim indication displays dashes.

Canceling the malfunction restores normal rudder trim operation.

VALIDITY: FFS




MALFUNCTION : RUDDER FAULT UPR (LOW) AIRCRAFT : A380 CAUSE : Servo-control runaway CONSEQUENCES:

Single rudder fails: • UPR (LOW) rudder is stuck in position, • EFCS reverts to alternate law, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL ALTN LAW (PROT LOST) • F/CTL SINGLE RUDDER FAULT • SD displays F/CTL page,

- UPR (LOW) rudder indication becomes X amber, - UPR (LOW) rudder actuators indication becomes amber boxed.

-

Dual rudder fails: • Both rudders are stuck in the current position, • EFCS reverts to alternate law, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL ALTN LAW (PROT LOST) F/CTL SINGLE RUDDER FAULT • SD displays F/CTL page,

- UPR & LOW rudder indications become X amber, - UPR & LOW rudder actuators indication become amber boxed.

Canceling the malfunction restores normal rudder operation.

VALIDITY: FFS




MALFUNCTION : ALTERNATE LOW DEMO (PROT LOST) AIRCRAFT : A380 CAUSE : No existing cause: synthetic failure


The malfunction doesn’t downgrade any A/C system (except Flight Controls) functioning. • All A/C systems behave normally, • Flight controls system reverts to Alternate law, • E/WD displays message: F/CTL ALTN LAW (PROT LOST)


VALIDITY: FFS




MALFUNCTION : DIRECT LAW DEMO (PROT LOST) AIRCRAFT : A380 CAUSE : No existing cause: synthetic failure


The malfunction doesn’t downgrade any A/C system (except Flight Controls) functioning. • All A/C systems behave normally, • Flight controls system reverts to Direct law, • E/WD displays message: F/CTL DIRECT LAW (PROT LOST)


VALIDITY: FFS



ATA 27 – FLIGHT CONTROLS - SURFACES

MALFUNCTION : SPEED BRAKES FAULT AIRCRAFT : A380 CAUSE : Speed brake lever transducer unit fault CONSEQUENCES:

• Flight computers detect a loss of SPD BRKs function, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL GND SPLRs FAULT F/CTL SPEED BRAKES FAULT • There is no more extension of speed brakes

Canceling the malfunction restores normal speed brake operation.



ATA 27 - FLIGHT CONTROLS - SURFACES

MALFUNCTION : AILERON FAULT L INR AIRCRAFT : A380 CAUSE : Surface runaway CONSEQUENCES :

• Both aileron actuators are set in damping mode after runaway. • The right outboard aileron is floating at its zero hinge moment position. • As soon as an aileron movement is requested by the EFCS:

Single Chime sounds, MASTER CAUT lights illuminate, E/WD displays message: F/CTL L INR AILERON FAULT SD displays F/CTL page,

- Left inboard aileron indication becomes amber crossed, - Both servo controls become amber boxed.

Canceling the malfunction restores normal aileron operation.

VALIDITY: FFS




MALFUNCTION : AILERON ACTUATOR FAULT L OUTBD AIRCRAFT : A380 CAUSE : Jamming of a slide in the left outboard aileron servo fed by the

green hydraulic circuit CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL AILERON ACTUATOR FAULT • SD displays F/CTL page,

- Green left outboard aileron servo indication is amber boxed.


VALIDITY: FFS




MALFUNCTION : AILERON FAULT (DOWN) R OUTR AIRCRAFT : A380 CAUSE : Surface axis worn CONSEQUENCES :

When the servo controls are depowered on ground on ground, after lying on its mechanical stop: • The right outer aileron is stuck in position,

When the servo controls are powered once again on ground: • The right outer aileron is stuck in its lowest position, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL R OUTR AILERON FAULT • SD displays F/CTL page,

- Right outboard aileron indication becomes amber, - Right outboard aileron actuators become amber boxed.


VALIDITY: FFS




MALFUNCTION : STABILIZER FAULT AIRCRAFT : A380 CAUSE : Actuator screw worn CONSEQUENCES : As soon as a THS movement is requested by the EFCS on ground or during autotrim operations, after fault confirmation:

• The THS is stuck in position, • EFCS reverts to alternate law • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL STABILIZER FAULT F/CTL ALTN LAW (PROT LOST) • SD displays F/CTL page,

- Amber Pitch trim indication is displayed, - THS position indication is amber, - G, Y and elec. Motors indication are amber boxed,

Note: up to 50 seconds order on THS switch may be needed before fault confirmation by computers depending on flight conditions. During manual flight F/CTL STABILIZER ACTUATOR FAULT may be detected during the first minute, F/CTL STAB FAULT will be detected two minutes later.

Canceling the malfunction restores normal stabilizer operation.

VALIDITY: FFS




MALFUNCTION : SINGLE ELEVATOR FAULT R OUTB AIRCRAFT : A380 CAUSE : Surface runaway CONSEQUENCES :

• Both elevator actuators are set in damping mode after runaway. • The right outboard elevator is floating at its zero hinge moment position. • EFCS reverts to alternate law • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: F/CTL ALTN LAW (PROT LOST) F/CTL SINGLE ELEVATOR FAULT • SD displays F/CTL page,

- Right outboard elevator indication becomes amber, - Right outboard elevator actuators indications become amber boxed.

Canceling the malfunction restores normal elevator operation.

VALIDITY: FFS




MALFUNCTION : ELEVATOR ACTUATOR FAULT R INBD AIRCRAFT : A380 CAUSE : Jamming of a slide in the right inboard elevator servo fed by the

yellow hydraulic circuit CONSEQUENCES :

• E/WD displays message: F/CTL ELEVATOR ACTUATOR FAULT • SD displays F/CTL page,

- Right inboard elevator Y servo indication is amber boxed.


VALIDITY: FFS




MALFUNCTION : SINGLE ELEVATOR FAULT (DOWN) L OUTB AIRCRAFT : A380 CAUSE : Surface axis worn CONSEQUENCES :

When the servo controls are depowered on ground, after lying on its mechanical stop: • The left outboard elevator is stuck in position,

When the servo controls are powered once again on ground: • The left outboard elevator is stuck in its lowest position, • As soon as an elevator movement is requested by the EFCS:

- Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: F/CTL SINGLE ELEVATOR FAULT - SD displays F/CTL page,

- Left outboard elevator indication becomes amber, - Left outboard elevator actuators become amber boxed.


VALIDITY: FFS



ATA 27 – FLIGHT CONTROLS - SLATS + FLAPS

MALFUNCTION : SLATS SYS FAULT 1 (2) AIRCRAFT : A380 CAUSE : SFCC 1: Loss of actuator electrical motor SFCC 2: Loss of Green hydraulic actuator motor CONSEQUENCES:

Single SFCC slats channel fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • Slats operate at half speed. • E/WD displays message: F/CTL SLAT SYS 1 (2) FAULT

SLAT SLOW • SD displays F/CTL page

- SLAT 1 (2) indication appear amber.

Dual SFCC slats channel fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • All slats are inoperative • EFCS reverts to alternate law. • E/WD displays message: F/CTL SLATS SYS 1+2 FAULT. F/CTL ALTN LAW (PROT LOST) • PFD “S” indication and actual Slat position appear amber. • SD displays F/CTL page

- SLAT 1&2 indications appear amber.

Canceling the malfunction(s) restores normal Slats and Flaps system behavior.




MALFUNCTION : FLAPS SYS FAULT 1 (2) AIRCRAFT : A380 CAUSE : SFCC 1: Loss of Green hydraulic actuator motor SFCC 2: Loss of Yellow hydraulic actuator motor CONSEQUENCES:

Single SFCC flaps channel fault • Flaps operate at half speed. • E/WD displays message: F/CTL FLAP SYS 1 (2) FAULT

FLAP SLOW • SD displays F/CTL page

- FLAP 1 (2) indication appear amber

Dual SFCC flaps channel fault • Single Chime sounds, • MASTER CAUT lights illuminate, • All flaps are inoperative. • EFCS reverts to alternate law. • E/WD displays message: F/CTL FLAPS SYS 1+2 FAULT. F/CTL ALTN LAW (PROT LOST) • PFD “F” indication and actual Flap position appear amber. • SD displays F/CTL page

- FLAP 1&2 indications appear amber.

Canceling the malfunction(s) restores normal Slats and Flaps system behavior.




MALFUNCTION : SLATS SYS FAULT / FLAPS SYS FAULT AIRCRAFT : A380 CAUSE : All electrical and hydraulic actuator motors loss


• Single Chime sounds, • MASTER CAUT lights illuminate, • Slats and flaps freeze in the current position • EFCS reverts to alternate law. • E/WD displays message: F/CTL SLATS SYS 1+2 FAULT.

F/CTL FLAPS SYS 1+2 FAULT F/CTL ALTN LAW (PROT LOST)

• "F" and "S" indication and actual flaps position appear amber on PFD. • SD displays F/CTL page

- SLAT 1&2 indications appear amber. - FLAP 1&2 indications appear amber.

Canceling the malfunction restores normal Slats and Flaps system behavior.




MALFUNCTION : SLATS LOCKED (WTB) AIRCRAFT : A380 CAUSE : Shaft overspeed (shaft rupture) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • All slats become inoperative, • E/WD displays message: F/CTL SLATS LOCKED F/CTL ALTN LAW (PROT LOST) • "S LOCKED" indication and actual slats position appear amber on PFD. • SD displays F/CTL page

- SLAT 1&2 indications appear amber.

Canceling the malfunction restores system behavior, however WTB remain engaged once triggered by the failure.




MALFUNCTION : FLAPS LOCKED (WTB) AIRCRAFT : A380 CAUSE : Shaft overspeed (shaft rupture) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • All flaps become inoperative. • E/WD displays message: F/CTL FLAPS LOCKED

F/CTL ALTN LAW (PROT LOST) • "F LOCKED" indication and actual flaps position appear amber on PFD. • SD displays F/CTL page

- FLAP 1&2 indications appear amber.

Canceling the malfunction restores system behavior, however WTB remain engaged once triggered by the failure.



ATA 28 – FUEL PUMPS

MALFUNCTION : FEED TANK MAIN PUMP FAULT 1(2)(3)(4) AIRCRAFT : A380 CAUSE : Pump fails mechanically (5KA1(2)(3)(4)) CONSEQUENCES:

• FAULT light of MAIN 1 (2)(3)(4) PUMP P/B SW illuminates, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL FEED TK 1 (2)(3)(4) MAIN PMP FAULT • SD displays FUEL page, • During the ECAM procedure:

After MAIN 1 (2)(3)(4) PUMP has been switched off: MAIN 1 (2)(3)(4) FAULT light extinguishes, MAIN 1 (2)(3)(4) OFF light illuminates.

Canceling the malfunction restores normal operation of the main 1(2)(3)(4) pump. System operates as per switch positions following ECAM actions.




MALFUNCTION : FEED TANK MAIN + STBY PUMPS FAULT 1(2)(3)(4) AIRCRAFT : A380 CAUSE : MAIN and STBY Pump fails mechanically (6QA1(2)(3)(4)) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of MAIN and STBY 1(2)(3)(4) PUMP P/B SW illuminates, • E/WD displays message: FUEL FEED TK 1 (2)(3)(4) MAIN + STBY PMPs FAULT • SD displays FUEL page, • During the ECAM procedure:

After MAIN and STBY 1(2)(3)(4) PUMP has been switched off: - MAIN and STBY 1(2)(3)(4) FAULT light extinguishes, - MAIN and STBY 1(2)(3)(4) OFF light illuminates.

Canceling the malfunction restores normal operation of the MAIN and STBY 1(2)(3)(4) pump. System operates as per switch positions following ECAM actions.




MALFUNCTION : WING FEED PUMPS FAULT L (R) AIRCRAFT : A380 CAUSE : All left wing feed pumps are operating at low pressure (5QA1(2) or

5QA3(4)) CONSEQUENCES:

If all L (R) wing feed pumps are switched on: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of MAIN and STBY PUMP P/B SW illuminates, • E/WD displays message: FUEL L (R) WING FEED PMPs FAULT • SD displays FUEL page, • During the ECAM procedure:

After MAIN and STBY PUMP has been switched off : FAULT light extinguishes, OFF light illuminates.

Canceling the malfunction restores normal operation of the affected pump. System operates as per switch positions following ECAM actions.




MALFUNCTION : INR TANK FWD+AFT PUMPS FAULT R AIRCRAFT : A380 CAUSE : Both right inner tank transfer pumps fail mechanically

(13QN2&13QL2) CONSEQUENCES:

During an automatic FWD transfer:

After 5 minutes, automatic FWD transfer aborts:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL R INR TK FWD PMP FAULT • FAULT light of the R INR tank transfer pump FWD is illuminated until it is selected off,

After 5 minutes, when AFT pump failure is detected: • Single Chime sounds, • MASTER CAUT lights illuminate, • Previous E/WD message is replaced by: FUEL R INR TK FWD+AFT PMPs FAULT • SD displays FUEL page. • FAULT light of the R INR tank transfer pump AFT is illuminated until it is selected off,

NOTE: right INNER TK fuel is unusable.

Canceling the malfunction restores normal operation of the pumps. System operates as per switch positions following ECAM actions.




MALFUNCTION : MID TANK FWD+AFT PUMPS FAULT L AIRCRAFT : A380 CAUSE : Both left mid tank transfer pumps fail mechanically

(10QL1&20QN1) CONSEQUENCES: After 5 minutes, automatic FWD transfer aborts:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL L MID TK FWD PMP FAULT • FAULT light of the L MID tank transfer pump FWD is illuminated until it is selected off,

After 5 minutes, AFT pump failure is detected: • Single Chime sounds, • Previous E/WD message is replaced by: FUEL L MID TK FWD+AFT PMPs FAULT • SD displays FUEL page. • FAULT light of the L MID tank transfer pump AFT is illuminated until it is selected off

NOTE: Left MID TK fuel is unusable.

Canceling the malfunction restores normal operation of the pumps. System operates as per switch positions following ECAM actions.




MALFUNCTION : OUTR TANK PUMP FAULT L (R) AIRCRAFT : A380 CAUSE : Transfer pump fails mechanically (11QL1&11QL2) CONSEQUENCES: Note: in flight the malfunction must be inserted without OUTR transfer.

If OUTR TK L (R) is switched on, after 5 minutes: • FAULT light on L (R) OUT TK pump P/B SW illuminate until it is selected off, • Single Chime sounds, • MASTER CAUT lights illuminate • E/WD displays message: FUEL L (R) OUTR TK PMP FAULT • SD displays FUEL page:

- The affected pump is displayed closed amber

If any feed tank is below 13t • E/WD displays message: FUEL NORM XFR FAULT

Canceling the malfunction restores normal operation of the pump. System operates as per switch positions following ECAM actions.




MALFUNCTION : TRIM TANK PUMP FAULT L (R) AIRCRAFT : A380 CAUSE : Trim tank transfer pump fails mechanically (6QN1&6QN2) CONSEQUENCES:

If TRIM TK 1(2) is switched on, after 5 minutes: • FAULT light of TRIM TK L (R) PUMP P/B SW illuminates until it is selected off, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL TRIM TK L (R) PMP FAULT • SD displays FUEL page,

If both TRIM TK pumps fail: • FAULT light of TRIM TK L and R PUMPs P/Bs SWs illuminate until they are selected off, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL TRIM TK L+R PMPs FAULT • SD displays FUEL page.

Canceling the malfunction restores normal operation of the pump. System operates as per switch positions following ECAM actions.



ATA 28 – FUEL TANKS

MALFUNCTION : OUTR TANK XFR FAULT L (R) AIRCRAFT : A380 CAUSE : Failure of automatic transfer pump and valves CONSEQUENCES:

After 5 minutes, the pump is displayed abnormally OFF • SD displays FUEL page. • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL L(R) OUTR TK PMP FAULT • E/WD displays message for a few seconds: FUEL NORM XFR FAULT • E/WD displays message: FUEL NORM+ALTN XFR FAULT

Select OT Manual XFR • E/WD displays message: FUEL OUTR TK XFR FAULT

Canceling the malfunction restores normal operation. System operates as per switch positions following ECAM actions.




MALFUNCTION : ENG LP VALVE FAULT 1(2)(3)(4) AIRCRAFT : A380 CAUSE : Valve stuck in position CONSEQUENCES:

On the ground before engine start or before engine shut down: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL ENG 1(2)(3)(4) LP VLV FAULT • SD displays FUEL page.

Canceling the malfunction restores normal valve operation. System operates as per switch positions following ECAM actions.




