N952CA
Registered owner: AC SPE 3 LLC, FL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
2EA CRACK INDICATON FOUND AT BS2598 BULKHEAD R/H S-11R LONGERON P/N 65B02522-4 PER BOEING SR MUA-MUA-26-0026-22B REPAIR CARRIED OUT PER BOEING 8100-9 DATED MAY 12-2026 AND PER BCS 202603210023-0016
1EA CRACK FOUND AT BS2598 BULKHEAD RHS OUTER CHORD HOLE C PER BOEING SR MUA-MUA-26-0022-07B REPAIR CARRIED OUT PER BOEING 8100-9 DATEED MAY, 12,2026.REFF BOEING BCS 202603210023-0016
FCD 744-53-0025 OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS WHILE PERFORMING STA R/H 1160 AND STRINGER 10R REPAIR CARRIED OUT PER 8100-9 DATED 04/28/2026 REF BOEING COMMUNICATION SYSTEM MESSAGE NUMBERS FOR CASE # 06320986
ONE CRACK FOUND AT FRAME SUPPORT OF 747 SSID REV. H ITEMS FÂ49G ON THE RHS AREA OF THE HINGE FITTING. PER BOEING SR MUAÂMUAÂ26Â0026Â03B. REPAIR CARRIED OUT PER BOEING 8100Â9 DATED MAY 13 2026 AND REF BCS 202603130057Â009
FCD 744-53-0025 OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS WHILE PERFORMING STA L/H 1160 AND STRINGER 10L REPAIR CARRIED OUT PER BOEING 8100-9 DATED MAY 12, 2026 REF BCS 0632095
OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS AT 1120 R/H TENSION TIE. REPAIR CARRIED OUT PER 8100=9 DATED 05/08/2026 REFF BOEING COMMUNICATION CASE 063200880
LOCK FASTENER HEAD BROKEN AT TENSION TIE ATTACH FRAME LOCATED AT BS 1220 RT AND STRINGER 10R
FINDING 002002 DOCUMENT FCD 744-53-0057-DURING C-CHECK 0.7" CRACK HAS EXTENDED FROM THE STOP HOLE OF THE PREVIOUS CRACK AT R/H STABILIZER UPPER LOBE DOUBLER. REPAIR WAS COMPLTED PER FAA 8100-9 DATED 0/21/2006 ON BOEING SERVICE REQUEST 202603060065-0011.
0.7" CRACK HAS EXTENDED FROM THE STOP HOLE OF THE PREVIOUS CRACK AT R/H STABILIZER UPPER LOBE DOUBLER. REPAIR COMPLETED PER :CASTLE ID: 202603060065: BOEING 8100-9 ISSUED DATED 04/21/2026. REF ID 202603060065-0011
AFT CARGO INTERCOSTAL CRACK AT STA 1940 TO STA 1960, LBL77 PERFORMED REPAIR IAW SRM 51-70-13 R1
CRACK FOUND ON FORWARD FUSELAGE WEB OF THE NOSE GEAR WELL AT STRINGER 26, BS 160-180 CORRECTIVE ACTION: CAT B. REPAIR PER SRM. REINSPECT DUE AT 33,018 CYCLES
OPEN-HOLE NDI INSPECTION FOUND DEFECT SIGNALS WHILE PERFORMING BS 1180LT - 1140 RT.
CRACK FOUND ON FORWARD FUSELAGE WEB OF NOSE GEAR WELL AT STRINGER S-26 STA 140-160 WL 205 R&R WEB PART NUMBER 65B01870U243 IAW SRM 51-40-02
OPEN-HOLE NDI INSPECTION FOUND DEFECT SIGNALS WHILE PERFORMING STA 1180 L/H STA 1140 R/H. REPAIR COMPLETED PER BCS MESSAGE NUMBER 06316150 INSPECTION THRESHOLD 21,108 TOTAL FLIGHT CYCLES
WHILE IN C CHECK - PERFORMED SURFACE HFEC INSPECTION OF FCD 744-53-0017 R2 A 1 INCH CRACK WAS FOUND ON CHORD BETWEEN S-37R AND S-38R. REPAIR PERFORMED PER BOEING BCS MUA N952CA / 25238 FRAME CRACK BS 1140 RH, RBL 80 / WL 330.
LH EMERGENCY SLIDE RESERVOIR PRESSURE IS BELOW GREEN BAND.
ON DESCENT ELECTRICAL BURNING SMELL. STATUS: EE CLNG EXH FAN. PERFORMED EE CLNG EXT FAN GROUND TEST PER AMM 21-58-00, TEST OF. INSPECTED ELECTRONIC EQUIPMENT COMPARTMENT FOR SUSPECTED BURNING AND CHECKED FOR ALL CBS, ALL OK. NO VISIBLE BURNS OR BURNING SMELL NOTICED UPON INSPECT. AIRCRAFT OK FOR SERVICE.
FUEL PANEL WAS INCORRECTLY SET AND CAUSED FUEL TO OVERBOARD THROUGH THE FUEL TANK VENT R/H. PANEL TESTED AND NO DEFECTS NOTED.
DURING A-CHECK INSPECTION AT LEVEL 5 AEROSPACE KCNW, IT WAS FOUND THAT EMERGENCY POWER RESERVOIR P/N: 1270156-4 S/N: ALT183-3683 HAS LOW PRESSURE. EMERGENCY POWER RESERVOIR P/N: 1270156-4 S/N: ALT183-3683 WAS REMOVED AND REPLACED ON NR 0072 UNDER LEVEL 5 AEROSPACE WORK ORDER NO. SV0002.
DURING A-CHECK AT LEVEL 5 KCNW, IT WAS DISCOVERED THAT A WIRE BUNDLE WAS CHAFFING WITH POST P/N: 65B14087-3 LOCATED AT FRAME STA. 460, LBL 87. THE DAMAGE WAS MEASURED AS 4MM X 5MM, WHICH IS OUT OF LIMITS. PERMANENT REPAIR ACCOMPLISHED IN ACCORDANCE WITH FVCI E.O. NO. 24224-3 REV. IR DATED 01/07/2025, APPROVED ON FAA 8110-3 DATED 01/13/2025 BY ROBERT MANASHI DER-T 876272412, AND DOCUMENTED ON LEVEL 5 WORK ORDER NO. SV0002, NR NO. 0076.
DURING C CHECK IN GMF, FOUND CRACK ON SKIN AT LH WLG W/W CANTED PRESSURE DECK STA 1241LBL 11.33 CATEGORY B REPAIR WAS ACCOMPLISED IN ACCORDANCE WITH BOEING MESSAGE BOE MUA-MUA 24-0122
DURING C CHECK IN GMF FOUND CRACK ON SKIN AT LH WLG CANTED PRESSURE DECT STA 1241 LBL 11.33. CATEGORY B REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH BOEING MESSAGE NUMBER- BOE-MUA-24-0122
FOUND RIVET HOLES ELOGATED ON SKIN RH SIDE AFTER MEASURMENT RIVET HOLES DIAMETER IS BETWEEN .280 TO .320 INCH
FOUND RIVET HOLES ELOGATED ON SKIN 2700 LH SIDE AFTER MEASURMENT RIVET HOLES DIAMETER BETWEEN .280 INCH UP TO .320 INCH
DURING MAINTENANCE C CHECK AT GMF FOUND LOWER FUSALAGE STA 1000 CENTER TO RH SIDE SUPPORT FRAME FOR BODY FAIRING CORRISON . REAPIR ACCOMPLISHED IN ACCORDANCE WITH SRM 51-70-12 (REV59/20FEB2024) AND WAS A CAT A REPAIR.
WHILE PERFORMING C CHECK RH WING O/B AILERON UPPERSURFACE L/E FAIRING CRACK POS O/B SIDE REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-60-01 REPAIR 1 (REV59 20FEB2024)
WHILE PERFORMING C CHECK RH WING O/B AILERON UPPER SURFACE LE FAIRING CRACK POS CENTER REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-60-01 REPAIR 1 (REV 59 20FEB2024.
