A330-300 ECAM 경고 및 리셋 빠른 참조 가이드

A330-300 ECAM WARNING AND RESET QUICK REFERENCE GUIDE. UNCONTROLLED DOCUMENT REFER TO APROVED MANUALS A330 ECAM MESSAGE RESET GUIDE L/H RESET PANEL. ACP/AMU Audio Control Panel / Audio Management Unit. AEVC Avionics Equipment Ventilation Controller. AEVC1 (2HQ) CIDS Cabin Intercommunication Data System. CIDS Director (101RH) CMC Central Maintenance Computer. CMC1 (1TM1) CPC Cabin Pressure Controller. CPC1 (311HL) DMC Display Management Computer. DMC1 (1WT1) DMC3 (1WT3) DMU Data Management Unit. DMU (1TV) EIVMU Engine Interface and Vibration Monitoring Unit. EIVMU2 (1KS2) EIVMU4 (1KS4) FCDC Flight Control Data Concentrator. FCDC1 (1CE1) FCMC Fuel Control and Management Computer. FCMC1 (5QM1) FCU Flight Control Unit. FCU1 (3CA1) FM Flight Management. FMGEC1 FMGEC FWC Flight Management Guidance Envelope Computer. Flight Warning Computer. FMGEC1 (1CA1) FWC1 (1WW1) LGCIU Landing Gear Control Interface Unit. LGCIU1 (5GA1) PC Pack Controller. PC1 (531HH) PHC Probe Heat Computer. PHC1 (6DA1) PHC3 (6DA3) PSCU Proximity Switch Control Unit. PSCU1 (5MJ1) SDAC System Data Acquisition Computer. SDAC1 (1WV1) SDCU Smoke Detector Control Unit. SDCU1 (20WH1) SFCC Slat/Flap Control Computer. SFCC1 (21CV) WHC Window Heat Computer. WHC1 (2DG1) Created by: Brett A Mumford 2 of 45 A330 ECAM MESSAGE RESET GUIDE R/H RESET PANEL ACP/AMU Audio Control Panel / Audio Management Unit. CIDS Cabin Intercommunication Data System. CIDS Director (102RH) CMC Central Maintenance Computer. CMC2 (1TM2) CPC Cabin Pressure Controller. CPC2 (312HL) DMC Display Management Computer. DMC2 (1WT2) EIVMU Engine Interface and Vibration Monitoring Unit. EIVMU1 (1KS1) EIVMU3 (1KS3) FCDC Flight Control Data Concentrator. FCDC2 (1CE2) FCMC Fuel Control and Management Computer. FCMC2 (5QM2) FCU Flight Control Unit. FCU2 (3CA2) FM Flight Management. FMGEC2 FMGEC FWC Flight Management Guidance Envelope Computer. Flight Warning Computer. FMGEC2 (1CA2) FWC2 (1WW2) LGCIU Landing Gear Control Interface Unit. LGCIU2 (5GA2) PC Pack Controller. PC2 (532HH) PHC Probe Heat Computer. PHC2 (6DA2) PSCU Proximity Switch Control Unit. PSCU2 (5MJ2) SDAC System Data Acquisition Computer. SDAC2 (1WV2) SDCU Smoke Detector Control Unit. SDCU2 (20WH2) SFCC Slat/Flap Control Computer. SFCC2 (22CV) VC Ventilation Controller VC (280HN) WHC Window Heat Computer. WHC1 (2DG1) AEVC Avionics Equipment Ventilation Controller. AEVC1 (2HQ) Created by: Brett A Mumford 3 of 45 A330 ECAM MESSAGE RESET GUIDE Figure 1: LH Reset Panel. Created by: Brett A Mumford 4 of 45 A/C EFF CODE/ MSN NO. A/C NO. EFF MSN HL7524 003 206 HL7525 004 219 HL7540 005 214 HL7550 001 162 HL7551 002 172 HL7553 052 267 HL7554 051 156 HL7584 053 338 HL7585 054 350 HL7586 055 351 HL7587 056 368 HL7701 057 425 HL7702 058 428 HL7709 059 484 HL7710 060 490 HL7720 061 550 HL7538 101 222 HL7539 102 226 HL7552 103 258 HL8211 151 1133 HL8212 152 1155 HL8227 153 1200 21. AIR CONDITIONING PNL DESIGNATION FIN LOC 721VU AEVC 4HQ L05 ALL 721VU AVNCS EXTRACT FAN 1HQ J02 ALL 721VU AVNCS VENT CED 6HQ T07 ALL 742VU AVNCS VENT CTL 8HQ A65 ALL 718VU BULK FAN 1HC C60 ALL 721VU CAB PRESS MAN 3HL P11 ALL 722VU CARGO VENT CTL L1 2HN U43 ALL 742VU CARGO VENT CTL L2 1HN L72 ALL 742VU CPC 1 1HL A66 ALL 722VU CPC 2 2HL U44 ALL 722VU EXTC FAN BULK CRG 5HN A37 ALL 722VU EXTC FAN FWD CARGO 11HN A34 ALL 721VU GND COOL CTL 3HD V11 001-099, 101-149 715VU GRU 1HD F54 001-099, 101-149 715VU GRU FAN 2HD T57 001-099, 101-149 5005VE HEATING LD-MCR CTL 6HK B03 101-149 5005VE HEATING LD-MCR CTL 6HK D04 151-199 5005VE HEATING LD-MCR POWER 5HK B01 101-149 5005VE HEATING LD-MCR POWER 5HK D02 151-199 742VU ISOL VLV LDMCR 4HG L70 101-149, 151-199 715VU L RECIRC FAN 1HG1 B54 ALL 721VU LAV+GALY EXTC FAN 1HU A02 ALL 742VU PACK 1 FLOW CTL 1HB1 A67 ALL 721VU PACK 1 L1 115VAC 1HH1 F02 ALL 721VU PACK 1 L1 28VDC 2HH1 T08 ALL 721VU PACK 1 L2 115VAC 3HH1 K04 ALL 721VU PACK 1 L2 28VDC 4HH1 R07 ALL 742VU PACK 2 FLOW CTL 1HB2 F80 001-099, 101-149 742VU PACK 2 FLOW CTL 1HB2 F71 151-199 722VU PACK 2 L1 115VAC 1HH2 H48 ALL 722VU PACK 2 L1 28VDC 2HH2 U40 ALL 722VU PACK 2 L2 115VAC 3HH2 E44 ALL 722VU PACK 2 L2 28VDC 4HH2 U41 ALL 725VU R RECIRC FAN 1HG2 B23 ALL 742VU RAM AIR 1HZ A68 ALL 721VU RPCU SPLY 4HL Q13 151-199 721VU TURBO FAN CTL 3HR T06 ALL 721VU ZONE CTL SYS 1 1HK1 R08 ALL 722VU ZONE CTL SYS 2 1HK2 U42 ALL PNL 722VU 742VU 722VU 742VU 722VU 742VU 722VU 742VU 742VU 742VU 22. AUTO FLIGHT DESIGNATION FIN LOC AP ELEC PWR SPLIT 14CA Q41 FCU A+B 8CA1 E69 FCU C 8CA2 R42 FMGEC 1 5CA1 M75 FMGEC 2 5CA2 R43 MCDU 1 7CA1 Q61 MCDU 2 7CA2 C47 MCDU 3 7CA3 N71 RUDDER ARTF FEEL 7CB M74 6CB M73 SIDE STICK LOCK EFF ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL 23. COMMUNICATIONS PNL 721VU 721VU DESIGNATION ACARS FIN 2RB LOC B01 ACP 3RD OCCPNT 4RN3 V05 ALL 721VU ACP 4TH OCCPNT 4RN4 V06 ALL 721VU ACP AVNCS COMPT 4RN5 V07 001-099, 101-149 001-058, 101-149 EFF 101-102 742VU ACP CAPT 4RN1 A71 742VU ACP CAPT AVNCS SELCAL 4RN1 A71 059-099, 151-199 742VU ACP F/O 4RN2 A72 001-058, 101-149 742VU ACP F/O 3&4 OCC BITE 4RN2 A72 059-099, 151-199 001-056, 101-149 5005VE CIDS CENTER AFT1 613RH A03 5005VE CIDS CENTER AFT1 613RH B07 057-099 5005VE CIDS CENTER AFT2 614RH A04 001-056, 101-149 5005VE CIDS CENTER AFT2 614RH B08 057-099 001-056, 101-149 5005VE CIDS CENTER MID2 612RH A02 5005VE CIDS CENTER MID2 612RH B06 057-099 5005VE CIDS CREW REST 618RH A06 101-149 743VU CIDS DEU A C1 AFT ESS 1413RH A93 151-199 151-199 743VU CIDS DEU A C1 FWD ESS 1411RH A91 743VU CIDS DEU A C2 AFT ESS 1414RH A94 151-199 743VU CIDS DEU A C2 FWD ESS 1412RH A92 151-199 609RH J06 057-099 001-056, 101-149 5001VE CIDS DEU A CENTER FWD 1 5001VE CIDS DEU A CENTER FWD 1 609RH B09 5001VE CIDS DEU A CENTER FWD 2 610RH J07 057-099 5001VE CIDS DEU A CENTER FWD 2 610RH B10 001-056, 101-149 5001VE CIDS DEU A CENTER FWD 609RH J06 151-199 057-099 5001VE CIDS DEU A CENTER MID 1 611RH J08 5001VE CIDS DEU A CENTER MID 1 611RH B11 001-056, 101-149 5001VE CIDS DEU A CENTER MID 610RH J07 151-199 743VU CIDS DEU A L1 AFT ESS 1407RH A87 151-199 151-199 743VU CIDS DEU A L1 FWD ESS 1403RH A83 743VU CIDS DEU A L2 AFT ESS 1409RH A89 151-199 743VU CIDS DEU A L2 FWD ESS 1405RH A85 151-199 743VU CIDS DEU A LDMCR ESS 1419RH A99 151-199 5001VE CIDS DEU A LEFT FWD NORM 603RH J04 151-199 5001VE CIDS DEU A LEFT MID NORM 605RH J08 151-199 5001VE CIDS DEU A LH FWD 603RH J04 057-099 5001VE CIDS DEU A LH FWD 603RH B07 001-056, 101-149 057-099 5001VE CIDS DEU A LH MID 605RH J05 5001VE CIDS DEU A LH MID 605RH B08 001-056, 101-149 743VU CIDS DEU A R1 AFT ESS 1408RH A88 151-199 743VU CIDS DEU A R1 FWD ESS 1404RH A84 151-199 151-199 743VU CIDS DEU A R2 AFT ESS 1410RH A90 743VU CIDS DEU A R2 FWD ESS 1406RH A86 151-199 5001VE CIDS DEU A RH FWD 604RH J09 057-099 5001VE CIDS DEU A RH FWD 604RH B12 001-056, 101-149 5001VE CIDS DEU A RH MID 606RH J10 057-099 5001VE CIDS DEU A RH MID 606RH B13 001-056, 101-149 151-199 5001VE CIDS DEU A RIGHT FWD 604RH J05 5001VE CIDS DEU A RIGHT MID 606RH J09 151-199 743VU CIDS DEU B L ESS 1415RH A95 151-199 722VU CIDS DEU B L FWD NORM 613RH N35 151-199 743VU CIDS DEU B LDMCR ESS 1418RH A98 151-199 743VU CIDS DEU B R ESS 1416RH A96 151-199 722VU CIDS DEU B R FWD NORM 614RH N34 151-199 742VU CIDS DIR 1 ESS 401RH A74 001-099, 101-149 151-199 743VU CIDS DIR 1 ESS 1401RH A81 722VU CIDS DIR 1 NORM 601RH P45 ALL 742VU CIDS DIR 2 ESS 402RH A75 001-099, 101-149 743VU CIDS DIR 2 ESS 1402RH A82 151-199 ALL 722VU CIDS DIR 2 NORM 602RH P46 743VU CIDS FLT ATTND PNL ESS 1417RH A97 151-199 5005VE CIDS LH AFT 607RH A01 001-056, 101-149 5005VE CIDS LH AFT 607RH B05 057-099 001-056, 101-149 5005VE CIDS RH AFT 608RH A05 5005VE CIDS RH AFT 608RH B09 057-099 5005VE CIDS TOP LINE DEU A C 612RH B06 151-199 5005VE CIDS TOP LINE DEU A L 607RH B05 151-199 5005VE CIDS TOP LINE DEU A R 608RH B09 151-199 5005VE CIDS TOP LINE DEU A/B 618RH B10 151-199 5001VE CTU 1RY G12 051-056 742VU 4RK Q67 001-099, 101-149 001-099, 101-149 CVR 721VU CVR CTL 5RK V09 742VU DEU A C 1 ESS 407RH F73 001-099, 101-149 742VU DEU A C 2 ESS 408RH F74 001-099, 101-149 742VU DEU A L 1 ESS 403RH F77 001-099, 101-149 001-099, 101-149 742VU DEU A L 2 ESS 405RH F75 742VU DEU A R 1 ESS 404RH F78 001-099, 101-149 742VU DEU A R 2 ESS 406RH F76 001-099, 101-149 742VU DEU B L ESS 409RH F71 001-099, 101-149 ALL 722VU DEU B L NORM 615RH P43 742VU DEU B R ESS 410RH F72 001-099, 101-149 722VU DEU B R NORM 616RH P44 ALL 721VU DOORS CKPT VIDEO SPLY 15RA S19 151-199 742VU EXT HORN 2WC H78 ALL 742VU FLT INTPH 5RN A73 001-058, 101-149 742VU FWD ATTND PNL ESS 411RH F70 001-099, 101-149 722VU FWD ATTND PNL NORM 617RH P42 ALL ALL 742VU HF 1 2RE1 J63 722VU HF 2 2RE2 E37 001-056, 101-149, 151-199 742VU INT 1+2 5RN A73 059-099, 151-199 1RF G13 001-050, 101-149 5001VE PES CPMS 5001VE PES CTU 1RY G12 001-050, 101-149 5001VE PES IN-SEAT AREA 1 21MK G01 001-056, 101-149 5001VE PES IN-SEAT AREA 1 21MK H01 057-099 5001VE PES IN-SEAT AREA 2 22MK G02 001-056, 101-149 5001VE PES IN-SEAT AREA 2 22MK H02 057-099 5001VE PES IN-SEAT AREA 3 28MK G03 001-056, 101-149 5001VE PES IN-SEAT AREA 3 28MK H03 057-099 5001VE PES IN-SEAT AREA 4 27MK H04 057-099 5001VE PES IN-SEAT AREA 4 27MK G04 001-056, 101-149 5005VE PES IN-SEAT AREA 5 23MK A09 001-056, 101-149 5005VE PES IN-SEAT AREA 5 23MK C09 057-099 5005VE PES IN-SEAT AREA 6 24MK A10 001-056, 101-149 5005VE PES IN-SEAT AREA 6 24MK C10 057-099 5005VE PES IN-SEAT AREA 8 29MK A12 101-149 5005VE PES IN-SEAT AREA7 26MK A11 001-056, 101-149 5005VE PES IN-SEAT AREA7 26MK C11 057-099 5001VE PES IN-SEAT CTL 25MK H05 057-099 5001VE PES IN-SEAT CTL 25MK G05 001-056, 101-149 5001VE PES MAIN 27MH G07 057-099 5001VE PES OVERHEAD FWD 22MH H06 057-099 5001VE PES OVERHEAD FWD 22MH G06 001-056, 101-149 5001VE PES OVERHEAD MID 23MH H07 057-099 5001VE PES OVERHEAD MID 23MH G07 001-056, 101-149 5005VE PES OVHD AFT 24MH A08 001-056, 101-149 5005VE PES OVHD AFT 24MH C08 057-099 2RX H11 057-099 5001VE PES PRAM 2RX G11 001-056, 101-149 5001VE PES PVIS 1MM J05 051-056 5001VE PES PVIS 1MM G05 057-099 5001VE PVIS DIU 1MM E05 101-149 001-050 5001VE PES PRAM 5001VE PVIS DIU 1MM J05 742VU RMP 1 2RG1 F79 001-099, 101-149 742VU RMP 1 2RG1 F70 151-199 722VU RMP 2 2RG2 X44 ALL ALL 721VU RMP 3 2RG3 V10 722VU SAT HI AMPL D/LNA 3RV K48 POST SB 23-3042 for A/C 057-099 722VU SAT R BSU & D/LNA 2RV F40 001-056, 101-149 722VU SATCOM SDU/RFU 1RV J48 POST SB 23-3208 for A/C 057-099 721VU SELCAL 6RN V08 ALL 5001VE VCC AC1 221MH H08 057-099, 151-199 5001VE VCC AC2 222MH H09 057-099, 151-199 5001VE VCC AC3 223MH H10 051-099, 151-199 5001VE VCC AC3 223MH G10 001-050, 101-149 5001VE VCC DC 240MH H11 151-199 742VU VHF 1 2RC1 A70 ALL 722VU VHF 2 2RC2 X43 ALL 721VU VHF 3 2RC3 S05 ALL 24. ELECTRICAL POWER PNL 735VU 101PP DESIGNATION 715VU 101XP 735VU 103PP 715VU 103XP 735VU 105PP 715VU 105XP FIN LOC EFF 2PN1 D21 ALL 1XN1 D55 ALL 3PN1 D22 ALL 2XN1 G55 ALL 4PN1 D23 ALL 721VU 107XP/115XP CTL 3XN1 H55 ALL 37XN W15 ALL 715VU 107XP/SHED 51XN B55 ALL 717VU 111XP 6XN1 D51 ALL 721VU 111XP CTL 16XN X07 ALL 725VU 111XP GND SPLY 1XX ALL 722VU 111XP GND SPLY CTL B21 717VU 113XP 10XX N38 ALL 7XN1 D52 ALL 721VU 113XP CTL 17XN X08 ALL 725VU 113XP GND SPLY 3XX ALL 722VU 113XP GND SPLY CTL 11XX N39 ALL 33XN E55 ALL 715VU 115XP 725VU 115XP GND SPLY 722VU 115XP GND SPLY CTL 715VU 131XPA 26VAC B22 17XX C22 ALL 20XX N37 ALL 721VU 1XP VOLT REF 4XN1 G54 ALL 41XN B02 ALL 721VU 1XP VOLT REF 45XN K07 ALL 721VU 1XP VOLT REF 43XN K06 ALL 721VU 1XP VOLT REF/TEST 29XE D04 ALL 2PN2 D28 ALL 735VU 202PP 715VU 202XP 735VU 204PP 715VU 204XP 1XN2 R56 ALL 3PN2 D27 ALL 735VU 206PP 2XN2 U56 ALL 4PN2 D26 ALL 715VU 206XP 3XN2 V56 715VU 208XP / SHED 722VU 208XP CTL 718VU 212XP ALL Q57 ALL 23XN S46 ALL 5XN 722VU 212XP CTL 6XN2 D59 ALL 18XN S44 ALL 715VU 212XP GND SPLY 2XX 722VU 212XP GND SPLY CTL N56 ALL 12XX N40 ALL 718VU 214XP 7XN2 D60 ALL 722VU 214XP CTL 19XN S45 715VU 214XP GND SPLY 4XX 722VU 214XP GND SPLY CTL ALL N57 ALL 13XX N41 ALL 725VU 216XP GND SPLY 9XX 725VU 218XP/SHED 58XN A23 715VU 232XPA 26VAC 742VU 26VAC 931XPA C24 ALL 054-099, 151-199 4XN2 U57 ALL 9XH R71 ALL 722VU 2XP VOLT REF 42XN B46 722VU 2XP VOLT REF 40XN H47 ALL 30XE D49 ALL 722VU 2XP VOLT REF/TEST 735VU 301PP ALL 735VU 303PP 11PB D24 ALL 9PB E24 ALL 742VU 401PP 5PH S73 ALL 740VU 401XP 15XH T71 742VU 401XP 15XH S66 001-099, 101-149 742VU 401XP CTL 17XH A77 ALL 742VU 401XP VOLT REF 8XH 151-199 Q62 ALL S74 ALL 742VU 403PP 6PH 742VU 407PP 10PH S75 ALL 740VU 470PP BAT1 SPLY 24PB1 T64 151-199 740VU 470PP BAT2 SPLY 24PB2 T65 151-199 151-199 742VU 470PP CTL 16PH B80 740VU 470PP TR ESS SPLY 15PH T66 151-199 735VU 501PP 3PR E27 ALL 742VU 501PP BAT SPLY 5PR R73 ALL R72 ALL 742VU 501PP ESS SPLY 7PR 722VU 501PP ESS/GND SWTG 8PR 735VU 502PP 9PR 742VU 502PP BAT SPLY 4PR N42 ALL E28 ALL 735VU 601PP 3PX R74 ALL D25 ALL 735VU 602PP 4PX E25 ALL 735VU 603PP 5PX E26 ALL 742VU 701PP 10PB1 S72 ALL 742VU 702PP 10PB2 S71 742VU 801/805PP CTL 3PH 742VU 801/805PP SHED CTL 4PH ALL N63 ALL N64 ALL 742VU 801PP 7PH S76 742VU 805PP 11PH S77 ALL 12XH R79 ALL 14XH N80 ALL 742VU 901XP 742VU 901XP VOLT REF 742VU 903XP 742VU 905XP 721VU 905XP SHED ALL 20XH R70 001-004, 101-102 21XH R69 ALL 742VU AC EMER DET RLY 13XH Q11 ALL 25XE E77 ALL 721VU APU GLC CTL 4XS 715VU APU TR Q07 001-099, 101-149 3PU3 S56 ALL 742VU BAT 1 CNTOR 12PB1 J73 742VU BAT 2 CNTOR 742VU BAT REF BCL 1 742VU BAT REF BCL 2 742VU BAT1/ESS BUS CNTOR 742VU BAT2/ESS BUS CNTOR 721VU BCL 1 301PP REF ALL 12PB2 H74 ALL 13PB1 J74 ALL 13PB2 H75 ALL 13PC1 J76 ALL 13PC2 H76 ALL 14PB1 Q08 ALL 721VU BCL 2 301PP REF 721VU BTC 1 GND SPLY 14PB2 Q09 ALL 8XU1 M09 ALL 721VU BTC 1 NORM 2XU1 Q05 ALL 722VU BTC 2 GND SPLY 8XU2 L45 722VU BUS 3-4 TIE CNTOR ALL 2XU2 N05 ALL 12PC S42 ALL 721VU CBMU 2XD 721VU BTC 2 NORM 722VU COML SHED 742VU CSM/G AUTO START 742VU CSM/G MAN START 742VU CSM/G OFF CTL X05 ALL 25XN N43 ALL 17XE J78 ALL 22XE N61 ALL 24XE N62 ALL 5000V DC SUPPLY 309PP REF BCL APU 14PB3 B02 ALL 5000V DC SUPPLY APU VM 2PV B05 ALL 5000V DC SUPPLY BAT APU CNTOR 12PB3 B04 ALL ALL 5000V DC SUPPLY BAT REF BCL APU 13PB3 B03 721VU ECMU 1 1PP SNSG 4XM X06 ALL 721VU ECMU 1 1XP SNSG 6XM K05 ALL 742VU ECMU 1 ESS 3XM1 J77 ALL 722VU ECMU 1 GND SPLY B 16XM M39 ALL 742VU ECMU 1 NORM 2XM1 A78 721VU ECMU 1 SNSG 3PP 722VU ECMU 2 2PP SNSG 722VU ECMU 2 2XP SNSG ALL 10XM N08 ALL 9XM S43 ALL 722VU ECMU 2 GND SPLY A 7XM F49 ALL 3XM2 H77 ALL 14XM M43 ALL 742VU ECMU 2 NORM 2XM2 E79 722VU ECMU1 SIDE 2 BUS SHED 46XN Q34 ALL 47XN W18 ALL 742VU ECMU 2 ESS 721VU ECMU2 SIDE 1 BUS SHED 722VU EPC A CTL ALL 722VU EPC B CTL 12XG M46 ALL 16XG M42 ALL 715VU ESS BUS ALTN SPLY 2XC 722VU ESS BUS ALTN SWTG 6XC 715VU ESS BUS NORM SPLY 1XC 721VU ESS BUS NORM SWTG 5XC 742VU ESS DC EMER CTL 742VU ESS NTWK AUTO ALT S57 ALL M38 ALL E54 ALL M14 ALL 14PC J75 ALL 721VU ESS TR MONG 13XC G72 ALL 5PE X10 ALL 722VU EXT A AVAIL 6XG 722VU EXT A NOT IN USE 722VU EXT B AVAIL M44 ALL 11XG M45 ALL 722VU EXT B NOT IN USE 14XG M40 ALL 15XG M41 ALL 722VU FLT SPLY SVCE BUS 8PN 717VU GALLEY AFT 12MC A54 717VU GALLEY AFT 24MC B60 057-099 718VU GALLEY AFT 24MC B60 001-056, 101-149, 151-199 715VU GALLEY AFT 12MC A54 001-056, 101-149, 151-199 T45 ALL 057-099 717VU GALLEY FWD MID 11MC B51 717VU GALLEY FWD MID 001-056, 101-149, 151-199 717VU GALLEY FWD MID 111M C51 ALL 23MC P56 057-099 710VU GALLEY FWD MID 11MC B51 057-099 715VU GALLEY FWD MID 23MC P56 001-056, 101-149, 151-199 715VU GALLEY FWD MID AFT 718VU GALLEY FWD MID AFT 112M C55 054-056, 151-199 223M P57 101-149 710VU GALLEY FWD MID AFT 223M P57 057-099 715VU GALLEY FWD MID AFT 223M P57 001-056, 151-199 715VU GALLEY FWD MID AFT 722VU GALLEY SHED 113M C55 ALL 3XA N44 ALL 721VU GALLEY SYS 1 1MC T10 ALL 722VU GALLEY SYS 2 2MC S39 ALL 721VU GAPCU 39XG P13 721VU GCU 1 722VU GND SPLY A 4XU1 Q10 ALL 4XU2 N06 ALL 2XG L42 151-199 722VU GND SPLY B 5XG 721VU GCU 2 L39 151-199 001-099, 101-149 722VU GPCU AC GND SPLY A 2XG L42 722VU GPCU AC GND SPLY B 5XG L39 721VU GPCU AC VOLT SNSG 721VU GPCU DC SPLY 742VU IDG 1 DISC 151-199 001-099, 101-149 27XG M15 001-099, 101-149 13XG Q06 001-099, 101-149 742VU LAND RCVY BUS SWTG A76 ALL D69 ALL 13PH E80 ALL 742VU LAND RCVY CTL 9XC 742VU LAND RCVY CTL 9XC 742VU IDG 2 DISC 1XT1 1XT2 K64 151-199 742VU STAT INV CTL A80 001-099, 101-149 10PR G73 ALL 6XB N65 ALL 722VU SVCE BUS GND SPLY 2PX 742VU REFUEL BAT/GND SW 715VU TR 1 M37 ALL 3PU1 J55 ALL 742VU TR 1 MONG 4PU A79 ALL 742VU TR 2 ESS MONG 9PU E78 ALL 725VU TR 2 GND SPLY 8XX 715VU TR 2 NORM C23 ALL 3PU2 W56 ALL 721VU TR 2 NORM MONG 10PU X09 ALL 722VU TR 2 NORM SPLY CTL 8PU J50 ALL 742VU TR ESS 4PE R76 ALL 25. EQUIPMENT /FURNISHINGS PNL DESIGNATION 5006VE AFT CARGO LOADING CTL FIN LOC EFF 5006VE AFT CARGO LOADING POWER LH1 101MY C13 ALL 103MY A10 001-099 5006VE AFT CARGO LOADING POWER LH2 102MY B10 001-099 5006VE AFT CARGO LOADING POWER RH1 105MY A13 001-099 5006VE AFT CARGO LOADING POWER RH2 104MY B13 001-099 5006VE AFT CLS / RH1-PWR 105MY A13 101-149, 151-199 5006VE AFT CLS / RH2-PWR 104MY B13 101-149, 151-199 5006VE AFT CLS/LH1-POWER 103MY A10 101-149, 151-199 5006VE AFT CLS/LH2-POWER 102MY B10 101-149, 151-199 742VU CLASS DIVIDER 1NC E65 057-099 5001VE FC SEAT CTL LH 3MR A03 001-056.101-149 5001VE FC SEAT CTL MID 2MR A07 001-056.101-149 5001VE FC SEAT CTL RH 1MR A11 722VU FLOOR PNL DR3 L SPLY 7DS 722VU FLOOR PNL DR3 R SPLY 8DS 001-056.101-149 H39 151-199 F31 151-199 722VU FLOOR PNL DR4 L SPLY 9DS J39 151-199 722VU FPH AFT/GALY DR4/L&R 101DS J44 151-199 722VU FPH AFT/GALY FWD 722VU FPH/IPCU AFT/SPLY 102DS H40 151-199 52DS R31 151-199 5002VE FWD CARGO LOADING CTL 5002VE FWD CARGO LOADING POWER LH1 3MY C13 ALL A10 ALL 5002VE FWD CARGO LOADING POWER LH2 2MY B10 ALL 5002VE FWD CARGO LOADING POWER RH1 5MY A13 ALL 5002VE FWD CARGO LOADING POWER RH2 4MY B13 ALL 5001VE MED OUT DC 9MF A14 151-199 5001VE MEDICAL OUT DOOR1 LH PWR AC 30MF J12 001-056 5001VE MEDICAL OUT DOOR1LH PWR OUT 31MF J09 001-056 5001VE MEDICAL OUTLET AC 31MF A04 057-099, 151-199 5001VE MEDICAL OUTLET AC 30MF A01 057-099, 151-199 5001VE MEDICAL OUTLET AC 30MF J06 101-149 5001VE MEDICAL OUTLET AC 31MF J03 101-149 722VU 1NA S31 151-199 5005VE RAZOR SOCKET 7MT E13 057-099 5005VE RAZOR SOCKET 5MT E12 057-099 5001VE RAZOR SOCKET 1MT F05 001-099,101-149 5001VE RAZOR SOCKET 3MT F06 057-099 5002VE VACUUM CLEANER SOCKET Z 132 21ME B05 ALL 5006VE VACUUM CLEANER SOCKET Z 152 22ME B03 ALL 5006VE VACUUM CLEANER SOCKET Z 162 23ME B05 ALL 5001VE VACUUM CLEANER SOCKET Z221 1ME E01 001-099 PILOTS OUTLETS/STAT INV 1MY 5001VE VACUUM CLEANER SOCKET Z221 1ME 5001VE VACUUM CLEANER SOCKET Z221 1ME D09 101-149 F01 151-199 5001VE VACUUM CLEANER SOCKET Z222 2ME E02 5001VE VACUUM CLEANER SOCKET Z222 2ME 5001VE VACUUM CLEANER SOCKET Z222 2ME 001-099 D10 101-149 F03 151-199 5001VE VACUUM CLEANER SOCKET Z241 3ME E03 5001VE VACUUM CLEANER SOCKET Z241 3ME 5001VE VACUUM CLEANER SOCKET Z241 3ME D11 101-149 F04 151-199 5001VE VACUUM CLEANER SOCKET Z242 4ME E04 5001VE VACUUM CLEANER SOCKET Z242 4ME 5001VE VACUUM CLEANER SOCKET Z242 4ME 5005VE VACUUM CLEANER SOCKET Z261 15ME 5005VE VACUUM CLEANER SOCKET Z261 15ME 5005VE VACUUM CLEANER SOCKET Z262 16ME 5005VE VACUUM CLEANER SOCKET Z262 16ME 5005VE VACUUM CLEANER SOCKET Z271 5ME 5005VE VACUUM CLEANER SOCKET Z271 5ME 5005VE VACUUM CLEANER SOCKET Z272 6ME 5005VE VACUUM CLEANER SOCKET Z272 6ME 001-099 001-099 D12 101-149 F02 151-199 C08 001-056, 101-149 D13 057-099, 151-199 C09 001-056, 101-149 D14 057-099, 151-199 C10 001-056, 101-149 D15 057-099, 151-199 C11 001-056, 101-149 D16 057-099, 151-199 26. FIRE PROTECTION PNL DESIGNATION FIN LOC EFF 742VU APU FIRE AUTOEXTNG 31WF G78 ALL 742VU APU FIRE SQUIB A 1WF J72 ALL 721VU APU FIRE SQUIB B 2WF P09 ALL 721VU APU FIRE VLV CTL 4WF P07 ALL 742VU APU FIRE VLV CTL 3WF J71 ALL 742VU CRG FIRE EXTNG/A 1WX J70 001-099, 101-149 722VU CRG FIRE EXTNG/B 2WX W44 ALL 721VU CRG HEATED SMK DET1 31WH S18 001-060, 101-149 722VU CRG HEATED SMK DET2 32WH X34 001-060, 101-149 721VU FDU LOOP B APU 2WG P08 ALL 742VU FIRE BTL1/A ENG1&2 37WE H73 ALL 722VU FIRE BTL1/B ENG1&2 37WE T37 ALL 742VU FIRE BTL2/A ENG1&2 38WE J69 ALL 722VU FIRE BTL2/B ENG1&2 38WE W38 ALL 742VU FIRE LOOP A APU 1WG D80 ALL 742VU FIRE LOOP A ENG 1 3WD1 D78 ALL 742VU FIRE LOOP A ENG 2 3WD2 D79 ALL 722VU FIRE LOOP B ENG 1 4WD1 W42 ALL 722VU FIRE LOOP B ENG 2 4WD2 W43 ALL 742VU S/D LDMCR 30WQ L69 101-149 742VU SDCU CHAN 1 11WH L75 001-099, 101-149 722VU SDCU CHAN 2 12WH T38 001-099, 101-149 27. FLIGHT CONTROLS PNL DESIGNATION FIN LOC EFF 742VU ECAM FLAP POS SYS1 1CF P62 ALL 722VU ECAM FLAP POS SYS2 2CF L33 ALL 742VU ECAM SLAT POS SYS1 1CN P63 ALL 722VU ECAM SLAT POS SYS2 2CN L34 ALL 742VU FCDC 1 6CE1 L76 001-099, 101-149 742VU FCDC 1 6CE1 E64 151-199 722VU FCDC 2 6CE2 T42 ALL 742VU FCPC 1 NORM 7CE1 C69 ALL 742VU FCPC 1 STBY 11CE K69 ALL 722VU FCPC 2 NORM 7CE2 V41 ALL 722VU FCPC 3 7CE3 V42 ALL 722VU FCPC 3 7CE4 V38 ALL 742VU FCSC 1 NORM 10CE1 C70 ALL 742VU FCSC 1 STBY 9CE G77 ALL 722VU FCSC 2 10CE2 T39 ALL 742VU FCSC2 STBY SPLY 41CE D66 ALL 742VU RUD T ACTR STBY 38CS L67 ALL 742VU RUD TRIM ACTR MOT1 30CS1 L78 ALL 722VU RUD TRIM ACTR MOT2 30CS2 T40 ALL 742VU RUD TRV LIM MOT 1 29CS1 E70 001-099, 101-149 722VU RUD TRV LIM MOT 2 29CS2 T41 001-099, 101-149 742VU RUD TRV LIM STBY 37CS D67 001-099, 101-149 742VU SFCC 1 FLAP 1CV L61 ALL 721VU SFCC 1 NORM 10CV X14 ALL 721VU SFCC 1 NORM AVAIL 10CW X13 ALL 742VU SFCC 1 SLAT 1CW L62 ALL 722VU SFCC 2 FLAP 2CV T43 ALL 722VU SFCC 2 SLAT 2CW V40 ALL 742VU THS ACTR MOT 1 5CS1 L77 ALL 722VU THS ACTR MOT 3 5CS3 V44 ALL 722VU THS ACTR MOT2 NORM 5CS2 V43 ALL 28. FUEL PNL DESIGNATION FIN LOC EFF 742VU 28VDC ESS BUS 6QC F65 ALL 742VU 28VDC ESS BUS 5QC F64 ALL 722VU ACTR MOT L&R 2CTL 2QB K39 ALL 742VU ACTR MOT L/R1 CTL 1QB 742VU APU AFT FUEL PUMP 1QC M71 ALL N78 ALL 742VU APU CTL & LP VLV MOT1 1QF K76 ALL 721VU APU FWD FUEL PUMP 2QC B09 ALL 742VU APU ISOL VLV 3QF K75 ALL 721VU APU LP VLV MOT 2 2QF P10 ALL 722VU BAT REFUEL SYSTEM 7QM K35 ALL 742VU FCMC 1 SPLY 1 1QM1 742VU FCMC 1 SPLY 2 2QM1 M76 ALL M78 ALL 742VU FCMC 2 SPLY 1 1QM2 722VU FCMC 2 SPLY 2 2QM2 742VU FCMC1 BAT R/F SPLY 6QM 742VU FCMC2 BAT R/S SPLY 9QM 742VU FCMC2 BAT R/S SPLY 9QM 722VU FUEL AFT XFR L SPLY2 M63 151-199 30QN1 Q36 ALL 742VU FUEL AFT XFR R SPLY2 30QN2 F68 ALL 742VU FUEL AUX FWD XFR 3QN B69 ALL 722VU FUEL HI LVL 1QJ K36 ALL 742VU FUEL L AFT XFR VLV 1QN1 E68 ALL 722VU FUEL L PUMP 1 CTL 722VU FUEL L PUMP 1 SPLY 54QA1 U46 ALL 51QA1 E34 ALL 742VU FUEL L PUMP 2 CTL 742VU FUEL L PUMP 2 SPLY 55QA1 D68 ALL 52QA1 K62 ALL 721VU FUEL L STBY PUMP 53QA1 J05 ALL 721VU FUEL L STBY PUMP CTL 56QA1 T05 ALL 742VU FUEL LO LVL 16QJ L74 ALL 742VU FUEL LP MOT 1 ENG1 1QG1 K77 ALL 742VU FUEL LP MOT 1 ENG2 1QG2 K78 ALL 722VU FUEL LP MOT 2 ENG1 2QG1 722VU FUEL LP MOT 2 ENG2 2QG2 U45 ALL Q39 ALL 742VU FUEL MAIN XFR L 6QL1 B67 722VU FUEL MAIN XFR L SPLY2 742VU FUEL MAIN XFR R 29QL1 Q38 ALL 6QL2 B68 ALL 722VU FUEL MAIN XFR R SPLY2 29QL2 Q37 ALL FUEL OVFL 2QJ K37 ALL 722VU M77 ALL K34 ALL M67 ALL M68 001-099, 101-149 ALL 722VU FUEL R AFT XFR VLV 722VU FUEL R PUMP 1 CTL 722VU FUEL R PUMP 1 SPLY 721VU FUEL R PUMP 2 CTL 742VU FUEL R PUMP 2 SPLY 721VU FUEL R STBY PUMP 721VU FUEL R STBY PUMP CTL 742VU FUEL TRIM TK INLET 56QA2 R05 ALL 6QN M61 ALL 742VU FUEL TRIM TK ISOL 5QN B70 742VU FUEL TRIMPIPE ISOL 4QN 721VU FUEL XFR L PMP CTL 2QL1 M62 ALL S06 101-149, 151-199 721VU FUEL XFR L PUMP 1QL1 E05 101-149, 151-199 742VU FUEL XFR OVRD 13QL E76 ALL 721VU FUEL XFR OVRD MAIN 27QL T14 ALL 722VU FUEL XFR R PMP CTL 2QL2 722VU FUEL XFR R PUMP 1QL2 Q46 101-149, 151-199 G48 101-149, 151-199 721VU L INR TK INLET VLV 8QL1 742VU R INR TK INLET VLV 8QL2 R12 ALL M64 ALL 722VU REFUEL CTR TK 12QU K38 721VU REFUEL L OUTR TK 1QU1 722VU REFUEL PNL CTL&IND 16QU R13 ALL K33 ALL 722VU REFUEL R ISOL 15QU K32 721VU REFUEL R OUTR TK 1QU2 722VU TRIM XFR PUMP CTL 26QN R14 ALL Q40 ALL 722VU TRIM XFR PUMP SPLY 24QN E40 742VU VLV BAT REFUEL SPLY 1 14QM1 M69 001-099, 101-149 VLV BAT REFUEL SPLY 1 14QM1 M65 151-199 742VU 742VU 1QN2 Q45 ALL 54QA2 Q43 ALL 51QA2 G45 ALL 55QA2 V13 ALL 52QA2 H62 ALL 53QA2 A11 ALL ALL 101-149, 151-199 ALL ALL 742VU VLV BAT REFUEL SPLY 2 14QM2 M70 001-099, 101-149 VLV BAT REFUEL SPLY 2 14QM2 M66 151-199 742VU XFEED VLV MOT 1 1QE B66 722VU XFEED VLV MOT 2 2QE Q44 ALL ALL 29. HYDRAULIC PNL DESIGNATION 725VU B ELEC PUMP FIN 3JC2 LOC EFF A24 ALL 717VU G ELEC PUMP 3JV2 A52 001-002 717VU G ELEC PUMP 3JV1 A51 ALL 721VU HSMU B + PART G 6JG 722VU HSMU Y + PART G 7JG U10 ALL X46 ALL 742VU HYD FIRE ENG 1 SOV 742VU HYD FIRE ENG 1 SOV 15JG2 D75 ALL 13JB D73 ALL 742VU HYD FIRE ENG 2 SOV 11JY 742VU HYD FIRE ENG 2 SOV D74 ALL 15JG1 D72 ALL 742VU HYD PRESS XDCR 3JS 721VU HYD PUMP B CTL 9JC 721VU HYD PUMP B ENG 1 11JB 721VU HYD PUMP G CTL 9JV 721VU HYD PUMP G ENG 1 14JG2 X11 ALL 722VU HYD PUMP G ENG 2 14JG1 X45 ALL 722VU HYD PUMP Y CTL 9JJ 722VU HYD PUMP Y ENG 2 12JY 722VU HYD PUMP Y SVCE 10JJ 742VU HYD RAT EXT SOL 2 5JR 722VU HYD SOV BUS SWTG 8JG 722VU HYD SOV ENG 2 NORM 15JY 722VU HYD SOV ENG 2 NORM 19JG D71 ALL X12 ALL U08 ALL U09 ALL R36 ALL T46 ALL N46 ALL D76 ALL R33 ALL R35 ALL 722VU LEAK MEAS VALVES 2JL R34 ALL N45 ALL 742VU RAT MAN ON 2JR K74 742VU RAT STOW CTL 1JR 715VU Y ELEC PUMP 3JJ4 D77 ALL C54 001-001 715VU Y ELEC PUMP 3JJ2 A55 ALL 725VU Y ELEC PUMP SVCE 3JJ1 A22 ALL 725VU Y ELEC PUMP SVCE 3JJ3 A21 001-001 ALL 30. ICE AND RAIN PROTECTION 742VU ANTI ICE AOA 1 OR 3 31DA1 Q68 722VU ANTI ICE AOA 2 1DA2 F48 721VU ANTI ICE AOA 3 31DA3 C05 721VU ANTI ICE ENG 1 2DN1 W06 722VU ANTI ICE ENG 2 2DN2 W39 721VU ANTI ICE P2T2 ENG 1 32DA1 L08 722VU ANTI ICE P2T2 ENG 2 32DA2 C44 722VU ANTI ICE PITOT 2 4DA2 F43 721VU ANTI ICE PITOT 3 4DA1 L07 742VU ANTI ICE PITOT1OR3 3DA Q72 721VU ANTI ICE STAT 1 11DA1 W09 722VU ANTI ICE STAT 2 11DA2 X41 721VU ANTI ICE STAT 3 11DA3 W10 721VU ANTI ICE TAT 1 12DA1 B06 722VU ANTI ICE TAT 2 12DA2 E43 721VU ANTI ICE WINDOWS L 4DG1 D03 722VU ANTI ICE WINDOWS R 4DG2 D43 742VU ANTI ICE WING 1DL L68 740VU ANTI ICE WSHLD L 1DG1 T74 742VU ANTI ICE WSHLD L 1DG1 S69 715VU ANTI ICE WSHLD R 1DG2 R57 5058VE CARGO DRAIN AFT 11DU B01 742VU ESS ANTI ICE AOA3 15DA H68 742VU ESS ANTI ICE PITOT 3 16DA H69 721VU FOOT WARMER 1DR B10 5060VE HEATER POTABLE 214DW C06 5060VE HEATER POTABLE 210DW C05 5060VE HEATER POTABLE 213DW B07 5058VE HEATER POTABLE 2DW A05 5058VE HEATER POTABLE 4DW B06 5058VE HEATER POTABLE 3DW B05 5058VE HEATER POTABLE 1DW B07 5060VE HEATER POTABLE 220DW C01 5060VE HEATER POTABLE 212DW A07 5060VE HEATER POTABLE 211DW A06 5060VE HEATER POTABLE 217DW A05 5060VE HEATER POTABLE DRAIN PNL 221DW C02 5058VE HEATER POTABLE DRAIN PNL 11DW C07 5060VE HEATER POTABLE SVCE PNL 21DV C07 5060VE HEATER WASTE 203DU A03 5060VE HEATER WASTE 202DU B03 5060VE HEATER WASTE 201DU B02 5060VE HEATER WASTE 219DW B01 5060VE HEATER WASTE 206DU C03 5058VE HEATER WASTE 2DU B03 5058VE HEATER WASTE 1DU B02 5060VE HEATER WASTE SVCE PNL 22DV A02 721VU ICE DET 1 2DD1 B07 722VU ICE DET 2 2DD2 F47 5001VE ICE PROT ESC SLIDE DOOR 1/2 1DH E09 ALL ALL ALL 151-199 151-199 ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL 151-199 001-099, 101-149 ALL 001-003 ALL ALL 053-099, 151-199 ALL ALL 051-056, 101-149, 151-199 ALL ALL ALL 101-149, 151-199 001-099, 101-149 ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL 001-099, 101-149 5001VE ICE PROT ESC SLIDE DOOR 1/2 5005VE ICE PROT ESC SLIDE DOOR 3/4 5005VE ICE PROT ESC SLIDE DOOR 3/4 5005VE ICE PROT ESC SLIDE DOOR 3/4 721VU PHC 1 722VU PHC 2 721VU PHC 3 742VU RAIN RPLNT CAPT 722VU RAIN RPLNT F/O 5060VE WATER ICE PROTECTION CTL 5058VE WATER ICE PROTECTION CTL 742VU WHC 1 722VU WHC 2 721VU WIPER CAPT 722VU WIPER F/O 1DH F07 2DH A13 2DH C13 2DH C01 2DA1 P12 2DA2 X40 2DA3 N07 5DB1 A69 5DB2 X42 218DW A01 9DW A01 5DG1 G64 5DG2 X39 2DB1 W05 2DB2 S40 151-199 001-056, 101-149 057-099 151-199 ALL ALL ALL 001-050, 053-099, 101-149, 151-199 001-050, 053-099, 101-149, 151-199 ALL ALL ALL ALL ALL ALL 31. INDICATING RECORDING PNL 721VU DESIGNATION ACMS DMU/DAR FIN 4TV LOC EFF F04 001-099, 101-149 742VU CLOCK 6FS B71 ALL 742VU CLOCK TBU 4FS K73 ALL 721VU DAR 115VAC 7TV F01 001-099, 101-149 721VU DAR 28VDC 6TV T13 001-099, 101-149 5000VE DC SUPPLY 309PP NO VDC 7WV B01 ALL 742VU ECAM CTL PNL 1WM B72 ALL 721VU ECAM DMC 1 NORM 12WT1 L12 10WT Q77 001-099, 101-149 12WT2 C45 001-099, 101-149 11WT2 W46 ALL 742VU ECAM DMC 1 STBY 722VU ECAM DMC 2 NORM 722VU ECAM DMC 2 SWTG 742VU ECAM DMC 3 001-099, 101-149 742VU ECAM EWD 12WT3 Q78 001-099, 101-149 6WK1 N77 ALL 742VU ECAM EWD SWTG 11WK1 B78 ALL 721VU ECAM SD 6WK2 L06 ALL 721VU ECAM SD SWTG 11WK2 S07 ALL 001-099, 101-149 742VU ECAM SWTG DMC 1 11WT1 B75 742VU ECAM SWTG DMC 3 11WT3 B76 742VU EFIS DMC 1 3WT1 722VU EFIS DMC 2 3WT2 ALL Q75 ALL K50 ALL 722VU EFIS DMC 2 SWTG 2WT2 W45 ALL 721VU EFIS DMC 3 NORM 3WT3 L11 742VU EFIS DMC 3 STBY 4WT 742VU EFIS SWTG DMC 1 2WT1 ALL Q76 ALL B73 ALL B74 742VU EFIS SWTG DMC 3 2WT3 742VU EMER GEN FREQ&VOLT 13WV 722VU FDIU/DFDR 7TU 742VU FWC 1 ALL N67 ALL F42 001-099, 101-149 722VU FWC 2 2WW1 Q80 ALL 2WW2 C48 ALL 721VU LA/DAR/QAR 28VDC 9TU 742VU ND CAPT 4WK1 722VU ND F/O 4WK2 742VU ND SWTG CAPT 9WK1 C49 ALL L71 ALL 722VU ND SWTG F/O 9WK2 V45 ALL 742VU PFD CAPT 5WK1 P80 ALL 722VU PFD F/O 5WK2 J49 ALL 10WK1 B77 U11 ALL Q66 ALL 742VU PFD SWTG CAPT 722VU PFD SWTG F/O 742VU SDAC 1 ALL 10WK2 R46 ALL 2WV1 Q79 ALL 722VU SDAC 2 2WV2 H49 ALL B79 ALL 742VU SDAC ESS DC MONG 5WV 721VU SDAC NORM DC1 MONG 3WV 722VU SDAC NORM DC2 MONG 4WV W11 ALL V46 ALL 742VU STAT INV FREQ&VOLT 11WV N66 ALL 32. LANDING GEAR PNL DESIGNATION 722VU BRK FAN CTL 722VU BRK FAN WHL 1+2 722VU BRK FAN WHL 3+4 721VU BRK FAN WHL 5+6 721VU BRK FAN WHL 7+8 722VU BRK TEMP WHL1 TO 4 742VU BRK TEMP WHL5 TO 8 742VU BSCU SYS 1 722VU BSCU SYS 2 742VU L/G DNLK IND 742VU L/G FREE FALL SYS1 742VU L/G FREE FALL SYS2 721VU L/G SAFETY VLV 742VU LGCIU 1 722VU LGCIU 2 721VU NLG OVSTEER IND 742VU NLG OVSTEER WARN SPLY 722VU PARK BRK CTL 742VU PARK BRK EMER CTL 721VU TYRE PRESS IND FIN 5GD 1GD 2GD 3GD 4GD 2GW 1GW 1GG 2GG 1GB 1GF 2GF 3GA 1GA 2GA 6GH 4GH 1GZ 2GZ 1GV LOC EFF R44 ALL G36 ALL G39 ALL E08 ALL E11 ALL U39 ALL G63 ALL G62 ALL U37 ALL C76 ALL K71 ALL G74 ALL S12 ALL L63 ALL U38 ALL S16 001-099, 101-149 L65 001-099, 101-149 P35 ALL K70 ALL T09 ALL 33. LIGHTS PNL DESIGNATION FIN LOC EFF 721VU BEACON 1LV A08 ALL 721VU WING SCAN LIGHT L 4LX B04 ALL 721VU ENG SCAN LIGHT L 3LX B03 ALL 721VU CAB EMER LT 3WL 721VU ANN LT SYS 1 3LP1 C03 ALL C02 ALL 721VU INTG LT 5VAC 5LF 721VU LT RWY TURN OFF L 1LC 721VU LT TAXI/T.O L 1LR 721VU INTG LT OVHD PNL 4LF H02 ALL S14 ALL 721VU INTG LT PED + MAIN 3LF S13 721VU ANN LT RLY SYS 1 7LP 721VU CKPT LT CAPT+MISC 4LE3 721VU CKPT LT CAPT+MISC 4LE1 721VU LAV LT 2LQ U05 ALL W14 ALL 722VU WING STROBE LT 10LV A43 ALL 722VU BEACON 5LV A40 ALL 722VU LOGO LT 2LY B50 ALL 722VU LOGO LT 1LY B49 ALL 722VU ENG SCAN LIGHT R 2LX B48 ALL 722VU WING SCAN LIGHT R 1LX B47 ALL 722VU ANN LT SYS 2 3LP2 722VU LT TAXI/T.O R 2LR C46 ALL D48 ALL 722VU LT RWY TURN OFF R 2LC 722VU LT LDG R 2LB D47 ALL D46 ALL 722VU AVNCS OUTLET 115V 4LS F44 722VU NAV 2 LT SPLY/CTL 2LA 722VU NAV LT 1LA ALL H33 ALL H32 ALL 722VU CKPT OUTLET 115VAC 2LE J31 ALL 722VU CKPT OUTLET 28VDC 6LE P40 ALL 722VU CKPT LT SWTG+DOME 1LE2 P39 ALL 722VU NLG OUTLET 28V 2LL P38 ALL 722VU MLG OUTLET 28V 6LL P37 ALL 722VU NLG + MLG WELL LT 4LL P36 ALL 722VU LT TAXI/T.O CTL 3LR 722VU CKPT LT F/O+MISC 4LE2 R41 ALL R40 ALL 722VU AVNCS COMPT LT 12LS 722VU AVNCS OUTLET 28V 2LS 722VU ANN LT RLY SYS 2 6LP 742VU CKPT LT EMER 1LE1 R37 ALL E75 ALL 742VU ANN LT RLY ESS 8LP E74 ALL 742VU EMER CAB LT 1WL E73 ALL 742VU EMER CAB LT 2WL E72 ALL H05 ALL H03 ALL ALL U12 ALL U06 ALL R39 ALL R38 ALL 742VU EMER CAB LT 9WL E71 742VU LT LDG CTL 3LB 742VU ANN LT STAT INV 3LP3 G61 ALL P79 ALL 742VU LT LDG L 1LB 742VU ANN LT ESS 3LP5 ALL Q69 ALL Q63 ALL 5001VE LIGHT - CABIN WINDOW AFT RH 304LG B04 001-050, 101-149, 151-199 5001VE LIGHT - CABIN ENTRY AFT 315LG B06 001-056, 101-149 5001VE LIGHT - CABIN CENTER AFT 314LG B05 001-056, 101-149 5001VE LIGHT - CABIN WINDOW AFT LH 311LG B03 001-056, 101-149, 151-199 5001VE LIGHT - CABIN CLNG AFT RH 310LG B02 001-056, 101-149, 151-199 5001VE LIGHT - CABIN CLNG AFT LH 305LG B01 5001VE LIGHT - CABIN ENTRY FWD 5001VE LIGHT - CABIN CENTER MID 5001VE LIGHT - CABIN CENTER FWD 5001VE LIGHT - CABIN WINDOW MID RH 5001VE LIGHT - CABIN WINDOW MID LH 5001VE LIGHT - CABIN WINDOW FWD RH 5001VE LIGHT - CABIN WINDOW FWD LH 5001VE LIGHT - CABIN CLNG MID RH 5001VE LIGHT - CABIN CLNG MID LH 5001VE LIGHT - CABIN CLNG FWD RH 5001VE LIGHT - CABIN CLNG FWD LH 5001VE LIGHT - CABIN ENTRY AFT 5001VE COM CTR DC 5001VE LIGHT - CABIN ENTRY FWD 5001VE LIGHT - CABIN WINDOW MID RH 5001VE LIGHT - CABIN WINDOW MID LH 5001VE LIGHT - CABIN WINDOW FWD RH 5001VE LIGHT - CABIN WINDOW FWD LH 5001VE LIGHT - CABIN CLNG MID RH 5001VE LIGHT - CABIN CLNG MID LH 5001VE LIGHT - CABIN CLNG FWD RH 001-056, 101-149, 151-199 316LG C12 001-099, 101-149 312LG C11 001-099 313LG C10 001-099, 101-149 302LG C09 001-099, 101-149 309LG C08 001-099, 101-149 300LG C07 001-099, 101-149 307LG C06 001-099, 101-149 308LG C05 001-099, 101-149 303LG C04 001-099, 101-149 306LG C03 001-099, 101-149 301LG C02 001-099, 101-149 315LG B05 151-199 318LG C11 151-199 316LG C09 151-199 302LG C08 151-199 309LG C07 151-199 300LG C06 151-199 307LG C05 151-199 308LG C04 151-199 303LG C03 151-199 5001VE LIGHT - CABIN CLNG FWD LH 306LG C02 151-199 301LG C01 151-199 5001VE LIGHT PAX & CABIN ATTND 9LW 5001VE LIGHT PAX & CABIN ATTND 8LW 5001VE LIGHT PAX & CABIN ATTND 10LW 5001VE LIGHT PAX & CABIN ATTND 7LW 5001VE LIGHT PAX & CABIN ATTND 2LW 5001VE LIGHT PAX & CABIN ATTND 4LW D15 151-199 D14 151-199 D13 151-199 D12 151-199 D05 151-199 D02 151-199 5001VE LAV FWD&MID DOOR 2 OCCUPIED 1WJ F13 151-199 5001VE LAV FWD&MID DOOR 2 LIGHT 1LQ F12 151-199 5002VE CARGO LIGHTING C/C 1LU A05 ALL 5002VE CARGO LIGHTING AREA 3LU A04 5002VE ACCESSORY COMPT SOCKET 1LK ALL C05 ALL 5005VE LIGHT PAX & CABIN ATTND 12LW B10 001-056, 101-149 5005VE LIGHT PAX & CABIN ATTND 11LW B09 001-056, 101-149 5005VE LIGHT PAX & CABIN ATTND 6LW B08 001-056, 101-149 5005VE LIGHT PAX & CABIN ATTND 3LW B07 001-056, 101-149 5005VE LIGHT APU 2LJ B06 001-056, 101-149 5005VE LIGHT SEC19 1LJ B05 001-056, 101-149 5005VE LIGHT LAV AFT & MID 11LQ B04 001-056, 101-149 5005VE LAV AFT&MID DOOR 3 OCCUPIED 11WJ 5005VE LIGHT PAX & CABIN ATTND 12LW C01 001-056, 101-149 D12 057-099, 151-199 5005VE LIGHT PAX & CABIN ATTND 11LW 5005VE LIGHT PAX & CABIN ATTND 6LW 5005VE LIGHT PAX & CABIN ATTND 3LW 5005VE LIGHT LAV AFT & MID 11LQ 5005VE LIGHT APU 2LJ 5005VE LIGHT SEC19 1LJ D07 057-099, 151-199 D06 057-099, 151-199 5005VE LAV AFT&MID DOOR 3 OCCUPIED 11WJ E07 5001VE LIGHT PAX & CABIN ATTND 10LW 5001VE LIGHT PAX & CABIN ATTND 9LW D10 001-099 D09 001-099 5001VE LIGHT PAX & CABIN ATTND 8LW 5001VE LIGHT PAX & CABIN ATTND 7LW 5001VE LIGHT PAX & CABIN ATTND 5LW 5001VE LIGHT PAX & CABIN ATTND 4LW 5001VE LIGHT PAX & CABIN ATTND 2LW 5001VE LIGHT PAX & CABIN ATTND 1LW D11 057-099, 151-199 D10 057-099, 151-199 D09 057-099, 151-199 D08 057-099, 151-199 D08 001-099 D07 001-099 D06 001-099, 151-199 D05 001-099 D04 001-099 D03 001-099 5001VE LAV FWD&MID DOOR 2 OCCUPIED 1WJ F03 5001VE LAV FWD&MID DOOR 2 LIGHT F01 1LQ 057-099, 151-199 001-099, 101-149 5001VE COM CTR AC 001-099, 101-149 318LG D13 003-056 319LG D11 003-056 5001VE LIGHT - CABIN WINDOW AFT RH 304LG B08 051-099 5001VE LIGHT - CABIN ENTRY AFT 315LG B10 057-099 5001VE LIGHT - CABIN CENTER AFT 314LG B09 057-099 5001VE LIGHT - CABIN WINDOW AFT LH 311LG B07 057-099 5001VE LIGHT - CABIN CLNG AFT RH 310LG B06 057-099 5001VE LIGHT - CABIN CLNG AFT LH 305LG B05 057-099 5001VE COM CTR DC 318LG B04 057-099 5001VE COM CTR AC 319LG B02 057-099 5001VE LIGHT - CABIN CENTER MID 5001VE LIGHT PAX & CABIN ATTND 312LG C11 101-149 10LW D08 101-149 5001VE LIGHT PAX & CABIN ATTND 9LW 5001VE LIGHT PAX & CABIN ATTND 8LW 5001VE LIGHT PAX & CABIN ATTND 7LW 5001VE LIGHT PAX & CABIN ATTND 5LW 5001VE LIGHT PAX & CABIN ATTND 4LW 5001VE LIGHT PAX & CABIN ATTND 2LW 5001VE COM CTR DC D07 101-149 D06 101-149 D05 101-149 D04 101-149 D03 101-149 D02 101-149 5001VE LIGHT PAX & CABIN ATTND 1LW 5001VE COM CTR DC D01 101-149, 151-199 318LG E11 101-149 5001VE COM CTR AC 319LG E10 101-149 5006VE AFT CARGO LIGHTING 2LU A05 ALL 5006VE AFT CARGO LIGHTING 4LU A04 ALL 5006VE LIGHT SEC 18 14LJ C03 ALL 34. NAVIGATION system PNL DESIGNATION FIN LOC EFF 742VU ADF 1 3RP1 P78 ALL 742VU ADF 1 / VOR 1 SWTG 5FN F66 001-099, 101-149 722VU ADF 2 3RP2 E48 ALL 721VU ADIRU 1 & 3 SWTG 9FP K02 ALL 742VU ADIRU 1 115VAC 4FP1 N75 ALL 742VU ADIRU 1 BAT 7FP1 K72 ALL 722VU ADIRU 2 115VAC 4FP2 H46 ALL 742VU ADIRU 2 BAT 7FP2 G75 ALL 721VU ADIRU 3 115VAC 4FP3 G04 ALL 742VU ADIRU 3 115VAC ESS 13FP P68 ALL 742VU ADIRU 3 BAT 7FP3 G76 ALL 742VU ADIRU 3 SWTG 8FP F69 ALL 742VU ADIRU/AOA 1 26VAC 5FP1 P64 ALL 722VU ADIRU/AOA 2 26VAC 5FP2 L32 ALL 721VU ADIRU/AOA 3 26VAC 5FP3 M05 ALL 721VU AOA 1 & 3 TEST 6FP1 W12 ALL 722VU AOA 2 TEST+ADIRU 2 6FP2 T44 ALL 742VU AOA3 & PRB3 SWTG CTL 51FP H65 ALL 742VU ATC 1 3SH1 Q64 ALL 722VU ATC 2 3SH2 E47 ALL 742VU COM NAV/MMR/1 42RT1 N68 005-099, 103-149, 151-199 722VU COM NAV/MMR/2 42RT2 H43 005-099, 103-149, 151-199 742VU DDRMI 2FN P77 001-099, 101-149 742VU DME 1 2SD1 Q65 001-099, 101-149 742VU DME 1 2SD1 N79 POST SB 34-3204 for A/C 001-099, 101-149 722VU DME 2 2SD2 E50 ALL 742VU EMER AOA3 26VAC 50FP P61 ALL 721VU GPSSU 1 2SN1 W16 001-002 722VU GPSSU 2 2SN2 S38 001-002 721VU GPWC 3WZ K01 ALL 742VU ILS 1 2RT1 P66 001-004, 101-102 722VU ILS 2 2RT2 H45 001-004, 101-102 742VU INST STBY 11FC D64 151-199 742VU INST STBY BAT 13FC K66 151-199 721VU PVI 2FW B08 001-001,051-051,053-099,101-149 721VU RA 1 2SA1 L14 ALL 722VU RA 2 2SA2 E46 ALL 742VU STBY ALTM 2FV M72 001-099, 101-149 742VU STBY HORIZON 1FC F67 001-099, 101-149 721VU TCAS 4SG B05 ALL 742VU VOR 1 2RS1 N76 ALL 722VU VOR 2 2RS2 E45 ALL 742VU WXR 1 9SQ1 H64 ALL 722VU WXR 2 9SQ2 E49 ALL 35. OXYGEN PANEL DESIGNATION 742VU PAX OXY CTL 742VU PAX OXY CTL 742VU PAX OXY CTL 742VU PAX OXY CTL 742VU CREW OXY CTL 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY 742VU PAX OXY FIN LOC 4WR C80 3WR C79 2WR C78 1WR C77 4HT L73 5WR P76 6WR P75 7WR P74 8WR P73 9WR P72 10WR P71 11WR P70 12WR