MALFUNCTION : WINGS NOT BALANCED / LEAK DETECTED 1(2)(3)(4) AIRCRAFT : A380 CAUSE : Leak in the 1(2)(3)(4) feed tank PARAMETER : min value max value

Fuel leak rate 0 kg/min 6000 kg/min CONSEQUENCES:

After a confirmation time of 30 sec

If the difference between the fuel quantity in Feed Tank 1 and Feed Tank 4 above 3000kg (6600 lbs), or between Feed Tank 3 and Feed Tank 2 above 3000 kg (6600 lbs):

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL WINGS NOT BALANCED • SD displays FUEL page.

If the fuel leak quantity > 8000 kg (17600 lbs) since the beginning of the fly (slow fuel leak) or if the fuel leak is > 2000kg(around 70kg/mn) in less than 30minutes(fast fuel leak) :

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL LEAK DETECTED • SD displays FUEL page.

Canceling the malfunction restores initial quantities in all tanks and fuel used.




MALFUNCTION : HIDDEN FUEL LEAK ENG 1(4) AIRCRAFT : A380 CAUSE : Engine fuel pump assembly seal broken CONSEQUENCES:

• There is no warning, • Affected engine behavior does not change: engine fuel flow remains normal, • Fuel leak is evacuated overboard through the engine drain mast, • Engine fuel used indication is not affected by fuel leak, • Fuel consumption at relevant tank level is consistent with the maximum throughput of wing fuel

pump

Canceling the malfunction restores normal engine operation, but initial fuel quantities are not restored.




MALFUNCTION : CROSSFEED VALVE FAULT 1 AIRCRAFT : A380 CAUSE : Valve stuck in position (10QE1) CONSEQUENCES: Selecting crossfeed valve if it is OFF or deselecting crossfeed valve if it is ON:

• E/WD displays message: FUEL CROSSFEED VLV 1 FAULT • SD displays FUEL page.

Canceling the malfunction restores normal operation of the X FEED valve.




MALFUNCTION : JETTISON FAULT/ VLV NOT CLOSED AIRCRAFT : A380 CAUSE : Left and right jettison valves stuck in position (7QV1 7QV2) CONSEQUENCES:

1- After JETTISON ARM & ACTIVE P/B are switched ON: • ON lights of JETTISON ARM & ACTIVE P/B SW illuminate • OPEN light of JETTISON ACTIVE P/B SW remains extinguished,

After 15s: • E/WD displays message: FUEL JETTISON FAULT

2- After JETTISON ARM & ACTIVE P/B are switched OFF (having been switched ON before the malfunction was inserted): • OPEN light of JETTISON ACTIVE P/B SW remains illuminated, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL JETTISON VLV NOT CLOSED • SD displays FUEL page.

Canceling the malfunction restores normal operation of the left and right jettison valves. System operates as per switch positions following ECAM actions.




MALFUNCTION : FQDC FAULT 1 (2) AIRCRAFT : A380 CAUSE : Fuel Quantity Data Concentrator (FQDC) internal failure CONSEQUENCES:

If one FQDC fails: • E/WD displays message: FUEL FQDC 1 (2) FAULT • SD displays FUEL page.

If FQDC 2 (1) is already failed: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL FQMS 1+2 FAULT FUEL FQI FAULT • SD displays FUEL page.

Note: info from CPIOMs are still valid

Canceling the malfunction restores normal operation of the FQDCS 1 (2). System operates as per switch positions following ECAM actions.




MALFUNCTION : FEED TANK TEMP HIGH 2(3) AIRCRAFT : A380 CAUSE : Fuel temperature INC/DEC CONSEQUENCES:

When fuel temperature is between 48°C and 53°C • Indication is green

When fuel temperature is above 53°C • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: FUEL FEED TK 2(3) TEMP HI • SD displays FUEL page:

- Indication is amber

Canceling the malfunction restores the initial temperature of the fuel. System operates as per switch positions following ECAM actions.



ATA 28 – FUEL CG

MALFUNCTION : AFT CG GW & CG BKUP/FQMS DISAGREE AIRCRAFT : A380 CAUSE : Fuel trapped in trim tank with no transfer trim tank transfer pump

T81 andT82 fails CONSEQUENCES:

Note: others caution message will occur as well as AFT CG caution. It will be possible for the pilots to effect gravity transfer

If CG goes >46% during 5 minutes and FQMS above 10000ft (warning will come in flight phase 1 or 12) • E/WD displays message: FUEL WBBC / FQMS CG DISAGREE

Canceling the malfunction restores normal center of gravity. System operates as per switch positions following ECAM actions.




MALFUNCTION : RSVR LOW LEVEL (FLUID QTY INC/DEC) GREEN AIRCRAFT : A380 CAUSE : Green reservoir quantity varies according to the quantity selected

on the IOS PARAMETER : min value max value rate

green rsvr quantity 0L 100L 15L/s CONSEQUENCES:

When tank level is below 10 L • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT lights on ENG 1 and 2 PUMP A, B and A+B P/B SW illuminate, • E/WD displays message: HYD G RSVR LEVEL LO • SD displays HYD page

- Fluid level indication is displayed in amber, • During the ECAM procedure:

After GREEN ENG PUMP P/B SW are switched off: FAULT lights extinguish OFF light of GREEN PUMP P/B SW illuminates GREEN system pressure reduces to 0 PSI E/WD displays message: G SYS PRESS LO

Canceling the malfunction restores Green hydraulic quantity. System operates as per switch positions following ECAM actions.

Note: need also a FWC reset, if malfunction was done before, in order to have the DISC message on the E/WD




MALFUNCTION : RSVR LOW LEVEL (FLUID QTY INC/DEC) YELLOW AIRCRAFT : A380 CAUSE : Yellow reservoir quantity varies according the quantity selected on

the IOS PARAMETER : min value max value rate

Yellow rsvr quantity 0L 100L 15L/s CONSEQUENCES:

When tank level is below 10 L • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT lights of ENG 3 and 4 PUMP A, B and A+B P/B SW illuminate, • E/WD displays message: HYD Y RSVR LEVEL LO • SD displays HYD page,

- Fluid level indication is displayed in amber, • During the ECAM procedure:

When YELLOW ENG PUMP P/B SW are switched off: FAULT lights extinguish OFF light of YELLOW PUMP P/B SW illuminates YELLOW system pressure reduces to 0 PSI E/WD displays message: Y SYS PRESS LO

Canceling the malfunction restores Yellow hydraulic quantity. System operates as per switch positions following ECAM actions.

Note: need also a FWC reset, if malfunction was done before, in order to have the DISC message on the E/WD




MALFUNCTION : SYSTEM OVERHEAT GREEN (YELLOW) AIRCRAFT : A380 CAUSE : Temperature reservoir greater than 94 deg C CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • Affected ENG pump P/B FAULT light illuminate and remain illuminated as long as the overheat

exists, regardless P/B position, • Affected ELEC pump P/B FAULT light illuminate and remain illuminated as long as the overheat

exists, regardless P/B position, • E/WD displays message: HYD G (Y) SYS OVHT • SD displays HYD page,

- OVHT reservoir indication is displayed amber.

Canceling the malfunction restores rapidly normal hydraulic reservoir temperature. System operates as per switch positions following ECAM actions.




MALFUNCTION : RSVR AIR PRESS LO GREEN (YELLOW) AIRCRAFT : A380 CAUSE : Air pressure in affected reservoir is lower than 22 psi CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • Affected ENG pump P/B FAULT light SW illuminate, • E/WD displays message: HYD G (Y) RSVR AIR PRESS LO • SD displays HYD page, with AIR PRESS LO • During the ECAM procedure:

After affected PUMPS (ENG) have been switched off: FAULT lights extinguish OFF lights illuminate Affected system pressure reduces to 0 psi E/WD displays message: G (Y) SYS PR LO

Canceling the malfunction restores normal air pressure. System operates as per switch positions following ECAM actions.




MALFUNCTION : ENG PUMP PRESS LO GREEN A(B) 1(2) AIRCRAFT : A380 CAUSE : Pump seized CONSEQUENCES:

When ENG pump pressure reduces below 2910 psi • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of affected PUMP P/B SW illuminates, • E/WD displays message: HYD G ENG 1(2) PMP A(B) PRESS LO • SD displays HYD page, • During the ECAM procedure:

After affected PUMP P/B SW have been switched off: FAULT light extinguishes OFF lights illuminate

Canceling the malfunction restores green system pump performance. System operates as per switch positions following ECAM actions.




MALFUNCTION : ENG PUMP A+B OVERHEAT YELLOW 3 AIRCRAFT : A380 CAUSE : Temperature above 120 deg. C CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of affected and unaffected PUMP P/B illuminates • E/WD displays message: HYD Y SYS OVHT • SD displays HYD page,

Canceling the malfunction restores rapidly yellow system pump performance. System operates as per switch positions following ECAM actions.




MALFUNCTION : ELEC PUMP FAULT (LO PRESS) GREEN A (B) AIRCRAFT : A380 CAUSE : Pump Lo press (seized) CONSEQUENCES:

If ELEC PUMP is running: • ON light of affected ELEC PUMP P/B SW extinguishes, • The ELEC pump pressure reduces to 0 psi.

When ELEC PUMP pressure reduces below 2175 psi • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ELEC PUMP P/B illuminates, • E/WD displays message: HYD G ELEC PMP A (B) FAULT • SD displays HYD page, • During the ECAM procedure:

When affected ELEC PUMP P/B SW is switched off: FAULT light extinguishes OFF lights illuminate

Note: malfunction effects available with FWC std. L41 and next

Canceling the malfunction restores normal electric pump performance. System operates as per switch positions following ECAM actions.




MALFUNCTION : ELEC PUMP FAULT (OVHT) YELLOW A (B) AIRCRAFT : A380 CAUSE : Overheat, temperature above 180 deg. C CONSEQUENCES:

If ELEC PUMP is running: • Single Chime sounds, • MASTER CAUT lights illuminate, • ON light of affected PUMP P/B SW extinguishes, • FAULT light of affected PUMP P/B SW illuminates • E/WD displays message: HYD Y ELEC PMP A (B) FAULT • SD displays HYD page.

Canceling the malfunction restores rapidly normal pump temperature. System operates as per switch positions following ECAM actions.




MALFUNCTION : ELEC PUMP FAULT (POWER SUPPLY) G(Y) A(B) AIRCRAFT : A380 CAUSE : The three phase AC bus control unit is failed and de-energizes the

affected ELEC pump actuator relay CONSEQUENCES:

When ELEC PUMP pressure reduces below 2175 psi • Single Chime sounds, • MASTER CAUT lights illuminate, • ON light of affected PUMP P/B SW extinguishes, • FAULT light of affected PUMP P/B illuminates, • E/WD displays message: HYD G (Y) ELEC PMP A (B) FAULT • SD displays HYD page, • During the ECAM procedure:

After affected PUMP P/B SW has been switched off: FAULT light extinguishes OFF light illuminates

Canceling the malfunction restores normal electric pump performance.




MALFUNCTION : HYDRAULIC SYSTEM MONITORING FAULT GREEN (YELLOW) AIRCRAFT : A380 CAUSE : Loss of the power supply CONSEQUENCES:

• E/WD displays message: HYD G (Y) SYS MONITORING FAULT • On HYD page:

- Fluid level is replaced by amber XX

Canceling the malfunction restores HSMU operation.



ATA 30 – ICE AND RAIN PROTECTION

MALFUNCTION : ICE DETECTION FAULT AIRCRAFT : A380 CAUSE : Internal failure of the two ice detectors CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: A. ICE ICE DET FAULT

Canceling the malfunction restores instantaneously normal detection.




MALFUNCTION : WING VALVE CLOSED L (R) AIRCRAFT : A380 CAUSE : Two valves stuck in closed position CONSEQUENCES:

If the WING ANTI ICE P/B SW is selected on: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of WING ANTI ICE P/B SW illuminates, • E/WD displays message: A.ICE L(R) WING VLV CLOSED • SD displays BLEED page.

Canceling the malfunction restores wing anti ice system. System operates as per switch positions following ECAM actions.




MALFUNCTION : WING VALVE PRESS LOW L (R) AIRCRAFT : A380 CAUSE : Failure of the pressure regulating shut off valve CONSEQUENCES:

If the WING ANTI ICE P/B SW is selected on: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of WING ANTI ICE P/B SW illuminates, • E/WD displays message: A.ICE L(R) WING VLV PRESS LOW • SD displays BLEED page.

Canceling the malfunction restores wing anti ice system.




MALFUNCTION : ENG VALVE CLOSED / OPEN 1(4) AIRCRAFT : A380 CAUSE : Engine Anti-ice valve stuck in current position CONSEQUENCES:

If engine anti-ice valve is in closed position:

When the ENG 1(4) ANTI ICE is selected on: • Single Chime sounds • MASTER CAUT lights illuminate • FAULT light of ENG 1(4) ANTI ICE illuminates • E/WD displays message: A.ICE ENG 1(4) VLV CLOSED • Loss of the ENG 1(4) anti-ice protection.

If engine anti-ice valve is in open position:

When the ENG 1(4) ANTI ICE is selected off: • Single Chime sounds • MASTER CAUT lights illuminate • FAULT light of ENG 1(4) ANTI ICE illuminates • E/WD displays message: A.ICE ENG 1(4) VLV OPEN

Canceling the malfunction restores engine anti ice system.




MALFUNCTION : WINDSHIELDS HEATG FAULT (NO HEAT) L (R) AIRCRAFT : A380 CAUSE : Open circuit CONSEQUENCES:

Single Failure • Windshield heating is lost, • E/WD displays message: A.ICE L(R) WINDSHIELD HEATG FAULT

Dual Failure • Windshield heating is lost, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: A.ICE L+R WINDSHIELD HEATG FAULT

Canceling the malfunction restores windshield-heating system.



ATA 31 – INDICATING/RECORDING

MALFUNCTION : CAPT PFD CDS UNIT FAULT AIRCRAFT : A380 CAUSE : Internal CDS unit power supply failure CONSEQUENCES:

• The CAPT PFD display is blank, • The CAPT PFD image is automatically transferred to CAPT ND • Single Chime sounds, • Master Caution light illuminates. • E/WD displays message: CDS CAPT PFD DU FAULT • The captain can recover the ND image on ND or MFD by using the PFD/ND/MFD control

pushbuttons on the CAPT reconfiguration switching panel.

Canceling the malfunction restores normal CAPT PFD.




MALFUNCTION : F/O ND CDS UNIT FAULT AIRCRAFT : A380 CAUSE : Internal CDS unit power supply failure CONSEQUENCES:

• The F/O ND display is blank, • Single Chime sounds, • Master Caution light illuminates. • E/WD displays message: CDS FO ND DU FAULT • The F/O can recover the ND image on PFD or MFD by using the PFD/ND/MFD control

pushbuttons on the F/O reconfiguration switching panel

Canceling the malfunction restores normal F/O ND.




MALFUNCTION : UPPER ECAM CDS UNIT FAULT AIRCRAFT : A380 CAUSE : Internal CDS unit power supply failure CONSEQUENCES:

• The UPPER ECAM DU display is blank, • The E/WD is automatically transferred to the lower ECAM DU, replacing the system / ATC page, • Single Chime sounds, • Master Caution light illuminates. • E/WD displays message: CDS EWD DU FAULT • The system / ATC page can be recovered on CAPT MFD or F/O ND by switching the RECONFIG

BUTTON.

Canceling the malfunction restores normal UPR ECAM behavior.




MALFUNCTION : MFD CDS UNIT FAULT CAPT (F/O) AIRCRAFT : A380 CAUSE : Internal CDS unit power supply failure. CONSEQUENCES:

• The CAPT (F/O) MFD screen is blank • Single Chime sounds, • Master Caution light illuminates. • E/WD displays message: CDS CAPT (F/O) MFD DU FAULT

Canceling the malfunction restores normal MFD behavior.




MALFUNCTION : ECP INTEGRATED CTL PANEL FAULT AIRCRAFT : A380 CAUSE : Internal unit controllers failure (dual ECP channels fault) CONSEQUENCES:

• Both ECP CAN busses don’t communicate with their respective IOM (7 & 8). • SD selection push buttons are inoperative. • E/WD displays message: FWS ECP FAULT • Only generic buttons are operative. • Video selection buttons are inoperative. • ETACS, CDSS, CFVS, and CVMS are no more selectable for display on the SD and ND using the

ECP. • Only ETACS and TDS remain operative on PFD & ND due to their controls located on the FCU. • Backlighting control is inoperative.

Canceling the malfunction restores normal MFD behavior.




