FASE 1

FAULT LEGEND ON THE GALLEY P/B COMES ON WHEN. AC GENERATOR OVERLOAD AND IF NO AUTOMATIC SHEDDING DONE BY ECMU. .

IF ENGINE 2 FAILS IN FLIGHT AND APU IS OPERATING. EN 1 SUPPLIES AC BUS 1 AND APU GEN SUPPLIES AC BUS 2. .

IF BUS TIE P/BSW 13XU ON 235VU IS SET TO OFF. BTC 1, BTC 2 AND SIC OPENS. .

TO RESET A TRIPPED RCCB YOU MUST PUSH. RESET P/B ON THE FRONT FACE OF THE RCCB. .

THE MAIN AND APU BATTERIES ARE VENTILATED BY. DIFFERENTIAL PRESSURE BETWEEN CABIN AND THE OUTSIDE. .

THE PURPOSE OF THE INADVERTENT PARALLELING TRIP FUNCTION ON AN AC BUS IS. PREVENTS TWO DIFFERENT SOURCES TO BE CONNECTED IN PARALLEL FOR MORE THAN 80 MS. .

THE RELAY IN THE ENGINE GENERATOR CONTROL UNIT (GCU) TO CONTROLS THE GLC AND NBPT IS. POWER READY RELAY (PRR). .

TO CARRY OUT THE STATIC INVERTER TEST WITH ALL AC BUSES NOT SUPPLIED AND HYDRAULICS NOT PRESSURISED SELECT. BAT P/BSW'S (235VU) IN OFF POSITION, PRESS AND HOLD THE EMER GEN TEST P/BSW (15XEON 211VU). .

THE PRIMARY FUNCTIONS OF THE ELECTRICAL CONTACTOR MANAGEMENT UNITS ARE. CONTROL THE MAIN AC AND DC POWER CONTACTORS, MANAGE THE POWER SOURCE PRIORITIES AND NBPT FUNCTION. .

THE OUTPUT OF INTEGRATED DRIVE GENERATOR (IDG) IS. 115 KVA, 115/200VAC, 3-PHASE, 400HZ. .

TRANSFORMER RECTIFIER UNITS (TRUS) THERE ARE. FOUR. .

THE TWO MAIN BATTERIES INSTALLED. IN THE AVIONICS BAY. .

TO RECOVER THE FAILED ND. MANUALLY PRESSING PFD/ND TRANSFER P/B. .

WHEN A PFD FAILS THE PFD DATA SHOW ON. THE RELATED INBOARD DISPLAY. .

A DISPLAY UNIT MONITORED BY TWO OTHER DISPLAY UNITS BECAUSE. FEEDBACK MONITORING FUNCTION OF CRITICAL PARAMETER. .

THE MAXIMUM NUMBER OF AIRCRAFT PARAMETERS THAT CAN BE VIEWED ON MCDU BY THE ALPHA CALL UP FUNCTION IS. 300. .

THE EFIS SINGLE SOURCE 2 MESSAGE ON BOTH PFDS COMES ON WHEN. WHEN DMC 2 IS DRIVING ALL 6 DUS. .

ECAM MODES OF OPERATION LET AIRCRAFT SYSTEM OPERATION AND STATUS DATA SHOW ON THE SD ARE. 1 MANUAL AND 3 AUTOMATIC. .

CLOCK (UTC) DATA COME FROM. MULTI-MODE RECEIVER. .

CLASS 2 AIRCRAFT SYSTEM FAILURES SHOW ON ECAM. ON THE ECAM STATUS PAGE. .

THE EFIS CONTROL PANEL MODE SELECTOR CONTROLS DATA ON. ND DISPLAY. .

THE EFIS SINGLE SOURCE 2 MESSAGE ON THE CAPT AND FO PFDS WHEN. DMC 2 IS GIVING DATA ALL 6 DUS. .

ECAM LEVEL 1 ALERT SHOW WHEN. EWD MESSAGE AND SD SYSTEM PAGE DISPLAY (IF RELATED). .

WHEN THE ANNUNCIATOR LIGHTS SWITCH IS SET TO TEST. ALL LEDS SHOW A TEST PATTERN. .

THE TYPE 1 SYSTEM COMPUTERS IN CMS. CAN REMEMBER LAST 64 FLIGHT MEMORIES. .

EXTERNAL FAILURES SENT BY SYSTEM BITE TO CMC ARE. FAILURES OF THE SYSTEM INTERFACING WITH THE AFFECTED SYSTEM. .

THE ADIRU SUPPLIES SPEED SIGNAL TO THE HSMU ARE. ADIRU 1 AND ADIRU 3. .

THE ECAM PAGES SHOW FLIGHT CONTROL DATA ARE. F/C TL, WHEEL AND EWD. .

THE CIDS CAUTION ANNUNCIATION ON THE FAP SHOW. A CIDS FAILURE HAS OCCURRED. .

IF THERE IS A GPS FAILURE. NAVGPS 1(2) FAULT MESSAGE SHOWS IN THE LOWER PART OF THE EWD. .

THE RECONFIGURATION IF THE EWD FAILS IS. EWD IS AUTOMATICALLY TRANSFERRED TO LOWER ECAM DISPLAY. .

THE FUNCTION COMPUTES THE LIMIT AND MANOEUVRING SPEEDS THAT SHOW ON THE PFD IS. FE. .

THE EMERGENCY LIGHTS BE SUPPLIED FROM EPSU BATTERIES WHEN. THE EMER LT SWITCH IS ARM, USUAL AC POWER AND DC ESSENTIAL BUS FAILS. .

THE EMERGENCY LIGHTS COME ON. WHEN THE EMERGENCY LIGHT SWITCH IS SET TO ARM AND DC ESS BUS FAILS. .

THE CIDS CAUTION ANNUNCIATION ON THE FAP SHOW. THAT A CIDS FAILURE. .

WHEN A DEU IS INSTALLED. DEU ADDRESS SETTING IS NOT NEEDED BECAUSE THE DEU ADDRESS IS ALREADY SET ON THE DEU MOUNTING UNIT. .

THE USUAL IN-FLIGHT POWER SUPPLY OF THE CIDS DIRECTORS. ARE 28VDC SERV AND ESS. .

THE TEMPERATURE DATA TO CIDS IS TRANSMITED BY. ECS. .