P69 36. PNEUMATIC PNL DESIGNATION FIN LOC 721VU AIR BLEED ENG 1 6HA1 R06 722VU AIR BLEED ENG 2 6HA2 W41 722VU AIR XBLEED 1HV R45 742VU AIR XBLEED MAN 2HV C75 742VU BLEED VLV ENG 1 3HA1 C74 722VU BLEED VLV ENG 2 3HA2 T35 742VU BMC 1 2HA1 C73 722VU BMC 2 2HA2 T34 38. WATER/WASTE PNL DESIGNATION 5005VE LAV AFT&MID DOOR 3 HOT WTR 5005VE LAV AFT&MID DOOR 3 HOT WTR 5005VE LAV AFT&MID DOOR 3 HOT WTR FIN LOC EFF 102MB C05 001-056, 101-149 103MB C04 001-056, 101-149 5005VE LAV AFT&MID DOOR 3 HOT WTR 104MB C03 001-056 101MB C02 001-056, 101-149 5005VE LAV AFT&MID DOOR 3 HOT WTR 102MB E11 057-099, 151-199 5005VE LAV AFT&MID DOOR 3 HOT WTR 103MB E10 057-099, 151-199 5005VE LAV AFT&MID DOOR 3 HOT WTR 104MB E09 057-099, 151-199 5005VE LAV AFT&MID DOOR 3 HOT WTR 101MB E08 057-099, 151-199 5001VE LAV FWD&MID DOOR 2 HOT WTR 4MB F08 001-056 5001VE LAV FWD&MID DOOR 2 HOT WTR 3MB F08 151-199 5001VE LAV FWD&MID DOOR 2 HOT WTR 1MB F11 001-099, 101-149 5001VE LAV FWD&MID DOOR 2 HOT WTR 2MB F10 001-099, 101-149 5001VE LAV FWD&MID DOOR 2 HOT WTR 5005VE LAV PWR LH AFT 3MB F09 001-099, 101-149 104MG D08 101-149 104MG F08 151-199 5005VE LAV PWR LH FWD 101MG F05 151-199 5005VE LAV PWR LH L11 101MG F05 057-099 5005VE LAV PWR LH L35 102MG F06 057-099 5005VE LAV PWR LH L61 103MG F07 057-099 5005VE LAV PWR LH L73 104MG F08 057-099 5005VE LAV PWR LH MID-AFT 103MG F07 151-199 5005VE LAV PWR LH MID-FWD 102MG F06 5005VE LAV PWR RH AFT 4MG 5005VE LAV PWR RH AFT 4MG 151-199 D11 003-056 F11 151-199 5005VE LAV PWR RH L36 2MG F13 057-099 5005VE LAV PWR RH L62 3MG F12 057-099 5005VE LAV PWR RH L74 4MG F11 057-099 5005VE LAV PWR RH MID AFT 3MG F12 151-199 5005VE LAV PWR RH-MID-AFT 3MG 5005VE LAV PWR RH-MID-AFT 4MG D12 101-149 D11 101-149 5005VE LAV PWR RH-MID-FWD 2MG F13 151-199 5001VE LAVATORY FWD & MID DOOR 2 2MB F11 151-199 5001VE LAVATORY FWD & MID DOOR 2 1MB F10 151-199 104MG D08 001-056 103MG D07 001-056, 101-149 5005VE LAV PWR LH AFT 5005VE LH - LAV PWR IN LOCATION 5005VE LH - LAV PWR IN LOCATION 5005VE LH - LAV PWR IN LOCATION 5005VE LH - LAV PWR IN LOCATION 102MG D06 001-056, 101-149 101MG D05 001-056, 101-149 5005VE RH - LAV PWR IN LOCATION 1MG 5005VE RH - LAV PWR IN LOCATION 4MG 5005VE RH - LAV PWR IN LOCATION 2MG 5005VE RH - LAV PWR IN LOCATION 3MG 5005VE VACUUM GEN 6MG D14 001-002 D11 001-002 D13 001-056, 101-149 D12 001-056 5005VE VACUUM GEN D17 001-056, 101-149 106MG D02 001-056, 101-149 5005VE VACUUM GEN 6MG F17 057-099, 151-199 5005VE VACUUM GEN 106MG F02 5005VE VACUUM TOILET SYSTEM 5MG 057-099, 151-199 5005VE VACUUM TOILET SYSTEM D15 001-056, 101-149 105MG D04 001-056, 101-149 5005VE VACUUM TOILET SYSTEM 5MG F15 057-099, 151-199 5005VE VACUUM TOILET SYSTEM 105MG F04 057-099, 151-199 5005VE WATER SYSTEM AIR COMPRESSOR 1MD 5005VE WATER SYSTEM AIR COMPRESSOR 1MD 5005VE WATER SYSTEM DRAIN 1MP 5005VE WATER SYSTEM DRAIN 1MP 5005VE WATER SYSTEM QUANT IND 1MA 5005VE WATER SYSTEM QUANT IND 1MA C13 051-056 E02 057-099, 151-199 C16 001-056, 101-149 E05 057-099, 151-199 C17 001-056, 101-149 E06 057-099, 151-199 45. ONBOARD MAINTENANCE PNL DESIGNATION FIN LOC EFF 721VU DATA LOAD SEL 5TD R10 001-099, 101-149 721VU PRINTER 1TP D02 ALL 721VU DATA LOADER 3TD L13 ALL 721VU TEST PLUG 1 7TM R11 ALL 721VU CMC 1 SWTG 4TM1 U07 ALL 721VU DLS/DLRB SPLY 27TD S20 151-199 722VU CMC 2 3TM2 D45 001-099, 101-149 722VU CMC 2 SWTG 4TM2 W40 001-099, 101-149 722VU TEST PLUG 2 6TM Q42 ALL 742VU CMC 1 3TM1 N72 ALL 46. AIR TRAFFIC AND INFORMATION 721VU ATSU 1 SWTG 5TX1 T19 721VU ATSU1 115VAC PWR SPLY 3TX1 G09 721VU DCDU 1 6TX1 T20 722VU DCDU 2 6TX2 R32 49. APU PANEL DESIGNATION 5000VE APU COM MODE SUPPLY 5000VE APU CTL 742VU APU INTRPT SPLY 5000VE APU INTRPT SUPPLY 5000VE APU MAIN SUPPLY 742VU APU START CTL 5000VE OIL HEATER 5000VE OIL SCV HEATER FIN LOC EFF 3KD A04 ALL 2KD A02 ALL 35KD C71 ALL 58KD A05 ALL 1KD A03 ALL 1KA C72 ALL 1KT C01 001-002 1KT C01 003-099, 101-149, 151-199 52. DOORS PANEL DESIGNATION FIN LOC 5002VE CARGO DOOR CTL 1MJ C03 722VU CKPT DOOR LATCH 1MQ V39 721VU DOORS & SLIDES CTL 3MJ N09 722VU DOORS & SLIDES CTL 2MJ P41 70. ENGINE PANEL DESIGNATION 721VU EIVMU 1 FIN LOC EFF 14KS1 P05 001-099, 101-149 721VU EIVMU 1 14KS1 N10 151-199 14KS2 P06 ALL 721VU EIVMU 2 742VU FADEC A ENG 1 742VU FADEC A ENG 2 722VU FADEC B ENG 1 12KS1 Q73 ALL 12KS2 Q74 ALL 722VU FADEC B ENG 2 13KS1 D44 ALL 13KS2 K49 ALL 742VU HP FUEL SOV ENG 1 1KC1 742VU HP FUEL SOV ENG 2 1KC2 742VU IGN SYS A ENG 1 1EH1 742VU IGN SYS A ENG 2 1EH2 721VU IGN SYS B ENG 1 2EH1 C68 ALL D70 ALL Q70 ALL Q71 ALL 722VU IGN SYS B ENG 2 2EH2 G03 ALL F50 ALL 721VU OIL LO PR RLY ENG 1 5EN1 V12 ALL 722VU OIL LO PR RLY ENG 2 5EN2 S41 ALL 721VU T / R LOCKING ENG 1 3EG1 722VU T / R LOCKING ENG 2 3EG2 G05 ALL C43 ALL 721VU T-R COWL OPENING ENG1 1EG1 722VU T-R COWL OPENING ENG2 1EG2 722VU TR INHIB A ENG 1 7KS1 721VU TR INHIB A ENG 2 7KS2 721VU TR INHIB B ENG 1 8KS1 722VU TR INHIB B ENG 2 8KS2 U14 ALL X38 ALL U35 ALL R15 ALL R16 ALL U34 ALL C/B PANEL LOCATION LOCATION E/E COMPT 721VU/722VU 됫쪽 E/E COMPT 721VU 됫쪽 L/H SIDE E/E COMPT 721VU 됫쪽 R/H SIDE E/E COMPT MAIN RACK 앞 왼쪽 E/E COMPT MAIN RACK 앞 오른쪽 E/E 721VU와 722VU 사이 중간 내부 E/E 721VU와 722VU 사이 하단 내부 E/E CKPT에서 E/E 접근 사다리 앞 742VU 바로 위 BULK CGO DOOR 왼쪽 옆 CKPT DOOR 전방 천장 FWD CGO DOOR 입구 천장 AFT GLY 입구 천장 AFT CGO DOOR 입구 천장 E/E에서 FWD CGO 접근 DOOR 옆 AFT CGO DOOR 왼쪽 옆 CKPT OVHD PNL PANEL 715VU 717VU 718VU 721VU 722VU 725VU 735VU 742VU 743VU 5000VE 5001VE 5002VE 5005VE 5006VE 5058VE 5060VE 261VU 262VU A/C EFF CODE/ MSN NO. A/C NO. HL7524 HL7525 HL7540 HL7550 HL7551 HL7553 HL7554 HL7584 HL7585 HL7586 HL7587 HL7701 HL7702 HL7709 HL7710 HL7720 HL7538 HL7539 HL7552 HL8211 EFF 003 004 005 001 002 052 051 053 054 055 056 057 058 059 060 061 101 102 103 1133 MSN 206 219 214 162 172 267 156 338 350 351 368 425 428 484 490 550 222 226 258 1133 HL8212 1155 1155 A330 ECAM MESSAGE RESET GUIDE Figure 2: RH Reset Panel. Created by: Brett A Mumford 5 of 45 A330 ECAM MESSAGE RESET GUIDE CAB PR CAB PR CAB PR CAB PR CAB PR CAB PR CAB PR CAB PR CAB PR CAB PR AFT OFV NOT OPEN. NO DISPATCH - Check forward outflow Valve OPEN. EXCESS CABIN ALT. Not applicable - Reset breakers CPC 1 and CPC 2 on LH and RH reset panels FWD OFV NOT OPEN. NO DISPATCH - Check aft outflow Valve OPEN. LDG ELEV FAULT MEL 21-31-05 - Reset breakers CPC 1 and CPC 2 on LH and RH reset panels. - Reset breaker, DMC 3 on RH reset panel. LO DIFF PR Not applicable - No Action required. SAFETY VALVE OPEN MEL 21-31-05 - If safety valves are visually closed. - Reset breakers SDAC 1 and 2 on LH and RH reset panels. SYS 1 + 2 FAULT MEL 21-31-05 - Reset breakers CPC 1 and 2 on LH and RH reset panels. SYS 1 FAULT MEL 21-31-05 - Reset breaker CPC 1 on LH reset panel. SYS 2 FAULT MEL 21-31-05 - Reset breaker CPC 2 on RH reset panel. Created by: Brett A Mumford 6 of 45 A330 ECAM MESSAGE RESET GUIDE COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND COND AFT CRG ISOL FAULT MEL 21-28-03-B - Reset breaker VENT CONT Lane 1/2 on RH reset panel. AFT CRG VENT FAULT MEL 21-28-03-A - Reset breaker VENT CONT Lane 1/2 on RH reset panel. BULK CRG DUCT OVHT MEL 21-43-02 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. BULK CRG HEAT FAULT MEL 21-43-02 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. BULK CRG ISOL FAULT MEL 21-28-04-B - Reset breaker VENT CONT Lane1/2 on RH reset panel. BULK CRG VENT FAULT MEL 21-28-04-A - Reset breaker VENT CONT Lane 1/2 on RH reset panel. L + R CAB VENT FAULT MEL 21-21-01 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. L CAB VENT FAULT MEL 21-21-01 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. LAV + GALLEY FAN FAULT MEL 21-23-01 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. R CAB VENT FAULT MEL 21-21-01 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. VENT SYS FAULT MEL 21-26-04 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. ZONE CTLR FAULT MEL 21-63-01 - Reset breaker ZONE CONT on RH reset panel. ZONE CTLR 2 FAULT MEL 21-63-01 - Reset breaker ZONE CONT on RH reset panel. ZONE REGUL FAULT MEL 21-63-01 or 21-63-03 - Reset breaker ZONE CONT on RH reset panel. CAB REST ISOL FAULT MEL 21-21-04 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. DUCT OVHT MEL 21-63-03 or 21-43-01 - Reset breaker ZONE CONT on RH reset panel. FWD CRG COOL FAULT MEL 21-28-02-D - Reset breaker VENT CONT Lane 1/2 on RH reset panel. FWD CRG HEAT FAULT MEL 21-43-01 - Reset breaker VENT CONT Lane 1/2 on RH reset panel. FWD CRG ISOL FAULT MEL 21-28-02-B - Reset breaker VENT CONT Lane 1/2 on RH reset panel. FWD CRG VENT FAULT MEL 21-28-02-A - Reset breaker VENT CONT Lane 1/2 on RH reset panel. Created by: Brett A Mumford 7 of 45 A330 ECAM MESSAGE RESET GUIDE VENT VENT VENT VENT VENT VENT BLOWING FAULT MEL 21-21-02 or 21-26-08-A - Reset breaker AEVC on LH reset panel. EXTRACT FAULT MEL 21-26-01 - Reset breaker AEVC on LH reset panel. GND COOL FAULT MEL 21-27 - Reset breaker AEVC on LH reset panel. OVBD VALVE FAULT MEL 21-26-02 - Reset breaker AEVC on LH reset panel. PACK BAY VENT FAULT MEL 21-25 - Reset breaker AEVC on LH reset panel. Created by: Brett A Mumford 8 of 45 A330 ECAM MESSAGE RESET GUIDE AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR AIR ABNORM BLEED CONFIG MEL 36-11-01 - Operational message… No further action required. APU BLEED FAULT MEL 36-12-02 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) APU BLEED LEAK MEL 36-12-01 or 36-22-03 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) BLEED LO TEMP MEL 36-11-01 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) BMC 1 + 2 FAULT MEL 36-11-01 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) BMC 3 + 4 FAULT MEL 36-11-01 - Perform BITE Test of BMC 3 & 4 on MCDU (ATA36) BMC 1 (2) (3) (4) FAULT MEL 36-11-01 - Perform BITE Test of BMC 1 (2) (3) (4) on MCDU (ATA36) ENG 1 (2) (3) (4) BLEED FAULT MEL 36-11-01 - Perform BITE Test of BMC 1 (2) (3) (4) on MCDU (ATA36) ENG 1 (2) (3) (4) BLEED LEAK NO DISPATCH or MEL 36-2201 - Perform BITE Test of BMC 1 (2) (3) (4) on MCDU (ATA36) ENG 1 (2) (3) (4) BLEED NOT CLSD MEL 36-11-02 - Perform BITE Test of BMC 1 (2) (3) (4) on MCDU (ATA36) ENG 1 (2) (3) (4) HPV NOT OPEN MEL 36-11-07 - Perform BITE Test of BMC 1 (2) (3) (4) on MCDU (ATA36) HOT AIR SYS 1 (2) FAULT MEL 21-63-03 - Perform System Test of the Temp CTL system on MCDU (ATA21) L WING LEAK NO DISPATCH or MEL 36-2202 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) - Switch ON/OFF ENG 1 Bleed L WING LEAK DET FAULT MEL 36-22-02 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) PACK 1 + 2 FAULT MEL 21-52-01 - Check push button switch PACKS 1 & 2 ON. - Passenger doors not closed and locked? PACK 1 OFF MEL 21-52-01 - Check push button switch PACK 1 ON. PACK 1 OVHT MEL 21-52-01 - Perform System Test of the Temp CTL system on MCDU (ATA21) - Faulty Pack Controller 1 (531HH) PACK 1 REGUL FAULT MEL 21-52 or 21-53 - Perform System Test of the Temp CTL system on MCDU (ATA21) - Faulty Pack Controller 1 (531HH) PACK 2 OFF MEL 21-52-01 - Check push button switch PACK 2 ON. PACK VALVE 1 FAULT MEL 21-52-01 - Faulty Pack Controller 1 (531HH) PACK VALVE 2 FAULT MEL 21-52-01 - Faulty Pack Controller 2 (532HH) Created by: Brett A Mumford 9 of 45 A330 ECAM MESSAGE RESET GUIDE AIR AIR AIR AIR AIR AIR CONTINUED PACK 2 OVHT MEL 21-52-01 - Perform System Test of the Temp CTL system on MCDU (ATA21) - Faulty Pack Controller 2 (532HH) PACK 2 REGUL FAULT MEL 21-52 or 21-53 - Perform System Test of the Temp CTL system on MCDU (ATA21) - Faulty Pack Controller 2 (532HH) R WING LEAK NO DISPATCH or MEL 36-2202 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) - Switch ON/OFF ENG 2 Bleed R WING LEAK DET FAULT MEL 36-22-02 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) X BLEED FAULT MEL 36-12-04 - Perform BITE Test of BMC 1 & 2 on MCDU (ATA36) Created by: Brett A Mumford 10 of 45 A330 ECAM MESSAGE RESET GUIDE AUTO FLT AUTO FLT A/THR LIMITED Not Applicable - Operational message… No further action required. AUTO FLT A/THR OFF MEL 22-30-01 - Reset breaker FMGEC 1 on LH reset panel. - Reset breaker FMGEC 2 on RH reset panel. AUTO FLT AP OFF MEL 22-10-01 - Reset breaker FMGEC 1 on LH reset panel. - Reset breaker FMGEC 2 on RH reset panel. - Recycle FCPC1,2 and 3 (Flight Control Primary Computer) AUTO FLT FCU FAULT NO DISPATCH - Reset breaker FMGEC 1 on LH reset panel. - Reset breaker FMGEC 2 on RH reset panel. - Reset breaker FCU 1 on LH reset panel. - Reset breaker FCU 2 on RH reset panel. AUTO FLT FM 1 + 2 FAULT MEL 22-83-01 - Reset breaker FMGEC 1 on LH reset panel. - Reset breaker FMGEC 2 on RH reset panel. AUTO FLT FM 1 FAULT MEL 22-72-01 - Reset breaker FMGEC 1 on LH reset panel. AUTO FLT FM 2 FAULT MEL 22-72-01 - Reset breaker FMGEC 2 on RH reset panel. AUTO FLT REAC W/S DET FAULT MEL 22-60-02-B - Perform System Test of the Auto Flight System on MCDU (ATA22) Created by: Brett A Mumford 11 of 45 A330 ECAM MESSAGE RESET GUIDE COM COM COM COM COM COM COM COM COM COM COM ACARS FAULT MEL 23-24-01 - Perform BITE Test of ACARS on MCDU (COM-Radio) ACARS ALERT Not Applicable - If no message on PFR… No Action Required. ACARS CALL Not Applicable - If no message on PFR… No Action Required. CIDS 1 + 2 FAULT MEL 23-73-01-A - Reset breakers CIDS 1, CIDS 2 and DMC 3 on reset panels LH and RH. CIDS PA FAULT MEL 23-31-01 - Perform interface and Power Up test as follows: - Open CB’s CIDS DIR 1 and DIR 2 ESS on panel 742VU - Open CB’s CIDS DIR 1 and DIR 2 NORM on panel 722VU - Close all breakers again. HF 1 EMMITTING NO DISPATCH - Reset breaker 2RE1 on panel 721VU HF 2 EMMITTING NO DISPATCH - Reset breaker 2RE2 on panel 722VU VHF 1 EMMITTING NO DISPATCH - Reset breaker 2RC1 on panel 742VU VHF 2 EMMITTING NO DISPATCH - Reset breaker 2RC2 on panel 722VU VHF 3 EMMITTING NO DISPATCH - Reset breaker 2RC3 on panel 721VU Created by: Brett A Mumford 12 of 45 A330 ECAM MESSAGE RESET GUIDE ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC AC BUS 1-1 FAULT NO DISPATCH - On panel 721VU cycle breakers M09, N11, Q05 and N07. - On panel 722VU cycle breakers M39, L45 and M43. - On panel 742VU cycle breakers A78, J77, E79 and H77. AC BUS 1-2 FAULT NO DISPATCH - On panel 721VU cycle breakers M09, N11, Q05 and N07. - On panel 722VU cycle breakers M39, L45 and M43. - On panel 742VU cycle breakers A78, J77, E79 and H77. AC BUS 2-3 FAULT NO DISPATCH - On panel 721VU cycle breakers M09, N11, Q05 and N07. - On panel 722VU cycle breakers M39, L45 and M43. - On panel 742VU cycle breakers A78, J77, E79 and H77. AC BUS 2-4 FAULT NO DISPATCH - On panel 721VU cycle breakers M09, N11, Q05 and N07. - On panel 722VU cycle breakers M39, L45 and M43. - On panel 742VU cycle breakers A78, J77, E79 and H77. AC ESS BUS ALTN NO DISPATCH - Perform operational test of the ESS generation manual switching. - Open CB 1XC on panel 715VU. - Release AC ESS FEED pushbutton. - Close CB 1XC on panel 715VU. - Push the AC ESS FEED pushbutton. - Perform operational test of the ESS generation automatic switching. - Open CB 41XN and 5XC on panel 721VU - Close CB 41XN and 5XC on panel 721VU AC ESS BUS FAULT NO DISPATCH - Cycle CB 17XH on panel 742VU. - Cycle CB 12XH on panel 742VU. AC ESS BUS SHED NO DISPATCH - Cycle CB 8XH on panel 742VU. - Cycle CB 15XH on panel 742VU. - Cycle CB 17XH on panel 742VU. APU BAT FAULT MEL 24-38-01-A - Switch APU Battery OFF. APU BAT OFF MEL 24-38-01-A - Operational message… No further action required. APU BCL FAULT MEL 24-38-01-B - Switch APU Battery OFF. APU GEN FAULT MEL 24-23-01 - Perform APU GCU BITE test on MCDU (ATA 24-AC-EPGS) APU GEN OVERLOAD MEL 24-26-01 - Perform EMCU BITE test on MCDU (ATA 24-AC-EMCU) APU TR FAULT MEL 24-32-01 - Perform APU TR Reset on APU TR or through MCDU (ATA 24) BAT 1 FAULT MEL 24-38-01-A - Switch BAT 1 OFF then ON. Created by: Brett A Mumford 13 of 45 A330 ECAM MESSAGE RESET GUIDE ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC CONTINUED BAT 1 OFF Not Applicable - Switch BAT 1 ON BAT 2 FAULT MEL 24-38-01-A - Switch BAT 2 OFF then ON. BAT 2 OFF Not Applicable - Switch BAT 2 ON BCL 1 FAULT MEL 24-38-01-B - Switch BAT 1 OFF then ON. BCL 2 FAULT MEL 24-38-01-B - Switch BAT 2 OFF then ON. BUS TIE OFF Not Applicable - Switch BUS TIE ON. C/B MONITOR FAULT MEL 24-53-01-A - Perform CBMU BITE test on MCDU (ATA 24) C/B TRIPPED Refer to effected system. - Operation message… No further action required. DC BAT BUS FAULT NO DISPATCH - Reset breakers ECMU 1 & 2 at panels 722VU and 742VU. DC BUS 1 + 2 FAULT NO DISPATCH - Check GPCU. DC BUS 1 FAULT NO DISPATCH - Reset breakers ECMU 1 & 2 at panels 722VU and 742VU DC BUS 2 FAULT NO DISPATCH - Reset breakers ECMU 1 & 2 at panels 722VU and 742VU DC ESS BUS FAULT NO DISPATCH - Check ELE/DC system for normal configuration. DC ESS BUS SHED NO DISPATCH - Reset breaker 801PP and 805PP at panel 742VU position N63 ECMU 1 FAULT MEL 24-29-01 - Perform ECMU 1 BITE test on MCDU (ATA 24) ECMU 2 FAULT MEL 24-29-01 - Perform ECMU 2 BITE test on MCDU (ATA 24) EMER CONFIG NO DISPATCH - Operation message… No further action required. ESS TR FAULT MEL 24-34-01 - Perform ESS TR reset on ESS TR or MCDU (ATA 24) EXT PWR A OVERLOAD MEL 24-26-01 - Perform ECMU 2 BITE test on MCDU (ATA 24) EXT PWR B OVERLOAD MEL 24-26-01 - Perform ECMU 1 BITE test on MCDU (ATA 24) GEN 1 (2) (3) (4) FAULT MEL 24-22-01 - Perform GCU BITE test on MCDU (ATA24) GEN 1 (2) (3) (4) OFF Not Applicable - Cycle push button switch ELEC/GEN 1 (2) (3) (4) GEN 1 (2) (3) (4) OVERLOAD MEL 24-26-01 - Push galley and commercial P/BSW OFF and check RCCB’s Created by: Brett A Mumford 14 of 45 A330 ECAM MESSAGE RESET GUIDE ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC ELEC CONTINUED IDG 1 (2) (3) (4) DISCONNECTED MEL 24-22-01 - Check PFR for IDG OIL OVHT or LO OIL PRESS - Check IDG Oil level - Re-connect. IDG 1 (2) (3) (4) MINOR FAULT MEL 24-22-02 - Check PFR for high or low oil level. IDG 1 (2) (3) (4) OIL LO PR MEL 24-22-01 - Check IDG 1 (2) (3) (4) oil level or IDG 1 (2) (3) (4) cooler. IDG 1 (2) (3) (4) OIL OVHT MEL 24-22-01 - Check IDG 1 (2) (3) (4) oil level or IDG 1 (2) (3) (4) cooler. PART GALLEY SHED Not Applicable - Operation message… No further action required. STATIC INV FAULT NO DISPATCH - Check breaker 6XB “STAT INV CTL” on panel 742VU position N65 TR 1 FAULT MEL 24-32-01 - Perform TR 1 reset on TR 1 or with MCDU (ATA 24) TR 2 FAULT MEL 24-32-01 - Perform TR 2 reset on TR 1 or with MCDU (ATA 24) Created by: Brett A Mumford 15 of 45 A330 ECAM MESSAGE RESET GUIDE APU FIRE APU FIRE - NO DISPATCH Perform BITE test of the APU fire and overheat detector unit. (ATA 26) Created by: Brett A Mumford 16 of 45 A330 ECAM MESSAGE RESET GUIDE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE SMOKE AFT CRG BTL 1 FAULT MEL 26-23-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. AFT CRG BTL 2 FAULT MEL 26-23-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. AFT CRG DET FAULT MEL 26-16-02 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. AFT/BULK CRG SMOKE NO DISPATCH - Reset breakers SDCU 1 and 2 on LH and RH reset panel. - If no real smoke in bulk or in the Air conditioning system, Perform BITE test of Smoke Detection System with MCDU (ATA 26) AVIONICS DET FAULT NO DISPATCH - Reset breakers SDCU 1 and 2 on LH and RH reset panel. AVNCS VENT SMOKE NO DISPATCH - Reset breakers SDCU 1 and 2 on LH and RH reset panel. - If no real smoke in bulk or in the Air conditioning system, Perform BITE test of Smoke Detection System with MCDU (ATA 26) BULK CRG DET FAULT MEL 26-16-03 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. CAB REST DET FAULT MEL 26-18-02 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. CAB REST SMOKE NO DISPATCH - Check for real smoke in Cabin Attendant Rest Room. - Reset breakers SDCU 1 and 2 on LH and RH reset panel. DET FAULT NO DISPATCH - Reset breakers SIDS 1 and 2 on LH and RH reset panel. - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FLT REST DET FAULT MEL 26-18-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FLT REST SMOKE NO DISPATCH - Check for real smoke in Flight Crew Rest Room. - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FWD CRG BTL 1 FAULT MEL 26-23-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FWD CRG BTL 2 FAULT MEL 26-23-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FWD CRG DET FAULT MEL 26-16-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. FWD CRG SMOKE NO DISPATCH - Reset breakers SDCU 1 and 2 on LH and RH reset panel. - If no real smoke in bulk or in the Air conditioning system, Perform BITE test of Smoke Detection System with MCDU (ATA 26) LAVATORY DET FAULT MEL 26-17-01 - Reset breakers SDCU 1 and 2 on LH and RH reset panel. LAVATORY SMOKE NO DISPATCH - Reset breakers SDCU 1 and 2 on LH and RH reset panel. - If no real smoke in bulk or in the Air conditioning system, Perform BITE test of Smoke Detection System with MCDU (ATA 26) Created by: Brett A Mumford 17 of 45 A330 ECAM MESSAGE RESET GUIDE F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL ADR DISAGREE NO DISPATCH - Check PFR. AIL SERVO FAULT MEL 27-14-01 - Cycle FCPC 2 (Flight Control Primary Computer). ALTN LAW NO DISPATCH - Cycle FCPC 1 & 2 (Flight Control Primary Computer). - Cycle FCSC 1 & 2 (Flight Control Secondary Computer). DIRECT LAW NO DISPATCH - Check PFR. ELEV REDUND LOST NO DISPATCH - Perform BITE test of the EFCS ground scanning through MCDU (ATA 27). ELEV SERVO FAULT MEL 27-43-01 - Perform BITE test of the EFCS ground scanning through MCDU (ATA 27). FCFC 1 FAULT MEL 27-95-01 - Reset FCDC 1 on LH reset panel. FCDC 1 + 2 FAULT MEL 27-95-01 - Reset FCFC 1 and 2 on LH and RH reset panels. FCDC 2 FAULT MEL 27-95-01 - Reset FCDC 2 on RH reset panel. FLAP SYS 1 FAULT MEL 27-51-01 - Cycle breakers SFCC 1 NORM on 721VU position X14. - Cycle breakers SFCC 1 AVAIL on 721VU position X13. - Cycle breakers SFCC 1 SLAT on 742VU position L62. - Cycle breakers SFCC 1 FLAP on 742VU position L61. FLAP SYS 2 FAULT MEL 27-51-01 - Cycle breakers SFCC 2 SLAT on 722VU position T43. - Cycle breakers SFCC 2 FLAP on 722VU position V40. FLAP TIP BRK FAULT NO DISPATCH - Reset Wing tip Brake with MCDU (ATA 27) FLAP/MCDU DISAGREE NO DISPATCH - Check the PFR. FLAPS FAULT NO DISPATCH - Reset Wing tip Brake with MCDU (ATA 27) FLAPS LOCKED NO DISPATCH - Reset Wing tip Brake with MCDU (ATA 27) GND SPLR FAULT MEL 27-92-02 or 32-42-05 - Cycle FCPC 1, 2 and 3 (Flight Control Primary Computers) IR DISAGREE NO DISPATCH - Check the PFR. L ELEV FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). L INR AIL FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). L OUTR AIL FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). Created by: Brett A Mumford 18 of 45 A330 ECAM MESSAGE RESET GUIDE F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL CONTINUED L SIDESTICK FAULT NO DISPATCH - Check the PFR. L + R ELEV FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). PRIM 1 FAULT MEL 27-93-01 - Cycle FCPC 1 (Flight Control Primary Computer). PRIM 1 PITCH FAULT MEL 27-44-01 or 27-93-01 - Cycle FCPC 1 (Flight Control Primary Computer). PRIM 2 FAULT MEL 27-93-01 - Cycle FCPC 2 (Flight Control Primary Computer). PRIM 2 PITCH FAULT MEL 27-44-01 or 27-93-01 - Cycle FCPC 2 (Flight Control Primary Computer). PRIM 3 FAULT MEL 27-93-01 - Cycle FCPC 3 (Flight Control Primary Computer). PRIM 3 PITCH FAULT MEL 27-44-01 or 27-93-01 - Cycle FCPC 3 (Flight Control Primary Computer). R ELEV FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). R INR AIL FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). R OUTR AIL FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). R SIDESTICK FAULT NO DISPATCH - Check PFR - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). RUD B SERVO JAM MEL 27-25-02-B - Perform Operational test of the Rudder Servo Control. - Pressurize the BLUE hydraulic system with the elec pump. - Release the LEAK MEASUREMENT VALVE/G pushbutton. - Release the LEAK MEASUREMENT VALVE/Y pushbutton. - Slowly push the right pedal until it touches the mechanical stop. - Slowly push the left pedal until it touches the mechanical stop. - Put the pedals into neutral position. - If rudder moves during test… Replace the jammed detection switch. - If rudder does not move during test… Replace rudder servo control. RUD G SERVO JAM MEL 27-25-02-B - Perform Operational test of the Rudder Servo Control. - Pressurize the BLUE hydraulic system with the elec pump. - Release the LEAK MEASUREMENT VALVE/B pushbutton. - Release the LEAK MEASUREMENT VALVE/Y pushbutton. - Slowly push the right pedal until it touches the mechanical stop. - Slowly push the left pedal until it touches the mechanical stop. - Put the pedals into neutral position. - If rudder moves during test… Replace the jammed detection switch. - If rudder does not move during test… Replace rudder servo control. Created by: Brett A Mumford 19 of 45 A330 ECAM MESSAGE RESET GUIDE F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL CONTINUED RUD Y SERVO JAM MEL 27-25-02-B - Perform Operational test of the Rudder Servo Control. - Pressurize the BLUE hydraulic system with the elec pump. - Release the LEAK MEASUREMENT VALVE/G pushbutton. - Release the LEAK MEASUREMENT VALVE/B pushbutton. - Slowly push the right pedal until it touches the mechanical stop. - Slowly push the left pedal until it touches the mechanical stop. - Put the pedals into neutral position. - If rudder moves during test… Replace the jammed detection switch. - If rudder does not move during test… Replace rudder servo control. RUD TRIM 1 FAULT MEL 27-22-01 - Cycle FCPC (Flight Control Primary Computer) 1, 2 and 3. RUD TRIM 2 FAULT MEL 27-22-01 - Cycle FCPC (Flight Control Primary Computer) 1, 2 and 3. RUD TRIM FAULT MEL 27-22-01 - Check PFR. - Push rudder trim reset switch on the rudder trim control panel (115VU) RUD TRV LIM 1 FAULT MEL 27-23-01 - Cycle FCPC (Flight Control Primary Computer) 1, 2 and 3. RUD TRV LIM 2 FAULT MEL 27-23-01 - Cycle FCPC (Flight Control Primary Computer) 1, 2 and 3. RUD TRV LIM FAULT MEL 27-23-01 - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). SEC 1 FAULT MEL 27-94-01 - Cycle FCSC (Flight Control Secondary Computer) 1 and 2. SEC 1 PITCH FAULT MEL 27-94-01 - Cycle FCSC (Flight Control Secondary Computer) 1 and 2. SEC 2 FAULT MEL 27-94-01 - Cycle FCSC (Flight Control Secondary Computer) 1 and 2. SEC 2 PITCH FAULT MEL 27-94-01 - Cycle FCSC (Flight Control Secondary Computer) 1 and 2. SENSOR FAULT MEL 27-92-05 or 27-92-06 - Cycle FCPC (Flight Control Primary Computer) 1 and 3. SLAT SYS 1 FAULT MEL 27-81-01 - Cycle breakers SFCC 1 NORM on 721VU pos X14. - Cycle breakers SFCC 1 AVAIL on 721VU pos X13. - Cycle breakers SFCC 1 SLAT on 742VU pos L62. - Cycle breakers SFCC 1 FLAP on 742VU pos L61. SLAT SYS 2 FAULT MEL 27-81-01 - Cycle breakers SFCC 2 SLAT on 722VU pos T43. - Cycles breakers SFCC 2 SLAT on 722VU pos V40. SLAT TIP BRK FAULT NO DISPATCH - Reset Wing Tip Brake with MCDU (ATA 27). SLATS FAULT NO DISPATCH - Reset Wing Tip Brake with MCDU (ATA 27). SLATS LOCKED NO DISPATCH - Reset Wing Tip Brake with MCDU (ATA 27). Created by: Brett A Mumford 20 of 45 A330 ECAM MESSAGE RESET GUIDE F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL F/CTL CONTINUED SPD BRK DISAGREE MEL 27-92-01 - Check the PFR. SPD BRK FAULT MEL 27-92-01 - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). SPLR FAULT MEL 27-64-01 - Cycle FCPC (Flight Control Primary Computer) 1 and 3. STAB CTL FAULT NO DISPATCH - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). TURB DAMP FAULT MEL 27-93-05 - Cycle FCPC (Flight Control Primary Computer) 1 and 3. YAW DAMPER 1 MEL 27-26-01 - Cycle FCPC (Flight Control Primary Computer) 1. - Cycle FCSC (Flight Control Secondary Computer) 1. YAW DAMPER 2 MEL 27-26-01 - Cycle FCPC (Flight Control Primary Computer) 3. - Cycle FCSC (Flight Control Secondary Computer) 2. YAW DAMPER 3 MEL 27-26-01 - Perform BITE test of EFCS ground scanning with MCDU (ATA 27). Created by: Brett A Mumford 21 of 45 A330 ECAM MESSAGE RESET GUIDE FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL ABNORMAL MAN FWD XFR Not Applicable - No Action Required. APU AFT PUMP FAULT MEL 49-30-01-A - Reset breakers FCMC 1 and 2 on LH and RH reset panel. APU LP VALVE FAULT MEL 49-30-03 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. CTR TO INNER FAULT MEL 49-30-03 - Reset breakers FCMC 2 on RH reset panel. ENG1 LP VALVE FAULT MEL 28-24-01 - Reset breakers FWC 1 and 2 on LH and RH reset panel. ENG2 LP VALVE FAULT MEL 28-24-01 - Reset breakers FWC 1 and 2 on LH and RH reset panel. ENG3 LP VALVE FAULT MEL 28-24-01 - Reset breakers FWC 1 and 2 on LH and RH reset panel. ENG4 LP VALVE FAULT MEL 28-24-01 - Reset breakers FWC 1 and 2 on LH and RH reset panel. EXCESS AFT CG MEL 28-40-13-A - Reset breakers FCMC 1 and 2 on LH and RH reset panel. FCMC 1 FAULT MEL 28-51-01-A or 28-51-01-B - Reset breakers FCMC 1 on LH reset panel. FCMC 1 + 2 FAULT NO DISPATCH - Reset breakers FCMC 1 and 2 on LH and RH reset panel. FCMC 2 FAULT MEL 28-51-01-A or 28-51-01-B - Reset breakers FCMC 2 on RH reset panel. FUEL LO TEMP MEL 28-49-02-A, -B OR -C - Reset breakers FCMC 1 and 2 on LH and RH reset panel. JETTISON FAULT MEL 28-31-02 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. JETTISON NOT CLOSED MEL 28-31-01 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. L CTR PUMP LO PR MEL 28-26-02 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. R CTR PUMP LO PR MEL 28-26-01 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. L INNER TK HI TEMP Not Applicable - Apply ECAM procedure. - If MCDU shows no maintenance message, no further action is required. L WING PUMPS LO PR MEL 28-21-01-A or 28-21-01-B - Reset breakers FCMC 1 and 2 on LH and RH reset panel. L WING TK LO LVL MEL 28-46-04-A - Check the PFR. - Operational message… No further action required. L + R WING TK LO LVL MEL 28-46-04-A - Check the PFR. - Operational message… No further action required. PUMP 1 LO PR MEL 28-21-01-A - Cycle breaker FUEL PUMP 1 on 742VU pos S66. Created by: Brett A Mumford 22 of 45 A330 ECAM MESSAGE RESET GUIDE FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL CONTINUED PUMP 2 LO PR MEL 28-21-02-A - Cycle breaker FUEL PUMP 2 on 721VU pos J05. PUMP 3 LO PR MEL 28-21-01-A - Cycle breaker FUEL PUMP 3 on 722VU pos G45. PUMP 4 LO PR MEL 2-21-01-A - Cycle breaker FUEL PUMP 4 on 722VU pos A46. OUTR TO INR FAULT MEL 28-26-01 - Perform operational test of the FCMS controlled valves on MCDU (ATA 28) R INNER TK HI TEMP Not Applicable - Apply ECAM procedure. - If MCDU shows no maintenance message, no further action is required. R WING PUMPS LO PR MEL 28-21-01-A and 28-21-01B - Reset breakers FCMC 1 and 2 on LH and RH reset panel. R WING TK LO LVL MEL 28-46-04-A - Apply ECAM procedure. - If MCDU shows no maintenance message, no further action is required. L + R CTR PUMPS LO PR MEL 28-26-02 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. PUMPS 1 + STBY LO PR MEL 28-21-01-A or 28-21-01-B - Cycle breakers FUEL STBY PUMP 1 on 722VU pos G42 PUMPS 2 + STBY LO PR MEL 28-21-01-A or 28-21-01-B - Cycle breakers FUEL STBY PUMP 2 on 722VU pos A49 PUMPS 3 + STBY LO PR MEL 28-21-01-A or 28-21-01-B - Cycle breakers FUEL STBY PUMP 3 on 721VU pos J08 PUMPS 4 + STBY LO PR MEL 28-21-01-A or 28-21-01-B - Cycle breakers FUEL STBY PUMP 4 on 742VU pos S69 T TANK XFR FAULT MEL 28-27 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. TRIM LINE FAULT MEL 28-25-04-C or 28-27-01 - Reset breakers FCMC 1 and 2 on LH and RH reset panel. WING TK OVERFLOW NO DISPATCH - Reset breakers FCMC 1 and 2 on LH and RH reset panel. X FEED 1 (2) (3) (4) FAULT MEL 28-23-01 - Cycle Cross Feed Valve P/BSW ZFW ZFCG DISAGREE MEL 28-51-02 - Check the PFR. - Operational message… No further action required. Created by: Brett A Mumford 23 of 45 A330 ECAM MESSAGE RESET GUIDE HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD HYD B + Y SYS LO PR MEL 29-30-03-F - Check Hydraulic fluid levels. B ELEC PUMP FAULT MEL 29-22-01 or 29-30-03-D - Cycle breaker HSMU B + PART G on 721VU pos U11. - Cycle breaker HYD PUMP B CTL on 721VU pos X12. B ENG 2 PUMP LO PR MEL 29-30-03-E - Check BLUE Hydraulic fluid level. - Bleed BLUE Hydraulic system. B RSVR LO AIR PR MEL 29-30-03-B - Check Air pressure in reservoir from reservoir gauge. - Pressurize the hydraulic reservoirs with APU Bleed air. (Selection of ENG MASTER SW to crank will boost APU Bleed PX to 58 PSI for 30 sec). B RSVR LO LVL MEL 29-30-03-A - Check BLUE hydraulic fluid level. G + B SYS LO PR MEL 29-30-03-F - Check hydraulic fluid levels. G + Y SYS LO PR MEL 29-30-03-F - Check hydraulic fluid levels. G ELEC PUMP FAULT MEL 29-21-01 or 29-30-0-D - Cycle breaker HSMU B + PART G on 721VU pos U11. - Cycle breaker HSMU Y + PART G on 722VU pos X46. G ENG 1 PUMP LO PR MEL 29-30-03-E - Check GREEN hydraulic fluid level. - Bleed GREEN hydraulic system. G ENG 1 + 4 PUMPS LO PR MEL 29-30-03-E - Check GREEN hydraulic fluid level. G ENG 4 PUMP LO PR MEL 29-30-03-E - Check GREEN hydraulic fluid level. - Bleed GREEN hydraulic system. G RSVR LO AIR PR MEL 29-30-03-B - Check Air pressure in reservoir from reservoir gauge. - Pressurize the hydraulic reservoirs with APU Bleed air. (Selection of ENG MASTER SW to crank will boost APU Bleed PX to 58 PSI for 30 sec). G RSVR LO LVL MEL 29-30-03-A - Check GREEN hydraulic fluid level. B (G) (Y) RSVR OVHT MEL 29-30-03-C - Check the PFR. G RSVR UNDERFILLED NO DISPATCH - Check for obvious leaks. - Re-fill the GREEN hydraulic system reservoir. G SYS LEAK Not Applicable - Cross check fluid level indication on GREEN reservoir and ECAM HYD page. - Check for obvious leaks. Created by: Brett A Mumford 24 of 45 A330 ECAM MESSAGE RESET GUIDE HYD HYD HYD HYD HYD HYD HYD CONTINUED MONITORING FAULT MEL 29-30-03-H - Reset breakers FWC 1 and 2 on the LH and RH reset panels. - Reset breakers SDAC 1 and 2 on the LH and RH reset panels. RAT FAULT MEL 29-30-03-G - Pressurize GREEN hydraulic system, On the YELLOW hydraulic service panel set the ON/OFF switch to ON and back to OFF. Y ELEC PUMP FAULT MEL 29-23-01-A or 29-30-03-D - Cycle breaker HSMU B + PART G on 721VU pos U11. - Cycle breaker HYD PUMP Y SVCE on 722VU pos N46. - Cycle breaker HYD PUMP Y CTL on 722VU pos R36. - Cycle breaker HSMU Y + PART G on 722VU pos X46. Y RSVR LO AIR PR MEL 29-30-03-B - Check Air pressure in reservoir from reservoir gauge. - Pressurize the hydraulic reservoirs with APU Bleed air. (Selection of ENG MASTER SW to crank will boost APU Bleed PX to 58 PSI for 30 sec). Y ENG 3 PUMP LO PR MEL 29-30-03-E - Check YELLOW hydraulic fluid level. - Bleed YELLOW hydraulic system. RSVR LO LVL MEL 29-30-03-A - Check all HYD reservoir fluid levels. Created by: Brett A Mumford 25 of 45 A330 ECAM MESSAGE RESET GUIDE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE CAPT AOA HEAT MEL 30-31-04 - Reset breaker PHC1 on the LH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) CAPT PITOT HEAT MEL 30-31-02 - Reset breaker PHC1 on the LH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) CAPT PROBES HEAT MEL 30-31-01 - Reset breaker PHC1 on the LH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) CAPT TAT HEAT MEL 30-31-05 - Reset breaker PHC1 on the LH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) DETECT FAULT MEL 30-81-01 - Cycle breaker ICE DET 1 on panel 721VU pos B08. - Cycle breaker ICE DET 2 on panel 722VU pos F46. - Perform operational test of the Probe Ice Detection system with the MCDU (ATA 30) ENG 1 (2) (3) (4) VALVE CLOSED MEL 30-21-01 - ENG 1… Cycle breaker ANTI ICE ENG 1 on panel 722VU pos X39. - ENG 1… Cycle breaker ANTI ICE ENG 2 on panel 721VU pos W06. - ENG 1… Cycle breaker ANTI ICE ENG 3 on panel 722VU pos X40. - ENG 1… Cycle breaker ANTI ICE ENG 4 on panel 721VU pos W07. - Cycle breaker FADEC B ENG 1 on panel 722VU pos D44. - Cycle breaker FADEC A ENG 1 on panel 742VU pos Q73. - Check Engine Air Intake Anti-ice Valve (4000DN). ENG 1 VALVE OPEN MEL 30-21-01 - Cycle breaker ANTI ICE ENG 1 on panel 722VU pos X39. - Cycle breaker FADEC B ENG 1 on panel 722VU pos D44. - Cycle breaker FADEC A ENG 1 on panel 742VU pos Q73. ENG 2 VALVE OPEN MEL 30-21-01 - Cycle breaker ANTI ICE ENG 2 on panel 721VU pos W06. - Cycle breaker FADEC B ENG 1 on panel 722VU pos D44. - Cycle breaker FADEC A ENG 1 on panel 742VU pos Q73. ENG 3 VALVE OPEN MEL 30-21-01 - Cycle breaker ANTI ICE ENG 3 on panel 722VU pos X40. - Cycle breaker FADEC B ENG 2 on panel 722VU pos K49. - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. ENG 4 VALVE OPEN MEL 30-21-01 - Cycle breaker ANTI ICE ENG 4 on panel 721VU pos W07. - Cycle breaker FADEC B ENG 2 on panel 722VU pos K49. - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. Created by: Brett A Mumford 26 of 45 A330 ECAM MESSAGE RESET GUIDE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE CONTINUED F/O AOA HEAT MEL 30-31-02 - Reset breaker PHC2 on the RH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) F/O PITOT HEAT MEL 30-31-01 - Reset breaker PHC2 on the RH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) F/O TAT HEAT MEL 30-31-05 - Reset breaker PHC2 on the RH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) L + R WINDOW HEAT MEL 30-42-02 - Reset breakers WHC 1 and WHC 2 on the LH and RH reset panel. L + R WSHLD HEAT MEL 30-42-03 - Reset breakers WHC 1 and WHC 2 on the LH and RH reset panel. L CAPT STAT HEAT MEL 30-31-03 - Reset breaker PHC 1 on the LH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) L F/O STAT HEAT MEL 30-31-03 - Reset breaker PHC 2 on the RH reset panel. - Perform operational test of the Probe Ice protection system with the MCDU (ATA 30) L INR WING HI PR NO DISPATCH - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH inner Wing anti-ice valve (10DL1). L INR WING LO PR MEL 30-11-01 - Check Wing Anti-ice Control Valve filter for contamination. - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH inner Wing anti-ice valve (10DL1). L INR WING OPEN MEL 30-11-01 - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH inner Wing anti-ice valve (10DL1). L OUTR WING HI PR NO DISPATCH - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH outer Wing anti-ice valve (9DL1). L OUTR WING LO PR MEL 30-11-01 - Faulty LH outer Wing anti-ice valve (9DL1). - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Check Wing Anti-ice Control Valve filter for contamination. - Faulty Bleed Valve (4001HA) L OUTR WING OPEN MEL 30-11-01 - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH outer Wing anti-ice valve (9DL1). Created by: Brett A Mumford 27 of 45 A330 ECAM MESSAGE RESET GUIDE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE A.ICE CONTINUED L STBY STAT HEAT MEL 30-31-03 - Reset breaker PHC 3 on LH reset panel. - Perform operational test of the Probe Ice protection on the MCDU (ATA 30) L WINDOW HEAT MEL 30-42-02 - Reset WHC 1 on LH reset panel. L WSHLD HEAT MEL 30-42-03 - Reset WHC 1 on LH reset panel. R CAPT STAT HEAT MEL 30-31-03 - Reset PHC 1 on LH reset panel. F/O R STAT HEAT MEL 30-31-03 - Reset PHC 2 on LH reset panel. R INR WING HI PR NO DISPATCH - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty RH inner Wing anti-ice valve (10DL2). R INR WING LO PR MEL 30-11-01 - Check Wing Anti-ice Control Valve filter for contamination. - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty RH inner Wing anti-ice valve (10DL2). R INR WING OPEN MEL 30-11-01 - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty RH inner Wing anti-ice valve (10DL2). R OUTR WING HI PR NO DISPATCH - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty RH outer Wing anti-ice valve (9DL2). R OUTR WING LO PR MEL 30-11-01 - Faulty LH outer Wing anti-ice valve (9DL2). - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Check Wing Anti-ice Control Valve filter for contamination. - Faulty Bleed Valve (4001HA) R OUTR WING OPEN MEL 30-11-01 - Cycle breaker ANTI ICE WING on panel 721VU pos W09. - Faulty LH outer Wing anti-ice valve (9DL2). STBY R STAT HEAT MEL 30-31-03 - Reset breaker PHC3 on the LH reset panel. R WINDOW HEAT MEL 30-42-02 - Reset breaker WHC2 on the RH reset panel R WSHLD HEAT MEL 30-42-03 - Reset breaker WHC2 on the RH reset panel. STBY AOA HEAT MEL 30-31-04 - Reset breaker PHC3 on the LH reset panel. STBY PITOT HEAT MEL 30-31-02 - Reset breaker PHC3 on the LH reset panel. STBY PROBES HEAT MEL 30-31-01 - Reset breaker PHC3 on the LH reset panel. Created by: Brett A Mumford 28 of 45 A330 ECAM MESSAGE RESET GUIDE A.ICE A.ICE A.ICE A.ICE CONTINUED WAI SYS FAULT - Reset breaker LGCIU on the RH reset panel. - Faulty Wing Anti Ice Control Relay (5DL). - Faulty Wing Ice Control Relay (11DL). - Faulty P/BS (3DL). WING OPEN ON GND - Faulty Wing Anti Ice System Mode Relay (6DL). - Faulty Wing Anti Ice Ground Relay (4DL). WING VALVE NOT OPEN - Cycle breaker ANTI-ICE WING on 721VU pos W09. - Faulty RH outer Wing Anti-ice valve (9DL2). - Faulty LH outer Wing Anti-ice valve (9DL1). - Faulty RH inner Wing Anti-ice valve (10DL2). - Faulty LH inner Wing Anti-ice valve (10DL1). Created by: Brett A Mumford MEL 30-11-01 MEL 30-11-01 MEL 30-11-01 29 of 45 A330 ECAM MESSAGE RESET GUIDE EIS EIS EIS EIS EIS EIS EIS EIS DISPLAY DISCREPANCY NO DISPATCH - Reset breaker DMC 1,2 and 3 on the LH and RH reset panels. ECAM DMC 1 FAULT MEL 31-62-01-B - Reset breaker DMC 1 on the LH reset panel. ECAM DMC 2 FAULT MEL 31-62-01-B - Reset breaker DMC 2 on the RH reset panel. ECAM DMC 3 FAULT MEL 31-62-01-B - Reset breaker DMC 3 on the LH reset panel. EFIS DMC 1 FAULT MEL 31-62-01-A - Reset breaker DMC 1 on the LH reset panel. EFIS DMC 2 FAULT MEL 31-62-01-A - Reset breaker DMC 2 on the RH reset panel. EFIS DMC 3 FAULT MEL 31-62-01-A - Reset breaker DMC 3 on the LH reset panel. Created by: Brett A Mumford 30 of 45 A330 ECAM MESSAGE RESET GUIDE FWS FWS FWS FWS FWS FWS FWS FWS EPC FAULT MEL 31-56-01 - Reset breaker FWC 1 and SDAC 1 on the LH reset panel. - Reset breaker FWC 2 and SDAC 2 on the RH reset panel. FWC 1 FAULT MEL 31-53-01 - Reset breaker FWC 1 on the LH reset panel. FWC 1 + 2 FAULT MEL 31-53-01 - Reset breaker FWC 1 and FWC 2 on the LH and RH reset panels. FWC 2 FAULT MEL 31-53-01 - Reset breaker FWC 2 on the RH reset panel. SDAC 1 FAULT MEL 31-55-01 - Reset breaker SDAC 1 on the LH reset panel. SDAC 1 + 2 FAULT MEL 31-55-01 - Reset breaker SDAC 1 and SDAC 2 on the LH and RH reset panels. SDAC 2 FAULT MEL 31-55-01 - Reset breaker SDAC 2 on the RH reset panel. Created by: Brett A Mumford 31 of 45 A330 ECAM MESSAGE RESET GUIDE RECORDER RECORDER DFDR FAULT NO DISPATCH - Cycle breaker FDIU/DFDR on panel 722VU pos F42. RECORDER FDIU FAULT NO DISPATCH - Cycle breaker FDIU/DFDR on panel 722VU pos F42. Created by: Brett A Mumford 32 of 45 A330 ECAM MESSAGE RESET GUIDE WHEEL WHEEL WHEEL WHEEL HYD SEL VALVE NO DISPATCH - Cycle A/SKID & N/W STRG switch on F/O instrument panel. N/W STRG FAULT MEL 32-51-01 - Cycle A/SKID & N/W STRG switch on F/O instrument panel. - Reset breakers LGCIU 1 and LGCIU 2 on the LH and RH reset panels. TIRE LO PR NO DISPATCH - Cycle A/SKID & N/W STRG switch on F/O instrument panel. - Adjust tire pressures as required. Created by: Brett A Mumford 33 of 45 A330 ECAM MESSAGE RESET GUIDE BRAKES BRAKES BRAKES BRAKES BRAKES BRAKES BRAKES BRAKES BRAKES A/SKID NWS OFF Not Applicable - No action required is A/SKID & N/W STRG switch is in the OFF position. ANTI SKID FAULT NO DISPTCH - Cycle A/SKID & N/W STRG switch on F/O instrument panel. AUTO BRAKE FAULT MEL 32-42-02 or 32-42-04 - Cycle A/SKID & N/W STRG switch on F/O instrument panel. BSCU CH 1 FAULT MEL 32-42-03 - Perform BITE test of BSCU 1 on the MCDU (ATA 32) BSCU CH 2 FAULT - Perform BITE test of BSCU 2 on the MCDU (ATA 32) HOT NO DISPATCH - Max 150 deg C difference between 2 brakes on same gear. - Max 200 deg C difference between brakes on LH and RH rears. - Cool down brakes or delay dispatch until cool. RELEASED MEL 32-42-01 or 32-42-05 - Perform BITE test of BSCU 1 on the MCDU (ATA 32) - Perform BITE test of BSCU 2 on the MCDU (ATA 32) RESIDUAL BRAKING MEL 32-42-01 - Perform BITE test of BSCU 1 on the MCDU (ATA 32) - Perform BITE test of BSCU 2 on the MCDU (ATA 32) Created by: Brett A Mumford 34 of 45 A330 ECAM MESSAGE RESET GUIDE L/G L/G L/G L/G L/G L/G L/G L/G L/G L/G L/G L/G L/G DOORS NOT CLOSED NO DISPATCH - Perform visual inspection of Landing Gear Doors. - Reset breaker LGCIU 1 and LGCIU 2 on the LH and RH rest panels. GEAR NOT DOWN Not Applicable - No action if no PFR report. GEAR NOT DOWNLOCKED Not Applicable - Reset breaker LGCIU 1 and LGCIU 2 on the LH and RH rest panels. GEAR NOT UPLOCKED Not Applicable - Reset breaker LGCIU 1 and LGCIU 2 on the LH and RH rest panels. GEAR UPLOCK FAULT FCOM 2-04-25 - Check up lock Assy of all Landing Gears. L LENGTHENING FAULT FCOM 2-04-25 - Check for damage to the shortening mechanism or the proximity sensor target on the LH Gear. R LENGTHENING FAULT FCOM 2-04-25 - Check for damage to the shortening mechanism or the proximity sensor target on the RH Gear. LGCIU 1 FAULT MEL 32-31-01 - Reset breakers FWC 1 and LGCIU 1 on the LH reset Panel. - Reset breakers FWC 2 and LGCIU 2 on the RH reset Panel. LGCIU 1 + 2 FAULT MEL 32-31-01 - Reset breakers FWC 1 and LGCIU 1 on the LH reset Panel. - Reset breakers FWC 2 and LGCIU 2 on the RH reset Panel. LGCIU 2 FAULT MEL 32-31-01 - Reset breakers FWC 1 and LGCIU 1 on the LH reset Panel. - Reset breakers FWC 2 and LGCIU 2 on the RH reset Panel. RETRACTION FAULT FCOM 2-04-25 - Check for damage to the proximity sensors or targets on all Gears. SYS DISAGREE NO DISPATCH - Reset breaker LGCIU 1 and LGCIU 2 on the LH and RH rest panels. Created by: Brett A Mumford 35 of 45 A330 ECAM MESSAGE RESET GUIDE NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV ADR 1 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU1 115VAC on panel 721VU pos C04. - Cycle breaker ADIRU1 28VDC on panel 742VU pos B80. - Cycle breaker ADIRU1 BAT on panel 742VU pos K70. ADR 1 + 2 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Check PFR. ADR 1 + 3 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Check PFR. ADR 2 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU2 115VAC on panel 722VU pos H46. - Cycle breaker ADIRU2 BAT on panel 742VU pos G73. ADR 2 + 3 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Check PFR. ADR 3 FAULT MEL 34-10-01-B - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU3 115VAC on panel 721VU pos G05. - Cycle breaker ADIRU3 28VDC on panel 742VU pos F68. - Cycle breaker ADIRU3 BAT on panel 742VU pos G74. ALTI DISCREPANCY MEL 34-10-01-B - No action required if there is no failure on the PFR. ATT DISCREPANCY MEL 34-10-01-A - No action required if there is no failure on the PFR. EXTREME LATITUDE Not Applicable - No action required if there is no failure on the PFR. FM/IR POS DISAGREE Not Applicable - Reset ADIRU 1 (2) (3) - No action required if there is no failure on the PFR. GPWS FAULT MEL 34-38-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Re-rack ILS 1 after pulling breaker on panel 742VU pos P66. HDG DISCREPANCY MEL 34-10-01-A - No action required if there is no failure on the PFR. ILS 1 FAULT MEL 34-36-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Re-rack ILS 1 after pulling breaker on panel 742VU pos P66. ILS 1 + 2 FAULT MEL 34-36-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Re-rack ILS 1 after pulling breaker on panel 742VU pos P66. - Re-rack ILS 2 after pulling breaker on panel 722VU pos H44. ILS 2 FAULT MEL 34-36-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Re-rack ILS 2 after pulling breaker on panel 722VU pos H44. Created by: Brett A Mumford 36 of 45 A330 ECAM MESSAGE RESET GUIDE NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV NAV CONTINUED IR 1 FAULT MEL 34-10-01-A - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU1 115VAC on panel 721VU pos C04. - Cycle breaker ADIRU1 28VDC on panel 742VU pos B80. - Cycle breaker ADIRU1 BAT on panel 742VU pos K70. IR 1 + 2 FAULT MEL 34-10-01-A - Check the PFR. IR 1 + 3 FAULT MEL 34-10-01-A - Check the PFR. IR 2 FAULT MEL 34-10-01-A - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU2 115VAC on panel 722VU pos H46. - Cycle breaker ADIRU2 BAT on panel 742VU pos G73. IR 2 + 3 FAULT MEL 34-10-01-A - Check the PFR. IR 3 FAULT MEL 34-10-01-A - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker ADIRU3 115VAC on panel 721VU pos G05. - Cycle breaker ADIRU3 28VDC on panel 742VU pos F68. - Cycle breaker ADIRU3 BAT on panel 742VU pos G74. IR NOT ALIGNED MEL 34-10-01-A - No action required if there is no failure on the PFR. RA 1 FAULT MEL 34-42-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. RA 1 + 2 FAULT MEL 34-42-01 - If message RA1 and RA2 is shown only on the ground, no actions are required. RA 2 FAULT MEL 34-42-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. TCAS FAULT MEL 34-42-01 - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. - Cycle breaker TCAS on panel 721VU pos B06. - Cycle breaker ATC1 on panel 742VU pos Q64. - Cycle breaker ATC2 on panel 722VU pos E47. Created by: Brett A Mumford 37 of 45 A330 ECAM MESSAGE RESET GUIDE APU APU APU APU APU FAULT MEL 49-11-01 - Check the PFR FIRE DET FAULT MEL 26-13 - Cycle breaker FDU LOOP B APU on panel 721VU pos P08. - Cycle breaker FIRE LOOP A APU on panel 742VU pos D80. FIRE LOOP A FAULT MEL 26-13-01 - If LOOP A OK…. Faulty FDU (13WG). - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. FIRE LOOP B FAULT MEL 26-13-01 - If LOOP B OK…. Faulty FDU (13WG). - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. Created by: Brett A Mumford 38 of 45 A330 ECAM MESSAGE RESET GUIDE DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR DOOR AFT CARGO MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). AVIONIC MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). BULK CARGO MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). FWD CARGO MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). L AFT CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). L EMER EXIT MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). L FWD CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). L MID CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). POS DET 1 FAULT MEL 52-71-01-A - Reset breakers CPC 1 and CPC 2 on the LH and RH reset panels. - Perform system test of PSCU on the MCDU (ATA 52). POS DET 1 + 2 FAULT MEL 52-71-01-A - Reset breakers CPC 1 and CPC 2 on the LH and RH reset panels. - Cycle breaker DOORS & SLIDES CTL on panel 721VU pos N12. - Cycle breaker DOORS & SLIDES CTL on panel 722VU pos P41. POS DET 2 FAULT MEL 52-71-01-A - Reset breakers CPC 1 and CPC 2 on the LH and RH reset panels. - Perform system test of PSCU on the MCDU (ATA 52). R AFT CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). R EMER EXIT MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). R FWD CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). R MID CABIN MEL 52-71-01-B - Check proximity sensor and target. - Perform system test of PSCU on the MCDU (ATA 52). Created by: Brett A Mumford 39 of 45 A330 ECAM MESSAGE RESET GUIDE CONFIG CONFIG CONFIG CONFIG CONFIG CONFIG CONFIG CONFIG CONFIG FLAPS NO IN T.O. RANGE NO DISPATCH - Check the PFR. - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. L SIDESTICK FAULT Apply ECAM procedure. - Check the PFR. - If there is no failure message… no action is required. R SIDESTICK FAULT Apply ECAM procedure. - Check the PFR. - If there is no failure message… no action is required. PARK BRK ON NO DISPATCH - Set brakes to OFF. PITCH TRIM NOT IN T.O. RANGE NO DISPATCH - Check the PFR. - If there is no failure message… no action is required. RUD TRIM NOT IN T.O. RANGE NO DISPATCH - Check the PFR. - If there is no failure message… no action is required. SLATS NOT IN T.O. RANGE NO DISPATCH - Check the PFR. - If there is no failure message… no action is required. SPD BRK NOT RETRACTED NO DISPATCH - Check the PFR. - If there is no failure message… no action is required. Created by: Brett A Mumford 40 of 45 A330 ECAM MESSAGE RESET GUIDE ENG ENG ENG ENG ENG THRUST LOSS MEL 73-30-03-B - Reset breaker ZONE CONT on the RH reset panel. ALL ENG FLAME OUT NO DISPATCH - Check Fuel filters for contamination. THR LEVERS NOT SET MEL 73-20-01 - Operational message… no further actions required. T.O. THRUST DISAGREE NO DISPATCH - Check the PFR for defective LRU’s. Created by: Brett A Mumford 41 of 45 A330 ECAM MESSAGE RESET GUIDE ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 BLEED STATUS Apply ECAM procedure - Reset breaker ZONE CONT on the RH reset panel. - Reset breaker EIVMU 1 on the RH reset panel. CTL SYS FAULT NO DISPATCH - Cycle breaker FADEC A ENG 1 on panel 742VU pos N74. - Cycle breaker FADEC B ENG 1 on panel 722VU pos K46. EGT OVERLIMIT Not Applicable - Perform visual inspection of the effected engine. EIU FAULT MEL 73-25-02 - Reset breaker EIVMU 1 on the RH reset panel. - Reset breaker FCU 1 on the LH reset panel. FADEC FAULT NO DISPATCH - Reset breakers SDAC 1 and SDAC 2 on the LH and RH reset panels. - Reset breaker FCU 1 on the LH reset panel. FADEC OVHT NO DISPATCH - Check for local overheating of the EEC, pay particular attention to the Nacelle ANTI-ICE ducting for leakages. FADEC SYS FAULT NO DISPATCH - Reset breaker EIVMU 1 on the RH reset panel. - Cycle breaker FADEC A ENG 1 on panel 742VU pos N74. - Cycle breaker FADEC B ENG 1 on panel 722VU pos K46. FIRE DET FAULT NO DISPATCH - Perform BITE test of the FDU through the MCDU (ATA 26) FIRE LOOP A FAULT MEL 26-12-01 - Perform BITE test of the FDU through the MCDU (ATA 26) FIRE LOOP B FAULT MEL 26-12-01 - Perform BITE test of the FDU through the MCDU (ATA 26) FUEL FILTER CLOG NO DISPATCH - Check the fuel pump filter for contamination. - Check the fuel pump differential pressure switch. HP FUEL VALVE NO DISPATCH - Perform FADEC system static test through the MCDU (ATA 70) IGN A FAULT MEL 74-31-01 or 74-31-03-A - Reset breaker EIVMU 1 on the RH reset panel. IGN B FAULT MEL 74-31-01 or 74-31-03-A - Reset breaker EIVMU 1 on the RH reset panel. IGN A + B FAULT MEL 74-31-01 or 74-31-03-A - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. MINOR FAULT MEL 73-25-01-A - Cycle breaker FADEC A ENG 1 on panel 742VU pos N74. - Cycle breaker FADEC B ENG 1 on panel 722VU pos K46. OIL FILTER CLOG MEL 79-35-02-A - Check the oil filter for contamination. - Check the oil filter differential pressure switch. OIL HI TEMP NO DISPATCH - Check engine oil level. Created by: Brett A Mumford 42 of 45 A330 ECAM MESSAGE RESET GUIDE ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 ENG 1 CONTINUED OIL LO TEMP Apply ECAM procedure - Operational message… No actions required. OIL PRESS MEL 79-34-01-A - Check engine oil level, and signs for obvious oil leakages. REV FAULT MEL 78-30-01 - Reset breaker EVIMU 1 on the RH reset panel. REV INHIBITED MEL 78-30-01 or 78-30-07-A - Open LH Fan cowl and check that the inhibit lever is not in the inhibit position, and that the lock out pin is not installed on the left interface bracket. REV PRESSURISED NO DISPATCH - Cycle breaker FADEC A ENG 1 on panel 742VU pos N74. - Cycle breaker FADEC B ENG 1 on panel 722VU pos K46. REV UNLOCKED MEL 78-30-01 - Perform visual inspection of the reverser cowls. SHUT DOWN NO DISPATCH - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. START FAULT NO DISPATCH - Cycle breaker FADEC A ENG 1 on panel 742VU pos N74. - Cycle breaker FADEC B ENG 1 on panel 722VU pos K46. START VALVE FAULT MEL 80-11-01 - Check the starter valve and starter for failures. THR LEVER DISAGREE NO DISPATCH - Reset breaker EVIMU 1 on the RH reset panel. - Disagree between Throttle Control Lever position and the position detected by the EEC. THR LEVER FAULT NO DISPATCH - Reset breaker EVIMU 1 on the RH reset panel. - Disagree between Throttle Control Lever position and the position detected by the EEC. Created by: Brett A Mumford 43 of 45 A330 ECAM MESSAGE RESET GUIDE ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 BLEED STATUS Apply ECAM procedure - Reset breaker ZONE CONT on the RH reset panel. - Reset breaker EIVMU 2 on the LH reset panel. CTL SYS FAULT NO DISPATCH - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. - Cycle breaker FADEC B ENG 2 on panel 722VU pos D43. EGT OVERLIMIT Not Applicable - Perform visual inspection of the effected engine. EIU FAULT MEL 73-25-02 - Reset breaker EIVMU 2 on the LH reset panel. - Reset breaker FCU 1 on the LH reset panel. FADEC FAULT NO DISPATCH - Reset breakers SDAC 1 and SDAC 2 on the LH and RH reset panels. - Reset breaker FCU 1 on the LH reset panel. FADEC OVHT NO DISPATCH - Check for local overheating of the EEC, pay particular attention to the Nacelle ANTI-ICE ducting for leakages. FADEC SYS FAULT NO DISPATCH - Reset breaker EIVMU 2 on the LH reset panel. - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. - Cycle breaker FADEC B ENG 2 on panel 722VU pos D43. FIRE DET FAULT NO DISPATCH - Perform BITE test of the FDU through the MCDU (ATA 26) FIRE LOOP A FAULT MEL 26-12-01 - Perform BITE test of the FDU through the MCDU (ATA 26) FIRE LOOP B FAULT MEL 26-12-01 - Perform BITE test of the FDU through the MCDU (ATA 26) FUEL FILTER CLOG NO DISPATCH - Check the fuel pump filter for contamination. - Check the fuel pump differential pressure switch. HP FUEL VALVE NO DISPATCH - Perform FADEC system static test through the MCDU (ATA 70) IGN A FAULT MEL 74-31-01 or 74-31-03-A - Reset breaker EIVMU 2 on the LH reset panel. IGN B FAULT MEL 74-31-01 or 74-31-03-A - Reset breaker EIVMU 2 on the LH reset panel. IGN A + B FAULT MEL 74-31-01 or 74-31-03-A - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. MINOR FAULT MEL 73-25-01-A - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. - Cycle breaker FADEC B ENG 2 on panel 722VU pos D43. OIL FILTER CLOG MEL 79-35-02-A - Check the oil filter for contamination. - Check the oil filter differential pressure switch. OIL HI TEMP NO DISPATCH - Check engine oil level. Created by: Brett A Mumford 44 of 45 A330 ECAM MESSAGE RESET GUIDE ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 ENG 2 CONTINUED OIL LO TEMP Apply ECAM procedure - Operational message… No actions required. OIL PRESS MEL 79-34-01-A - Check engine oil level, and signs for obvious oil leakages. REV FAULT MEL 78-30-01 - Reset breaker EVIMU 2 on the LH reset panel. REV INHIBITED MEL 78-30-01 or 78-30-07-A - Open LH Fan cowl and check that the inhibit lever is not in the inhibit position, and that the lock out pin is not installed on the left interface bracket. REV PRESSURISED NO DISPATCH - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. - Cycle breaker FADEC B ENG 2 on panel 722VU pos D43. REV UNLOCKED MEL 78-30-01 - Perform visual inspection of the reverser cowls. SHUT DOWN NO DISPATCH - Reset breakers FWC 1 and FWC 2 on the LH and RH reset panels. START FAULT NO DISPATCH - Cycle breaker FADEC A ENG 2 on panel 742VU pos Q73. - Cycle breaker FADEC B ENG 2 on panel 722VU pos D43. START VALVE FAULT MEL 80-11-01 - Check the starter valve and starter for failures. THR LEVER DISAGREE NO DISPATCH - Reset breaker EVIMU 2 on the LH reset panel. - Disagree between Throttle Control Lever position and the position detected by the EEC. THR LEVER FAULT NO DISPATCH - Reset breaker EVIMU 2 on the LH reset panel. - Disagree between Throttle Control Lever position and the position detected by the EEC. Created by: Brett A Mumford 45 of 45 (M) 60 PAGE 참조 (M) 64 PAGE 참조 (M) 66 PAGE 참조 (M) 59 PAGE 참조 (M) 60 PAGE 참조 (M) 52 PAGE 참조 (M) 50 PAGE 참조 (M) 30 PAGE 참조 (M) 47 PAGE 참조 (M) 56 PAGE 참조 (M) 46 PAGE 참조 - 1 - (M) 34 PAGE 참조 (M) 45 PAGE 참조 (M) 36 PAGE 참조 (M) 33 PAGE 참조 (M) 70 PAGE 참조 - 2 - (M) 73 PAGE 참조 (M) 73 PAGE 참조 - 3 - (M) 79 PAGE 참조 (M) 81 PAGE 참조 (M) 86 PAGE 참조 (M) 81 PAGE 참조 (M) 75 PAGE 참조 (M) 75 PAGE 참조 (M) 75 PAGE 참조 (M) 75 PAGE 참조 (M) 77 PAGE 참조 - 4 - (M) 94 Page - 5 - (M) 93 PAGE 참조 - 6 - (M) 104 PAGE 참조 (M) 117 PAGE 참조 (M) 117 PAGE 참조 (M) 125 PAGE 참조 (M) 115 PAGE 참조PAGE (M) 125 참조 - 7 - (M) 109 PAGE 참조 (M) 107 PAGE 참조 (M) 133 PAGE 참조 (M) 133 PAGE 참조 (M) 122 PAGE 참조 (M) 124 PAGE 참조 (M) 120 PAGE 참조 (M) 118 PAGE 참조 (M) 111 PAGE 참조 - 8 - (M) 163 PAGE 참조 (M) 150 PAGE 참조 (M) 151~156 P 참조 (M) 143 PAGE 참조 - 9 - (M) 151 PAGE 참조 (M) 138 PAGE 참조 - 10 - (M) 176 PAGE 참조 (M) 175 PAGE 참조 (M) 174 PAGE 참조 (M) 176 PAGE 참조 (M) 176 PAGE 참조 (M) 175 PAGE 참조 (M) 174 PAGE 참조 (M) 178 PAGE 참조 (M) 177 PAGE 참조 - 11 - (M) 176 PAGE 참조 (M) 175 PAGE 참조 (M) 174 PAGE 참조 - 12 - (M) 193 PAGE 참조 (M) 190 PAGE 참조 (M) 185, 187 P 참조 (M) 182 PAGE 참조 (M) 183 PAGE 참조 (M) 190 PAGE 참조 (M) 185,187 P 참조 (M) 191 PAGE 참조 (M) 191 PAGE 참조 (M) 179 PAGE 참조 (M) 179 PAGE 참조 (M) 191 PAGE 참조 (M) 193 PAGE 참조 (M) 190 PAGE 참조 (M) 185, 187 P 참조 (M) 179 PAGE 참조 (M) 179 PAGE 참조 (M) 179 PAGE 참조 - 13 - - 14 - (M) 208 PAGE 참조 (M) 204 PAGE 참조 (M) 204 PAGE 참조 (M) 312 PAGE 참조 (M) 199 PAGE 참조 (M) 217 PAGE 참조 - 15 - (M) 224 PAGE 참조 (M) 224 PAGE 참조 (M) 225 PAGE 참조 (M) 225 PAGE 참조 - 16 - (M) 236 PAGE 참조 (M) 238 PAGE 참조 (M) 233 PAGE 참조 (M) 235 PAGE 참조 (M) 241 PAGE 참조 - 17 - (M) 274 PAGE 참조 (M) 265 PAGE 참조 (M) 265 PAGE 참조 (M) 272 PAGE 참조 (M) 265 PAGE 참조 (M) 265 PAGE 참조 (M) 264 PAGE 참조 - 18 - (M) 283 PAGE 참조 (M) 284 PAGE 참조 (M) 286 PAGE 참조 (M) 280 P 참조 (M) 282 P 참조 (M) 282 P 참조 (M) 298 P 참조 - 19 - (M) 288 PAGE 참조 (M) 288, 290, 293 P (M) 292 PAGE 참조 (M) 293 PAGE 참조 (M) 290 PAGE 참조 (M) 300 PAGE 참조 - 20 - A330 REFERENCE HAND BOOK NO DISPATCH ITEM ● ATA 21 ▷ ECAM WARNING • FWD(AFT) OFV NOT OPEN - VC : BOTH CH FAIL 시 NO GO. (MEL 21-28-01) - AUTO CABIN PRESS CONTROL SYS (CPC, OFV AUTO CH) (MEL 21-31-01 a)): ER OPER' 시 SYSTEM 1 은 작동해야함. - MANUAL CABIN PRESS CONTROL SYS (CPC, OFV MAN CH, MAN V/S CONTROL SEL) (MEL 21-31-02) : ER OPER' 시 작동해야함. (CONTACT DISPATCHER FOR FLIGHT PLANNING) - NAGATIVE RELIEF V/V (MEL 21-31-07) - PC (MEL 21-53-01 a), b)) : 2 개 모두 작동해야함. (각 PC 의 ONE CH 은 INOP 되도됨), 1개 PC FAIL 시 나머지 PC 의 BOTH CH 은 작동해야함. - EMER RAM AIR INLET (MEL 21-55-01) - ZC (MEL 21-63-01) : BOTH CH FAIL 시 NO GO. ● ATA 22 ▷ ECAM WARNING • FCU FAULT • FM 1+2 FAULT - AUTO PILOT (MEL 22-10-01a), b)) : ER OPER' 시 AP1 은 작동해야함. (CONTACT DISPATCHER) - SIDE STICK TAKE OVER PB PRIORITY FUNCTION (MEL 22-10-03-A)) - AP DISENGAGEMENT WARNING (MEL 22-10-05) : ER OPER' 시 NO GO - LATERAL NAVIGATION (MEL 22-72-01a), b)) : ER OPER' 시 FM1의 LNAV 는 작동해야 하 며, MCDU1 의 BACK UP NAV 도 작동해야함. MAIN BASE 의 RNP 10 OPER 시 BOTH LNAV 작 동 해야함. - FUEL/TIME PREDICTION (MEL 22-73-02) : ER OPER' 시 FM1 의 FUEL/TIME PREDICTION 은 작동해야함. (CONTACT DISPATCHER) (REF MEL 28-51-02) - FCU SPD-MACH, ALT, HDG-TRK SELECTION KNOB (MEL 22-81-01-D)) - FCU BARO REFERENCE SEL INNER KNOB (MEL 22-81-02-B)-b)) - FMGEC (MEL 22-83-01) : ER OPER' 시 FMGEC 1 은 작동해야함. - 21 - ● ATA 23 ▷ ECAM WARNING • CIDS 1+2 FAULT - HF SYSTEM (MEL 23-11-01b)) : ER OPER' 시 HF 가 필요할 때 HF1 VOICE MODE 는 작동해야 함. (CONTACT DISPATCHER) - VHF SYSTEM (MEL 23-12-01) : VHF 1 은 작동해야함. - FLIGHT CREW INTERPHON SYSTEM (MEL 23-43-01) - CIDS (MEL 23-73-01) - RMP (MEL 23-81-01-A)) : RMP1 은 작동해야함. - RMP1의 HF1 & VHF1 KEY (MEL 23-81-01B)) ● ATA 24 ▷ ECAM WARNING • AC BUS 1 FAULT • DC BUS 1 FAULT • AC ESS BUS ALTN • DC BUS 2 FAULT • DC BUS 1+2 FAULT • AC BUS 2 FAULT • DC ESS BUS FAULT • AC ESS BUS FAULT • DC ESS BUS SHED • AC ESS BUS SHED • EMER CONFIG • BAT 1(2) FAULT • ESS TR FAULT • BAT 1(2) SYS FAULT • STATIC INV FAULT • DC BAT BUS FAULT • TR1(2) FAULT - AC BUS TIE CONTROL FUNCTION (MEL 24-20-01) - IDG OIL CIRCUIT (MEL 24-22-02a)) : 매 FLT 시 CHECK 항목 수행시 DISPATCH 가능 - AC EMERGENCY GENERATION (CSM/G, GCU, LINE CONTACTOR) (MEL 24-24-01) - MANUAL TRANSFER TO AC BUS 2 (ALTN FUNCTION) (MEL 24-25-01 B)) : ER OPER' 시 NO GO (CONTACT DISPATCHER) - LAND RECOVERY FUNCTION (MEL 24-27-01-H)-b)) - STATIC INVERTER AC GENERATION (MEL 24-28-01) - DC MAIN GENERATION(TR1, TR2, APU TR) (MEL 24-32-01) : TR1,TR2 는 NORMAL 이어야함. - DC EMER GENERATION ESS TR (MEL 24-34-01) - DC TIE CONTACTOR 1PC1 (DC BUS1-DC BAT BUS) (MEL 24-35-01-A)) - 22 - ● ATA 25 - COCKPIT SEAT MAN HORIZONTAL CONTROL (MEL 25-11-01-A)-a)) - COCKPIT SEAT SHOULDER HARNESS (MEL 25-11-02-A)) - MISCELLANEOUS EMERGENCY EQUIPMENT ∙ MEGAPHONE (MEL 25-65-01-A)) ∙ COCKPIT FLASH LT (MEL 25-65-01-B)) ∙ AUTOMATED EXTERNAL DEFIBRILLATORS (AED) (심장 제세동기) (MEL 25-65-01-H)b)) ● ATA 26 ▷ ECAM WARNING • ENG1(2) FIRE • APU FIRE • AVIONICS DET FAULT • AVNCS VENT SMOKE • AFT/BULK CRG SMOKE • FIRE DET FAULT • BULK CRG SMOKE • BULK AVN SMOKE • CAB 1(2)(3)(4) SMOKE (IF INSTALLED) • CAB REST SMOKE (A330-200) • DET FAULT • CAB VIDEO SMOKE (IF INSTALLED) • FLT REST SMOKE (IF INSTALLED) • FWD CRG SMOKE • LAVATORY SMOKE - FIRE LIGHT IN ENG FIRE/PUSH PB SW (MEL 26-12-03) : 각 PB 에는 8개의 BULB 가 있음. 각 PB 당 4개 BULB 의 OUT 은 GO ITEM 임. - APU FIRE DETECTION LOOP A (MEL 26-13-01-A)b)) : LOOP B INOP 은 EACH FLIGHT 시 APU FIRE TEST OK 시 GO ITEM 임. LOOP A 는 APU 사용안할시 GO (APU MASTER SW OFF). - APU FIRE P/B LT (MEL 26-13-02a),b)) : 4 개 의 BULB INOP 또는 APU 사용안할시 GO. - COCKPIT POTABLE FIRE EXTINGUSHER (MEL 26-24-01-A)) - 23 - ● ATA 27 ▷ ECAM WARNING • PITCH TRIM NOT IN T.O RANGE • L(R) INR(OUTR) ALL FAULT • RUD TRIM NOT IN T.O RANGE • L(R) SIDE STICK FAULT • SLAT(FLAP) NOT IN T.O CONFIG • L+R ELEV FAULT • SPD BRAKE NOT RETRACED • PRIM 2 FAULT • ADR DISAGREE • RUD TRIM FAULT • ALTN LAW • RUD TRV LIM FAULT • DIRECT LAW • SEC 2 FAULT • ELEV REDUND LOST • SEC 2 PITCH FAULT • ELEV SERVO FAULT • SIDESTICK PRIORITY FAULT • FCDC 1 FAULT • SLAT TIP BRK FAULT • FCDC 1+2 FAULT • SLAT SYS 1 FAULT • FLAP TIP BRAKE FAULT • SLATS FAULT • FLAPS FAULT • SLATS LOCKED • FLAPS LOCKED • SPD BRK STILL OUT • FLAP/MCDU DISAGREE • STB CTL FAULT • IR DISAGREE • YAW DAMPER 1 FAULT • L(R) ELEV FAULT • YAW DAMPER FAULT - INBORAD AILERON SERVO CONTROL (MEL 27-14-01-B)) - RUD G(B,Y) SERVO JAM (MEL MEL 27-25-02-A)B) : ONLY FOR -300 KAL MSN 0162-0219 ,0241-0256, 0267-055, T/S 후 FALSE 확인되지 않거나 ACTUAL 이면 NO GO. - RUD G(B,Y) SERVO JAM (MEL MEL 27-25-02-A)C) : ONLY FOR -200 KAL MSN 0222-0226, 0258, T/S 후 실제 결함 일경우 NO GO - YAW DAMPER SYSTEM (MEL 27-26-01) : SYSTEM 1 INOP → NO GO. SYSTEM 2 INOP → 매 FLIGHT 마다 BYDU OPER' CHECK. (CAT Ⅱ DOWN GRADE, CONTACT DISPATHCER) - ELEV SERVO CONTROL (MEL 27-34-01) - THS STABILIZER MECHANICAL CONTROL (MEL 27-41-01) - THS STABILIZER ACT' ELEC MOTOR (MEL 27-44-01a) : ER OPER' 시 MOTOR 1 은 작동해야 함.(CONTACT DISPATHCER) MOTOR 2,3 는 DEACTIVE 상태에서 작동안해도됨. - FLAP POSITION INDICATION ON EWD (MEL 27-55-01-A)) - SLAT SYSTEM 1 (MEL 27-81-01-A)) - SLAT POSITION INDICATION ON EWD (MEL 27-85-01-A)) - SIDE STICK PRIORITY LIGHT (MEL 27-92-04) - FCPC 1 (MEL 27-93-01-A)) : ER OPER' 시 NO GO. - FCPC 2(MEL 27-93-01-B)) - NORMAL LAW (MEL 27-93-04) - SEC 2 (MEL 27-94-01 B)) - FCDC (MEL 27-95-01) : FCDC1 INOP → NO GO. - 24 - ● ATA 28 ▷ ECAM WARNING • ENG 1(2) LP VLV FAULT • L(R) STBY PUMP LO PR • FCMC 1 FAULT • L(R) WING PUMP LO PR • FCMC 1+2 FAULT • L(R) WING TK LO LVL (ACTUAL CAUTION) - EMER INNER TANK ISOL VALVE (MEL 28-11-01) - OVERPRESSURE PROTECTOR IN CENTER TANK (MEL 28-12-01B)) : FOR-200 KAL MSN 222-226, 025 - INNER TANK MAIN PUMP (MEL 28-21-01 A)a)) : L2 또는 R2 INOP 은 GO 이나 ER OPER' 시 NO GO (CONTACT DISPATCHER) - INNER TANK STBY PUMP (MEL 28-21-01 B)) - CROSS FEED VALVE (MEL 28-23-01) : CLOSE POS' 으로 GO 이나 ER OPER' 시 NO GO. (CONTACT DISPATCHER) - ENG LP VALVE (MEL 28-24-01) - LP VALVE INDICATION ON ECAM FUEL PAGE (MEL 28-40-15-B)) - WING TANK OVER FLOW WARNING ON EWD (MEL 28-46-04-B)b)) : T/S 후 FALSE 확인되지 않 거나 ACTUAL 이면 NO GO. - FCMC 1 (MEL 28-51-01-A)) ● ATA 29 ▷ ECAM WARNING • B ENG 1 PUMO LO PR (ACTUAL CAUTION) • B RSVR LO AIR PR (ACTUAL CAUTION) • G RSVR UNDER FILLED • G SYS LO PR (ACTUAL CAUTION) • G+B SYS LO PR (ACTUAL CAUTION) • B RSVR LO LVL (ACTUAL CAUTION) • G+Y SYS LO PR (ACTUAL CAUTION) • B RSVR OVHT (ACTUAL CAUTION) • RAT FAULT (ACTUAL CAUTION) • B SYS LO PR (ACTUAL CAUTION) • B+Y SYS LO PR (ACTUAL CAUTION) • G ENG 1+2 PUMP LO PR (ACTUAL CAUTION) • G ENG 1(2) PUMP LO PR (ACTUAL CAUTION) • G RSVR LO AIR PR (ACTUAL CAUTION) • G RSVR LO LVL (ACTUAL CAUTION) • G RSVR OVHT (ACTUAL CAUTION) - EDP (MEL 29-10-01-A)) - B BRAKE ACCUMULATOR (MEL 29-10-03) - ENG PUMP FIRE VALVE (MEL 29-10-04) - HP SYSTEM FILTER (MEL 29-10-05) - RAT (MEL 29-24-01) - 25 - • Y ENG 2 PUMP LO PR (ACTUAL CAUTION) • Y RSVR LO AIR PR (ACTUAL CAUTION) • Y RSVR LO LVL (ACTUAL CAUTION) • Y RSVR OVHT (ACTUAL CAUTION) • Y SYS LO PR (ACTUAL CAUTION) ● ATA 30 ▷ ECAM WARNING • L(R) INR(OUTR) WING HI PR • L+R WSHLD HEAT - ENG ANTI ICE VALVE (MEL 30-21-01-A)) : CLOSE DEACITVE 로 GO 이나 ER OPER' 시 AIV 는 작동해야됨(INOP 시 NO GO) (CONTACT DISPATCHER). - AOA PROBE HEATING (MEL 30-31-04a) : ER OPER' 시 CAPT 과 STBY 는 작동해야함. - ICING CONDITION 일 경우 ATA30 결함 나올경우 CONTACTI DISPATCHER ● ATA 31 ▷ ECAM WARNING • DISPLAY DISCREPANCY • FWC 1+2 FAULT • EFIS DMC 1(3) FAULT • SDAC 1 FAULT • ECAM DMC 1(3) FAULT • OEB/FWC DISCREPANCY • FWC 1 FAULT • SDAC 1+2 FAULT - ECP ALL PB (MEL 31-56-01-B)) - ECP RCL PB(MEL 31-56-01-C)) - ECP EMER CANC PB (MEL 31-56-01-F)) - DISPLAY UNIT (MEL 31-63-01b)) : ER OPER' 시 NDU 1 은 작동해야함. - 26 - ● ATA 32 ▷ ECAM WARNING • ANTI SKID FAULT • LGCIU 1+2 FAULT • PARKING BRK ON • HYD SEL VALVE • HOT • SYS DISAGREE • DOOR NOT CLOSED • N/W STRG FAULT • LGCIU 1 FAULT • TIRE LO PR (ACTUAL FAULT) - LGCIU1 (MEL 32-31-01-A)) - SAFETY VALVE (MEL 32-31-02) : TWO CH 중 ONE CH 이 작동 되면 GO. - LANDING GEAR RETRACTING SYSTEM (MEL 32-31-03) : ER OPER' 시 NO GO. - LANDING GEAR GRAVITY EXT' SYSTEM (MEL 32-33-01) : ER OPER' 시 NO GO. - GREEN BRAKE SYSTEM (MEL 32-42-02) : LANDING GEAR 당 1개의 WHEEL BRAKING 의 INOP 은 GO 임. 해당 결함 BRAKE DEACTIVE 하고 해당 WHEEL 의 TACHOMETER 는 정상작동해야함. FLIGHT MANUAL 의 PERF PENALTY 적용됨. - BSCU (MEL 32-42-03) : ONE CH 이 작동되면 GO - BLUE BRAKE SYSTEM (MEL 32-44-01) : LANDING GEAR 당 1개의 WHEEL BRAKING 의 INOP 은 GO 임. 해당 결함 BRAKE DEACTIVE 하고 BOTH T/R 은 정상작동해야함. - PARKING BRAKE (MEL 32-45-01) : PARKING BRAKE 를 작동시키는 2개의 MOTOR중 1개의 MOTOR는 작동해야함. - NWS CONTROL SYSTEM (MEL 32-51-01) : FCOM 3.04.32 참조 - GEAR NOT DOWN WARNING (MEL 32-61-02) : ECAM IND 이 작동하면 DOWN RED ARROW 는 작동안해도 됨. ● ATA 33 - LDMCR 의 EXIT SIGN (MEL 33-50-04-B)A)) : 3개까지의 인접하지 않는 BULB 나 LED 는 INOP 되도 됨. EMER EXIT LT 작동하거나, FLASH LT 가 있거나, LDMCR 을 LOCKED CLOSE 하고 PLACARD 부착 하면 GO. - OVERHEAD EMERGENCY LIGHTING (MEL 33-51-01A)) : MAX 3개까지 인접하지 않는 EMER LIGHT 는 INOP 되도 됨. - FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING (MEL 33-51-01-E)-a)) : 인접해서 INOP 되거나 INOP 된 PATH MARKING 의 끝이 DOOR 쪽을 가르키는 방향이면 NO GO. - FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING EXIT MARKER (MEL 33-51-01-E)-b)) : INOP 된부분 DOOR 쪽 SEAT BLOCK 후 DISPATCH. - 27 - ● ATA 34 ▷ ECAM WARNING • ADR 1+2(1+3)(2+3) FAULT • RA 1+2 FAULT • IR 1+2(1+3)(2+3) FAULT - IR (MEL 34-10-01-A)) : ER OPER' 시 IR1 또는 IR3 INOP 시 NO GO. - ADR (MEL 34-10-01-B)) : ER OPER' 시 ADR1 또는 ADR3 INOP 시 NO GO. - ACTUAL AIRSPEED REFERENCE LINE AND SCALE ON PFD (MEL 34-13-01-A)) - VMO/MMO IND ON PFD (MEL 34-13-01-C)-a)) - ALTITUDE IND ON PFD (MEL 34-13-01-D)) - BARO REFERENCE IND ON PFD (MEL 34-13-01-E)) - VERTICAL SPD ON PFD (MEL 34-13-01-F)) - ATTITUDE DISPLAY (MEL 34-14-01-A)) : ER OPER' 시 NO GO. - ILS (MEL 34-36-01) : ILS1 INOP 은 NO GO. (CONTACT DISPATCHER) - WEATHER RADAR SYSTEM (MEL 34-41-01) : ER OPER' 시 WEATHER RADAR SYSTEM 1 은 작 동해야함. (CONTACT DISPATCHER) - DME (MEL 34-51-01) : ER OPER' 시 DME 1 은 작동해야함. (CONTACT DISPATCHER) - ATC TRANSPONDER (MEL 34-52-01) : ER OPER' 시 ATC 1 은 작동해야함. (CONTACT DISPATCHER) - ADF (MEL 34-53-01) : ER OPER' 시 ADF 가 INTENDED FLIGHT 를 위해 필요시 ADF1 은 작동 해야함. (CONTACT DISPATCHER) - VOR (MEL 34-55-01) : ER OPER' 시 VOR 1 은 작동해야함. (CONTACT DISPATCHER) ● ATA 35 - CREW OXYGEN CYLINDER (MEL 35-12-01-B)) ● ATA 36 ▷ ECAM WARNING • BMC 1 FAULT • L(R) WING LEAK DET FAULT • L(R) WING LEAK - CROSSBLEED VALVE (MEL 36-12-04) : AUTO CONTROL MODE 는 INOP 되도 됨. - EWD AIR ENG 1(2) BLEED LEAK (MEL 36-23-01-A)b)) : T/S 결과 ACTUAL LEAK 이면 NO GO FALSE WARNING 일 경우 관련 PYLON LEAK DETECTION LOOP 는 DEACTIVE - 28 - ● ATA 56 - COCKPIT FRONT WINDSHIELD (MEL 56-11-01a),b)) : 1개의 WINDSHIED 의 OUTER PLY CRACK (or BURN SPOT) 은 10 FLIGHT 까지 가능 (HEATING DEACTIVED). 하지만 VISUALITY 에 이상이 없어야하며, ICING COND' 이 아니고, 다른쪽 WINDSHIELD 는 NORMAL 이어야함. - COCKPIT FIXED WINDOW (MEL 56-11-02a),b)) : 1개의 FIXED LATERAL WINDOW 의 OUTER PLY CRACK(or BURN SPOT) 은 ONE FLIGHT 까지 가능 하지만 WINDOW HEATING 이 DEACTIVE 되고, VISUALITY 에 이상이 없어야하며, ICING COND' 이 아니고, 다른쪽 FIXED LATERAL WINDOW 는 NORMAL 이어야함. - COCKPIT SLIDING WINDOW (MEL 56-12-01a),b)) : 1개의 FIXED LATERAL WINDOW 의 OUTER PLY CRACK(or BURN SPOT) 은 ONE FLIGHT 까지 가능 하지만, WINDOW HEATING 이 DEACTIVE 되고 VISUALITY 에 이상이 없어야하며, ICING COND' 이 아니고, 다른쪽 FIXED LATERAL WINDOW 는 NORMAL 이어야함. ※ NOTE : WINDOW 의 MINOR DAMG 의 경우(MM 기준) CREW 의 VISIBLITY 에 영향이 없다는 동 의 를 얻어야 함. ※ CKPT WINDOW INR PLY DMGE 는 NO GO. ※CABIN WINDOW (MEL 56-21-01) : DAMG 의 숫자는 상관없으나, NON PRESSURIZATION 운항을 해야함. ● ATA 70 ▷ ECAM WARNING • ALL ENG FLAME OUT • HP FUEL VLV • IGN A+B FAULT (ACTUAL FAULT) • START FAULT • OIL FILTER CLOG (ACTUAL FAULT) • T.O THRUST DISAGREE • OIL HI TEMP • TYPE DISAGREE • OIL LO PR • CTL SYS FAULT • SHUT DOWN • FADEC FAULT • START FAULT • FADEC OVHT • THE LEVER DISAGREE • FADEC SYS FAULT • THE LEVER FAULT • FUEL FILTER CLOG (ACTUAL FAULT) - FADEC CH A (MEL 73-25-01-B)) : ER OPER' 시 NO GO. (CONTACT DISPATCHER) - EPR CONTROL MODE (MEL 73-25-01-C)) : ER OPER' 시 NO GO - IGN SYS A (MEL 74-31-01-A)) : ER OPER' 시 NO GO. (CONTACT DISPATCHER) - N1 INDICATION ON EWD (MEL 77-00-01-B)) - N2 INDICATION ON EWD (MEL 77-00-01-C)) - EGT INDICATION ON EWD (MEL 77-00-01-E)) - EWD ENG 1(2) REV PRESSURIZED (MEL 78-30-07) : T/S 결과 FALSE 로 판정되지않으면 NO GO - OIL TEMP INDICATION ON ECAM ENG PAGE (MEL 79-32-01-A)) - OIL PRESSURE INDICATION ON ECAM ENG PAGE (MEL 79-33-01-A)) - 29 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA21) ● MMEL 21-21-04-B) VENTILATION ○ DEACTIVATION OF THE LDMCR ISOLATION-VALVE (AMM 21-21-00-040-801) 1. CB OPEN PANEL 722VU 742VU 742VU DESIGNATION CARGO VENT CTL L1 CARGO VENT CTL L2 ISOL VLV LDMCR FIN 2HN 1HN 4HG LOCATION U43 L72 L70 2. ENG BLEED, APU BLEED, ALL PACK SW OFF 3. AFT CARGO 로 접근후 LDMCR SERVICE PANEL OPEN 4. CLAMP (4) 와 DUCT (5) REMOVE 5. 152VW (3) OPEN 후 ISOLATION VALVE 에 접근. 6. ELEC' CONNECTOR (2) 분리후 STRUCTURE 에 ATTACH. 7. ISOLATION VALVE 의 MANUAL OVERRIDE LEVER (1) 를 CLOSE 위치에 놓을것. 8. OPEN 되었던 CB CLOSE 후 항공기 원상. 9.EWD 에 'COND CRG REST ISOL VALVE FAULT' MSG DISPLAY. (1) (2) 152VW - 30 - ● MMEL 21-25-01 TURBOFAN ○ DEACTIVATION OF THE TURBOFAN SUPPLY LINE (AMM 21-25-00-040-801) 1. ACCESS DOOR 193CB OPEN & ACCESS COVER 192CZ REMOVE 2. ENG BLEED, APU BLEED SW OFF 3. DUMMY CONNECTION (2) 에서 PLUG REMOVE 4. TURBOFAN 에서 SUPPLY LINE (1) 분리하여 DUMMY CONNECTION (2) 에 연결. 5. 분리된 LINE 은 BLANKING PLUG 로 채움. SIZE : 1 1/2" - 31 - ○ DEACTIVATION OF THE MECHANIC CALL HORN (AMM 21-25-00-040-801) - L RELAY PLATE 807VU 의 TERMINAL BLOCK 3101VT의 PIN 17/V 에서 WIRE 19 를 DISCONNECT 한다음 DISCONNECT 된 부분 정리. NOTE : ONLY TURBOFAN MONITORING 이 DEACTIVE 된것이며, HORN 은 다른 기능을 위하여 계속 SVCABLE 쓸수있음. ALTERNATE 방법으로 EXT PWR CONTROL PANEL 에 있는 RESET P/B 을 이용할수 있다 (다음 FLIGHT 후 에도 FAULT 지속된다면 HORN 이 다시 울리게됨) 3101VT ● MMEL 21-25-02 TURBOFAN SUPPLY VALVE ○ DEACTIVATION OF THE MECHANIC GROUND CALL HORN WHEN THE TURBOFAN SUPPLY VALVE IS INOPERATIVE IN THE CLOSED POSITION (AMM 21-25-00-040-803) - 상기 DEACTIVATION OF THE MECHANIC CALL HORN (AMM 21-25-00-040-801) 절차와 동일함. - 32 - ● MMEL 21-25-03 PRESSURE SWITCH ○ DEACTIVATION OF THE AIR-CONDITIONING-COMPARTMENT VENTILATION PRESSURE SWITCH (AMM 21-25-00-040-802) 1. CB OPEN : TURBO FAN CTL 3HR (T06), EXT HORN 2WC (H78) 2. APU BLEED, ENG BLEED, PACK PB OFF 3. ACCESS DOOR 193CB OPEN & ACCESS COVER 192CZ REMOVE 4. PRESSURE SW (2) 로부터 ELEC' CONNECTOR (1) 분리하여 STRUCTURE 에 ATTACH 하라. 2HR 1 2 - 33 - ● MMEL 21-26-01 EXTRACT FAN ○ DEACTIVATION OF THE MECHANIC CALL HORN (6WC) AFTER A FAILURE OF THE AVIONICS VENTILATION EXTRACT FAN (AMM 21-26-00-040-809) ※ 이 PROCEDURE 는 EXTRACT FAN FAILURE 후에 HORN 작동을 방지하기위한 DEACTIVATION 이며 MANDATORY 는 아님. 