MALFUNCTION : CDS CURSOR CTL+ KEYBOARD FAULT CAPT (F/O) AIRCRAFT : A380 CAUSE : Internal failure (CCD and KBD simultaneous faults) CONSEQUENCES:

• The CAPT (F/O) KCCU keyboard is inoperative. • The CAPT (F/O) KCCU cursor control device is inoperative. • The CAPT (F/O) mailbox access is impossible. • E/WD displays message: CDS CAPT (F/O) CURSOR CTL+KEYBOARD FAULT

Canceling the malfunction restores normal KCCU behavior.




MALFUNCTION : CDS KEYBOARD FAULT CAPT (F/O) AIRCRAFT : A380 CAUSE : Internal failure CONSEQUENCES:

• The CAPT (F/O) KCCU keyboard is inoperative. • The CAPT (F/O) mailbox access is available through software keyboard • E/WD displays message: CDS CAPT (F/O) KEYBOARD FAULT

Canceling the malfunction restores normal KCCU behavior.




MALFUNCTION : L/G NOT LOCKED DOWN LEFT BLG AIRCRAFT : A380 CAUSE : Affected gear down lock actuator inoperative CONSEQUENCES:

Malfunction is active only when set before L/G is downlocked: • The affected gear does not lock in down position during a landing gear extension sequence, • The affected gear UNLK (red) light remains illuminated, • The affected gear DOWNLOCKED (green) light remains extinguished,

After 60s: • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: L/G GEAR NOT LOCKED DOWN • SD displays WHEEL page: • L/G CTL indication appears amber, • Body doors remain open and appear amber, • During the ECAM procedure:

A gravity extension allows the affected gear to downlock

Canceling the malfunction restores normal operations provided green hydraulic system available and free fall actuator has been reset.




MALFUNCTION : L/G NOT LOCKED UP NOSE GEAR AIRCRAFT : A380 CAUSE : Uplock mechanism mechanical failure CONSEQUENCES:

When the landing gear lever is selected to UP, after 40 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: L/G GEAR NOT LOCKED UP • SD displays WHEEL page

Canceling the malfunction restores normal landing gear operation.




MALFUNCTION : L/G RETRACTION FAULT AIRCRAFT : A380 CAUSE : L/G is not seen in the correct configuration for stowage. Bogie

proximity sensor doesn’t sense a target NEAR condition after take off and indicate a target FAR. It must be the sensor associated with the LGERS side in control.

CONSEQUENCES: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: L/G RETRACTION FAULT • All doors stay open. • SD displays WHEEL page • During the ECAM procedure:

Recycling the lever solves the problem.

Note: as long as the sensors for the other side are in the correct state for retraction, by just cycling the lever should result in a successful retraction.

Canceling the malfunction restores normal retraction.




MALFUNCTION : L/G DOORS NOT CLOSED LEFT BG AIRCRAFT : A380 CAUSE : Actuator locked CONSEQUENCES:

• Affected doors remain open, • Motion and sound effects take place,

After 40 seconds for a retraction and 60 seconds for an extension: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: L/G DOORS NOT CLOSED • SD displays WHEEL page,

- Affected doors position indication is displayed in amber.





MALFUNCTION : L/G LEVER LOCKED (DOWN POS) AIRCRAFT : A380 CAUSE : Internal lock prevents to set L/G lever to UP position CONSEQUENCES:

• L/G cannot be retracted





MALFUNCTION : L/G CONTROL INDICATION SYS FAULT 1 (2) AIRCRAFT : A380 CAUSE : Loss of single channel or both Landing Gear Control Indication

System (LGCIS) are faulty CONSEQUENCES:

Single LGCIS fails: • The LGCIS 2(1) takes control of landing gear operation, • E/WD displays message: L/G CTL 1(2) FAULT • SD displays WHEEL page,

- All system 1 (2) gear indicators show amber XX, • For system 1 only, the L/G red unlock indicator lights remain off whatever the state of the landing

gear.

Both LGCIS fail: • MASTER CAUT lights illuminate, • Single Chime sounds, • E/WD displays message: L/G CTL 1+2 FAULT • SD displays WHEEL page,

- All gear and door indicators show amber XX, • The L/G selector lever is inoperative and locked if in down position

Canceling the malfunction restores normal L/G operation. System operates as per LDG GEAR GRVTY EXTN selector position following ECAM actions.



ATA 32 – STEERING

MALFUNCTION : STEER B/W STEER FAULT AIRCRAFT : A380 CAUSE : Linear Variable Differential Transducer (LVDT) failure of one side CONSEQUENCES:

• BLG aft axes remain centered and locked • E/WD displays message: STEER B/W STEER FAULT • SD displays WHEEL page.

Canceling the malfunction restores normal Body wheel steering.



ATA 32 – STEERING

MALFUNCTION : STEER TILLER FAULT CAPT (F/O) AIRCRAFT : A380 CAUSE : TILLER FAILURE CONSEQUENCES:

• E/WD displays message: STEER CAPT (F/O) STEER TILLER FAULT • SD displays WHEEL page

Canceling the malfunction restores normal steering operation.



ATA 32 – STEERING

MALFUNCTION : STEER N/W SYS FAULT NORMAL (ALTN) AIRCRAFT : A380 CAUSE : NSELV pressure switch fault; ALTSELV failed open CONSEQUENCES:

NORMAL mode failure: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: STEER NORM N/W STEER FAULT • SD displays WHEEL page

ALTN mode failure: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: STEER SEL VLV JAMMED OPEN

Canceling the malfunction restores normal steering operation.



ATA 32 – BRAKES

MALFUNCTION : ANTI SKID FAULT AIRCRAFT : A380 CAUSE : Total loss of the normal/alternate control system (failures of RDCs,

tachometers) CONSEQUENCES:

• Antiskid regulation is lost on normal and alternate system, • Alternate braking without antiskid is possible, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: BRAKES A-SKID FAULT ON ALL L/G • SD displays WHEEL page:

- A-SKID appears amber

Canceling the malfunction restores normal braking.



ATA 32 – BRAKES

MALFUNCTION : AUTO BRK FAULT AIRCRAFT : A380 CAUSE : Loss of auto brake function CONSEQUENCES:

• Normal braking system is cancelled, • Alternate braking with anti skid becomes available • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: BRAKES AUTO BRK FAULT • SD displays WHEEL page:

- AUTO-BRK appears amber

Canceling the malfunction restores normal auto brake.



ATA 32 – BRAKES

MALFUNCTION : EMER BRK FAULT AIRCRAFT : A380 CAUSE : EBCU power supply fails CONSEQUENCES:

• E/WD displays message: BRAKES EMER BRK FAULT • Alternate braking is operative (if BCS is operative).

Canceling the malfunction restores normal braking operation.



ATA 32 – BRAKES

MALFUNCTION : NORM BRK FAULT AIRCRAFT : A380 CAUSE : Normal servo valves fails (WLG) CONSEQUENCES:

If A/C is on ground: • E/WD displays message: BRAKES NORM BRK FAULT • SD displays WHEEL page,

Canceling the malfunction restores normal brake operation. System operates as per switch positions following ECAM actions.



ATA 32 – BRAKES

MALFUNCTION : ALTN + EMER BRK FAULT AIRCRAFT : A380 CAUSE : ABSELV (ALTN Brake SELector Valve) failed + ECBU fault CONSEQUENCES:

• ECBU is inoperative, • E/WD displays message: BRAKES ALTN + EMER BRK FAULT • SD displays WHEEL page,

Canceling the malfunction restores alternate and emergency brake operation. System operates as per switch positions following ECAM actions.



ATA 32 – BRAKES

MALFUNCTION : ALTN BRK FAULT AIRCRAFT : A380 CAUSE : ABSELV failed CONSEQUENCES:

• Normal and emergency braking still available • E/WD displays message: BRAKES ALTN BRK FAULT • SD displays WHEEL page,

Canceling the malfunction restores alternate brake operation. System operates as per switch positions following ECAM actions.



ATA 32 – BRAKES

MALFUNCTION : LOSS OF BRAKING AIRCRAFT : A380 CAUSE : No existing cause: synthetic failure (Disagreement between the

two BSCU channels) CONSEQUENCES:

• Normal braking and autobrake are lost, • Pressing the pedals has no effect on braking action, • After switching off the A/SKID SW, emergency braking is operational.

If auto-brake is selected: • It will not engage.

Canceling the malfunction restores normal braking.



ATA 32 – WHEELS

MALFUNCTION : TIRE PRESS LO (WLG BURST ON GND) L(R) AIRCRAFT : A380 CAUSE : On ground, the tires on left (right) wing L/G burst CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: WHEEL TYRE PRESS LO • On WHEEL system page, Tire 1,2,5, 6 (3,4,7,8) indication appears amber, • Motion, sound, braking, ground handling effects take place.

Canceling the malfunction restores normal tire pressure



ATA 32 – WHEELS

MALFUNCTION : TIRE PRESS LO (BLG BURST ON GND) L AIRCRAFT : A380 CAUSE : On ground, the tires on left body L/G burst CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: WHEEL TYRE PRESS LO • On WHEEL system page, Tire 9,10,13,14,17,18 indications appear amber, • Motion, sound, braking, ground handling effects take place.

Canceling the malfunction restores normal tire pressure



ATA 32 – WHEELS

MALFUNCTION : TIRE PRESS LO (BURST 90 KT) NOSE AIRCRAFT : A380 CAUSE : Low Press (100 psi) + Burst at 90 Kts CONSEQUENCES:

If the aircraft is on ground: • On WHEEL system page, N/W tire pressures indicates 100 psi in amber

As long as the A/C speed is below 80 kts: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: WHEEL TYRE PRESS LO • SD displays WHEEL page.

When the A/C speed exceeds 90 kts: • The nose wheel tires are blown, • The nose wheel tires pressures are 0 psi.

If the aircraft is in flight: • No effect

At landing, as soon as affected L/G is compressed: • The nose wheel tires are blown, • On WHEEL system page, N/W tire pressures indicates 0 psi in amber.

When the A/C speed is below 80 kts: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: WHEEL TYRE PRESS LO • SD displays WHEEL page.

Canceling the malfunction restores normal tire pressure.



ATA 34 – NAVIGATION - ADIRS

MALFUNCTION : IR1 FAULT AIRCRAFT : A380 CAUSE : IR 1 fails internally (ARINC output buses failed) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADIRS ICP IR1 illuminates, • E/WD displays message: NAV IR1 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY • On the CAPT PFD:

- Attitude and heading information are lost, - Red ATT and HDG flags are in view, - Inertial vertical speed is replaced by the barometric vertical speed,

• On the CAPT ND: - Heading information is lost - Red HDG and MAP NOT AVAILABLE flags are in view, - Wind and ground speed values disappear,

• On the CAPT VD:

- Vertical background image is not displayed - Weather / terrain information are lost

Canceling the malfunction restores healthy IR.





• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADIRS ICP IR2 illuminates, • E/WD displays message: NAV IR2 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY • On the F/O PFD:


• On the F/O ND: - Heading information is lost - Red HDG and MAP NOT AVAILABLE flags are in view, - Wind and ground speed values disappear.

• On the F/O VD: - Vertical background image is not displayed - Weather / terrain information are lost






• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADIRS ICP IR3 illuminates, • E/WD displays message: NAV IR3 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY

If ATT HDG selector is on CAPT ON 3 position: • On CAPT PFD:


• On CAPT ND: - Heading information is lost, - Red HDG and MAP NOT AVAILABLE flags are in view, - Wind and ground speed values disappear,

• On the CAPT VD: - Vertical background image is not displayed - Weather / terrain information are lost

If ATT HDG selector is on F/O ON 3 position: • On F/O PFD:

- Attitude and heading information are lost, - Red ATT and HDG flags are displayed, - Inertial vertical speed is replaced by the barometric vertical speed,

• On F/O ND: - Heading information is lost, - Red HDG and MAP NOT AVAILABLE flags are in view, - Wind and ground speed values disappear,

• On the F/O VD:

- Vertical background image is not displayed - Weather / terrain information are lost

If ATT HDG selector is on NORM position: • All inertial parameters are displayed,





MALFUNCTION : ADR1 FAULT AIRCRAFT : A380 CAUSE : ADR 1 fails internally (all ARINC output buses fail) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADR1 P/B SW on ADIRS ICP illuminates, • E/WD displays message: NAV ADR1 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY • On CAPT PFD:

- Airspeed, altitude and mach information is lost - Red SPD and ALT flags are in view

• On CAPT ND: - TAS information is not displayed,

• On the CAPT VD: - Vertical background image is not displayed - Weather / terrain information are lost

Canceling the malfunction restores normal ADR operation.




MALFUNCTION : ADR2 FAULT AIRCRAFT : A380 CAUSE : ADR 2 fails internally (all ARINC output buses fail) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADR2 P/B SW on ADIRS ICP illuminates, • E/WD displays message: NAV ADR2 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY • On F/O PFD:


• On F/O ND: - TAS information is not displayed.

• On the F/O VD: - Vertical background image is not displayed - Weather / terrain information are lost





MALFUNCTION : ADR 3 FAULT AIRCRAFT : A380 CAUSE : ADR 3 fails internally (all ARINC output buses fail) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ADR3 P/B SW on ADIRS ICP illuminates, • E/WD displays message: NAV ADR3 FAULT • SD STATUS page displays message: CAT 3 SINGLE ONLY

If AIR DATA selector is in CAPT ON 3 position: • On CAPT PFD:


• On CAPT ND: - TAS information is not displayed,

• On the CAPT VD: - Vertical background image is not displayed - Weather or terrain information are lost

If AIR DATA selector is in F/O ON 3 position: • On F/O PFD:


• On F/O ND: - TAS information is not displayed.

• On the F/O VD: - Vertical background image is not displayed - Weather or terrain information are lost

If AIR DATA selector is in NORM position: • All anemometric information is displayed.





MALFUNCTION : CAPT & F/O ATT DISAGREE (PITCH) 1 (2) AIRCRAFT : A380 CAUSE : Increase of the IR 1 (2) pitch attitude CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV CAPT & F/O ATT DISAGREE when the detection

threshold (5°) is exceeded • On CAPT (F/O) PFD: pitch attitude displayed increases by 8 degrees in 5 seconds, • Red "CHECK ATT" message flashes for 9 seconds and then remains steady on both PFDs.

Canceling the malfunction restores normal attitude.




MALFUNCTION : CAPT & F/O ATT DISAGREE (BANK) 1 (2) AIRCRAFT : A380 CAUSE : Left drift of IR 1 (2) bank data CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV CAPT & F/O ATT DISAGREE when the detection

threshold (5°) is exceeded • On CAPT (F/O) PFD: bank attitude displayed increases by 8 degrees in 5 seconds, • Red "CHECK ATT" message flashes for 9 seconds and then remains steady on both PFDs.

Canceling the malfunction restores normal roll data.




MALFUNCTION : CAPT & F/O HDG DISAGREE 1 (2) AIRCRAFT : A380 CAUSE : IR 1 (2) heading computation drift CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV CAPT & F/O HDG DISAGREE when the detection

threshold (5° in TRU reference or 7° in MAG reference) is exceeded • On CAPT (F/O) PFD and ND: heading increases by 8 degrees in 5 seconds, • "CHECK HDG" message flashes for 9 seconds and then remains steady on both PFDs and

NDs.

Canceling the malfunction restores normal heading




MALFUNCTION : ADR FAULT (AIRSPEED CHANNEL) 1 (2) (3) AIRCRAFT : A380 CAUSE : Loss of ADR 1 (2) (3) computed airspeed label (n° 206) CONSEQUENCES:

For ADR 1 (2): • On CAPT (F/O) PFD airspeed scale is lost and red SPD flag appears, • On CAPT (F/O) ND, TAS is displayed. • As soon as the aircraft speed changes:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV AIR DATA DISAGREE ADR 1(2) REJECTED BY PRIMs

For ADR3: • As soon as the aircraft speed changes:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV AIR DATA DISAGREE

ADR 3 REJECTED BY PRIMs

If the AIR DATA selector is in CAPT ON 3 or F/O ON 3 position: • On CAPT (F/O) PFD airspeed scale is lost and red SPD flag is in view, • On CAPT (F/O) ND, TAS is displayed.

Canceling the malfunction restores normal ADR airspeed. Reset PRIM1 and PRIM3 in order to remove E/WD flight warning message



ATA 34 – RADIO - NAVIGATION

MALFUNCTION : ILS LOC TRANSMITTER FAULT AIRCRAFT : A380 CAUSE : LOC system of tuned ILS fails CONSEQUENCES:

If an ILS approach has been selected and LOC has been captured: • On both PFD

- LOC scale without diamond is displayed and the FD lateral deviation bar flashes, - ILS ident is not displayed,

• On the ISIS when the LS P/B is pushed, the LOC scale without diamond is displayed.