WHILE PERFORMING C CHECK RH WING O/B AILRERON UPPER SURFACE BRAKET LE FAIRING CRACK POS I/B SIDE. REPAIR WAS ACCOMPLISED IN ACCORDANCE WITH SRM 57-60-01 REPAIR 1 (REV 59/20FEB2024)
WHILE PERFORMING C CHECK IN GMF FOUND CORRISION OUT OF LIMTS ON STA 1000 LBL 11.33-37.50 SUPPORT FRAME FOR BODY FAIRING THIS REPAIR IS CATIGORY A REPAIR WAS ACCOMPLISHE IN ACCORDANCE WITH THE SRM 51-70-12 (REV 59,20 FEB/2024
WHILE PERFORMING C CHECK RH WING O/B AILERON UPPER SURFACCE BRACKET FE FAIRING CRACK POS I/B SIDE. REPAIR WAS ACCOMPLISED IN ACCORDANCE WITH SRM 57-60-01 REPAIR 1 (REV 59 20FEB2024)
WHILE PERFOMING C CHECK IN GMF RH WING O/B AILERON BRACKET BALLAST CORROSION POS #1 FROM O/B. REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-56-02 REPAIR 1 (REV 59 20FEB2024)
WHILE PERFOMING C CHECK IN GMF FOUND CORROSION ON LH WING L/E CHORD OLES 1530. THIS REPAIR IS CATEGORY A. REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-41-13 REPAIR 1 & 51-70-11 (REV 59 20FEB 2024)
WHILE PERFORMING C CHECK IN GMF FOUND CHAFING ON FWD CARGO COMPARTMENT SEAT TRACK AT STA 570 RBL 45.5 THIS REPAIR IS CATEGORY A REPAIR WAS ACCOMPLICHED IN ACCORDANCE WITH SRM 53-00-52 REPAIR 10 (RREV 59 20FEB2024)
DURING CHECK AT GMF FOUND TEMPERARY REPAIR AT LH WING LEADING EDGE WS 1000 THAT NEEDS REPLACED TO PERMANET REPAIR CATEGORY A REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-41-01 REPAIR 6 (REV 59/20 FEB 2023
WHILE PERFORMING C CHECK IN GMF RH WING AILERON LOWER SURFACE PUNCTURE REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 57-60-01 REPAIR 1 (REV 59/20FEB 2024
DURING C CHECK IN GMF FOUND CRACK AT MED#1 RH UPPER SILL WEB CRACK AT STA 480 STR 16R CATEGORY B REPAIR WAS ACCOMPISHED IN ACCORDANCE WITH SRM 53-10-15 REPAIR 1 (REV 59/20 FEB 2024
WHILE PERFORMING C CHECK IN GMF FOUND CRACK AT MED#5 CUTOUT DOOR REVEAL AT STA 2240 STR 21 NEAR DOOR LOCK RELEASE THIS REPAIR IS ACCOMPLISHED ANS CATOGORIZED AS CAT A REPAIR IN ACCORDANCE WITH SRM 53-60-15 REPAIR 7 (REV 59/20 FEB 2024
WHILE PERFOMING C CHEHCK IN GMF, FOUNF CRACK ON SKIN AT RH W/G W/W CANTED PRESSURE DECK SURFACE SKIN AT STA 1241 RBL 5.5 CATEGORY B REPAIR WAS ACCOMPLISHED IN ACCORDANCE WITH SRM 53-40-51 REPAIR 6 (REV 59, 20 FEB /2024
RT SIDE FUSELAGE INNER WINDOW BELT CORROSION AT STA 1000 STR 15-STR 23
UPPER DECK RIGHT EMERGENCY DOOR BATTER TEST FAIL - REMOVED AND REPLACED BATTERY PACK IN ACCORDANCE WITH MAINTENANCE MANUAL. OPS CHECK OK.
AIRCRAFT SUSTAINED DAMAGE TO #4 ENGINE NOSE COWL DURING GROUND HANDLING. ACCOMPLISHED TEMPORARY REPAIR TO NOSE COWL PER FVCI EO 24009-1. THIS IS A TEMPORARY REPAIR AND WILL REQUIRED PERMANENT REPAIR OR COWL REPLACEMENT.
DURING OFF-LOADING OF CARGO, CARGO LOADING VEHICLE STRUCK THE SEAL DEPRESSOR AT THE FORWARD LOWER CORNER OF THE DOOR CUT-OUT. DAMAGE OCCURRED TO AN EXISTING REPAIR DOUBLER; REFER TO AML #63577-2 AND FVCI E.O. 23184-1 REV. IR DATED 09/08/2023. DAMAGED DOUBLER ON SKIN BETWEEN BS 1800 AND BS 1810, STR. 38R TO STR. 39R, WAS REMOVED AND REPLACED WITH NEW DOUBLER REPAIR DOCUMENTED IN FLIGHT VEHICLES CONSULTING, INC. (FVCI) ENGINEERING ORDER #23184-1 AND APPROVED BY 8110-3 ISSUED BY DER-T #876272412, DATED 09/11/2023.
DURING A-CHECK WO 230107, MRO HANGAR 901 DISCOVERED A MID EMERGENCY LIGHT IN FLIGHT DECK WAS NOT ILLUMINATING. THE LIGHT BULB WAS REPLACED WITH AN ILLUMINATION TEST PRODUCING SATISFACTORY RESULT. SEE HANGAR 901 (CRS: HAIY901D) PROJECT# H1-23-05-00084, WO 18590, NR 0104 FOR WORK ACCOMPLISHED.
DURING A-CHECK, ACCOMPLISHMENT OF SCHEDULED BOEING 747 TASK CARD 52-023-05-01, LEFT HAND UPPER DOOR, BATTERY PACK M7037 FAILED TO TEST ON PRESS-TO-TEST SWITCH. WORK ACCOMPLISHED ON (CRS# HAIY901D) HANGAR 901, PROJECT H1-23-05-00084, W/O 18590, NR 0046.
DURING A-CHECK, ACCOMPLISHMENT OF SCHEDULED BOEING 747 TASK CARD 52-023-05-01, LEFT HAND UPPER DOOR, DISCHARGE CARTRIAGE FOR THE PRESSURE VESSEL M7039 FAILED THE RESISTANCE CHECK. WORK ACCOMPLISHED ON CRS# HAIY901D) HANGAR 901, PROJECT H1-23-05-00084, W/O 18590, NR 0049.
DURING A-CHECK, ACCOMPLISHMENT OF SCHEDULED BOEING 747 TASK CARD 52-023-05-01, RIGHT HAND UPPER DOOR, BATTERY PACK M7038 FAILED TO TEST ON PRESS-TO-TEST SWITCH. WORK ACCOMPLISHED ON (CRS# HAIY901D) HANGAR 901, PROJECT H1-23-05-00084, W/O 18590, NR 0047.
DURING INSPECTION FOR ROUTINE WO 18360 â 0137 (SB TABLE 2 - INBOARD FLAP INSPECTION/LUBRICATION - AD 2021-02-15 (G)). IT WAS FOUND THAT ON SEQUENCE CARRIAGE NR 5 (R/H WING INBOARD FOREFLAP TRACK# 5), THE NUT ITEM NO. 11, WASHER ITEM NO. 12, OUTER CLAMP-UP WASHER ITEM NO. 10 AND THE COTTER PIN ITEM NO. 15 WAS COMPLETELY MISSING (SEE PICTURE SEQUENCE CARRIAGE NO. 5). THE BOLT ITEM NO. 9 WAS ALSO ALREADY SLIDING OUT OF HIS POSITION. DURING FURTHER INSPECTION IS WAS NOTICED THAT ON SEQUENCE CARRIAGE NO. 6 ON THE SAME POSITION THE COTTER PIN ITEM NO. 15 WAS ALSO MISSING, AND THE NUT ITEM NO. 11 WAS STILL ON THE BOLT BUT ALREADY LOOSE(SEQUENCE CARRIAGE NO. 6 PICTURE 1 OF 2 AND 2 OF 2). ALSO IT WAS FOUND THAT ON THE MAIN CARRIAGE NO. 5 OF THE MAIN FLAP A BOLT AND A WASHER WAS MISSING (MAIN CARRIAGE NO. 5 RH SIDE). (FOR THE ITEM NO. SEE ATTACHED AMM) THE CUSTOMER WAS INFORMED BY THE B1 ABOUT THE FINDINGS. NRC WAS RAISED (18361 - 0037) AND PART´S ORDERED. THE B1 OCCASIONED A FURTHER DETAILED INSPECTION AN ALL COMPONENTS AND ALSO ON THE LEFT WING TO ENSURE, THAT THERE IS NO MORE MISSING PARTS OR INCORRECT INSTALLED PARTS.
DURING ROUTINE INSPECTION, FOUND RIGHT INBOARD MID FLAP WITH GROUND DAMAGE (DENTED). ACCOMPLISHED A TIME LIMITED MAJOR REPAIR PER FLIGHT VEHICLES CONSULTING ENGINEERING ORDER 23069-1. DATA APPROVED ON FAA FORM 8110-3 DATED 3/31/2023 BY R. MANASHI DERT-876272412.
AFTER FUEL UPLIFT, FUEL FOUND VENTING FROM R/H WING SURGE TANK. ALLOWED FUEL TO FINISH VENTING - OPERATIONALLY CHECKED FUEL SYSTEM AND CONTINUED WITH MISSION. NO DEFECTS NOTED - SUSPECT THERMAL EXPANSION CAUSED VENTING.
RECEIVED INTERMITTANT FIRE CARGO AFT WARNING MESSAGE DURING GO AROUND - INSPECTED AFT CARGO FOR SMOKE/FIRE AND FOUND NONE. FIRE DETECTION SYSTEM TEST ACCOMPLISHED PER AIRCRAFT MAINTENANCE MANUAL 26-16-00 WITH NOW DEFECTS NOTED.
RIGHT SIDE EMERGENCY EXIT DOOR "BATTERY OK" TEST LAMP IS INOPERATIVE - RESEATED BATTERY, CLEANED BATTERY CONNECTION, VERIFIED PROPER VOLTAGE, OPS CHECK SATISFACTORY PER AMM 52-23-14.
MAIN DECK FIRE WARNING ACTIVATED AFTER LANDING. NO STATUS OR EICAS MESSAGE SHOWN. - NO FIRE PRESENT. PERFORMED GROUND TEST PER AIRCRAFT MAINTENANCE MANUAL 26-14-00. SYSTEM OPS CHECKS GOOD.