다른 기능을 위한 HORN 의 작동은 계속 유지됨. 1. EXT HORN CB 2WC (H78) OPEN 2. L RELAY PLATE 807VU 의TERMINAL BLOCK 3101VT의 PIN 5/M에서 WIRE 28을 DISCONNECT 한다음 DISCONNECT 된부분 정리후 CB CLOSE. NOTE : WIRE DISCONNECT 할때 CB 2WC (H78) OPEN 되어있으면 HORN 작동하지 않음. HORN 은 다른 기능을 위하여 계속 SVCABLE 쓸수있으며. ALTERNATE 방법으로 EXT PWR CONT PNL에 있는 RESET PB 을 이용할수 있다 (다음 FLIGHT 후에도 FAULT 지속된다면 HORN 이 다시 울리게됨). - 34 - 3101VT ○ DEACTIVATION 후 추가 조건 1) BOTH CABIN FAN 작동 2) OVERHEAD PANEL EXTRACT PB 을 OVRD POSITION 에 놓음. (UNDERFLOOR V/V CLOSE 되고 OVBD EXTRACT V/V PARTIALLY OPEN.) 3) FLIGHT ALTITUDE 에 제한이 있음. - 35 - ● MMEL 21-26-02 OVERBOARD EXTRACT FAN ○ DEACTIVATION OF THE AVIONICS VENTILATION OVERBOARD EXTRACT VALVE (13HQ) (AMM 21-26-00-040-801) CAUTION : SWITCH ON POSITION SET시 손가락 부상위험 있음. 1) ENG STOP 된 상태에서 GROUND 작동을 위한 FULLY OPEN POSITION DEACTIVATION - 'PUSH' LATCH 를 PUSH 하여 HANDLE을 RELEASE. - HANDLE을 당기지만 MECHANMISM 에는 ENGAGE 하지말것. - DEACTIVATION SW OFF 하고 HANDEL을 당겨 MECHANISM 에 ENGAGE. - CW 방향으로 MAIN FLAP 이 FULLY OPEN 상태가 될 때까지 TURN NOTE : AUX FLAP 은 OPEN 되어있어야 함. - HANDLE을 집어 넣어라. ※ 이상태에서 는 DISPATCH 안됨. DISPATCH 위해서는 다음 PROCEDURE 수행요함. - 36 - 2) ENG START 직전 PATIALLY OPEN POSTION 으로 DEACTIVATION - 'PUSH' LATCH 를 PUSH 하여 HANDLE을 RELEASE. - HANDLE을 당기지만 MECHANMISM 에는 ENGAGE 하지말것. - DEACTIVATION SW OFF 하고 HANDEL을 당겨 MECHANISM 에 ENGAGE. - CCW 방향으로 MAIN FLAP 이 FULLY CLOSE 상태가 될 때까지 TURN NOTE : MAIN FLAP 이 닫혔을때 HANDLE 을 계속 TURN 하게 되면 AUX FLAP 이 닫힘. - AUX FLAP 이 OPEN POSITION 인지 확인하고 HANDLE 집어 넣을것. DEACTIVATION SWITCH HANDLE LATCH HANDLE 3) OVERHEAD PANEL EXTRACT PB 을 OVRD POSITION 에 놓음. (UNDERFLOOR V/V CLOSE 되고 OVBD EXTRACT V/V PARTIALLY OPEN.) 4) ONE ENG TAXI NOT ALLOWED 5) ONE PACK INOP‘ 시 고도제한 에 관련사항. (DEFER INTERVAL 에 의한 ALTITUDE LIMIT 가 다름.) - 37 - ● MMEL 21-26-03 UNDERFLOOR EXTRACT VALVE ○ DEACTIVATION OF THE UNDERFLOOR EXTRACT VALVE (12HQ) IN THE CLOSED POSITION (AMM 21-26-00-040-805) 1. FLOOR PNL 132JF (FWD CGO) REMOVE 2. ELEC' CONNECTOR (1) 분리하고 BLANKING CAP. STRUCTURE 에 붙들어 맬것. 3. VALVE 의 MANUAL MECH' LEVER 를 CCW 로 TURN 하여 VALVE 를 FULLY CLOSE. NOTE : HANDLE 을 'C' 방향으로 ALIGN 시켜야함. 4. OVERHEAD PANEL EXTRACT PB 을 OVRD POSITION 에 놓음. ○ DEACTIVATION 후 추가 조건 1) ENG START 직전 OVERHEAD PANEL EXTRACT PB 을 OVRD POSITION 에 놓음 2) ONE PACK INOP‘ 시 고도제한 에 관련사항. (DEFER INTERVAL 에 의한 고도 LIMIT 가 다름.) - 38 - ON A/C 001-099 (다른 A/C 도 거의 동일한 위치임) - 39 - ● MMEL 21-26-04 AVIONICS EQUIPMENT VENTILATION CONTROLLER (AEVC) ○ DEACTIVATION OF THE AVIONICS EQUIPMENT VENTILATION CONTROLLER (AEVC) (2HQ) (AMM 21-26-00-040-808) 1. CB OPEN : AEVC 4HQ (L05), AVNCS VENT CTL 8HQ (A65) 2. FWD CGO FLOOR PNL 132JF REMOVE (다음 FIG 참조) 3. OVERHEAD PANEL EXTRACT PB 을 OVRD POSITION 에 놓음. 4. UNDERFLOOR EXTRACT VALVE(12HQ) 를 OPEN POSITION 에 SET 5. MANUAL LEVER를 'O' POSITION 으로 ALIGN 하고 ELEC CONNECTOR 는 분리 하지말것 6. ENG STOP 시 OVBD EXTRACT VALVE (13HQ) 를 FULL OPEN POSITION 에 두라 (AMM 21-26-00-040-801) 7. BEFORE THE ENG START (OVBD EXTRACT V/V (13HQ) CLOSE POSITION SET) • HANDLE을 RELEASE POS 으로 하되 MECH' 에는 ENGAGE 시키지 마라. • DEACTIVE SW를 “OFF" 하고 HANDLE을 MECH' 에 ENGAGE 시켜 CCW 방향으로 • TURN 하여 MAIN & AUX FLAP 을 FULL CLOSE 시켜라. • DEACTIVE SW 를 “ON" 하고 HANDLE 을 집어넣어라. NOTE : DEACTIVE SW 를 ‘OFF’ 에 놓아서는 안되며 MAIN FLAP & AUX FLAP 이 FULLY CLOSE 되었는지 확인할것. 8. CB CLOSE 후 A/C 원상할것. - 40 - ON A/C 001-099 (다른 A/C 도 거의 동일한 위치임) - 41 - COMPONENT LOCATION FIN 2HQ 11HQ 7HQ 12HQ 13HQ 5HQ 3HQ 9HQ 10HQ FUNCTIONAL DESIGNATION AEVC PRESS SW-EXTRACT. AVNCS VENT FAN-EXTRACT V/V-U/FLOOR V/V-OVBD CED RELAY CAUT LT-ADIRU&AVNCS VENT PB-VENT/EXTRACT - 42 - PANEL 807VU 925VU 212VU ZONE 122 134 134 134 133 121 121 120 212 ACCESS DOOR 811 132EF 132JF 132LF 811 811 811 ATA REF. 21-26-34 21-26-11 21-26-51 21-26-56 21-26-57 21-26-15 21-26-00 21-26-00 21-26-00 ● MMEL 21-26-05 COOLING EFFECT DETECTOR (CED) ○ DEACTIVATION OF THE COOLING EFFECT DETECTOR (AMM 21-26-00-040-806) 1. 아래 CB CLOSE 되었는지 확인할것. 2. ELEC RACK을 통해서 VENT' AIR FLOW 의 BLOW 상태를 확인 NOTE : SD 의 COND PAGE에서 'FAN' INDICATION 이 보이지 않은 것으로 확인가능 FAN : FAN FAILURE 또는 PB OFF, VC FAULT 일 경우 AMBER 지시 NOTE : NORMAL CONDITION 일 경우지시 하지 않음. 3. COCKPIT CREW 에게 CED DEACTIVATION 인지시킬것. - 43 - ● CED : 내부저항(HEATING UNIT)에 의해 ELEC PWR 과 통과하게 되면 열을 발생 GRU DOWN STREAM 에 위치하여 INSUFFICIENT COOLING 시 WARNING SIGNAL 제공 (GRD HORN) I (PICK UP 전류) = V(일정) / R (∝TEMP 가변저항) ● PRESS' SW : VENT AIR 의 PRSS'를 감지하여 LO FLOW 시 WARNING SIGNAL 제공 및 EXTRACT P/B 의 FAULT LT ON 시킴 EXT' FAN 이 작동하면 PRESS‘ SW 의 PRESS' 는 높아짐. ※ CED와 PRESS' SW 에 의해 COOLING CAPACITY MONITOR - 44 - ● MMEL 21-27-02 SKIN VALVE ○ DEACTIVATION OF THE GRU SKIN VALVE (8HD) (AMM 21-27-00-040-801) 1. OVERHEAD PANEL GND COOL PB SW OFF 2. SKIN V/V의 HANDLE LATCH PUSH 하여 HANDLE RELEASE 3. HANDLE 잡아당겨 MECHNISM ENGAGE 4. DEACTIVE SW 'OFF' 놓고 CCW 방향으로 HANDLE 돌려 FLAP을 FULL CLOSE 5. HANDLE 접고 LATCH 건다 GRU SKIN VALVE - 45 - ● MMEL 21-28-02-B) FWD CARGO ISOLATION VALVE ○ DEACTIVATION OF THE FWD CARGO-COMPARTMENT ISOLATION-VALVE/S AND OF THE COLD AIR VALVE (298HN) (AMM 21-28-00-040-801) 1. CB OPEN : CARGO VENT CTL L1 2HN (U43), CARGO VENT CTL L1 2HN (L72) 2. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 3. FWD ISOL VALVES PB 'OFF' 4. FWD CARGO COOLING SELECTOR 'OFF' 5. REMOVE PNL : 286HN (REM 132WW OR 132UW), 287HN(131WW) 289HN(131QW OR 131FX), 298HN(131QF OR 131VF) 6. ELEC PLUG (2) DISCONNECT 하고 TIE WRAP 으로 STRUCTURE 에 묶을것. 7. FOR 286HN, 287HN, 289HN (ISOLATION VALVE) : MANUAL OVRD LEVER (1) 를 CLOSE POSITION ‘C’ 로 움직일것. 8. FOR 298HN (COLD AIR VALVE) : MANUAL OVRD LEVER (1) 를 CLOSE POSITION ‘C’ 로 움직여 TEMPORARILY 고정시켜 놓을것. 9. EWD 에 "COND FWD CRG ISOL FAULT" MESSAGE 나타나고 ISOL VALVES PB ‘FAULT’ LT ON 됨. 10. EWD 에 "COND FWD CRG COOL FAULT" MESSAGE 나타나고 SD COND PAGE 에 COLD AIR VALVE IND' 이 AMBER DISPLAY 됨. 11. OPEN 됨 CB CLOSE 하고 항공기 원상할것. - 46 - ● MMEL 21-28-02-D) CARGO COOLING SYSTEM ○ DEACTIVATION OF THE FWD CARGO-COMPARTMENT COOLING SYSTEM (AMM 21-28-00-040-804) 1. CB OPEN : CARGO VENT CTL L1 2HN (U43), CARGO VENT CTL L1 2HN (L72) 2. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 3. FWD CARGO COOLING SELECTOR 'OFF' 4. 131QF (A/C 001-099) OR 131VF (A/C101-199) PNL REMOVE 5. ELEC PLUG (2) DISCONNECT 하고 TIE WRAP 으로 STRUCTURE 에 묶을것. 6. COLD AIR VALVE (298HN) 의 MANUAL OVRD LEVER (1) 를 CLOSE POSITION ‘C’ 로 움직여 TEMPORARILY 고정시켜 놓을것. 7. EWD 에 "COND FWD CRG COOL FAULT" MESSAGE 나타나고 SD COND PAGE 에 COLD AIR VALVE IND' 이 AMBER DISPLAY 됨. 8. OPEN 된 CB CLOSE 하고 항공기 원상할것. COOLING SELECTOR - 47 - 287HN(ISOL V/V) 132U 287HN (ISOL V/V) 131W 298HN (COLD AIR V/V) 131QW Z130 132Q 289HN (ISOL V/V) FOR 298HN, 1 OPEN CLOSED OPEN CLOSED FOR 286HN, 287HN 289HN - 48 - 2 - 49 - ● MMEL 21-28-04-B) BULK CARGO ISOLATION VALVE ○ DEACTIVATION OF THE BULK CARGO-COMPARTMENT ISOLATION-VALVE (283HN, 284HN) (AMM 21-28-00-040-803) 1. CB OPEN : CARGO VENT CTL L1 2HN (U43), CARGO VENT CTL L1 2HN (L72) 2. BULK ISOL VALVES PB 'OFF' 3. ACCESS PNL REMOVE : FOR 283HN (151TW), FOR 284HN (162RW) 4. ELEC CONNECTOR (2) 분리후 고정 하고 MAN OVRD LEVER (1) 를 'C' 방향으로 TURN (CLOSE POSITION) 5. EWD 에 "COND BULK CRG ISOL VALVE FAULT" MESSAGE 나타남 6. BULK CGO ISOL VALVES PB 에 'OFF' OR 'FAULT' ON 7. OPEN 된 CB CLOSE 하고 항공기 원상할것. 284HN 162RW 151TW 283HN - 50 - - 51 - ● MMEL 21-31-02 MANUAL CABIN PRESSURE CONTROL SYSTEM ○ VERIFICATION TEST OF THE TWO AUTOMANTIC CABIN-PRESSURE CONTROL SYSTEM (AMM 21-31-00-040-805) - PRESSURE CONTROL AND MONITORING SYSTEM OPERATION TEST 수행 (AMM 21-31-00-710-801) ● MMEL 21-31-04 SAFETY VALVE ○ VERIFICATION TEST (SAFETY VALVES AND OUTFLOW VALVES) (AMM 21-31-00-040-803) 1. SAFETY VALVE POSITION IND' OPER TEST 수행 (AMM 21-31-00-710-805) • AFT GLY 후방 WALL 에 있는 ACCESS PNL OPEN. (316HL,317HL : SAFETY VALVE) • VALVE DIAPHRAGM 을 손가락으로 눌러 SPRING 을 압축 시키고 최소 1분동안 그상태 로 HOLD ① SD : CAB PRESS PAGE (SAFETY IND 'GREEN' → 'AMBER') & SC, MC LT + , - 52 - (SINGLE CHIME) ② EWD : 'CAB PR SAFETY V/V OPEN' MESSAGE ON • SAFETY V/V DIAPHRAGM RELEASE ① OPEN SAFETY VALVE SYMBOL CLOSE 되고 'AMBER' → 'GREEN' • ECAM CONT PNL 에있는 CLR PB PUSH ① MC LT OFF + SC OFF ② 'CAB PR SAFETY V/V OPEN' MESSAGE OFF • 나머지 SAFETY VALVE 에 대해서도 상기 절차 수행. 316HL FR80 317HL SAFETY VALVES Z270 FR72 POS' IND' OPER' TEST 시 PUSH HOLD 할부분 (1) AFT GALLEY 뒤쪽 ACCESS DOOR OPEN 후 접근 2. ONE SAFETY VALVE 가 정상작동하는지와 INOP‘ SAFETY VALVE 가 CLOSE POSITION 에있는가 확인 3. PRESSURE SENSE LINE (1)을 분리하여 항공기 STRUCTURE 에 ATTACH 할것. 4. PRESSURE CONTROL & MONITORING SYSTEM OPER' TEST (AMM 21-31-00-710 -801) 와 MANUAL MODE OPER TEST (AMM 21-31-00-710-802) 수행 • AMM 21-31-00-710-801 MCDU SYSTEM REPORT/TEST 의 'AIRCOND' PAGE 접근 → CPC1 → 'TEST' PUSH (INITIAL CONDITION 만들어줌) → START TEST → 45초후에 'TEST OK' ※ INITIAL CONDITION : 1. PACK1 & 2 SW OFF 2. ADIRU 1,2,3 'NAV' 3. MODE SEL PB 'AUTO' • AMM 21-31-00-710-802 - ONE OUTFLOW VALVE 를 TEST 하는동안 OTHER OUTFLOW VALVE 가 2~3° 정도 움직일수있음. - ADIRU ‘NAV’ ACTION RESULT 1) LDG ELEV SELECTOR ON THE SD (CABIN PRESS PAGE) 를 AUTO 위치에서 - GREEN 'SYS1 (or 2)' - LDG ELEV (WHITE) 시계방향 으로 움직임. - GREEN 'AUTO ... xxxx FT' 에서 ‘MAN ... xxxx FT' 로 바뀜. - 53 - ACTION RESULT ON THE SD (CABIN PRESS PAGE) - LDG ELEV (WHITE) - GREEN 'SYS1 (or 2)' 2) MAN VALVE SEL SW - GREEN ‘MAN ... xxxx FT' 를 AFT 위치에놓고 - GREEN ‘MAN' IND' ON (AFT OUTFLOW VALVE SYMBOL MODE SEL PB를 위쪽) PUSH AND RELEASE - CAB PRESS PNL 에 MAN LEGEND ON NOTE : MAN MODE 에서 CABIN ALT ACCURACY 는 ±1,100 FT 임. ON THE SD (CABIN PRESS PAGE) - AFT OUT FLOW VALVE SYMBOL CLOSE NOTE : OUTFLOW VALVE CLOSE 된다음 70초후에 EWD 4) MAN V/S CTL TOGGLE 에 'CAB PR AFT OFV NOT OPEN' 나타나고 SW 'DN' 위치에 놓고 MASTER CAUT LT 와 SING CHIME 이 들리게 되 HOLD 는데 이상황에서는 무시해도 되고 이러한 WARNING 은 OUTFLOW VALVE 가 FULLY OPEN 되면 사라지게 됨. 5) MAN V/S CTL TOGGLE SW 'UP' 위치에 놓고 - AFT OUTFLOW VALVE SYMBOL OPEN HOLD ON THE SD (CABIN PRESS PAGE) 6) MAN VALVE SEL SW - LDG ELEV (WHITE) - GREEN 'SYS1 (or 2)' - GREEN ‘MAN ... xxxx FT' PUSH 하여 'FWD' - GREEN ‘MAN' IND' ON (FWD OFV SYMBOL 위) 위치로 놓음. - GREEN ‘MAN' IND' OFF (AFT OFV SYMBOL 위) - FWD OUTFLOW VALVE SYMBOL CLOSE NOTE : OUTFLOW VALVE CLOSE 된다음 70초후에 EWD 7) MAN V/S CTL TOGGLE 에 'CAB PR FWD OFV NOT OPEN' 나타나고 MASTER CAUT LT 와 SING CHIME 이 들리게 되 SW 'DN' 위치에 놓고 는데 이상황에서는 무시해도 되고 이러한 HOLD. WARNING 은 OUTFLOW VALVE FULLY OPEN 되면 사라지게됨 8) MAN V/S CTL TOGGLE SW 'UP' 위치에 놓고 - FWD OUTFLOW VALVE SYMBOL OPEN HOLD. 9) MAN V/S CTL TOGGLE ON THE SD (CABIN PRESS PAGE) SW RELEASE 하고 - OUTFLOW VALVE SYMBOL STAY OPEN MAN VALVE SEL SW - LDG ELEV (WHITE) OFF - GREEN 'SYS1 (or 2)' PUSH 하여 'BOTH' 위 - GREEN ‘MAN ... xxxx FT' - GREEN ‘MAN' IND' ON (FWD & AFT OFV SYMBOL 위) 치에 놓을것 ON THE SD (CABIN PRESS PAGE) - LDG ELEV (WHITE) - GREEN ‘MAN ... xxxx FT' 10) MODE SEL PB PUSH - GREEN 'SYS1 (or 2)' - GREEN ‘MAN' OFF - CAB PRESS PNL 에 MAN (WHITE) LEGEND OFF NOTE : 만일 MODE SEL SW ON/OFF 가 1.5 초 이내에 행해진다면 CPC SYSTEM 은 그대로 유지됨(ex : CPC1→CPC1). MODE SEL SW ON/OFF 를 1.5초 이상 시 간을 두고 행하면 CPC SYSTEM CONFIG' 가 바뀌게됨. (ex : CPC1→CPC2) - 54 - ACTION RESULT 11) LDG ELEV SELECTOR ON THE SD (CABIN PRESS PAGE) 를 반시계방향으로 돌 - LDG ELEV (WHITE) 려 AUTO 위치로 - GREEN 'MAN ... xxxx FT' 에서 ‘AUTO ... xxxx FT' 로 놓을것. 바뀜. NOTE : △P8.75~8.95 PSI 에서 SAFETY VALVE OPEN - 55 - ● MMEL 21-43-01 FORWARD CARGO ○ DEACTIVATION OF THE FWD CARGO TRIM AIR VALVE(483HC) (AMM 21-31-00-040-802) 1. 아래 CB OPEN PANEL DESIGNATION FIN LOCCATION 721VU PACK 1 L1 115VAC 1HH1 F02 721VU PACK 1 L2 115VAC 3HH1 K04 721VU ZONE CTL SYS 1 1HK1 R08 721VU PACK 1 L2 28VDC 4HH1 R07 721VU PACK 1 L1 28VDC 2HH1 T08 722VU PACK 2 L2 115VAC 3HH2 E44 722VU PACK 2 L1 115VAC 1HH2 H48 722VU CARGO VENT CTL L1 2HN U43 722VU ZONE CTL SYS 2 1HK2 U42 722VU PACK 2 L2 28VDC 4HH2 U41 722VU PACK 2 L1 28VDC 2HH2 U40 742VU CARGO VENT CTL L2 1HN L72 2. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 3. FWD CARGO 뒤쪽 ACCESS PNL REMOVE (131CX) 4. MANUAL OVERRIDE LEVER (1) 로 TRIM AIR VALVE CLOSE 5. ELEC' CONNECTOR (2) 분리하고 TIE WRAP 사용하여 항공기 STRUCTURE 에 TEMPORARILY ATTACH 해놓을것. 6. CREW 에게 TRIM AIR VALVE (438HC) DEACTIVE 사항 인지시킬것. 7. DEACTIVE 된 TRIM AIR VALVE 의 POSITION 은 SD 에 'XX' 지시함. 8. CB & REMOVED PNL CLOSE 하고 항공기 원상할것. - 56 - 131CX FWD CARGO DOOR (2) (1) H(HOT) : VALVE FULLY OPEN C(COLD) : VALVE FULLY CLOSED XX : VALVE POSITION DATA NOT AVAIL (& DEACTIVATION) - 57 - ● MMEL 21-43-02 BULK CARGO ○ DEACTIVATION OF THE HEATER (AMM 21-43-00-040-801) 1. BULK HOT AIR P/B SW 'OFF' 2. CB OPEN : CARGO VENT CTL L1(2HN) U43, CARGO VENT CTL L2 (1HN) L72 3. REMOVE PNL 151TW 4. ELEC' CONNECTOR (1) 과 (2)를 분리하여 TIE-WRAP 으로 항공기 STRUCTURE 에 ATTACH 할것. 5. CREW 에게 TRIM AIR VALVE (431HC) DEACTIVE 사항 인지시킬것. 151TW 431HC (1) - 58 - (2) ● MMEL 21-51-01 PACK FLOW CONTROL VALVE ○ DEACTIVATION OF THE PACK FLOW CONTROL VALVE (AMM 21-51-00-040-050) 1. 관련 PACK 1(2) SW 'OFF' : 511HB → PACK 1, 512HB → PACK 2 2. OVERHEAD PNL 의 RESET SW/PC1(2) OPEN 3. REMOVE ACCESS PNL : 511HB → 193BB, 512HB → 192JB 4. FLOW CONTROL VALVE POSITION 1 의 LOCKING SCREW ⑨ 를 REMOVE 하여 POSITION 2 에 장착. 5. 관련 RESET SW/PC1(2) CLOSE 하고 ACCESS PNL 장착 6. IN FLIGHT 중에 EWD 에 ‘PACK 1(2) OFF’ MSG 와 MAINT STS MSG 로 ‘CAB TEMP’ MSG DISPLAY 됨. - 59 - - 60 - ● MMEL 21-52-01 AIR CONDITIONING PACK ○ DEACTIVATION OF THE AIR CONDITIONING PACK (AMM 21-53-00-040-803) 1. INOP' 된 PACK 1(2) PB SW 'OFF' 2. SD BLEED PAGE 를 통하여 관련 FLOW CONTROL V/V 가 CLOSE 되었나 확인. 3. HP GROUND CONNETION 이나 APU 를 사용하여 ACTIVE PACK 의 DISCHARGE TEMP NOMAL 상태확인. (ACTIVE PACK 에 대해서는 WARNING 이 없어야 한다.) 4. IN FLIGHT 중에 EWD 에 ‘AIR PACK 1(2) REGUL FAULT' 와 'AIR PACK 1(2) OFF' MSG 나타나게 됨. ○ DEACTIVATION 후 추가조건 1) DEFER INTERVAL 'C' 일 경우 FLIGHT ALTITUDE 가 35,400FT 로 제한됨. 2) ACTIVE PACK 의 PACK CONTROLLER 의 BOTH CANNEL 이 모두 NORMAL 이어야함. 3) INOP' 된 PACK PB SW 'OFF' 후 SD BLEED PAGE 와 CAB PRESS PAGE 에 FLOW CONTROL VALVE CLOSE 되었나 확인할것. 4) ACTIVE PACK 마저도 FAIL 시 FLT WITHOUT CABIN PRESS' (FCOM 2.04.20)의 FUEL CONSUMED 적용할것.(ONLY CREW 용) ○ FWD CRG COOLING & HEATING 은 이뤄지지않기 때문에 동식물 (LIVESTOCK) 을 운반시는 LIVESTOCK TRANSPORTATION MANUAL을 참조할것. FOR FLIGHT PLAN, MCQ 전화통보 + SYS 입력 ○ MMEL 21-52-01-C) 1) 해당 PACK 은 AIRBORN 이나 TAT 12℃ 이하될때까지 작동금지 2) 해당 PACK OUTLET TEMP IND은 ECAM BLD PAGE 에 정상작동되어야함. - 61 - BY-PASS VALVE FULLY CLOSE BY-PASS VALVE NOT FULLY CLOSE BY-PASS VALVE POSITION DATA NOT AVAIL ※ PACK BY-PASS MODE : ACM FAILURE FLOW CONTROL VALVE → PRIMARY HEAT EXTCHANGER → CHECK VALVE → MAIN HEAT EXCHANGER → BY PASS VALVE 를 통한 ONLY HEAT EXCHANGER 에 의존한 COOLING 방식으로 PACK TEMP CONTROL 은 RAM AIR MODULATION 과 TCV REG'에 의하 고 SPLIT DUCT EXTRACT WATER 는 BY PASS VALVE 작동하는 동안 축적되어 WATER EXTRACTOR 와 WATER INJECTOR 에 보내진다. - 62 - INOP 된 PACK SW 'OFF' EWD : SD : PACK DISCAHRGE TEMP MASTER CAUT + SINGLE CHIME : - 63 - ● MMEL 21-53-02 BYPASS VALVE ○ DEACTIVATION OF THE BYPASS VALVE (AMM 21-53-00-040-801) 1. 아래 CB OPEN PANEL DESIGNATION FIN LOCCATION FOR 521HH2 721VU PACK 1 L1 115VAC 1HH1 F02 721VU PACK 1 L2 115VAC 3HH1 K04 721VU PACK 1 L2 28VDC 4HH1 R07 721VU PACK 1 L1 28VDC 2HH1 T08 FOR 522HH2 722VU PACK 2 L2 115VAC 3HH2 E44 722VU PACK 2 L1 115VAC 1HH2 H48 722VU PACK 2 L2 28VDC 4HH2 U41 722VU PACK 2 L1 28VDC 2HH2 U40 2. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 3. REMOVE PNL : 521HH2 → 193DB, 522HH2 → 192PB 4. ELEC' CONNECTOR (1) 분리하여 TIE-WRAP 으로 항공기 STRUCTURE 에 ATTACH 할것. 5. MANUAL LEVER (2)를 'CLOSED' POSITION 으로 위치시킬것. 6. EWD 에 MAINT STS MSG 'CAB TEMP' 나타나게됨. 7. CB 와 REMOVE 된 PNL 장착후 항공기 원상할것. - 64 - 192PB 1 193DB 2 - 65 - ● MMEL 21-53-04 AIR CONDITIONING RAM AIR INLET/OUTLET FLAP (DOOR) ○ DEACTIVATION OF THE RAM-AIR INLET ACTUATOR (AMM 21-53-00-040-804) 1. RAM-AIR INLET DIM 측정 - RAM AIR INLET DIM 'A' 를 측정하여 31mm 이상이면 DEACTIVATION 이 필요 없고 31mm 이하이면 DEACTIVATION 시켜라. (DIM 'A' 31mm 는 FULL OPEN 의 11% 에 해 당됨.) 2. 아래 CB OPEN PANEL DESIGNATION FOR 533HH 721VU PACK 1 L1 115VAC 721VU PACK 1 L2 115VAC 721VU PACK 1 L2 28VDC 721VU PACK 1 L1 28VDC FOR 534HH 722VU PACK 2 L2 115VAC 722VU PACK 2 L1 115VAC 722VU PACK 2 L2 28VDC 722VU PACK 2 L1 28VDC FIN LOCCATION 1HH1 3HH1 4HH1 2HH1 F02 K04 R07 T08 3HH2 1HH2 4HH2 2HH2 E44 H48 U41 U40 3. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 4. REMOVE PNL : 533HH2 → 191FB, 534HH → 193BB 5. ELEC' CONNECTOR 분리하고 항공기 STRUCTURE 에 TIE-WRAP 으로 ATTACH 할것. 6. CB OPEN : MLG OUTLET 28V 6LL (P37) 7. ELEC' CONNECTOR 8LL(9LL) 의 '1(+)' 을 ACTUAOTR ELEC' CONNECTOR PIN 'U' 에 연결하고 'N(-)'을 PIN 'J' 에 연결하라. (CF22 GAUGE ELEC WIRE 로 연결) 8. CB CLOSE : MLG OUTLET 28V 6LL (P37) - RAM AIR INLET 의 INTERNAL PWR BRK 는 RELEASE 상태로 됨. 9. INLET DOOR를 손으로 밀어 GAP(A) 이 112~118mm 되게 하라 10. CB OPEN : MLG OUTLET 28V 6LL (P37) - 66 - 11. ACTUATOR 와 ELEC CONNECTOR (8LL/9LL)사이 WIRE 를 제거하라. 12. CB CLOSE : MLG OUTLET 28V 6LL (P37) 13. INLET FLAP 이 MANUAL 로 OPEN 안되면 ACTUATOR 를 교환 또는 MEL 21-52-01 을 적용하라. 14. 앞서 OPEN 했던 CB & PNL CLOSE 하고 항공기 원상하라. 15. SD의 MAINT SATUS ‘CAB TEMP’ 나타나게됨. ※ 반복적인 PACK OVHT 결함 때문에 TSM 권고에 의해 DEACTIVATION 시킬때에는 RAM AIR INLET DIM 'A' 가 112mm 이상되어야하고 112mm 이하일때에는 DEACTIVE 절차를 수행하여 야 한다. ※ 112mm IS EQUIVALENT TO 50% OF THE OPEN POSITION 533HH (534HH) 193BB 191FB (2) - 67 - ACTUATOR DIM 'A' (31mm 이하일때 DEACTIVE 할것.) WHEEL WELL 의 CONNECTOR ○ DEACTIVATION OF THE RAM-AIR OUTLET ACTUATOR (AMM 21-53-00-040-806) 1. 아래 CB OPEN PANEL DESIGNATION FOR 535HH 721VU PACK 1 L1 115VAC 721VU PACK 1 L2 115VAC 721VU PACK 1 L2 28VDC 721VU PACK 1 L1 28VDC FOR 536HH 722VU PACK 2 L2 115VAC 722VU PACK 2 L1 115VAC 722VU PACK 2 L2 28VDC 722VU PACK 2 L1 28VDC FIN LOCATION 1HH1 3HH1 4HH1 2HH1 F02 K04 R07 T08 3HH2 1HH2 4HH2 2HH2 E44 H48 U41 U40 2. APU BLEED, ENG BLEED, PACK 1(2) PB 'OFF' 3. DIM 'A' 를 측정하여 36mm 이상이면 NO DEACTIVATION. 36mm 이하이면 DEACTIVATION 수행 (※ 36mm IS EQUIVALENT TO 11% OF THE FULL OPEN POSITION) 4. REMOVE PNL : 535HH(#1 PACK) → 196GB, 536HH(#2 PACK) → 196EB 5. ELEC' CONNECTOR (8) 분리하여 항공기 STRUCTURE 에 TIE-WRAP 으로 ATTACH 하라. 6. ROD END (2) 를 분리하여 길이를 ADJUST 하라. 7. DIM 'A' 가 36mm 이상인가 확인하라. 8. 앞서 OPEN 했던 CB & PNL CLOSE 하고 항공기 원상하라. 9. SD의 MAINT SATUS ‘CAB TEMP’ 나타나게됨. - 68 - (2) (8) - 69 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA22) ● MMEL 22-30-01 AUTOTHRUST FUNCTION ○ AUTOTHRUST FUNCTION-CHECK OF ALL THROTTLE CONTROL UNIT (AMM 22-30-00-040-802) 1. THROTTLE CONTROL LEVER 를 IDLE STOP (‘0’ GATE) 2. ENG FADEC GND PWR PB & ENG/MASTER SW 'OFF' 3. 아래 CB 는 CLOSE 되어있어야함. PANEL 722VU 722VU 722VU 722VU 742VU 742VU 742VU 742VU DESIGNATION FADEC B ENG 1 FADEC B ENG 2 FMGEC 2 FCU C FCU A+B FMGEC 1 FADEC A ENG 2 FADEC A ENG 1 FIN 13KS1 13KS2 5CA2 8CA2 8CA1 5CA1 12KS1 12KS1 LOCATION D44 K49 R43 R42 E69 M75 Q74 Q73 4. CHECK OF ALL THROTTLE CONTROL UNITS EEC1 과 2 의 CHANNEL A 에 대한 TEST 임. CHANNEL B 는 괄호 안의 내용 수행할것. NOTE : CHANNEL A TEST 동안 SYSTEM 은 자동으로 N1 RATED MODE 로 됨. TEST 동안의 관련 WARNING 은 무시할것. ACTION RESULT 1. 722VU(742VU) 의 CB D44, K49 (Q74, Q73) OPEN - ON LEGENDS COME ON. 2. ENG FADEC GND PWR 1 AND 2 PB PUSH 3. ENG 1 과 2 의 THROTTLE LEVER 를 TO/GA GATE 까지 움직여라. 4. ENG 1 과 2 의 THROTTLE LEVER 를 IDLE GATE 까지 움직여라. - EWD 에 ENG PARAMETER 값이 나타나게됨. - ON THE EWD, FOR THE RELATED ENGINE, THE SMALL CYAN CIRCLE FOLLOWS THE THROTTLE POSITION. - 70 - 5. ENG FADEC GND PWR 1 과 2 PB THE ON LEGENDS GO OFF. 을 RELEASE 하라. 6. 722VU(742VU) 의 CB D44, K49 (Q74, Q73) CLOSE 7. DO THE TEST AGAIN (STEP 1 THROUGH STEP 5 WITH INFORMATION BETWEEN PARENTHESES). ● MMEL 22-30-02 AUTOTHRUST INSTINCTIVE DISCONNECT PB ○ AUTOTHRUST DISCONNECTION - DISCONNECTION CHECK (AMM 22-30-00-040-801) 1. ADIRU Align, ENG FADEC GND PWR PB ON 2. THROTTLE CONTROL LEVER 가 IDLE STOP 에 있는지 확인. 3. FCU 의 FD PB 을 PUSH 하여 FD DISENGAGE (the green legends are off) 4. 관련 CB 는 모두 CLOSE 되어 있어야함. ACTION RESULT 1. OVER HEAD RESET PNL 의 FMGEC1 (2) OPEN ← 한번씩 번갈아가면서 아래사항 수행 FCU 의 A/THR PB 에 GREEN LEGEND ON 2. FCU 의 A/THR PB PUSH - PFD 에 GREEN SPEED MSG 와 WHITE A/THR MSG 나타남. FCU 의 A/THR PB 에 GREEN LEGEND OFF - PFD 에 GREEN SPEED MSG 와 WHITE 3. RH THROTTLE LEVER A/THR MSG 사라짐. - A/THR INSTINCTIVE DISCONNECT - SD MEMO ZONE 에 A/THR OFF MSG 일시 PB PUSH (15초이내) 적으로 나타남 (약 8초) - SINGLE CHIME 울림. FCU 의 A/THR PB 에 GREEN LEGEND ON 4. FCU 의 A/THR PB PUSH - PFD 에 GREEN SPEED MSG 와 WHITE A/THR MSG 나타남. 5. LH THROTTLE LEVER - A/THR INSTINCTIVE DISCONNECT 3항과 결과 동일 PB PUSH (15초이내) - 71 - ACTION 6. FCU 의 A/THR PB PUSH 7. FCU 의 A/THR PB RELEASE 8. FMGEC RESET SW 1 (2) CLOSE RESULT FCU 의 A/THR PB 에 GREEN LEGEND ON - PFD 에 GREEN SPEED MSG 와 WHITE A/THR MSG 나타남. FCU 의 A/THR PB 에 GREEN LEGEND OFF - PFD 에 GREEN SPEED MSG 와 WHITE A/THR MSG 사라짐. - EWD 에 AUTO FLT A/THR OFF MSG 나타남 - SINGLE CHIME 울림. ● MMEL 22-83-01 FMGEC ○ DEACTIVATION OF THE FMGEC (AMM 22-83-00-040-801) 1. CB OPEN : FMGEC1 5CA1 (M75) 또는 FMGEC2 5CA2 (R43) 2. GLARESHIELD 의 FCU 에 FMGEC DEACTIVE 되었다는 PLACARD 부착 (CREW INFORM 요함). - 72 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA23) ● MMEL 23-12-01 VHF SYSTEM ○ DEACTIVATION OF THE ACARS MANAGEMENT UNIT (or ACARS COMMUNICATIONS MANAGEMENT UNIT) (AMM 23-24-00-040-801) EFF ON A/C 001~050, 101~102 ◆ CB OPEN : ACARS 2RB (B01) ※ SIDE STICK RADIO SELECTOR 가 CLOSE POSITION (TRANSMIITING POS') 에서 FAIL 시 (M) 사항 적용 ● MMEL 23-51-07 SIDE STICK RADIO SELECTOR ○ DEACTIVATION OF THE RADIO PTT SWITCH (11RN, 12RN) (AMM 23-51-00-040-801) 1. CB OPEN PANEL DESIGNATION ON A/C 001-058, 101-199 742VU ACP F/O 742VU ACP CAPT ON A/C 059-099 742VU ACP F/O 3&4 OCC BITE 742VU ACP CAPT AVNCS SELCAL - 73 - FIN LOCATION 4RN2 4RN1 A72 A71 4RN2 4RN1 A72 A71 2. RADIO PTT SWITCH DISENGAGEMENT - REMOVE THE SCREW (1) & COVER PLATE (2) - REMOVE THE BLANKING PLUG (11), NUT (10), WASHER (9), TRIGGER (8) - REMOVE THE NUT (7), WASHER (6), SWITCH (4) WITH THE LOCK PLATE (3) 3. POWER SUPPLY WIRE (5)을 CUT 하고 잘려진 WIRE 끝에 END CAP 을 씌어라. 4. REMOVE 했던 RADIO PTT SWITCH 관련 PARTS INSTALL 5. CB CLOSE 1 2 11 10 9 8 3 7 4 WIRE CUT 5 6 6. EWD 에 ‘HF1 (2) EMITTING’, ‘VHF1 (2) (3) EMITTING', 'PRIM 1 FAULT', 'PRIM 2 FAULT' 가 DISPLAY 되지 않아야됨. - 74 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA24) ● MMEL 24-22-01 AC MAIN GENERATION (IDG, GCU, LINE CONTACTOR) ○ CHECK OF THE AC MAIN GENERATION AND APU OIL CONSUMPTION (AMM 24-22-00-040-801-A) 1) APU는 FLT 구간내내 작동시켜 ELEC PWR 를 공급해야함. 2) 모든 BUS 에는 PWR 가 공급 되어야함. 3) IND 은 정상작동 해야함 4) ELEC IDG1(2) MINOR FAULT 가 없어야 함. 5) FUEL APU AFT PUMP FAULT 가 없어야함. 6) OPER' TEST AC ESS' GENERATION AUTO SWITCHING (AMM 24-22-00-710-053) 1. ECAM AC PAGE DISPLAY : AC BUS #1 과 AC ESS BUS 로 GREEN BAR 연결됨. 2. CB OPEN (721VU 41XN/B02) : ECAM 변화없음. 3. CB OPEN (721VU 5XC/M14) : ELEC AC ESS BUS ALTN MSG "ON" AC #1에서 AC ESS로 가는 GREEN BAR 사라짐 AC #2에서 AC ESS로 GREEN BAR 연결됨. 4. ECAM DC PAGE DISPLAY : ESS TR에서 EC ESS 로 PWR 공급 - 75 - 5. ECAM AC PAGE DISPLAY 6. CB CLS (721VU 5XC/M14) : ECAM 변화없음 7. CB CLS (721VU 41XN/B02): ECAM AC ESS BUS 공급 PWR 가 AC #2 에서 AC #1 으로 변함 7) OPER' TEST AFT FUEL FEED PUMP SHEDDING IN LAND RECOVERY CONFIGURATION (AMM 28-22-00-710-807) 1. L1,L2,R1,R2 FUEL PUMP "OFF"하라. 2. FCMC INPUT PARAMETER에 접근하라 (SPECIFIC DATA→INPUT PARAMETER) 3. ALL CB CLS 상태에서 APU FWD PUMP CB (2QC/B09) OPEN 하라. 4. FUEL PAGE DISPLAY : SD TRIM TK ISOL SYMBOL IN CLS POS 5. TRIM TK INLET V/V POS을 확인하라(CLOSED POS) • FCMC1(2) INPUT PARAMETER 9/10 에서 F2="0", F4="1" 지시, G5="1" (AFT APU PUMP NOT OPER') NOTE : 만일 TT INLET V/V AND/OR TT ISOL V/V 가 NOT CLS일때 GRD FUEL SVC PNL(990VU)에서 - MODE SEL SW "REFUEL" SET - TT REFUEL V/V SW "SHUT" SET - MODE SEL SW "OFF" SET 만일 G5 가 APU MASTER SW "OFF"해도 “0”지시하면 PNL 312AR OPEN 하여 작동상태를 손으로 확인하라. 6. OVHD PNL, MASTER SW PUSH IN • SD 에 APU IND 은 WHITE 로 남고 APU TRIANGLE SYMBOL 은 WHITE→GREEN 으로 INPUT PARAMETER 9/10에서 G5="0" 으로 변화할때까지 기다려라 7. OVHD PNL, LAND RECOVERY SW "PUSH IN" • FUEL PAGE APU IND WHITE → AMBER • APU TRIANGLE SYMBOL 사라짐 • INPUT PARAMETER 9/10에 G5="1"지시 NOTE : G5="1"이 아니면 IND을 무시하고 AFT APU PUMP 작동을 손으로 만져 CHECK 하라. 이것은 APU FUEL LINE 의 PRESS' 로 MONITOR 하기 때문임 8. LAND RECOVERY SW "RELEASE OUT" • FUEL PAGE APU IND AMBER → WHITE • APU TRIANGLE SYMBOL "GREEN" 9. RELEASE THE APU MASTER SW • SD FUEL PAGE APU IND STAY "WHITE" • TRIANGLE SYMBOL GREEN → WHITE • INPUT PARAMETER 9/10에 G5="1" 지시 NOTE : AFT APU FUEL PUMP 의 OPER'후 G5="0"에서 “1”로 변화를 보여도 몇분을 기 다려라. 이것은 TT FUEL XFR LINE 과 APU FUEL LINE 속 잔여 PRESS' 때문임 8) INTENDED FLIGHT 를 위한 APU OIL 이 충분한지 확인. 9) APU GENERATOR SCAV' OIL FILTER 와 DRAIN PLUG 에 DEBRIS 가 나오는지확인. 10) APU GENERATOR SEAL PLATE 가 올바르게 장착되어있는지 확인. - 76 - ※ 한개의 IDG 에대해서 FAULT(ELEC IDG 1(2) OIL SYS FAULT) 가 다음과 같은 조건이 있는 경우 DISPATCH 가능함. MEL 적용후 첫 번째 FLIGHT 전 또는 하루한번씩 아래사항 CHECK (ER OPER 시 매 FLIGHT 전 CHECK) 1) CMS FAILURE MSG 확인하여 - EXCESSIVE △T 또는 OIL COOLER 의 DMGE 여부, FILTER CLOGGING 있는지 CHECK 2) 결함 IDG 에 대해 SIGHT GLASS 통해 OIL LEVEL 이 정상인지 확인 ● MMEL 24-22-02 a) IDG OIL CIRCUIT (BOTH OPERATIVE) ○ CHECK OF THE IDG MAINTENANCE CONDITION (AMM 24-22-00-040-802) CAUTION : IDG DISCONNECTED MODE에서 50시간 이상 작동하였는지 확인후 초과시 IDG REMOVE 하라. ON THE MCDU : PRF PRINT하여 - IDG 1(2) COOLER - IDG 1(2) (E1(2)-4000XU) OIL TEMP/GCU1(2) (1XU1(2)) - IDG 1(2) (E1(2)-4000XU) CLOG FLTR MSG 가 있나 CHECK 하고 없다면 EPGS CROUND REPORT 를 확인하여 상기 MSG 가 없 나 CHECK 하라. 없다면 IDG OIL LEVEL 이 정상인가 확인하라 - 77 - ● MMEL 24-22-02 b) IDG OIL CIRCUIT (ONE INOPERATIVE) ○ DRAINING OF THE OIL FROM THE IDG AFTER DETECTION OF OIL LEAKS (AMM 24-22-00-040-804) 1. 결함있는 IDG 에 대해서 IDG DISCONNECT ACTION 1) ENG IDLE RUN 후 - GUARD 제끼고 IDG1(2) PB PUSH RESULT - GEN PB 에 ‘FAULT' LT ON - IDG PB 에 'OFF' LT ON ON THE SD (ELEC/AC PAGE) - LOAD, VOLTAGE, FREQUENCY 가 ZERO 됨. - AMBER 'DISC' MSG 나타남 ON THE EWD - 'IDG1(2) DISCONNECT' MSG 나타남. 2) GEN PB RELEASE - GEN PB 에 ‘FAULT' LT 없어지고 ’OFF' LT ON 3) IDG DISCONNECT 사항 LOG BOOK 기록 4) ENG STOP 2. ENG COWL OPEN 후 IDG OIL LEAK INSPECTION. - IDG FITTING : PRESSURE FILL PORT, OVER FLOW DRAIN PORT, CASE DRAIN, OIL-IN AND OIL-OUT PORT - TUBING - IDG OIL COOLER : OIL-IN AND OIL-OUT PORT, DRAIN PLUG, COOLER BODY 3. 만약 OIL LEAK 가 발생시 IDG OIL FULL DRAIN (AMM 12-13-24-680-804) 후 OIL LEAK 하는 POSTION 을 LOG 에 기록할것. - 78 - 1) MECHANICAL FAILURE 가없어야하며 2) APU GEN PB OFF 되어야함. ● MMEL 24-23-02 b) APU GEN OFF ○ Check of the APU-Generator Maintenance Condition (TASK 24-23-00-040-803) 1. MCDU 의 PFR PRINT 하여 다음 MSG 가 없어야 함. • GEN APU (8XS) PMG / GAPCU (40XG) • GEN APU (8XS) PMG / GAPCU (40XG) / ECB (59KD) • GAPCU (40XG) / GEN APU (8XS) • GEN APU (8XS) PMG • GCU APU (1XS) / GEN APU (8XS) / APU AUTO SHUT DN • GENERATOR (8XS) / OIL PUMP MODULE (5100KT9) 2. PFR 에 상기 MSG 가없을 경우 EPGS GROUND REPORT 도 확인할것. ● MMEL 24-23-02 b) APU GEN OFF ○ DEACTIVATION OF THE APU GENERATOR BY INSTALLATION OF THE SUBSTITUTION KIT (AMM 24-23-00-040-801) NOTE ; 이 DEACTIVATION 은 다음과 같은 MSG 가 DISPLAY 됐을 경우 적용됨. EWD : APU GEN FAULT CMS : GEN APU (8XS) PMG / GAPCU (40XG) or GEN APU (8XS) PMG / GAPCU (40XG) / ECB (59KD) or GAPCU (40XG) / GEN APU (8XS) or GEN APU (8XS) PMG or GCU APU (1XS)/GEN APU (8XS)/APU AUTO SHUT DN or GENERATOR (8XS) / OIL PUMP MODULE (5100KT9) NOTE : APU GENERATOR REMOVE 되었을때의 FLIGHT 에 관련된 WIEGHT IMPACT 와 BLANCE 등의 고려하여 MEL REQUIREMENT 적용할것. - 79 - 1. CB OPEN 2. APU GENEARATOR REMOVE (AMM 24-23-51-000-801) 3. GENERATOR 가 장착되었던 부분 INSP‘ & CLEAN 후 NUT (4) REMOVE 4. GENARATOR PAD 와 STUD 그리고 SEAL PLATE 등 INSP. 5. 아래 FIG 참고후 MM 절차수행. FLIGTH INST WITHOUT GEN SUBSITUTION KIT : G4907002500251 (IPC 49-11-04-05) TQ : 71~88 in.lb PN : M83248-1-261 IPC 24-23-51-01-100 DOWL PIN 이 GEN PAD 의 HOLE 잘 끼워지게 INST 6. CB CLOSE : 1KA, 1KD, 2KD, 3KD, 35KD, 58KD, 1KT, 1WF, 3WF, 4WF 7. APU OPERATION 후 LEAK CHECK. (OIL QTY 확인후 보급) - 80 - ● MMEL 24-26-01 b) AUTO AND MAN LOAD SHED SYS INOP ○ DEACTIVATION OF THE GALLEY SUPPLY SYSTEM (AMM 24-26-00-040-801) 1. 다음 CB OPEN 후 SAFETY CLIP 장착 PANEL 721VU 722VU 722VU DESIGNATION GALLEY SYS 1 GALLEY SHED GALLEY SYS 2 2. GALLEY EQUIPMENT 가 작동하지 않는지 확인. FIN 1MC 3XA 2MC ● MMEL 24-26-01 c) MAN LOAD SHED SYS INOP LOCATION T10 N44 S39 ○ OPERATION TEST OF COMMERCIAL LOAD SHEDDING (AMM 24-26-00-040-802). 1. AMM 24-51-00-710-801 (OPERATION TEST OF COMMERCIAL LOAD SHEDDING) 수행 2. COMMERCIAL PB, GALLEY PB PUSHED (OFF LT OFF) 3. FAP 에서 CTR, AISLE, WDO SW PUSHED (CABIN LT ON) 4. FWD, MID, AFT GALLEY 의 GALLEY UNITS 가 작동하는지 확인. ACTION 1) COMMERCIAL PB RELEASE 2) COMMERCIAL PB PUSH RESULT - COMMERCIAL PB 에 'OFF' LT ON ON THE SD - ‘COMMERCIAL OFF’ IND 나타남. IN THE CABIN - CENTER, AISLE, WINDOW LT 들이 OFF 됨. FWD, MID, AFT GALLEY - GALLEY UNIT 들이 작동안함. - COMMERCIAL PB 에 'OFF' LT OFF ON THE SD - ‘COMMERCIAL OFF’ IND 사라짐 IN THE CABIN - CENTER, AISLE, WINDOW LT 들이 ON 됨. FWD, MID, AFT GALLEY - GALLEY UNIT 들이 작동함. - 81 - ● MMEL 24-27-01-E)-a) AC GENERATION GALLEY FAULT LIGHT ○ CHECK OF THE AUTOMATIC GALLEY SHEDDING (AMM 24-27-00-040-801) 1. GALLEY PB, COMMERCIAL PB, BATT SW, GEN1(2) PB, APU GEN PB PUSH ('OFF' LT OFF). 2. APU BATT 이용하여 APU STARTING 3. CHECK OF THE AUTO GALLEY SHEDDING ACTION 1) ENG1(2) STARTING 2) APU GEN PB RELEASE RESULT - APU GEN PB ‘OFF' LT ON ON THE SD - 'GALLEY PATIALLY SHED' IND 나타남. ON THE 717VU - RCCB1(11MC) 앞면 VISUAL IND → OPEN - RCCB2(111MC) 앞면 VISUAL IND → CLOSED ON THE 715VU - RCCB3,4,6(12MC, 23MC, 223MC) 앞면 VISUAL IND → OPEN ON THE 718VU - RCCB5(24MC) 앞면 VISUAL IND → OPEN - 82 - 3) APU GEN PB PUSH 4) STOP THE ENG - APU GEN PB ‘OFF' LT OFF ON THE SD - 'GALLEY PATIALLY SHED' IND 사라짐. ON THE 717VU - RCCB1,2(11MC,111MC) 앞면 VISUAL IND → CLOSED ON THE 715VU - RCCB3,4,6(12MC, 23MC, 223MC) 앞면 VISUAL IND → CLOSED ON THE 718VU - RCCB5(24MC) 앞면 VISUAL IND → CLOSED ● MMEL 24-27-01-J)-b) AC GENERATION ECAM ELEC AC PAGE OTHERS ○ CHECK OF THE AUTOMATIC GALLEY SHEDDING (AMM 24-27-00-040-802) 1. GALLEY PB, COMMERCIAL PB, BATT SW, APU GEN PB PUSH ('OFF' LT OFF). 2. GEN1 과 GEN2 PB RELEASE ('OFF' LT ON) 8) ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 3. APU BATT 이용하여 APU STARTING 4. CHECK OF THE AUTO GALLEY SHEDDING (앞선 PAGE FIG‘ 참조) - 83 - ACTION 1) GEN1(2) PB PUSH 2) ENG1(2) STARTING 3) APU GEN PB RELEASE 3) APU GEN PB PUSH 4) STOP THE ENG RESULT - GEN PB 에 'FAULT' LT ON - APU GEN PB ‘OFF' LT ON ON THE SD - 'GALLEY PATIALLY SHED' IND 나타남. ON THE 717VU - RCCB1(11MC) 앞면 VISUAL IND → OPEN - RCCB2(111MC) 앞면 VISUAL IND → CLOSED ON THE 715VU - RCCB3,4,6(12MC, 23MC, 223MC) 앞면 VISUAL IND → OPEN ON THE 718VU - RCCB5(24MC) 앞면 VISUAL IND → OPEN - APU GEN PB ‘OFF' LT OFF ON THE SD - 'GALLEY PATIALLY SHED' IND 사라짐. ON THE 717VU - RCCB1,2(11MC,111MC) 앞면 VISUAL IND → CLOSED ON THE 715VU - RCCB3,4,6(12MC, 23MC, 223MC) 앞면 VISUAL IND → CLOSED ON THE 718VU - RCCB5(24MC) 앞면 VISUAL IND → CLOSED ● MMEL 24-29-01 ECMU ○ CHECK OF THE AC AND DC ELECTRICAL TRANSFER FUNCTION (AMM 24-29-00-040-801) NOTE : TEST 전에 FLIGHT PLAN INITIALIZE 시키지 말것. 왜냐하면, ENG START 3분후에 는 CMS를 통한 ECMU TEST 는 되지않음. 1. MCDU SYSTEM REPORT/TEST ELEC: AC page → < ECMU1(2) PUSH → < LAST LEG/GND REPORT PUSH - 만약 CLASS1 AND/OR CLASS2 MSG 'ECMU1(2) (1XM1(2)) 28VDC HOT BUS SUPPLY' 가 NOT DISPLAY 경우 - 84 - ACTION 1) ENG1(2) STARTING RESULT - GEN1(2) PB ‘OFF' LT OFF ON THE SD ELEC AC PAGE - ENG1 STARTING 경우 • GEN1 이 AC1 과 AC ESS BUS 에 PWR 공급 2) GEN1(2) PB PUSH • APU GEN 가 AC2 BUS 에 PWR 공급 - ENG2 STARTING 경우 • GEN2 가 AC2 BUS 에 PWR 공급 • APU GEN 가 AC1 과 AC ESS BUS 에 PWR 공급 3) ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 - APU GEN PB ‘OFF' LT ON 4) APU GEN PB ON THE SD ELEC AC PAGE RELEASE - GEN1(2) 이 ALL NETWORK 에 PWR 공급 5) ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 - BUS TIE PB ‘OFF' LT ON ON THE SD ELEC AC PAGE - ENG1 STARTING 경우 • GEN1 : AC1 과 AC ESS BUS 에 PWR 공급. AC2 BUS 에는 PWR 공급되지 않음. - ENG2 STARTING 경우 6) BUS TIE PB • GEN2 : AC2 와 AC ESS BUS 에 PWR 공급. RELEASE AC1 BUS 에는 PWR 공급되지 않음. ON THE SD ELEC DC PAGE - TR1(2) 이 DC1, DC BAT, DC2 BUS 에 PWR 공급 - ESS TR 이 DC ESS BUS 에 PWR 공급 - TR2(1) LOST - BUS TIE PB ‘OFF' LT OFF 7) BUS TIE PB - GEN1(2) 이 ALL NETWORK 에 PWR 공급 PUSH - ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 - APU GEN PB ‘OFF' LT OFF ON THE SD ELEC AC PAGE - ENG1 STARTING 경우 8) APU GEN PB • GEN1 이 AC1 과 AC ESS BUS 에 PWR 공급 PUSH • APU GEN 가 AC2 BUS 에 PWR 공급 - ENG2 STARTING 경우 • GEN2 가 AC2 BUS 에 PWR 공급 • APU GEN 가 AC1 과 AC ESS BUS 에 PWR 공급 9) ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 - GEN1(2) PB ‘OFF' LT ON 10) GEN1(2) PB ON THE SD ELEC AC PAGE RELEASE - APU GEN 가 ALL NETWORK 에 PWR 공급 11) ELEC DC PAGE 확인하여 NORMAL CONFIGURATION 인지 확인 - 만약 CLASS1 AND/OR CLASS2 MSG 'ECMU1(2) (1XM1(2)) 28VDC HOT BUS SUPPLY' 가 DISPLAY 된 경우 - 85 - ACTION RESULT 1) MCDU RETURN KEY PUSH → < ECMU 1(2) 2) ENG1(2) STARTING 3) GEN1(2) PB PUSH - GEN1(2) PB ‘OFF' LT OFF 4) EXTERNAL PWR 분리 확인 5) MCDU TEST KEY PUSH 6) 'ECMU1(2) (1XM1(2)) 28VDC HOT BUS SUPPLY' 이 NOT DISPLAY 되어야함. 7) 앞선 TEST 절차 2) 항~11) 항 수행 ● MMEL 24-53-01-A) CBMU ○ DEACTIVATION OF THE CIRCUIT BREAKER MONITORING UNIT (CBMU) (AMM 24-53-00-040-801) 1. ALL CB PANEL 의 CB OPEN 된 것 없나 확인. 2. CB OPEN : CBMU 2XD (X05) 3. EWD 'C/B MONITOR FAULT' DISPLAY. 4. SD CB PAGE 'NOT AVAIL' DISPLAY. - 86 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA25) ● MMEL 25-11-01-B) COCKPIT SEAT ELEC CONTROL ○ DEACTIVATION OF THE INOPERATIVE ADJUSTMENT SYSTEM OF THE CAPT (F/O) SEAT (ELECTRICAL CONTROL) (AMM 25-11-00-040-801) - CB OPEN : SEAT CAPT 1MS1 (A05), SEAT F/O 1MS2 (B39) ● MMEL 25-13-01 PILOT SLIDING TABLE ○ DEACTIVATION OF THE CAPTAIN AND/OR FIRST OFFICER SLIDING-TABLES (AMM 25-13-00-040-801) 1. SLIDING TABLE REMOVE (AMM 25-13-14-000-804) 2. TABLE 당기고 SCREW (2) REMOVE 하여 SLDING TABLE ASSY (3) REMOVE. (1) (2) (3) - 87 - ● MMEL 25-13-02 PILOT RETRACTABLE FOOT REST ○ DEACTIVATION OF THE CAPTAIN AND/OR FIRST OFFICER RETRACTABLE FOOT-RESTS (AMM 25-13-00-040-802) 1. RETRACTALBE FOOT REST REMOVE (AMM 25-13-14-000-803) 2. COTTER PIN (6), NUT (5), WASHER (4) REMOVE. 3. FOOT REST 잡고 HINGE PIN (1), WASHER (2) REMOVE. (6) (5) (4) (1) (2) (3) (3) - 88 - - 89 - ※ SEAT POSITION, BELT 또는 HANESS 의 MISSING 은 SEAT INOP 으로 간주됨 (REMOVE 또는 STOW POSTION 으로 SECURE 시킴) 1) INOP 된 SEAT 에 ASSIGN 된 CABIN 승무원은 EXIT DOOR 에서 가장 가까운 곳의 PAX SEAT 에 자리하고 2) CABIN 승무원에 의해서 쓰이는 PAX SEAT 는 적절한 PLACARD 부착하며 3) CABIN 승무원은 INOP 된 CABIN ATTENDANT SEAT 에서와 동일하게 EMER' QUIPMENT 와 EXIT' DOOR 에 도달할수있어야함. ● MMEL 25-22-01 PILOT RETRACTABLE FOOT REST ○ DEACTIVATION OF A DEFECTIVE CABIN ATTENDANT SEAT (AMM 25-22-040-801) - SEAT 를 SAFETY SECURE 할 수 없다면 SEAT REMOVE 할것. • WALL-MOUNTED CABIN ATTENDANT SEAT REMOVE (AMM 25-22-41-000-801) • FREE-STANDING CABIN ATTENDANT SEAT, RAIL MOUNTED SEAT REMOVE (AMM 25-22-44-000-801) • FREE-STANDING CABIN ATTENDANT SEAT, HARDPOINT MOUNTED SEAT REMOVE (AMM 25-22-44-000-802) - 90 - ※ 50% 의 GALLEY WASTE COMPART FLAPPER DOOR 의 MISSING 은 WASTE COMP'T 가 비어있고 FLAPPER DOOR 대신 ACCESS 가 SECURE 되면 허용됨. ● MMEL 25-35-01 GALLEY WASTE COMP'T FLAPPER DOOR ○ DEACTIVATION OF THE GALLEY-WASTE-COMPARTMENT FLAPPER-DOOR (AMM 25-35-00-040-801) 1. GALLEY WASTE COMP'T 안에 이물질이 있는지 확인후 제거. 2. FLAPPER DOOR 가 결함이있는 경우 - FLAPPER DOOR 를 BLOCK 시키고 사용금지 WARING TAG 부착 3. FLAPPER DOOR 가 MISSING 인 경우 - 사용금지 WARING TAG 부착 후 입구를 TAPE 로 봉인. ● MMEL 25-40-01 TOILET WASTE COMP'T FLAPPER DOOR ○ DEACTIVATION OF THE TOILET WASTE-COMPARTMENT FLAPPER-DOOR (AMM 25-40-00-040-801) - WASTE COMP'T 안에 이물질이 있는지 확인후 제거 후 FLAPPER-DOOR TAPE 로 봉인후 사용금지 WARING TAG 부착 - 91 - ● MMEL 25-62-01-A)b) ESCAPE SLIDE OR SLIDE/RAFT ○ DEACTIVATION OF THE EMERGENCY ESCAPE SLIDES AND SLIDE/RAFTS (AMM 25-62-00-040-801) 1. 1L/1R, 2L/R, 4L/R DOOR - SLIDE OR SLIDE RAFT REMOVE (AMM 25-62-41-000-801) - 1L/1R : LOAD ADJUSTMENT OF THE CONTROL HANDLE (AMM 52-11-00-820-801) 2L/2R : ADJUSTMENT OF THE TORSTION BAR SPRING (AMM 52-12-00-820-801) 4L/4R : ADJUSTMENT OF THE TORSTION BAR SPRING (AMM 52-13-00-820-801) 2. 3L/3R DOOR - SLIDE OR SLIDE RAFT REMOVE (AMM 25-62-42-000-801) - ADJUSTMENT OF THE TORSTION BAR SPRING (AMM 52-22-00-820-801) - 92 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA26) 1) 매 FLIGHT 전 LAVATORY FIRE EXTINGUISHING SYSTEM CHECK. 2) 매 15분 마다 해당 LAVATORY 에 SMOKE 흔적이 있는지 CHECK. ● MMEL 26-17-01a) LAVATORY SMOKE DETECTION SYSTEM (CHECK EVERY 15MIN) ○ DEACTIVATION OF THE LAVATORY SMOKE DETECTION SYSTEM (AMM 26-17-00-040-801) 1. FIRE EXTINGUSHER 의 PRESSURE GAGE 를 통해서 적절한 PRESSURE 가 있는지 확인 (AMM 26-25-00-280-803) • SANITORY CABINET DOOR 를 열고 GAGE 의 IND 이 GREEN SECTOR 에 있는지확인. 2. 만약 PRESSURE GAGE 가 없다 면 WEIGHT CHECK 를 수행하여 SERVICEBLE 인지 판정할것. (AMM 26-25-00-280-804) • BOTTLE REMOVE 하여 ID LABEL 의 WEIGHT 에서 ±5g 인지 확인. (ONLY BOTTLE WEIGHT 만) - 93 - 1) 매 FLIGHT 전 LDMCR FIRE EXTINGUISHING SYSTEM CHECK. 2) 매 15분 마다 LDMCR 에 SMOKE 흔적이 있는지 CHECK. ● MMEL 26-18-03a) LDMCR SMOKE DETECTION SYSTEM (CHECK EVERY 15MIN) ○ OPERATIONAL CHECK OF THE FIRE-EXTINGUISHING SYSTEM IN THE LDCR (AMM 26-18-00-040-801) 1. GROUND LO PRESSURE AIR 공급 (LDCR 의 VENT 를 위함.) 2. 5005VE 의 HEATING LDMCR CTL 6HK (B03) CB CLOSE 확인 ACTION 1) FIRE EXTINGUISHER TEST PANEL에서 'TEST PRESSURE' PB PUSH 2) ‘TEST CARTRIDGE' PB PUSH RESULT - GREEN 'CORRECT' IND 나타남. - GREEN 'CORRECT' IND 나타남. 3. 항공기 원상 - 94 - ● MMEL 26-18-10b) VCC STANDALONE SMK DET SYSTEM ○ DEACTIVATION OF THE VCC WITH STANDALONE SMOKE DETECTION SYSTEM (IF INSTALLED) (AMM 26-18-00-040-805) - 아래 CB OPEN 후 DEACTIVE PLACARD 부착 - 95 - ● MMEL 26-21-01-A) ENG FIRE EXTINGUISH AGENT PB DISCH LT ○ ENG AGENT DISCH LT - PRESSURE CHECK OF THE ENGINE FIRE-EXTINGUISHER BOTTLE (AMM 26-21-00-040-805) 1. 관련 CB CLOSE 되어있는지 확인. (T37, W38, H73, J69) 2. SAFETY PRECAUTION 확인후 수행할것. (HYD PWR OFF, FADEC GND PWR OFF, ENG MASTER SW OFF) 3. 해당 FIRE BOTTLE PRESSURE SW CONNECTOR 분리. 4. PRESSURE SW 에 ALLEN WR (3/32 in) 끼워서 시계방향으로 약 10° TURN. 5. PRESSURE SW CONNECTOR 의 PIN 2 와 3번 사이 NO CONTIUITY 인지 확인. (TEST TOOL : 98F26103000000) - 96 - 6. ALLEN WR 를 INITIAL POS 으로 위치.(TENSION 에 의해 제위치로 오지 않으면 INTERNAL DMGE 된것임) 7. PRESSURE SW CONNECTOR 의 PIN 2 와 3번 사이 CONTIUITY 확인. 만약 TEST NOT OK 이면, BOTTLE WEIGHT 측정해야함 (AMM 26-21-00-040-808) 8. 항공기 원상. PRESS' SW TEST PORT (3/32in ALLEN) CONNECTOR - 97 - P>31BAR : PIN2~3 → CONTIUITY 16.5<P<19 BAR : PIN2~3 NO CONTIUITY ● MMEL 26-21-01-B) ENG FIRE EXTINGUSHING SQUIB LIGHT ○ ENG AGENT LTS - CIRCUIT VERIFICATION (AMM 26-21-00-040-806) 1. SAFETY PRECAUTION 확인후 수행할것. (HYD PWR OFF, FADEC GND PWR OFF, ENG MASTER SW OFF) 2. CB OPEN PANEL 722VU 742VU 742VU 742VU DESIGNATION FIRE BTL1/B ENG1&2 FIRE BTL2/B ENG1&2 FIRE BTL1/B ENG1&2 FIRE BTL2/B ENG1&2 FIN 37WE2 38WE2 37WE1 38WE1 LOCATION T37 W38 H73 J69 PANEL 742VU 742VU 722VU 742VU DESIGNATION FIRE BTL1/A ENG1&2 FIRE BTL2/A ENG1&2 FIRE BTL1/B ENG1&2 FIRE BTL2/B ENG1&2 FIN 37WE1 38WE1 37WE2 38WE2 LOCATION H73 J69 T37 W38 3. 해당 FIRE BOTTLE PRESSURE SW CONNECTOR 분리. 4. PIN 1,2.3 을 SHUNT 시킴. 5. OPEN 되었던 CB CLOSE CAUTION : ENG FIRE PB 을 PUSH 하게되면 다른 SYSTEM 에도 영향을 주니 주의 할것. 6. FIRE TEST PB PUSH : BOTH SQIB LT ON, FIRE TEST PB RELEASE : SQUIB LT OFF 7. 