If an ILS approach has been selected but LOC has not been captured yet: • On both PFD

- LOC indication is not displayed, - ILS ident is not displayed and the lateral FD bar doesn’t flash,

• On the ISIS when the LS P/B is pressed the LOC scale without diamond is displayed.

Canceling the malfunction restores LOC information.




MALFUNCTION : ILS G/S TRANSMITTER FAULT AIRCRAFT : A380 CAUSE : GLIDE system of tuned ILS fails CONSEQUENCES:

If an ILS approach has been selected and G/S has been captured: • On both PFD the GLIDE scale without diamond is displayed and the horizontal FD bar flashes, • On the ISIS when the LS P/B is pushed, the GLIDE scale without diamond is displayed.

If an ILS approach has been selected but G/S has not been captured yet: • On both PFD the GLIDE scale without diamond is displayed and the horizontal FD bar doesn’t

flash, • On the ISIS when the LS P/B is pressed, the GLIDE scale without diamond is displayed.

Canceling the malfunction restores GLIDE information.




MALFUNCTION : LS FAULT (MMR FUNCTION) 1 (2) AIRCRAFT : A380 CAUSE : loss of ILS, GLS and FLS functions of MMR 1 (2) CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV LS1 (2) FAULT • CAT 1 only is available.

If CAPT (F/O) LS P/B is pressed: • On the CAPT (F/O) PFD:

- All LS information are removed, - Red LS, LOC, G/S, F-LOC, F-G/S flags flash for 9 seconds and then remain steady.

• On the F/O (CAPT) ND, in ROSE-LS mode: - All LS information are removed - Red LS1(2), LOC, G/S, F-LOC, F-G/S fags flash for 9 seconds and then remain steady.

• On the ISIS, if LS P/B is pressed (only for ILS1): - All LS information is removed, - Amber LOC and G/S flags appear.

Canceling the malfunction restores normal LS operation.




MALFUNCTION : VOR FAULT (RECEIVER) 1 AIRCRAFT : A380 CAUSE : VOR1 receiver power supply lost CONSEQUENCES:

• VOR1 and MKR call signs are no longer received, • Marker information is no longer displayed when the aircraft over flies the beacon. • On the CAPT ND, in VOR mode:

- VOR red flag is in view, - Red VOR1 and CRSXXX flags are displayed on the right upper corner.

If the CAPT and F/O ADF/VOR 1 selectors are on VOR position: - The associated pointers disappear on both ND in all ROSE modes or ARC mode, - Red VOR1 flag is displayed on both ND in all ROSE modes or ARC mode.

Canceling the malfunction restores normal VOR operation




MALFUNCTION : GPS FAULT (MMR FUNCTION) 1(2) AIRCRAFT : A380 CAUSE : GPS L band antenna failure CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate • E/WD displays message: NAV GPS 1 (2) FAULT

Canceling the malfunction restores normal GPS operation




MALFUNCTION : MMR FAULT (RECEIVER) 1(2) AIRCRAFT : A380 CAUSE : Total unit internal failure CONSEQUENCES:

If MMR 1 is failed: • Single chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV LS 1 FAULT

NAV GPS 1 FAULT • On CAPT PFD, LS 1 information is no longer displayed, • On F/O ND, LS 1 information is no longer displayed, • On ISIS, ILS data is no longer displayed,

If MMR 2 is failed: • Single chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV LS 2 FAULT NAV GPS 2 FAULT • On F/O PFD, LS 2 information is no longer displayed, • On CAPT ND, LS 2 information is no longer displayed,

If MMR 1+2 failed: • Single chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV LS 1+2 FAULT NAV GPS 1 FAULT NAV GPS 2 FAULT • On CAPT and F/O PFD, LS information is no longer displayed, • On CAPT and F/O ND, LS information is no longer displayed, • On ISIS, ILS and GPS data are no longer displayed,

Canceling the malfunction restores normal MMR operation




MALFUNCTION : RA SYS FAULT A(B)(C) AIRCRAFT : A380 CAUSE : RA A(B)(C) receiver power supply lost CONSEQUENCES:

If 1 R/A is failed: • E/WD displays message: NAV RA SYS A (B) (C) FAULT (only on ground with all engines off) • The radio height information is still displayed on CAPT and F/O PFD, • CAT 3 DUAL approach is available.

If 2 R/A are failed: • Single Chime sounds, • MASTER CAUT lights illuminate • E/WD displays message: NAV RA SYS A+B (A+C) (B+C) FAULT • In the FMA part, the message CAT2 is displayed, • The radio height information is still displayed on CAPT and F/O PFD

If all R/A are failed: • Single Chime sounds, • MASTER CAUT lights illuminate • E/WD displays message: NAV RA SYS A+B+C FAULT • Red RA flag appears on both PFDs, • TCAS and GPWS are lost, • CAT I approach is still possible.

Canceling the malfunction restores normal RA operations




MALFUNCTION : ISIS FAULT 1 (2) AIRCRAFT : A380 CAUSE : Total unit internal failure CONSEQUENCES:

If ISIS 1 is failed: • ISIS 1 screen is blank and present no more display, nor backlighting. • The front face keys have no effects. • If ISIS 2 remains in operation, ISIS 2 screen switches automatically to SFD horizon display mode

If ISIS 2 is failed: • ISIS 2 screen is blank and present no more display, nor backlighting. • The front face keys have no effects. • If ISIS 1 remains in operation, ISIS 1 screen remains on SFD horizon display mode

If ISIS 1 and ISIS 2 are failed: • ISIS 1 and 2 screens are blank and present no more display, nor backlighting. • The front face keys have no effects. Canceling the malfunction restores normal ISIS operation. ISIS attitude need manual realignment.



ATA 34 – NAVIGATION - SURVEILLANCE

MALFUNCTION : TAWS FAULT 1(2) AIRCRAFT : A380 CAUSE : TAWS function of AESS 1 (2) failure CONSEQUENCES:

Single TAWS function fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: SURV TAWS 1(2) FAULT • TAWS function of AESS 1(2) is inoperative Dual TAWS functions fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • Amber TERR INOP message on both ND right lower corners and on both VD lower center parts • E/WD displays message: SURV TAWS 1+2 FAULT • TAWS function of AESS1 and AESS2 are inoperative

Canceling the malfunction restores normal TAWS function.




MALFUNCTION : TCAS FAULT 1(2) AIRCRAFT : A380 CAUSE : TCAS function of AESS 1 (2) failure CONSEQUENCES:

Single TCAS function fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: SURV TCAS 1(2) FAULT • Amber TCAS message appears on both PFDs and NDs. Dual TCAS functions fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: SURV TCAS 1+2 FAULT • Amber TCAS message appears on both PFDs and NDs.

Canceling the malfunction restores normal TCAS operation.




MALFUNCTION : PWS FAULT 1(2) AIRCRAFT : A380 CAUSE : PWS function of AESS 1 (2) failure CONSEQUENCES:

Single PWS function fault: • Single chime sounds • MASTER CAUT lights illuminate, • E/WD displays message: SURV PWS 1(2) FAULT • Amber PRED W/S message appears on both NDs only when the A/C is on ground or when the

FLAPS lever position is not set to zero. Dual PWS functions fault: • Single chime sounds • MASTER CAUT lights illuminate, • E/WD displays message: SURV PWS 1 + 2 FAULT • Amber PRED W/S message appears on both NDs only when the A/C is on ground or when the

FLAPS lever position is not set to zero.

Canceling the malfunction restores normal PWS operation.




MALFUNCTION : WXR FAULT 1(2) AIRCRAFT : A380 CAUSE : WXR function of AESS 1(2) failure CONSEQUENCES:

Single WXR function fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • Amber WXR INOP message on both ND right lower corners and on both VD lower center parts • E/WD displays message: SURV WXR 1(2) FAULT • WXR function of AESS 1(2) is inoperative Dual WXR functions fault: • Single Chime sounds, • MASTER CAUT lights illuminate, • Amber WXR INOP message on both ND right lower corners and on both VD lower center parts • E/WD displays message: SURV WXR 1+2 FAULT • WXR function of AESS1 and AESS2 are inoperative

Canceling the malfunction restores normal WXR function.

VALIDITY: FFS



ATA 34 – NAVIGATION - SENSORS

MALFUNCTION : BLOCKED PITOT PROBE ADR 1(2)(3), STBY AIRCRAFT : A380 CAUSE : Obstruction of the hole of the ADR 1(2)(3), SBY MFP pitot probe CONSEQUENCES:

Case of blocked ADR1(2)(3) MFP pitot probe • IAS, TAS, MACH and WIND indications provided by ADR 1(2)(3) are not reliable, • IAS, TAS, MACH provided by ADR1 (2)(3) are frozen as long as the aircraft stays in level flight and

increase/decrease if the aircraft climbs/descends. • As soon as the difference between ADR1 and ADR2 IAS or ADR1 and ADR3 IAS or ADR2 and

ADR3 IAS reaches at or above 16 knots: - Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: NAV AIR DATA DISAGREE

ADR 1(2)(3) REJECTED BY PRIMs

Case of blocked standby MFP pitot probe • IAS indication provided by the standby pitot is not reliable • IAS on ISIS is frozen as long as the aircraft stays in level flight and increases/decreases if the

aircraft climbs/descends. • As soon as the difference between ADR1 and ISIS IAS or ADR3 and ISIS IAS or ADR2 and ISIS

IAS reaches at or above 16 knots: - Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: NAV AIR DATA DISAGREE

STBY INSTRUMENTS REJECTED BY PRIMs

Canceling the malfunction restores CAPT (F/O) (standby) PITOT probe operation. Reset of PRIM 1 and 3 is necessary in order to remove E/WD flight warning message




MALFUNCTION : BLOCKED L(R) STATIC PROBES ADR 1(2)(3) STBY AIRCRAFT : A380 CAUSE : Obstruction of the hole of the ADR 1(2)(3) STBY static probes CONSEQUENCES:

Case of blocked L/R ADR 1(2)(3) static probes

On ground, EXT PWR ON or engines running and before takeoff thrust application: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV STATIC PROBE FAULT L/R ADR 1(2)(3) STAT PROBE

In flight: • ADR1 (2)(3) IAS, TAS, MACH, WIND and ALTITUDE indications are not reliable, • ADR 1(2)(3) IAS is frozen as long as the aircraft stays in level flight and is much lower/higher than

the correct IAS if the aircraft climbs/descends. • ADR 1(2)(3) ALTITUDE is frozen as long as the aircraft is in level flight and increases/decreases

very slowly if the aircraft climbs/descends. • As soon as the difference between ADR1 and ADR2 ALTITUDE or ADR1 and ADR3 ALTITUDE or

ADR2 and ADR3 ALTITUDE reaches at or above 400 feet: - Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: NAV AIR DATA DISAGREE

ADR 1(2)(3) REJECTED BY PRIMs • As soon as ADR 1(2)(3) IAS and ALTITUDE becomes invalid:

- Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: NAV ADR 1(2)(3) FAULT - FAULT light of ADR 1(2)(3) P/B switch on ADIRS ICP illuminates

Case of blocked L/R standby static probes • IAS and ALTITUDE indications on ISIS are not reliable • IAS on ISIS is frozen as long as the aircraft stays in level flight and is much lower/higher than the

correct IAS if the aircraft climbs/descends. • ALTITUDE on ISIS is frozen as long as the aircraft is in level flight and increases/decreases very

slowly if the aircraft climbs/descends. • As soon as the difference between ADR1 and ISIS ALTITUDE or ADR3 and ISIS ALTITUDE or

ADR2 and ISIS ALTITUDE reaches at or above 400 feet: - Single Chime sounds, - MASTER CAUT lights illuminate, - E/WD displays message: NAV AIR DATA DISAGREE

STBY INSTRUMENTS REJECTED BY PRIMs

Canceling the malfunction restores CAPT (F/O) (standby) PITOT probe operation. Reset of PRIM 1 and 3 is necessary in order to remove E/WD flight warning message




MALFUNCTION : LEFT STATIC PROBE HEATING FAULT ADR 1 AIRCRAFT : A380 CAUSE : Breakdown of ADR1 left static probe heater CONSEQUENCES:

• On CAPT PFD: the altitude becomes false when icing conditions are activated • Single Chime sounds • MASTER CAUTION lights illuminate • E/WD displays message: A-ICE STATIC PROBE 1 HEATING FAULT A-ICE ALL PROBES 1 NOT DEICED

Canceling the malfunction restores ADR1 left static probe heater operation.




MALFUNCTION : MULTI FUNCTION PROBE HEATG FAULT ADR1 AIRCRAFT : A380 CAUSE : Breakdown of ADR1 MFP heater CONSEQUENCES:

• On CAPT PFD: the speed becomes false when icing conditions are activated • On CAPT ND: the TAS becomes false when icing conditions are activated • Single Chime sounds • MASTER CAUTION lights illuminate • E/WD displays message: A-ICE PITOT TAT AOA PROBES 1 HEATG FAULT A-ICE ALL PROBES 1 NOT DEICED

Note: TAT and SAT indications become false when icing conditions are activated only if ADR 2 and 3 are failed.

Canceling the malfunction restores ADR1 MFP heater operation.




MALFUNCTION : SIDE SLIP ANGLE PROBE HEATING FAULT ADR1 AIRCRAFT : A380 CAUSE : Breakdown of ADR1 SSA heater CONSEQUENCES:

• Single Chime sounds • MASTER CAUTION lights illuminate • E/WD displays message: A-ICE SIDESLIP PROBE 1 HEATING FAULT A-ICE ALL PROBES 1 NOT DEICED

Canceling the malfunction restores ADR1 SSA heater operation.




MALFUNCTION : STBY STATIC PROBE HEATG FAULT ISIS 1+2 AIRCRAFT : A380 CAUSE : Breakdown of ISIS 1+2 Static Probe heater CONSEQUENCES:

• Single Chime sounds • MASTER CAUTION lights illuminate • On SFD: altitude value becomes false when icing conditions are activated • E/WD displays message: A-ICE STBY STATIC PROBE HEATG FAULT

Canceling the malfunction restores ISIS 1+2 Static Probe heater operation.




MALFUNCTION : STBY PITOT PROBE HEATG FAULT ISIS 1+2 AIRCRAFT : A380 CAUSE : Breakdown of ISIS 1+2 Pitot Probe heater CONSEQUENCES:

• On SFD: speed value becomes false when icing condition are activated • Single Chime sounds • MASTER CAUTION lights illuminate • E/WD displays message: A-ICE STBY PITOT PROBE HEATG FAULT

Canceling the malfunction restores ISIS 1+2 Pitot Probe heater operation.




MALFUNCTION : FM / GPS POSITION DISAGREE AIRCRAFT : A380 CAUSE : Deviation between FMC-A, FMC-B and FMC-C from either GPS 1

or GPS 2 by more than 0.5 NM of latitude or longitude CONSEQUENCES:

Note: GPS PRIMARY must have been selected for 10 minutes

After 10 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: NAV FM / GPS POS DISAGREE

Canceling the malfunction restores normal position.




MALFUNCTION : GPS PRIMARY LOST AIRCRAFT : A380 CAUSE : Number of satellites tracked by the GPS reduces below 4 CONSEQUENCES:

• Amber GPS PRIMARY LOST message is displayed on both NDs, • MFD scratchpad line shows amber GPS PRIMARY LOST message • Amber TERR flag appears on both ND and VD

Canceling the malfunction restores normal position.



ATA 34 – NAVIGATION - OANS

MALFUNCTION : AIRPORT NAV FAULT AIRCRAFT : A380 CAUSE : Airport navigation computer internal failure CONSEQUENCES:

• The airport navigation system is inoperative. • The ND displays blank video image with amber NOT AVAIL message when airport navigation

function (EFIS-CP RANGE button on ZOOM notch) is selected.

After 45s: • E/WD displays message: NAV ARPT NAV FAULT

Canceling the malfunction restores normal airport navigation system after 45s. VALIDITY: FFS



ATA 35 – OXYGEN

MALFUNCTION : CKPT BOTTLE PRESS LO AIRCRAFT : A380 CAUSE : Leak in the cockpit oxygen system CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: OXY CKPT BOTTLE PRESS LO • SD displays DOOR/OXY page.

- Amber CKPT legend - Amber indication REGUL PR LO (on ground only)

Canceling the malfunction restores the oxygen pressure to 1850 PSI.