MAIN DECK FIRE WARNING, MASTER WARNING AND FIRE BELL ON TAKEOFF ROLL. REJECTED TAKEOFF. FIRE BELL CONTINUED TO SOUND AFTER SILENCED. - NO FIRE PRESENT. DISCOVERED MOISTURE IN CARD FILE M5206 CAUSED BY PALLETS BEING LOADED WET AND WATER DRIPPING INTO THE ELECTRICAL AND ELECTRONICS BAY. CLEANED MOISTURE FROM CARD FILE M5206. FIRE MAIN DECK FIRE WARNING EXTINGUISHED. TESTS NORMAL.
LEFT UPPER DECK EMERGENCY DOOR BATTERY OK TEST LIGHT IS INOP. REMOVED AND REPLACED BATTERY PACK PER AIRCRAFT MAINTENANCE MANUAL 52-23-14. OPS NORMAL
RIGHT UPPER DECK DOOR ASSIST BOTTLE POWER PACK DOES NOT TEST - REMOVED AND REPLACED POWER PACK IN ACCORDANCE WITH AIRCRAFT MAINTENANCE MANUAL 52-23-14.
FUEL DISCOVERED LEAKING FROM THE RIGHT WING SURGE TANK. EXTENUATING CIRCUMSTANCES INCLUDE PARKING CONFIGURATION THAT LEFT THE AIRCRAFT TILTED TO THE RIGHT. RIGHT WING SURGE TANK WAS SUMPED OF FUEL - NO FURTHER LEAKS WERE NOTED.
GROUND EQUIPMENT DAMAGE TO NUMBER 1 ENGINE INLET COWLING - ACCOMPLISHED TIME LIMITED MAJOR REPAIR OF COWLING PER FLIGHT VEHICLES CONSULTING, INC ENGINEERING ORDER 220092-1 REVISION IR DATED 6/14/2022.
DURING REFUEL, FUEL SPILLED FROM THE RIGHT WING OVERBOARD VENT. - SUMPED RIGHT WING SURGE TANK AND CONTINUED REFUEL OF AIRCRAFT PER AIRCRAFT MAINTENANCE MANUAL 12-11-10 WITHOUT INCIDENT. NO DEFECTS NOTED PER AIRCRAFT MAINTENANCE MANUAL 28-21-00
DURING INSPECTION FOUND ELONGATED FASTENER HOLES ALONG THE #4 PYLON OUTBOARD SKIRT BEAM LOWER CHORD @ NAC STA 400 TO 420.55. REPAIRED AS DIRECTED IN FVCI EO # 22071-4 REV C. DATED 05/29/2022 AND APPROVED BY FORM 8130-3 ISSUED BY DERT-710167-SW; DATED 05/30/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
DURING INSPECTION FOUND ELONGATED FASTENER HOLES COMMON TO LONGERONâS P/N 65B0279-13 (L/H) AND P/N 65B0279-14 (R/H) BETWEEN BS 2742 AND BS 2775. REPAIRED AS DIRECTED IN FVCI EO # 22071-6 REV B. DATED 05/21/2022 AND APPROVED BY FORM 8130-3 ISSUED BY DERT-710167-SW; DATED 05/30/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
DURING INSPECTION OF THE R/H #5 MED CUT-OUT AFT UPPER CORNER, INTERNAL BEAR STRAP FOUND CRACKED. ACCOMPLISHED REPAIR AS REQUIRED BY BOEING SB 747-53A2839 PART 5, TO INCLUDE DEVIATION (DAMAGE REMOVAL TRIM OUT RADIUS REDUCED TO 1.0â INSTEAD OF 1.5â AS REQ. BY SB) APPROVED BY BAC SR #4-5508991981 AND FORM 8100-9 ISSUED BY BOEING; DATED 05/29/2022. THIS IS AN APPROVED AMOC TO AD 2013-19-15 PARA (G)(2).
DURING INSPECTION FOUND 5 EACH ELONGATED FASTENER HOLES COMMON TO THE P/N 65B02789 FRAME STRAP @ BS 2775.3. REPAIRED AS DIRECTED IN FVCI EO # 22071-8 REV C. DATED 05/26/2022 AND APPROVED BY FORM 8130-3 ISSUED BY DERT-710167-SW; DATED 05/29/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
CORROSION DAMAGE FOUND AT LEFT WING L/E PANEL SUPPORT BEAM @ OLES 1510 APPROXIMATE. REMOVED DAMAGED SECTION AND SPLICED IN REPLACEMENT BEAM AS REQUIRED PER B747-400 SRM 57-41-13 REPAIR 3, BAC SR #4-5471089571, AND FORM 8100-9 ISSUED BY BOEING; DATED 05/29/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
DURING INSPECTION FOUND CHAFFING DAMAGE TO CARGO COMPARTMENT âTIE-DOWNâ TRACK P/N 65B18740-10 BETWEEN BS 1900 AND BS 1920. REPAIRED AS DIRECTED IN FVCI EO # 22071-7 REV A. DATED 05/20/2022 AND APPROVED BY FORM 8130-3 ISSUED BY DERT-710167-SW; DATED 05/27/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
DURING INSPECTION FOUND ELONGATED FASTENER HOLES ALONG FORWARD SEGMENT OF THE #4 PYLON OUTBOARD SKIRT BEAM SKIN PANEL P/N 323U2384-134. REPAIRED AS DIRECTED IN FVCI EO # 22071-3 DATED 05/10/2022 AND APPROVED BY FORM 8130-3 ISSUED BY DERT-710167-SW; DATED 05/26/2022. REPAIR CATEGORIZED AS A PERMANENT REPAIR.
UPPER DECK R/H DOOR EMERGENCY ASSIST BOTTLE TEST LIGHT INOPERATIVE. REMOVED AND REPLACED THE UPPER DECK R/H DOOR EMERGENCY SYSTEM BATTERY PACK PER B747 AMM 52-23-14.
RIGHT EMERGENCY ESCAPE DOOR BATTERY TEST FUNCTION INOPERATIVE - RESEATED CONNECTOR ON THE BATTERY PACK AND SYSTEM FUNCTIONS NORMAL PER AIRCRAFT MAINTENANCE MANUAL 52-23-14.
DURING DAILY SERVICE CHECK, FOUND R/H UPPER DECK ENTRY DOOR EMERGENCY ASSIST BATTERY PACK INOPERATIVE. REMOVED AND REPLACED BATTERY PACK PER AMM - OPERATIONAL CHECK NORMAL.
REF. LP 49190-3, HAITEC W/O H1-21-05-00060/17084 & NRC 0021, AND FVCI E/O #21123-3: FWD. CARGO DOOR HAS DAMAGE TO THE LOWER FORWARD CORNER â EXTERIOR SKIN IS DENTED AND CREASED. ACCOMPLISHED DOUBLER REPAIR TO THE FWD. CARGO DOOR LOWER FORWARD CORNER AS PER FVCI EO #21123-2 REV A. AND FORM 8110-3 DATED 08/16/2021. THIS CONSTITUTES A MAJOR REPAIR TO THE FORWARD CARGO DOOR.
DURING ACCOMPLISHMENT OF TASK CARD 54-153-01-01, ENLARGED BOLT HOLES NOTED ON NUMBER 1 PYLON PANEL NUMBER 452EL. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20298-8.
DURING ACCOMPLISHMENT OF TASK CARD 54-153-01-04, ENLARGED BOLT HOLE NOTED ON NUMBER 4 PYLON PANEL NUMBER 482EL. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20298-8.
DURING ACCOMPLISHMENT OF TASK CARD 54-814-00-02, 1 EACH CRACK NOTED ON ANGLE OF NUMBER 2 PYLON PANEL 464B INBOARD UPPER FORWARD SIDE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20305-1.
DURING ACCOMPLISHMENT OF TASK CARD 54-814-00-02, 1 EACH CRACK NOTED ON SKATE ANGLE OF NUMBER 3 PYLON INBOARD FAIRING AT NACELLE STATION 457. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20305.
DURING ACCOMPLISHMENT OF TASK CARD 53-510-00-01, 1 EACH CRACK NOTED ON STANCHION AT FORWARD CARGO DOOR CUTOUT AREA AT BODY STATION 560 STRINGER S-35R. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20307.
CRACK NOTED ON NUMBER 4 PYLON LEFT UPPER SIDE SKIN. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-1.
DEFORMATION NOTED ON SKIN OF NUMBER 4 PYLON LEFT UPPER FAIRING DOOR FORWARD SIDE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-2.
GOUGE NOTED ON NUMBER 1 PYLON UNDERWING FAIRING UPPER SIDE SKIN PANEL AT NACELLE STATION 338. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20322-5.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-02, A NICK WAS NOTED ON THE NUMBER 2 PYLON FAN COWL AFT SUPPORT BEAM OUTBOARD AREA. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20314.