상기 TEST 가 OK 일시 아래항부터 수행, 그렇지 않을 경우 8. CB OPEN - 98 - ● MMEL 26-21-02 ENG FIRE EXTINGUSHING ENG FIRE TEST ○ ENG FIRE TEST - CIRCUIT VERIFICATION (AMM 26-21-00-040-804) 1. FDU1 과 FDU2 BITE TEST 수행 (AMM 26-12-00-740-804) 2. COCKPIT LIGHT TEST 수행. (AMM 33-14-00-710-801) TOGGLE SW → 'TEST' POSTION : ENG FIRE PB 에 RED LT ON SQUIB, DISCH LT ON 되는지 확인. - 99 - ● MMEL 26-22-01-A) APU FIRE EXTINGUSHING DISCH LIGHT ○ BOTTLE PRESSURE CHECK (AMM 26-22-00-040-804-01) 1. CB OPEN : APU FIRE SQUIB B (P09), APU FIRE SQUIB A (J72) 2. APU FIRE BOTTLE PRESSURE SW 에서 ELEC CONNECTOR (11WF-A) 분리 ACTION RESULT 1) FIRE BOTTLE PRESUSRE SW에서 - MULTIMETER : CLOSED CIRCUIT PIN B 와 PIC C 사이 (BOTTLE PRESSURIZATION) 에 MULTIMETER LEAD 연결. 2) 3/32in ALLEN 을 PRESSURE SW SOCKET 에 넣는다. 3) 3/32in ALLEN 을 CW - MULTIMETER : OPEN CIRCUIT 방향으로 10° TURN 4) RELEASE ALLEN - MULTIMETER : CLOSED CIRCUIT 3. OPEN 되었던 CB CLOSE 하고 항공기 원상. ○ BOTTLE WEIGHT CHECK (AMM 26-22-00-040-804) - 실제 BOTTLE 을 REMOVE 하여 WEIGHT CHECK 하는 절차임. - 100 - ● MMEL 26-22-01-B) APU FIRE EXTINGUSHING SQUIB LIGHT ○ CIRCUIT TEST (AMM 26-22-00-040-801) (2명 필요) 1. CB OPEN : APU FIRE SQUIB B (P09), APU FIRE SQUIB A (J72) 2. ZONE 313 안의 APU FIRE BOTTLE CARTRIGE (12WF) 에서 CONNECTOR 분리 3. OPEN 했던 CB CLOSE ACTION RESULT 1) ELEC CONNECTOR (12WF-A) 의 PIN 2 와 4를 TEMPORARY GROUND 시킴 2) OVHD APU FIRE PNL ‘TEST' PB PUSH & - APU FIRE PANEL 231VU 의 'SQUIB' LEGEND ON HOLD 3) ‘TEST' PB RELEASE - APU FIRE PANEL 231VU 의 'SQUIB' LEGEND OFF NOTE : 'SQUIB' LEGEND 가 ON 되면 (TEST IS CORRECT) SQUIB 결함으로 교환 할것. NOTE : 'SQUIB' LEGEND 가 ON 되지 않으면 (TEST ISN'T CORRECT) FIRING CIRCUIT 또는 TEST CIRCUIT 결함. 아래 TEST 수행하여 FIRE SYSTEM 이 잘 작동하는지 확인 4) ELEC CONNECTOR (12WF-A) 의 PIN 2 와 4에서 TEMPORARY GROUND PIN REMOVE 5) 12WF-A 의 PIN 2 와 PIN 1 에 (PIN1:GRD) - MULTIMETER : 0 VDC 지시 MULTIMETER 연결 6) OVHD APU FIRE PANEL 에서 APU FIRE PB GUARD 제끼고 PUSH 7) AGENT PB PUSH & - MULTIMETER : 28 VDC 지시 HOLD 8) AGENT PB RELEASE - MULTIMETER : 0 VDC 지시 9) 12WF-A 의 PIN 4 와 PIN 3 에 (PIN3:GRD) - MULTIMETER : 0 VDC 지시 MULTIMETER 연결 10) AGENT PB PUSH & - MULTIMETER : 28 VDC 지시 HOLD 11) AGENT PB RELEASE - MULTIMETER : 0 VDC 지시 12) OVHD APU FIRE PANEL 에서 APU FIRE PB PUSH 하여 집어넣고 GUARD 접을것. NOTE : TEST 가 올바르게 잘된다면 FIREING SYSTEM 은 이상이 없음. TEST SYSTEM 의 결함임. NOTE : TEST 가 잘안되었을 경우(NO VOLTAGE) 는 FIREING SYSTEM 의 결함임. 2. CB OPEN : APU FIRE SQUIB B (P09), APU FIRE SQUIB A (J72) 3. CARTRIGE CONNECTOR 장착 후 CB CLOSE 4. 항공기 원상 - 101 - ● MMEL 26-22-03 APU FIRE EXTINGUSHING APU FIRE TEST ○ APU FIRE TEST VERIFICATION (AMM 26-22-00-040-802) 1. MCDU SYSTEM TEST ATA26 FIRE PROT:ENGINES 2. 관련 CB CLOSE 확인 (P09, P08, P07, D80, G78, J72, J71) ACTION 1) MCDU 의 APU FDU PUSH 2) 'TEST' KEY PUSH RESULT - ‘APU FDU’ PAGE 나타남. - TEST IN PROGRESS 90S - 약 4초후 APU FIRE PB 과 SQUIB, DISCH LT ON. - 약 6초후 APU FIRE PB 과 SQUIB, DISCH LT OFF. - MCDU : 약 90초후 'TEST OK' DISPLAY 3) MCDU에서 RETURN KEY PUSH 4) 'APU AFE' PUSH - ‘APU AUTO FIRE EXTING’ PAGE 나타남. 5) 'TEST' KEY PUSH - TEST IN PROGRESS 8S - 약 4초후 APU FIRE PB 과 SQUIB, DISCH LT ON. - 약 6초후 APU FIRE PB 과 SQUIB, DISCH LT OFF. - MCDU : 약 8초후 'TEST OK' DISPLAY 6) AGENT PB PUSH & - MULTIMETER : 28 VDC 지시 HOLD 7) MCDU에서 RETURN KEY PUSH 3. 항공기 원상. ● MMEL 26-22-04 APU FIRE EXTINGUSHER OPERPRESS' IND' (RED DISK) ○ APU FIRE EXTINGUISHER OVERPRESSURE INDICATION (RED DISK) MISSING (AMM 26-22-00-040-805) 1. 관련 CB CLOSE 확인 (P09, P08, P07, D80, G78, J72, J71) 2. TEST OF THE SQUIB CIRCUIT - 102 - ACTION 1) OVHD PNL 의 APU FIRE TEST PB PUSH& HOLD 2) 'TEST' PB RELEASE RESULT - APU FIRE PB 과 SQUIB, DISCH LT ON. - MASTER WARN, CRC - ON THE EWD APU FIRE APU FIRE P/B..............PUSH MASTER SW .................OFF - 상기 MSG 와 IND & LT 모두 OFF 3. OPERATION CHECK OF THE PRESSURE SW ACTION 1) APU FIRE BOTTLE 의 PRESSURE SW 에 3/32 in ALLEN 넣어 CW 로 10° TURN 2) RELEASE ALLEN KEY 4. 항공기 원상. RESULT - APU FIRE PANEL 231VU AGENT PB 에 DISCH LEGEND ON - ALLEN KEY 가 INITIAL POSTION 으로 돌아옴. - APU FIRE PANEL 231VU AGENT PB 에 DISCH LEGEND OFF ● MMEL 26-22-05a) APU FIRE EXTINGUSHING SQUIB ○ REMAINING SQUIB INTEGRITY CHECK (AMM 26-22-00-040-806) 1. APU FIRE AND OVERHEAD DETECTION SYSTEM BITE TEST 수행 • MCDU SYSTEM TEST ATA26 FIRE PROT:ENG/APU → APU FDU PUSH → TEST PUSH 2. 다음 MSG 가 나타나는지 확인 - ‘BTL APU CARTRIDGE (12WF) SPLY/FDU APU (13WG)’ : 1개의 SQUIB 만 INOP. 다 른 SQUIB 는 정상 - ‘BTL APU CARTRIDGE CONNECTOR (12WF)’ : BOTH SQUIBS ARE INOPERATIVE. IN THAT CASE, APPLY THE OTHER MMEL ITEM EXCEPTION. - 103 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA27) SERVO CONTROL 이 SEIZING 되지 않아야함. ※ PRIM 3 와 관계되는 BOTH S․C 은 작동되지 않아도 된다 : LH WING 'Y', RH WING 'G' ● MMEL 27-14-01-A) OUTBOARD AILERON ○ DEACTIVATION OF THE OUTBOARD AILERON SERVO CONTROL (AMM 27-14-00-040-801) 1. HYD SYSTEM DE-PRESSURIZATION 2. CB OPEN FCS1 NORM C70 FCPC3 V42 FCPC3 STBY MON R19 FCPC3 STBY CON R20 FCPC3 V38 FCPC3 V42 FCPC3 STBY MON R19 FCSC2 T39 FCPC3 V38 FCSC2 STBY SPLY D66 FCPC3 STBY COM R20 3. ACCESS PANEL REMOVE : 9CS1 & 10CS1 (576CB), 9CS2 & 10CS2 (675CB) 4. HYD PRESS LINE (1) 과 RETURN LINE (3) 이 정확하게 S.C 에 장착되어있나 확인 5. HYD LEAK 가 없나 확인 6. RECEPTACLE 로부터 ELEC CONNECTOR (4) 분리 7. BLANKING CAP 씌우고 TIE WRAP 으로 PIPE 에 고정 8. CB CLOSE : CB FCPC3 7CE3 (V42) 와 FCPC3 7CE4 (V38) 는 동시에 CLOSE 하라. OVHD PNL 에 PRIM3 PB 에 FAULT 가 ON 되어있으면 다시 7CE3 와 7CE4 를 OPEN & CLS 하라 9. AILERON HYD ACTUATION TEST 수행 (TASK 27-14-00-710-810) : LEAK MEASUREMENT V/V PB 을 OFF 하여 각 SYSTEM (G, B, Y) 마다 개별적으로 SIDE STICK을 FULL LEFT/RIGHT 로 움직여 AILERON 이 잘 작동 되는지 확인하는 절차임. - 모든 FLT CONT PB NML POS, SLAT/FLAP FULL RETRACT POS SPD BRK CONT LVR - 104 - FULL RET' POS & HYD PUMP ON NOTE : DEACTIVATED 된 OUTB'D AILERON SC 은 작동되지 않는다. ELEC' CONNECTOR 만 분리 - 105 - ● MMEL 27-14-02-A) AILERONS POSTION INDICATION ○ CHECK OF THE AILERONS DEFLECTION (AMM 27-14-00-040-802) 1. ALL HYD ELEC PUMP ON 2. ALL PRIM, SEC PB ON 3. ALL LEAK MESUREMENT PB ON 4. FLAP/SLAT FULL RETRACT, SPD BRK LEVER 'RET' POSTION 5. 관련 CB CLOSE 되어있는지 확인 (R20, R19, T42, T39, V42, V41, V38, C70, C69, D66, L76) 6. OPERATION TEST OF THE AILERONS ACTION RESULT - LEAK MEASURE' V/V PB B & Y 에 'OFF' LT 1) LEAK MEASURE' V/V ON THE SD PB B & Y RELEASE - BLUE, YELLOW HYD PRESSURE DECREASE - INBD & OUTBD AIL (LH & RH) NEUTRAL POSTION 유지 2) SIDE STICK FULL - LH INBD & OUTBD AIL MOVE DOWN RIGHT POSTION 으로 - RH INBD & OUTBD AIL MOVE UP 움직임. 3) SIDE STICK FULL - LH INBD & OUTBD AIL MOVE UP LEFT POSTION 으로 - RH INBD & OUTBD AIL MOVE DOWN 움직임. 4) SIDE STICK NEUTRAL - INBD & OUTBD AIL (LH & RH) NEUTRAL POSTION 유지 POSTION 으로 움직임. - LEAK MEASURE' V/V PB B & Y 에 'OFF' LT 없어짐. - LEAK MEASURE' V/V PB G 에 'OFF' LT 5) LEAK MEASURE' V/V ON THE SD PB B & Y PUSH, - BLUE, YELLOW HYD PRESSURE INCREASE G RELEASE - GREEN HYD PRESSURE DECREASE - INBD & OUTBD AIL (LH & RH) NEUTRAL POSTION 유지 6) SIDE STICK FULL - LH INBD & OUTBD AIL MOVE DOWN RIGHT POSTION 으로 - RH INBD & OUTBD AIL MOVE UP 움직임. 7) SIDE STICK FULL - LH INBD & OUTBD AIL MOVE UP LEFT POSTION 으로 - RH INBD & OUTBD AIL MOVE DOWN 움직임. 8) SIDE STICK NEUTRAL - INBD & OUTBD AIL (LH & RH) NEUTRAL POSTION 유지 POSTION 으로 움직임. 9) LEAK MEASURE' V/V - GREEN HYD PRESSURE INCREASE PB G PUSH 7. 항공기 원상 - 106 - ※ RUDDER TRIM ANGLE : (001-099) 25±0.8°, (101-199) 29.2±1° ● MMEL 27-22-01 RUDDER TRIM SYSTEM ○ DEACTIVATION OF THE RUDDER-TRIM ELECTRIC MOTOR (1 OR 2) (AMM 27-22-00-040-801) 1. 아래 CB OPEN - FOR THE ELEC MOTOR1 : OPEN CB RUD TRIM ACTR MOT1 30CS1 (L78) 742VU - FOR THE ELEC MOTOR2 : OPEN CB RUD TRIM ACTR MOT2 30CS2 (T40) 722VU 2. RUDDER TRIM ACT' OPERATION TEST 수행하라 (AMM 27-22-00-710-805) NOTE : DEACTIVE 된 RUD TRIM CHANNEL1 또는 2 는 작동되지 않는다. ① "G" HYD SYS PRESSURIZED ② OVHD PNL PRIM1, SEC1 & 2 PB PUSH IN ③ RUDDER TRIM ZERO 확인 ④ RELEASE THE SEC2 PB (OFF LT ON) ⑤ RUD TRIM CONTROL SW 를 NOSE/L 로 TRUN 하고 HOLD : RUD TRIM IND L25°±0.8° (RUD 는 LH 로 움직임) ⑥ PUSH RUD TRIM/RESET PB : RUD TRIM IND 0±0.6° (RUD NEUTRAL POS 으로 오게됨) ⑦ RUD TRIM CONT SW 를 NOSE/R 로 TURN 하라. : IND 은 상기 ⑤⑥의 R 방향임(생략) ⑧ PUSH RUD TRIM/RESET PB : ⑥ ITEM 과 동일함. ⑨ PUSH THE SEC2 PB ("OFF" LT OFF) ※ 상기 TEST 는 RUDDER TRIM 1을 TEST 한 절차이며 TRIM 2를 TEST 하고자 할때에는 SEC1 SW 를 RELEASE 하고 TEST 한다. - 107 - ● MMEL 27-25-01-A) RUDDER POSITION INDICATION ○ CHECK OF THE RUDDER MOVEMENT (AMM 27-25-00-040-801) 1. GREEN HYD PWR ON 2. ALL PRIM, SEC PB ON 3. RUD TRIM '0' 확인 4. RUD PEDAL 을 FULL LH/RH 로 차서 실제 RUD 가 잘 작동하는지 외부에서 직접확인할것. - 108 - ● MMEL 27-25-02-A) F/CTL RUD G(Y)(B) SERVO JAM (FALSE CAUTION & INTERVAL C) ○ CHECK OF THE CORRECT SYNCHRONIZATION OF THE RUDDER SERVO CONTROLS (AMM 27-25-00-040-802) ◆ AMM 27-24-00-220-801 수행 1. RUDDER MECH' CONTROL ROD (CABLE QUADRANT 와 RUDDER-LINKAGE INTERFACE BELLCRANK 사이에있음). 분리하고 RIG PIN (98F27207515000) 장착 하여 MECH' 을 LOCK 시킴. (AMM TASK 27-21-00-840-801) 2. ALL FCPC, FCSC 'ON', RUDDER TRIM '0' 3. 'G' HYD PWR ON - 109 - 4. RIG PIN 장착 (98F27208312000) : CONTROL ROD 를 천천히 움직이면 쉽게 장 착할수있음. 5. TAIL CONE 위에 RUDDER 움직임을 측정할수있는 SCALE 표시 (종이 테이프이용) 6. ‘G' HYD PWR 만 ON 되어있는 상태에서 RUDDER TRAILING EDGE 위치 표시 7. 'B' HYD ON, 'G' HYD OFF 8. 'B' HYD PWR 만 ON 되어있는 상태에서 RUDDER TRAILING EDGE 위치 표시 9. ‘Y' HYD ON, 'B' HYD OFF 10. 'Y' HYD PWR 만 ON 되어있는 상태에서 RUDDER TRAILING EDGE 위치 표시 11. RUDDER 움직임의 끝에서 끝까지의 거리인 ‘D' 값 측정 - ‘D' 값이 10MM(EFF 001~099),13MM(EFF 101~199) 이하일 경우 • REF' TRIANGLE 의 중심이 ‘D' 안에 있는지확인하라. → 'D' 안에있다면 NO MAINT ACTION → 'D' 안에 없다면 ADJUST THE RUDDER SERVOCONTROL ACTUATING SPRING ROD(S) (REF. AMM TASK 27-21-00-820-804) OR (REF. AMM TASK 27-21-00-820-805) - ‘D' 값이 10MM(EFF 001~099),13MM(EFF 101~199) 이상이고 17MM(EFF 001~099), 22MM(EFF 101~199) 이하일 경우 ADJUST THE RUDDER SERVOCONTROL ACTUATING SPRING ROD(S) (REF. AMM TASK 27-21-00-820-804) OR (REF. AMM TASK 27-21-00-820-805) - ‘D' 값이 17MM(EFF 001~099), 22MM(EFF 101~199) 이상일 경우 • 가장많이 벗어나는 SERVO CONTROL 교환할것 (LARGEST LOAD) : 상기그림의 * • SERVO CONTROL 의 ATTACH 되는부분 INSP • 다른 2개의 SERVO CONTROL ADJUST 할것. 12. 항공기 원상 - ‘F/CTL RUD X SERVO JAM’ warning (X = B or G or Y) 이 FALSE 임을 나타내는 WARNING NOTICE 를 COCKPIT 에 부착할것. - 110 - ※ YAW DAMPER SYSTEM 1 (19CS1, GREEN HYD) INOP 은 NO-GO 이므로 SYSTEM 1, 2 SWAP 후 DISPATCH 할것. CAT-Ⅱ OPERATION 관련 CONTACT DISPATCHER ● MMEL 27-26-01 YAW DAMPER SYSTEM ○ DEACTIVATION OF THE YAW DAMPER SERVO-ACTUATOR (19CS2) (AMM 27-26-00-040-801) 1. CB OPEN FCPC STBY COM FCPC STBY MON R20 R19 FCSC2 FCPC3 T39 V42 FCPC3 FCSC2 STBY SPLY V38 D66 2. OPEN ACCESS DOOR (312R) 3. ELEC CONNECTOR 2, 3 을 분리하여 CAPPING 하고 TIE WRAP 으로 묶어라. 만일 YAW DAMPER ACTUATOR 에 HYD LEAK 한다면YELLOW HYD DEPRESS‘ 후 HYD HOSE 4,5 를 DISCONNECTION 하고 LINE END 를 BLANKING 하라. HYD LEAK 시 분리 19CS2 5 FR80 4 1 2 3 - 111 - 312AR FR80 4. CLOSE CB 5. BYDU OPER' TEST 수행하라. (TASK 27-26-00-740-802) - ‘B’ HYD ELEC PUMP ON - PRIM 1,2,3 & SEC2 PB RELEASE(OFF LT ON) - SEC1 만 PUSH IN - ADIRS 1,2,3 OFF - RUD TRIM “ZERO” 확인후 SD 에 F/CTL PAGE를 DISPLAY 시켜라. - ON MCDU, SYS REPORT/TEST F/CTL:EFCS ACTION RESULT 1) SYS REPORT/TEST, F/CTL:EFCS PAGE의 EFCS #1 KEY PUSH 2) SCTL TEST PUSH - 'SERVO CONTROL TEST' PAGE 나타남 3) BYDU TEST PUSH → START TEST PUSH ON THE SD F/CTL PAGE 4) CONFIRM START - RUD IND POINT 가 MOVING 하였다가 처음위치로 옴 TEST - 'TEST IN PROGRESS 15 SEC' DISPLAY 5) 15S 후 'B' HYD SYS DEPRESS 하고 2분 기다리되 3분을 넘기지 말것. 6) ‘Y’ HYD ELEC PUMP ON - RUD IND POINT 가 MOVING 하였다가 처음 위치로 옴 - BYDU TEST PAGE 에 ‘TEST IN PROGRESS 15S’ 보이고 5S 후에 “TEST OK" - A/C 원상 6. YD ACTUATION TEST 수행하라. (TASK 27-26-00-710-803) - PRIM1,2,3 SEC1 & 2 PB PUSH IN ("OFF" LT OFF) - LEAK MESUREMENT V/V G,Y PB PUSH IN ("OFF/FAULT" LT OFF) - RUDDER TRIM ZERO 확인 - ADIRS 1 을 'NAV' POS 으로 2,3 는 'OFF' - 'G','Y' HYD SYS ELEC PUMP ON - CB OPEN (CB OPEN 전 PRECAUTION 지킬것.) : - 112 - LG SAFETY V/V 3GA (S12), LGCIU2 2GA (U38), LGCIU1 1GA (L63) ※ LGCIU CB OPEN 할 경우 LGCIU 관련 SYSTEM을 차단하기 위하여 TASK 32-00 -00-860-804 FLIGHT CONF' PRECAUTION 를 참조하여 관련 CB 추가로 OPEN 할것. CAUTION 사항 준수할것. - 관련 CB 는 CLOSE 되어있어야 한다. (R20, R19, T39, V42, V38, C70, C69, D66, G77, K69) - FLAP/SLAT EXTEND 시킬것. - OPER' OF THE YD ACTUATION (DEACTIVATED 된 YD ACT' 는 작동안한다.) CAUTION : FLAP/SLAT 작동하는 동안 LEAK MEASUREMENT V/V PB PUSH 나 RELEASE하지 말것. MECH' JAMMING 이 발생함. SIDE STICK 천천히 움직일것. NOTE : WARNING 과 SPOILER 와 AILERON 의 움직임 은 무시할것. ACTION RESULT 1) LEAK MEASUREMENT V/V “Y" PB RELEASE - 'OFF' LT ON ON THE SD F/CTL PAGE 2) SIDE STICK 을 MAX RH ROLL 에 놓아라 - RUD POINT 가 RH 로 조금 움직임 3) SIDE STICK 을 MAX LH ROLL 에 놓아라 - RUD POINT 가 LH 로 조금 움직임 4) SIDE STICK을 NEUTRAL POS 에 두라 - RUD POINT 가 NEUTRAL 로 옴. 5) LEAK MEASUREMENT V/V “Y" PB PUSH - ‘OFF' LT OFF 6) LEAK MEASUREMENT V/V "G" PB RELEASE - 'OFF' LT ON ON THE SD F/CTL PAGE 7) SIDE STICK 을 MAX RH ROLL 에 놓아라 - RUD POINT 가 RH 로 조금 움직임 8) SIDE STICK 을 MAX LH ROLL 에 놓아라 - RUD POINT 가 LH 로 조금 움직임 9) SIDE STICK을 NEUTRAL POS 에 두라 - RUD POINT 가 NEUTRAL 로 옴. 10)LEAK MEASUREMENT V/V “G" PB PUSH - ‘OFF' LT OFF - CLOSE CB (LGCIU와 관련된 CB CLOSE시 PRECAUTION을 지켜라) - 항공기 원상. - 113 - ※ 매 FLIGHT 전 아래사항 수행할것. ● MMEL 27-34-02-A) ELEVATOR POSITION INDICATION ○ CHECK OF THE ELEVATOR TRAVEL (AMM 27-34-00-040-801) 1. ALL FCPC, FCSC PB PUSH IN ('OFF' LT OFF) 2. ALL HYD LEAK MEASUREMENT V/V PB PUSH IN ('OFF' LT OFF) 3. EWD 에 LGCIU 관련하여 WARNING 이 없나 확인할것. 4. “B,Y" HYD PUMP ON 하고 아래의 CB가 CLOSE 되었나 확인 FCPC3 STBY COM FCPC3 STBY MON FCDC2 FCSC2 R20 R19 T42 T39 FCPC3 FCPC2 NORM FCPC3 FCSC1 NORM V42 FCPC1 NORM V41 FCSC STBY SPLY V38 FCDC1 C70 5. ADIRU1,2,3 'OFF' POS' 6. OPERATION TEST OF THE ELEVATORS (TEST 동안 항공기 외부에서 ELEVATOR 의 움직임을 확인할것.) ACTION 1) HYD LEAK MEASUREMENT V/V B, Y PB RELEASE 2) SIDE STICK을 MAX NOSE DOWN 으로 움직임. 3) SIDE STICK을 MAX NOSE UP 으로 움직임. 4) HYD LEAK MEASUREMENT V/V B, Y PB PUSH 5) HYD LEAK MEASUREMENT V/V G PB RELEASE 6) SIDE STICK을 MAX NOSE DOWN 으로 움직임. 7) SIDE STICK을 MAX NOSE UP 으로 움직임. 8) SIDE STICK을 NEUTRAL 로 움직임. 9) HYD LEAK MEASUREMENT V/V G PB PUSH 7. 항공기 원상. RESULT - 'OFF' LT ON - B, Y HYD PRESSURE DECREASE ON THE SD F/CTL PAGE - LH/RH ELEV' 모두 MOVE DOWN - LH/RH ELEV' 모두 MOVE UP - 'OFF' LT OFF - B, Y HYD PRESSURE INCREASE - 'OFF' LT ON - G HYD PRESSURE DECREASE - LH/RH ELEV' NEUTRAL POSTION ON THE SD F/CTL PAGE - LH/RH ELEV' 모두 MOVE DOWN - LH/RH ELEV' 모두 MOVE UP - LH/RH ELEV' NEUTRAL POSTION - 'OFF' LT OFF - G HYD PRESSURE INCREASE - 114 - C69 D66 L76 ● MMEL 27-44-01 THS ACTUATOR ELEC MOTOR ○ DEACTIVATION OF THE TRIMMABLE HORIZONTAL-STABILIZER (THS) ACTUATOR ELECTRICAL MOTOR (AMM 27-44-00-040-801) 1. HYD SYS DEPRESS' 2. PRIM1,2,3 SEC1,2 PUSH IN ("OFF" LT OFF) 3. 아래 CB 중 관련 CB 만 OPEN THS ACTR MOT1 L77 THS ACTR MOT2 NORM V43 THS ACTR MOT3 V44 (FOR THS ACT MOT 1) (FOR THS ACT MOT 2) (FOR THS ACT MOT 3) 4. THS ACT' ELEC MTR DEACTIVATION WARNING : RUD TRAVEL RANGE 내 CLR 가 되어야 하며 SAFETY BARRIER 로 접근을 방지하라. NOTE : DEACTIVATION 은 ELEC MOTOR 1 으로 하고 MOTOR 2,3 는 MOTOR 1 과 PROCEDURE 가 같다. ( ) 로 대체함 ① ALL HYD ELEC PUMP ON ② ECAM 에 'F/CTL PRIM 1,2 & 3 PTCH FAULT' 가 DISPLAY 되었나 확인하라. ③ F/CT L PNL PRIM1.2 & 3 PB 을 RELEASE 하라. (“OFF" LT ON) ④ CTR PEDESTAL 에서 PTCH CONTROL WHEEL 을 FULL UP POS 으로 움직여라 ⑤ PRIM1(2)(3) PB 을 PUSH 하라(“OFF" LT OFF) ⑥ PTCH TRIM CTL WHEEL 이 움직이지 않는가 확인하라. ⑦ EWD 에 'F/CTL STAB CTL FAULT' WARNING 이 들어오나 확인 ⑧ MCDU 에서 EFCS GRD SCANNING BITE TEST 를 수행하라. ⑨ 아래 MAINT MSG 가 보이는지 확인하라 : • WRG/THS ACTR CIRCUIT BREAKER TO FCPC1, WHEN THE CIRCUIT BREAKER FOR THS ACTR MOTOR 1 IS OPEN, • THS ELEK MDL (1CS)/FCPC2 (2CE2)/RLY(6CS2/23CS2), WHEN THE C/B FOR THS ACTR MOTOR 2 ARE OPEN, • THS ELEK MDL (1CS)/FCPC3 (2CE3)/RLY(6CS3/23CS3), WHEN THE C/B FOR THS ACTR MOTOR 3 IS OPEN, ⑩ FLT CTL PNL 에 PRIM 2(3)(1) & PRIM3(1)(2) PUSH 하라 (“OFF" LT OFF) ⑪ CTR PEDESTAL 에 PTCH TRIM CTL WHEEL은 자동적으로 4° UP POS 으로 움직인다. - 115 - ⑫ ALL HYD ELEC PUMP OFF ⑬ BALL SCRW ASSY 의 PRIM & SEC' LOAD PATH 를 INSP 하라.(AMM 27-44-51-210-505) - 이 STEP 은 EWD 에 ‘PRIM1(2)(3) PITCH FAULT’ 와 CLASS1 MAINT MSG 'PITCH TRIM ACTR(1CS) 이 나타났을때 수행한다. ⑭ CKPT 에 WARNING NOTICE 를 부착하라. • 1EA 의 THS ACT MTR 1,2 OR 3 DEACTIVATED • EWD 에 PRIM1(2)(3) PTCH FAULT가 DISPLAY 된다. ⑮ A/C를 원상하라. ● MMEL 27-45-01-A) THS PTICH TRIM POSITION ○ CHECK FOR THE SYNCHRONOUS OPERATION OF THE PITCH TRIM HANDWHEELS AND THE THS (AMM TASK 27-45-00-040-801) 1. B, Y HYD ELEC PUMP 'ON' 2. 관련 CB CLOSE 확인 : R20, R19, T42, T39, V44, V43, V42, V41, V38, C70, C69, G77, K69, L77, L76 ACTION 1) PTCH TRIM CONTROL WHEEL 을 2° DOWN 하라 2) PTCH TRIM CONTROL WHEEL을 14° UP POS SET 하라 3) PTCH TRIM CONTROL WHEEL을 4° 에 SET 하라 3. A/C를 원상하라. RESULT - 항공기 외부 THS STRUCTURE SCALE 에 REF' MARK 가 2ND 에 오는지 확인 - REF' MARK 가 "0" POS 이하 14TH에 ALIGN 되어있나 확인하라. - REF' MARK 가 GND POS 에 ALIGN 되어 있나 확인하라. - 116 - ※ FLAP/SLAT SYSTEM 2 가 NML 인상태이며 FLAP SYSTEM 1 이 DEACTIVE 되면 MAX 9 CALENDAR DAY 까지 FLIGHT 가능 ※ FLAP SYSTEM 2 가 DEACTIVE 되고 YELLOW ELEC PUMP 가 정상작동 하면 MAX 9 CALENDAR DAY 까지 FLIGHT 가능 ● MMEL 27-51-01 FLAP SYSTEM 1, 2 ○ DEACTIVATION OF THE CONTROL AND MONITORING OF THE FLAP SYSTEM 1 OR 2 (AMM 27-51-00-040-801) 1. ADIRU 1,2,3 를 NAV POS' 에 놓아라. 2. G, Y HYD ELEC PUMP 를 ON 하라. 3. LEAK MEASUREMENT V/V B,Y,G PB PUSH ("OFF" LT OFF) 되어있는지 확인. 4. 관련 CB CLOSE 확인 : X14, X13, L33, T43, V40, L62, L61, P62 5. FLAP SYSTEM 1 DEACTIVATION : SFCC1 FLAP 1CV (L61) CB OPEN FLAP SYSTEM 2 DEACTIVATION : SFCC2 FLAP 2CV (T43) CB OPEN 6. FLAP 2 SYSTEM DEACTIVE 시 SYSTEM 1 아래 TEST 수행 (SYSTEM 1 DEACTIVE 시 SYSTEM 2 TEST 수행) ACTION RESULT 1) SYS REPORT/TEST 27 → SFCC1(2) → FLAP SYSTEM 1 GROUND SCAN 시 - 'SFCC1 22CV FLAP BUS6/SFCC1 21CB FLAP BUS 28 2) GROUND SCANNING SYSTEM 2 GROUND SCAN 시 - SFCC 1 21CV FLP BUS 6/SFCC 2 22CV FLP BUS 28 KEY PUSH 상기 MSG 들은 DISPLAY 되지만, TEST 하는 SYSTEM 의 MAINT IND 은 없어야한다. 3) SLAT/FLAP CONT - EWD FLAP IND‘ 이 LEVER 와 일치 하는지 확인. LVR 1,2,3 & FULL POS - TEST 하는 SYSTEM 의 FAULT 는 없어야한다. 에 단계적으로 움직여라 7. EWD : 'FLAP SYS1(2) FAULT', THE STATUS 'FLAPS SLOW' NOTE : FLAP SYS1(2) DEACTIVATION 상태일때 ADIRU & EIVMU 관련된 MSG TRIGGER 된다. 8. 항공기 원상하라. - 117 - ● MMEL 27-64-01 SPOILER ○ DEACTIVATION OF THE SPOILER SERVO CONTROL (AMM 27-64-00-040-801) WARINING : EXTERNAL LEAK 가 있을 경우 SERVO CONTROL DEACTIVE 하지 말것. NOTE : 아래사항은 POST SB 에 해당 (SERVO CONTROL 138X TYPE) 1. SPOILER OPERATION TEST 수행하라. 2. EFCS 의 GROUND SCANNING 수행하라. (GROUND SCANNING 화면에 DEACTIVE 된 SERVO CONTROL 의 MAINT MSG DISPLAY 될것임.) 3. FLAP 을 EXTEND 하라. 4. 다음 CB OPEN하라. FCPC3 STBY COM R20 FCPC3 FCPC3 STBY MON R19 FCSC1 NORM FCDC2 T42 FCPC1 NORM V38 FCSC2 T39 FCSC1 STBY G77 C70 FCPC3 V42 FCPC1 STBY K69 C69 FCPC2 NORM V41 FCDC1 L76 5. 해당 SPOILER(SSC) 에 MAINT DEVICE 에 MAINT KEY (98D27603002001) 를 장착하여 “M" POSTION 으로 TURN. 6. ELEC CONNECTOR 를 분리하고 CAPPING 한다음 STRUCTURE 에 ELEC CONNECTOR 를 잘 붙들어 맬것. 7. SPOILER 가 FULL RET' POS 인가 확인하라. 8. MAINT KEY (98D27603002001) 를 다시 반대 방향으로 돌려 “O" POSITION 으로 놓을것. CAUTION : "O" STOP 에 놓지 않을 경우 AERODYNAMIC FORCE 가 SPOIER에 원하지 않 는 MOVEMENT를 야기시킬수있다. 9. MAINT KEY (98D27603002001) 를 제거. 10. ALL CB CLOSE 하라. 11. SPOILER OPERATION TEST 수행하라.(TASK 27-64-00-710-803) NOTES : SD 에 DEACTIVATED SPILER 와 함께 반대쪽 SPOILER도 대칭적으로 AMBER 지시하나 확인 12. EWD 에 ‘SPLR FAULT' MSG 지시 13. A/C를 원상하라. - 118 - PRE SB (SSC S4 TYPE) POST SB (SSC 138X TYPE) - 119 - ● MMEL 27-64-02-A) SPOILERS/SPEED-BRAKES INDICATION ○ DEACTIVATION OF THE SPOILERS/SPEEDBRAKES INDICATION (AMM 27-64-00-040-802) 1. FLAP "0", SPEED BRAKE LEVER RET' POS 에 두라. 2. FLT CONTROL 관련 CB CLOSE, PRIM1,23 SEC1,2 PUSH IN 3. ALL HYD ELEC PUMP ON 4. SPEED BRK LEVER 'FULL' SET 하라 : ALL SPOILER EXTEND 5. SPEED BRK LEVER FULL 'RET' SET 하라 : ALL SPOILER RETRACT (상기 4항 5항은 항공기외부 WING TRAILING EDGE 에서 확인) ※ SLAT SYSTEM 2 DEACTIVE 된상태로 9 CALENDAR DAY 까지 FLIGHT 가능 ● MMEL 27-81-01-B) SLAT SYSTEM 2 ○ DEACTIVATION OF THE SLAT SYSTEM 2 1. ALL ADIRU 'NAV' POSTION 2. G,B HYD ELEC PUMP ON 3. LEAK MESUREMENT V/V B,Y AND G PB PUSH IN ("OFF" LT OFF) 4. REV' CONTROL LEVER 가 STOWED POS 에 LOCKED 되어있나 확인. 5. MCDU SYSTEM REPORT/TEST → ATA27 F/CTL FLAP/SLAT PAGE DISPALY 시킬것. 6. 관련 CB CLOSE 확인 : X14, X13, L34, T43, V40, L62, L61, P63 7. CB SFCC2 SLAT 2CW (V40) OPEN 8. SLAT SYSTEM2 가 DEACTIVE 되었다는 NOTICE TAG 부착하고 FLT LOG 기록. 9. SLAT SYSTEM OPERATION TEST CAUTION : LEAK MEASUREMENT V/V PB 을 OPERATION 동안 작동하지 말것. NOTE : OPERATION 동안 EWD 에 ‘FLAP SYS1 FAULT' MSG DISPLAY 될 수있다. - 120 - ACTION RESULT 1) MCDU 의 F/CTL:FLAP/SLAT MENU PAGE 에서 'SFCC1' 을 PUSH. 2) SFCC1 MENU PAGE 에서 'SLAT' PUSH - SLAT SYS1 에 관련된 MAINT IND 이 보이지 않아야 한 3) SLAT MENU에서 GRD 다. 단, 'SFCC2(22CV) SLT BUS5 / SFFC1(21CV) SLT SCANNING을 PUSH. BUS27' 은 볼수있다. 4) SLAT/FLAP CONT LVR - SLAT 이 SET POS 에 작동하고 SLAT SYSTEM 1 에 관 를 “1” 에 SET 련된 WARNING 이 없어야한다 5) SLAT CONT LVR를 “2”에 SET. 또한 “3” POS 까지 SET 하여 WARNING 이 없어야한다. - SLAT POS BAR 는 움직이지 않고, SLAT SYS1 에 관련 6) LVR 를 "FULL" POS 까지 SET. 된 WARNING 이없어야한다 - SLAT SYS1 에 관련된 WARNING 이없어야한다 7 )SLAT CONT LVR 를 3 NOTE : SLAT/FLAP CONT LVR를 “FULL"에서 ”3“ POS →2→1→0 에 SET 까지 움직일때 SLAT은 움직이지 않는다. 8) MCDU GRD -SLAT SYS1 에 관련된 MAINT IND 이 보이지 않아야 한 SCANNING 하여 MAINT 다. 단, 'SFCC2(22CV) SLT BUS5 / SFFC1(21CV) SLT MSG 가 없나 확인하라. BUS27' 은 볼수있다. 10. A/C를 원상하라. 11. ON EWD 'SLAT SYS2 FAULT', STATUS 'SLAT SLOW' DISPLAY - 121 - ※ FOR A/C THAT CONTAIN FCPC PN: LA2K01500A60000 (SB LA2K0-27-013) OR LA2K1A100D40000 (SB LA2K1-27-003) ⇒ THEY ARE ASSOCIATED TO PRIM 3 ONLY FOR A/C THAT CONTAIN FCPC PN: LA2K1A100D60000 (SB A330-27-3132) OR LA2K01500AB0000 (SB A330-270-3132) ⇒ THEY ARE ASSOCIAED WITH A SINGLE PRIM (PRIM1 OR PRIM3), AND ● MMEL 27-92-05 PRIM SIDESTICK POTENTIOMETER SIGNAL ○ DEACTICATION OF THE SIDE STICK POTENTIOMETER 1. ALL HYD POWER OFF 2. PRIM1,2,3 AND SEC 1,2 PB PUSH IN ("OFF" LT OFF) 3. 아래 CB CLOSE 확인 FCPC STBY COM FCPC3 STBY MON FCSC2 FCSC1 STBY R20 FCPC3 R19 FCPC2 NORM T39 FCPC3 G77 FCPC1 STBY V42 FCSC1 NORM V41 FCPC1 NORM V38 FCSC2 STBY SPLY K69 FCDC C70 C69 D66 L76 4. EFCS BITE TEST 수행하라.(TASK 27-96-00-740-802) - MCDU 에 SIDE STICK POTENTIOMETER 에 관련된 FAULT DISPLAY - 만약 SIDE STICK POTENTIOMETER 에 관련된 많은 FAULT 들이 나타난다면 FAULT 들과 관련된 FCPC, FCSC 까지 점검할것. 5. TAKEOVER AND PRIORITY FUCTION TEST 수행(TASK 27-96-00-710-804) NOTE : PRIM1 또는 PRIM3 가 INOP 시 TEST 안됨. - ALL HYD ELEC PUMP ON NOTE : HYD PWR 없는상태에서도 TEST 할수있으나 이러한 ALTERNATIVE 방법을 사용 시에는 STEP 을 수행하기전 SEC1 AND 2 ENGAGE 후 FCSC가 PWR UP TEST 를 수행하는데 필요한시간 20S INTERVAL이 필요하다 - ECAM F/CTL KEY PUSH - 122 - ACTION RESULT 1) SEC1 PB RELEASE 하라 SEC1 PB "OFF" LT ON 2) PRIM2,3 SEC2 PB RELEASE 하라 PB "OFF" LT ON 3) CAPT SIDE STICK에 TAKEOVER & “PRIORITY LEFT" SOUND PRIORITY SW를 PUSH AND HOLD 하라. 412VU 에 PRIORITY/FO RED ARROW LT ON 4) TAKEOVER & PRIORITY SW RELEASE RED ARROW LT "OFF" 5) F/O SIDE TAKEOVER & PRIORITY SW “PRIORITY LEFT" SOUND PUSH AND HOLD 하라. PRIORITY/FO RED ARROW LT ON 6) TAKEOVER & PRIORITY SW RELEASE RED ARROW LT "OFF" EWD 에 F/CTL SENSOR FAULT WARNING 이 없는지 확인하라. 7) PRIM1 PB SW RELEASE 하라 PRIM1 PB "OFF" LT ON 8) PRIM2 PB SW PUSH 하라 PRIM2 PB "OFF" LT OFF 9) 상기 ITEM C 항의 3~6을 CHECK 하라. 10) PRIM2 PB RELEASE 하라 PRIM2 PB "OFF" LT ON PRIM3 PB PUSH 하라 PRIM3 PB "OFF" LT OFF 11) 상기 ITEM C 항의 3~6을 CHECK 하라. 12) SEC1 PB PUSH SEC1 PB "OFF" LT OFF 13) PRIM3 PB RELEASE 하라 PRIM3 PB "OFF" LT ON 14) 상기 ITEM C 항의 3~6을 CHECK 하라. 15) SEC1 PB RELEASE 하라. SEC1 PB "OFF" LT ON 16) SEC2 PB PUSH 하라. SEC2 PB "OFF" LT OFF 17) 상기 ITEM C 항의 3~6을 CHECK 하라. 18) EFCS GRD SCNNING BITE TEST 수행하라. 19) A/C 원상하라. 6. 관련된 FCPC1 또는 3 DEACTIVE (TASK 27-93-00-040-801 OR 27-93-00040-802) (MEL 27-93-01-A) or MEL 27-93-01-C) 의 FCPC 1,3 DEACTIVE 절차 참조) - 123 - ※ 매 FLIGHT 전 FCPC1 또는 3 의 관련 SIGNAL CHECK 하고 다른 2개의 PRIM 와 BOTH SEC' 와 ALL SIDE STICK POTENTIOMETER SIGNAL 이 CORRECT 한지 확인후 결함나온 SW SIGNAL 관련 PRIM COMPUTOR 는 INOP 된 것으로 간주하여 DEACTIVE 한다. ● MMEL 27-92-06 PRIM SIDESTICK PRIORITY SWITCH SIGNAL ○ DEACTIVATION OF THE SIDE-STICK PRIORITY SWITCH (AMM 27-92-00-040-802) 1. ALL HYD POWER OFF 2. PRIM1,2,3 AND SEC 1,2 PB PUSH IN ("OFF" LT OFF) 3. 관련 CB CLOSE 확인 : R20, R19, T39, V42, V41, V38, C70, C69, D66, G77, K69 4. EFCS BITE TEST 수행하라.(TASK 27-96-00-740-802) - MCDU 에 SIDE STICK PRIORITY SW 에 관련된 FAULT DISPLAY - 만약 SIDE STICK PRIORITY SW 에 관련된 많은 FAULT 들이 나타난다면 FAULT 들과 관련된 FCPC, FCSC 까지 점검할것. 5. TAKEOVER AND PRIORITY FUCTION TEST 수행(TASK 27-96-00-710-804) (이전 PAGE MEL 27-92-05 절차 참조) 6. 관련된 FCPC1 또는 3 DEACTIVE (TASK 27-93-00-040-801 OR 27-93-00040-802) (MEL 27-93-01-A) or MEL 27-93-01-C) 의 FCPC 1,3 DEACTIVE 절차 참조) - 124 - 1) PRIM 1 PB 은 전체 FLIGHT 구간동안 OFF 해놓을것. 2) BOTH SEC 와 관계되는 모든 SIDE STICK XDUCER 는 정상으로 작동되어야함. 3) ALL SEC, SFCC, LGCIU, RA, ADIRU, PRIM 3 는 정상 작동해야 하며 4) 매 FLT 마다 SIDESTICK FUNCTION CHECK 필요 5) PRIM1 & 2 와 관련된 STAB ACT ELEC MTR 들은 정상작동 되어야 함. 6) 각 FLIGHT 전마다 PRIM 와 SEC 에 의해 작동되는 ELEVATOR CONTROL CHECK. 7) AMM 27-34-00-710-801 OPER' TEST OF THE ELEV & HYD ACTUATION 수행 8) FLT CREW 적용사항으로 TWO PAIR OF SPOILER (SURFACE1 & 2 ) INOP' PENALTIES 를 적용하라. (MEL 02-27-93-01-C) - 125 - 9) MEL 적용후 첫 번째 DISPATCH 시 FCPC3 SECOND ELEC POWER SUPPLY CHECK (AMM 27-96-00-710-814) ※ 해당 SPOILER 의 DEACTIVATION 은 필요치 않음. ● MMEL 27-93-01-A) PRIM1 ○ DEACTIVATION OF THE FLIGHT CONTROL PRIMARY COMPUTER 1 (FCPC) (AMM 27-93-00-040-801) 1. HYD SYS DEPRESS' 2. PRIM1,2,3 SEC1,2 PB PUSH하라 ("OFF" LT OFF, PRIM1 는 "FAULT" LT ON 된다.) 3. RUDDER TRIM "ZERO" 에 있나 확인하라. 4. CB CLOSE 확인 (ADIRU, FLT CTL 관련 CB) : G04, L14, M05, R20, R19, X14, X13, E46, H46, L32, T43, T42, T39, U38, V42, V41, V40, V38, C70, C69, D66, G76, G75, K72, K69, L76, L63, L62, L61, N75, P64 5. FCPC1을 처음 DEACTIVE 한후 매 FLIGHT 전 STEP 4)~29) 항까지 수행할것. 1) PFR 에 다음 MSG 있는지 확인 - LB ELEVATOR SERVOCTL MODE XDCR (3CS1) in Class 1 - RY ELEVATOR SERVOCTL MODE XDRC (3CS1) in class 1 - FCPC1/WRG:L B ELEV SERVO MODE XDCR in class 1 - FCPC1/WRG:R Y ELEV SERVOCTL MODE XDCR in class 1 - FCSC1/WRG:L B ELEV SERVO MODE XDCR in class 3 - FCSC1/WRG:R Y ELEV SERVOCTL MODE XDCR in class 3. 2) EFIS (SYSTEM TEST) BITE TEST 수행하라. - MCDU 에 아래와 관련된 MAINT IND (CLASS1) 이 없어야한다. • FCSC(3CE1,3CE2) 와 관련된 SIDE STICK TRANDUCER UNIT (4CE1, 4CE2, 4CE3, 4CE4) 3) FCPC 3 POWER SUPPLY OPERATION TEST 수행 (AMM 27-96-00-710-814) - PRIM1,2 와 SEC1,2 PB RELEASE ('OFF' LT ON) - PRIM3 는 PUSH IN ('FAULT' AND 'OFF' LT OFF) - ADIRU 3 'NAV' 나머지 1 & 2 는 ‘OFF' - SWITCHING PNL 의 AIR DATA SW 를 CAPT/ON 3 POS 에 놓을것. - FLIGHT CONFIGURATION PRECAUTION 수행 (AMM 32-00-00-860-804) - 관련 CB CLOSE 확인 : W56, R20, R19, S43, V42, V38 - ADR3 의 INTERFACE TETST 수행 (AMM 34-13-00-740-801) NOTE : YES KEY PUSH 하지 말것. ACTION RESULT ① MCDU SYSTEM REPORT/TEST 'NAV:ALTITUDE' PAGE 접근 ② ADR3 KEY PUSH → OUTPUT TESTS PUSH → INTERFACE TEST PUSH ③ NEXT PAGE FUNCTION KEY PUSH 하여 2/2 PAGE 로 이동 - 0~5초사이 • ADR 3 PB 에 'FAULT' & 'OFF' LT ON 되었다 OFF ④ START TEST PUSH • PFD : SPEED 와 ALT SCALE 의 SYMBOL 이 사라짐 'SPD' & 'ALT' FLAG 가 수초동안 FLASH 함. - 126 - ACTION ④ START TEST PUSH RESULT • ND : TAS ‘0’ 지시 • MW & CRC - 5~10초사이 • WARINING 들이 사라짐 • SPEED & ALT INCREASE 됨 • V/S 600ft/mn 까지 INCREASE - 10초 이상 • PFD : CAS '367KTS', MACH '0.66M', ALT '10000ft' V/S '0ft/mn' • ND : TAS '433KTS' • SD : TAT +35 ℃, SAT +10℃ • EWD : 'OVERSPEED VMO/MMO 330/.86' 'OVERSPEED VLE 250/.55' (FLAP/SLAT LEVER POS 에 따라 다음 MSG 가 나옴) LEVER POS' MSG 0 OVERSPEED VFE 240 1 OVERSPEED VFE 215 2 OVERSPEED VFE 196 3 OVERSPEED VFE 186 FULL OVERSPEED VFE 180 NOTE : ALT DISCREPANCY 에 의한 WARNING 은 무시할것. - G,B HYD ELEC PUMP ON - PFD 에 CAS : 367KTS. ALT : 10000ft 지시하는지 확인 - PITCH TRIM CONTROL WHEEL 10 UP POS 으로 움직임 - CB TR2 NORM 3PU2 (W56) OPEN 후 바로(5초이내) CLOSE • G & B HYD PWR 가 계속 PRESSURIZED • MIN 15S 동안 PTCH TRIM WHEEL 을 MONITOR 하여 WHEEL 이 움직이지 않아야 된다. (HYD PWR 가 DEPRESS' 되면 GROUND CART 사용하여 다시 TEST 수행) • EWD 의 WARNING 은 무시할것. - PITCH TRIM CONTROL WHEEL 0 POS 으로 움직임 - G,B HYD ELEC PUMP OFF - CB FCPC3 STBY MON 7CE5 (R19) OPEN - CB ECMU2 2PP SNSG 9XM (S43) OPEN • PRIM3 PB 에 ‘FAULT’ LT ON 되었다가 7S 후에 OFF 됨. • EWD : 'F/CTL PRIM3 FAULT' MSG 나왔다가 7S 후에 OFF 됨. (만약 FAULT 가 계속 남았다면 PRIM3 PB RESET 할것) - CB FCPC3 STBY MON 7CE5 (R19) CLOSE - CB ECMU2 2PP SNSG 9XM (S43) CLOSE - CB FCPC3 7CE3 (V42), FCPC3 7CE4 (V38) OPEN • PRIM3 PB 에 'FAULT' LT ON - PFD 에 CAS : 367KTS. ALT : 10000ft 지시하는지 확인 - CB ECMU2 2PP SNSG 9XM (S43) OPEN - CB FCPC3 7CE3 (V42), FCPC3 7CE4 (V38) CLOSE • PRIM3 PB 에 'FAULT' LT OFF • EWD : 'F/CTL PRIM3 FAULT' MSG 없어짐 (만약 FAULT 가 계속 남았다면 PRIM3 PB RESET 할것) - MCDU에서 TEST 끝난 다음 ‘YES' KEY PUSH → TEST OK DISPLAY - 127 - - 3) 항 TEST 동안 진행되었던 사항 원상시킬것. 4) ALL HYD ELEC PUMP ON 5) PRIM1 과 SEC1 PB RELEASE - 'OFF' LT ON 6) PRIM3 와 SEC2 PB RELEAE - 'OFF' LT ON 7) CAPT & F/O SIDE 각각 아래사항 TEST하라. SD F/CTL - SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 4 ARROW EXTEND - LH INBD AILERON INDEX MOVE DOWN - SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL - SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 4 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN - SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN - SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 - SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 8) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 5S 후 PTCH TRIM WHEEL 이 약 4° UP 으로 9) PRIM2 PB RELEASE AND PUSH 하라. TURN & STOP된다. 10) SEC1 PB PUSH - 'OFF' LT OFF 11) PRIM2 PB RELEASE 하라. - 'OFF' LT ON 12) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL - RH INBD AILERON INDEX MOVE UP ① SIDE STICK을 RH방향으로 STOP TOUCH - RH SPOILER 6 ARROW EXTEND 될 때까지 움직여라 - LH INBD/OUTBD AILERON INDEX MOVE DOWN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL - LH INBD/OUTBD AILERON INDEX ③ SIDE STICK을 LH방향으로 STOP TOUCH MOVE UP 될 때까지 움직여라 - LH SPOILER 6 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 13) SIDE STICK 과 PEDAL 이 중립위치에 있는지 확인하라. AILERON, ELEV' SURFACE IND가 진동이 없 14) 10S 기다려라 나 확인하라. - 128 - 15) PRIM2, SEC2 PB PUSH 하라. - 'OFF' LT OFF 16) SEC1 RELEASE - 'OFF' LT ON 17) SIDE STICK 과 PEDAL 이 중립위치에 있는지 확인하라. 18) 10S 기다려라 RUDDER SURFACE IND 가 진동이 없나 확인 19) PRIM2 PB RELEASE - 'OFF' LT ON 20) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL - RH INBD/OUTBD AILERON INDEX ① SIDE STICK을 RH방향으로 STOP TOUCH MOVE UP 될 때까지 움직여라 - RH SPOILER 3 ARROW EXTEND - LH INBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL - LH INBD AILERON INDEX MOVE UP ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH SPOILER 3 ARROW EXTEND 될 때까지 움직여라 - RH INBD/OUBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 21) CAPT & F/O S/STICK이 중립에 있나 확인하라. 22) 10S 기다려라 AIL, ELEV SURFACE IND가 진동이 없나 확인 23) SEC2 PB RELEASE 하라. - 'OFF' LT ON 24) PRIM3 PB PUSH 하라. - 'OFF' LT OFF 25) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH OUTBD AIL INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 2 ARROW EXTEND - LH OUTBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH OUTBD AIL INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 2 ARROW EXTEND - RH OUTBD AIL INDEX MOVE DN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN 26) PITCH TRIM WHEEL을 8 UP POS 에 놓아라. - 5S 후 PITCH TRIM WHEEL 이 4UP 으로 27) PRIM3 PB RELEASE AND PUSH 하라. 오게됨 28) SEC1 PB PUSH - 'OFF' LT OFF 29) PRIM2 & SEC2 PB을 PUSH하라. - PRIM1 & SEC1 "OFF" LT OFF 6. SD F/CTL PAGE : NO.5 SPOILER AMBER 지시 STATUS PAGE INOP SYS : PRIM1, PART SPLRS 7. PRIM1 PB 에 INOP TAG 부착 8. 항공기 원상 - 129 - 1) PRIM 3 PB 은 전체 FLIGHT 구간동안 OFF 해놓을것. 2) BOTH SEC 와 관계되는 모든 SIDE STICK XDUCER 는 정상으로 작동되어야함. 3) ALL SEC, SFCC, LGCIU, RA, ADIRU, PRIM 1 은 정상 작동해야 하며 4) PRIM1 & 2 와 관련된 STAB ACT ELEC MTR 들은 정상작동 되어야 함. 5) FLT CREW 적용사항으로 TWO PAIR OF SPOILER (SURFACE1 & 2 ) INOP' PENALTIES 를 적용하라. (MEL 02-27-93-01-C) ※ 해당 SPOILER 의 DEACTIVATION 은 필요치 않음. ● MMEL 27-93-01-C) PRIM 3 ○ DEACTIVATION OF THE FLIGHT CONTROL PRIMARY COMPUTER 3 (FCPC3) (AMM 27-93-00-040-802) 1. HYD SYS DEPRESS' 2. PRIM1,2,3 SEC1,2 PB PUSH하라 ("OFF" LT OFF, PRIM3 는 "FAULT" LT ON 된다.) 3. RUDDER TRIM "ZERO" 에 있나 확인하라. 4. CB CLOSE 확인 (ADIRU, FLT CTL 관련 CB) : G04, L14, M05, R20, R19, X14, X13, E46, H46, L32, T43, T42, T39, U38, V42, V41, V40, V38, C70, C69, D66, G76, G75, K72, K69, L76, L63, L62, L61, N75, P64 1) EFIS (SYSTEM TEST) BITE TEST 수행하라. MCDU 에 아래와 관련된 MAINT IND (CLASS1,23) 이 없어야한다. - FCSC(3CE1,3CE2) 와 관련된 SIDE STICK TRANDUCER UNIT (4CE1,4CE2,4CE3,4CE4) - FCPC1 & 2 (2CE1,2CE2) - FCSC1 & 2 (3CE1,3CE2) - LGCIU1 & 2 (5GA1,5GA2) - RA1 & 2 (1SA1,1SA2) - ADIRU1,2 & 3 (1FP1,1FP2,1FP3) - SFCC1 & 2 (21CV,22CV) 2) ALL HYD ELEC PUMP ON 3) PRIM 2,3 AND SEC1,2 PB RELEASE - “OFF" LT ON 4) CAPT & F/O SIDE 각각 아래사항 TEST하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP - RH SPOILER 5 ARROW EXTEND 될 때까지 움직여라 - LH INBD AILERON INDEX MOVE DOWN - 130 - ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 5 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 5) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 5S 후 P/RIM WHEEL 이 약 4° UP 으로 6) PRIM1 PB SW를 RELEASE AND PUSH TURN & STOP된다. 7) PRIM2 PB PUSH 하라. PRIM2 "OFF" LT OFF 8) PRIM1 PB SW를 RELEASE 하라. PRIM1 "OFF" LT ON 9) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 4 ARROW EXTEND - LH INBD AILERON INDEX MOVE DOWN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 4 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 10) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 11) PRIM2 PB SW를 RELEASE AND PUSH 5S 후 P/RIM WHEEL 이 약 4° UP 으로 하라. TURN & STOP된다. 12) SEC1 PB PUSH 하라. SEC1 "OFF" LT OFF 13) CAPT & F/O S/STICK이 중립에 있나 확인하라. RUDDER SURFACE IND가 진동이 없나 14) 10S 기다려라 확인하라. 15) PRIM2 PB SW를 RELEASE 하라. PRIM2 "OFF" LT ON 16) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 6 ARROW EXTEND - LH INBD & OUTBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN - 131 - SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 6 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 17) CAPT & F/O S/STICK이 중립에 있나 확인하라. AIL, ELEV SURFACE IND가 진동이 없나 18) 10S 기다려라 확인하라. 19) SEC2 PB PUSH 하라. SEC2 "OFF" LT OFF 20) SEC1 PB SW를 RELEASE 하라. SEC1 "OFF" LT ON 21) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD & OUTBD AIL INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 3 ARROW EXTEND - LH INBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD & OUTBD AIL INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 3 ARROW EXTEND - RH INBD & OUTBD AIL INDEX MOVE DN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 22) CAPT & F/O S/STICK이 중립에 있나 확인하라. AIL, ELEV SURFACE IND가 진동이 없나 23) 10S 기다려라 확인하라. 24) PRIM2 PB PUSH 하라. SEC2 "OFF" LT OFF RUDDER SURFACE IND가 진동이 없나 25) 10S 기다려라 확인하라. 26) PRIM1 & SEC1 PB을 PUSH하라. PRIM1 & SEC1 "OFF" LT ON NOTE : DEACTIVATE 된 FCPC3 와 관련된 SPOILER는 작동하지 않을것이다. 27) PRIM3 에 INOP NO RESET NOTICE 부착하라. 28) A/C 원상하라. - 132 - 1) SEC 1 PB 은 전체 FLIGHT 구간동안 OFF 해놓을것. 2) SEC 2 와 관계되는 모든 SIDE STICK XDUCER 는 정상으로 작동되어야함. 3) ALL PRIM, SFCC, LGCIU, RA, ADIRU 는 정상 작동해야 하며 4) FCDC 2 와 FWC 2 또한 NORMAL 이어야한다. 5) FLT CREW 적용사항으로 ONE PAIR OF SPOILER INOP' PENALTIES 를 적용하라. ※ 해당 SPOILER 의 DEACTIVE 는 필요치 않음 (DEACTIVATE FCSC1 과 관련된 SPOILERS 는 작동되지않음.) ● MMEL 27-94-01-A) SEC 1 ○ DEACTIVATION OF THE FLIGHT CONTROL PRIMARY COMPUTER 3 (FCPC3) (AMM 27-94-00-040-801) 1. HYD SYS DEPRESS' 2. PRIM1,2,3 SEC1,2 PB PUSH하라 ("OFF" LT OFF, SEC 1 은 "FAULT" LT ON 된다.) 3. RUDDER TRIM "ZERO" 에 있나 확인하라. 4. CB CLOSE 확인 (ADIRU, FLT CTL 관련 CB) : G04, L14, M05, R20, R19, X14, X13, E46, H46, L32, T43, T42, T39, U38, V42, V41, V40, V38, C70, C69, D66, G76, G75, K72, K69, L76, L63, L62, L61, N75, P64 1) EFIS (SYSTEM TEST) BITE TEST 수행하라. MCDU 에 아래와 관련된 MAINT IND (CLASS1,23) 이 없어야한다. - FCSC(3CE1,3CE2) 와 관련된 SIDE STICK TRANDUCER UNIT (4CE1,4CE2,4CE3,4CE4) - FCPC1,2,3 (2CE1,2CE2,2CE3) - SFCC1 & 2 (21CV,22CV) - LGCIU1 & 2 (5GA1,5GA2) - RA1 & 2 (1SA1,1SA2) - FCDC 2 & FWC 2 - ADIRU1,2 & 3 (1FP1,1FP2,1FP3) 2) ALL HYD ELEC PUMP ON 3) PRIM 2,3 AND SEC1,2 PB RELEASE - “OFF" LT ON 4) CAPT & F/O SIDE 각각 아래사항 TEST하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP - RH SPOILER 5 ARROW EXTEND 될 때까지 움직여라 - LH INBD AILERON INDEX MOVE DOWN - 133 - ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 5 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD → RELEASE ELEV INDEX MOVE UP → NEUTRAL → → FORWARD 로 움직여라 MOVE DOWN ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 5) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 5S 후 P/RIM WHEEL 이 약 4° UP 으로 6) PRIM1 PB SW를 RELEASE AND PUSH TURN & STOP된다. 7) PRIM2 PB PUSH 하라. PRIM2 "OFF" LT OFF 8) PRIM1 PB SW를 RELEASE 하라. PRIM1 "OFF" LT ON 9) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 4 ARROW EXTEND - LH INBD AILERON INDEX MOVE DOWN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH INBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 4 ARROW EXTEND - RH INBD AILERON INDEX MOVE DOWN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 10) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 11) PRIM2 PB SW를 RELEASE AND PUSH 5S 후 P/RIM WHEEL 이 약 4° UP 으로 하라. TURN & STOP된다. 12) PRIM3 PB PUSH, PRIM2 PB RELEASE. PRIM3 "OFF" LT OFF, PRIM2 "OFF" LT ON 13) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH OUTBD AILERON INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 2 ARROW EXTEND - LH OUTBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - LH OUTBD AILERON INDEX MOVE UP 될 때까지 움직여라 - LH SPOILER 2 ARROW EXTEND - RH OUTBD AIL INDEX MOVE DN ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN - 134 - 14) PTCH TRIM CTL WHEEL을 NOSE UP 8° 움직여라 15) PRIM3 PB SW를 RELEASE AND PUSH 5S 후 P/RIM WHEEL 이 약 4° UP 으로 하라. TURN & STOP된다. 16) SEC2 PB PUSH, PRIM3 PB RELEASE SEC2 "OFF" LT OFF, PRIM3 "OFF" LT ON 17) CAPT & F/O SIDE 각각 아래 사항을 TEST 하라. SD F/CTL ① SIDE STICK을 RH방향으로 STOP TOUCH - RH INBD & OUTBD AIL INDEX MOVE UP 될 때까지 움직여라 - RH SPOILER 3 ARROW EXTEND - LH INBD AIL INDEX MOVE DN ② SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN SD F/CTL ③ SIDE STICK을 LH방향으로 STOP TOUCH - RH INBD & OUTBD AIL INDEX MOVE DN 될 때까지 움직여라 - LH SPOILER 3 ARROW EXTEND - LH INBD AIL INDEX MOVE UP ④ SIDE STICK을 RELEASE 하라. AIL GO BACK TO NEUTRAL & SPOILER DN ⑤ SIDE STICK을 REARWARD 로 STOP ELEV INDEX MOVE UP TOUCH 될 때까지 움직여라 ⑥ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL ⑦ SIDE STICK을 FWD 로 STOP TOUCH 될 ELEV INDEX MOVE DOWN 때까지 움직여라 ⑧ SIDE STICK을 RELEASE 하라. ELEV INDEX NEUTRAL 18) PRIM1 PB PUSH PRIM1 "OFF" LT OFF 24) PRIM2,3 PB PUSH 하라. PRIM2,3 "OFF" LT OFF 5. SD F/CTL PAGE : NO.6 SPOILER AMBER, LH OUTBD AILERON 의 G SYMBOL 에 AMBER BRACKET 지시 6. STATUS PAGE INOP SYS : CAT3 DUAL, SEC1, RUD TRIM1, RUD TRV LIM1 지시 7. SEC1 PB 에 INOP TAG 부착후 항공기 원상. - 135 - ● MMEL 27-95-01 FCDC ○ DEACTIVATION OF THE FCDC2 (AMM 27-95-00-040-801) 1. OVHD RESET SW PANEL 에서 FCDC2 RESET SW 를 PULLING 하라. 2. TRAVEL LIMITING ACTUATING OPERATION TEST 수행하라. (AMM 27-23-00-710-802) - PRIM1, SEC1 PB PUSH ("OFF" LT OFF) - PRIM2 & 3 PB RELEASE("OFF" LT ON) 하고 SEC2 PB SW PUSH("OFF" LT OFF) 하라. - ADR3 SEL SW를 'NAV' POS 에두고 ADR1,2 는 'OFF' POS 에 두라. - SWITCHING PANEL 135VU 에 AIR DATA SEL SW 를 CAPT/ON3 에 SET 하라. - CENTER PEDESTAL 에 RUD TRIM "ZERO" 확인하라. - "G" HYD SYS ELEC PUMP ON 하라. - 관련 CB CLOSE 확인 : T41, T39, C70, D67, D66, E70, G77 - OPER TEST OF RTLU, PTLU (NOTE : TEST 동안의 WARNING 은 무시하라.) 1) SEC2 PB을 RELEASE 하라 “OFF" LT ON 2) ADIRU3 CAS DYNAMIC SLEW TEST PAGE를 열어라. (SYSTEM REPORT TEST → NAV:ALTITUDE → ADR3 → OUTPUT TESTS → SLEW TESTS → CAS DYNAMIC SLEW) 3) SLEW TEST PAGE 에 '050/400 KTS'. '100 KTS/MIN' 을 입력하라. - PFD : SPEED SCALE 은 SPEED SEL 에 따라 움직인다.