MALFUNCTION : BLEED FAULT / HP BLEED VLV NOT OPEN 1(3) AIRCRAFT : A380 CAUSE : High Pressure valve 1 (3) stuck in current position CONSEQUENCES:

If HP valve 1(3) is stuck open (engine low speed) and engine 1(3) speed increases when bleed temperature reaches 290 deg C:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of BLEED 1 (3) P/B SW illuminates, • E/WD displays message: AIR ENG 1 (3) BLEED FAULT • SD displays BLEED page,

- Engine 1(3) bleed temperature is displayed in amber, - Bleed valve 1 (3) is closed amber, - HP valve 1 (3) is closed amber,

After a few seconds: • Cross-bleeds open • Engine 1(3) bleed temperature decreases to engine 2(4) temperature and is displayed in green

If HP valve 1(3) is stuck closed (engine normal speed) and engine 1(3) speed decreases:

• E/WD displays message: AIR ENG 1 (3) HP BLEED VLV NOT OPEN • SD displays BLEED page:

- HP valve 1 (3) is closed amber, - Bleed valve 1(3) is opened green.

Canceling the malfunction restores normal air BLEED generation.




MALFUNCTION : BLEED FAULT / BLEED NOT CLOSED 1(4) AIRCRAFT : A380 CAUSE : Bleed pressure regulating valve 1(4) stuck in open position CONSEQUENCES:

When APU BLEED is selected ON and engine 1(4) power is increased: When engine 1(4) bleed pressure exceeds the APU bleed pressure: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of ENG 1(4) BLEED P/B SW illuminates, • E/WD displays message: AIR ENG 1(4) BLEED NOT CLOSED • SD displays BLEED page,

- Bleed valve 1(4) is open amber.

When engines 1 and 2 (3 and 4 speed) increase, if bleed valve 1(4) outlet pressure is above 60 psi for at least 15 seconds:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of BLEED 1(4) P/B SW illuminates, • E/WD displays message: AIR ENG 1(4) BLEED FAULT • SD displays BLEED page,

- Engine 1(4) bleed pressure is amber while overpressure condition is valid, - Bleed valve 1(4) is open amber, - HP valve 1(4) is closed amber.

Canceling the malfunction restores normal air bleed operation and parameters.




MALFUNCTION : BLEED TEMP LO 1 AIRCRAFT : A380 CAUSE : Fan Air Valve 1 low temperature regulation (thermostat) CONSEQUENCES:

If the aircraft is in cruise with WING ANTI ICE P/B SW indicates ON, after 60 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: AIR ENG BLEED TEMP LO

ON BLEED 1 • SD displays BLEED page,

- Precooler outlet temperature 1 decreases below 150 deg C and is displayed in amber.

Canceling the malfunction restores normal air BLEED operation and parameters.




MALFUNCTION : INR WING LEAK LEFT (RIGHT) AIRCRAFT : A380 CAUSE : LEFT (RIGHT) inner wing duct leak CONSEQUENCES:

When temperature in the vicinity of the leak detection loop reaches 124 deg C: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light of BLEED 2(3) P/B SW illuminates, • E/WD displays message: AIR L(R) INR WING LEAK • SD displays BLEED page,

- Flow control valve 2(3) closes and is displayed in amber, - Bleed valve 2(3) closes and is displayed in amber, - HP valve 2(3) is closed and displayed in amber, - Engine 2(3) bleed pressures decrease to 0 psi and bleed temperatures decrease to SAT

Canceling the malfunction restores normal air BLEED operation and parameters.




MALFUNCTION : APU BLEED FAULT AIRCRAFT : A380 CAUSE : APU bleed valve stuck closed CONSEQUENCES:

If the aircraft is in cruise below 22500 ft, when APU BLEED is selected ON, after 10 seconds: • Single Chime sounds, • MASTER CAUT lights illuminate, • APU BLEED P/B FAULT light illuminates • E/WD displays message: AIR APU BLEED FAULT • SD displays BLEED page,

- APU Bleed Valve is closed and displayed in amber - APU Isolation Valve is closed and displayed amber (after 20s)

Canceling the malfunction restores normal APU BLEED function.




MALFUNCTION : AVNCS CPIOM-A FAULT (BLEED) 1 (ALL) AIRCRAFT : A380 CAUSE : Total internal failure (host computer failure) CONSEQUENCES:

Single Failure • The relevant CPIOM fails. • All supported applications are no longer executed. • Failsafe application states are selected according own A/C logics and according to the state of

remaining applications on others CPIOM-A.

All CPIOM Failure • All CPIOM-B fail. • All supported applications are no longer executed. • Single Chime sounds, • Master Caution light illuminates, • E/WD displays message: AIR ENG 1 BLEED FAULT AIR ENG 2 BLEED FAULT AIR ENG 3 BLEED FAULT AIR ENG 4 BLEED FAULT AIR XBLEED FAULT

Canceling the malfunction restores normal CPIOM-A functions. VALIDITY: FFS




MALFUNCTION : AVNCS CPIOM-B FAULT (COND) 1 (ALL) AIRCRAFT : A380 CAUSE : Total internal failure (host computer failure) CONSEQUENCES:

Single Failure • The relevant CPIOM fails. • All supported applications are no longer executed. • Failsafe application states are selected according own A/C logics and according to the state of

remaining applications on others CPIOM-B. • E/WD displays message: COND FWD VENT CTL REDUNDANCY LOST COND TEMP CTL REDUNDANCY LOST CAB PRESS AUTO CTL FAULT AUTO CTL SYS 1 FAULT

All CPIOM Failure • All CPIOM-B fail. • All supported applications are no longer executed. • Single Chime sounds, • Master Caution light illuminate, • SD display COND page

- All temperature fields are XX amber - TEMP CTL 1 and 2 are amber - FWD VENT CTL 1 and 2 are amber - AFT VENT CTL 1 and 2 are amber

• E/WD displays message: CAB PRESS AUTO CTL FAULT AUTO CTL SYS 1+2+3+4 FAULT COND FWD VENT CTL DEGRADED COND TEMP CTL FAULT COND AFT VENT CTL DEGRADED

Canceling the malfunction restores normal CPIOM-B functions. VALIDITY: FFS




MALFUNCTION : AVNCS CPIOM-C FAULT (COCKPIT) 1 (2) AIRCRAFT : A380 CAUSE : Total internal failure (host computer failure) CONSEQUENCES:

• The relevant CPIOM fails. • All supported applications are no longer executed. • Failsafe application states are selected according own A/C logics and according to the state of

remaining applications on others CPIOM-C.

When a single failure is selected: • E/WD displays message: FCTL FCDC 1 (2) FAULT FWS FWS 1 (2) FAULT

When a dual failure is selected: • Dual FWCs failure inhibits all warning message generation. • There is no more FCDC, FCU BACKUP, FWC and WBBC available • E/WD displays message: CDS FWS 1+2 & FCDC 1+2 FAULT

Canceling the malfunction restores normal CPIOM-C functions. VALIDITY: FFS




MALFUNCTION : AVNCS CPIOM-D1 FAULT (ATC) AIRCRAFT : A380 CAUSE : Total internal failure (host computer failure) CONSEQUENCES:

• The relevant CPIOM fails. • All supported applications are no longer executed. • CPIOM-D1 failure leads to ATC and ADS communications interruption. • Single Chime sounds, • Master Caution light illuminates, • E/WD displays message: COM ATC DATALINK FAULT COM ADS DATALINK FAULT

Canceling the malfunction restores normal CPIOM-D1 functions. All connections are lost, and all applications are reset on the affected CPIOM-D. VALIDITY: FFS




MALFUNCTION : AVNCS CPIOM-D3 FAULT (ACR) AIRCRAFT : A380 CAUSE : Total internal failure (host computer failure) CONSEQUENCES:

• The relevant CPIOM fails. • All supported applications are no longer executed. • CPIOM-D3 failure leads to a total datalink loss. • Single Chime sounds, • Master Caution light illuminates, • E/WD displays message: COM DATALINK FAULT

Canceling the malfunction restores normal CPIOM-D functions. All connections are lost, and all applications are reset on the affected CPIOM-D. VALIDITY: FFS



ATA 42 – IMA – DEMONSTRATION FAULTS

MALFUNCTION : CAB PRESS AUTO CTL FAULT / BACKUP MODE 1(ALL) AIRCRAFT : A380 CAUSE : ACP application passivation by the CPIOM host after three

consecutive application failure detections.. CONSEQUENCES:

• The relevant CPIOM stops and inhibits the application after three consecutive application faults and resets.

• The application is no longer executed. • Failsafe application states are selected according own A/C logic and according to the state of

remaining applications on others CPIOM-B.

One ACP inoperative • E/WD displays message: CAB PRESS AUTO CTL FAULT AUTO CTL SYS 1 FAULT

ALL ACP inoperative • Single Chime sounds, • Master Caution light illuminates, • E/WD displays message: CAB PRESS AUTO CTL FAULT AUTO CTL SYS 1+2+3+4 FAULT CAB PRESS IN BACK UP MODE

Canceling the malfunction restores normal CPIOM-B / ACS application function. VALIDITY: FFS




MALFUNCTION : COND ZONE TEMP REGUL FAULT AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive

application failure detections.




remaining applications on others CPIOM-B. • Single Chime sounds, • Master Caution light illuminates, • E/WD displays message: COND TEMP CTL FAULT

Canceling the malfunction restores normal CPIOM-B application function. VALIDITY: FFS




MALFUNCTION : F/CTL FCDC FAULT 1 (2) AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive




• The application is no more executed.

When single failure is activated: • One single FCDC failure has no effect on A/C. • E/WD displays message: FCTL FCDC 1 (2) FAULT

When dual failure is activated: • Dual FCDCs failure leads to inhibit all flight control displays and warnings on CDS. • Tripple click is heard if AP is engaged, • Single Chime sounds, • Master Caution light illuminates. • E/WD displays message: FCTL FCDC 1+2 FAULT

Canceling the malfunction restores normal CPIOM-C application function. VALIDITY: FFS




MALFUNCTION : AUTO FLT FCU BACKUP FAULT 1 (2) AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive




• The application is no longer executed. • One single FCU BACKUP failure has effect only on associated MFD. • Dual FCU BACKUP failure leads to inhibit all access to FCU functions through MFDs.

If AFS FCU is detected as failed by FWS: • Single Chime sounds. • Master Caution light illuminates • E/WD displays message: AUTO FLT CAPT (F/O) AFS BKUP CTL FAULT

Canceling the malfunction restores normal CPIOM-C application function.

VALIDITY: FFS




MALFUNCTION : ELEC NETWORK MANAGEMENT UNIT (ENMU) FAULT 1 AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive





remaining applications on others CPIOM-E. • Single Chime sounds, • Master Caution light illuminate, • E/WD displays message: ELEC ELEC NETWORK MANAGEMENT 1 FAULT

Canceling the malfunction restores normal CPIOM-E application function. VALIDITY: FFS




MALFUNCTION : FWS FAULT 1 (2) AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive




• The application is no longer executed.

Single FWS failure: • No effect on A/C. • E/WD displays message FWS FWS 1 (2) FAULT

Dual FWSs failure leads to inhibit all warnings on CDS. • No effect on A/C. • E/WD displays message FWS FWS 1+2 FAULT

Canceling the malfunction restores normal CPIOM-C application function. VALIDITY: FFS




MALFUNCTION : FUEL QUANTITY AND MANAGEMENT SYSTEM FAULT 1 (2) AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive

application failure detections. (This failure is absolutely unrealistic and shall only be used for demonstration)

CONSEQUENCES:



One single FQMS failure • No effect on A/C. • SD display FUEL page • E/WD displays message: FUEL FQMS 1 (2) FAULT

Dual FQMSs failure: • Single Chime sounds, • Master Caution light illuminates, • SD display FUEL page • E/WD displays message: FUEL FQMS 1+2 FAULT

Canceling the malfunction restores normal CPIOM-F application function. VALIDITY: FFS




MALFUNCTION : BRAKES SYS FAULT 1 (2) AIRCRAFT : A380 CAUSE : Application passivation by the CPIOM host after three consecutive


(This failure is absolutely unrealistic and shall only be used for demonstration) CONSEQUENCES:



One single BCS failure: • E/WD displays message: BRAKES CTL 1 (2) FAULT

Dual BCSs failure: • Single Chime sounds, • Master Caution light illuminates, • SD display WHEEL page • E/WD displays message: BRAKES A-SKID FAULT ON ALL L/G

Canceling the malfunction restores normal CPIOM-G application function. VALIDITY: FFS



ATA 44 – CABIN SYSTEMS

MALFUNCTION : CIDS CABIN COM FAULT AIRCRAFT : A380 CAUSE : CIDS system detect that upper deck passenger address has failed CONSEQUENCES:

• Major failure affecting A/C dispatch. • No visible or audible effect in cockpit coming from the upper deck. • Single chimes sounds, • Master Caution light illuminates, • E/WD displays message CAB COM CIDS CABIN COM FAULT

UPPER DECK PA FAULT Canceling the malfunction restores normal PA behavior.




MALFUNCTION : COM OIS/AVNCS DATA XFR FAULT ALL AIRCRAFT : A380 CAUSE : Dual SCI internal failures CONSEQUENCES:

• SCI failures are only presented to the crew when both SCI have failed. • Both SCI stop all parameters transmission. • OpenWorld applications may be affected by the loss of some transmitted parameters depending

on the design of these applications.

After fault confirmation delay: • E/WD displays message: COM NSS/AVNCS DATA XFR FAULT

Canceling the malfunction restores normal SCI behavior. VALIDITY: FFS




MALFUNCTION : OIS FAULT CAPT (F/O) AIRCRAFT : A380 CAUSE : Internal OIT power supply failure CONSEQUENCES:

• The relevant OIT becomes blank. • OpenWolrd applications can no longer be used on the affected OIT. • When both OITs are failed, the crew shall use the servers in laptop configuration as backup,

Canceling the malfunction restores normal OIT behavior. VALIDITY: FFS



ATA 49 – APU

MALFUNCTION : APU FAULT (START/RUNNING) AIRCRAFT : A380 CAUSE : Fuel control unit failed CONSEQUENCES:

If the APU is not running and normal starting procedure carried out: • APU start is aborted, • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on APU MASTER P/B SW illuminates • E/WD displays message: APU FAULT • SD displays APU page

If APU is running on ground: • APU shutdown occurs and the APU cannot be restarted • Single chime sounds, • MASTER CAUT lights illuminate, • FAULT light on APU MASTER P/B SW illuminates • E/WD displays message: APU FAULT

AUTO SHUTDOWN • SD displays APU page

If APU is running in flight: • The APU continues to run, • On SD APU page: amber message FUEL PRESS LO

Canceling the malfunction restores normal APU operation.



ATA 49 – APU

MALFUNCTION : APU FAULT (N1 OVERSPEED) AIRCRAFT : A380 CAUSE : Loss of N1 due to overspeed CONSEQUENCES:

• APU shutdown occurs and the APU cannot be restarted • Single chime sounds, • MASTER CAUT lights illuminate, • FAULT light on APU MASTER P/B SW illuminates • E/WD displays message: APU FAULT

AUTO SHUTDOWN • SD displays APU page




ATA 49 – APU

MALFUNCTION : APU OIL QTY INC/DEC AIRCRAFT : A380 CAUSE : APU oil quantity varies according to the quantity selected on the

IOS PARAMETER : min value max value rate

OIL QTY 0 L 19 L 1 L/s CONSEQUENCES:

When the APU is not running and A/C is on ground:

When the oil quantity drops to 11 L • On SD APU page OIL LO LVL is displayed flashing green.

When the APU is running:

When the oil quantity drops to 9 L • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on APU MASTER p/b sw illuminates, • E/WD displays message: APU FAULT • SD displays APU page

NOTE: APU auto shut down occurs only on ground




ATA 52 - DOOR

MALFUNCTION : FWD CARGO DOOR NOT CLOSED AIRCRAFT : A380 CAUSE : Switch faulty CONSEQUENCES :

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: DOOR FWD CARGO NOT CLOSED • SD displays DOOR page,

- FWD cargo door symbol is displayed in amber,

Before take off power application: • AGS and CAB PRESS are not available, • On PRESS system page: all outflow valves are opened, • On BLEED system page: all Flow Control Valves are closed.

If A/C is in flight: • CAB PRESS remain operative

Canceling the malfunction restores normal doors operation.