DURING ACCOMPLISHMENT OF SB 747-53A2450 REV 8, 2 EACH CRACKED FASTENER HOLE NOTED AT NR 5 RIGHT MAIN ENTRY DOOR CUTOUT, 1 EACH AT BODY STATION 2231 STRINGER S-19R. REPAIR ACCOMPLISHED IN ACCORDANCE WITH B747-400SF STRUCTURAL REPAIR MANUAL 53-60-15-2R-2, WITH DEVIATIONS CALLED OUT IN BOEING SERVICE REQUEST 3-4783741881 AND ITS ASSOCIATED MESSAGES. AD 2013-17-08 ALTERNATE METHOD OF COMPLIANCE APPROVAL GRANTED ON 8100-9 DATED 8/23/2020 BY CS ADAMS AR-830677.
DURING ACCOMPLISHMENT OF SB 747-53A2450 REV 8, 2 EACH CRACKED FASTENER HOLES WERE NOTED, 1 EACH AT BODY STATION 2231 STRINGER S-16L AND 1 EACH AT BODY STATION 2231 STRINGER S-19L. REPAIRS ACCOMPLISHED IN ACCORDANCE WITH B747-400SF STRUCTURAL REPAIR MANUAL 53-60-15-2R-2, WITH DEVIATIONS CALLED OUT IN BOEING SERVICE REQUEST 3-4778074844 AND ITS ASSOCIATED MESSAGES. AD 2013-17-08 ALTERNATE METHOD OF COMPLIANCE APPROVAL ON GRANTED ON 8100-9 DATED 8/23/2020 BY CS ADAMS AR-830677.
DURING ACCOMPLISHMENT OF BOEING SERVICE BULLETIN 747-53A2465 REVISION 5, FOUND NOSE WHEEL WELL SIDE PANEL STIFFENER CRACKED AT BODY STATION 265-STA 280 WATERLINE 170, LEFT BUTTOCK LINE 30. FABRICATED STIFFENER IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER 20293-5. REPLACEMENT ACCOMPLISHED IN ACCORDANCE WITH SB 747-53A2465 REVISION 5.
GOUGE NOTED ON NUMBER 1 PYLON UNDERWING FAIRING SKIN PANEL AT NACELLE STATION 332. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-5.
DURING ACCOMPLISHMENT OF DAMAGE TOLERANCE INSPECTION FOR SATELITE COMMUNICATION SYSTEM ANTENNA DOUBLER, CORROSION WAS NOTED ON THE SKIN INTERIOR AT BODY STATION 1480 FROM STRINGER S-10L TO STRINGER S-11L. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20330.
DURING ACCOMPLISHMENT OF TASK CARD 54-806-00-01, A CRACK WAS NOTED ON A PNEUMATIC TUBE SUPPORT BRACKET, INSIDE NUMBER 1 PYLON PANEL 451B. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER 20293-4.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-03, CRACKS WERE NOTED ON THE EXTERNAL SURFACE OF NUMBER 3 PYLON PANEL NUMBER 472FL. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20316-8.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-02, CRACKS WERE NOTED ON THE EXTERNAL SURFACE OF NUMBER 2 PYLON PANEL NUMBER 462GL. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20316.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-04, CHAFING WAS NOTED ON SKIN OF NUMBER 4 PYLON PANEL NUMBER 482FR. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20319-1.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-03, ENLARGED BOLT HOLE NOTED ON NUMBER 3 PYLON PANEL NUMBER 472ER. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20298-8.
DURING ACCOMPLISHMENT OF TASK CARD 71-814-01-01, CHAFING WAS NOTED ON DOUBLER OF NUMBER 1 ENGINE LEFT CORE COWL INNER FACE AFT SIDE FRAME. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER 20316-10.
DURING ACCOMPLISHMENT OF TASK CARD 71-802-01-04, DENT WITH GOUGES WAS NOTED ON THE SKIN OF NUMBER 4 ENGINE LEFT CORE COWL OUTER SURFACE AT NACELLE STATION 182.5. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20318.
DURING ACCOMPLISHMENT OF TASK CARD 71-802-01-04, DENT WITH GOUGES WAS NOTED ON THE SKIN OF NUMBER 4 ENGINE LEFT CORE COWL OUTER SURFACE AT NACELLE STATION 182.5. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20318.
DURING ACCOMPLISHMENT OF TASK CARD 71-810-01-01, CHAFING WAS NOTED ON THE SKIN OF NUMBER 1 ENGINE RIGHT THRUST REVERSER COWL INNER SURFACE FORWARD SIDE, NAC STA 131.78. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20309.
DURING ACCOMPLISHMENT OF TASK CARD 53-804-01-01, EXISTING BLEND REPAIR NOTED ON SKIN AT LOWER FUSELAGE STA 1801 S-38R TO S-39R. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC, ENGINEERING ORDER NUMBER 20288.
DURING ACCOMPLISHMENT OF TASK CARD 71-810-01-01, CHAFING NOTED ON THE SKIN OF THE NUMBER 1 ENGINE LEFT THRUST REVERSER COWL INNER FACE LOWER BIFURCATION. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20319-2.
DURING ACCOMPLISHMENT OF TASK 57-810-01-01, A CRACK WAS NOTED ON THE SKIN OF THE LEFT WING INBOARD FIXED LEADING EDGE NOSE BEAM CUTOUT, ADJACENT TO THE NUMBER 11 KRUEGER FLAP INBOARD LINK, LEADING EDGE ILES 543.93. REPAIR ACCOMPLISHED, IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER 20300-2.
DURING ACCOMPLISHMENT OF TASK CARD 71-802-01-02, A DENT WAS NOTED ON THE OUTER SKIN OF THE NUMBER 2 ENGINE EXHAUST SLEEVE, NACELLE STATION 318 NEAR 7 O`CLOCK POSITION. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20322-6.
DURING ACCOMPLISHMENT OF BOEING SERVICE BULLETIN 747-53A2390, CRACKED FASTENER HOLES WERE NOTED AT SKIN PANEL UNDER LONGERON EXTENSION FITTING 1 EACH BODY STATION 1480 STRINGER S-32L AND 1 EACH AT BODY STATION 1480 BETWEEN STRINGERS S-32R AND S-34R. REPAIR ACCOMPLISHED IN ACCORDANCE WITH BOEING SERVICE BULLETIN 747-53A2390 PLAN A REPAIRS.
DURING ACCOMPLISHMENT OF TASK CARD 32-820-01-01, RIGHT WING LANDING GEAR FORWARD PRIMARY DOOR INNER SKIN WAS NOTED AS DEFORMED. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20289.
DURING ACCOMPLISHMENT OF TASK CARD 55-820-01-01, CORROSION WAS NOTED ON THE SKIN OF THE RIGHT HORIZONTAL STABILIZER UPPER SURFACE AT STABILIZER STATION 385 STRINGER 5. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20322-1.
DURING ACCOMPLISHMENT OF TASK CARD 53-630-00-07, CORROSION WAS NOTED ON NUMBER 4 MAIN ENTRY DOOR AREA FRAME STRAP AT BODY STATION 1660 STRINGER S-26L. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20287-1.
DURING ACCOMPLISHMENT OF TASK CARD 71-810-01-02, CHAFING WAS NOTED ON NUMBER 2 ENGINE RIGHT THRUST REVERSER CORE COWL TRAILING EDGE INNER UPPER SIDE CLOSE OUT PANEL. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-4.
DURING ACCOMPLISHMENT OF TASK CARD 57-888-01-01, FASTENER NOTED AS LOOSE ON THE RIGHT WING INBOARD FIXED LEADING EDGE NOSE SKIN, OUTBOARD SIDE, ILES 330. - REPAIR ACCOMPLISHED IN ACCORDANCE WITH B747SF STRUCTURAL REPAIR MANUAL 57-41-01-2R-5, WITH DEVIATIONS IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20301.
DURING ACCOMPLISHMENT OF TASK CARD 71-812-01-02, NR 2 ENGINE RIGHT THRUST REVERSER TORQUE BOX UPPER CABLE BOLT HOLE WORN WAS NOTED AS WORN. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20316-7.
DURING ACCOMPLISHMENT OF TASK CARD 57-810-01-01, A CRACK WAS NOTED ON THE LEFT WING INBOARD FIXED LEADING EDGE NOSE BEAM CUTOUT, ADJACENT TO THE NUMBER 12 KRUEGER FLAP INBOARD LINK, ILES 445.5. REPAIR ACCOMPLISHED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER 20300-1.
DURING ACCOMPLISHMENT OF TASK CARD 57-888-01-01, A CRACK WAS NOTED ON THE UPPER FACE OF RIGHT WING INBOARD FIXED LEADING EDGE NOSE SKIN, ILES 630. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20320-3.
DURING ACCOMPLISHMENT OF TASK CARD 57-570-00-04, CORROSION WAS DISCOVERED ON THE UPPER FACE OF RIGHT WING OUTBOARD AILERON LEADING EDGE SKIN AT WBL 998 TO WBL 1023. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20320-1.
DURING ACCOMPLISHMENT OF TASK CARD 57-808-01-01, 2 EACH FASTENER WERE NOTED AS LOOSE ON THE LEFT WING INBOARD FIXED LEADING EDGE NOSE SKIN, OUTBOARD SIDE, ILES 330. REPAIR ACCOMPLISHED IN ACCORDANCE WITH B747SF STRUCTURAL REPAIR MANUAL 57-41-01-2R-5, WITH DEVIATIONS IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20301.