(50KTS→400KTS) 4) UP START SLEW LINE KEY 를 PUSH. - SD F/CTL PAGE : TRAVEL LIMITATION SMMETRICAL INDEXES 가 CLOSED POS 으로 움직인다. - CAPT OR F/O SIDE PEDAL TRAVEL LIMIT 5) CAPT OR F/O SIDE 에 RH PEDAL 유지됨 PUSH 하고나서 LH PEDAL을 PUSH - SD F/CTL PAGE의 RUD IND POINT 는 하라. TRAVEL LIMITATION 의 SYMMETRICAL INDEXES 사이로 움직인다. 6) CAPT OR F/O SIDE에서 LH PEDAL을 RUD IND POINT 는 중립으로 돌아온다. RELEASE 하라 CAPT PFD 에 SPD SCALE은 INITIAL POS으 로 돌아가고 SD 의 RUD IND 은 TRAVEL 7) CAS DYNAMIC SLEW IND을 PUSH하라. LIMITATION SYMMETRIC INDEXES MAX OPEN POS 으로 움직인다. - 136 - 8) CAPT OR F/O SIDE에서 RH PDEAL PUSH 하고나서 LH PEDAL PUSH 하라 9) LH PEDAL을 RELEASE 하라 10) SEC2 PB PUSH 하라 11) SEC1 PB RELEASE 하라 RUD IND POINT는 LH & RH 로 MAX POS 으로 움직임 RUD 중립으로 옴 "OFF" LT OFF “OFF" LT ON SPD SCALE이 SELECTION SPEED 로 움직이 12) UP-START SLEW PUSH 고 TRAVEL LIMITATION SYMMETRIC INDEX 가 닫힌 POS으로 움직인다. PEDAL TRAVEL은 LIMIT 유지하고 RUD IND 13) RH PEDAL PUSH 하고나서 LH PEDAL POINT는 SYMMETRICAL INDEXES 사이로 움 PUSH 하라. 직인다. 14) LH PEDAL RELEASE 하라 RUD IND POINT는 중립으로 온다. SPD SCALE은 INITIAL POS으로 오고 RUD 15) RETURN KEY PUSH 하라. SYMMETRICAL INDEX MAX OPEN POS으로 움직임 16) MCDU MANU PAGE가 나올때까지 RETURN/STOP KEY를 PUSH하라. 17) PEDAL을 LH & R H PUSH 했을때 RUD MAX 로 움직임 18) PEDAL을 RELEASE 하고 SEC1 PB SEC1 "OFF" LT OFF PUSH 하라. 3. 항공기 원상하라. - 137 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA28) ● MMEL 28-23-01 CORSSFEED VALVE ○ DEACTIVATION OF CROSSFEED VALVE (AMM 28-23-00-040-801) 1. CB OPEN : XFEED VLV MOT2 2QE (Q44), XFEED VLV MOT1 1QE (B66) 2. MCDU SYSTEM REPORT/TEST FUEL → FCMC 1 or 2 → FUEL VALVES TEST → START TEST • ON A/C 001-099 : - OUTER TANK INLET V/V 와 INNER TANK INLET V/V 가 정상정으로 OPEN/CLOSE 되는지 확인. • ON A/C 101-199 : - CENTER TANK TRANSFER PUMP 의 OPERATION CHECK 수행하여 NORMAL 상태인 지 확인 - SD FUEL PAGE 확인하여 ALL FUEL QTY 가 정상인지 확인 (AMBER '=' 가 없어야함.) 3. CROSS FEED V/V ACTUATOR (300QE) 의 VISUAL IND' 를 통해서 OPEN 또는 CLOSE 상태인지 확인 후 ACTUATOR REMOVE (O-RING 은 REMOVE 하지말것.) 4. DUMMY PLUG (5) 를 분리된 NO.1 MOTOR ELEC CONNECTOR 에 연결 5. RECEPTACLE (6) 를 분리된 NO.2 MOTOR ELEC CONNECTOR 에 연결 NOTE : DUMMY PLUG SET (99F28304000000) 에 DUMMY PLUG (98F283040000040) (5) 와 RECEPTACLE (NSA938004-10) (6) 이 포함되어있음. 6. 분리된 2개의 CABLE 은 SAFETY 조치하라. 7. CROSSFEED V/V 가 OPEN 되어있을경우, APPLICABLE TOOL 을 사용하여 V/V를 FULLY CLOSE 하라. 만약 FULLY CLOSE 가 안될 경우 V/V 교환할 것. - 138 - 8. V/V LOCKING TOOL (T720456) (2) 의 DOWEL 과 LOCK-KEY 부분을 V/V DRIVE ASSY 에 ALIGN 시켜서 ENGAGE 하라. (DOWEL 이 LOOSE 되면 TOOL 이 안좋은것임.) 9. V-BAND CLAMP (3)을 11.5 lbf.in 로 TORQUE 하라. 10. OPEN 되었던 CB CLOSE 하고 항공기 원상. - 139 - (O) : T, TANK FEED SEL ……… ISOL • CG CONTROL은 되지 않고 • FUEL CONSUMPTION 은 1% 증가 • OPERATOR 는 T/O CG 를 결정하기 위한 PROCEDURE 를 확립하여야한다. 1) TRIM TANK 속에 연료가 없거나 아니면 TRIM TANK 에 있는 연료가 사용되어지지 않고 그것 이 ZFW 의 한부분으로 계산되어져 CG 결정을 위해 고려 되었다면 INNER INLET V/V 는 CLOSE POS 에서 작동 되지않아도 된다. ● MMEL 28-25-04-A) INNER TANK INLET VALVE ○ DEACTIVATION OF THE INNER TANK INLET V/V 5603QA1(5603QA2) IN THE CLOSE POS' (AMM 28-25-00-040-806) 1. TOOL : ACT ALL MECHNICAL (D97B00-003) 2. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 3. FUEL SYS 작동과 REFUELING 금지. 4. MLG DOOR OPEN 하라. (LH : 5603QA1, RH : 5603QA2) 5. CB OPEN 하라. : L INR TK INLET V/V (8QL1/R12), R INR TK INLET V/V (8QL2/M64) 6. DEAVTIVATION OF THE INR TK INLET V/V - ACT를 장탈하라. - 장탈된 ELEC CONNETOR 를 DUMMY PLUG (99F28304001000) 에 장착하고 SAFETY 조치하라. - ACT MECHANICAL (D97B00-003) 을 STUDS (1) 에 NUTS (5) 로써 장착하라. - CONNECT THE BONDING STRAP WITH THE BOLT (4) AND THE NUT (2) - ACT MECHANICAL (1) 의 CONT KNOB 를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하라. (NOTE : INNER TK INLET V/V 를 CLOSE 할수없을 경우 V/V 를 교환하여 야한다.) 7. OPEN 되었던 CB CLOSE 하고 항공기 원상. 8. OPER' TEST INNER TK XFR V/V ACT (AMM 28-51-00-710-801) ● MCDU (EFF 001~099) SYS REPORT/TEST FUEL PAGE → FCMC1 → FUEL V/V TEST (만일 FCMC 1 이 SLAVE 이면 RETURN KEY 로 FUEL PAGE까지 나가서 FCMC 2 MAIN MANU 사용) → START TEST → CONFIRM START OF TEST → 해당 V/V OPEN 또는 SHUT LINE KEY - 140 - PUSH 하여 TEST ● MCDU (EFF 101~199) SYS REPORT/TEST FUEL PAGE → FCMC1 → FUEL V/V TEST → CONTINUE PUSH → 해당 V/V OPEN 또는 SHUT LINE KEY PUSH 하여 TEST P/N:D97B00-003 - 141 - ● MMEL 28-25-04-B) CENTER TANK INLET VALVE ○ DEACTIVATION OF THE CENTER TANK INLET V/V 5501QA IN THE CLOSED POSITION (AMM 28-25-00-040-801) 1. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 2. FUEL SYS 작동과 REFUELING 금지. 4. LH MLG DOOR OPEN 하라. 5. CB OPEN 하라. : FUEL CTR TK (12QU/K38) 6. DEAVTIVATION OF THE CTR TK INLET V/V - ACT를 장탈하라. - ELEC CONNECTOR에 DUMMY PLUG (99F28304001000) 연결 - ACT MECHANICAL (D97B00-003) 장착하라. - CONNECT THE BONDING STRAP WITH THE BOLT (4) AND THE NUT (2) - ACT MECHANICAL (1) 의 CONT KNOB를 V/V CLOSE를 위해 SHUT POS 으로 TURN 하고 LOCK하라. (NOTE : CENTER TANK INLET V/V 를 CLOSE 할수없을 경우 V/V 를 교환 하여야한다.) 7. OPEN 되었던 CB CLOSE 하고 항공기 원상. PN : D97B00-003 - 142 - COCKPIT PREPARATION (CREW) (O) 1. CG CONTROL은 되지 않고 2. FUEL CONSUMPTION 은 1% 증가 3. OPERATOR 는 T/O CG를 결정하기 위한 PROCEDURE 를 확립하여야한다. 2) TRIM TANK 속에 연료가 없거나 아니면 TRIM TANK 에 있는 연료가 사용되어지지 않고 그것 이 ZFW 의 한부분으로 계산되어져 CG 결정을 위해 고려되었다면 INNER INLET V/V 는 CLOSE POS 에서 작동 되지않아도 된다. ● MMEL 28-25-04-C) TRIM TANK INLET VALVE ○ DEACTIVATION OF THE TRIM TANK INLET V/V 5705QA IN THE CLOSED POSITION (AMM 28-25-00-040-808) 1. TOOL : ACT ALL MECHNICAL(D97B00-003) 1EA PIN-SIDE STICK LOCKING (98D27903500000) 2EA DUMMY PLUG (99F28304001000) 2. EELV & HOR' STAB' SAFETY 조치하라. - CAPT & F/OI SIDE STICK 에 PIN-S/STICK LOCKING을 장착하라. - PTCH TRIM 작동 하지않도록 TAG 부착 - PRIM2,3 & SEC2 PB RELEASE 하라. 3. FUEL SYS 작업시 SAFETY PROCEDURE를 지켜라. 4. FUEL SYS 작동과 REFUELING 금지. 5. THS COMPARTMENT ACCESS DOOR 312AR OPEN 6. CB OPEN : TRIM TK INLET V/V (8QN1/M61) 7. DEACTIVATION OF THE TRIM TANK INLET V/V - ACT를 장탈하라. (NOTE : ELEC CONNECTOR (1) 에 DUMMY PLUG를 장착하라. APU OPERATION 을 확실히 하기위해서임.) - 장탈된 ELEC CONNETOR (1) 를 SAFETY 조치하라. - ACT MECHANICAL (D97B00-003) 장착 (두가지 TYPE 이 있음) - ACT MECHANICAL (D97B00-003) AMENDMENT TOOL 일 경우 • ACT MECHANICAL (D97B00-003) (AMENDMENT) (9) 을 NUT (8) & WASHER (7) 로 장착하라. 이때 FULLY TIGHT 하지말것. • BONDING STRAP 을 연결하라. : (2),(3),(4),(5),(6) 연결 • ACT MECHANICAL 의 CONT KNOB를 V/V CLOSE를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. NUT (8) 을 FULLY TIGHT 할것. (NOTE : TRIM TK INLET V/V 를 CLOSE 할수없을 경우 V/V 를 교환하여야한다.) - 143 - - ACT MECHANICAL (D97B00-003) 일 경우 • 필요시 TRIM TANK DEFUEL 하라. • INLET V/V 에서 NUT (9), WASHER (10) 을 REMOVE • ACT MECHANICAL (D97B00-003) (AMENDMENT) (11) 을 NUT (8) & WASHER (7) 로 장착하라. • BONDING STRAP 을 연결하라. : (2),(3),(4),(5),(6) 연결 • ACT MECHANICAL 의 CONT KNOB를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하고 LOCK 하라. (NOTE : TRIM TK INLET V/V를 CLOSE 할수없을 경우 V/V를 교환 하여야한다.) 8. OPEN 되었던 CB CLOSE 하고 항공기 원상. D97B00-003 D97B00-003 AMENDMENT - 144 - 1) 관련 OUTER TANK 가 FULL 이고 2) UNUSABLE FUEL 로 간주되며 3) 관련 OUTER TO INNER TRANSFER V/V 가 작동해야함. ● MMEL 28-25-04-D) OUTER TANK INLET VALVE ○ DEACTIVATION OF THE OUTER TANK INLET V/V 5500QA1(5500QA2) IN THE CLOSED POSITION (AMM 28-25-00-040-807) 1. TOOL : ACT ALL MECHNICAL(D97B00-003), DUMMY PLUG (99F28304001000) 2. FUEL SYS 작업시 SAFETY PROCEDURE를 지켜라. - 145 - 4. FUEL SYS 작동과 REFUELING 금지. 5. ACCESS PNL REMOVE : 574FB (5500QA ), 674FB (5500QA2) 574FB(674FB) 6. CB OPEN : REFUEL R OUTR TK 1QU2 (R14), REFUEL L OUTR TK 1QU1 (R13), SFCC1 NORM 10CV (X14), SFCC2 FLAP 2CV (T43), SFCC1 FLAP 1CV (L61) 7. DEAVTIVATION OF THE OUTER TANK INLET V/V - ACT를 장탈하고 분리된 ELEC CONNETOR (5) 를 SAFETY 조치하라. - ACT MECHANICAL (D97B00-003) 을 NUT (2) 로 장착하라. - BONDING STRAP 을 연결하라. : (3),(4),(6) 연결 - ACT MECHANICAL 의 CONT KNOB 를 V/V CLOSE를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. (NOTE : OUTER TANK INLET V/V 를 CLOSE 할수없을 경우 V/V를 교환하여야한다.) - ELEC CONNECTOR (5) 에 DUMMY PLUG (9828304001000) 장착하라 8. REMOVE 하였던 ACCESS PNL 장착. 9. OPEN 되었던 CB CLOSE 하고 항공기 원상. - 146 - ● MMEL 28-25-05 REFUEL ISOLATION V/V ○ DO THE GRAVITY OVERWING REFUEL PROCEDURE (AMM 28-25-00-040-809) 1. AMM 12-11-28-650-805 OVERWING REFUEL 수행 2. FUEL SAFETY PROCEDURE를 지켜라. 3. PARKING BRAKE SET 확인. 4. 항공기 NOSE & MAIN TIRE 의 CHOCK 를 TIRE 로부터 조금 떨어뜨려놀것. (REFUEL 동 안 MLG 가 COMPRESS 되면 NOSE TIRE 가 뒤로 구르게되고, CHOCK 가 TIRE 에끼게됨.) 5. ADIRU 1,2,3 'NAV' POS' 6. SLAT RETRACT 되었는지 확인. NOTE : LH 또는 RH WING 또는 LH/RH 동시에 모두 OVERWING REFUEL 이 가능하다. 7. OVERWING REFUEL CAP REMOVE (5508QA1, 5508QA2) 8. OVERWING REFUEL JOINT 에 FUEL NOZZLE을 통해 FUEL SVC' 9. INNTER TANK 에서 GROUND TRANSFER 하여 OTHER TANK 로 분배함. (OVERWING PROCEDURE 로 TRIM TANK FUEL FILLING 은 안됨.) 10. INNER TANK 에만 보급하므로 필요한 양만큼 보급시 GROUND FUEL SVC CAR 에서 FUELING 중단할것. NOTE : REFUEL 시 OVERFILL 되지 않도록 조심할것. OVERWING PROCEDURE 는 FUEL AUTO CUT OUT 이 안됨. 11. SVC 완료후 CAP (5508QA1, 5508QA2)을 ALIGN IND' 에 맞추어 정확히 장착할것. - 147 - ● MMEL 28-26-01 a) OUTER TO INNER TRANSFER VALVE (CLOSED POSITION) ○ DEACTIVATION OF THE INTER TANK TRANSFER V/V 5601QA1(5601QA2) IN THE CLOSE POSITION (AMM 28-26-00-040-809) NOTE : 이 정비절차는 INTER TANK XFR V/V 가 OPEN POS 일때만 적용된다. 1. TOOL : ACT ALL MECHNICAL(D97B00-003), DUMMY PLUG (99F28304001000) 2. FUEL SYS 작업시 SAFETY PROCEDURE를 지켜라. 3. SLAT 을 FULL EXTEND 하라. 4. CB OPEN 하라. : FUEL MAIN XFR R 6QL2 (B68), FUEL MAIN XFR L 6QL (B67) 5. ACCESS PNL 522RB (5601QA1), 622RB (5601QA2) 6. DEAVTIVATION OF THE INTER TK XFR V/V - ACT를 장탈하라. (NOTE : ELEC CONNECTOR (5) 에 DUMMY PLUG를 장착하라.) - ACT MECHANICAL (D97B00-003) (1)을 NUT (2) 와 함께장착하라. - BONDING STRAP (4)를 BOLT (3)와 NUT (6)로 장착하라. - ACT MECHANICAL 의 CONT KNOB를 V/V CLOSE를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라.. (NOTE : V/V를 CLOSE 할수없을 경우 V/V 를 교환하여야 하거나 MMEL 28-26-01 의 LIMIT 기준에 의하여 항공기 FLIGHT 할수있다. MMEL28-26-01b 적용) 7. REMOVE 하였던 ACCESS PNL 장착. 8. OPEN 되었던 CB CLOSE 하고 항공기 원상. - 148 - - 149 - ● MMEL 28-26-01 a) OUTER TO INNER TRANSFER VALVE (OPEN POSITION) ○ OUTER TO INNER TANK TRANSFER VALVE OPEN FAIL 시 MEL 적용 ※ A330 MEL 28-26-01 b) 검토사항 (MAINTENANCE TIP 05년 9월 A330-28-003 참조) 1. ECAM PROCEDURE 에의거 조치시 별도 (m) 사항 요구안됨 2. BOTH OUTER TANK EMPTY 시 Vmo 제한없음 - 최대 3 FLIGHTS 만 가능 (V/V CLOSE DEACTIVATE 시 계속비행가능) - XFR V/V CLOSE DEACTIVATION 절차 (TR01-28/01L) 3. 상기결함 발생시 조치사항 ① FCMC에서 XFR V/V CLOSE ② MAX ALLOWABLE WING FUEL IMBALANCE (FCOM 3.01.28) 적용하여 FUEL XFR 또는 REFUEL ③ ONE XFR V/V INOP IN OPEN POS 인 경우 조치 - ECAM PROCEDURE에 의거 OUT TK XFR SW ON 하여 V/V MAN OPEN 하여 BVOTH OUTR TK EMPTY 상태로 DISPATCH FUEL OUTR TO INR FAULT OUTR TK XFR...............ON ④ BOTH OUTER TANK EMPTY 시 제한사항 - STRUCTURE 보호 (BENDING RELIEF) 를 위해 3 FLIGHTS 로 제한 - MTOW 및 MZFW 제한 - Vmo 제한은 없음 - 150 - ● MMEL 28-27-01 TRIM TANK ISOLATION VALVE ○ DEACTIVATION OF THE TRIM TANK ISOLATION VALVE (AMM 28-27-00-040-803) 1. TOOL : ACT ALL MECHNICAL(D97B00-003) 1EA PIN-SIDE STICK LOCKING (98D27903500000) 2EA DUMMY PLUG (99F28304001000) 2. EELV & HOR' STAB' SAFETY 조치하라. - CAPT & F/OI SIDE STICK 에 PIN-S/STICK LOCKING을 장착하라. - PTCH TRIM 작동 하지않도록 TAG 부착 - PRIM 2,3 & SEC 2 PB RELEASE 하라. 3. FUEL SYS 작업시 SAFETY PROCEDURE를 지켜라. 4. FUEL SYS 작동과 REFUELING 금지. 5. THS COMPARTMENT ACCESS DOOR 312AR OPEN 6. CB OPEN : FUEL TRIM TK ISOL 5QN (B70) 7. DEACTIVATION OF THE TRIM TANK ISOLATION V/V - ACT 를 장탈하라. - ACT MECHANICAL (D97B00-003) 장착. (MASTER SPLINE 이 ALIGN 되어야함.) - BONDING STRAP 을 연결하라. : (2),(3),(4),(5) 연결 - ACT MECHANICAL 의 CONT KNOB 를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. (NOTE : TRIM TANK ISOLATION V/V 를 CLOSE 할수없을 경우 V/V 를 교환하여야한다.) - 분리한 ELEC CONNETOR (8) 에 DUMMY PLUG (99F28304001000) 장착후 SAFETY 조치하라. (FCMC 에 ELEC SIGNAL 을 보내어 APU OPERATION 을 확실히 하기위해서임.) 8. CB CLOSE 후 항공기 원상. 9. TRIM TANK 에는 REFUEL 금지 되며 REFUEL 은 MANUAL REFUEL 실시. - 151 - - 152 - ● MMEL 28-27-02 AFT TRANSFER VALVE ○ DEACTIVATION OF THE AFT TRANSFER VALVE 5700QA1(5700QA2) IN THE CLOSED POSTION (AMM 28-27-00-040-802) 1. TOOL : ACT ALL MECHNICAL (D97B00-003), DUMMY PLUG (99F28304001000) 2. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 3. LH MLG DOOR OPEN 4. CB OPEN : FUEL L AFT XFR V/V 1QN (E68), FUEL R AFT XFR V/V 1QN2 (Q45) 5. DEACTIVATION OF THE AFT XFR V/V - ACT 를 장탈하라. - ACT MECHANICAL (D97B00-003) 장착. - BONDING STRAP 을 연결하라. : (3),(4),(5) 연결 - ACT MECHANICAL 의 CONT KNOB 를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. (NOTE : AFT TRANSFER V/V 를 CLOSE 할수없을 경우 V/V 를 교환하여야한다.) - 분리한 ELEC CONNETOR (6) 에 DUMMY PLUG (99F28304001000) 장착후 SAFETY 조치하라. (FCMC 에 ELEC FEED BACK SIGNAL 을 보내어 APU OPERATION 을 확실히 하기위해서임.) 7. CB CLOSE 후 항공기 원상. - 153 - ※ AUX FWD XFR V/V 가 작동하며 NOSE UP PTCH TRIM 3° 이내일때 가능한 빨리 T/O 후 MAN FWD XFR 하라. ※ TRIM TANK 속에 연료가 없거나 아니면 TRIM TANK 에 있는 연료가 사용되어지지 않고 그것 이 ZFW 의 한부분으로 계산되어져 CG 결정을 위해 고려되었다면 TRIM PIPE ISOL V/V 는 CLOSE POS 에서 작동 되지않아도 된다. ● MMEL 28-27-02 TRIM PIPE ISOLATION VALVE ○ DEACTIVATION OF THE TRIM PIPE ISOLATION VALVE (AMM 28-27-00-040-801) 1. TOOL : ACT ALL MECHNICAL (D97B00-003), DUMMY PLUG (99F2830400100) 2. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 3. LH MLG DOOR OPEN 4. CB OPEN : FUEL TRIM PIPE ISOL V/V 4QN (M62) 5. DEACTIVATION OF THE TRIM PIPE ISOL V/V 5701QA - ACT 를 장탈하라. - 분리한 ELEC CONNETOR (6) 에 DUMMY PLUG (99F28304001000) 장착후 SAFETY 조치하라. (FCMC 에 ELEC FEED BACK SIGNAL 을 보내어 APU OPERATION 을 확실히 - 154 - 하기위해서임.) - ACT MECHANICAL (D97B00-003) 장착. - ACT MECHANICAL 의 CONT KNOB 를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. (NOTE : TRIM PIPE ISOL V/V 를 CLOSE 할수없을 경우 V/V 를 교환하여야한다.) - BONDING STRAP 을 연결하라. : (3),(4),(5) 연결 ※ 만약 항공기에 36000 kg (79366.392 lb) 이상 REFUEL 시 (WITH APU RUNNING) TRIM TANK INLET V/V 는 SHUT 해야함. 이는 APU FUEL STARVATION 을 방지하기위 함임. 6. CB CLOSE 후 항공기 원상. - 155 - ● MMEL 28-27-02 AUX FWD TRANSFER VALVE ○ DEACTIVATION OF THE AUX FWD TRANSFER VALVE (AMM 28-27-00-040-804) 1. TOOL : ACT ALL MECHNICAL (D97B00-003), DUMMY PLUG (99F2830400100) 2. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 3. LH MLG DOOR OPEN 4. CB OPEN 하라. : AUX FWD XFR 3QN (B69) 5. DEACTIVATION OF THE AUX FWD FUEL XFR V/V ACT - ACT 를 장탈하라. - 분리한 ELEC CONNETOR (6) 에 DUMMY PLUG (99F28304001000) 장착후 SAFETY 조치하라. (FCMC 에 ELEC FEED BACK SIGNAL 을 보내어 APU OPERATION 을 확실히 하기위해서임.) - ACT MECHANICAL (D97B00-003) 장착. - BONDING STRAP 을 연결하라. : (3),(4),(5) 연결7. CB를 CLOSE 하라. - ACT MECHANICAL 의 CONT KNOB 를 V/V CLOSE 를 위해 SHUT POS 으로 TURN 하 고 LOCK 하라. 6. CB CLOSE 후 항공기 원상. 7. TRIM TANK 에는 REFUEL 금지 되며 REFUEL 은 MANUAL REFUEL 실시. - 156 - ● MMEL 28-40-07-A) INR TK SPILT Pb SW SHUT LIGHT ○ TO DO A CHECK THAT THE APPLICABLE VALVE OPERATES WHEN THE INR TK SPLIT SHUT LIGHT IS UNSERVICEABLE (AMM 28-11-00-040-801) 1. FUEL SYS 작업시 SAFETY PROCEDURE 를 지켜라. 2. INNER TANK SPLIT PB 이 RELEASE OUT 되어있는지 확인 (OPEN POSTION) 3. CB CLOSE 확인 : K39, M71 ACTION RESULT - 'ON' LT ON 1) L INR TK SPLIT (R INR TK SPLIT) PB PUSH 2) L INR TK SPLIT (R INR TK SPLIT) PB RELEASE OUT 4. 항공기 원상. - LH (RH) EMER ISOLATION V/V ACTUATOR 에가서 INDICATOR 가 SHUT POSITION 에 있는지 확인 - 'ON' LT OFF - LH (RH) EMER ISOLATION V/V ACTUATOR 의 INDICATOR 가 OPEN POSITION 로 돌아옴. CLOSED POSITION - 157 - OPEN POSITION ● MMEL 28-42-01-A) OUTER TANK FUEL QTY INDICATION ○ CHECK OF THE QUANTITY INDICATING SYSTEM, WHEN A TANK INDICATION IS UNSERVICEABLE - OUTER TANK (AMM 28-42-00-040-802) 1. ECAM FUEL PAGE DISPLAY 2. RE/DEFUEL PANEL 또는, MLA 로써 QTY 를 CEHCK (AMM 12-11-28-650-806) 3. SD FUEL PAGE : 해당 FUEL USED & INNER TK FUEL INDICATION 이 GREEN 인지 확인하라. 4. 인접한 INNER TK FUEL QTY INDICATION 이 정상적으로 작동하는지 확인하라. 5. 해당 LO LEVEL SENSING IND 이 정상작동 하는가 확인하라 : SYS REPORT/TEST FUEL → SYSTEM TEST → START TEST FCMC1 → FCMC1 RESET CB OPEN (MIN 5S WAIT) → CLOSE RESET CB (50S WAIT) → MCDU TEST IN PROGRESS 250S MSG 보임 → TEST OK 또는 FAULT DISPLAY 됨 → RETURN KEY PUSH → FCMC1 MAIN MENU에서 RETRUN KEY PUSH → FUEL PAGE 에서 FCMC2 → SYS TEST PUSH → FCMC2 RESET CB OPEN → 5S 후 CB CLS 하고 50S WAIT → MCDU 에 'TEST IN PROGRESS 250S' MSG 보임 → CHECK NOMAL 이면 TEST OK 6. EIS STOP하고 A/C 원상하라. - 158 - ● MMEL 28-42-01-B) INNER TANK FUEL QTY INDICATION ○ CHECK OF THE QUANTITY INDICATING SYSTEM, WHEN A TANK INDICATION IS UNSERVICEABLE - INNER TANK (AMM 28-42-00-040-803) NOTE : ECAM FUEL PAGE 의 INNER TANK QTY 가 INOP 되었을 경우 ‘FUEL T TANK XFR FAULT' ECAM WARNING 나타남. 이 MSG 는 무시해도됨. (ELEC‘ ISOLATION 시키 더라도 MSG 는 사라지지을것임.) 1. ECAM FUEL PAGE DISPLAY 2. RE/DEFUEL PANEL 또는, MLA 로써 INNER TANK QTY 를 CEHCK (AMM 12-11-28-650-806) 3. SD FUEL PAGE : 해당 FUEL USED INDICATION 이 GREEN 인지 확인하라. - 159 - 4. 해당 LO LEVEL SENSING IND 이 정상작동 하는가 확인하라 : SYS REPORT/TEST FUEL → SYSTEM TEST → START TEST FCMC1 → FCMC1 RESET CB OPEN (MIN 5S WAIT) → CLOSE RESET CB (50S WAIT) → MCDU TEST IN PROGRESS 250S MSG 보임 → TEST OK 또는 FAULT DISPLAY 됨 → RETURN KEY PUSH → FCMC1 MAIN MENU에서 RETRUN KEY PUSH → FUEL PAGE 에서 FCMC2 → SYS TEST PUSH → FCMC2 RESET CB OPEN → 5S 후 CB CLS 하고 50S WAIT → MCDU 에 'TEST IN PROGRESS 250S' MSG 보임 → CHECK NOMAL 이면 TEST OK 5. LH AND RH INTERTANK TRANSFER VALVE (5601QA1 AND 5601QA2) 를 CLOSE DEACTIVE 시켜라. NOTE : V/V 자체결함이 아니므로 MAUAL LOCKING 을 사용하지 않고 CB OPEN 만으로 DEACTIVE 시킴 ACTION 1) FUEL OUTER TK XFR PB 을 PUSH 2) FUEL OUTER TK XFR PB 을 RELEASE - 'ON' LT ON RESULT - SD FUEL PAGE : INTER TANK XFR V/V 삼각형 GREEN SYMBOL 이 나타남. - 'ON' LT OFF - SD FUEL PAGE : INTER TANK XFR V/V 삼각형 GREEN SYMBOL 이 사라짐. - CB OPEN : FUEL MAIN XFR L SPLY2 29QL1 (Q38), FUEL MAIN XFR L 6QL1 (B67) - 160 - ● MMEL 28-42-01-C) CNETER TANK FUEL QTY INDICATION ○ CHECK OF THE QUANTITY INDICATING SYSTEM, WHEN A TANK INDICATION IS UNSERVICEABLE - CENTER TANK (AMM 28-42-00-440-801) - FCMC BITE TEST 수행 (AMM 28-51-00-740-801) 하여 QTY INDICATION 이 SERVICEABLE 인지 확인할것. - 161 - ● MMEL 28-46-02-B) CENTER TANK LO LEVEL DETECTION SYSTEM ○ CHECK THE OPERATION OF THE CENTER TANK PUMPS, THE MANUAL TRANSFER FROM CENTER TANK TO INNER TANK AND THE MANUAL TRANSFER FROM THE TRIM TANK TO CENTER TANK (AMM 28-46-00-040-801) ACTION RESULT 'OFF' LT OFF 1) CTR TK L AND R ON THE SD FUEL PAGE FUEL PUMP PB SW PUSH IN - CTR TANK L & R FUEL PUMP 가 작동. - 'MAN' LT ON 2) CTR TK XFR PB SW ON THE SD FUEL PAGE PUSH IN - ECAM CTR TO INNER IND 이 GREEN 으로 보이고 CTR TK FUEL QTY 가 줄기 시작한다. 3) CTR TK L,R AND XFR - 'OFF' LT ON, 'MAN' LT OFF PB RELEASE OUT - 'FWD' LT ON. ON THE SD FUEL PAGE 4) TRIM TK MODE PB - TRIM TK TO CTR TK LEGEND 가 GREEN 으로 보이는 FWD 에 SET 가 CHECK 하라. - TRIM TK FUEL 이 줄기 시작한다. 5) TRIM TK MODE PB 을 - 'FWD' LT OFF RELEASE OUT - 162 - ● MMEL 28-51-01-B) FCMC 2 ○ CHECK THAT THE APPLICABLE LEVEL SENSING IS OPERATIVE (AMM 28-51-00-040-801) 1. MCDU SYSTEM REPORT/TEST FUEL PAGE DISPLAY 2. FCMC2 의 FCMC INPUT PARAMETER 를 확인하라.(TASK 28-51-00-740-803) NOTE : PROBE CAPACITANCE 값이 보이면 아래 DEACTIVE PROCEDURE 할필요없음. - FCMC 관련 CB CLOSE 확인 - SYS REPORT/TEST →FCMC2 → INPUT PARAMETER → ARROW KEY 이용하여 PAGE 1/10부터 10/10까지 CAPACITANCE VALUE CHECK (ON 101~199 는 11/11 PAGE 까지) → DASH(-) 나타나면 다음 아래사항을 수행할것. 3. LVL SENSE TEST THE FCMC1 (TASK 28-51-00-710-802) - SYS REPORT/TEST FUEL PAGE → FCMC1 → LVL SENSE TEST → NML 이면 TEST OK 아니면 FAULT MSG 뜬다. → RETURN 4. CB OPEN : FCMC2 SPLY2 2QM2 (K34) - 163 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA29) ※ ACCUMLATOR 계통에 HYD LEAK 가 있을 경우에 (M) 사항 적용 ● MMEL 29-10-02 HYD SYSTEM ACCUMULATOR ○ CHECK FOR ABSENCE OF HYDRAULIC LEAKAGE ON THE ACCUMULATOR NITROGEN CHARGING- CIRCUIT (AMM 28-10-00-040-809) 1. 해당 HYD SYSTEM ELEC PUMP ON. 2. 해당 HYD SYSTEM ACCUMUALTOR 의 NITROGEN CHARGING-CIRCUIT 의 HYD LEAK 가 있는지 확인 3. 만약 LEAK 가 있다면 해당 ACCUMLATOR 를 DEACITIVATION 하라. ○ DEACTIVATION OF THE GREEN POWER ACCUMULATOR (5151JM1) (AMM 29-10-00-040-806) ○ DEACTIVATION OF THE BLUE POWER ACCUMULATOR (5151JM2) (AMM 29-10-00-040-807) ○ DEACTIVATION OF THE BLUE POWER ACCUMULATOR (5151JM3) (AMM 29-10-00-040-808) 1. TOOL : PLUG (ABS0946V08L), PLUG (MS21914-8J) 2. 해당 HYD SYSTEM HYD PUMP 작동금지 3. 해당 HYD SYSTEM CB OPEN - GREEN : HSMU B + PART G 6JG (U10), HYD PUMP G CTL 9JV (U09), HSMU Y + PART G 7JG (X46), HYD RAT EXT SOL2 5JR (D76) - BLUE : HSMU B + PART G 6JG (U10), HYD PUMP B CTL 9JC (X12) HSMU Y + PART G 7JG (X46), HYD RAT EXT SOL2 5JR (D76) - YELLOW : HSMU B + PART G 6JG (U10), HYD PUMP Y SVCE 10JJ (N46), HYD PUMP Y CTL 9JJ (R36), HSMU Y + PART G 7JG (X46), HYD RAT EXT SOL2 5JR (D76) 4. GREEN (BLUE, YELLOW) HYD SYSTEM RSVR DEPRESS' 5. DEACTIVATION OF THE ACCUMULATOR GREEN HYD SYSTEM - 164 - 1) 197CB PANEL OPEN 후 ACCUM' CHARGING V/V (7) LOOSE 하여 NITROGEN을 DEPRESS' 한다. 2) LEFT MLG DOOR OPEN 3) UNION (2) 와 (5) 를 풀어서 PIPE (3) REM' 하고 MANINFOLD (1) 과 ACCUM (4) 에 PLUG 장착 (TORQUE : 106.19~132.74 lbf.in) BLUE HYD SYSTEM 195CB 1) 195BB ACCESS PANEL OPEN 후 ACCUM' CHARGING V/V (7) LOOSE 하여 NITROGEN 을 DEPRESS' 한다. 2) 195CB PANEL REMOVE 3) UNION (4) 와 (2) 를 풀어서 PIPE (1) REM' 하고 MANINFOLD (3) 과 ACCUM (5) 에 PLUG 장착 (TORQUE : 106.19~132.74 lbf.in) - 165 - YELLOW HYD SYSTEM 1) 196BB ACCESS PANEL OPEN 후 ACCUM' CHARGING V/V (7) LOOSE 하여 NITROGEN 을 DEPRESS' 한다. 2) UNION (4) 와 (2) 를 풀어서 PIPE (3) REM' 하고 T-UNION (5) 과 ACCUM (1) 에 PLUG 장착 (TORQUE : 106.19~132.74 lbf.in) 6. OPEN 되었던 CB CLOSE 7. RSVR AIR PRESS' 하고 해당 HYD ELEC' PUMP ON 하여 PLUG 장착부위 LEAK 수행. 8. A/C를 원상하라 - 166 - ● MMEL 29-10-07 RESERVOIR FILLING FILTER ○ CHECK THAT THE APPLICABLE LEVEL SENSING IS OPERATIVE (AMM 28-51-00-040-801) NOTE : FILTER DEACTIVATION 후 GROUND HYD CART 로 SVC 한다면 CART 에 15 MICRON FILTER 가 있는지 확인할것. 1. HYD SERVICE PALEL (197CB) OPEN 2. FILTER BOWL (4) 을 REM' 하고 ELEMENT (3) 와 “O" RING (2) DISCARD (ELEMENT 가 FILTER HEAD (8) 쪽에 박혀있을 경우 빼서 제거할것.) 3. FILTER BOWL (4) CLEANING 하고 FILTER HEAD (8) 쪽의 O-RING (6) DISCARD 하고 NEW 로 교환 4. BOWL 장착 (4), HAND TIGHT 하고 SAFETY 하라. 5. FILTER ELEMENT 가 없다는 WARNING NOTICE 부착. 6. 만약 RED INDICATOR POP-OUT 시 DOME COVER 를 풀고 INDICATOR 를 PUSH 할것. 7. RSVR FILLING MANUAL SELECTOR V/V 4JS 를 'NEUTRAL' POSITION 8. HYD FILLING FLEX' HOSE 를 빼내어 FILLING V/V 에 연결 10. HAND PUMP 에 LEVER 연결하여 약 20회 정도 젖는다. 11. FILTER 에서 LEAK 있는지, RED IND' 가 POP-OUT 되는지 확인하라. 12. RSVR FILLING MANUAL SELECTOR V/V 4JS 를 ‘GREEN', 'BLUE', 'YELLOW' POS 에 차례로 놓아서 HYD PRESSURE 를 RELEASE 시키고 다시 'NEUTRAL' 에 놓을것. 13. 항공기 원상. NAS1611-131A - 167 - ● MMEL 29-10-08 CASE DRAIN FILTER ○ DEACTIVATION OF THE ENGINE PUMP CASE DRAIN FILETER (5013JM1, 5013JM2) (AMM 29-10-00-040-801) 1. HYD SYSTEM & RSVR DEPRESS' 2. APU BLD "OFF', HYD SYS 관련 PUMP 작동금지 3. 관련 HYD SYSTEM CB OPEN - FOR 4030EM1 : U09, U08, X12, X11, D44, Q73 - FOR 4030EM2 : U09, K49, R36, T46, X45, Q74 4. ENG RH COWL OPEN 하고 INSULATION BLANKET (6) REM' 5. FILTER BOWL (5) REM' 하고 ELEMENT (4)를 REMOVE 후 DISCARD 시켜라 6. BOWL 장착 (TQ :14.99~19.99 lbf-ft) 하라. 7. RSVR PRESS' 시키고 ENG MOTORING 하면서 LEAK CHK 하라. - RED INDICATOR 가 POP OUT 되었다면 PUSH 해서 RESET 할것. 8. HYD QTY CHECK 하고 필요시 보급하라. 9. INSULATION BLANKET를 장착 10. OPEN 되었던 CB CLOSE 후 항공기 원상하라. - 168 - ● MMEL 29-23-01-B) YELLOW AUX HYD POWER HAND PUMP ○ DEACTIVATION OF THE YELLOW HYD HAND PUMP 7155JE (ONLY IF IT IS LEAKING) (AMM 29-23-00-040-802) 1. ACCESS DOOR 196BB OPEN 2. MLG DOOR OPEN 3. YELLOW HYD SYSTEM OPRATION TEST 수행 (AMM 29-13-00-710-801) ACTION RESULT 1) 관련 CB CLOSE 확인 : U10, R35, R33 ,T46, X46, D74 - EWD : N2 20% 확인 2) DRY MOTOR ENG 2 - SD HYD PAGE : YELLOW PRESSURE 3000±200 PSI 확인 3) SIDE STICK 사용하여 FLIGHT CONROL 움직임. 4) STOP THE ENG 4. 만약 HAND PUMP 에 LEAK 발생하지 않고 YELLOW HYD SYSTEM 이 정상적으로 작동시 NO DEACTIVATION 5. HAND PUMP 에 LEAK 발생시 ※ HAND PUMP LEAK LIMIT (AMM 29-00-00-790-801) • NORMAL OPRATION LIMIT : 5 DROPS/MIN • DISPATCH LIMIT : 30 DROPS/MIN - LEAK RATE 가 LIIMIT 이내면 NO DEACTIVATION - LEAK RATE 가 LIIMIT 벗어나면 YELLOW HAND PUMP DEACTIVATION 수행 4. DEACTIVATION OF THE YELLOW HAND PUMP (7155JE) - YELLOW HYD HAND PUMP REMOVE (AMM 29-23-52-000-801) - PIPE (4), (5) REMOVE 하여 항공기 보관. - UNION (6), (3) 에 BLANKING CAP (MS21914V4P, MS21914-4W or MS21914-4J) 장착 후 (TORQUE : 106.19~115.04 lb.in) 5. YELLOW HYD SYSTEM OPRATION TEST 수행 (AMM 29-13-00-710-801) 하여 (상기 3 항 수행) CAPPING 부위 LEAK CHECK 6. 항공기 원상. - 169 - HAND PUMP REMOVE 1 6 2 5 - 170 - 4 3 ● MMEL 29-30-02-A) RESERVOIR QUANTITY INDICATION ○ DEACTIVATION OF THE RESERVOIR QUANTITY INDICATION OF THE HYDRAULIC SYSTEMS ON THE ECAM HYD PAGE (AMM 29-31-00-040-801) WARNING : TEST 하는동안 RAT TAVEL RANGE 내 모든 물체를 CLEAR 시켜라. 1. CB OPEN : HSMU B + PART G 6JG (U10), HSMU Y + G 7JG (X46) RAT EXT SOL2 5JR (D76) 2. MLG DOOR OPEN 3. DEACTIVATION OF THE RSVR QTY INDICATION - 해당 RSVR 에 있는 QTY TRANSMITTER 로부터 ELEC PLUG (1) 을 분리하고 SAFETY 조치하라. - RSVR 에 있는 SIGHT GLASS 로 부터 QTY CHECK 하고 필요하면 보급하라. - OPEN 되었던 CB CLOSE. - 해당 RSVR 를 LO LVL WARNING 이 작동할때까지 HYD 를 DRAIN 하라. NOTE : DRAINING OPERATION 은 DEACTIVATION 동안 오직 한번만 수행하라. NOTE : GREEN SYSTEM 의 경우 LO LEVEL 시 FIRE SHUT OFF V/V CLOSE 됨. ※ HYD SERVICE 후 5JR (D76) CB RESET 할것. PLUG (3),(4) REMOVE 후 CLOSING SCREW (2)를 LOOSE 하여 HYD DRAIN 시킴. PLUG TORQUE : 10.32~11.79 lb.ft DRAIN V/V - RSVR에 CORRECT LVL 로 HYD SVC 하라. 4. 항공기 원상하라. - 171 - GREEN YELLOW BLUE - 172 - ● MMEL 29-30-02-H) OVHT INDICATION ○ DEACTIVATION OF THE ELECTRIC-PUMP OVERHEAT INDICATION ON THE ECAM HYD PAGE (AMM 29-31-00-040-807) • FOR 1JV (GREEN) 1. MLG DOOR OPEN 2. CB OPEN : HYD PUMP G CTL 9JV (U09) 3. ELEC CONNECTOR 1JVA (1) REMOVE 하고 SAFETY 조치 4. 항공기 원상. • FOR 1JC (BLUE) 1. ACCESS PANEL 195CB REMOVE 2. CB OPEN : HYD PUMP B CTL 9JC (X12) 3. ELEC CONNECTOR 1JCA (1) REMOVE 하고 SAFETY 조치 4. 항공기 원상. - 173 - • FOR 1JJ (YELLOW) 1. ACCESS PANEL 196EB REMOVE 2. CB OPEN : HYD PUMP Y SVCE 10JJ (N46), HYD PUMP Y CTL 9JJ (R36) 3. ELEC CONNECTOR 1JJA (1) REMOVE 하고 SAFETY 조치 4. 항공기 원상. 196EB ※ 매 FLIGHT 전 ECAM HYD PAGE 상에 HYD QTY 가 NORMAL 인지 확인할것. NOTE : (M) 사항은 GREEN FIRE SHUT-OFF V/V 가 ENG START 중에 AUTO CLOSE 되었 을 경우 에 수행할것. ● MMEL 29-30-03-A) RSVR LO LVL ○ UNWANTED CLOSING OF THE FIRE SHUT-OFF VALVE ON THE GROUND DURING ENGINE START (AMM 29-31-00-040-809) - ENG STARING 중 GREEN FIRE SHUT-OFF V/V 가 AUTO CLOSE 되었을 경우 V/V 를 OPEN 시키기 위해 5JR CB (D76) 를 RESET 시켜라. - 174 - ● MMEL 29-30-03-B) RSVR LO AIR PR ○ DEACTIVATION OF THE RESERVOIR AIR PRESSURE SWITCHES (AMM 29-31-00-040-802) 1. MLG DOOR OPEN 하라. 2. CB OPEN : HSMU B + PART G 6JG (U10), HSMU Y + PART G 7JG (X46) RAT EXT SOL2 5JR (D76) 3. DEACTIVATION OF THE RSVR AIR PRESSURE SW - 해당 RSVR 에 PRESSURE SW 로부터 ELEC CONNECTOR (1)을 분리하고 양쪽에 CAPPING 후 TIE WRAP 하라. - RSVR 의 PRESS‘ IND’를 통하여 3 BAR 이상인지 확인하고 필요하면 SVC 하라. - CB CLOSE 하고 A/C 원상하라. - 175 - ● MMEL 29-30-03-E) PUMP LO PR ○ DEACTIVATION OF THE PRESSURE INDICATION OF THE ENGINE-PUMP PRESSURE SWITCH ON THE ECAM HYD PAGE (AMM 29-31-00-040-808) 1. CB OPEN 2. ACCESS PANEL REMOVE 하라. • GREEN SYSTEM : FOR 4030EM1 (451DL), FOR 4030EM2 (461DL) • BLUE SYSTEM : FOR 4030EM1 (451DL) • YELLOW SYSTEM : FOR 4030EM2 (461DL) 3. 해당 SYSTEM PRESSURE SW 로부터 ELEC CONNECTOR (1) 분리하여 SAFETY 조치하 고 RECEPTACLE 에는 PROTECTIVE CAP 을 씌워라. • GREEN SYSTEM : 11JG1A, 11JG2A • BLUE SYSTEM : 5JBA • YELLOW SYSTEM : 8YA 4. OPEN 되었던 CB CLOSE 하고 항공기 원상하라. - 176 - 11JG1 11JG2 1 GREEN YELLOW BLUE 1 5JB 1 ● MMEL 29-30-03-G) RAT FAULT 8JY ○ INTEGRITY CHECK OF THE RAT AFTER RAT FAULT WARNING (AMM 29-31-00-040-803) 1. EWD 에 'RAT FAULT' WARNING 이 뜨는가 확인하라. 2. RH WING 에 RAT 가 EXTEND 되었나 확인하고 EXTEND 되었다면 항공기 DISPATCH 전 에 TSM 2924 에 따라 T/S 절차수행하라. 3. GREEN HYD ELEC PUMP ON 하라. 4. RAT 를 EXTEND 하라 : OVHD PNL 에 RAT MAN ON SW "PUSH" (1분이상 PUSH 금지) 5. RAT 가 DEPLOY 된 것 확인후 RAT 를 RETRACT 하라. ※ RAT RETRAT/EXTEND 중에 'RAT STOWED' IND LT 가 ON/OFF 될 수있으나 무시할것. ※ 만약 RAT 가 STOWED POSITION 에 있는데도 ‘RAT FAULT' MSG 가 사라지지 않으면 이 러한 ’RAT FAULT' MSG 는 FALSE 임. 무시할것. 6. 항공기 원상하라. - 177 - ● MMEL 29-30-03-H) MONITORING FAULT ○ DEACTIVATION OF THE MONITORING FAULT WARNING (AMM 29-31-00-040-804) 1. 관련 CB CLOSE 확인 : HSMU B + PART G 6JG (U10), HSMU Y + PART G 7JG (X46), RAT EXT SOL2 5JR (D76) 2. HSMU 가 RACK 에 정확하게 장착되었나 확인하라. 3. HSMU BITE TEST를 수행하라. (AMM 29-31-00-740-802) - MCDU SYS REPORT/TEST → ATA29 HYD → HSMU → TEST → OVHD PNL 에 G,B,Y FAULT LT 가 3초동안 연속적으로 ON 됨. → NORMAL 이면 NO HYD PART TESED OK MSG DISPLAY → RETURN - 178 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA30) (FCON 3.04.30 P1, POM 7.3.1) ※ OUTSIDE TEMP 가 19℃ 이하일때만 BLEED 사용하여 ENG STARTING 할수있다. ● MMEL 30-11-01-a) WING ANTI ICE V/V ○ DEACTIVATION OF THE WING ANTI-ICE CONTROL VALVE (AMM 30-11-00-040-801) 1. CB OPEN : SFCC2 SLAT 2CW (V40), ANTIICE WING 1DL (L68), SFCC1 SLAT 1CW (L62) 522LB (622LB) 2. ACCESS PNL REMOVE : 522LB (LH WING), 622LB (RH WING) 3. DEACTIVATION OF THE WAI CONT' V/V 9DL1 OR 10DL1 IN THE CLOSED POSITION (LH WING) WARNING : ENG 이 정지후 얼마동안 DUCT 가 뜨거우므로 접촉되지않도록 조심할것. - LOCKING SCREW (1) 의 LOCKING WIRE 제거하라. - 179 - - IND‘ (2) 이 'CLOSED' POSITION 인지 확인하고 'CLOSED' 가 아니면 손으로 IND' 를 'CLOSED' POSITION 으로 움직여라 - LOCKING SCREW (1) 장탈하라. - LOCKING SCREW (1) 를 IND (2) 의 LOCKING HOLE 을 통하여 WAI V/V 에 장착하라. - LOCKING SCREW (1) 에 SAFETY WIRE 하라. 4. DEACTIVATION OF THE WAI CONT' V/V 9DL1 OR 10DL1 IN THE OPEN POSITION (LH WING) - LOCKING SCREW (1) 의 LOCKING WIRE 제거하라. - IND‘ (2) 이 'OPEN' POSITION 인지 확인하고 'OPEN' POSITION 이 아니면 손으로 IND' 를 'OPEN' POSITION 으로 움직여라 - LOCKING SCREW (1) 장탈하라. - LOCKING SCREW (1)를 IND (2) 의 LOCKING HOLE을 통하여 WAI V/V 에 장착하라. - LOCKING SCREW (1)에 SAFETY WIRE 하라. ※ LOG 에 DEACTIVE 사항 기록하라. ENG STARTING 을 제외하고 ENG 또는 APU BLEED 작동하지 말것. 이는 SLAT 에 HEAT DAMAGE 를 유발할수있다. ※ OUTSIDE TEMP 가 19℃ 이하일때만 BLEED 사용하여 ENG STARTING 할수있다. (REF : FCOM 3.02.30) 5. DEACTIVATION OF THE WAI CONT' V/V 9DL2 OR 10DL2 IN THE CLOSED POSITION (RH WING) ※ 9DL2 DEACTIVE 할때는 INSPECTION MIRROR 가 필요하다. - ANTI-ICE CONTROL SHAFT (11) 가 'CLOSED' POSITION 인지 확인하라. (SHAFT 는 - 180 - FULLY OUT 됨). SHAFT 가 'CLOSED' POSITION 이 아니라면 SHAFT 를 손으로 서서 히 'CLOSED' POSITION 으로 움직여라. - LOCKING CLIP (12) 을 눌러서 LOCKING 시켜라. (SHAFT (11) 를 조금씩 움직이면 쉽 게 LOCKING 시킬수있음) 6. DEACTIVATION OF THE WAI CONT' V/V 9DL2 OR 10DL2 IN THE OPEN POSITION (RH WING) WARNING : ENG 이 정지후 얼마동안 DUCT가 뜨거우므로 접촉되지 않도록 조심할것. ※ 9DL2 DEACTIVE 할때는 INSPECTION MIRROR 가 필요하다. - ANTII-ICE CONTROL SHAFT (11) 가 'OPEN' POSITION 인지 확인하라. (SHAFT 는 FULLY IN) SHAFT 가 ‘OPEN’ POSITION 이 아니면 SHAFT 를 손으로 서서 히 ‘OPEN’ POSITION 으로 움직여라. - LOCKING CLIP (12) 을 눌러서 LOCKING 시켜라. (SHAFT (11) 를 조금씩 움직이면 쉽 게 LOCKING 시킬수있음) NOTE : LOCKING CLIP 은 양 방향으로 움직여지며 아무방향이나 LOCKING 할수있음. ※ LOG 에 DEACTIVE 사항 기록하라. ENG STARTING 을 제외하고 ENG 또는 APU BLEED 작동하지 말것. 이는 SLAT 에 HEAT DAMAGE 를 유발할수있다. ※ OUTSIDE TEMP 가 19℃ 이하일때만 BLEED 사용하여 ENG STARTING 할수있다. (REF : FCOM 3.02.30) 7. OPEN 되었던 CB CLOSE 및 PANEL INSTALL 하고 항공기 원상하라. - 181 - ※ SHUT-OFF SECTION 은 NORMAL 상태에서 OPEN POSITON 유지하여 10 CALENDAR DAY 를 초과하지 않는 기간동안 FLIGHT 가능함. ● MMEL 30-21-01-B) ENGINE ANTI-ICE V/V PRESSURE REGULATION SECTION ○ CHECK OF THE OPERATION OF THE PRESSURE REGULATING SECTION OF THE AIR INTAKE ANTI ICE VALVE (AMM 30-21-00-040-805) 1. CB OPEN • ENG 1 : FADEC B ENG1 13KS1 (D44), FADEC A ENG1 12KS1 (Q73) • ENG 2 : FADEC B ENG2 13KS2 (K49), FADEC A ENG1 12KS2 (Q74) 2. ACCESS DOOR OPEN (ENG1 :417DL, ENG2 : 427DL) ※ LH REVERSER COWL 을 OPEN 하여 작업하는게 나을수도있음. 3. PUSH BUTTON 을 눌러 V/V POSITIONER 를 UNLOCK 시킴. 4. ‘OPEN’ IND 이 PB 과 일치될때까지 WRENCH 사용하여 V/V POSITIONER 를 TURN 하라. 5. POSITIONER 를 LOCK 하기위해 PB RELEASE 하라. ※ 'A.ICE ENG 1(2) REGUL FAULT' EWD MSG 는 무시해도 된다. 6. ENG ANTI-ICE V/V TEST (AMM 30-21-00-710-803) 수행하여 SHUT-OFF PART 가 제 대로 작동되는지 확인. ACTION RESULT 1) FADEC CB CLOSE 2) ENG RUN 하여 MIN IDLE 상태유지하여 5분간 STABLE. 3) OVERHEAD PANEL 의 ENG ANTI-ICE PB PUSH - 'ON' LT ON : - IIN THE FAILURE PANEL : 'ENGINE ANTI-ICE - ENG (1 OR 2) NAC VALVE NOT OPEN' MSG DISPLAY 4) ECAM SCREEN 을 - IN THE DISPLAY PANEL : 1분동안 MONITOR 'A.ICE ENG (1OR2) VALVE CLOSED‘ AND ’AVOID ICING CONDITIONS' MSG DISPLAY 하라. - P/B 에 FAULT LT ON - MASTER LIGHT ON - SINGLE CHIME OPERATES. 5) 1분후 ENG ANTI-ICE PB RELEASE 6) ECAM SCREEN 을 다시 - ANTI-ICE 에 관련된 아무런 FAULT MSG 가 나오지 1분동안 MONITOR 않아야됨. 7) ENG SHUT-DOWN - 182 - ※ SHUT-OFF SECTION의 SHUT-OFF PISTON 은 PS3 PRESSURE 에 의해 NML OPER' 되 어야함. ※ MAINT MESSAGE 2.V/V FAILED CLS OR REG V/V REG' HI (SENSED LO PRESS'>153PSI) "A.ICE ENGx VALVE "A.ICE ENGx REG' FAULT FDE "A.ICE ENGx VALVE OPEN" CLOSED" THERMAL THERMAL NAI(Ex-5000DN) / FUSE(Ex-5001DN)/ENG NAI FUSE(Ex-5001DN)/ENG NAI MSG ENGTVBC-NAI SOL VLV(Ex-5000DN) VLV(Ex-5000DN 1. V/V FAILED OPEN ● MMEL 30-21-01-C) ENGINE ANTI-ICE V/V SHUT-OFF SECTION ○ CHECK OF THE OPERATION OF THE SHUT-OFF SECTION OF THE ENGINE AIR INTAKE ANTI ICE VALVE IN THE UNLOCKED POSITION (AMM 30-21-00-040-808) 1. CB OPEN • ENG 1 : FADEC B ENG1 13KS1 (D44), FADEC A ENG1 12KS1 (Q73) • ENG 2 : FADEC B ENG2 13KS2 (K49), FADEC A ENG1 12KS2 (Q74) 2. ACCESS DOOR OPEN (ENG1 :417DL, ENG2 : 427DL) 3. ANTI-ICE VALVE POSITION 을 확인하라. (만약 VALVE 가 ‘UNLOCKED' POSITION 이아니라면, ’UNLOCKED' POSITION 으로 SET 하라.) 4. PUSH BUTTON 을 눌러 V/V POSITIONER 를 UNLOCK 시킴. 5. ‘UNLOCKED’ IND 이 PB 과 일치될때까지 WRENCH 사용하여 V/V POSITIONER 를 TURN 하라. 6. POSITIONER 를 LOCK 하기위해 PB RELEASE 하라. 7. PFR 에 'A.ICE ENG 1(2) REGUL FAULT' WARNING 이 없어야한다. 만약 MSG 가 있다면 TSM 30-21-00-810-851, TSM 30-21-00-810-852 수행. 8. OPEN 되었던 CB CLOSE 하고 항공기 원상. - 183 - - 184 - ● MMEL 30-31-01a) PHC PROBE HEATING CH OPARATIVE ○ CHECK OF THE OPERATION OF THE PROBE HEATING CHANNEL (AMM 30-31-00-040-801-1) CAUTION : 1분이상 TEST 진행하지말것. (PROBE 에 DAMAGE 야기 할수있음.) 1. SIMULATION OF FLIGHT WHEN THE A/C IS ON THE GND (AMM 32-69-00-860-801) • FLIGHT CONFIGURATION PRECATION 수행 (AMM 32-00-00-860-804) PNL 715VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU DESIGNATION FIN LOC PNL DESIGNATION FIN LOC ANTI ICE WSHLD R 1DG2 R57 722VU ANTI ICE AOA 2 1DA2 F48 ICE DET 1 2DD1 B07 722VU ICE DET 2 2DD2 F47 ANTI ICE TAT 1 12DA1 B06 722VU ANTI ICE PITOT 2 4DA2 F43 TCAS 4SG B05 722VU BRK FAN CTL 5GD R44 3LR R41 ANTI ICE AOA 3 31DA3 C05 722VU LT TAXI/T.O CTL ANTI ICE WINDOWS L 4DG1 D03 722VU SDCU CHAN 2 12WH T38 LT RWY TURN OFF L 1LC H03 722VU CPC 2 2HL U44 LT TAXI/T.O L 1LR H02 722VU ANTI ICE STAT 2 11DA2 X41 RA 1 2SA1 L14 722VU PHC 2 2DA2 X40 5DG2 X39 ANTI ICE PITOT 3 4DA1 L07 722VU WHC 2 PHC 3 2DA3 N07 742VU CPC 1 1HL A66 PHC 1 2DA1 P12 742VU APU START CTL 1KA C72 TURBO FAN CTL 3HR T06 742VU HYD RAT EXT SOL 2 5JR D76 LA/DAR/QAR 28VDC 9TU U11 742VU 28VDC ESS BUS 6QC F65 ANTI ICE STAT 3 11DA3 W10 742VU 28VDC ESS BUS 5QC F64 5DG1 G64 ANTI ICE STAT 1 11DA1 W09 742VU WHC 1 ON A/C 001-56, 101-199 742VU HF 1 2RE1 J63 722VU HF2 2RE2 E37 742VU RAT MAN ON 2JR K74 ON A/C ALL 742VU SDCU CHAN 1 11WH L75 722VU LT TAXI/T.O R 2LR D48 742VU CSM/G MAN START 22XE N61 722VU LT RWY TURN OFF R 2LC D47 742VU ANTI ICE PITOT1OR3 3DA Q72 722VU ANTI ICE WINDOWS R 4DG2 D43 742VU ANTI ICE AOA 1 OR 3 31DA1 Q68 722VU ATC 2 3SH2 E47 742VU ATC 1 3SH1 Q64 722VU RA 2 2SA2 E46 742VU ANTI ICE WSHLD L 1DG1 S69 722VU ANTI ICE TAT 2 12DA2 E43 CAUTION : 2DA1(P12), 2DA2(X40), 2DA3(N07), 5DG1(G64),5DG2(X39) 는 맨마지막에 OPEN 시킬것. 그렇지 않으면 HEATING SYSTEM 의 원치않는 작동이 이뤄지게 됨. CB CLOSE 시킬때는 제일먼저 상기 CB 를 CLOSE 시킬것. • SYSTEM REPORT/TEST L/G:EXT/RETR page → 'LGCIU1 or 2' PUSH → 'L-G CONFIGURATION SIMULATION' PUSH → 'START TEST' PUSH → 'CONFIRM START OF TEST' → 관련 L/G KEY PUSH - 185 - 2. CHECK OF THE PROBES HEATING WARNING : 이 작업수행시 바로 PROBE 만지지 말것. 화상염려있음. ※ 관련 PROBE HEATING 관련 CB 는 CLOSE 할것. - PHC1 2DA1 (P12), TAT1 12DA1 (B06), STAT1 11DA1 (W09), PITOT1 OR 3 31DA1 (Q68), ANTI ICE AOA 1 OR 3 3DA (Q72) - PHC2 2DA2 (X40), TAT2 12DA2 (E43), STAT2 11DA2 (X41), PITOT2 4DA2 (F43) AOA2 1DA2 (F48) - PHC3 2DA3 (N07), STAT3 11DA3 (W10), PITOT3 4DA1 (L07), AOA3 31DA3 (C05) ACTION 1) PROBE/WINDOW HEAT PB PUSH RESULT - 'ON' LT ON 2) UNSERVICABLE PHC 와 관련된 PROBE 의 HEATING 이 되는지 400℃ (752℉) 까지 의 읽을 수 있는 온도계를 이용하여 확인하라. • 6DA1 (PHC1 : LH LG로부터 FLT SIGNAL) 에서 7DA1, 8DA1, 9DA1, 3FP1, 11FP1 • 6DA2 (PHC2 : RH LG로부터 FLT SIGNAL) 에서 7EA2, 8DA2, 9DA2, 3FP2, 11FP2 • 6DA3 (PHC3 : NLG로부터 FLT SIGNAL) 에서 7DA3, 8DA3, 9DA3, 3FP3 ※ REF‘ : 7DAx (LH STATIC), 8DAx (RH STATIC), 9DAx (PITOT), 3FPx (AOA), 11FPx (TAT) 3) EWD 에는 WARNING 이 없어야한다. - 186 - (FCON 3.04.30 P1, POM 7.3.1) (FCON 3.04.30 P1, POM 7.3.1) ● MMEL 30-31-01b) c) CAPT or F/O PHC, STBY PHC INOPERATIVE ○ CHECK OF THE ADR, CAPT (F/O, STBY) HEATERS AND FAILURE WARNINGS OPERATION (AMM 30-31-00-040-801) CAUTION : TEST 수행전 PROBE 로부터 PROTECTOR를 장탈할것. 1. SIMULATION OF FLIGHT WHEN THE A/C IS ON THE GROUND (AMM 32-69-00-860-801) (MEL 30-31-01a) 절차 참고) ※ PROBE HEATING 관련 CB 는 OPEN 하지 말것 2. PROBE ICE-PROTECTION SYSTEM 의 OPERATION TEST 수행 (TASK 30-31-00-710-801) - PROBE & WINDOW HEAT PB RELEASE (‘ON’ LEGEND OFF) - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : HEATING PAGE - PHC1(2,3) PUSH → PHC1(2,3) PAGE DISPLAY → TEST KEY PUSH → "TEST IN PROGRESS 25S DISPLAY 몇초후 “TEST OK" → RETURN 3. ADR CURRENT STATUS를 수행하라 (AMM 34-13-00-740-802) - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : ALTITUDE PAGE - 관련 CB CLOSE 확인 : G04, M05, H46, L32, G76, G75, K72, N75, P64 - READ CMC FOR ADR CURRENT STATUS 'ADR1(2,3)' KEY PUSH → ADR1(2,3) PAGE → 'CURRENT STATUS' KEY PUSH → CURRENT STATUS PAGE 1/8 에 ADR1(2,3) 의 GROUND STATUS CURRENT PARAMETER DISPLAY → CURRENT STATUS PAGE 2/8 ~ 8/8까지 DOWN ARROW KEY PUSH → 관련 PAGE 나타남 → RETURN KEY → TEST PROCEDURE STOP - 187 - 4. 다음 CB OPEN 하라. DESINATION FOR 6DA1 (PHC1) ANTI ICE TAT1 ANTI ICE STAT1 ANTI ICE PITOT1 OR 3 ANTI ICE AOA1 OR 3 FOR 6DA2 (PHC2) ANTI ICE TAT2 ANTI ICE AOA2 ANTI ICE PITOT2 ANTI ICE STAT2 LOC B06 W09 Q72 Q68 E43 F48 F43 X41 DESINATION FOR 6DA3 (PHC3) ANTI ICE AOA3 ANTI ICE PITOT3 ANTI ICE STAT3 ESS ANTI ICE PITOT3 ESS ANTI ICE AOA3 ANTI ICE PITOT1 OR 3 5. EWD에서 다음 MSG 가 DISPLAY 되는가 확인하라. “A. ICE CAPT (F/O, STBY) L(R) STAT HEAT" “A. ICE CAPT (F/O, STBY) AOA HEAT" “A. ICE CAPT (F/O, STBY) PITOT HEAT" “A. ICE CAPT (F/O, STBY) TAT HEAT" 6. CB CLOSE 하고 A/C 원상하라. - 188 - LOC C05 L07 W10 H69 H68 Q72 ※ MCDU CURRENT STATUS 출력 SAMPLE - 189 - (FCON 3.04.30 P1, POM 7.3.1) (FCON 3.04.30 P1, POM 7.3.1) ● MMEL 30-31-02 PROBE ICE PROTECTION PITOT HEATER ○ DEACTIVATION OF THE HEATING OF THE PITOT PROBES (9DA1, 9DA2, 9DA3) (AMM 30-31-00-040-802) 1. PROBE ICE-PROTECTION SYSTEM 의 OPERATION TEST 수행 (TASK 30-31-00-710-801) - PROBE & WINDOW HEAT PB RELEASE (‘ON’ LEGEND OFF) - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : HEATING PAGE - PHC1(2,3) PUSH → PHC1(2,3) PAGE DISPLAY → TEST KEY PUSH → "TEST IN PROGRESS 25S DISPLAY 몇초후 “TEST OK" → RETURN 2. ADR CURRENT STATUS (AMM 34-13-00-740-802) 또는 ADR SYSTEM TEST (AMM 34-13-00-740-803) 수행 - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : ALTITUDE PAGE - 관련 CB CLOSE 확인 : G04, M05, H46, L32, G76, G75, K72, N75, P64 - READ CMC FOR ADR CURRENT STATUS 'ADR1(2,3)' KEY PUSH → ADR1(2,3) PAGE → 'CURRENT STATUS' KEY PUSH → CURRENT STATUS PAGE 1/8 에 ADR1(2,3) 의 GROUND STATUS CURRENT PARAMETER DISPLAY → CURRENT STATUS PAGE 2/8 ~ 8/8까지 DOWN ARROW KEY PUSH → 관련 PAGE 나타남 → RETURN KEY → TEST PROCEDURE STOP 3. 