ATA 52 - DOOR

MALFUNCTION : MAIN SLIDE FAULT (NOT ARMED) 1L AIRCRAFT : A380 CAUSE : Switch faulty CONSEQUENCES :

• E/WD displays message: DOOR MAIN 1L SLIDE FAULT • SD displays DOORS page,

- Symbol "SLIDE" of MAIN 1L Pax door disappear.

Canceling the malfunction restores normal doors and slide operations.



ATA 70 RR – ENGINE FAILURES

MALFUNCTION : ENG FAIL (NO DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 - RR CAUSE : Engine flame out CONSEQUENCES:

• Rapid decrease in EGT, N1, N2, N3, FF and THR, • No vibrations, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD (during around 4

seconds on ground), • N1, N2, N3 parameters freely decrease, • During the ECAM procedure:

While the failure is activated any engine relight attempt is unsuccessful: - E/WD displays message: ENG 1(2)(3)(4) START FAULT – NO LIGHT UP

Canceling the malfunction restores normal engine performance. Engine can be restarted and the ECAM engine message will then disappear.




MALFUNCTION : ENG FAIL (DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : LP compressor damage due to the absorption of foreign object CONSEQUENCES:

• Rapid decrease in N1, N2, N3, FF and THR, • N1decreases quickly to 0% (no N1 rotation due to fan deterioration), • Fan vibration peak takes place during N1 decrease and stabilizes higher than normal, • Sound effect takes place • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD (during around 4

seconds on ground), • During the ECAM procedure:

While the failure is activated any engine relight attempt is unsuccessful: - E/WD displays message: ENG 1(2)(3)(4) START FAULT – NO LIGHT UP





MALFUNCTION : ENG FAIL (SERIOUS DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : Foreign object ingestion – Eng blade disintegration CONSEQUENCES:

As soon as N1 is above 68% • THR, N1 decrease with a large reduction, N2, N3 and Fuel Flow small and slow reduction

Then all engine parameters move erratically lower and upper than in normal operation,

• Vibration levels reach advisories, • Oil temperature reaches the amber value, • EWD displays message: ENG 1(2)(3)(4) OIL TEMP HIGH, • Nacelle temperature pulses, • Aircraft yaws with loss of thrust, • Sound effects take place. • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

Then: • Single Chime sounds, • MASTER CAUT lights illuminate, • THR value drops, • Complete loss of engine thrust, • EGT decreases, • Oil temperature decreases, • Nacelle temperature slowly decreases, • High vibration levels decrease, but stay just above advisories value • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD.





MALFUNCTION : BIRD INGESTION ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : Bird ingestion CONSEQUENCES:

As soon as N1 is above 68% • THR, N1decrease with a large reduction, N2, N3 and Fuel Flow small reduction,

Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates without exceeding over limit, • N1 vibration level reaches advisory, • Aircraft yaws with loss of thrust, • Sound effects take place, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

Then after 30 seconds: • Stall effects disappear, • N1 vibrations and EGT return to nominal operation.

Canceling the malfunction restores normal engine performance.




MALFUNCTION : ENG STALL ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : Compressor stall CONSEQUENCES:

As soon as N1 is above 68% • THR, N1 and decrease with a large reduction, N2, N3 and Fuel Flow small reduction, Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates but below over limit, • Sound effects take place, • Motion effects take place, • Relevant engine vibrations increase, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

As soon as thrust lever of relevant engine is reduced and actual N1 is lower than 50% • Stall effects disappear

The effects should reoccur when thrust lever is increased and N1 is greater than 60% • THR, N1 decrease with a large reduction, N2, N3 and Fuel Flow small reduction, Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates but below over limit, • Sound effects take place, • Motion effects take place, • Relevant engine vibrations increase, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

As soon as thrust lever of relevant engine is reduced again and actual N1 is lower than 50% • Stall effects disappear

Canceling the malfunction restores normal engine operation.




MALFUNCTION : REVERSER LOCKED ENG 2 (3) AIRCRAFT : A380 RR CAUSE : Thrust reverser doors stuck in position. Reverser retracted: one primary lock clamped in locked position CONSEQUENCES:

If reverser doors are previously fully stowed (engine in forward thrust): When reverse control lever is pulled in max reverse position: • The thrust reverser cannot be deployed, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2(3) REVERSER LOCKED • The amber REV x indication is displayed on EWD and disappears after 20s, • REV IDLE is automatically selected by EEC.

In order to restore normal operation, cancel the malfunction and execute a new reverse sequence




MALFUNCTION : REV UNLOCKED(DURING RETRACTION)-ON GROUND ENG 2(3) AIRCRAFT : A380 RR CAUSE : Thrust reverser doors stuck in position. Reverser deployed: reverser jammed in position. CONSEQUENCES:

If reverser doors are previously fully deployed (engine in reverse thrust): When reverse control lever is pulled in idle position: • The reversers cannot be retracted, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2(3) REVERSER UNLOCKED • The amber REV x indication is displayed on EWD. • Thrust is limited to idle by the EEC.





MALFUNCTION : REV UNLOCKED ENG 2(3) AIRCRAFT : A380 RR CAUSE : Locks detected unlocked with the throttle in forward position (door

position remains below 5% of maximum door deployment) CONSEQUENCES:

If reverser doors are previously fully stowed:

As soon as the failure is inserted: If the A/C is on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • The amber REV x indication is displayed on EWD. • E/WD displays message: ENG 2 (3) REVERSER UNLOCKED • REV IDLE is not automatically selected by EEC If the A/C is in flight: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER UNLOCKED • IDLE is not automatically selected by EEC • An amber attention getting box appears on the EWD, • The amber REV x indication flashes on EWD for a few seconds, and then remains displayed





MALFUNCTION : REV INHIBITED ENG 2(3) AIRCRAFT : A380 RR CAUSE : reverser de-activated by maintenance action. CONSEQUENCES:

If reverser doors are previously fully stowed and the engines are not running

As soon as the failure is inserted on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER INHIBITED • If throttle lever is set on reverser position, thrust reverser doors remain stuck in closed position. • As soon as the engine is started, the effects are latched until the engine is shut down. Note: do not use ENG QUICK START as effects are not as advertised.

Canceling the malfunction restores normal engine operation (provided the engine is not started).




MALFUNCTION : REV FAULT ENG 2(3) AIRCRAFT : A380 RR CAUSE : ETRAC overheat or TRPU overheat CONSEQUENCES:


As soon as the failure is inserted on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER FAULT • If throttle lever is set on reverser position, thrust reverser doors remain stuck in closed position and

EWD displays message ENG 2 (3) REVERSER LOCKED.

In order to restore normal operation, cancel the malfunction and execute a master lever reset.



ATA 70 RR – ENGINE START

MALFUNCTION : START FAULT (ENG STALL) - HUNG START ENG 1(2) AIRCRAFT : A380 RR CAUSE : Start fails (no sufficient starter air pressure) CONSEQUENCES:

If A/C is on ground: During AUTO start: • N1, N2, N3 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL • SD displays ENGINE page • The SAV (Starter Air Valve), FUEL and IGNITERS are commanded off, • As soon as N3 decreases below 10% (starter air valve re-engagement level), the EEC commands

starter air valve to open position and performs a dry crank for a minimum time of 20s and until the EGT goes below 150°C.

• A second start is automatically initiated with the same effects if the malfunction is still active. After the second dry crank sequence (for a minimum time of 20s and until the EGT goes below 150°C, the EEC closes the SAV and aborts the automatic start.

• FAULT light on the master lever is ON. During MAN start: • N1, N2, N3 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL • SD displays ENGINE page, • The pilot must shut down the engine, and perform DRY CRANK according to ECAM procedure,

If A/C is in flight: During AUTO start: • N1, N2, N3 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL • SD displays ENGINE page, • Manual shut down is required according to ECAM procedure. During MAN start: • N1, N2, N3 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL • SD displays ENGINE page,



• The pilot must shut down the engine, and perform DRY CRANK according to ECAM procedure,

Note: If the fault is removed at any time during the start sequence, the start sequence shall continue as if hot start conditions were self-cleared during the start attempt.

Canceling the malfunction restores normal engine operation. After engine shut down, the engine ECAM message will disappear when a new start is performed.




MALFUNCTION : START FAULT (EGT OVER LIMIT) - HOT START ENG 3(4) AIRCRAFT : A380 RR CAUSE : Incorrect engine operation CONSEQUENCES:

If A/C is on ground:

During AUTO start: • N3 acceleration is slower than normal, • EGT acceleration is higher than normal, • When EGT reaches over limit: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT

• SD displays ENGINE page, • The SAV (Starter Air Valve), FUEL and IGNITERS are commanded off, • As soon as N3 decreases below 10% (starter air valve re-engagement level), the EEC

commands starter air valve to open position and performs a dry crank for a minimum time of 20s and until the EGT goes below 150°C.

• A second start is automatically initiated with the same effects if the malfunction is still active. After the second dry crank sequence (for a minimum time of 20s and until the EGT goes below 150°C, the EEC closes the SAV and aborts the automatic start,

• FAULT light on master lever is ON,

During MAN start: • N3 acceleration is slower than normal, • EGT acceleration is higher than normal, • When EGT reaches over limit:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT • SD displays ENGINE page,

• The pilot must shut down the engine, and perform DRY CRANK according to ECAM procedure.

If A/C is in flight:

During AUTO or Manual start: • N3 acceleration is slower than normal, • EGT acceleration is higher than normal, • When EGT reaches over limit:

• Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT • If N3 > 50%, the message ENG 3(4) EGT OVERLIMIT appears.



• SD displays ENGINE page, • Manual shut down is required according to ECAM procedure.






MALFUNCTION : IGN A+B FAULT ENG 1(2) AIRCRAFT : A380 RR CAUSE : Ignition plugs failed CONSEQUENCES:

If A/C is on ground: During AUTO start: • EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT – NO LIGHT UP

ENG 1(2) IGN A (B) FAULT • SD displays ENGINE page, • The FUEL and IGNITERS are commanded off, • If the EGT > 150 Deg.C, the EEC performs a crank sequence during 30s and until the EGT goes

below 150 Deg.C, • A second start attempt is automatically initiated, • Single Chime sounds, • MASTER CAUT lights illuminate, • Fault light on Master Lever is ON, • E/WD displays message: ENG 1(2) START FAULT – NO LIGHT UP

ENG 1(2) IGN A+B FAULT • Automatic start aborts.

During MAN start: • EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT – NO LIGHT UP

ENG 1(2) IGN A+B FAULT • The pilot must shutdown the engine and perform a dry crank according to ECAM procedure,

If A/C is in flight: • EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT – NO LIGHT UP

ENG 1(2) IGN A+B FAULT

Canceling the malfunction restores normal IGNITION operation. After engine shut down, the engine ECAM message will disappear when a new start is performed.




MALFUNCTION : START VLV FAULT (CLOSED/NOT CLOSED) ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : start valve stuck in position CONSEQUENCES:

Before start procedure (starter valve in closed position):

During start sequence, few seconds after the master switch is set to ON position • Starter valve remains closed • The symbol of starter valve becomes amber on the ENGINE page, • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, • E/WD displays message: ENG (1)(2)(3)(4) START VLV FAULT VLV STUCK CLOSED • FAULT light on master lever is ON (during automatic start only), • SD displays ENGINE page.

During start procedure (starter valve in open position): • Start sequence takes place normally, • The symbol of starter valve becomes amber on the ENGINE page, • Starter valve remains open, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG (1)(2)(3)(4) START VLV FAULT START VLV NOT CLOSED • SD displays ENGINE page.

Canceling the malfunction restores starter air valve operation:

• after engine shut down, the engine ECAM message will disappear when a new start is performed, • after a manual start, execute a master lever reset to remove FWC message and amber symbol on

the ENGINE system page.




MALFUNCTION : ENG HP FUEL VALVE FAULT (HPV NOT OPEN / NOT CLOSED) ENG 3 (4)

AIRCRAFT : A380 RR CAUSE : Fuel valve stuck in position CONSEQUENCES:

If engine is not running (HP fuel valve not open): During automatic start sequence, a few seconds after EEC commands ignition and fuel: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) HP FUEL VLV FAULT HP FUEL VLV NOT OPEN • SD displays ENGINE page.

With engine running (HP fuel valve not closed): A few seconds after master switch is set to OFF position: • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) HP FUEL VLV FAULT HP FUEL VLV NOT CLOSED • SD displays ENGINE page.

- LP fuel valve closes and after approximately 40 seconds, engine parameters decrease.

After engine shut down, the engine ECAM message will disappear when a new start is performed. Canceling the malfunction restores HP fuel valve operation



ATA 70 RR – ENGINE CONTROLS

MALFUNCTION : FADEC FAULT ENG 1(4) AIRCRAFT : A380 RR CAUSE : FADEC output bus driver fails CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) FADEC FAULT • SD displays ENGINE page,

- All engine indications are lost on ENGINE page and on EWD, but the engine is still running and controllable.

- HYD, BLEED, ELEC AC pages must be used to confirm engine status.





MALFUNCTION : NORM MODE FAULT – ALTN MODE ENG 2(3) AIRCRAFT : A380 RR CAUSE : EGT failure CONSEQUENCES:

• ENG 2(3) EGT indication is flagged (amber XX) • THR indication changes if aircraft is not in take-off phase, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2(3) NORM MODE FAULT ENG 2(3) ALTN MODE

In order to restore normal operation:

• Cancel malfunction on the Instructor Station, • Select ALTN mode P/B ON then OFF.




MALFUNCTION : EGT FAILED BLANKED ENG 1(2)(3)(4) AIRCRAFT : A380 RR CAUSE : EGT sensor failure CONSEQUENCES:

• ENG 1(2)(3)(4) EGT indication is flagged (amber XX), • No ECAM message is displayed. • Canceling the malfunction restores normal engine operation.



ATA 70 RR – ENGINE FLUIDS

MALFUNCTION : FUEL FILTER CLOGGED ENG 3 (4) AIRCRAFT : A380 RR CAUSE : Clogging of fuel filter CONSEQUENCES:

If engine is running: • E/WD displays message (on ground): ENG 3(4) FUEL FILTER CLOGGED • An amber attention getting box appears on Engine system page, • SD displays ENGINE page,

- CLOGGED indication appears in amber under the fuel flow indication.

Canceling the malfunction restores normal engine fuel indication.




MALFUNCTION : OIL PRESS (INC/DEC) ENG 3 (4) AIRCRAFT : A380 RR CAUSE : Oil pump fails or oil jet clogging PARAMETER : min value max value rate

OIL PRESS 0 PSI 440 PSI 10 PSI/s CONSEQUENCES:

When engine is running: • Oil pressure indication is green. When oil pressure reduces below oil low press amber limit (dependant on N3 shaft speed): • If N3 is between 70% and 95%, advisory limit is between 25 and 50 psi (linear interpolation), above

95% N3 advisory limit is 50 psi. • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 3(4) OIL PRESS LO (amber alert) • SD displays ENGINE page,

- Amber box appears on ENGINE page and oil pressure indication turns amber, - After reducing thrust lever, oil pressure may decrease.

When oil pressure reduces below red line limit (25PSI): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 3(4) OIL PRESS LO (Red Alert) • Amber box is still displayed on ENGINE page and oil pressure indication turns red.

Canceling the malfunction restores normal engine oil pressure.




MALFUNCTION : OIL TEMP (INC/DEC) ENG 1(2) AIRCRAFT : A380 RR PARAMETER : min value max value rate

OIL TEMP TAT 250°C 20°C/s CAUSE : Incorrect engine operation CONSEQUENCES:

Engines running: • Oil temperature indication is green. When oil temperature exceeds the amber limit (196deg.C): • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) OIL TEMP HI • SD displays ENGINE page: • Oil temperature indication becomes amber, • After reducing thrust lever, oil temperature may decrease but remains above amber limit

When oil temperature is below the engine warm up threshold (40 deg.C), and

- if the pilot depressed the Take-Off Configuration Test P/B with the throttle levers at idle position: or

- if aircraft is in take-off phase with throttles levers at Flex/MCT or Take-Off positions

Single Chime sounds, MASTER CAUT lights illuminate, E/WD displays message: ENG 1(2) OIL TEMP LO SD displays ENGINE page, Minimum temperature is limited to TAT

Canceling the malfunction restores normal engine oil temperature.




MALFUNCTION : OIL FILTER CLOGGED ENG 2 AIRCRAFT : A380 RR CAUSE : Clogging of oil filter CONSEQUENCES:

If engine is running: • E/WD displays message (on ground): ENG 2 OIL FILTER CLOGGED • An amber attention getting box appears on Engine system page, • On SD ENGINE page,

- CLOGGED indication appears amber under the oil pressure analog indication.

Canceling the malfunction restores normal engine oil indication.