DURING ACCOMPLISHMENT OF TASK CARD 57-906-01-01, DEFORMED SKIN WAS NOTED AT INBOARD EDGE OF RIGHT WING NUMBER 18 VARIABLE CAMBER FLAP FOLDING NOSE SKIN. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20298.
DURING ACCOMPLISHMENT OF TASK CARD 54-804-00-02, NICK NOTED ON NUMBER 2 ENGINE PYLON LFAN COWL AFT SUPPORT BEAM OUTBOARD AREA. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20314.
DURING ACCOMPLISHMENT OF TASK CARD 57-820-01-01, A CRACK WAS NOTED ON THE LEFT WING CENTER LEADING EDGE NOSE BEAM INBOARD UPPER AT ILES 693.5. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER 20320-2.
DURING ACCOMPLISHMENT OF BOEING SERVICE BULLETIN 747-54A2182 REVISION 3, CORROSION NOTED ON NUMBER 3 ENGINE PYLON UPPER LINK FORWARD BUSHING. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20314-1.
DESCRIPTION CORRECTION FOR U2RA202010160012. CORROSION NOTED ON NUMBER 3 PYLON UPPER FORWARD BUSHING. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20314-1.
DURING ACCOMPLISHMENT OF TASK CARD 57-820-01-01, A CRACK WAS NOTED ON LEFT WING CENTER LEADING EDGE NOSE BEAM INBOARD UPPER AT ILES 693.5, UPPER CHORD, LOWER CHORD, AND WEB. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20320-2. CHORD P/N 65B07895-131, CHORD P/N 65B07895-171, WEB P/N 65B07895-137.
DURING ACCOMPLISHMENT OF TASK CARD 53-916-01-01, RIGHT APU DOOR EXTERNAL SKIN NOTED AS DENTED, STA 2725, 15 INCHES BELOW APU DOOR HINGE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20309-2.
DURING ACCOMPLISHMENT OF SERVICE BULLETIN 747-54A2182 POST STRUT MODIFICATION INSPECTIONS OF NUMBER 3 PYLON, CORROSION WAS NOTED ON THE FORWARD UPPER SPAR FITTING AND THE WING FRONT SPAR TO STRUT UPPER LINK FITTING. ACCOMPLISHED REPAIRS IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL 54-51-90-2R-5 REPAIR 5 AND 57-20-90-2R-1 REPAIR 1.
DURING ACCOMPLISHMENT OF SERVICE BULLETIN 747-54A2182 POST STRUT MODIFICATION INSPECTIONS OF NUMBER 2 PYLON, CORROSION WAS NOTED ON THE FORWARD UPPER SPAR FITTING AND THE WING FRONT SPAR TO STRUT UPPER LINK FITTING. ACCOMPLISHED REPAIRS IAW STRUCTURAL REPAIR MANUAL 54-51-90-2R-5 REPAIR 5 AND 57-20-90-2R-1 REPAIR 1.
A DENT WITH A NICK WAS NOTED ON THE FUSELAGE SKIN LOCATED APPROXIMATELY BODY STATION 444.5 AT STRINGER S-44L. ACCOMPLISHED REPAIR IN ACCORDANCE WITH BOEING SERVICE REQUEST 4-4843050665 AND ITS ASSOCIATED MESSAGES.
A CRACK WAS NOTED IN THE WEB OF THE AFT CARGO COMPARTMENT FLOOR AT BODY STATION 1820 LEFT BUTTOCK LINE 14. ACCOMPLISHED REPAIR IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL 53-60-07-2R-8 REPAIR 8.
DURING ACCOMPLISHMENT OF TASK CARD 57-710-00-01, CORROSION WAS NOTED ON THE CONDUCTIVE STRIP OF THE LEFT WINGLET TRAILING EDGE WEDGE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBERS 20315 AND 20315-1.
DURING ACCOMPLISHMENT OF INSPECTION REQUIRED BY TASK CARD 57-830-01-01, LEFT WING OUTER LEADING EDGE LOWER FIXED PANEL LEADING EDGE SEAL RETAINER NOTED AS DEFORMED BETWEEN OLES 1545.50 AND WBL 1241. ACCOMPLISHED REPAIR OF SEAL RETAINER IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20320-4.
DURING ACCOMPLISHMENT OF TASK CARD 25-054-01-01, DAMAGE WAS NOTED ON FORWARD CARGO LOADING SYSTEM BALL TRANSFER UNIT. - ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20287.
DURING ACCOMPLISHMENT OF TASK CARD 25-054-01-01, DAMAGE WAS NOTED ON AFT CARGO LOADING SYSTEM BALL TRANSFER UNIT. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 20287.
DURING ACCOMPLISHMENT OF INSPECTIONS REQUIRED BY TASK CARD 53-804-01-01, A DENT WAS NOTED ON LOWER FUSELAGE EXTERNAL SKIN, AFT CARGO CUTOUT AFT EDGE , BODY STATION 1920, BETWEEN STRINGERS S-36R S-37R. DENT WAS REPAIRED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20292.
DURING ACCOMPLISHMENT OF TASK CARD 54-812-00-04, CRACK NOTED ON NUMBER 4 ENGINE PYLON LEFT AFT FAIRING DOOR INNER SURFACE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-9A.
CRACKS FOUND ON MAIN ENTRY DOOR NR 2 LT/RT SIDE BODY STATION 800 FRAME AFT ANGLE INNER CHORD AND LHS DOOR STOP TEE AT STRINGER S-17 DURING INSPECTIONS PER SERVICE BULLETIN 747-53A2451, REV. 02. ALSO, EXISTING ADDITIONAL FASTENER FOUND ON LT DOOR STOP INTERCOSTAL AT STRINGER S-17L. - ACCOMPLISHED REPAIRS PER INSTRUCTIONS PROVIDED IN BOEING SERVICE REQUEST NUMBER 3-4762064646 AND ITS ASSOCIATED MESSAGES.
DURING ACCOMPLISHMENT OF TASK CARD 54-812-00-01, CRACK NOTED ON NUMBER 1 ENGINE PYLON LEFT AFT FAIRING DOOR INNER SURFACE. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20316-9B.
SHIM MIGRATION NOTED ON LEFT WING MAIN LANDING GEAR GATE SUPPORT FITTING DURING FOLLOW ON INSPECTION FOR PREVIOUS SHIM MIGRATION. ACCOMPLISHED SHIM REPLACEMENT IAW BOEING SERVICE REQUEST NUMBER'S 4-4817985813 AND ASSOCIATED MESSAGES.
DURING ACCOMPLISHMENT OF TASK CARD 32-836-01-01, A DENT WAS NOTED ON THE SKIN OF RIGHT BODY LANDING GEAR SHOCK STRUT DOOR. ACCOMPLISHED REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER EO 20289-1.
DURING ACCOMPLISHMENT OF SB 747-53A2305, SKIN CRACKING WAS DISCOVERED NEAR THE LEFT AND RIGHT HAND AFT CORNERS OF THE NOSE WHEEL WELL. ACCOMPLISHED REPAIRS AS OUTLINED IN SERVICE REQUEST 4-4818744620 AND ITS ASSOCIATED MESSAGES.
RIGHT WING INBOARD MID FLAP LOWER SKIN HAS MULTIPLE DENTS. ACCOMPLISHED REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER EO 20219.
NUMBER 4 ENGINE PYLON OUTBOARD SIDE DOOR PANEL MISSING. ACCOMPLISHED MAJOR REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20159.
AUXILIARY POWER UNIT COMPARTMENT LNTERCOSTAL DAMAGED. ACCOMPLISHED MAJOR REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20152.
AUXILIARY POWER UNIT COMPARTMENT LNTERCOSTAL DAMAGED. ACCOMPLISHED MAJOR REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20152.
AUXILIARY POWER UNIT COMPARTMENT LNTERCOSTAL DAMAGED. ACCOMPLISHED MAJOR REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20152.
AUXILIARY POWER UNIT COMPARTMENT LNTERCOSTAL DAMAGED. ACCOMPLISHED MAJOR REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER NUMBER 20152.
NUMBER 4 ENGINE INBOARD THRUST REVERSER DAMAGED - ACCOMPLISHED MAJOR REPAIR OF DAMAGE ON NUMBER 4 ENGINE INBOARD THRUST REVERSER HALF. REPAIR COMPLETED IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING, INC. ENGINEERING ORDER CONTROL NUMBER 20140 REVISION IR DATED APRIL 15, 2020, DATA APPROVED ON FAA FORM 8110-3 CONTROL NUMBER 20140 DATED APRIL 15, 2020.
SUPPORT ANGLE PN 65B07430-97 FOR WING TO BODY PANEL 293HL CRACKED AND HOLES MISALIGNED WITH CHORD PN 65B15823-7. REMOVED AND REPLACED SUPPORT ANGLE ASSEMBLY P/N 65B07430-97 AND PERFOMED REPAIR TO CHORD P/N 65B15832-7 IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER 19321-2.