다음 CB OPEN 하라. • FOR 9DA1 (CAPT PITOT PROBE) : ANTI ICE PITOT1 or 3 3DA (Q72) • FOR 9DA2 (F/O PITOT PROBE) : ANTI ICE PITOT2 4DA2 (F43) • FOR 9DA3 (STBY PITOT PROBE) : ANTI ICE PITOT1 or 3 3DA (Q72), ANTI ICE PITOT 3 (L07) - 190 - 4. EWD 에 다음 MESSAGE 가 있는지 확인하라. • FOR 9DA1 (CAPT PITOT PROBE) : “A. ICE CAPT PITOT HEAT" • FOR 9DA2 (F/O PITOT PROBE) : “A. ICE F/O PITOT HEAT" • FOR 9DA3 (CAPT PITOT PROBE) : “A. ICE STBY PITOT HEAT" 5. OPEN 되었던 CB CLOSE 하고 항공기 원상하라. (FCON 3.04.30 P1, POM 7.3.1) ● MMEL 30-31-03 PROBE ICE PROTECTION STATIC PORTS HEATER ○ DEACTIVATION OF THE HEATING OF THE STATIC PROBES (7DA1, 7DA2, 7DA3, 8DA1, 8DA2, 8DA3) (AMM 30-31-00-040-803) 1. PROBE ICE-PROTECTION SYSTEM 의 OPERATION TEST 수행 (TASK 30-31-00-710-801) - PROBE & WINDOW HEAT PB RELEASE (‘ON’ LEGEND OFF) - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : HEATING PAGE - PHC1(2,3) PUSH → PHC1(2,3) PAGE DISPLAY → TEST KEY PUSH → "TEST IN PROGRESS 25S DISPLAY 몇초후 “TEST OK" → RETURN 2. ADR SYSTEM TEST (AMM 34-13-00-740-803) 수행 3. 다음 CB OPEN 하라. - 191 - 4. EWD 에 다음 MESSAGE 가 있는지 확인하라. • FOR 7DA1 : 'A.ICE CAPT L STAT HEAT' • FOR 8DA1 : 'A.ICE CAPT R STAT HEAT' • FOR 7DA2 : 'A.ICE F/O L STAT HEAT' • FOR 8DA2 : 'A.ICE F/O R STAT HEAT' • FOR 7DA3 : 'A.ICE STBY L STAT HEAT' • FOR 8DA3 : 'A.ICE STBY R STAT HEAT' 5. OPEN 되었던 CB CLOSE 하고 항공기 원상하라. - 192 - ● MMEL 30-31-04 PROBE ICE PROTECTION ANGLE OF ATTACK PROBES HEATING ○ DEACTIVATION OF THE HEATING OF THE ANGLE OF ATTACK SENSORS (3FP1, 3FP2,3FP3) (AMM 30-31-00-040-804) 1. PROBE ICE-PROTECTION SYSTEM 의 OPERATION TEST 수행 (TASK 30-31-00-710-801) - PROBE & WINDOW HEAT PB RELEASE (‘ON’ LEGEND OFF) - ADIRS START (NAV' POS) - MCDU 의 SYS REPORT/TEST → ICE RAIN : HEATING PAGE - PHC1(2,3) PUSH → PHC1(2,3) PAGE DISPLAY → TEST KEY PUSH → "TEST IN PROGRESS 25S DISPLAY 몇초후 “TEST OK" → RETURN 2. ADR SYSTEM TEST (AMM 34-13-00-740-803) 수행 3. 다음 CB OPEN 하라. 4. EWD 에 다음 MESSAGE 가 있는지 확인하라. • FOR 3FP1 : 'A.ICE CAPT AOA HEAT' • FOR 3FP2 : 'A.ICE F/O AOA HEAT' • FOR 3FP3 : 'A.ICE STBY AOA HEAT' 5. OPEN 되었던 CB CLOSE 하고 항공기 원상하라. - 193 - (FCON 3.04.30 P1, POM 7.3.1) ● MMEL 30-42-01 WHC ○ CHECK OF THE HEATERS AND THE FAILURE WARNINGS OF THE FIXED AND SLIDING WINDOWS ASSOCIATED WITH THE OPERATIVE WINDOW HEAT COMPUTER (WHC) (2DG1, 2DG2) (AMM 30-42-00-040-801) 1. WINDSHIELD ANTI-ICING AND DEFOGGING SYSTEM OPERATION TEST 수행. (AMM 30-42-00-710-801) - 관련 CB CLOSE 확인 : R57, D03, D43, X39, G64, S69 - PROBE & WINDOW HEAT PB RELEASE - MCDU SYSTEM REPORT/TEST/ATA:HEATING → WHC1(2) KEY PUSH → 'TEST' PUSH → 'TEST IN PROGRESS 20S' 나타나고 20초 후 'TEST OK' → RETURN 2. 다음 CB OPEN 하라. 3. EWD 에 다음 MESSAGE 가 있는지 확인하라. 'A.ICE L WSHLD HEAT' 'A.ICE R WSHLD HEAT' 'A.ICE L WINDOW HEAT' 'A.ICE R WINDOW HEAT' 4. OPEN 되었던 CB CLOSE 하고 항공기 원상하라. - 194 - ● MMEL 30-45-01-D)b) WINDSHIELD WIPER PARK FUNCTION ○ DEACTIVATION OF THE WINDSHIELD WIPER (AMM 30-45-00-040-803) 1. WINDSHIELD WIPER ARM 을 REMOVE 하라. (AMM 30-45-52-000-801) 1) CB OPEN : E49, H64, W05, S40 2) BOLT (4) 를 FULLY LOOSE (REMOVE 하지말것) 3) SREW (3) REMOVE 하여 WIPER ARM (1) 을 분리하라. 4) CB CLOSE 후 항공기 원상. 2. 다음 CB CLOSE 확인하라 • WXR2 9SQ2 (E49), WXR1 9SQ1 (H64) - 195 - ● MMEL 30-71-01 WATER LINES WASTE WATER IC PROTECTION ○ DEACTIVATION OF WASTEWATER DRAIN-MAST HEATIN-SYSTEM (AMM 30-71-00-040-801) 1. AFT CARGO COMP'T DOOR 또는 BULK CARGO DOOR OPEN 2. 관련 CB CLOSE 확인 : 5058VE (A01, B03, B02) 5060VE (A03, A01, B05, B03, B02, C03), EFF 001~003 5058VE (B01, C06) 3. WASTEWATER ICE-PROTECTION SYSTEM BITE TEST 수행 - MCDU SYSTEM REPORT/TSET COM: CABIN → 'CIDS1' KEY PUSH → 'GND SCANNING' PUSH → 1분후 ‘NO RESULT' MSG 확인 4. PIM (PROGRAMMING AND INDICATION MODULE) 'SYSTEM CHECK‘ MENU 의 ’WATER ICE PROTECTION' 확인 (이 MENU 는 관련 LAVATORY 와 GALLEY 가 CLOSE 되어야만 나타남) 만약, 관련 LAVATORY 와 GALLEY 가 나타나지 않는다면 NO MAINT ACTION. 5. 관련 LAVATORY DEACTIVATION - LAVATORY TOILET SHROUD 분리하여 WATER SHUT-OFF V/V ACCESS - WATER SHUT-OFF V/V CLOSE 하고 TOILET SHROUD INSTALL - LAVATORY DOOR CLOSE - LAVATORY 에 사용금지 PLACARD 부착. 6. 관련 GALLEY WATER SUPPLY DEACTIVATION - WAER SHUT-OFF ACCESS PANEL REMOVE - WAER SHUT-OFF CLOSE 하고 ACCESS PANEL INSTALL - WATER FAUCET 사용금지 PLACARD 부착. - 196 - SCREW (2) LOOSE 하여 SHROUD REMOVE FLOW DIRECTION WATER SHUT OFF V/V - 197 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA31) ● MMEL 31-68-01-A)-a) DMC SWITCHING SELECTOR ○ CHECK OF THE AUTOMATIC ECAM DMC SWITCHING (AMM 31-68-00-040-801) 1. 관련 CB CLOSE 확인 : L12, C45, B72, Q78 2. OVERHEAD RESET PANEL에서 SW-RESET/DMC3 ECAM (13WT3) 를 OPEN 했다 CLOSE. 3. EWD 와 SD IMAGE 가 RESET 후에도 계속 AVAIL 한지 확인하라. - 198 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA32) ● MMEL 32-31-01-B) LGCIU 2 ○ CHECK THAT THE SFCC1 AND SFCC2 OPERATE AND ISOLATE THE LGCIU2 (AMM 32-31-00-040-802) 1. CB 2GA (LGCIU2) 를 OPEN 하기전 SAFETY V/V OPERATION TEST (AMM 32-31-00-710-809) 수행하라. 이는 SAFETY V/V CHANNEL 1 의 사용가능 여부를 확인 하기 위하여 필요하다. ACTION RESULT 1) ADIRU 'OFF' POSTION, 'G' HYD ELEC PUMP ON 2) CB OPEN : 3GA L/G SAFETY V/V (S12) 3) BOTH MLG DOOR 를 GRD OPEN DOOR HANDLE을 이용하여 OPEN 하라. 4) BOTH MLG DOOR 를 GRD OPEN DOOR HANDLE을 이용하여 CLOSE 하라. 5) CB OPEN : 2GA LGCIU2 (U38) 6) BOTH MLG DOOR 를 GRD OPEN - HANDLE이 움직이지 않고 DOOR 가 CLOSE DOOR HANDLE 을 이용하여 되지 않을것 이다 CLOSE 하라. 7) CB CLOSE : 3GA L/G SAFETY V/V (S12) 8) BOTH MLG DOOR 를 GRD OPEN DOOR HANDLE 을 이용하여 - DOOR 가 CLOSE 될것이다 CLOSE 하라. 9) CB CLOSE : 2GA LGCIU2 (U38) 2. CB OPEN 후 SAFETY TAG 부착 : 2GA LGCIU2 (U38) 3. LGCIU2 CB OPEN 하므로서 다음과 같은 COCKPIT EFFECTS 발생할수있음. 27-81 27-94 29-10 32-31 32-48 34-00 SLATS AND FLAPS (ON GROUND) FCSC1 AND SFCS2 (ON GRD) HYD POWER L/G EXTEND AND RETRACT L/G BRAKE FAN NAVIGATION SFCC2 SHOWS ON ECAM STS PAGE - SFCC2 TEST IS NOT POSSIBLE 4개의 EDP FAULT LT ON 됨 - ON ENG START THE RELATED EDP FAULT LT GOES OFF OVHD PANEL EDP PB 에 'FAULT' LT ON ENG START 하면 관련 EDP ‘FAULT’ LT OFF 됨 EWD 에 LGCIU2 FAULT 나타남 BRK FAN REPORT INOP NO TEST FUNCTION FOR : HF2, ADF2, ILS2, VOR2, RMP2/3, GPS1/2, VHF2/3, MLS2/3, SATCOM1,2, RADAR2 - 199 - 5. WHEEL PAGE 에 다음과 같은 COCKPIT EFFECT를 DISPLAY 한다. - 200 - ● MMEL 32-31-02 SAFETY VALVE ○ CHECK THAT THE ALTERNATE CHANNEL OF THE L/G SAFETY VALVE IS OPERATIVE (AMM 32-31-00-040-801) ▲ LANDING GEAR SAFETY V/V SYSTEM1 or 2) 의 OPERATION TEST 를 수행하라. (SYSTEM 1 이 INOP 시 SYSTEM 2 TEST, SYSTEM 2 INOP 시 SYSTEM 1 TEST 할것.) 1. 관련 CB CLOSE 확인 : S12, U38, C76, L63 2. ADIRU 1,2,3 'OFF' POSITION 3. L/G CONTROL LEVER 'DOWN' 4. 'G' HYD ELEC PUMP 'ON' 5. CB OPEN : L/G SAFETY VLV 3GA (S12), LGCIU2 2GA (U38), LGCIU1 1GA (L63), L/G DNLK IND 1GB (C76) (CB OPEN 전 FLIGHT CONFIGURATION PRECAUTION (AMM 32-00-00-860-804) 수행할것.) 6. LGCIU 1 (SYSTEM 2 TEST 시는 LGCIU 2) 을 REMOVE 하라. LGCIU2 LGCIU1 7. MLG DOOR OPEN 8. MLG DOOR HANDLE 을 다시 CLOSE POSITION 으로 하라. : HANDLE NOT MOVE 9. SAFETY V/V (85GA) 에서 SYSTEM 1 (2) ELEC CONNECTOR 를 분리하라. 10. ADIRU1 또는 3 를 'NAV' POSITION 으로 놓아라. (SAFETY V/V SYSTEM 2 TEST 시는 ADIRU2 'NAV') 11. MULTIMETER 로 분리한 ELEC CONNECTOR 의 PIN A 와 B 사이에 28VDC 가 PICK UP 되는지 확인하라. 12. ADIRU1 또는 3 를 'OFF' POSITION 으로 놓아라. (SAFETY V/V SYSTEM 2 TEST 시는 ADIRU2 'OFF') 13. SAFETY V/V (85GA) 의 SYSTEM 1 (2) ELEC CONNECTOR 를 연결하라. - 201 - SYSTEM1 CONNECTOR SYSTEM2 CONNECTOR SYSTEM 2 CONNECTOR 14. LGCIU1 (SYSTEM 2 TEST 시는 LGCIU2) 을 INSTALL 하라. 15. OPEN 되어있는 MLG DOOR 를 CLOSE 하라. 16. 'G' HYD ELEC PUMP 'OFF' 17. LGCIU BITE TEST 수행 (AMM 32-31-00-740-801) (L/G SAFETY V/V 에 관련된 BITE MEMORY 는 무시할것. 일정 SPEED 이하에서는 SAFETY V/V 가 NOT ENER' 되기때문에 이러한 MSG 발생할수있음) 18. DEACTIVATION 수행후 다음과 같은 COCKPIT EFFECTS 발생할수있음. • LGCIU 의 BITE TEST 시 ‘VALVE-HYDRAULIC SAFETY, L/G (85GA)' • AIR TRAFFIC SERVICE UNIT (ATSU) 가 FLIGHT MODE 계속 지시할 때 → OVHD RESET PANEL에서 'SW-RESET/ATSU1' 을 RESET - 202 - ● MMEL 32-41-01 WHEELS WHEEL TIE BOLTS ○ TO CHECK THE WHEEL TIE-BOLTS (AMM 32-41-00-040-801) 1. NLG WHEEL TIE-BOLTS CHECK • TIE-BOLT 의 깨진 흔적이 있는지 확인하라. • 깨진 조각이 WHEEL 안에서 발견시 조각을 제거하라. • WHEEL 의 DAMAGE 상태를 INSTPECTION 하고 만약 DAMAGE 가 발견 (DAMAGE NOT PERMITTED) 되면 WHEEL/TIRE ASSY 를 교환하라. (AMM 32-41-12-000(400)-801) 2. MLG WHEEL TIE-BOLTS CHECK • TIE-BOLT 의 깨진 흔적이 있는지 확인하라. • 깨진 조각이 WHEEL 안에서 발견시 조각을 제거하라. • WHEEL 과 BRAKE 의 DAMAGE 상태를 INSTPECTION 하고 만약 DAMAGE 가 발견 (DAMAGE NOT PERMITTED) 되면 WHEEL/TIRE ASSY (AMM 32-41-11-000(400)-801) 또는 BRAKE (AMM 32-42-27-000(400)-801) 를 교환하라. - 203 - ● MMEL 32-42-01 NORMAL BRAKING MAIN WHEEL BRAKE ○ DEACTIVATION OF THE MAIN WHEEL BRAKE (AMM 32-42-00-040-801) 1. BSCU BITE TEST 수행 (AMM 32-46-00-740-801) 하여 해당 BRAKE 에 관련된 TACHOMETER 결함이 없어야한다. WHEEL/BRAKE 1 2 3 4 5 6 7 8 TACHOMETER FIN 13GG1 14GG1 13GG2 14GG2 15GG1 16GG1 15GG2 16GG2 TACHOMETER DRIVE FIN 5013GG1 5014GG1 5013GG2 5014GG2 5015GG1 5016GG1 5015GG2 5016GG2 2. BRAKING 을 위한 다른 WHEEL 들은 NORMAL 인지 확인할것. ※ BRAKE DEACTIVATION 은 2가지 방법이 있음. BRAKE REMOVAL 이 필요없는 아래 방법이 있고 WHEEL/BRAKE 가 DAMAGE 되어 PART 가 FREE TURN 하지 않을 경우 BRAKE 를 RMOVAL 해야하는 DEACTIVATION 방법이 있음. 3. HYD PUMP OFF, PARKING BRAKE OFF 4. DEACTIVATION WITHOUT THE BRAKE REMOVAL • HYD HALF COUPLING (61), (62) 를 분리하라. • HYD HALF COUPLING (61), (62) 를 TAPE 로 봉인하라. • BRAKE 쪽 HYD CONNECTOR 에 COUPLING (61), (62) 를 WIRE 로 SAFETY 하라. • DUST CAP (63) 을 풀고 BLEED V/V (64) 에 BLEED HOSE를 연결 후 V/V OPEN 하여 BRAKE 의 잔여 PRESSURE 를 제거할것. • BLEED V/V CLOSE (64) 후 DUST CAP (63) 장착 • SERVO V/V 결함시 아래절차 수행 ※ SERVO V/V 의 EELC CONNECOR 는 절대 분리 하지 말것. 만약 분리 하게되면 BRAKING 이 ‘NORM' 에서 ’ALT' 로 넘어가게될뿐 DEACTIVATION 은 안됨. - 관련 PRESSURE TRANDUCE 의 ELEC CONNECTOR (51) 을 분리 - 분리된 ELEC CONNECTOR (51) 에 CAP 씌우고 SAFETY 조치 하라. - 204 - 5. DEACTIVATION WITH THE BRAKE REMOVAL • 관련 WHEEL 을 REMOVE 하라. • 관련 BRAKE 를 REMOVE 하라. • 관련 BRAKE-ROD RESTRAINT 를 REMOVE 하라. • BRAKE-ROD PIN COLLAR-RETAINER 를 REMOVE 하라. • 해당 BRAKE-ROD (9) 를 REMOVE 하여 SAFETY PLACE 에 보관할것. - 205 - 1. BRAKE ROD REMOVE 시 관련 PARTS REMOVE 2. SPACER 장착후 재장착 • BRAKE-ROD SPACER 를 INSTALL 하라. - 나머지 BRAKE ROD (9) 를 SHOCK ABSORBER LUG HOLE 에 ALIGN 시키고 SPACER-BRAKE ROD (460007019) (26) 과 (460007020) (25) 를 장착하여 REMOVED PART INTALL 할것. (SPACER 의 SIZE 가 틀리므로 유의해서 장착할것.) - PIN (15) 의 HEAD 방향은 INBOARD 방향임 (L/G RETRACT 시 HEAD 가 UP 방향) • HYD HALF COUPLING (1), (3) 그리고 ELEC CONNECTOR (2) 를 TAPE 로 봉인하라. • ELEC CONNECTOR (2) 를 BRAKE PIPE MANIFOLD 쪽에 SAFETY 조치하라. • HYD HALF COUPLING (1), (3) 을 BRAKE HOSE FAIRLEAD 쪽에 SAFETY 조치하라. - 206 - • WHEEL 을 INSTALL 하라. • SERVO V/V 결함시 아래절차 수행 ※ SERVO V/V 의 EELC CONNECOR 는 절대 분리 하지 말것. 만약 분리 하게되면 BRAKING 이 ‘NORM' 에서 ’ALT' 로 넘어가게될뿐 DEACTIVATION 은 안됨. - 관련 PRESSURE TRANDUCE 의 ELEC CONNECTOR (51) 을 분리 - 분리된 ELEC CONNECTOR (51) 에 CAP 씌우고 SAFETY 조치 하라. WHEEL 1 2 3 4 PRESSURE TRANSDUCER 5GG1 6GG1 5GG2 6GG2 WHEEL 5 6 7 8 PRESSURE TRANSDUCER 7GG1 8GG1 7GG2 8GG2 • GREEN HYD PUMP ON 하여 BRAKE PEDAL 을 여러번 PUSH → PUMP OFF • BLUE HYD PUMP ON 하여 BRAKE PEDAL 을 여러번 PUSH → PUMP OFF • 관련부위 의 HYD LEAK CHECK 수행. 6. SD 의 해당 BRAKE TEMP INDICATION 이 ‘XX' 지시함. 7. PRESSURE TRANSDUCER 의 ELEC CONNECTOR 가 REMOVE 된 경우 CLASS 3 MSG 로 ‘PRESS XDCR-NORM BRK' 잡힘. EWD 'BRAKES RELEASE FAULT' or 'RESIDUAL BRAKING' MSG 경우 PRESSURE TRANSDUCER 의 ELEC CONNECTOR 를 REMOVE 하면 MSG CANCEL 시킬수있음. 8. 항공기 원상하라. - 207 - ● MMEL 32-42-02 NORMAL BRAKING GREEN BRAKE SYSTEM ○ DEACTIVATION OF THE MAIN WHEEL BRAKE - WITH ISOLATION OF GREEN HYDRAULIC SUPPLY (AMM 32-42-00-040-802) 1. BSCU BITE TEST 수행 (AMM 32-46-00-740-801) 하여 해당 BRAKE 에 관련된 TACHOMETER 결함이 없어야한다. WHEEL/BRAKE 1 2 3 4 5 6 7 8 TACHOMETER FIN 13GG1 14GG1 13GG2 14GG2 15GG1 16GG1 15GG2 16GG2 TACHOMETER DRIVE FIN 5013GG1 5014GG1 5013GG2 5014GG2 5015GG1 5016GG1 5015GG2 5016GG2 2. HYD PUMP OFF, PARKING BRAKE OFF 3. DEACTIVATION WITH ISOLATION OF GREEN HYDRAULIC SUPPLY • HYD HALF COUPLING (11) 를 분리하라. • HYD HALF COUPLING (11) 를 TAPE 로 봉인하라. • HYD HALF COUPLING (11) 을 BRAKE HOSE FAIRLEAD 쪽에 SAFETY 조치하라. • DUST CAP (12) 을 풀고 BLEED V/V (13) 에 BLEED HOSE를 연결 후 V/V OPEN 하여 BRAKE 의 잔여 PRESSURE 를 제거할것. • BLEED V/V CLOSE (13) 후 DUST CAP (12) 장착 • SERVO V/V 결함시 아래절차 수행 ※ SERVO V/V 의 EELC CONNECOR 는 절대 분리 하지 말것. 만약 분리 하게되면 BRAKING 이 ‘NORM' 에서 ’ALT' 로 넘어가게될뿐 DEACTIVATION 은 안됨. - 관련 PRESSURE TRANDUCE 의 ELEC CONNECTOR (51) 을 분리 - 분리된 ELEC CONNECTOR (51) 에 CAP 씌우고 SAFETY 조치 하라. (이전 PAGE 그림 참조) 4. ‘G' HYD ELEC PUMP ON 5. BRAKE PEDAL 을 수차례 PUSH 후 DISCONNECT 부위 LEAK CHECK 수행. 6. ‘G' HYD ELEC PUMP OFF 후 항공기 원상. - 208 - POSITION OF HOSE FOR WHEELS 2,4,6,8 11 POSITION OF HOSE FOR WHEELS 1,3,5,7 FIXED HALF COULPLING - 209 - ● MMEL 32-42-06 LANDING GEAR NOSE WHEEL BRAKE PADS ○ DEACTIVATION OF THE NOSE WHEEL BRAKE BANDS (AMM 32-42-00-040-805) 1. 'G' HYD PUMP OFF 확인 2. NOSE WHEEL STEERING SYSTEM DEACTIVATION 수행. 3. NLG DOOR OPEN 4. BRACKET (4) 으로부터 8개의 NUT 와 BOLT 를 REMOVE. 5. SPRING ASSEMBLY (3) REMOVE. 6. SPRING ASSEMBLY (3) 로부터 PLATE (2) 를 REMOVE. 7. BRACKET (4) 에 PLATE (2) 를 위치한후 8개의 BOLT 와 NUT 로 INSTALL. 1 4 3 8. 항공기 원상하라. - 210 - 2 ● MMEL 32-44-01 ALTERNATE RAKING BLUE BRAKE SYSTEM ○ DEACTIVATION OF THE ALTERNATE BRAKE SYSTEM AT A WHEEL BRAKE (AMM 32-43-00-040-801) 1. HYD PUMP OFF, PARKING BRAKE OFF 2. DEACTIVATION OF THE ALTERNATE BRAKE SYSTEM • HYD HALF COUPLING (2) 를 분리하라. • HYD HALF COUPLING (2) 를 TAPE 로 봉인하라. • BRAKE 쪽 HYD CONNECTOR 에 COUPLING (2) 를 WIRE 로 SAFETY 하라. • DUST CAP (11) 을 풀고 BLEED V/V (12) 에 BLEED HOSE 를 연결 후 V/V OPEN 하여 BRAKE 의 잔여 PRESSURE 를 제거할것. • BLEED V/V CLOSE (12) 후 DUST CAP (11) 장착 3. ‘B' HYD ELEC PUMP ON 5. BRAKE PEDAL 을 수차례 PUSH 후 DISCONNECT 부위 LEAK CHECK 수행. 6. ‘B' HYD ELEC PUMP OFF 후 항공기 원상. 12 11 POSITION OF HOSE FOR WHEEL 2,4,6,8 W H E E L POSITION OF HOSE FOR WHEEL 1,3,5,7 1 2 LEG GEAR SIDE - 211 - ● MMEL 32-44-03 BRAKES PRESSURE INDICATOR ○ CHECK OF THE ALTERNATE BRAKING SYSTEM AND BSCU (AMM 32-44-00-040-801) 1. ALTERNATE BRAKING SYSTEM OPERATION 수행 (AMM 32-43-00-710-801) ※ 아래 TEST 중 TRIPLE INDICATOR 가 UNSERVICABLE 일 경우 INDICATOR 가 작동하지 않기 때문에 BRAKE PISTON 이 올바르게 작동하는지 확인할것. ACTION 1) 'B' HYD ELEC PUMP ON 2) PARKING BRAKE 'OFF' POSITION 3) A/SKID & N/W STRG SW 'OFF' POSITION RESULT NOTE : OPERATION 시 2사람 필요. 한사람은 COCPIT OPERATION 수행 다른 한사람은 BRAKE 의 PISTON 이 실제 작동하는지 확인. - TRIPLE INDICATOR 의 아래쪽 왼쪽 GAGE 가 PEDAL 에 따라서 움직임. 4) L/H BRAKE PEDAL - FULL PEDAL 움직임에 따른 PRESSURE 는 2,400~2,682 PUSH PSI 임. - ALTERNATE BRAKE PISTON 이 EXTEND 됨. - TRIPLE INDICATOR 의 아래쪽 왼쪽 GAGE 가 ZERO 5) L/H BRAKE PEDAL PRESSURE 지시 RELEASE - ALTERNATE BRAKE PISTON 이 RETRACT 됨. - TRIPLE INDICATOR 의 아래 오른쪽 GAGE 가 PEDAL 에 따라서 움직임. 6) R/H BRAKE PEDAL - FULL PEDAL 움직임에 따른 PRESSURE 는 2,400~2,682 PUSH PSI 임. - ALTERNATE BRAKE PISTON 이 EXTEND 됨. - TRIPLE INDICATOR 의 아래 오른쪽 GAGE 가 ZERO 5) R/H BRAKE PEDAL PRESSURE 지시 RELEASE - ALTERNATE BRAKE PISTON 이 RETRACT 됨. R/H PEDAL L/H PEDAL - 212 - 2. 'B' HYD ELEC PUMP OFF 3. PARKING BRAKE CONTROL V/V MOTOR 1 AND 2 OPEARATION CHECK 수행. (AMM 32-45-00-710-803) ※ 아래 TEST 중 TRIPLE INDICATOR 가 UNSERVICABLE 일 경우 INDICATOR 가 작동하지 않기 때문에 BRAKE PISTON 이 올바르게 작동하는지 확인할것. ACTION RESULT 1) CB OPEN : PARK BRK EMER CTL 2GZ (K70) → NO.2 MOTOR ISOLATION 됨. - EWD : 'PARK BRK' MEMO MSG - TRIPLE INDICATOR 의 LH/RH PRESSURE 가 약 2500 2) PARKING BRAKE 'ON' PSI 지시 POSITION - BRAKE PISTON (BLUE SYSTEM) 이 EXTEND 됨. - NLG 의 NWS BOX 에 PARKING BRAKE LT 'ON' - EWD : 'PARK BRK' MEMO MSG 사라짐 3) PARKING BRAKE 'OFF' - TRIPLE INDICATOR 의 LH/RH PRESSURE 가 ZERO 지시 POSITION - BRAKE PISTON (BLUE SYSTEM) 이 RELEASE 됨. - NLG 의 NWS BOX 에 PARKING BRAKE LT OFF 4) CB CLOSE : - NO.2 MOTOR ENERZIED 됨. 2GZ (K70) 5) CB OPEN : PARK BRK EMER CTL 1GZ (P35) → NO.1 MOTOR ISOLATION 됨. - 현상은 동일하지만 NLG 의 NWS BOX 에 PARKING 6) 2)항과 3번항 수행 BRAKE LT 는 OFF 유지됨. 7) CB CLOSE : - NO.1 MOTOR ENERZIED 됨. 1GZ (P35) 8) NLG 의 NWS BOX 에 PARKING BRAKE LT ON 됨. 4. BSCU BITE TEST 수행 (AMM 32-46-00-740-801) 5. TRIPLE INDICATOR INOP PLACARD 부착후 항공기 원상. - 213 - ※ 한 L/G 당 2개까지 INOP CONDITION 가능 ● MMEL 32-47-01-A) BRAKE SYSTEM TEMPERATURE INDICATIONS ON ECAM WHEEL PAGE BRAKES TEMPERATURE ○ DEACTIVATION OF THE BRAKE TEMPERATURE SENSOR (AMM 32-47-00-040-801) 1. CB OPEN : BRK TEMP WHL5 TO 8 1GW (G63), BRK TEMP WHL1 TO 4 2GW (U39) ※ 1~4 또는 5~8 까지의 TEMP SENSOR 모두를 DEACTIVE 할 경우 관련 CB 만 OPEN 하면 됨. 아래절차는 개별적인 TEMP SENSOR 의 DEACTIVE 방법임. 2. CONNECTOR (2) 로부터 HEAT SHRINK SLEEVE 를 잘라내어 제거하라. 3. TEMP SENSOR 로부터 CONNECTOR (2) 를 DISCONNECT 하라. 4. QUICK RELEASE PIN (6)을 REMOVE 하고 CABLE (1) 로부터 CABLE CLAMP (5)를 REMOVE 하라. 5. QUIK RELEASE PIN (6) 을 CABLE CLAMP (5) 와 함께 CABLE CLAMP BRACKET 에 고정하라. 6. CABLE (1) 을 CABLE GUIDE 로부터 빼내어라. 7. CONNECTOR (2) 에 CAP 을 씌우고 POLYTHENE BAG 에 집어넣어 TAPE 로 봉인하라. 8. CONNECTOR (2) 와 CABLE (1) 을 BOGIE BEAM BRAKE MANIFOLD 쪽에 TIE-WARP (3) 으로 ATTACH 하라. 9. OPEN 되었던 CB CLOSE 하라. 10. A/SKID & N/W STRG SWITCH 를 OFF 했다가 ON 하라. 11. 관련 BRAKE TEMP 는 SD WHEEL PAGE 에 ‘XX' 지시할것임. 12. 항공기 원상하라. CABLE CLAMP BRACKET 6 1 CABLE GUIDE - 214 - 5 - 215 - ● MMEL 32-49-02-A)a) BRAKE SYSTEM TEMPERATURE INDICATIONS ON ECAM WHEEL PAGE BRAKES TEMPERATURE ○ DEACTIVATION OF THE TIRE PRESSURE INDICATING COMPUTER (TPIC) (AMM 32-49-00-040-802) 1. CB OPEN : TYRE PRESS IND 1GV (T09) 2. SD WHEEL PAGE 에 TIRE PRESSURE 가 AMBER 'XX' 지시하는지 확인 3. MEL 적용이후 첫 번째 DISPATCH 그리고 매 3일마다 ALL TIRE PRESSURE CHECK 수행. - 216 - ※ TPIS SENSOR 의 개별 DEACTIVATION 은 많은 시간을 소요하므로 긴 MAINT' ACTION 에 의한 지연을 막고자 MEL 32-49-02A)a) 를 적용하여 전체 TPIC DEACTIVATION 인 TPIC C/B PULLING 을 AIRBUS 에서는 권고하고있음. ● MMEL 32-49-02-A)b) TIRE PRESSURE INDICATING SYSTEM WARNING AND CAUTION ON ECAM E/WD WHEEL TIRE LO PR ○ DEACTIVATION OF THE TIRE PRESSURE INDICATING SYSTEM (TPIS) (AMM 32-49-00-040-801) 1. TP GAGE 사용하여 'WHEEL TIRE LO PR' MSG 나온 관련 TIRE 의 PRESSURE CHECK. 2. 만약 TIRE PRESSURE 가 NORMAL 이라면 아래 절차수행. 3. DEACTIVATION OF THE MLG TPIS SENSOR • DEBRIS GUARD (6) 와 SHROUD (5) REMOVE. • NUT (4) 의 WIRE 제거하고 NUT LOOSE 하여 FAN (3) REMOVE. • TPIS CONNECTOR (9) DICONNECT 한다음 CAP 을 씌워 봉인함. • TPIS CABLE 과 CONNECTOR (9) 를 WHEEL HUB 에있는 TPIS SENSOR 쪽에 TIE-WRAP 으로 ATTACH 하라. (이때 WHEEL 의 회전에의해 DAMAGE 가 발생되지 않 도록 단단히 묶을것.) • REMOVE 되었던 PARTS 다시 INSTALL. 4. DEACTIVATION OF THE NLG TPIS SENSOR • CLAMP (4) 와 GROMMET (1) 을 REMOVE 하여 HUB CAP 분리. • TPIS CONNECTOR (2) DICONNECT 한다음 CAP 을 씌워 봉인함. • TPIS CABLE 과 CONNECTOR (2) 를 WHEEL HUB 에있는 TPIS SENSOR 쪽에 TIE-WRAP 으로 ATTACH 하라. (이때 WHEEL 의 회전에의해 DAMAGE 가 발생되지 않 도록 단단히 묶을것.) • REMOVE 되었던 PARTS 다시 INSTALL. 5. 항공기 원상하라. 6. PFR 에 TPIS 관련 FAULT 가 매번 나타날것임. - 217 - - 218 - ● MMEL 32-51-03-b) NWS ELECTIRCAL DEVIATION BOX (FOR A/C TOWING) ○ DEACTIVATION OF NOSE WHEEL STEERING ELECTRICAL BOX (FOR FLIGHT) (AMM 32-51-00-040-802) 1. NWS DEACTIVATION BOX (5GC) 의 LEVER (2) 를 NON-TOWING POSITION 으로 SET 2. ELEC CONNECTOR (3) 을 DISCONNECT 여 CAP 을 씌우고 SAFETY 조치하라. 3. NWS DEACTIVATION BOX (5GC) 에는 ELEC' SUPPLY 가 되지 않음. • PARKING BRAKE LT → OFF 상태유지됨. - 219 - 1) NWS CONTROL SYSTEM 의 DAMAGE INSPECTION. 2) TOW BAR 있는 TOWING CAR 사용하여 TOWING 또는 OVERSTEER DETECTION 기능이 있 는 TOWBARLESS TOWING CAR 사용하여 TOWING 수행. ● MMEL 32-53-01-A) NWS ANGLE PROTECTION ELEC TOW LIMIT WARNING SYSTEM FAULT LIGHT ○ DEACTIVATION OF THE STEERING ANGLE PROTECTION SYSTEM (AMM 32-53-00-040-801) 1. NOSE WHEEL 을 양방향으로 30° TURN 하여 다음 PART 에대한 VISUAL INSPECTION 수행. (COMPONENT 의 DISCONNECT 는 필요없음.) • STEERING ACTUATOR 의 PISTON ROD END • UPPER FLANGE AND LOWER FLANGE 의 PIN 이 장착되는 AREA. INSPECTION AREA - 220 - ● MMEL 32-61-02 POSITION AND WARNING GEAR NOT DOWN WARNING ○ CHECK THAT THE ECAM WARNING 'L/G GEAR NOT DOWN' IS OPERATIVE (AMM 32-61-00-040-801) ◆ LANDING GEAR NOT DOWN WARNING 에 대한 OPERATION TEST 수행 (AMM 32-61-00-710-801) ※ DOWN ARROW LIGHT 는 작동하지 않을것임. • FULLY ENTEND THE FLAP • FADEC GND PWR 1 과 2 PB PUSH : 'ON' LT ON • LGCIU1 SIMULATION PAGE 접근 : MCDU SYSTEM REPORT/TEST L/G:EXT/RETR page → 'LGCIU1 → 'L-G CONFIGURATION SIMULATION' PUSH → 'START TEST' PUSH → 'CONFIRM START OF TEST' • CB OPEN : LGCIU2 2GA (U38) ※ LGCIU CB OPEN 전에 FLIGHT CONFIGURATION PRECATION 수행 (AMM 32-00-00-860-804) PNL 715VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 721VU 722VU 722VU 722VU 722VU DESIGNATION FIN ANTI ICE WSHLD R 1DG2 ICE DET 1 2DD1 ANTI ICE TAT 1 12DA1 TCAS 4SG ANTI ICE AOA 3 31DA3 ANTI ICE WINDOWS L 4DG1 LT RWY TURN OFF L 1LC LT TAXI/T.O L 1LR RA 1 2SA1 ANTI ICE PITOT 3 4DA1 PHC 3 2DA3 PHC 1 2DA1 TURBO FAN CTL 3HR LA/DAR/QAR 28VDC 9TU ANTI ICE STAT 3 11DA3 ANTI ICE STAT 1 11DA1 ON A/C 001-56, 101-199 HF2 2RE2 ON A/C ALL LT TAXI/T.O R 2LR LT RWY TURN OFF R 2LC ANTI ICE WINDOWS R 4DG2 LOC R57 B07 B06 B05 C05 D03 H03 H02 L14 L07 N07 P12 T06 U11 W10 W09 E37 D48 D47 D43 PNL 722VU 722VU 722VU 722VU 722VU 722VU 722VU 722VU 722VU 722VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU 742VU - 221 - DESIGNATION FIN ANTI ICE AOA 2 1DA2 ICE DET 2 2DD2 ANTI ICE PITOT 2 4DA2 BRK FAN CTL 5GD LT TAXI/T.O CTL 3LR SDCU CHAN 2 12WH CPC 2 2HL ANTI ICE STAT 2 11DA2 PHC 2 2DA2 WHC 2 5DG2 CPC 1 1HL APU START CTL 1KA HYD RAT EXT SOL 2 5JR 28VDC ESS BUS 6QC 28VDC ESS BUS 5QC WHC 1 5DG1 HF 1 2RE1 RAT MAN ON 2JR SDCU CHAN 1 11WH CSM/G MAN START 22XE ANTI ICE PITOT1OR3 3DA ANTI ICE AOA 1 OR 3 31DA1 LOC F48 F47 F43 R44 R41 T38 U44 X41 X40 X39 A66 C72 D76 F65 F64 G64 J63 K74 L75 N61 Q72 Q68 722VU ATC 2 3SH2 E47 742VU ATC 1 3SH1 Q64 722VU RA 2 2SA2 E46 742VU ANTI ICE WSHLD L 1DG1 S69 722VU ANTI ICE TAT 2 12DA2 E43 CAUTION : 2DA1(P12), 2DA2(X40), 2DA3(N07), 5DG1(G64),5DG2(X39) 는 맨마지막에 OPEN 시킬것. 그렇지 않으면 HEATING SYSTEM 의 원치않는 작동이 이뤄지게 됨. CB CLOSE 시킬때는 제일먼저 상기 CB 를 CLOSE 시킬것. ACTION 1) MCDU 화면에서 'NOSE+LH+RH' KEY PUSH 2) 'UPLOCKED' KEY PUSH 3) EMER CANC PB PUSH 4) MCDU 에서 RETURN KEY PUSH RESULT - 'NOSE+LH+RH' SCREEN DISPLAY - MASTER WARN LT FLASH - WARNING CHIME 울림. ON THE SD WHEEL PAGE - L/G UP POSITION 이 되고 30초후에 ‘L/G CTL' MSG 나 타남. (LGCIU2 CB 가 OPEN 되어서 AMBER CROSS 가 나타남) ON THE EWD - 'L/G NOT DOWN' MSG DISPLAY - 'UNLK' RED LIGHT ON - DOWN ARROW LIGHT ON (INOP 시 ON 되지 않음) - WANING CHIME STOP & MASTER WARN LT OFF - ALL MSG 와 INDICATION 이 원상됨. (LGCIU2 CB 가 OPEN 되어서 AMBER CROSS 계속 나타남) • OPEN 되었던 CB CLOSE 후 항공기 원상. - 222 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA33) ● MMEL 33-20-01 b) CABIN SIGNS (NO SMOKING / FASTEN SEAT BELT / RETURN TO SEAT) ○ DEACTIVATION OF THE CABIN NO SMOKING/FASTEN SEAT BELT (NS/FSB) SIGNS (AMM 33-20-00-040-801) 1. DO THE OPERATIONAL TEST OF THE PASSENGER LIGHTED SIGN 의 OPERATION TEST 를 수행 (AMM 23-73-00-710-806) 하여 결함있는 NS/FSB SIGN 을 찾아라. 2. INOP 된 NS/FSB SIGN 을 볼수없는 PASSENGER SEAT 를 찾아서 해당 SEAT 를 BLOCK 시켜라. NOTE : 모든 PAX SEAT 에서는 NS/FSB SIGN 을 볼수있어야함. - 223 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA34) ● MMEL 34-10-01-A) ADIRS IR ○ IR SYSTEM - CHECK OF THE VERTICAL ACCELEROMETERS AND RATE GYRO UNIT (AMM 34-10-00-040-801) ◆ 각 FLIGHT 전에 EFCS 의 BITE TEST (AMM 27-96-00-740-802) 를 수행하라. 이때 CLASS1 또는 2 로 아래의 FALSE 가 MAINT IND 으로 있으면 안된다. - VERTICAL ACCELERMETER (Nz) : 6EC1/16CE2 - RATE GYRO UNIT : 18CE ※ INERTIAL MODE : 통상적으로 ADIRS 의 IR 에서 지시하는데 IR VERTICAL SPEED CONTROL 을 INERTIAL MODE 라 하고 IR SIGNAL 이 FAIL 되면 VERTICAL SPEED 는 AUTO 로 ADR 에서 대체됨 ※ INERTIAL MODE 가 FAIL 되었을때 INDICATION : V/S를 나타내는 숫자 주위의 WINDOW 가 AMBER 로 변함. - 224 - ※ ALL ADIRS, SFCC, LGCIU 가 NORMAL 이어야함. NOTE : RA1 이 INOP 시, GPWS 와 TAWS 의 REACTIVE MODE 가 작동이 안됨. ● MMEL 34-42-01 RADIO ALTIMETER ○ DEACTIVATION OF THE RADIO ALTIMETER (AMM 34-42-00-040-801) ◆ CB OPEN : RA1 2SA1 (L14), RA2 2SA2 (E46) ※ INTRUDER 와의 충돌 예상시간(TAU)이 25S 일 경우 CREW 는 즉시 ACTION을 취해야함 ON PFD : VERTICAL ORDER ON ND : INTRUDER POSTION (RED SQUARE) AURAL SOUND : MONITORING V/S etc. ● MMEL 34-43-01 TCAS ○ DEACTIVATION OF THE TRAFFIC COLLISION AVOIDANCE SYSTEM (AMM 34-43-00-040-801) ◆ CB OPEN : TCAS 4SG (B05) REF' ONLY ※ A330 운항기술공지 제목 : TACS AMBER MSG (REV.05 : EFFECTIVITY CHANGE) 1. 배경 : TRANSPONDER 교환 장착 및 WIRING PROVISION 작업을 수행한 특정 항공기에서 , PWR-UP 또는 TCAS SYSTEM RESET (TACS 초도 PWR-UP) 시에 , ECAM INOP PAGE 에 TCAS AMBER MSG 가깜박임. 이는 MODE S STRNSPONDER 와 TCAS COMPUTER 간의 DATA COMMUNICATION 문제로 인하여 발생하는 현상임. 2. 적용항공기 (14대) : HL7525/24/38/39/50/51/52/53/54/84/85/87/7709 - 225 - 3. 운항승무원 조치사항 - 항공기 PWR-UP 또는 TCAS RESET 시에 ATC/TCAS CONTROL PNL 이 STBY 에있는 경우 그다음에 ATC/TCAS CONTROL PNL에서 TA ONLY 또는 TA/RA 를 선택하면 TCAS AMBER MSG 가 사라지면서 정상작동됨. - 항공기 PWR-UP 또는 TCAS RESET 시에 ATC/TCAS CONROL PNL 이 TA ONLY 또는 TA/RA 에 있는 경우, 그다음 ATC/TCAS CONTROL PNL에서 어떤 것을 선택하든지 (STBY, XPNDR, TA ONLY, TA/RA) TCAS SYSTEM은 정상작동함. 4. 향후 조치 - 해당 공시는 PON FCB 가 발행될때까지 유효 - SYSTEM BACKGROUND 관련된 좀더 상세 정보가 CREW LINK LIBRARY 에 등재되어있으니 참조하기 바랍니다. 2005.07.28 운항기술팀장 운항기술공시 OEM 05-08 R2 담당:6266 • CPA : CLOSEST POINT OF APPROACH • TAU : ESTIMATED TIME 충돌위험이 높은 V/S RANGE 권고하는 V/S RANGE LEVEL INTRUDER POSITION - NO COLLISION THREAT - INTRUDER IN VICINITY TO A/C (CLOSER THAN 6NM IN LATERAL AND ± 1200FT IN VERICAL DIRECTION) - ND : INTRUDER POSITION RESOLUTION ADVISORY (RA) (RED SQUARE) - REAL COLLISION THREAT - TAU IS ABOUT 25S OTHER INTUDERS (WHITE EMPTY DIAMOND) - NO COLLISION THREAT - ANY NON PROXIMATE, TA, RA WITHIN THE SUVEILLANCE ENVELOPE (LATERAL RANGE : CLOSER THAN 30NM) - ND : INTRUDER POSITION - AURAL MESSAGE - PFD : VERTICAL ORDERS. MAINTAIN ACTUAL V/S (REVENTIVE ADVISORY) OR MODIFY V/S (CORRECTIVE ADVISORY) PROXIMATE (WHITE DIAMOND) TRAFFIC ADVISORY (TA) (AMBER CIRCLE) - POTENTIAL COLLISION THREAT - TAU IS ABOUT 40S - 226 - DISPLAYED INFORM - ND : INTRUDER POSITION - AURAL MESSAGE - ND : INTRUDER POSITION A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA35) ● MMEL 35-13-01-A)-a) CREW OXYGEN CONTROL AND INDICATING OXY HIGH PRESSURE INDICATION ○ CHECK OF HIGH PRESSURE OF THE CREW OXYGEN CYLINDER (AMM 35-10-00-040-803) ◆ 매 FLIGHT 전 OXYGEN CYLINDER 의 DIRECT-READING PRESSURE GAGE 를 확인하여 CREW 에게 전달. - 227 - ● MMEL 35-23-01-A)-a) PASSENGER OXYGEN MASK MANUAL ON PB MAN CONTROL ○ CHECK OF THE AUTO CONTROL FUNCTION OF THE MASK MAN PUSHBUTTON (AMM 35-23-00-200-804) 1. 관련 CB CLOSE 확인 : C80, C79, C78, C77, P76, P75, P74, P73, P72, P71, P70, P69 5001VE G11(EFF 001~056, 101~199), 5001VE H11 (EFF 057~099) 2. 모든 OXYGEN CONTAINER 의 DOOR STOP 을 PULL OUT 하여 TEST POSITON 으로 TURN 하라. 3. ALTITUDE PRESSURE SWITCH 16WR 에 HOSE-ADPTER (98A35207599000) 연결후 VACUUM SORCE 연결 - 228 - ACTION RESULT 1) CB OPEN : PAX OXY CTL 3WR (C79), PAX OXY CTL 4WR (C80) - ALL EMER OXY CONTAINER OPEN 됨. 2) GUARD 올리고 ‘MASK - ‘SYS ON' LT ON MAN ON' PB PUSH - EMERGENCY ANNOUNCMENT 시작됨. (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) 3) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 4) OPEN 되었던 ALL EMER OXY CONTAINER 를 CLOSE 시켜라. - 14000(+250, -750)FT PRESSURE 에서 5) VACUMM SORCE • ‘SYS ON' LT ON 작동하여 14800FT 의 • EMERGENCY ANNOUNCMENT 시작됨. PRESSURE 로 (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) DECREASE 하라. • 해당 EMER OXY CONTAINER OPEN 됨. 6) 서서히 PRESSURE 를 증가시켜 GROUND LEVEL 로 맞추어라. 7) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH 8) ON THE RELAY BOX 751VU - RELAY 24WR 를 REMOVE 하고 24WRA2 와 24WRA3 사이에 JUMER 장착하라 - RELAY 25WR 를 REMOVE 하고 25WRA2 와 25WRA3 사이에 JUMER 장착하라 - ‘SYS ON' LT ON 9) GUARD 올리고 ‘MASK - EMERGENCY ANNOUNCMENT 시작됨. MAN ON' PB PUSH (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) - 30초후 ‘FAULT' LT ON 됨. 10) 25WRA2 와 25WRA3 - ‘FAULT' LT OFF 됨. 사이의 JUMER 제거하라. RELAY 25WR 을 장착 - ‘FAULT' LT 가 15초간 ON 됨. 하라. 11) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 12) OPEN 되었던 해당 EMER OXY CONTAINER 를 CLOSE 시켜라. - 관련 EMER OXY CONTAINER OPEN 됨. 13) GUARD 올리고 - ‘SYS ON' LT ON ‘MASK MAN ON' PB - EMERGENCY ANNOUNCMENT 시작됨. PUSH (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) 14) 15초 후에 OPEN 되 었던 EMER OXY - EMER OXY CONTAINER DOOR 는 그대로 CLOSE 유지함. CONTAINER 를 CLOSE 하라. 15) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 16) ON THE RELAY BOX 751VU - 24WRA2 와 24WRA3 사이의 JUMER 제거하고 RELAY 24WR 을 장착하라. - RELAY 25WR 를 REMOVE 하고 25WRA2 와 25WRA3 사이에 JUMER 장착하라 - 관련 EMER OXY CONTAINER OPEN 됨. 17) GUARD 올리고 - ‘SYS ON' LT ON ‘MASK MAN ON' PB - EMERGENCY ANNOUNCMENT 시작됨. PUSH (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) - 229 - ACTION RESULT 18) 15초 후에 OPEN 되 었던 EMER OXY - EMER OXY CONTAINER DOOR 는 그대로 CLOSE 유지함. CONTAINER 를 CLOSE 하라. 19) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 20) ON THE RELAY BOX 751VU - 25WRA2 와 25WRA3 사이의 JUMER 제거하고 RELAY 25WR 을 장착하라. - 관련 EMER OXY CONTAINER OPEN 됨. 21) GUARD 올리고 - ‘SYS ON' LT ON ‘MASK MAN ON' PB - EMERGENCY ANNOUNCMENT 시작됨. PUSH (PRE-RECORDED 된 ANNOUNCEMENT 가 끝나면 STOP 됨.) 22) ‘TMR RESET' PB - 'SYS ON' LT OFF PUSH - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 23) IN THE CABIN - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE FIRST 4 SEAT ROWS. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS IN AN AREA OF 4 SEAT ROWS BETWEEN THE DOOR 2 AND 3. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE LAST 4 SEAT ROWS. 24) CB 4WR (C80) CLOSE 하고 아래 CB OPEN : PAX OXY ACTUATION 5WR (P76), 7WR (P74), 9WR (P72), 10WR (P71), 11WR (P70), 12WR (P69) → RELAY 28WR 을 CHECK 하기위함. 25) GUARD 올리고 ‘MASK MAN ON' PB - 관련 EMER OXY CONTAINER 중 일부가 즉시 OPEN 됨. 을 MIN 6초동안 - 약 6초 후 관련 EMER OXY CONTAINER 모두 OPEN 됨. PUSH 하라. 26) ‘TMR RESET' PB - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. PUSH 27) IN THE CABIN - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE FIRST 4 SEAT ROWS. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS IN AN AREA OF 4 SEAT ROWS BETWEEN THE DOOR 2 AND 3. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE LAST 4 SEAT ROWS. 28) CB 4WR (C80) OPEN 하고 3WR (C79) CLOS 하라. 29) GUARD 올리고 ‘MASK MAN ON' PB - 관련 EMER OXY CONTAINER 중 일부가 즉시 OPEN 됨. 을 MIN 6초동안 - 약 6초 후 관련 EMER OXY CONTAINER 모두 OPEN 됨. PUSH 하라. 30) ‘TMR RESET' PB - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. PUSH - 230 - ACTION RESULT 31) IN THE CABIN - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE FIRST 4 SEAT ROWS. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS IN AN AREA OF 4 SEAT ROWS BETWEEN THE DOOR 2 AND 3. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE LAST 4 SEAT ROWS. 32) CB 6WR (P75) 과 8WR (P73) 을 OPEN 하고, 9WR (P72) 과 11WR (P70)을 CLOSE 하라. → RELAY 29WR 을 CHECK 하기위함. 33) GUARD 올리고 ‘MASK MAN ON' PB - 관련 EMER OXY CONTAINER 중 일부가 즉시 OPEN 됨. 을 MIN 6초동안 - 약 6초 후 관련 EMER OXY CONTAINER 모두 OPEN 됨. PUSH 하라. 34) ‘TMR RESET' PB - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. PUSH 35) IN THE CABIN - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE FIRST 4 SEAT ROWS. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS IN AN AREA OF 4 SEAT ROWS BETWEEN THE DOOR 2 AND 3. - CLOSE ALL OF THE DOORS OF THE EMERGENCY OXYGEN CONTAINERS AT THE LAST 4 SEAT ROWS. 36) CB 3WR (C79) OPEN 하고 4WR (C80) 을 CLOSE 하라. 37) GUARD 올리고 ‘MASK MAN ON' PB - 관련 EMER OXY CONTAINER 중 일부가 즉시 OPEN 됨. 을 MIN 6초동안 - 약 6초 후 관련 EMER OXY CONTAINER 모두 OPEN 됨. PUSH 하라. 38) ‘TMR RESET' PB PUSH 39) CB CLOSE : 3WR(C79), 5WR(P76), 6WR(P75),7WR(P74), - 'TMR REST' PB 에 'ON' LT ON 되었다가 사라짐. 8WR(P73),10WR(P71), 12WR(P69) 4. 모든 OXYGEN CONTAINER 의 DOOR STOP 을 NORMAL POSITION 으로 원상하라. 5. ALTITUDE PRESSURE SWITCH 16WR 의 장비제거하라. 6. OPEN 되었던 CB CLOSE 확인하고, 항공기 원상하라. - 231 - RELAY 24WR, 25WR BASE 24WRA, 25WRA - 232 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA36) ※ PRV CLOSE DEACTIVE 하고 관련 BLEED AIR SYSTEM 은 INOP' 으로 간주함. ● MMEL 36-11-02 BLEED VALVE ○ DEACTIVATION OF THE BLEED VLAVE (4001HA) (AMM 36-11-00-040-807) CAUTION : LOCKING PIN 장착시 제대로 ALIGN 안시키거나 많은 힘으로 TIGHT 하면 THREAD 가 망가질수있음. 주의할것. 1. CB OPEN : ENG1 (D44, Q73), ENG2 (K49, Q74) 2. 해당 ENG 의 LH REVERSER COWL OPEN 하라. 3. LOCKING PIN (1) REMOVE 하라. 4. MANUAL OVERRIDE 의 'CLOSED' POSTION 에 LOCKING PIN (1) 을 장착하라. (만약 LOCKING PIN 이 HEXAGONAL 이면 TORQUE 는 71~79 inlb 이다.) 5. SD BLEED PAGE 확인하여 관련 BLEED VALVE 가 CLOSE 되었는지 확인하라. 6. ENG COWL CLOSE & OPEN 되었던 CB CLOSE 하고 항공기 원상하라. 1 - 233 - 1) HP VALVE 를 CLOSE DEACTIVE 하라. 2) LOW POWER SETTING 시는 HP VALVE 가 CLOSE 되어있어 관련 ENG BLEED SYSTEM 은 사용할수없다. ● MMEL 36-11-06 b) IP CHECK VALVE ○ DEACTIVATION OF THE HP BLEED VALVE (4000HA) IN CLOSED POSITION TO ISOLATE THE IP BLEED CHECK-VALVE (7110HA) (AMM 36-11-00-040-808) CAUTION : LOCKING PIN 장착시 제대로 ALIGN 안시키거나 많은 힘으로 TIGHT 하면 THREAD 가 망가질수있음. 주의할것. 1. CB OPEN : ENG1 (D44, Q73), ENG2 (K49, Q74) 2. 해당 ENG 의 LH REVERSER COWL OPEN 하라. 3. LOCKING PIN (1) REMOVE 하라. 4. MANUAL OVERRIDE 의 'CLOSED' POSTION 에 LOCKING PIN (1) 을 장착하라. (만약 LOCKING PIN 이 HEXAGONAL 이면 TORQUE 는 71~79 inlb 이다.) 5. SD BLEED PAGE 확인하여 관련 BLEED VALVE 가 CLOSE 되었는지 확인하라. 6. ENG COWL CLOSE & OPEN 되었던 CB CLOSE 하고 항공기 원상하라. 1 - 234 - 1) HP VALVE 를 CLOSE DEACTIVE 하라. 2) LOW POWER SETTING 시는 HP VALVE 가 CLOSE 되어있어 관련 ENG BLEED SYSTEM 은 사용할수없다. ● MMEL 36-11-07 b) HP VALVE DEACTIVATED IN CLOSED ○ DEACTIVATION OF THE HP BLEED VALVE (4000HA) (AMM 36-11-00-040-809) CAUTION : LOCKING PIN 장착시 제대로 ALIGN 안시키거나 많은 힘으로 TIGHT 하면 THREAD 가 망가질수있음. 주의할것. 1. CB OPEN : ENG1 (D44, Q73), ENG2 (K49, Q74) 2. 해당 ENG 의 LH REVERSER COWL OPEN 하라. 3. LOCKING PIN (1) REMOVE 하라. 4. MANUAL OVERRIDE 의 'CLOSED' POSTION 에 LOCKING PIN (1) 을 장착하라. (만약 LOCKING PIN 이 HEXAGONAL 이면 TORQUE 는 71~79 inlb 이다.) 5. SD BLEED PAGE 확인하여 관련 BLEED VALVE 가 CLOSE 되었는지 확인하라. 6. ENG COWL CLOSE & OPEN 되었던 CB CLOSE 하고 항공기 원상하라. 1 - 235 - ● MMEL 36-12-02 a) APU BLEED VALVE SECURED CLOSED POSITION ○ DEACTIVATION OF THE APU BLEED VALVE (59KH7) (AMM 49-51-00-040-801) 1. APU 작동금지 TAG 를 COCKPIT 에 부착하라. 2. BULK CARGO DOOR OPEN 하여 ACCESS PANEL 162KW REMOVE 3. CB OPEN 5000VE 162KW - 236 - 4. APU COMPARTMENT DOOR (316AR) OPEN 5. APU BLEED VALVE 가 CLOSED POSITION 에 있는지 BLEED VALVE 의 VISUAL INDICATOR 를 통해서 확인하라. NOTE : 만약 BLEED VALVE 가 CLOSE 되어있지 않다면 BLEED VALVE 를 교환하라. VALVE 를 교환할 여건이 안될 경우 ALTERNATIVE MMEL PROCEDURE 적용하라. 6. WIRING CONNECTOR P12 (6) 을 SOLENOID CONNECTOR (5) 로부터 분리하라. 7. 분리된 CONNECTOR (5), (6) 에 CAP을 씌우고 WIRING CONNECTOR P12 (6) 을 TIE-WARP 으로 WIRING HARNESS 에 ATTACH 하라. NOTE : WIRING CONNECTOR P7 (7) 이 잘 연결되어있는지 확인하라. 8. PNEU PIPE (1) 을 UNION (4) 로부터 REMOVE 하라. 9. CAP (MS21914-4J) (3) 을 UNION (4) 에 장착하라. 10. PLUG (MS21913J4) (2) 를 PNEU PIPE (1) 에 장착하라. 11. PNEU PIPE 의 끝을 TIE-WARP 을 사용하여 SAFETY 조치하라. NOTE : 다른 COMPONENT 에 의해 DAMAGE 입지 않도록 조치할것. 12. OPEN 되었던 CB CLOSE, DOOR & PANEL CLOSE 후 항공기 원상하라. MS21913J4 2 3 1 MS21914-4J 4 5 P7 - 237 - 6 7 P12 ● MMEL 36-23-01 A)a) EWD AIR ENG1(2) BLEED LEAK FALSE ○ DEACTIVATION OF THE OVERHEAT SENSING-ELEMENT (2HF1, 2HF2) (AMM 36-22-00-040-805) 1. APU 또는 GTC 사용하여 관련 PYLON 부위의 AIR LEAK CHECK 수행. (AMM 36-22-00-790-801, AMM 36-11-48-790-801) ※ LEAK : NO GO. 결함 조치후 비행가능. NO LEAK : 아래사항 수행 2. APU, ENG BLEED PB OFF 후 작동금지 TAG 부착 3. 관련 PYLON 부위의 OVERHEAT SENSING-ELEMENT 를 REMOVE하고 CONNECTOR 부위 에 CAP 씌워 SAFETY 조치하라. (AMM 36-22-15-000-806) • CB OPEN : ENG1 (D44, C73, Q73), ENG2 (K49, T34, Q74) • ACCESS PANEL OPEN : FOR 2HF1 (452AL), FOR 2HF2 (462AL) • 4개의 SCREW (12), (18) 을 풀고 CLAMP (13), (17) OPEN 하여 각 CONNECTOR 의 OUTER SIDE 부분을 DRY CLOTH 로 CLEANING 하라. CAUTION : SENSING ELEMENT REMOVE 시 꼬이지 않도록 조심할것. • ELEC CONNECTOR (4), (7) 의 LOCKWIRE 를 제거하고 NUT LOOSE 하여 (4), (7) 을 분리하여 CAP 을 씌워라. • NUT (3), (9) 의 LOCKWIRE 를 제거하고 NUT (3), (9) 를 REMOVE 하라. • SCREW (2), (5), (8) 와 WASHER (1), (6), (10) 를 REMOVE 하라. • BRACKET (11) 을 REMOVE 하고 SENSING ELEMENT (15) 를 REMOVE 하라. • SENSING ELEMENT 로부터 4개의 BUSHING (14), (16) 을 REMOVE 하라. 4. OPEN 되었던 CB CLOSE, ACCESS PANEL CLOSE 후 항공기 원상하라. - 238 - - 239 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA38) ● MMEL 38-30-01 a) LAVATORY WASTE SYSTEM ○ 상기 MMEL 38-30-01 관련 정해진 AMM DEACTIVATION 절차는 없음. 상황에 따른 DEACTIVATION or ISOLATION 절차 수행. ○ DEACTIVATION OF THE TOILET ASSEMBLY (AMM 38-31-00-040-801) ※ AFM-CDL/MMEL DEACTIVATION TASK 와는 관련없음. - POTABLE-WATER SHUTOFF V/V CLOSE 후 해당 LAVATORY DOOR CLOSE LOCK 시킴. LAV DOOR POTABLE WATER SHUTOFF V/V ACCESS DOOR ACCESS PANEL - 240 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA49) ● MMEL 49-11-01 b) AIRBORNE AUXILIARY POWER POWER PLANT POWER PLANT (APU) ○ DEACTIVATION OF THE APU BY CIRCUIT BREAKER TAGGING (AMM 49-11-00-040-801) 1. AIR-INTAKE FLAP 이 CLOSE POSITION 에 있는지 확인하라. 2. 만약 OPEN 되어있다면 MANUAL CLOSE 절차수행 • AIR-INTAKE FLAP ACUTATOR (516KB) 의 MANUAL DRIVE SHAFT 를 INTAKE FLAP 이 FULLY CLOSE 될 때까지 TURN 하라. ※ MANUAL SHAFT 를 TURN 할때 TORQUE 35.39 lbin 를 초과하지말것. MECHANICAL STOP 에 도달시 정해진 TORQUE 를 초과시 ACTUATOR 에 DAMAGE 를 입힐수있음. ※ 약 47 바퀴 TURN 시 ACTUATOR 가 RETRACT POSITION 에서 EXTEND POSITION 으로 움직임. 313AL AIR-INTAKE FLAP ACTUATOR 516KB MANUAL DRIVE SHAFT 3. 'APU MASTER SW' PB OFF, 'APU START' PB OFF, 'APU BLEED PB' OFF 확인후 INOP TAG 부착. 4. CB OPEN - 241 - ○ DEACTIVATION OF THE APU BY APU SUBSTITUTION KIT (AMM 49-11-00-040-801-01) 1. APU 없는 상태에서 FLIGHT 시 WEIGHT IMPACT AND EFFECT ON BALANCE 지켜라. - A330-200 WEIGHT IMPACT : -617.54 LB, EFFECT ON BALANCE : -1498712 LBIN - A330-300 WEIGHT IMPACT : -617.54 LB, EFFECT ON BALANCE :-1628253 LBIN 2. DEACTIVATION OF APU • REMOVE THE APU (AMM TASK 49-11-11-000-801) • INSTALL THE APU SUBSTITUTION KIT (AMM TASK 49-11-11-400-802) • MAKE AN ENTRY IN THE TECHNICAL LOGBOOK THAT THE APU IS REMOVED. - 242 - ● MMEL 49-16-01 a) AIR INTAKE FLAP OPEN POSITION ○ DEACTIVATION OF THE AIR INTAKE FLAP (AMM 49-16-00-040-801) 1. CB OPEN - 742VU : C72, C71 - 5000VE : C01,A05, A04, A03, A02 2. ELEC CONNECTOR 5122VC-A 를 5122VC 로 부터 DISCONNECT 하여 CAP 을 씌우고 AIR INTAKE STRUCTURE 에 TIE-WRAP 으로 ATTACH 하라.. 3. AIR INTAKE FLAP 이 FULLY OPEN POSITION 이 아니면 MANUAL 로 OPEN 시켜라. • AIR-INTAKE FLAP ACUTATOR (516KB) 의 MANUAL DRIVE SHAFT 를 INTAKE FLAP 이 FULLY OPEN 될 때까지 TURN 하라. ※ MANUAL SHAFT 를 TURN 할때 TORQUE 35.39 lbin 를 초과하지말것. MECHANICAL STOP 에 도달시 정해진 TORQUE 를 초과시 ACTUATOR 에 DAMAGE 를 입힐수있음. ※ ACTUATOR 를 ONE FULL TRAVEL 로 움직이려면 MANUAL DRAIVE SHAFT 를 약 87 바퀴 TURN 해야한다. • AIR-INTAKE FLAP 이 CORRECT POSITION 인지 확인하라. : ARI-INTAK FLAP 이 UPPER WALL AIR CHANNEL 과 일치하여야함. TOLERANCE 'A' 는 1mm 이며 NO TOLERANCE 또한 허용된다. 4. ECB (59KD) 에 “FLAP OPEN" SIGNAL 을 주기위해서 AIR-INTAKE FLAP ACTUATOR (516KB) 를 DUMMY CONNECTOR 로 DUMMY 시킴. • CONNECT A JUMPER LEAD, MADE FROM WIRE CF24 GAUGE, BETWEEN THE PINS C AND D OF A CONNECTOR E0052R14B12PNF. • HOLD THE JUMPER LEAD IN POSITION ON THE CONNECTOR WITH A BACKSHELL ABS0638A14. - 243 - • PAINT THE DUMMY CONNECTOR WITH RED MATERIAL NO: 16018 (STRUCTURE PAINTS (MATERIAL NO.16-018)). 5. CONNECTOR (5122VC) 에 DUMMY CONNECTOR 연결하라. 313AL AIR-INTAKE FLAP ACTUATOR 516KB MANUAL DRIVE SHAFT DUMMY CONNECTOR 5122VC-A 5122VC 6. OPEN 되었던 CB 와 ACCESS PANEL CLOSE 후 항공기 원상하라. 7. CREW 가 인지할수있게 AIR-INTAKE FLAP DEACTIVE WARNING TAG 부착하라. 8. APU STARTING 하라. (APU OPERATION TEST AMM 49-00-00-710-801) - 244 - ● MMEL 49-30-02 APU ISOL VALVE ○ DEACTIVATION OF THE APU FUEL ISOLATION-VALVE (5204QA) (AMM 28-29-00-040-801) 1. CB OPEN : APU ISOL VLV 3QF (K75) 2. MLG DOOR OPEN 3. APU FUEL ISOLATION-VALVE ACTUATOR (5QF) 의 VISUAL INDICATOR 를 확인하여 V/V POSITION 을 CHECK 하라. 4. V/V 가 'SHUT' POSITION 일 경우 ELEC CONNECTOR (5QF-A) 를 분리하여 CAP 을 씌 우고 TIE-WRAP 으로 SAFETY 조치하라. 5. V/V 가 ‘OPEN' POSITION 일 경우 - ELECTRICAL POWER FAILURE 일경우 • ELEC CONNECTOR (5QF-A) 를 분리하여 ACTUATOR CONNECTOR PIN 'A' 에 28VDC 공급하고 PIN 'C' 는 GROUND 시켜 'SHUT' POSITION 으로 움직이게 하라. • CONNECTOR 에 CAP 을 씌우고 TIE-WRAP 으로 SAFETY 조치하라. - ACUTUATOR FAILURE 일경우 • APU FUEL ISOLATION-VALVE ACTUATOR 를 REMOVE 하라. • DRIVE SHAFT 를 돌려 VALVE 를 CLOSE POSITION 이 되게하라. • SHAFET 에 COVER LOCKING (B11990) (2) 을 V-CLAMP (1) 와 함께 장착하라. • 분리된 ELEC CONNECTOR 에 CAP 을 씌우고 TIE-WRAP 으로 SAFETY 조치하라. • REMOVE 된 ACTUATOR 는 안전하게 항공기에 보관하라. 6. MLG DOOR CLOSE하라. 