ATA 70 RR – ENGINE PARAMETERS

MALFUNCTION : TURBINE OVHT ENG 1(2) AIRCRAFT : A380 RR CAUSE : Air temperature around the IP turbine disk increases just above

the overheat limit CONSEQUENCES:

• Continuous Repetitive Chime, • MASTER WARN lights flash, • The EGT increases but below over limit, • E/WD displays message: ENG 1(2) TURBINE OVHT





MALFUNCTION : EGT OVER LIMIT (INC/DEC) ENG 1(4) AIRCRAFT : A380 RR CAUSE : Incorrect engine operation PARAMETER : min value max value rate

EGT EGT nominal value 1200 °C 10 °C/s

CONSEQUENCES:

When engine is running: When EGT exceeds amber limit (850°C) but is below red line limit (900°C) • EGT indication becomes amber • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) EGT OVER LIMIT • An amber attention getting box appears on the EWD. When EGT exceeds red line limit 900 deg C: • EGT indication becomes red, • E/WD message: ENG 1(4) EGT OVER LIMIT disappears, • Red mark appears on the EGT indicator at the max value achieved,

Canceling the malfunction restores normal EGT except the red mark.




MALFUNCTION : N1 OVER LIMIT (INC/DEC) ENG 3 AIRCRAFT : A380 RR CAUSE : Incorrect engine operation PARAMETER : min value max value rate

N1 Idle 120 % 5 %/s CONSEQUENCES:

If on ground then TCM detection is active (based on N1 thresholds) According to flight conditions, N1 TCM threshold can be higher or lower than N1 red line. Therefore N1Redline can be reached, or not, before TCM accommodation depending on flight conditions. If N1 value exceeds the N1 red line value (RR: 97.2%): while N1 is over red line • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N1 indication turns red, • A red cross appears and remains displayed, • E/WD displays message: ENG 3 N1 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the

pilot is invited to put master lever off.

When N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC can either shut the engine down (only if throttle

at idle) or perform a fuel reduction • For fuel reduction, E/WD displays message: ENG 3 CTL SYS FAULT • For shut down, E/WD displays message: ENG 3 FAIL THRUST CTL LOST • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the


Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start. If N1 value exceeds N1 red line, red cross remains after malfunction canceling.

If Altitude <15000 ft then TCM detection is active (based on N1 thresholds) According to flight conditions, N1 TCM threshold can be higher or lower than N1 red line. Therefore N1Redline can be reached or not before TCM accommodation depending on flight conditions. If N1 value exceeds the N1 red line value(RR: 97.2%): while N1 is over red line

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N1 indication turns red, • A red cross appears and remains displayed,



• E/WD displays message: ENG 3 N1 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the

pilot is invited to put master lever off If N1 reaches N1 overspeed value (RR: 110.9%):

• Overspeed function is triggered and a shutdown is performed.

When N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC performs a fuel reduction. • E/WD displays message: ENG 3 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the


Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start. If N1 value exceeds N1 red line, red cross remains after malfunction canceling.

If Altitude ≥ 15000 ft then TCM detection is not active

• EGT increases without exceeding over limit. When N1 value exceeds the N1 red line value (RR: 97.2%): while N1 is over red line

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N1 indication turns red, • A red cross appears and remains displayed, • E/WD displays message: ENG 3 N1 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the


If N1 reaches N1 overspeed value (RR: 110.9%): • Overspeed function is triggered and a shutdown is performed.

Canceling the malfunction restores normal LP rotor behavior except the red cross.






If on ground then TCM detection is active (based on N1 thresholds) N2 red line can be reached before TCM accommodation, or after, depending on flight conditions: therefore, N2 red line or N1 TCM thresholds are not necessary reached in all cases. If N2 value exceeds the N2 red line value (RR: 98.7%): while N2 is over red line



If N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC can either shut the engine down (only if throttle



Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start. If N2 value exceeds N2 red line, red cross remains.

If Altitude < 15000 ft then TCM detection is active (based on N1 thresholds) N2 red line can be reached before TCM accommodation, or after, depending on flight conditions: therefore, N2 red line or N1 TCM thresholds are not necessary reached in all cases.

• EGT increases without exceeding over limit. If N2 value exceeds the N2 red line value (RR: 98.7%): while N2 is over red line

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N2 indication turns red, • A red cross appears and remains displayed, • E/WD displays message: ENG 4 N2 OVER LIMIT,



• During throttle reduction to idle following ECAM procedure, there is no effect on N2 value and the pilot is invited to put master lever off.

If N2 reaches N2 overspeed value (RR: 110.9%):

• Overspeed function is triggered and a shutdown is performed. If N1 reaches a N1 TCM threshold:

• TCM function of the EEC is triggered and the EEC performs a fuel reduction. • E/WD displays message: ENG 4 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, there is no effect on N2 value and the


Canceling the malfunction restores normal HP rotor behavior but the fuel coefficient reduction is still active until next engine start (if TCM accommodation was done). If N2 value exceeds N2 red line, red cross remains.

If Altitude ≥ 15000 ft then TCM detection is not active • EGT increases without exceeding over limit. When N2 value exceeds the N2 red line value (RR: 98.7%): while N2 is over red line



If N2 reaches N2 overspeed value (RR: 110.9%) • Overspeed function is triggered and a shutdown is performed.

Canceling the malfunction restores normal HP rotor behavior except the red cross.






If on ground then TCM detection is active (based on N1 thresholds) N3 red line can be reached before TCM accommodation, or after, depending on flight conditions: therefore, N3 red line or N1 TCM thresholds are not necessary reached in all cases. If N3 value exceeds the N3 red line value (RR: 97.8%): while N3 is over red line



If N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC can either shut the engine down (only if throttle



Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start. If N3 value exceeds N3 red line, red cross remains.

If Altitude < 15000 ft then TCM detection is active (based on N1 thresholds) N3 red line can be reached before TCM accommodation, or after, depending on flight conditions: therefore, N3 red line or N1 TCM thresholds are not necessary reached in all cases.

• EGT increases without exceeding over limit. If N3 value exceeds the N3 red line value (RR: 97.8%): while N3 is over red line

• Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N3 indication turns red, • A red cross appears and remains displayed,



• E/WD displays message: ENG 4 N3 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N3 value and the


If N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC performs a fuel reduction. • E/WD displays message: ENG 4 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, there is no effect on N3 value and the


Canceling the malfunction restores normal HP rotor behavior but the fuel coefficient reduction is still active until next engine start (if TCM accommodation was done). If N3 value exceeds N3 red line, red cross remains.

If Altitude ≥ 15000 ft then TCM detection is not active

• EGT increases without exceeding over limit. When N3 value exceeds the N3 red line value (RR: 97.8%):: while N3 is over red line



Canceling the malfunction restores normal HP rotor behavior except the red cross.



ATA 70 RR – ENGINE ADVISORIES

MALFUNCTION : OIL QTY INC/DEC ENG 3(4) AIRCRAFT : A380 RR CAUSE : Leak in lubrication circuit PARAMETER : min value max value rate

OIL QTY 0 qts 25 qts 0.008 qts/s CONSEQUENCES:

Engine running, Oil quantity indication is green.

When oil quantity goes below advisory level (3.6 QTS): • SD displays ENGINE page, • A few seconds later, oil qty indication flashes green,

9 min later: • Oil press decreases and Oil temp increases,

Within 1 min: • Oil pressure reduces below amber line limit (dependant on N3 shaft speed): • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 3(4) OIL PRESS LO (amber alert) • SD displays ENGINE page, • Amber box appears on ENGINE page and oil pressure indication turns amber. • Oil pressure reduces below red line limit (25PSI): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 3(4) OIL PRESS LO (red alert) • Oil pressure indication turns red.





MALFUNCTION : N1 VIBRATION INC/DEC ENG 1 AIRCRAFT : A380 RR CAUSE : Unbalanced engine PARAMETER : min value max value rate

N1 VIBRATION 0 Cockpit Unit 10 Cockpit Unit 2 Cockpit Unit/s CONSEQUENCES:

When engine is running: • Cabin motion effects take place. If N1 vibrations exceeds advisory level (5 Cockpit Units): • A few seconds later, SD displays ENGINE page depending on flight phase, • N1 vibrations indication pulses green, • Sound effects take place. • During the recovery procedure:

After reducing thrust lever, N1 vibration may decrease but remains above advisory level.

Canceling the malfunction restores normal N1 vibration and associated effects.





N2 VIBRATIONS 0 Cockpit Unit 10 Cockpit Unit 2 Cockpit Unit/s CONSEQUENCES:

When engine is running, If N2 vibrations exceeds advisory level (5 Cockpit Units): • A few seconds later, SD displays ENGINE page depending on flight phase, • N2 vibrations indication pulses green, • Sound effects take place. • During the recovery procedure:


Canceling the malfunction restores normal N2 vibration.






When engine is running: If N3 vibrations exceeds advisory level (5 Cockpit Units): • A few seconds later, SD displays ENGINE page depending on flight phase, • N3 vibrations indication pulses green, • Sound effects take place. • During the recovery procedure:


Canceling the malfunction restores normal N3 vibration.




MALFUNCTION : NAC TEMP INC/DEC ENG 4 AIRCRAFT : A380 RR CAUSE : Incorrect engine operation PARAMETER : min value max value rate

NAC TEMP TAT 500 °C 10 °C/s CONSEQUENCES:

When engine is running: • When nacelle temp exceeds advisory level (300 °C), • SD displays ENGINE page depending on flight phase, • NAC temp indication flashes green.

Canceling the malfunction restores normal operation



ATA 70 EA – ENGINE FAILURES

MALFUNCTION : ENG FAIL (NO DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 – EA CAUSE : Engine flame out CONSEQUENCES:

• Rapid decrease in EGT, N1, N2, FF and THR, • No vibrations, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD. • N1, N2 parameters freely decrease, • During the ECAM procedure:

While the failure is activated any engine relight attempt is unsuccessful: - E/WD displays message: ENG 1(2)(3)(4) START FAULT

NO LIGHT UP





MALFUNCTION : ENG FAIL (DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 - EA CAUSE : LP compressor damage due to the absorption of foreign object CONSEQUENCES:

• Rapid decrease in N1, N2, FF and THR, • N1 decreases quickly to 0% (no N1 rotation due to fan deterioration), • Fan vibrations peak take place during N1 decreases and stabilizes higher than normal, • Sound effect takes place, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD. • During the ECAM procedure:

While the failure is activated any engine relight attempt is unsuccessful: - E/WD displays message: ENG 1(2)(3)(4) START FAULT

NO LIGHT UP





MALFUNCTION : ENG FAIL (SERIOUS DAMAGE) ENG 1(2)(3)(4) AIRCRAFT : A380 - EA CAUSE : Foreign object ingestion – Eng blade disintegration CONSEQUENCES:

As soon as N1 above 78%: • THR, N1 decrease with a large reduction, N2, and Fuel Flow small and slow reduction

Then all engine parameters move erratically lower and upper than in normal operation,

• Vibrations levels reach advisories, • Oil temperature reaches the amber value, • E/WD displays message: ENG 1(2)(3)(4) OIL TEMP HIGH • Nacelle temperature pulses, • Aircraft yaws with loss of thrust, • Sound effects take place. • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

Then: • Single Chime sounds, • MASTER CAUT lights illuminate, • THR value drops, • Complete loss of engine thrust, • EGT decreases, • Oil temperature decreases, • Nacelle temperature slowly decreases, • High vibration levels decrease, but stay just above advisories value, • E/WD displays message: ENG 1(2)(3)(4) FAIL • An amber attention getting box appears on the EWD and on the Engine SD.





MALFUNCTION : BIRD INGESTION ENG 1(2)(3)(4) AIRCRAFT : A380 EA CAUSE : Bird ingestion CONSEQUENCES:

As soon as N1 is above 78%: • THR, N1decrease with a large reduction, N2 and Fuel Flow small reduction,

Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates without exceeding over limit, • N1 vibration level reaches advisory, • Aircraft yaws with loss of thrust, • Sound effects take place, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2)(3)(4) STALL

Then after 30 seconds: • Stall effects disappear, • N1 vibrations and EGT return to nominal operation.

Canceling the malfunction restores normal engine performance.




MALFUNCTION : ENG STALL ENG 1(2)(3)(4) AIRCRAFT : A380 - EA CAUSE : Compressor stall CONSEQUENCES:

As soon as N1 is above 78%: • THR, N1 decrease with a large reduction, N2, and Fuel Flow small reduction, Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates but below over limit, • Sound effects take place, • Motion effects take place, • Relevant engine vibrations increase, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) STALL

As soon as thrust lever of relevant engine is reduced and actual N1 is lower than 60%. • Stall effects disappear.

The effects should reoccur when thrust lever is increased and N1 is greater than 70%. • THR, N1 decrease with a large reduction, N2, and Fuel Flow small reduction, Then all engine parameters move erratically lower and upper than in normal operation, • EGT fluctuates but below over limit, • Sound effects take place, • Motion effects take place, • Relevant engine vibrations increase, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) STALL

As soon as thrust lever of relevant engine is reduced again and actual N1 is lower than 60%. • Stall effects disappear





MALFUNCTION : REVERSER LOCKED ENG 2 (3) AIRCRAFT : A380 - EA CAUSE : Thrust reverser doors stuck in position. Reverser retracted: one primary lock clamped in locked position CONSEQUENCES:

If reverser doors are previously fully stowed (engine in forward thrust): When reverse control lever is pulled in max reverse position: • The thrust reverser cannot be deployed, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2(3) REVERSER LOCKED • The amber REV x indication is displayed on EWD, • IDLE is automatically selected by EEC.





MALFUNCTION : REV UNLOCKED (DURING RETRACTION)-ON GROUND ENG 2(3) AIRCRAFT : A380 - EA CAUSE : Thrust reverser doors stuck in position. Reverser deployed: reverser jammed in position. CONSEQUENCES:

If reverser doors are previously fully deployed (engine in reverse thrust): When reverse control lever is pulled in idle position: • The reversers cannot be retracted, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2(3) REVERSER UNLOCKED • The amber REV x indication is displayed on the EWD • Thrust is limited to idle by the EEC.





MALFUNCTION : REV UNLOCKED ENG 2(3) AIRCRAFT : A380 - EA CAUSE : Locks detected unlocked with the throttle in forward position (door

position remains below 5% of maximum door deployment) CONSEQUENCES:

If reversers doors are previously fully stowed:

As soon as the failure is inserted: If the A/C is on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • The amber REV x indication is displayed on the EWD, • E/WD displays message: ENG 2 (3) REVERSER UNLOCKED • IDLE is not automatically selected by the EEC. •

If the A/C is in flight: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER UNLOCKED • IDLE is not automatically selected by the EEC. • An amber attention getting box appears on the EWD. • The amber REV x indication flashes on EWD for a few seconds, and then remains displayed




MALFUNCTION : REV INHIBITED ENG 2(3) AIRCRAFT : A380 EA CAUSE : reverser de-activated by maintenance action. CONSEQUENCES:

If reverser doors are previously fully stowed and the engines are not running

As soon as the failure is inserted on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER INHIBITED • If throttle lever is set on reverser position, thrust reverser doors remain stuck in closed position. • As soon as the engine is started, the effects are latched until the engine is shut down. Note: do not use ENG QUICK START as effects are not as advertised.

Canceling the malfunction restores normal engine operation (provided the engine is not started).



ATA 70 – ENGINE FAILURES

MALFUNCTION : REV FAULT ENG 2(3) AIRCRAFT : A380 EA CAUSE : ETRAC overheat or TRPU overheat CONSEQUENCES:


As soon as the failure is inserted on ground: • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 2 (3) REVERSER FAULT • If throttle lever is set on reverser position, thrust reverser doors remain stuck in closed position and

EWD displays message ENG 2 (3) REVERSER LOCKED.




ATA 70 EA – ENGINE START

MALFUNCTION : START FAULT (ENG STALL) - HUNG START ENG 1(2) AIRCRAFT : A380 - EA CAUSE : Start fails (no sufficient starter air pressure) CONSEQUENCES:

If A/C is on ground: During AUTO start: • N1, N2 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL (for a few seconds) • SD displays ENGINE page, • FUEL and IGNITERS are commanded off, • EEC performs a crank sequence, • A second and a third start are automatically initiated with the same effects if the malfunction is still

active, • Automatic Start abort takes place, • FAULT light on Master lever is ON. (until M/L is put off). During MAN start: • N1, N2 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT ENG STALL (for a few seconds) • SD displays ENGINE page, • The pilot must shut down the engine, and perform a DRY CRANK according to ECAM procedure,

If A/C is in flight:

During AUTO start: • N1, N2 increase slowly, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT or ENG 1(2) START FAULT ENG STALL HUNG START (both for a few seconds) (Both messages can be displayed depending on altitude and mach conditions) • SD displays ENGINE page, • EEC performs successive starts, • After 300s, E/WD displays message: ENG 1(2) STARTER TIME EXCEEDED (Only if windmill is

not enable) • Manual shut down is required.