NR 1 PYLON SKIRT FAIRING FORWARD INBOARD, OUTER SKIN HAS SHEETMETAL HOLE DAMAGE AND TWO CRACKS. REPAIRED NUMBER 1 PYLON SKIRT FAIRING FORWARD INBOARD OUTER SKIN WITH SPLICE AND DOUBLER REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 19321-1.
LEFT WING TRAILING SUPPORT BEAM AT APPROXIMATE WING STATION 268.192 ATTACHING FITTING BEARING IS MISSING. INSTALLED NEW OVERSIZE BEARINGIN ATTACH FITTING PER FLIGHT VEHICLES CONSULTING INC ENGINEERING ORDER 19343.
LEFT WING TRAILING EDGE SUPPORT BEAM UPPER CHORD P/N 65B11614-15, INBOARD END AT APPROXIMATE WBL 130 HAS 3 EACH ELONGATED HOLES AND CORROSION ON UPPER SURFACE. REMOVED CORROSION AND REMAINING MATERIAL THICKNESS FOUND TO BE WITHIN LIMITS PER B747-400SF SRM 57-51-13-1A-1. REPAIRED ELONGATED HOLES IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER NUMBER 19227.
FOUND ONE EACH BREATHER ANGLE P/N 69B13824-11 CRACKED COMMON TO LEFT WING FIXED TRAILING EDGE PANEL OUTBOARD SIDE BETWEEN INBOARD AILERON AND NUMBER FIVE SPOILER. REMOVED AND REPALCED BREATHER ANGLE PER SRM 51-40-02.
RIGHT INBOARD MIDFLAP RUBSTRIP RIB CRACKED AND WORN THROUGH AT FASTENER HOLE TOP SIDE UNDER RETAINER. REMOVED AND REPLACED RIGHT INBOARD MID FLAP RUBSTRIP AND CLOSURE RIB ASSEMBLY PER B747-400 AMM 57-52-01.
LEFT FUSELAGE SKIN AT BODY STATION 1430, BETWEEN STRINGER 28 LEFT AND STRINGER 29 LEFT HAS DENT WITH APPARENT CREASE. REPAIRED LEFT FUSELAGE SKIN AT BODY STATION 1430 BETWEEN STRINGER 28 LEFT AND 29 LEFT IN ACCORDANCE WITH SRM 53-00-01 REPAIR 1.
ON TAKE-OFF AIRCRAFT TRIED TO ROLL TO THE LEFT. DURING FLAP RETRACTION AT APPROXIMATE 10 DEGREE AILERON CONTROL RETURNED TO NORMAL. AIRCRAFT WAS OPERATED TO DESTINATION STATION PHIK AND HAD AN UNEVENTFUL LANDING. ON POST FLIGHT FOUND LEFT WING INBOARD FORE FLAP MISSING. PIECES OF FORE FLAP WERE RECOVERED AT DEPARTURE STATION PGUA. DEPARTURE OF FORE FLAP DURING TAKE-OFF CAUSED ADDITIONAL DAMAGE TO THE AIRCRAFT WING TO BODY FAIRING, NUMBER 5 AND NUMBER 6 GROUND SPOILER, WING TRAILING EDGE COMPOSITE PANEL, LEFT WING INBOARD MID FLAP AND LEFT WING INBOARD AILERON. A CONDITIONAL INSPECTION FOR PARTS DEPARTING THE AIRCRAFT HAS BEEN ACCOMPLISHED IN ACCORDANCE WITH AMM 05-51-58. A SUPPLEMENT TO THIS REPORT WILL BE SUBMITTED SHOULD MORE INFORMATION REGARDING THE EVENT BECOME AVAILABLE.
RIGHT WING LEADING EDGE PANEL FOUND DELAMINATED. REMOVED AND REPLACED RIGHT WING LEADING EDGE PANEL IAW SRM 51-40-02.
RIGHT TRANSPONDER ALTITUDE REPORTING IN ERROR, AS REPORTED BY AIR TRAFFIC CONTROL. TROUBLESHOOTING REVEALED THE ERROR WAS CAUSED BY THE BY THE LEFT DIGITAL AIR DATA COMPUTER. THE LEFT DIGITAL AIR DATA COMPUTER WAS FOUND TO BE READING 250 FOOT HIGH. THE LEFT DIGITAL AIR DATA WAS REMOVED AND REPLACED IN ACCORDANCE WITH AMM 34-21-00 AND FUNCTIONALLY TESTED GOOD. THE RIGHT TRANSPONDER SYSTEM WAS FUNCTIONALLY TESTED AFTER THE REPLACEMENT OF THE LEFT DIGITAL AIR DATA COMPUTER USING THE LEFT SIDE AS THE SOURCE FOR DATA AND FUNCTIONALLY TESTED GOOD IN ACCORDANCE WITH AMM 34-50-00.
DURING ACCOMPLISHMENT OF SERVICE BULLETIN 747-53A2494 REVISION 2 FOUND FRAME AFT INNER CHORD AT STATION 2230 RT R5 DOOR CRACKED. ACCOMPLISHED FRAME INNER CHORD CRACK REPAIR IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL CHAPTER 53-60-07 REPAIR 7.
DURING ACCOMPLISHMENT OF SERVICE BULLETIN 747-53A2494 REVISION 2 FOUND FRAME AFT INNER CHORD AT STATION 2231 LEFT HAND R5 DOOR CRACKED. ACCOMPLISHED FRAME INNER CHORD CRACK REPAIR IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL CHAPTER 53-60-07 REPAIR 7.
LEFT SIDE AIRCONDITIONING BAY, AFT UPPER BODY FAIRING SUPPORT FRAME IS CRACKED AT THE ANGLE. REPAIRED FAIRING SUPPORT FRAME IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL 53-00-71-2R-1 AND 51-70-11.
LEFT WING TRAILING EDGE SUPPORT RIB WEB AT WBL 255.692 INBOARD OF THE NR 6 SPOILER IS CRACKED. REMOVED CRACKED WEB, FABRICATED NEW LAMINATED WEB IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL 57-51-02-01-1 IDENTIFICATION AND INSTALLED NEW WEB IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL 51-40-02.
DURING DECENT TO APPROACH, THE NR 1 HYDRAULIC SYSTEM FAILED DUE TO FLUID LEAK. FOUND THE NR 1 HYDRAULIC SYSTEM AIR DRIVEN DEMAND HYDRAULIC PUMP PRESSURE HOSE LEAKING. REMOVED AND REPLACED THE HYDRUALIC PRESSURE HOSE IIAW MM 29-11-17, 29-11-23, AND 20-11-05. PERFORMED A SATISFACTORY OPS AND LEAK CHECK.
DAMAGED SEAT TRACK BS 1915 - 1918, RBL 25.75, WL 118. ACCOMPLISHED INTERIM REPAIR EO 53-18042.
DURING LEVEL FLIGHT, DETECTED A SUDDEN MEDIUM FREQUENCY VIBRATION. AIRSPEED WAS REDUCED AND VIBRATION STOPPED. FOUND THE NUMBER 11 KRUEGER FLAP OUTBOARD SEAL PANEL UNDER LEFT WING AT APPROXIMATELY WS 614 TO 642 LEADING EDGE AREA TO BE MISSING. PERFORMED AIRFRAME VIBRATION CONDITIONAL INSPECTION IAW AMM 05-51-38 AND PART DEPARTED AIRPLANE CONDITIONAL INSPECTION IAW AMM 05-51-58. APPLIED INTERIM REPAIR IAW INSTRUCTIONS PROVIDED IN SERVICE REQUEST ID 3-4071766604.
DURING FLIGHT, RECEIVED EICAS MASSEAGE FOR DOOR U/D FLT LOCK MESSAGE REMAINED UNTIL LANDING. TROUBLESHOT ECIAS MESSAGE, FOUND RIGHT UPPERDECK DOOR FLIGHT LOCK ACTUATOR INOPERATIVE.
LEFT UPPER DECK EMERGENCY EXIT DOOR, EMERGENCY DEPLOY BATTERY DOES NOT TEST. REMOVED AND REPLACED THE BATTERY IAW AIRCRAFT MAINTENANCE MANUAL 52-23-14.
EMERGENCY EXIT LIGHT ABOVE RIGHT UPPER DECK EMERGENCY EXIT DOOR, L1 AND R1 MAIN DECK DOORS WON'T ILLUMINATE. REMOVED AND REPLACED THE BATTERY PACK IAW AMM 33-51-04. PERFORMED SATISFACTORY OPERATIONAL CHECK.
RIGHT UPPER DECK DOOR, EMERGENCY POWER SYSTEM WILL NOT TEST. REPLACED THE RT POWER SUPPLY IAW AMM 33-51-04. OPS CHECKED GOOD.
LEFT UPPER DECK DOOR EMERGENCY POWER SYSTEM WILL NOT TEST. REPLACED THE LT POWER SUPPLY IAW AMM 33-51-04. OPS CHECKED GOOD.
DAMAGE FOUND ON THE NR 4 ENGINE THRUST REVERSER OUTBOARD SLEEVE. ACCOMPLISHED A TIME LIMITED REPAIR IAW DRAWING 54-17042-1.