5QF-A 5QF POSITION IND' 1 - 245 - 2 LOCKING COVER ● MMEL 49-30-03 APU LP VALVE ○ DEACTIVATION OF THE APU LP FUEL SHUTOFF-VALVE (5200QA) (AMM 49-16-00-040-801) 1. CB OPEN : APU LP VLV MOT2 2QF (P10),APU CTL & LP VLV MOT1 1QF (K76) 2. ACCESS DOOR 312AR 를 OPEN 하라. 3. APU LP FUEL VALVE ACTUATOR (4QF) 의 VISUAL INDICATOR 를 확인하여 VALVE POSITION 을 CHECK 하라. 4. V/V 가 'SHUT' POSITION 일 경우 ELEC CONNECTOR 4QF-A 와 4QF-B 를 분리하여 CAP 을 씌우고 TIE-WRAP 으로 SAFETY 조치하라. 5. V/V 가 ‘OPEN' POSITION 일 경우 - ELECTRICAL POWER FAILURE 일경우 • ELEC CONNECTOR 4QF-A 와 4QF-B 를 분리하여 ACTUATOR CONNECTOR PIN 'A' 에 28VDC 공급하고 PIN 'C' 는 GROUND 시켜 'SHUT' POSITION 으로 움직이게 하라. • CONNECTOR 에 CAP 을 씌우고 TIE-WRAP 으로 SAFETY 조치하라. - ACUTUATOR FAILURE 일경우 • ELEC CONNECTOR 4QF-A 와 4QF-B 를 분리하여 CAP 을 씌우고 TIE-WRAP 으로 SAFETY 조치하라. • APU LP FUEL VALVE ACTUATOR 를 REMOVE 하라. • DRIVE SHAFT 를 돌려 VALVE 를 CLOSE POSITION 이 되게하라. • SHAFET 에 COVER LOCKING (B11990) (2) 을 V-CLAMP (1) 와 함께 장착하라. • REMOVE 된 ACTUATOR 는 안전하게 항공기에 보관하라. 6. ACCESS DOOR 312AR 를 CLOSE 하라. 4QF 4QF-B 1 4QF-A LOCKING COVER 2 - 246 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA52) 1) INOP 된 DOOR를 제외한 다른모든 DOOR 는 정상작동 해야함. 2) INOP 된 DOOR 는 PAX LOADING 금지 3) INOP 되었다는 PLACARD 부착 4) EMER EXIT SIGN AND FLOOR LT 는 어두운 것으로 COVERING 하라. 5) 승객들이 INOP 되었다는 DOOR 를 인지해야한다. 6) INOP된 DOOR 전후로 SEATS 반을 ROW 전체를 BLOCK 시키고 눈에 잘띄는 TAPE 나 ROPE 로 BLOCK 시킬때 INTERIOR 와 뚜렷이 대비되어야함. PAX BOARDING 전 SEAT 는 BLOCK 시키고 PAX가 다니는 통로는 장애가 없어야 한다. SEAT BLOCK은 MEL 02-52-10-01 참조 (다음 PAGE) 7) 승객이 앉지않도록 한다. 8) 규정된 capacity 를 초과하지마라. 9) ONE FLIGHT 후에 REPAIR NOTE1 : 승무원은 BLOCKED AREA 내 DOOR 근처 위치 NOTE2 : W/B SHEET 는 재구성할것. NOTE3 : DOOR CYLINDER 가 INOP‘된 DOOR 는 DOOR INOP' 으로 간주 A330-200 TOTAL 256 SEATS A330-300 TOTAL 296 SEATS FOR DOOR L-1 OR R-1 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 1 TO 7 FOR DOOR L-1 OR R-1INOPERATIVE : BLOCK ALL SEATS FROM ROWS 1 TO 7 FOR DOOR L-2 OR R-2 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 8 TO 36 FOR DOOR L-2 OR R-2 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 8 TO 36 FOR DOOR L-3 OR R-3 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 37 TO 51 FOR DOOR L-3 OR R-3 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 37 TO 51 FOR DOOR L-4 OR R-4 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 52 TO 58 FOR DOOR L-4 OR R-4 INOPERATIVE : BLOCK ALL SEATS FROM ROWS 52 TO 60 참고 L1/L4 SLIDE RAFT : 65명 (RATED CAPACITY), L2 : 55명, L3 : 50 명 (77 A/C 제외) - 247 - - 248 - - 249 - ● MMEL 52-10-03 b) PASSENGER EXIT STOP FITTING ○ DEACTIVATION OF THE PASSENGER EXIT STOP FITTINGS (AMM 52-10-00-040-801) 1. 해당 DOOR 를 OPEN 하라. 2. 해당 DOOR 주변의 STOP FITTING 을 VISUAL INSPECTION 하라. NOTE : 각 DOOR 마다 1개의 STOP FITTING 은 DAMAGE 되도 괜찮음. (OTHER STOP FITTINGS 는 이상이 없어야함.) 3. L1, R1 DOOR 의 BEAM 1, 2, 7, 8 의 STOP FITTING 은 반드시 NORMAL 이어야한다. 4. 만약 BEAM 1, 2, 7, 8 의 STOP FITTING 이 ABNORMAL 이라면 STOP FITTING 을 교환 하라.(AMM 52-11-31-000(400)-801) 1,2,7,8 STOP FITTING 은 정상이 어야한다. 1,2,7,8 STOP FITTING 은 정상이어야한다. - 250 - ● MMEL 52-10-07 PASSENGER CREW DOOR SPRING ROD ASSEMBLY ○ DEACTIVATION OF THE SPRING ROD ASSEMBLY (AMM 52-10-00-040-802) 1. SPRING ROD ASSEMBLY 의 EYE END 와 GIMBAL END 부분의 BOLT 를 VISUAL INSPECTION 하라. 2. EYE END 부분의 BOLT 가 BROKEN 시 (SPRING ROD ASSY 전부 REMOVE 할것.) • NUT (NAS509-4) (6) 을 SPRING ROD ASSEMBLY (10) 에 INSTALL 하라. • COTTER PIN (9) 빼고 NUT (8), WASHER (7), BOLT (4), WASHER (5) 를 REMOVE 하라. • SPRING ROD ASSEMBLY 의 남아있는 PART 를 REMOVE 하라. 3. GIMBAL 끝 부분의 BOLT BROKEN 시 (SPRING ROD ASSY 전부 REMOVE 할것.) • NUT (NAS509-4) (6) 을 SPRING ROD ASSEMBLY (10) 에 INSTALL 하라. • COTTER PIN (3) 빼고 NUT (2) 와 WASHER (1) 을 REMOVE 하라. • SPRING ROD ASSEMBLY 의 남아있는 PART 를 REMOVE 하라. 4. 해당 DOOR 를 CLOSE 하라. - 251 - SPRING ROD REMOVE 전 SAFETY를 위해 꼭 INSTALL 할 것(NAS509-4) ● MMEL 52-30-02 CARGO DOOR ACTUATOR ○ DEACTIVATION OF THE INOPERATIVE CARO DOOR ACTUATOR (AMM 52-30-00-040-801) - 상기 AMM 절차에 따르면 CARGO DOOR 를 CRANE 으로 OPEN/CLOSE 해야함. - 또한 DOOR FULL OPEN 후 MAIN BASE 에만 있는 CARGO DOOR SUPPORT-STRUT 을 장착하게 되어있음. - 상기 AMM 절차 내용중에 필요시 (DOOR ACTUATOR INOP or DAMAGE) DOOR ACTUATOR 를 REMOVE 하게되어 있는데 CARGO DOOR 를 CRANE 으로 OPEN/CLOSE 해야하는 절차 생략하고 바로 ACTUATOR REMOVE 하는게 나을수있음. (AMM 52-36-18-000-801) - 252 - ● MMEL 52-30-04 CARGO DOOR LATCHING HOOK, SPOOL AND BOLTS ○ DEACTIVATION OF THE INOPERATIVE LATCHING UNIT/LATCH FITTING COMPONENTS (AMM 52-30-00-040-802) 1. FWD or AFT CARGO DOOR 가 잘 닫혀있는지 확인하라. 2. 해당 CARGO DOOR 의 LOCKING HANDLE 을 PULL (UNLOCKING) 하라. 3. 821AR, 821BR 또는 822AR, 822BR ACCESS PANEL을 REMOVE 하라. 4. ECCENTRIC BUSING 에 LATCHING HOOK 가 잘 ENGAGE 되있는지 확인하라. 5. LATCHING HANDLE 을 UNLOCK POSITION 으로 움직여 잘 작동하는지확인하라. (자중에의해 DOOR 가 떨어지니 주의할것.) 6. 아래절차에 의해서 DEACTIVE 하라. - 만약 FWD CARGO DOOR 를 LATCH 할수없을 경우 • LATCHING UNIT 의 DAMAGE 또는 INOP (AMM 52-31-21-000-804) • LATCH FITTING 의 COMPONT DAMAGE 또는 INOP (AMM 52-31-32-000-801) - 만약 AFT CARGO DOOR 를 LATCH 할수없을 경우 • LATCHING UNIT 의 DAMAGE 또는 INOP • LATCH FITTING 의 COMPONT DAMAGE 또는 INOP (AMM 52-32-32-000-801) LATCHING SHAFT SHAFT LEVER BELLCRANK LOCKING SHAFT BELLCRANK BOLT LINK HOOK BOLT LATCHING HOOK LATCH FITTING - 253 - 7. REMAINING LATCHING UNITS/LATCH FITTINGS 에 대한 GENERAL VISUAL INSP 을 수행하라. - FWD or AFT CARGO DOOR 의 REMAINING LATCHING UNIT • LATCHING HOOK 의 DAMAGE 상태 확인 • PIVOT BOLT 들이 잘 장착되어있는지 확인하고 손으로 움직일때 돌아가지 말아야한다. • BELLCRANK BOLTS 가 DAMAGE 없이 잘 장착 되어있는지 확인. - FWD or AFT CARGO DOOR 의 REMAINING LATCH FITTING COMPONENT • ECCENTRIC BUSING 의 DAMAGE 여부 확인 • ECCENTRIC BUSING 이 제자리에 있고 관련 NUT 들이 COTTER PIN 에 의해 잘 장착 되어 있어야한다. • FUSELAGE 의 LATCH FITTING 들이 DAMAGE 가 없어야한다. 8. OPERATIONAL TEST OF THE PARTLY DEACTIVATED DOOR MECHANISM • CARGO DOOR 를 닫고 LATCH 시켜라. • 각 LATCHING HOOK 가 LATCH FITTING 의 ECCENTRIC BUSHING 에 잘 ENGAGE 되어있는지 확인하라. • LOCKING HANDLE 이 UNLOCKED POSITION 에 있는지 확인하라. 9. ACCESS PANELS 821AR, 821BR or 822AR, 822BR 을 장착하라. 10. LOCKING HANDLE 을 DOWN 시켜 DOOR 를 LOCKING 시켜라. 11. INDICATOR FLAGS 가 ACCESS PANEL 에 CONTOUR 되는지 확인하라. - 254 - ● MMEL 52-30-05 CARGO DOOR HINGE ARM or HINGE BOLT ○ DEACTIVATION OF THE INOPERATIVE DOOR HINGE CONNECTION (AMM 52-30-00-040-803) 1. FWD or AFT CARGO DOOR 가 CORRECTLY CLOSE & LOCK 되어있는지 확인하라. 2. ACCESS PANEL REMOVE 하라. - FWD CARGO DOOR : 132AR 132BR 132CR 132DR 132ER 132FR 132GR 132HR 132JR 132KR 132LR - AFT CARGO DOOR : 152AR 152BR 152CR 152DR 152ER 152FR 152GR 152HR 152JR 152KR 152LR 3. HINGE BOLT 에서 NUT 와 WASHER REMOVE 하고 GREASE NIPPLE 또한 REMOVE 하라. 4. HINGE BOLT NIPPLE HOLE 에 EXTRACTION TOOL (98A52208001001) 을 장착하여 HINGE BOLT 를 REMOVE 하라.. 5. 다른 HINGE BOLT 들이 올바로 장착되어있는지 확인하라 (손으로 돌려서 돌아가지 말아야한다) 6. HINGE ARM 과 FITTING 에 DAMAGE 가없는지 GENERAL VISUAL INSP 하라. 7. ACCESS PANEL 장착하라. HINGE FITTING GREASE NIPPLE 98A52208001001 HINGE BOLT HINGE ARM - 255 - ● MMEL 52-50-02-I)-a) CDLS KEY PAD ○ DEACTIVATION OF CDLS (AMM 52-51-00-040-805) - CB OPEN : CKPT DOOR LATCH 1MQ (V39) ※ CDLS 의 어떠한 PART 의 INOP' CONDITION 은 아래사항 충족시 CB (V39) OPEN 만으로 허용된다. • DOOR 가 UNLOCKED POSITION 으로 DEACTIVATION 되어야하며 INTENDED FILIGHT 를 위한 REGULATION 에 위반되지 않아야한다. ○ DEACTIVATION OF KEYPAD (AMM 52-51-00-040-801) NOTE : 만약 DEACTIVATION 하는 동안 COCKPIT DOOR 가 CLOSE 되고 안에 사람이 없다면 항공기를 DE-ENERGIZE 하라. 그러면 CABIN에서 COCKPIT DOOR 를 열수있다. 1. CB OPEN : CKPT DOOR LATCH 1MQ (V39) 2. CONTROL UNIT (1) 의 전면을 잡고 CAPTIVE SCREW (2) 를 LOOSE 하라. 3. ELEC CONNECTOR (3) 를 잡을수있을때까지 CONTROL UNIT (1) 를 내려라. 4. ELEC CONNECTOR (3) 를 DISCONNECT 하고 CAP 을 씌워라. 5. 다시 CONTROL UNIT (1) 를 INSTALL 하라. 6. OPEN 되었던 CB (V39) 를 CLOSE 하라. 3 1 2 4 - 256 - ● MMEL 52-50-02-C)-b) COCKPIT DOOR TOGGLE SW LOCK FUNCTION ○ DEACTIVATION OF CDLS (AMM 52-51-00-040-805) ○ DEACTIVATION OF THE LOCK FUNCTION (AMM 52-51-00-040-803) - KEYPAD 를 DEACTIVE 하라. (AMM 52-51-00-040-801) ● MMEL 52-50-02-H) CDLS BUZZER ○ DEACTIVATION OF CDLS (AMM 52-51-00-040-805) ○ DEACTIVATION OF THE BUZZER (AMM 52-51-00-040-802) - KEYPAD 를 DEACTIVE 하라. (AMM 52-51-00-040-801) - 257 - ● MMEL 52-50-02-J) CDLS DOOR RELEASE STRIKE ○ DEACTIVATION OF CDLS (AMM 52-51-00-040-805) ○ DEACTIVATION OF THE ELECTIRCAL RELEASE STRIKES (AMM 52-51-00-040-812) 1. CB OPEN : CKPT DOOR LATCH 1MQ (V39) 2. LATCH MECHANISM 의 D-RING (DOOR 손잡이) 을 돌려 CKPT DOOR 를 OPEN 하라. 3. 결함있는 ELEC‘ RELEASE STRIKE 의 CATCH 를 움직여서 FREE 하게 움직이는지 확인하라. 4. 만약 관련 PLUNGER 가 BLOCKAGE 로 인해 이상이 있다면 결함있는 ELEC‘ RELEASE STRIKE 를 REMOVE 하라. (AMM 52-51-12-000-801) • COCKPIT DOOR 를 OPEN 하라. • RH DOOR POST (1) 로부터 SCREW (4) 와 GAP COVER (3) 을 REMOVE 하라. CAUTION : ELEC‘ WIRE 분리전 반드시 MARKING 할것. • DOOR POST (1) 에서 COVER PLATE (2) 를 REMOVE 하라. • 결함있는 ELEC' RELEASE STRIKE 의 ELEC‘ CONNECTOR (6) 으로부터 WIRE HARNESS 7450VB 의 ELEC' CONNECTOR (5) 를 분리하라. (AWM 52-51-02, ESPM 204825) NOTE: Keep the jiffi junction connectors at the A/C wire harness for isolation reasons. In this case the wire ends remain in a confined space and cannot cause a short circuit. 2 5 6 3 30MQ 1 8 31MQ 1 7 32MQ 4 - 258 - • 분리된 CONNECTOR 에 CAP 을 씌워라. • SCREW (8) 과 ELEC' RELEASE STRIKE (7) 를 RH DOOR POST 에서 REMOVE 하라. 5. 만약 CATCH 가 FREE 하게 움직인다면 관련 ELEC' RELEASE STRIKE 의 CABLE 을 분리하라. (AWM 52-51-02, ESPM 204825) NOTE: Keep the jiffi junction connectors at the A/C wire harness for isolation reasons. In this case the wire ends remain in a confined space and cannot cause a short circuit. 6. WIRE END 부분에 CAP 을 씌워 PLASTIC-BAG 에 넣어라. 그리고, WIRE HARNESS를 DOOR POST 에 TIE-WRAP 으로 묶어 SAFETY 조치하라. 7. 나머지 ELEC‘ RELEASE STRIKE 가 정상적으로 작동하는지 확인하라. (AMM 52-51-00-710-802) 8. OPEN 되었던 CB (V39) 를 CLOSE 하라. SPRING CATCH PLUNGER - 259 - ● MMEL 52-50-02-K) PRESSURE RATE SENSOR ON NORMAL CKPT DOOR CONT PANEL ○ DEACTIVATION OF CDLS (AMM 52-51-00-040-805) - CB OPEN : CKPT DOOR LATCH 1MQ (V39) ※ CDLS 의 어떠한 PART 의 INOP' CONDITION 은 아래사항 충족시 CB (V39) OPEN 만으로 허용된다. • DOOR 가 UNLOCKED POSITION 으로 DEACTIVATION 되어야하며 INTENDED FILIGHT 를 위한 REGULATION 에 위반되지 않아야한다. ○ CHECK OF THE PRESSURE RATE SENSOR (AMM 52-51-00-040-806) 1. CB V39 CLOSE 확인 2. CONROL UNIT (24MQ) 의 남아있는 PRESSURE SENSOR 의 작동여부를 CHECK 하라. 3. VACUUM-PUMP 사용하여 DE-COMPRESSION 상황을 SIMULATION 하라. NOTE : 만약 LED CHAN1 이 ON 되어있다면 RH PRESSURE SENSOR HOLE 을 확인. LED CHAN2 가 ON 되어있다면 LH PRESSURE SENSOR HOLE 을 확인. ACTION RESULT - ELEC' RELEASE STRIKE 의 SOLENOID 로부터 1) VACUUM PUMP 를 관련 CLACKING NOISE 를 들을수있다. PRESSURE SENSOR HOL - 정해진 NAGATIVE PRESSURE 에 도달시 ELEC' 에 대고 작동시켜라. RELEASE STRIKE 가 AUTO 로 작동한다. 4. VACUUM-PUMP 를 제거하라. ※ PRESSURE SENSOR HOLE 에 VACUUM-PUMP 대신 주사기를 사용하여 VACUUM-PRESSURE 를 걸어도 된다. - 260 - ※ 만약 PSCU 또는 PROXI' SNSR 결함으로 DOOR CAUTION 지시할시 ENG STARTING 시 PRESSURIZATION 이 되지않는다. MMEL 52-71-01-A), 52-71-01-B) 적용할것. ※ 정비회보 A330-52-001R3 A330 ECAM DOOR WARNING DISPLAY 시 조치사항 참고 ● MMEL 52-70-01 DOOR WARNING IND' ECAM DOOR/OXY PAGE ○ VERIFICATION TEST (DOOR) (AMM 52-70-00-040-802) ※ FLIGHT LOG 확인후 결함있는 DOOR 및 DOOR LOCK INDICATOR 를 육안으로 확인하여 DOOR MECHANISM 이나 INDICATOR 에 이상이 있다면, NO DISPATCH 임. 1. 관련 DOOR OPEN 하여 MECHANICAL DOOR LOCKING INDICATION 을 CHECK 하라. - PASSENGER CREW AND EMERGENCY DOOR • LOCKING INDICATION : 'UNLOCKED' (RED) • UPPER DOOR LOCKING HOOK 의 작동점검 • FRAME SIDE FITTING 의 VISUAL CHECK - 261 - - FWD or AFT CARGO DOOR • LOCKING HANDLE 만 들어올려 LOCKING INDICATION FLAG 를 볼수있어야함. • DOOR OPEN 후 DOOR LATCHING HOOK 와 ECCENTRIC BOLT 를 VISUAL INSP' (DOOR 를 조금만 열어서 CHECK 할것.) - 262 - - BULK CARGO DOOR • OUTER DOOR HANDLE OPEN 하여 FRAME SIDE FITTING 의 VISUAL POSITION CHECK 와 BARREL LOCK 의 작동점검을 수행하라. - 263 - - AVIONIC COMARTMENT ACCESS DOOR • STOP FITTING 의 VISUAL CHECK, HINGE ARM 과 HANDLE MECHANISM 의 작동점검 을 수행하라. INSPECTION AREA HINGE FITTING DOOR STOP 2. 관련 DOOR CLOSE 하여 MECHANICAL DOOR LOCKING INDICATION 을 CHECK 하라. - PASSENGER CREW AND EMERGENCY DOOR • LOCKING INDICATION : 'LOCKED' • LOCKING HOOK LINING 과 DOOR LINING 이 ALIGN 되는지 확인 - FWD or AFT CARGO DOOR • LOCKING HANDLE (PUSH DOWN) 을 LOCK 위치로 놓았을때 LOCKING INDICATION FLAG 가 SKIN 과 일치해야함. - BULK CARGO DOOR • OUTER DOOR HANDLE 을 CLOSE AND PUSH 하여 DOOR SKIN 과 일치해야함. - AVIONIC COMARTMENT ACCESS DOOR • DOOR CLOSE 시 DOOR SKIN 과 HANDLE 이 SKIN 과 일치해야함. ● MMEL 52-71-01-A) PSCU ○ VERIFICATION TEST (DOORS) (AMM 52-71-00-040-802) - MMEL 52-70-01 의 DEACTIVATION 절차 VERIFICATION TEST (DOORS) (AMM 52-7000-040-802) 와 동일함. 상기 절차 참조할것. - 264 - ※ 1개의 DOOR PROXIMITY SWITCH 의 INOP' 은 아래사항 충족시 CABIN PRESSURIZED 기능 제공된상태에서 3 일동안 유지할수있다. 1) 관련 DOOR LOCKING MECHANISM 의 작동점검이 수행되어야하며 2) 결함있는 PROXIMITY SWITCH 대신 DUMMY PROXIMITY SWITCH 와 PSCU 가 연결되어야 하고 3) 관련 DOOR 가 CLOSED AND LOCKED 되어있는지 VISUAL CHECK 해야한다. NOTE : 만약 해당 DOOR 가 RE-OPEN 되면 MAINTENANCE PROCEDURE 를 다시수행하여 DOOR CLOSED INDICATION 을 제공해야한다. ※ 정비회보 A330-52-001R3 A330 ECAM DOOR WARNING DISPLAY 시 조치사항 참고 ● MMEL 52-71-01-B)-a)b) DUMMY PROXIMITY SWITCH IS CONNECTED (EXCEPT NO.3 EMER' DOOR) ※ DOOR PROXIMITY SENSOR DEACTIVACTION 요약 1) PROX' SENSOR (ZZMJ) / PSCU (5MJ) DISPLAY 시 a) DOOR CLOSE 후 LOCK 상태 VISUAL 확인 b) 해당 DOOR OPEN c) 721VU N09(3MJ), 722VU P41(2MJ) 의 CB OPEN d) DUMMY PLUG 를 해당 SENSOR 와 SWAP e) DOOR CLOSE f) CB CLOSE 하고 60S 후에 ECAM DOOR CLOSE 확인 g) 해당 DOOR OPEN 한후 10초 이내에 CLOSE 하여 RE CHK 2) PROX' SENSOR(ZZMJ)/ PROX' SENSOR(YYMJ)/PSCU(5MJ) DISPLAY a) DOOR CLOSE 후 LOCK 상태 VISUAL 확인 b) 해당 DOOR OPEN c) 721VU N09(3MJ), 722VU P41(2MJ) 의CB OPEN d) COMPENSATION PNL 에서 해당 DOOR 의 BRIDGE PLUG (11MJ,12MJ) 를 REMOVE e) CB CLOSE 하고 60S 후에 ECAM DOOR PAGE 가 나타나는가 확인 f) CB OPEN g) DUMMY PLUG 를 SENSOR PLUG (ZZMJ) 에 연결 h) DOOR CLOSE i) CB CLOSE 후 60S 후에 ECAM PAGE 확인 j) 만약 DOOR 가 계속 OPEN 시 SENSOR PLUG (YYMJ) 에 연결하여 상기사항 수행 k) DOOR OPEN 후 10S 이내에 CLOSE 하여 CHK - 265 - 3) 10S 이상 DOOR 를 OPEN 했을때 a) CB 2MJ, 3MJ OPEN c) CB CLOSE 후 60S b) DUMMY PLUG 장탈하고 기존 PLUG 연결 d) 해당 DOOR OPEN e) 재수행 ○ 정비회보 A330-52-001R3 ▲ SYSTEM 설명 : GROUND 에서 ECAM DOOR PAGE 에 실제 DOOR 는 CLOSE 되었으나 OPEN 을 지시 할 때 PSCU (Proximity Sensor Control Unit) 는 DOOR OPEN SIGNAL을 NO.1 & NO.2 CPC (Cabin Pressure Controller) 및 ZONE CONTROLLER 에 전송하며 이 에 따라, - NO.1 & NO.2 CPC : FORWARD & AFT OUTFLOW VALVE 를 FULLY OPEN - ZONE CONTROLLER : DOOR OPEN SIGNAL 을 NO.1 & NO.2 PACK CONTROLLER 에 전송하며, BOTH PACK CONTROLLER 는 PACK FLOW CONTROL VALVE 1 & 2 를 CLOSE 시킴. 또한 DOOR WARNING 발생 시점에 따라 아래와 같이 구분됨. DOOR WARNING 이 ENG STOP 에서 FLIGHT PHASE 2 (1st ENG START TO 1st ENG TAKE OFF POWER SET ) 사이 발생 시 ; - PSCU 는 DOOR OPEN SIGNAL 을 CPC 및 PACK CONTROLLER 로 보내며, OUTFLOW VALVE 를 FULL OPEN, PACK FLOW CONTROL VALVE 를 FULL CLOSE 시킴. - 이때 CABIN PRESS 는 작동되지 않으며, T/O 후에도 CABIN PRESS CONTROL 되지 않음. - DISPATCH 전 반드시 DUMMY SENSOR 를 이용하여 DOOR WARNING 을 CLEAR 시켜야 함. TAKE OFF POWER SET 후 및 FLIGHT 중 DOOR WARNING 발생 시 : DOOR WARNING 은 CPC 및 PACK CONTROLLER 에 영향을 미치지 못하며, CABIN PRESS 는 정상 작동됨. - PSCU 는 TAKE OFF POWER SET 시의 DOOR STATUS 를 전송하며 CPC 및 ZONE CONTROLLER 내에서 FROZEN 됨. - DOOR WARNING 은 정상적으로 ECAM 에 DISPLAY 됨. ▲ DOOR PROXIMITY SENSOR DEACTIVATION PROCEDURES (AMM 52-71-00-040-801) (AMM 52-71-00-040-805) NOTE : ALL DOOR CLOSE 후 ECAM DOOR PAGE 에 DOOR OPEN (AMBER INDICATION) 을 지시하면, NO.3 MCDU SYSTEM REPORT/TEST PAGE 의 ATA 52 PSCU에서 "GRD SCAN" 을 수행하여 FAULT MESSAGE 를 확인하라. ▷ CMC FAULT MESSAGE " PROX SENSOR (zzMY)/PSCU(5MJ) DISPLAY 시 조치 사항 1. DOOR CLOSE 후 ECAM DOOR PAGE 에 OPEN 을 지시하면 DOOR CLOSE 상태에 서 MECHANICAL DOOR LOCKING INDICATION 을 아래와 같이 CHECK 하라. NOTE : DOOR WARNING 의 원인이 MECHANICAL LOCK 결함인지 또는 INDICATION 결함인지 확인하기 위함. - PASSENGER DOOR • DOOR LOCKING INDICATION 에 "LOCKED" 가 보이는지 CHECK • LOCKING HOOK 의 LINING 이 DOOR LINING 와 ALIGN 되고 한쪽이 DISENGAGE 되지 않았는지 CHECK. - 266 - - FWD or AFT CARGO COMPARTMENT DOOR • LOCKING INDICATION FLAG 가 SKIN 과 FLUSH 되었는지 CHECK (FLAG 의 RED COLOR 가 보이지 않음) • DOOR LOCKING HANDLE 이 SKIN 과 FLUSH 되었는지 CHECK - BULK CARGO COMPARTMENT • OUTER DOOR HANDLE 이 SKIN 과 FLUSH 되었는지 CHECK. 2. 해당 DOOR 를 아래 절차와 같이 OPEN 하고 MECHANICAL DOOR LOCKING INDICATION 을 CHECK 하라. - PAX DOOR • LOCKING INDICATION 이 "UNLOCKED" 로 보이는지 CHECK - FWD or AFT CARGO DOOR • 반드시 LOCKING HANDLE 만 OPEN (UNLOCK) 하라. NOTE : FWD 또는 AFT CARGO DOOR 를 FULL OPEN 시 다음 절차에서 PSCU C/B (2MJ, 3MJ) 들의 OPEN 으로 인해 YELLOW HYDRAULIC PUMP 가 - 267 - 작동되지 않아 CARGO DOOR 를 CLOSE 할 수 없음. • LOCKING INDICATION FLAG 가 보이는지 CHECK NOTE : LOCKING HANDLE OPEN (UNLOCK) 시 LOCKING INDICATION FLAG 가 OUTBD 로 돌출되며 SIDE 에 RED COLOR 가 보임. - BULK CARGO DOOR • OUTER DOOR HANDLE 을 OPEN 하라. 3. CB OPEN : DOORS & SLIDES CTL 3MJ (N09), DOORS& SLIDES CTL 2MJ (P41) 4. AVIONICS COMPARTMENT REAR RIGHT SIDE 에 있는 COMPENSATION PANEL (5062VE) 의 ACCESS COVER 를 OPEN 하고 아래 절차와 같이 PROXIMITY SENSOR DEACTIVATION 절차를 수행하라. • DUMMY SENSOR PLUG (5260VC-A) 를 FAULT 로 MEMORY 된 'zzMY' 로 표시된 SENSOR POSITION 에 연결하라. 5. 해당 DOOR 를 CLOSE 하라. • FWD 및 AFT CARGO DOOR 는 OPEN 한 LOCKING HANDLE 을 CLOSE 함. 6. C/B PANEL 721VU 및 722VU 의 C/B 2MJ (P41), 3MJ (N09) 를 CLOSE 하고 ECAM SD DOOR/OXY PAGE 에 해당 DOOR INDICATION 이 GREEN 을 지시하는지 확인하라. (약 60초 소요) 7. 해당 DOOR 에 대하여 FINAL OPERATIONAL CHECK 를 아래와 같이 수행하라. • 1명은 ECAM SD 의 DOOR/OXY PAGE 에서 해당 DOOR INDICATION 의 작동상태 확인하라. • 다른 1명은 해당 DOOR 에 대한 OPEN/CLOSE 를 반드시 10 초 이내 수행하라. 10 초가 초과되면 PSCU 내부에서 SENSOR DISAGREE 로 인해 DOOR WARNING LATCH 됨. - FWD 및 AFT CARGO DOOR 는 LOCKING HANDLE 만 OPEN/CLOSE 하여 수행. - BULK CARGO DOOR 는 OUTER LOCKING HANDLE 을 PUSH OUT 하여 UNLOCKED POSITION 으로 TURN 후 다시 LOCKED POSITION 으로 TURN 하 여 CHECK 하라. • 만약 FINAL CHECK 중 해당 DOOR 를 OPEN/CLOSE 하는데 10 초 이상 소요되었 다면 DOOR WARNING 이 LATCH 되므로 아래와 같이 조치할 것. ① C/B PANEL 721VU 및 722VU 에서 PSCU C/B 2MJ (P41) 및 3MJ (N09)를 OPEN 하라. ② ‘zzMJ’ SENSOR POSITION 에 연결한 DUMMY SENSOR PLUG (5260VC-A) 를 REMOVE 하고 ORIGINAL PLUG 를 ‘zzMJ’ SENSOR POSITION 에 연결하라. ③ C/B PANEL 721VU 및 722VU 의 C/B 2MJ 및 3 MJ 를 CLOSE 하고 ECAM SD DOOR/OXY PAGE 에 DOOR INDICATION 이 지시하는지 확인하라. (약 60 초 소요) ④ 해당 DOOR 를 OPEN 하라. ⑤ 상기 3 항에서 7 항을 다시 수행하라. 8. 해당 DOOR 의 MECHANICAL LOCK INDICATION 을 상기 1항과 같이 CHECK 하라. - 268 - ▷ CMC FAULT MESSAGE "PROX SENSOR (zzMY)/PROX SENSOR (yyMY)/PSCU(5MJ)" DISPLAY 시 조치 사항 1. DOOR CLOSE 후 ECAM DOOR PAGE 에 OPEN 을 지시하면 DOOR CLOSE 상태에 서 MECHANICAL DOOR LOCKING INDICATION 을 아래와 같이 CHECK 하라. NOTE : DOOR WARNING 의 원인이 MECHANICAL LOCK 결함인지 또는 INDICATION 결함인지 확인하기 위함. - PASSENGER DOOR • DOOR LOCKING INDICATION 에 "LOCKED" 가 보이는지 CHECK • LOCKING HOOK 의 LINING 이 DOOR LINING 와 ALIGN 되고 한쪽이 DISENGAGE 되지 않았는지 CHECK. - FWD or AFT CARGO COMPARTMENT DOOR • LOCKING INDICATION FLAG 가 SKIN 과 FLUSH 되었는지 CHECK (FLAG 의 RED COLOR 가 보이지 않음) • DOOR LOCKING HANDLE 이 SKIN 과 FLUSH 되었는지 CHECK - BULK CARGO COMPARTMENT • OUTER DOOR HANDLE 이 SKIN 과 FLUSH 되었는지 CHECK. 2. 해당 DOOR 를 아래 절차와 같이 OPEN 하고 MECHANICAL DOOR LOCKING INDICATION 을 CHECK 하라. - PAX DOOR • LOCKING INDICATION 이 "UNLOCKED" 로 보이는지 CHECK - FWD or AFT CARGO DOOR • 반드시 LOCKING HANDLE 만 OPEN (UNLOCK) 하라. NOTE : FWD 또는 AFT CARGO DOOR 를 FULL OPEN 시 다음 절차에서 PSCU C/B (2MJ, 3MJ) 들의 OPEN 으로 인해 YELLOW HYDRAULIC PUMP 가 작동되지 않아 CARGO DOOR 를 CLOSE 할 수 없음. - 269 - • LOCKING INDICATION FLAG 가 보이는지 CHECK NOTE : LOCKING HANDLE OPEN (UNLOCK) 시 LOCKING INDICATION FLAG 가 OUTBD 로 돌출되며 SIDE 에 RED COLOR 가 보임. - BULK CARGO DOOR • OUTER DOOR HANDLE 을 OPEN 하라. 3. CB OPEN : DOORS & SLIDES CTL 3MJ (N09), DOORS& SLIDES CTL 2MJ (P41) 4. AVIONICS COMPARTMENT REAR RIGHT SIDE 에 있는 COMPENSATION PANEL (5062VE) 의 ACCESS COVER를 OPEN 하고 아래 절차와 같이 PROXIMITY SENSOR DEACTIVATION 절차를 수행하라. • DOOR OPEN 을 지시하는 DOOR POSITION 의 2 개의 PROXIMITY SENSOR PLUGs 를 REMOVE 하라. • C/B PANEL 721VU 및 722VU 의 C/B 2MJ (P41) 및 3MJ (N09) C/B 들을 CLOSE 하고 ECAM SD DOOR/OXY PAGE 에 DOOR INDICATION 이 지시할 때 까지 기다 려라. (약 60 초 소요) NOTE : 2개의 SENSOR PLUG 를 REMOVE 하는 이유는 C/B OPEN 전 DISAGREE 상태에서 LATCH 되었으므로 2개의 SENSOR PLUG 를 REMOVE 하여 BOTH SENSOR 의 POSITION 을 일치시켜 PSCU FAULT LATCH를 RESET 하기 위해서 임. • C/B PANEL 721VU 및 722VU 의 2MJ 및 3MJ C/B 를 OPEN 하라. • DUMMY SENSOR PLUG (5260VC-A) 를 FAULT 로 MEMORY 된 "zzMY" 로 표시된 SENSOR POSITION 에 연결하고, 나머지 "yyMJ" SENSOR POSITION 에는 처음에 REMOVE 한 같은 PLUG 를 다시 연결하라. • 해당 DOOR 를 CLOSE 하라. • C/B PANEL 721VU 및 722VU 의 C/B 2MJ (P41) 및 3MJ (N09) C/B 들을 CLOSE 하고 ECAM SD DOOR/OXY PAGE 에 해당 DOOR INDICATION 이 GREEN 을 지 시하는지 확인하라. (약 60 초 소요) 5. 만약 해당 DOOR POSITION 이 OPEN 을 지시하면 해당 DOOR 의 다른 SENSOR (yyMJ) POSITION 에 DUMMY SENSOR PLUG (5260VC-A) 를 연결하기 위해 상기 3 항과 4 항을 수행하라. 6. 해당 DOOR 에 대하여 FINAL OPERATIONAL CHECK 를 아래와 같이 수행하라. • 1 명은 ECAM SD 의 DOOR/OXY PAGE 에서 해당 DOOR INDICATION 의 작동 상 태 확인하라. • 다른 1 명은 해당 DOOR 에 대한 OPEN/CLOSE 를 반드시 10 초 이내 수행하라. 10 초가 초과되면 PSCU 내부에서 SENSOR DISAGREE 로 인해 DOOR WARNING LATCH 됨. - FWD 및 AFT CARGO DOOR 는 LOCKING HANDLE 만 OPEN/CLOSE 하여 수행. - BULK CARGO DOOR 는 OUTER LOCKING HANDLE 을 PUSH OUT 하여 UNLOCKED POSITION 으로 TURN 후 다시 LOCKED POSITION 으로 TURN 하 여 CHECK 하라. - 만약 FINAL CHECK 중 해당 DOOR 를 OPEN/CLOSE 하는데 10 초 이상 소요되 었다면 DOOR WARNING 이 LATCH 되므로 아래와 같이 조치할 것. • 만약 FINAL CHECK 중 해당 DOOR 를 OPEN/CLOSE 하는데 10 초 이상 소요되었 다면 DOOR WARNING 이 LATCH 되므로 아래와 같이 조치할 것. - DUMMY SENSOR PLUG (5260VC-A) 를 REMOVE 후 상기 3 항에서 6 항 까 지 다시 수행하라. 7. 해당 DOOR 의 MECHANICAL LOCK INDICATION 을 상기 1 항과 같이 CHECK 하라. - 270 - ○ DEACTIVATION OF A PROXIMITY SENSOR OF THE PASSENGER/CREW DOORS NO.1, 2, 4, THE FWD AND AFT CARGO-COMPARTMENT DOOR AND THE BULK CARGOCOMPARTMENT DOOR (AMM 52-71-00-040-801) - 상기 정비회보 절차 수행요함. COMPENSATION PANEL 5062VE PROXI SENSOR AT THE MID & AFT PAX/CREW DOOR 29MJ 27MJ FWD/AFT AND BULK CARGO DOOR - 271 - ● MMEL 52-71-01-B)-b)b) CABIN EMERGENCY PASSENGER DOOR (NO.3 EMER' DOOR) ※ DOOR PROXIMITY SENSOR DEACTIVACTION 요약 1) PROX' SENSOR (ZZMJ) / PSCU (5MJ) DISPLAY 시 a) DOOR CLOSE 후 LOCK 상태 VISUAL 확인 b) 해당 DOOR OPEN c) 721VU N09(3MJ), 722VU P41(2MJ) 의 CB OPEN d) DUMMY PLUG 를 해당 SENSOR 와 SWAP e) DOOR CLOSE f) CB CLOSE 하고 60S 후에 ECAM DOOR CLOSE 확인 g) 해당 DOOR OPEN 한후 10초 이내에 CLOSE 하여 RE CHK 2) PROX' SENSOR(ZZMJ)/ PROX' SENSOR(YYMJ)/PSCU(5MJ) DISPLAY a) DOOR CLOSE 후 LOCK 상태 VISUAL 확인 b) 해당 DOOR OPEN c) 721VU N09(3MJ), 722VU P41(2MJ) 의CB OPEN d) COMPENSATION PNL 에서 해당 DOOR 의 BRIDGE PLUG (11MJ,12MJ) 를 REMOVE e) CB CLOSE 하고 60S 후에 ECAM DOOR PAGE 가 나타나는가 확인 f) CB OPEN g) DUMMY PLUG 를 SENSOR PLUG (ZZMJ) 에 연결 h) DOOR CLOSE i) CB CLOSE 후 60S 후에 ECAM PAGE 확인 j) 만약 DOOR 가 계속 OPEN 시 SENSOR PLUG (YYMJ) 에 연결하여 상기사항 수행 k) DOOR OPEN 후 10S 이내에 CLOSE 하여 CHK 3) 10S 이상 DOOR 를 OPEN 했을때 a) CB 2MJ, 3MJ OPEN b) DUMMY PLUG 장탈하고 기존 PLUG 연결 c) CB CLOSE 후 60S d) 해당 DOOR OPEN e) 재수행 ○ 정비회보 A330-52-001R3 참고 ○ DEACTIVATION OF A PROXIMITY SWITCH OF THE CABIN EMERGENCY PASSENGER DOOR NO.3 (AMM 52-71-00-040-805) - 상기 MMEL 52-71-01-B)-a)b) 수행절차 참고 - 272 - PROXI SENSOR AT THE EMER' EXIT DOOR PROXI SENSOR AT THE EMER' EXIT DOOR COMPENSATION PANEL 5062VE - 273 - ● MMEL 52-71-01-B)-d) AVIONICS DOOR ○ VERIFICATION TEST OF THE AVIONICS DOOR (AMM 52-71-00-040-807) 1. ECAM SD DOOR/OXY PAGE 를 확인하라. (AVIONICS DOOR PROXIMITY SENSOR : 7MJ) 2. AVIONICS DOOR 의 OUTER DOOR HANDLE 이 제대로 작동하는지 확인하라. 3. HINGE ARM CONNECTION, HINGE FITTING, DOOR STOP FITTING, DOOR STOP 및 DOOR MECHANISM 을 VISUAL INSP 하라. 4. AVIONICS DOOR 를 닫고 HANDLE 이 SKIN 에 FLUSH 되는지 확인하라. HINGE ARM INNER HANDLE ROLLER ROLLER - 274 - OUTER LOCKING HANDLE RAMP A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA56) ※ WINDSHIELD 의 OUTER PLY 가 CRACK 시 는 아래사항 충족하면 10 FLIGHT 동안 운용 할수있다. 1) 다른쪽 WINDSHIELD 에 DAMAGE 가 없어야하고, 2) 해당 WINDSHIELD 의 HEATING 은 DEACTIVE 되어야 하며, 3) FLIGHT CREW 의 VISIBILITY 에 영향이 없고, 4) ICING CONDITION 이 아니어야한다. NOTE : AMM 에 명시된 LIMIT 이내의 MINOR DAMAGE 는 CREW 의 VISIBILITY 에 영향이 없 다면 OPERATION 에 지장없음. ● MMEL 56-11-01 COCKPIT WINDOWS/FRONT WINDSHIELD ○ DEACTIVATION OF THE FRONT WINDSHIELD (AMM 56-10-00-040-801) 1. CB OPEN : R57, D03, D43, E49, X39, G64, H64, S69 2. WINDSHIELD 를 INSPECTION 하라. (AMM 56-11-11-200-801) NOTE : 상기 AMM 절차의 SOFT LINER DAMAGE 는 INNER SURFACE 의 SOFT LINER 가 있는 WINDSHIELD (SPS supplier) 에만 해당된다. 3. OPEN 되었던 CB CLOSE 하라. - 275 - 4. 만약 WINDSHIELD OUTER PLY 에 CRACK 이나 BURN SPOT 이 LIMIT 이상일 경우 - CB OPEN : ANTI ICE WSHLD L 1DG1 S69 (LH), ANTI ICE WSHLD R 1DG2 R57 (RH) ● MMEL 56-11-02 COCKPIT WINDOWS/FIXED LATERAL WINDOW ○ DEACTIVATION OF THE FIXED WINDOW (AMM 56-10-00-040-802) 1. CB OPEN : R57, D03, D43, E49, X39, G64, H64, S69 2. FIXED WINDOW 를 INSPECTION 하라. (AMM 56-11-12-200-801) 3. OPEN 되었던 CB CLOSE 하라. 4. 만약 FIXED WINDOW OUTER PLY 에 CRACK 이나 BURN SPOT 이 LIMIT 이상일 경우 - CB OPEN : ANTI ICE WINDOWS L 4DG1 (D03), ANTI ICE WINDOWS R 4DG2 (D43) - 276 - ● MMEL 56-12-01 COCKPIT WINDOWS/SLIDING WINDOW ○ DEACTIVATION OF THE SLIDING WINDOW (AMM 56-10-00-040-803) 1. CB OPEN : R57, D03, D43, E49, X39, G64, H64, S69 2. FIXED WINDOW 를 INSPECTION 하라. (AMM 56-12-11-200-801) 3. OPEN 되었던 CB CLOSE 하라. 4. 만약 SLIDING WINDOW OUTER PLY 에 CRACK 이나 BURN SPOT 이 LIMIT 이상일 경우 - CB OPEN : ANTI ICE WINDOWS L 4DG1 (D03), ANTI ICE WINDOWS R 4DG2 (D43) - 277 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA73) (O) : ENG MINOR FAULT 로서 제보된 짧은 기간내에 REPAIR 하는 조건을 가정한 ITEM ※ ENG DEGRADED MODE : EPR MODE 가 FAUL 되면 AUTO 로 N1 MODE 로 변환하는데 이때 N1 MODE 는 두가지로 분류할수있음. - FUEL SCHEDULEING 이 되는 N1 RATED MODE - FUEL SCHEDULEING 이 안되는 N1 UNRATED MODE : OVER BOOSTING 될 위험성이 있음. N1 DERATED MODE 의 의미는 N1 UNRATED MODE 임. - 278 - ● MMEL 73-25-02 EIVMU ○ DEACTIVATION OF THE EIVMU 1 or 2 (1KS1, 1KS2) (AMM 73-25-00-040-807) ※ CAUTION : CAB FAN PB 과 EXTRACT PB 은 반드시 PUSH IN ('OFF' LT OFF) 되어있 어야한다. COMPUTER 의 OVER HEATING 발생시 EIVMU CB OPEN 하면 GROUND HORN 이 울지지 않음. NOTE : EIVMU CB OPEN 하면 AOA, PITOT, SATIC PROBE 들이 HEATING 되게됨. 1. CB OPEN 2. 다음과 같은 COCKPIT EFFECT 가 나타난다. ATA 21-50 27-00 SYSTEM AIR CONDITIONING (ON GROUND) EFCS (ON GROUND) EFFECT ANY CABIN DOOR OPEN 시 EWD “PACK 1+2 FAULT INHIB BY DOOR" 나타남. DOOR CLOSE 시 사라짐. EFCS TEST 불가능. ENGINE STOP 시 DEACTIVE 된 EIVMU ENGINE 쪽의 ENG ANTI ICE PB 에 'FAULT' LT ON 됨. 관련 ENGINE START 시 ANTI-ICE 'FAULT' LT OFF 됨. PROBE ICE PROTECTION EIVMU CB OPEN 하면 AOA, PITOT, SATIC PROBE 들이 30-31 (ON GROUND) HEATING 되게됨. 30-21 ENGINES ANTI-ICE (ON GROUND) - 279 - ● MMEL 73-30-03-A) EWD ENG1(2) FUEL FILTER CLOG ○ REPLACEMENT OF THE FULE PUMP FILTER ELEMENT (AMM 73-30-00-040-804) 1. FILTER ELEMENT 를 교환하라. (AMM 73-11-12-000(400)-801) - CB OPEN - OPEN 되었던 CB CLOSE 하라. - WET MOTORING 을 수행하여 FUEL LEAK CHECK 하라. (AMM 71-00-00-720-817) - 280 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA74) ※ ECAM IGNITION INDICATION (ENG STARTING 시 SD ENG PAGE 에 나타남) 의 INOP 은 IGNITION SYSTEM 의 FAULT MSG 가 정상으로 나타나는지 확인하면 DISPATCH 가능하다. ● MMEL 74-31-02-A) INDICATION ON ECAM ENG PAGE SELECTD IGNITER ○ CHECK OF THE IGNITION SYSTEM (AMM 74-31-00-040-805) 1. 관련 CB CLOSE 확인 : G03, C68, Q70 (ENG1) / F50, D70, Q71 (ENG2) 2. IGNITION SYSTEM A TEST ACTION 1) FADEC GND PWR1(2) PB PUSH RESULT - 'ON' LT ON NOTE : 가끔 약 2초 정도 기다려야 함. 2) ENG1(2) MASTER LEVER 'ON' 3) CB OPEN : Q70 (ENG1), ON EWD Q71(ENG2) - 'ENG1(2) IGN A FAULT' MSG 나타남 4) CB CLOSE ON EWD - 'ENG1(2) IGN A FAULT' MSG 사라짐 5) ENG1(2) MASTER LEVER 'OFF' & FADEC GND PWR1(2) PB RELEASE 3. IGNITION SYSTEM B TEST ACTION 1) FADEC GND PWR1(2) PB PUSH RESULT - 'ON' LT ON NOTE : 가끔 약 2초 정도 기다려야 함. 2) ENG1(2) MASTER LEVER 'ON' 3) CB OPEN : G03 (ENG1), ON EWD F50 (ENG2) - 'ENG1(2) IGN B FAULT' MSG 나타남 4) CB CLOSE ON EWD - 'ENG1(2) IGN B FAULT' MSG 사라짐 5) ENG1(2) MASTER LEVER 'OFF' & FADEC GND PWR1(2) PB RELEASE 4. 항공기 원상하라. - 281 - ● MMEL 74-31-03-A) ECAM EWD IGN FAULT ○ CHECK OF THE IGNITION WARNING SYSTEM (AMM 74-31-00-040-805) WARNING : APU BLEED PB OFF 하여 ENG STARTER VALVE 입구에 AIR PRESSURE 가 차지 않게 하라. - IGNITION SYSTEM OPERATION TEST (AUDIBLE CHECK) 를 수행하라. • IGNITION OPERATION TEST 수행전 DRY MOTORING 수행하여 REMAIN FUEL 제거 (AMM 71-00-00-720-816) • FADEC GROUND POWER PB 'ON' • MCDU SYSTEM REPORT TEST → ENG:EEC1(2) CHAN A → SUBSYSTEM TEST → IGNITERS TEST → ENG MODE SELECTOR S/W 'NORM' → ENG MASTER LEVER 1(2) ON → MCDU START TEST PUSH → CONFIRM START OF TEST → ENABLE IGNITER1 → YES → CONTINUE TEST → ENABLE IGNITER2 → YES → TEST CLOSE UP - 282 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA75) ● MMEL 75-24-01 TCC HPTCC VALVE ○ DEACTIVATION OF THE TURBINE CASE COOLING (TCC) HPT AIR VALVE (5009ED) (AMM 75-24-00-040-801) 1. 해당 ENGINE 의 RH T/R COWL OPEN 2. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 3. ROD END (3) 의 NUT (1) 와 BOLT (4) REMOVE. 4. ROD END JAM NUT 의 WIRE 제거후 JAM NUT (2) LOOSE 하여 TCC HPT CONTROL CABLE 로부터 ROD END 를 REMOVE. 5. TCC HPT VALVE LEVER 를 CCW 방향으로 돌려 움직여라. NOTE : VALVE 는 SPRING LOADED CLOSE 이다. 6. ROD END (3) 을 TCC CONTROL CABLE 에 임시적으로 ATTACH 하라. - BOLT (4) 와 NUT (1) 를 ROD END (3) 에 끼워 SELF LOCKING 이 될 때까지 TIGHT 하라. - WIRE 를 이용하여 그림과 같이 TEMPORARY ATTACH 하라. 7. OPEN 되었던 CB CLOSE 후 항공기 원상하라. - 283 - ● MMEL 75-24-02 TCC LPTCC VALVE ○ DEACTIVATION OF THE TURBINE CASE COOLING (TCC) LPT AIR VALVE (5008ED). (AMM 75-24-00-040-802) 1. 해당 ENGINE 의 RH T/R COWL OPEN 2. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 3. ROD END 의 NUT (25) 와 BOLT (26) REMOVE. NOTE : LEVER BUSHING (27) 이 분실되지 않게 조심할것. 4. EXTENSION ROD 에서 ROD END 를 REMOVE 하라. 5. TCC LPT VALVE LEVER 를 CCW 방향으로 돌려 움직여라. NOTE : VALVE 는 SPRING LOADED CLOSE 이다. 6. ROD END (3) 을 TCC CONTROL CABLE 에 임시적으로 ATTACH 하라. - BOLT (4) 와 NUT (1) 를 ROD END (3) 에 끼워 SELF LOCKING 이 될 때까지 TIGHT 하라. - WIRE 를 이용하여 그림과 같이 TEMPORARY ATTACH 하라. 7. OPEN 되었던 CB CLOSE 후 항공기 원상하라. - 284 - - 285 - 1) VALVE 가 CLOSED DEACIVATED 되고, 2) VALVE DEACTIVE 후에 'ENG1(2) CTL VALVE FAULT - NAC COOL VALVE OPEN' MSG EWD 에 NOT DISPLAY 되어야하며 3) VALVE DEACTIVE 후 'ENG1(2) COOL VALVE FAULT' MSG 에 관한 ACTION 은 MEL 75-26-03 참고하여 조치하라. ● MMEL 75-26-02 NCC VALVE ○ DEACTIVATION OF THE NACELLE CORE COMPARTMENT COOLING SYSTEM (AMM 75-26-00-040-801) 1. 해당 ENGINE 의 RH T/R COWL OPEN 2. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 3. VALVE INDICATOR 를 확인하여 CLOSED POSITION 인지 CHECK 하라. 4. VALVE 가 NOT CLOSED 이면 WRENCH 를 사용하여 VALVE 를 CLOSED POSITION 으 로 움직여 VALVE 에 붙어있는 QUICK RELEASE PIN 으로 고정하라. 5. CB CLOSE 하고 항공기 원상하라. - 286 - CLOSED POSTION - 287 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA78) ● MMEL 78-30-01-A) THRUST REVERSER CONTROL ○ DEACTIVATION OF THE THRUST REVERSER FOR OPERATIONS (DCV INHIBIT AND ACTUATORS LOCKING ONLY) (AMM 78-30-00-040-807) 1. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 2. 해당 ENGINE 의 FAN COWL OPEN 3. T/R FWD 부분 2시 방향의 DCV 에 접근하라. 4. DCV MANUAL LEVER 를 잡고 QUICK RELEASE PIN 을 REMOVE 하라. (SPRING TENSION 에의해 DEACTIVE POSITION (SENSOR NEAR POSITION) 으로 가게된다.) 5. QUICK RELEASE PIN 을 DEACTIVATED POSTION 에 INSERT 하라. INIBITED POSITION QUICK RELEASE PIN DEACTIVATED QUICK RELEASE PIN FLIGHT POSITION ACTIVATED 6. LH/RH LOCKING ACTUATOR (4EA) 의 LOCK RELEASE LEVER 에 QUICK RELEASE PIN 을 INSERT 하라. - 288 - LOCKING ACTUATOR LOCK RELEASE LEVER IN LOCKED POSITION 7. LH/RH 중간에 있는 TLS 가 ACTIVATED 되어있는지 확인하라. NOTE : 이 PROCEDURE 에서는 TLS 는 반드시 ACTIVATED 되어있어야한다. TLS 의 DEACTIVATION 은 필요없음. 8. OPEN 되었던 CB CLOSE 하고 FAN COWL 을 CLOSE 하라. 9. COCKPIT 에서 ENG1(2) FADEC GND PWR PB 을 PUSH 하라. : 'ON' LT ON 됨 10. EWD 에 ‘ENG1(2) REV INHIBITED’ MSG DISPLAY 된다. - 289 - ● MMEL 78-30-01-B) THRUST REVERSER ACTUATION ○ DEACTIVATION OF THE THRUST REVERSER FOR OPERATIONS (SECURED TRANSLATING COWL CONFIGURATION) (AMM 78-30-00-040-808) NOTE : MEL 78-30-01-A) 그림 참조 1. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 2. 해당 ENGINE 의 FAN COWL OPEN 3. T/R FWD 부분 2시 방향의 DCV 에 접근하라. 4. DCV MANUAL LEVER 를 잡고 QUICK RELEASE PIN 을 REMOVE 하라. (SPRING TENSION 에의해 DEACTIVE POSITION (SENSOR NEAR POSITION) 으로 가게된다.) 5. QUICK RELEASE PIN 을 DEACTIVATED POSTION 에 INSERT 하라. 6. LH/RH LOCKING ACTUATOR (4EA) 의 LOCK RELEASE LEVER 에 QUICK RELEASE PIN 을 INSERT 하라. 7. LH/RH 중간에 있는 TLS 가 ACTIVATED 되어있는지 확인하라. NOTE : 이 PROCEDURE 에서는 TLS 는 반드시 ACTIVATED 되어있어야한다. TLS 의 DEACTIVATION 은 필요없음. 8. LH/RH T/R TORQUE BOX 에 붙어있는 "DO NOT OPERATE THE THRUST REVERSER" ORANGE COLOR SIGNAL PLATE 를 REMOVE 하라. 9. LH (7:30, 8:30, 9:30, 10:30), RH 1:30, 2:30, 3:30, 4:30 방향의 LOCK PLATE 에 SIGNAL PLATE 를 장착하라. - 290 - 10. OPEN 되었던 CB CLOSE 하고 FAN COWL 을 CLOSE 하라. 11. COCKPIT 에서 ENG1(2) FADEC GND PWR PB 을 PUSH 하라. : 'ON' LT ON 됨 12. EWD 에 ‘ENG1(2) REV INHIBITED’ MSG DISPLAY 된다. - 291 - ● MMEL 78-30-04-A) THRUST REVERSER TRANSCOWL TERTIARY LOCK (REVERSER 정상) ○ DEACTIVATION OF THE TRANSLATING COWL LOCKING SYSTEM (TLS MODULE) (4005EG1 TO 4005EG2). (AMM 78-37-00-040-801) 1. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 2. 해당 ENGINE 의 FAN COWL OPEN 3. 결함있는 ENGINE 의 LH or (and) RH 의 TLS 를 DEACTIVE 하라. - 3시 또는 9시방향의 TLS MODULE 을 발견하라. - TLS MODULE 에 달려있는 QUICK RELEASE PIN 을 REMOVE 하라. - TLS MODULE 의 LEVER 를 바깥으로 제낀다음 QUICK RELEASE PIN 을 DEACTIVATED POSITION 에 INSERT 하라. (TRANSCOWL 의 LOCK 을 풀어주는 절차임.) 4. OPEN 되었던 CB 와 FANCOWL 을 CLOSE 하라. 5. COCKPIT 에서 ENG1(2) FADEC GND PWR PB 을 PUSH 하라. : 'ON' LT ON 됨 6. EWD 에 ‘ENG1(2) REV MINOR FAULT’ MSG DISPLAY 되고, ‘ENG1(2) REV LOCKED’ MSG 는 더 이상 DISPLAY 되지 않는다. - 292 - ※ THRUST REVERSER ACTUATION 에 결함이있을 경우 MMEL 78-30-01-B) 의 (M) 절차 수행 할것. - DEACTIVATION OF THE THRUST REVERSER FOR OPERATIONS (SECURED TRANSLATING COWL CONFIGURATION) (AMM 78-30-00-040-808) ※ 비행전 아래사항 충족시 MEL 적용하여 FLIGHT 가능 1) FAULT 에 대한 T/S 수행하여 FALSE 로 판명되어야함. 2) 관련 T/R SYSTEM 의 ISOLATION VALVE 의 CHECK 하여 OPERATION 되어야함. 3) FALSE 'ENG1(2) REV PRESSURIZED' MSG 를 동반한 'ENG1(2) REV MINOR FAULT' MSG 가 DISPLAY 되지 않아야함. ● MMEL 78-30-07-A) EWD ENG 1(2) REV PRESSURIZED (FALSE) ○ FUNCTIONAL TEST OF THE THRUST REVERSER ISOLATION VALVE (AMM 78-37-00-040-801) (ON A/C EFF : 001~004, 051~099, 101~199) NOTE : ISOLATION VALVE PRESSURE SWITCH 의 ABNORMAL 로 인해 EWD 'ENG1(2) REV PRESSURIZED' MSG 가 DISPLAY 될 수있다. 1. COCKPIT OVERHEAD PALNEL 'PRIM1,2' PB 'OFF' 2. 관련 CB CLOSE 확인 - ENG 1 : EIVMU1 14KS1 (P05), TR INHIB B ENG1 8KS1 (R16), FADEC B ENG1 13KS1 (D44), TR INHIB A ENG1 7KS1 (U35), FADEC A ENG1 12KS1 (Q73) - ENG 2 : EIVMU2 14KS2 (P06), TR INHIB B ENG2 7KS2 (R15), FADEC B ENG2 13KS2 (K49), TR INHIB B ENG2 7KS1 (U34), FADEC A ENG2 12KS2 (Q74) 3. BLUE HYD ELEC PUMP 'ON' (ENG1) or YELLOW HYD ELEC PUMP 'ON' (ENG2) 하라. NOTE : SD HYD PAGE 를 통하여 HYD PRESSURE 가 1500 PSI 이상 나오는지 확인하 - 293 - 라. 그렇지 않으면 TEST FAIL 될것임. 4. ENG MASTER LEVER 'OFF', ENG START SELECTOR SWITCH 'NORM', THRUST LEVER 'IDLE' POSITION 확인하라. 5. ENG1(2) FADEC GND PWR PB 을 PUSH 하라. : 'ON' LT ON 됨 WARNING : ENG T/R 근처에 사람이나 장비가 없는지 확인하라. T/R 작동중 DAMAGE 나 인명피해를 입을수있음. NOTE : NORMAL DEPLOY AND STOW 동안 T/R ISOLATION VALVE 는 EEC 로부터 POWERED 되어 PRESSURIZE 된다. T/R DEPLOY 시 DCV 는 ENERZIED 되며 STOW 시 DE-ENERZIED 된다. 이 TEST 는 T/R ISOLATION VALVE SOLENOID 가 EEC 에 의해 POWERED 되지 않고 DCV 만 POWERED 됨. 만약 T/R ISOLATION VALVE 가 FAILED IN PRESSURIZED POSITION 이면 T/R 은 DEPLOY 될것이고, NON-PRESSURIZED 이면 DEPLOY 되지 않을것이다. NOTE : 만약 T/R SYSTEM 이 FAILED PRSSSURIZED 되어있다면 TEST 동안 NACELL SUFACE 가 움직일것이고, FAILED PRESSURIZED 되어있지않다면 T/R 은 STOW POSITION 에서 변화없을것이다. 6. MCDU SYSTEM REPORT/TEST 접근하여 아래와 같이 ISOLATION VALVE 를 TEST 하라. - 294 - NOTE : 만약 THROTTLE LEVER 를 IDLE POSITION 으로 50초 이내에 움직이지 않으면 TRA 관련 FAULT SET 되며 TEST 는 이뤄지지 않을것이다. MCDU 에 TRA 관련 MSG DISPLAY 되면 TEST 를 다시하라. NOTE : THROTTLE LEVER 를 MAX REVERSE POSTION 에 놓으면 EEC 는 DCV SOLENOID 를 자화시키고, T/R ISOLATION VALVE 는 계속 비자화 상태이다. - 295 - IV SYSTEM IS NOT FAILED PRESSURIZED IV SYSTEM IS FAILED PRESSURIZED IV SYSTEM 은 정상 이나 PRESSURE SW 에 의한 IND‘ 결함임 T/R 이 DEPLOYED 되어있는상태이며 TIME LIMIT (50초) 를 지나서 RE-STOW 할수없는상황 (MANUAL STOW로 해야 함.). IV SYSTEM WAS FAILED PRESSURIZED ON A/C 001~004, 051~099, 101~199 NOTE : TEST OK 시 DISPATCH 전 에 다시 작동할필요없음. 그 외 MSG 발생시는 상기 - 296 - TEST를 매 DISPATCH 전에 수행하여 IV SYSTEM 이 NOT PRESSURIZED 되었다는 것을 확인해야한다. NOTE : IV SYSTEM 이 FAILED PRESSURIZED 되었다면 T/R 은 DEPLOY 된것임. T/R 이 10% 이상 DEPLOY 되거나, LOCKING ACTUATOR 의 LOCK RELEASE LEVER 가 UNLOCK 되어있을 경우 FAILURE 발생. (확인해볼것.) 만약 IV SYSTEM 이 NOT FAILED PRESSURIZED 라면 T/R 은 REMAIN STOW 상태 일것임. NOTE : EEC CHAN A,B 모두 TEST 수행할것. 6. MCDU TEST MENU 를 빠져나오고, B or Y ELEC HYD PUMP OFF 하라. 7. FADEC GND PWR PB 'OFF', PRIM 1,2 PB PUSH IN 하라. 8. 항공기 원상하라. - 297 - A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA79) ● MMEL 79-31-01-A) ECAM ENG PAGE OIL QUANTITY ○ CHECK OF THE OIL QUANTITY AND INDICATING - SYSTEM (AMM 79-31-00-040-803) - ENG LH OIL TANK ACCESS DOOR OPEN 하여 ENG SHUT DOWN 5분 이후 2시간 이내 에 OIL LEVEL 확인할것. ● MMEL 79-35-02-A) EWD ENG1(2) OIL FILTER CLOG ○ INSPECTION OF THE OIL FILTER ELEMENT (5010EN) (AMM 79-35-00-040-803) 1. ENG SHUT DOWN 5분 이후에 작업할것. 2. CB OPEN : D44, Q73 (ENG1), K49, Q74 (ENG2) 3. 해당 ENG 의 LH THRUST REVERSER COWL OPEN 4. MAIN OIL FILTER ELEMENT 를 REMOVE 하라. (AMM 79-21-22-000-801) 5. FILTER ELEMENT 를 INSPECTION 하라 - FILTER ELEMENT 가 CONTAMINATION 되었다면 관련 OIL SYSTEM 을 INSPECTION 하라. (AMM 79-00-00-200-808) - MAGNETIC CHIP DETECTOR 를 INSPECTION 하라. (AMM 79-22-11-200-801) 6. FILTER ELEMENT 를 INSTALL 하라. 7. OPEN 되었던 CB 와 ENG T/R COWL CLOSE 하여 항공기 원상하라. - 298 - PN : 815316 PN : AS3209-239 PN : ST1946-906 TQ : 110~120 lbin - 299 - PN : 776703 TQ : 180~200 inlb A330 REFERENCE HAND BOOK DEACTIVE PROCEDURE(ATA80) ● MMEL 80-11-01 START VALVE ○ STARTER AIR VALVE MANUAL OVERRRIDE (AMM 80-11-00-040-803) WARNING : ENG STARTING 된후에 HAZARD AREA 로부터 신속히 벗어나도록 하라. 특히 ENG 우측편의 INTAKE COWL 에서 SERVICE INTERPHONE 제거시 주의할것. 특히 INTAKE COWL 앞쪽으로 절대로 근접하지 말것. 1. INTAKE COWL RH JACK 에 SERVICE INTERPHONE 을 연결하여 CREW 와 COMMUNICATION 할수있게 하라. 2. ENG START 전에 STARTER AIR VALVE 의 POSITION 을 확인하라. - THRUST REVERSER COWL RH 5시방향에 STARTER AIR VALVE OVERRIDE ACCESS HOLE 이 있음. - 3/8“ SIZE DRIVE WRENCH 연결 (24" 이상) 하여 ACCESS HOLE 에 INSERT 하라. (COCKPIT 에 SPECIAL TOOL 보관하고있음) - CCW 방향으로 TURN : START AIR VALVE CLOSE (HOLE 근처의 PLACARD 참조) 3. ENG SAFETY PRECAUTION 사항을 지켜라 (AMM 71-00-00-860-823) 4. CREW 에게 연락해서 ENG NORMAL AUTO STARTING or MANUAL STARTING 수행. 5. CREW 의 지시에 따라서 START VALVE 를 MANUAL OPEN 하라. (CW TURN : OPEN) 6. CREW 의 지시에 따라서 START VALVE 를 MANUAL CLOSE 하라. (INTERNAL STOP 이 걸릴 때까지 CCW TURN : CLOSE) 7. SPEED HANDLE 을 제거하고 CREW 에게 VALVE CLOSE INFORM 을 준다음 신속히 ENG 에서 벗어나라. OPEN CLOSE MANUAL OVERRIDE ACCESS HOLE - 300 - SERCIVE INTER-PHONE JACK ○ STARTER AIR VALVE POSITION CHECK (AMM 80-11-00-040-804) WARNING : ENG STARTING 된후에 HAZARD AREA 로부터 신속히 벗어나도록 하라. 특히 ENG 우측편의 INTAKE COWL 에서 SERVICE INTERPHONE 제거시 주의할것. 특히 INTAKE COWL 앞쪽으로 절대로 근접하지 말것. 1. ENG START 후 STARTER AIR VALVE 의 POSITION 을 확인하라. - THRUST REVERSER COWL RH 5시방향에 STARTER AIR VALVE OVERRIDE ACCESS HOLE 이 있음. - 3/8“ SIZE DRIVE WRENCH 연결 (24" 이상) 하여 ACCESS HOLE 에 INSERT 하라. (COCKPIT 에 SPECIAL TOOL 보관하고있음) - CCW 방향으로 TURN : START AIR VALVE CLOSE (HOLE 근처의 PLACARD 참조) 8.2M TO 53.3M AT 54.4 KPH FWD THRUST AT IDLE POWER AIR INTAKE AND EXHAUST AREAS 30° 1.7M - 301 -

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