During MAN start: • N1, N2 increase slowly,



If windmill is not enable: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, (until M/L is put off) • E/WD displays message: ENG 1(2) START FAULT or ENG 1(2) START FAULT ENG STALL HUNG START (both for a few seconds) (Both messages can be displayed depending on altitude and mach conditions) • SD displays ENGINE page, The engine doesn’t start but fuel and igniters remain ON • The pilot must shut down the engine, and perform a DRY CRANK according to ECAM procedure, If windmill is enable: • N2 doesn’t reach the N2 threshold advised to put MASTER LEVER on. If you ever put the lever on,

the Hung Start or Stall Start message will appear, • Manual shut down is required.

Note: If the fault is removed at any time during the start sequence, the start sequence shall continue as if hung start conditions were self-cleared during the start attempt.





MALFUNCTION : START FAULT (EGT OVER LIMIT) - HOT START ENG 3(4) AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation CONSEQUENCES:

If A/C is on ground: During AUTO start: • N1, N2 increase slowly, When EGT reaches over limit: • Single Chime sounds, • MASTER CAUT lights illuminate, • EGT indication becomes amber, • An amber attention getting box appears on the EWD, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT (for a few seconds) • SD displays ENGINE page • FUEL and IGNITERS are commanded off, • The EEC performs a crank sequence, • A second and a third start are automatically initiated with the same effects if the malfunction is still

active. • Automatic Start abort takes place, • FAULT light on master lever is ON (until M/L is put off). During MAN start: • N1, N2 increase slowly, When EGT reaches over limit: • Single Chime sounds, • MASTER CAUT lights illuminate, • EGT indication becomes amber, • An amber attention getting box appears on the EWD, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT (for a few seconds) • SD displays ENGINE page, • The pilot must shut down the engine, and perform a DRY CRANK according to ECAM procedure,

If A/C is in flight: • N1, N2 increase slowly, When EGT reaches over limit: • Single Chime sounds, • MASTER CAUT lights illuminate, • EGT indication becomes amber, • An amber attention getting box appears on the EWD, • E/WD displays message: ENG 3 (4) START FAULT EGT OVER LIMIT (for a few seconds) • SD displays ENGINE page,

During AUTO start:



• EEC performs successive starts, • After 300s, E/WD displays message: ENG 1(2) START FAULT (STARTER TIME EXCEEDED)

(only if windmill is not enable) • Manual shut down is required.

During MAN start: • Fuel and igniters remain ON • The pilot must shut down the engine, and perform a DRY CRANK according to ECAM procedure,






MALFUNCTION : IGN A+B FAULT ENG 1(2) AIRCRAFT : A380 - EA CAUSE : Ignition plugs failed CONSEQUENCES:

If A/C is on ground: During AUTO start: • The EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD display messages: ENG 1(2) START FAULT – NO LIGHT UP ENG 1(2) IGN A or B FAULT • SD displays ENGINE page, • The EEC performs a crank sequence, • A second start is automatically initiated, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD display messages: ENG 1(2) START FAULT – NO LIGHT UP ENG 1(2) IGN A+B FAULT • A third start is automatically initiated with the same effects if the malfunction is still active, • Automatic Start abort takes place, • FAULT light on Master lever is ON (until M/L is put off).

During MAN start: • The EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) START FAULT – NO LIGHT UP • A few seconds later, E/WD displays message: ENG 1(2) IGN A+B FAULT • The pilot must shutdown the engine and perform a crank sequence according to ECAM procedure,

If A/C is in flight: During AUTO start: • The EEC detects no light up, • Fuel and ignition remain ON, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD display messages: ENG 1(2) START FAULT – NO LIGHT UP • A few seconds later, E/WD displays message: ENG 1(2) IGN A+B FAULT • The pilot must shutdown the engine During MAN start: • The EEC detects no light up, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD display messages: ENG 1(2) START FAULT – NO LIGHT UP • A few seconds later, E/WD displays message: ENG 1(2) IGN A+B FAULT



The pilot must shut down the engine, and perform a DRY CRANK according to ECAM procedure,

Canceling the malfunction restores normal IGNITION operation. After engine shut down, the engine ECAM message will disappear when a new start is performed.




MALFUNCTION : START VLV FAULT (CLOSED/NOT CLOSED) ENG 1(2)(3)(4) AIRCRAFT : A380 - EA CAUSE : start valve stuck in position CONSEQUENCES:

Before start procedure (starter valve in closed position): • Starter valve remains closed, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG (1)(2)(3)(4) START VLV FAULT VLV STUCK CLOSED The starter valve symbol on ENGINE page becomes amber, • SD displays ENGINE system page, For AUTO start procedure on Ground only: • Automatic Start abort takes place, • FAULT light on the Master lever is ON (until M/L is put off).

During start procedure (starter valve in open position): • Start sequence takes place normally, • Starter valve remains open, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG (1)(2)(3)(4) START VLV FAULT START VLV NOT CLOSED • The starter valve symbol on ENGINE page becomes amber, • SD displays ENGINE page.

Canceling the malfunction restores starter air valve operation:

• after engine shut down, the engine ECAM message will disappear when a new start is performed • after a manual start, execute a master lever reset to remove FWC message and amber symbol on

the ENGINE system page




MALFUNCTION : ENG HP FUEL VALVE FAULT (HPV NOT OPEN / NOT CLOSED) ENG 3 (4)

AIRCRAFT : A380 - EA CAUSE : Fuel valve stuck in position CONSEQUENCES:

If engine is not running (HP fuel valve not open): During start sequence, when EEC commands fuel: • Single Chime sounds, • MASTER CAUT lights illuminate, • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) HP FUEL VLV FAULT HP FUEL VLV NOT OPEN • SD displays ENGINE page, • A few seconds later, FWC message disappears and is replaced by: ENG 3 (4) START FAULT – NO LIGHT UP For auto start only: • A second and a third start are automatically initiated with the same effects if the malfunction is still

active, • Automatic Start abort takes place according to ECAM procedure,

Canceling the malfunction restores HP fuel valve operation. After engine shut down, the engine ECAM message will disappear when a new start is performed.

With engine running (HP fuel valve not closed): As soon as master switch is set to OFF position: • FAULT light on master lever is ON, • E/WD displays message: ENG 3 (4) HP FUEL VLV FAULT HP FUEL VLV NOT CLOSED • SD displays ENGINE page. • A few seconds later, fuel metering valve closes and engine parameters decrease,

In order to restore engine normal operation, cancel the malfunction and perform a M/L reset (ON then OFF). The engine ECAM message will disappear when a new start is performed.



ATA 70 EA – ENGINE CONTROLS

MALFUNCTION : FADEC FAULT ENG 1(4) AIRCRAFT : A380 - EA CAUSE : FADEC output bus driver fails CONSEQUENCES:

• Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) FADEC FAULT • SD displays ENGINE page,

- All engine indications are lost but the engine is still running and controllable. - HYD, BLEED, ELEC AC pages must be used to confirm engine status.




ATA 70 EA – ENGINE FLUIDS

MALFUNCTION : FUEL FILTER CLOGGED ENG 3 (4) AIRCRAFT : A380 - EA CAUSE : Clogging of fuel filter CONSEQUENCES:

If engine is running: • E/WD displays message (on ground): ENG 3(4) FUEL FILTER CLOGGED • An amber attention-getting box appears on Engine system page. • SD displays ENGINE page,

- CLOGGED indication appears in amber under the fuel flow indication.

Canceling the malfunction restores normal engine fuel indication.




MALFUNCTION : OIL PRESS (INC/DEC) ENG 3 (4) AIRCRAFT : A380 - EA CAUSE : Oil pump fails or oil jet clogging PARAMETER : min value max value rate

OIL PRESS 0 PSI 440 PSI 10 PSI/s CONSEQUENCES:

When engine is running: • Oil pressure indication is green. When oil pressure reduces below red line limit (25PSI): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 3(4) OIL PRESS LO (Red Alert) • Amber box is a displayed on ENGINE page and oil pressure indication turns red.

Canceling the malfunction restores normal engine oil pressure.




MALFUNCTION : OIL TEMP (INC/DEC) ENG 1(2) AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation PARAMETER : min value max value rate

OIL TEMP TAT 250°C 20°C/s CONSEQUENCES:

Engines running: • Oil temperature indication is green. When oil temperature exceeds the amber limit value (176.7°C): • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) OIL TEMP HI • SD displays ENGINE page, • Oil temperature indication becomes amber, • After reducing thrust lever, oil temperature may decrease but remains above amber limit value. When oil temperature is below 50°C with engine running for 30 seconds on ground:

- if the pilot depressed the Take-Off Configuration Test P/B with the throttles levers at idle position, or

- if aircraft is in take-off phase with the throttles levers at FLEX/MCT or Take-Off positions. • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(2) OIL TEMP LO • SD displays ENGINE page, • Minimum temperature is limited to TAT.

Canceling the malfunction restores normal engine oil temperature.




MALFUNCTION : OIL FILTER CLOGGED ENG 2 AIRCRAFT : A380 - EA CAUSE : Clogging of oil filter CONSEQUENCES:

If engine is running: • E/WD displays message (on ground): ENG 2 OIL FILTER CLOGGED • An amber attention-getting box appears on the Engine system page. • On SD ENGINE page,

- CLOGGED indication appears amber under the oil pressure analog indication.

Canceling the malfunction restores normal engine oil indication.



ATA 70 EA – ENGINE PARAMETERS

MALFUNCTION : EGT OVER LIMIT (INC/DEC) ENG 1(4) AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation PARAMETER : min value max value rate

EGT EGT nominal value 1100 °C 10 °C/s • CONSEQUENCES: When engine is running:

When EGT exceeds amber limit (970°C) but is below red line limit 1002°C: • EGT indication becomes amber, • Single Chime sounds, • MASTER CAUT lights illuminate, • E/WD displays message: ENG 1(4) EGT OVER LIMIT • An amber attention getting box appears on the EWD. When EGT exceeds red line limit 1002 deg C: • EGT indication becomes red, • E/WD message: ENG 1(4) EGT OVER LIMIT disappears. • Red mark appears on the EGT indicator at the max value achieved,

Canceling the malfunction restores normal EGT except the red mark.




MALFUNCTION : N1 OVER LIMIT (INC/DEC) ENG 3 AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation PARAMETER : min value max value rate

N1 idle 120% 5 %/s CONSEQUENCES:

If on ground then TCM detection is active (based on N1 thresholds): When N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC can either shut the engine down (only if throttle

at idle) or perform a fuel reduction • E/WD displays message: ENG 3 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, a shut down is instantly triggered and

the pilot is invited to put master lever off. • E/WD displays message: ENG 3 FAIL THRUST CTL LOST • An amber attention-getting box appears on the EWD. Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start.

If Altitude < 15000 ft and Mach < 0.4 then TCM detection is active (based on N1 thresholds): When N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC performs a fuel reduction. • E/WD displays message: ENG 3 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the


Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start.

If Altitude ≥ 15000 ft or Mach ≥ 0.4 then TCM detection is not active: When N1 value exceeds the N1 red line value (111%): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N1 indication turns red, • A red cross appears and remains displayed, • E/WD displays message: ENG 3 N1 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N1 value and the


If N1 exceeds N1 overspeed value (114%) • Overspeed function of the EOS is triggered and a shutdown is performed. • E/WD displays message: ENG 3 HP FUEL VLV FAULT



HP FUEL VLV NOT OPEN • An amber attention-getting box appears on the EWD. • E/WD displays message: ENG 3 FAIL - AUTORELIGHT IN PROGRESS.

Canceling the malfunction restores normal LP rotor behavior except the red cross.




MALFUNCTION : N2 OVER LIMIT (INC/DEC) ENG 4 AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation PARAMETER : min value max value rate

N2 idle 130% 5 %/s CONSEQUENCES:

If on ground then TCM detection is active (based on N1 thresholds): When N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC can either shut the engine down (only if throttle

at idle) or perform a fuel reduction • E/WD displays message: ENG 4 CTL SYS FAULT • During throttle reduction to idle following the ECAM procedure, a shut down is instantly triggered

and the pilot is invited to put master lever off. • E/WD displays message: ENG 4 FAIL THRUST CTL LOST • An amber attention-getting box appears on the EWD.

Canceling the malfunction restores normal LP rotor behavior but the fuel coefficient reduction is still active until next engine start.

If Altitude < 15000 ft and Mach < 0.4 then TCM detection is active (based on N1 thresholds): If N1 reaches a N1 TCM threshold: • TCM function of the EEC is triggered and the EEC performs a fuel reduction. • E/WD displays message: ENG 4 CTL SYS FAULT • During throttle reduction to idle following ECAM procedure, there is no effect on N2 value and the

pilot is invited to put the master lever to off.

Canceling the malfunction restores normal HP rotor behavior but the fuel coefficient reduction is still active until next engine start.

If Altitude ≥ 15000 ft or Mach ≥ 0.4 then TCM detection is not active: When N2 value exceeds the N2 red line value (118.7%): • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • N2 indication turns red, • A red cross appears and remains displayed, • E/WD displays message: ENG 4 N2 OVER LIMIT, • During throttle reduction to idle following ECAM procedure, there is no effect on N2 exceedance

If N2 exceeds N2 overspeed value (121%) • Overspeed function of the EOS is triggered and a shutdown is performed. • E/WD displays message: ENG 4 HP FUEL VLV FAULT



HP FUEL VLV NOT OPEN • An amber attention getting box appears on the EWD, • E/WD displays message: ENG 4 FAIL - AUTORELIGHT IN PROGRESS

Canceling the malfunction restores normal HP rotor behavior except the red cross



ATA 70 EA – ENGINE ADVISORIES

MALFUNCTION : OIL QTY INC/DEC ENG 3(4) AIRCRAFT : A380 - EA CAUSE : Leak in lubrication circuit PARAMETER : min value max value rate

OIL QTY 0 qts 25 qts 0.007 qts/s CONSEQUENCES:

Engine running, Oil quantity indication is green,

When oil quantity reaches advisory level 1.2 qts: • SD displays ENGINE page, • A few seconds later, oil qty indication flashes green.

9 min later: • Oil pressure decreases and oil temperature increases,

Within 1 min: • Oil pressure reduces below red line limit (25 PSI), • Continuous Repetitive Chime sounds, • MASTER WARN lights flash, • E/WD displays message: ENG 3(4) OIL PRESS LO (red alert), • Amber box appears on ENGINE page and oil pressure indication turns red.





MALFUNCTION : N1 VIBRATION INC/DEC ENG 1 AIRCRAFT : A380 - EA CAUSE : Unbalanced engine PARAMETER : min value max value rate


When engine is running: • Cabin motion effects take place.

If N1 vibrations exceeds advisory level (7 Cockpit Unit): • N1 vibrations indication pulses green, • Sound effects take place. • During the recovery procedure: • After reducing thrust lever, N1 vibration may decrease but remains above advisory level.





MALFUNCTION : N2 VIBRATION INC/DEC ENG 4 AIRCRAFT : A380 - EA CAUSE : Unbalanced engine PARAMETER : min value max value rate

N2 VIBRATIONS 0 Cockpit Unit 10 Cockpit Unit 2 Cockpit Unit/s CONSEQUENCES:

When engine is running, If N2 vibrations exceeds advisory level (7 Cockpit Unit): • N2 vibrations indication pulses green, • Sound effects take place.

• During the recovery procedure:






MALFUNCTION : NAC TEMP INC/DEC ENG 4 AIRCRAFT : A380 - EA CAUSE : Incorrect engine operation PARAMETER : min value max value rate

NAC TEMP TAT 400°C 10 °C/s CONSEQUENCES:

When engine is running: • When nacelle temp exceeds advisory level (300°C), • SD displays ENGINE page depending on flight phase, • NAC temp indication flashes green.

Canceling the malfunction restores normal operation



END OF DOCUMENT

Documents

Standard 1 42 – INTEGRATED MODULAR AVIONICS 19 ATA 44 – CABIN SYSTEMS 20 ATA 46 – INFORMATION SYSTEM 20 ATA 49 – APU 20 ATA 52 – DOOR 20 ATA 70 RR– POWERPLANT 20 ATA 70