FWD CARGO FIRE INDICATION DURING LANDING DECELERATION, EICAS MESSAGE AND FIRE BELL, SITUATION RESET ITSELF AND STOPPED AFTER RUNWAY EXIT. CHECKED FORWARD CARGO FOR SIGNS OF FIRE OR SMOKE, NONE FOUND. PERFORMED FIRE AND SMOKE DETECTION GROUND TEST IAW AMM 26-16-00. NO DEFECTS NOTED.
INLET COWL, COWL TO STRUT MATING FLANGE SURFACE AT 12 O'CLOCK POSITION WORN. ACCOMPLISHED INTERIM REPAIR IAW EO 5410ERO2253.
UPPER DECK, AISLE, STAIRWAY, AND COCKPIT EMERGENCY LIGHTS DO NOT OPERATE DURING TEST. REMOVED AND REPLACED THE BATTERY PACK IAW AMM 33-51-04. OPS TEST SATISFACTORY.
LEFT WINGLET TIP FOUND WITH ONE EACH LIGHTNING STRIKE. ACCOMPLISHED REPAIR OF LT WING WINGLET TE WEDGE CASTING IAW ENGINEERING REPAIR ORDER 5730ERO2161.
RT WING TO BODY FAIRING 192K SUPPORT FRAME CRACKED. R & R SUPPORT FRAME IAW SRM 51-40-02.
RT BODY STATION 1265 FRAME INNER CHORD FOUND WITH 1 CRACK MEASURING 0.030". ACCOMPLISHED REPAIR MODIFICATION OF BODY STATION 1265 CHORD IAW SB 747-53A2416.
RIGHT WING T/E SPAR CAVITY NR 8 SPOILER ACTUATOR INBD LOWER AREA HAS ONE CRACKED BRACKET. R & R BRACKET IAW SRM 51-40-02.
AFT CARGO DOOR FORWARD LOWER SKIN EDGE FOUND WITH DENT. REPAIRED AFT CARGO DOOR SKIN BY INSTALLATION OF EXTERNAL DOUBLER IAW SRM 52-30-01, REPAIR 2, FIGURE 201.
AFT LOWER CARGO COMPARTMENT AT BS 1534 LT OF BUTT LINE 25 POWER DRIVE UNIT SUPPORT ANGLE CRACKED. R & R SUPPORT ANGLE IAW SRM 51-40-02.
AFT LOWER CARGO COMPARTMENT AT BS 1625 RT OF BUTTLINE 25 POWER DRIVE UNIT SUPPORT ANGLE CRACKED. R & R SUPPORT ANGLE IAW SRM 51-40-02.
FOUND DENT AND BLEND OUT IN CLOSE PROXIMITY ON SKIN NEAR BODY STA 560 BETWEEN STR 35R AND 36R. REPAIR WAS ACCOMPLISHED IAW EB-53-2543 IN REF TO SERVICE REQUEST 3-3617438202. THE REPAIR METHOD HAS BEEN APPROVED.
FOUND FUSELAGE SKIN AT STA 720-740 BETWEEN STR 25L AND 26L WITH BLEND OUT IN CLOSE PROXIMITY TO PREVIOUS EXTERNAL SKIN REPAIR. ACCOMPLISHED EXTERNAL SKIN DOUBLER REPAIR IAW SRM 53-00-01, REPAIR 15, FIGURE 201.
FORWARD LOWER CARGO COMPARTMENT AT BS 935 LEFT OF BUTT LINE 25 POWER DRIVE UNIT SUPPORT ANGLE CRACKED. R & R SUPPORT ANGLE IAW SRM 51-40-02.
LEFT STA 1480, AFT BODY SCUPPER CRACKED. R & R SCUPPER IAW SRM 51-40-02.
LOWER FUSELAGE RT FIXED PANEL 192K SUPPORT FRAME FOUND WITH CRACK. R & R SUPPORT FRAME IAW SRM 51-40-02.
EMERGENCY LIGHT INOPERATIVE FORWARD OF GULL WING DOORS. R & R EMERGENCY LIGHT FORWARD OF GULL WING DOOR IAW AMM 33-51-07.
NOSE LANDING GEAR LT AND RT TRUNNION END CAPS HAVE CORROSION. REPAIRED LT AND RT NLG TRUNNIONS BY MACHINE BORING IAW SRM 53-10-90-2R-1.
EMERGENCY EXIT LIGHT ASSY INOPERATIVE AT BASE OF STAIRS AND L-1 DOOR. R & R M5170 BATTERY PACK IAW AMM 33-51-04, OPS CHECK GOOD.
LEFT UPPER DECK DOOR EMERGENCY BATTERY PACK DOES NOT TEST. R & R LT UPPER DECK DOOR BATTERY CHARGER IAW AMM 33-51-04 AND BATTERY IAW AMM 52-23-14. TESTS NORMAL.
ON DECENT, A BURNING ODOR WAS PRESENT ON THE UPPER FLIGHTDECK, ODOR FOLLOWED BY HEAVY VIBRATION FROM RT SIDE OF AIRCRAFT. CREW ELECTED TO SHUTDOWN NR 3 PACK. VIBRATION STOPPED. MAINTENANCE FOUND NR 3 ACM AS CAUSE. DEFERRED NR 3 PACK IAW MEL 21-51-01-01.
DURING FUEL TANK INSPECTION, FOUND SHEARED BOLT IN LT WING NR 2 MAIN TANK INBD OF WING BUTT LINE 150.0 ON STR 7. GENERATED ITEM TO PERFORM HARD LANDING INSPECTION. REPLACED BOLT AT LT WING NR 2 MAIN FUEL TANK INBD OF WING BUTT LINE 150.0, STR 7 IAW SRM 51-40-02.
UPPER DECK, LT FLOOR MOUNTED ESCAPE SLIDE FORWARD STORED GAS RESERVOIR READS EMPTY ON THE GUAGE. R & R STORED GAS RESERVOIR ASSY IAW AMM 2568-02.
BRAKING NOT NORMAL. EICAS GEAR PAGE INDICATES NO BRAKING ON RT SIDE BODY & WING GEAR. R & R BRAKE METERING VLV IAW AMM 32-41-03. R & R RT AUTO BRAKE SHUTTLE VLV IAW AMM 32-42-12. R & R ANTISKID SHUTTLE VLV IAW AMM 32-42-14. BRAKE SYS CHECK NORMAL. PERFORMED TAXI TEST OF ACFT. TAXI TEST CHECKED NORMAL.
EICAS, GEAR PAGE, INDICATES NO BRAKING ON RT WING & BODY MAIN GEAR. BRAKING NOT NORMAL. REPLACED RT ANTISKID MODULE FILTERS IAW AMM 32-41-03. PERFORMED FUNCTIONAL TEST OF BRAKING SYS USING HYD SYS 1, 2 & 4 BRAKE PRESSURES 31OOPSI. PERFORMED CABLE RIGGING & TENSION CHECKS. BRAKING SYS CHECKED GOOD IAW AMM 32-41-00.
ALL RT BRAKES SHOW TEMP ZERO AFTER LANDING WITH AUTO BRAKES 2 SELECTED. ALL LT BRAKES ROSE TO TEMP 4. MANUAL BRAKES NORMAL. DEFERRED AUTO BRAKE SYS IAW MEL 32-42-03-01.
RIGHT WING RIB SUPPORT AT MID SPAR IN NR 3 MAIN TANK WING STA 1140, CRACKED. CRACK LENGTH APPROXIMATELY 4". R & R RIB SUPPORT NR 112U9200.
LEFT WING UPPER SKIN AT APPROXIMATE WING STA 975 HAS 1 FASTENER, RIVET HEAD SHEARED OFF. R & R RIVET.
RIGHT UPPER DECK EMER EXIT EMER OPENING SYS WILL NOT TEST. TROUBLE SHOT & FOUND DEFECTIVE POWER PACK TRANSFERRED TO DEFERRED MX ITEM IAW MEL 52-23-01.
UPPER DECK LT ESCAPE OVERHEAD EMERGENCY BATTERY PACK FOUND WEAK UNABLE TO HOLD CHARGE.
UPPER DECK RT ESCAPE DOOR OVERHEAD EMERGENCY EXIT LIGHT POWER SUPPLY, BATTERY PACK FOUND WEAK. UNABLE TO HOLD CHARGE.
RIGHT WING NR 3 RESERVE TANK UNIT F192 FOUND MOUNTING PLATE CRACKED. CRACK LENGTH 1 INCH. DISCREPANCY DISCOVERED DURING ACCOMPLISHMENT OF TASK CARD 28-041-04-06.
LEFT WING TE UPPER FIXED PANEL SUPPORT AT WING STATION 720 FOUND CRACKED. CRACK LENGTH 2.1 INCHES FOUND DURING ACCOMPLISHMENT OF TASK CARD 57-872-01-01.
DURING ACCOMPLISHMENT OF TASK CARD 53-864-01-01 FOUND BODY FAIRING SUPPORT FRAME BRACKET CORRODED AT BS 880 LT. REPLACED BRACKET.
DURING ACCOMPLISHMENT OF TASK CARD 58-866-01-01 FOUND BODY FAIRING SUPPORT FRAME BRACKET CORRODED AT BS 920 RT. REPLACED BRACKET.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1200, UPPER ROW 3RD FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1200, LOWER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1200, MIDDLE ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1120, UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01 FOUND BULK CARGO COMPARTMENT STATION 2020 BL0 FLOOR INTERCOSTAL CRACKED. CRACK LENGTH 2.3 INCHES.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1120, MIDDLE ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1120, LOWER ROW 12TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
BULK CARGO COMPARTMENT STATION 2000 LT OF BL 22.5 FLOOR INTERCOSTAL FOUND CRACKED. CRACK LENGTH .9 INCHES.
BULK CARGO COMPARTMENT STATION 2000, LT OF BL 7.5 FLOOR INTERCOSTAL FOUND CRACKED IN TWO PLACES. CRACK NR 1 LENGTH 1.05 INCHES & CRACK NR 2 LENGTH .6 INCHES FOUND DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01
BULK CARGO COMPARTMENT STATION 2000 BL 0 FLOOR INTERCOSTAL FOUND CRACKED IN TWO PLACES. CRACK NR 1 LENGTH 1.1 INCHES & CRACK NR 2 .8 INCHES. CRACK FOUND DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1120, LOWER ROW F FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01 FOUND BULK CARGO COMPARTMENT STATION 2040 LT OF BL 22.5 FLOOR INTERCOSTAL CRACKED. CRACK LENGTH .6 INCHES.
DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01 FOUND BULK CARGO COMPARTMENT STATION 2020 LT OF BL 7.5 FLOOR INTERCOSTAL CRACKED. CRACK LENGTH .5 INCHES.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1200, MIDDLE ROW 16TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1200, UPPER ROW 4TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01 FOUND BULK CARGO COMPARTMENT STATION 2020 LT OF BL 22.5 FLOOR INTERCOSTAL CRACKED. CRACK LENGTH 1.4 INCHES.
DURING ACCOMPLISHMENT OF TASK CARD 53-858-01-01 FOUND BULK CARGO COMPARTMENT STATION 2000 LBL 45 INTERCOSTAL CRACKED. CRACK LENGTH 1.2 INCHES.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1200, UPPER ROW 2ND FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1200, LOWER ROW 16TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE AT STATION 1140 UPPER ROW 4TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
DURING INSPECTION IAW TASK CARD 53-852-01-01 FOUND AFT CARGO DOORWAY CEILING PANEL SUPPORT AT STATION 1900 RT OF BL 84 CRACKED. CRACK LENGTH .7 INCHES.
DURING HFEC OPEN HOLE INSPECTION ON AFT CARGO DOOR CUT OUT UPPER FWD CORNER AT HINGE AREA LOWER HOLE NR 1 SKIN FOUND CRACKED. CRACK LENGTH 1 INCH. INSPECTION CARRIED OUT IAW AD 2003-10-06, SB 747-53A2448 REVISION 1 DATED 4/4/2002.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1160, MIDDLE ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1160 UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE & FRAME AT STATION 1160, UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1160, UPPER ROW 14TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE AT STATION 1160, UPPER ROW 2ND FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1160, UPPER ROW 4TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1140, UPPER ROW 4TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1140, LOWER ROW 14TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE AT STATION 1140 UPPER ROW FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1140 UPPER ROW 9TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE & FAIL SAFE CHORD AT STATION 1140 UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE STEEL PLATE AT STATION 1220, UPPER MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME CLIP AT STATION 1220, UPPER ROW 3RD FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FWD CHANNEL AT STATION 1220, UPPER ROW 3RD FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE STEEL PLATE AT STATION 1220, UPPER 3RD FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE FWD CHANNEL AT STATION 1220, UPPER ROW 8 8TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE FWD CHANNEL AT STATION 1220, UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE & FRAME AT STATION 1220, UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE LT TENSION TIE FAIL SAFE CHORD AT STATION 1220, UPPER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION OF RT TENSION TIE & FRAME AT STATION 1220 LOWEST ROW, SECOND FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1180 UPPER FIFTH FASTENER HOLE OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING OPEN HOLE INSPECTION ON RT TENSION TIE & FAIL SAFE CORD AT STATION 1180 UPPER MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE & FAIL SAFE CHORD AT STATION 1140 LOWER ROW, MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE AT STATION 1180 UPPER ROW 8TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE FORWARD CHANNEL AT STATION 1180 UPPER ROW 7TH FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON LT TENSION TIE & AFT CHANNEL AT STATION 1220 LOWER MOST ROW 5TH FASTENER HOLE FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1220, LOWEST ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FWD CHANNEL AT STATION 1220, LOWEST ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & STEEL PLATE AT STATION 1220, LOWEST ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
FASTENER HOLE FOUND ELONGATED DURING HFEC OPEN HOLE INSPECTION ON THE RT TENSION TIE & FRAME AT STATION 1220, UPPER 3RD FASTENER FROM OTBD. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON RT TENSION TIE & FRAME AT STATION 1180, LOWER ROW MOST OTBD FASTENER. INSPECTION CARRIED OUT IAW AD 2012-15-13, SB 747-53A2507R2.
DURING ACCOMPLISHMENT OF TASK CARD 33-050-01-01 FOUND UPPER DECK CABIN EMERGENCY LIGHTS FOUND TWO LAMPS INOPERATIVE.
ON POST FLIGHT FOUND NR 22 LE FLAP DAMAGED. FOUND ROTARY ACTUATOR PN 178800-109 FAILED CAUSING DAMAGE.
ON POST FLIGHT INSPECTION, FOUND CRACK ON NR 2 ENGINE EXHAUST INNER LINER AFT RING WELD AT 7 O'CLOCK POSITION.
ON POST FLIGHT INSPECTION, FOUND CRACK ON NR 4 ENGINE EXHAUST NOZZLE INNER LINER AFT RING WELD AT 1 O'CLOCK POSITION.
MAIN DECK CARGO FIRE ALARM ACTIVATED DURING CRUISE. CREW CHECKED AND NO INDICATION OF FIRE OBSERVED. TROUBLESHOT SYSTEM IAW FIM 26-16 AND FOUND DETECTORS 10, 11, 12, 14, 16 ON LOOP "B" FAILED.
LEFT OTBD AFT FLAP PANEL 588 EXTERNAL SKIN HAS SEVERAL AREAS OF WEAR OUT OF LIMITS. NO CORROSION OR CRACKS FOUND. REPAIRED IAW DWG 5750D1751, REV IR DTD.
LEFT UPPER DECK DOOR EMERGENCY OPENING SYSTEM DOES NOT TEST.
UPPER DECK EMERGENCY LIGHT OPS TEST FOUND FOUR BULBS INOPERATIVE.
LT WING L/E UPPER FIXED PANEL FOUND CRACKED BETWEEN WING STATIONS 730 TO 862. CRACK LENGTH 38" REF NRCMOL0209. GENERATED FROM TASK CARD 57-806-01-01.
LEFT WING LEADING EDGE CAVITY AT WING STATION 780 FOUND SUPPORT ROD FRACTURED, REF NRC MOL0217 GENERATED FROM TASK 57-804-01-01.
LEFT WING L/E CAVITY LOWER FIXED PANEL AT WS 850 FOUND STRUCTURE CRACKED. CRACK IS 1.5" IN LENGTH.
GEAR DISAGREE AND GEAR DOOR EICAS RT BODY GEAR UNSAFE INDICATION ON LANDING. ALTERNATE GEAR EXTENSION METHOD PERFORMED AND ALL LIGHTS GREEEN. FOUND MLG DOOR SEQUENCE VALVE CARRIER BOLT FALLEN OUT. NUT MISSING. REPLACED HARDWARE WITH NEW LOCKING NUT.
REJECTED TAKEOFF AT 80KTS - NR 3 ENG N1 ROLLED BACK.
AT APPROX 65KTS, NR 3 ENGINE FAILED. N1 WAS APPROX 100 PERCENT.
AT APPROX 65 KNOTS, NR 3 ENGINE FAILED. N1 WAS APPROX 100 PERCENT. COMPLETED FAULT ISOLATION IAW FIM 71-00, FIG 114. R & R NR 3 ENGINE ECU IAW AMM 73-21-15, ALSO R & R NR 3 ENGINE HMU IAW AMM 73-21-14. ALL OPS CHECK NORMAL IAW AMM 73-21-15 AND 73-21-14.
AT APPROX 65 KNOTS, NR 3 ENGINE FAILED. N1 WAS ABOVE 100 PERCENT. COMPLETED FAULT ISOLATION IAW FIM 71-00, FIG 114. R & R NR 3 ENGINE ECU IAW AMM 73-21-15, ALSO R & R NR 3 ENGINE HMU IAW AMM 73-21-14. ALL OPS CHECK NORMAL IAW AMM 73-21-15 AND 73-21-14.
AIR PORTION OF THE APU FAILED WITH APU ELECTRONICS OPERATIONAL. COMPLETED FIM 49-11 TASK 827 WITH NO FAULTS NOTED. STARTED APU, ALL OPS CHECKED GOOD.
INCORRECT REPAIR OF FUSEALAGE SKIN DAMAGE.
INCORRECT REPAIR, INCORRECT FASTENERS.
AFT FUSELAGE SKIN, BS 1795, S48L, MISREPAIRED
FLIGHT 5288 - ON TAKEOFF ROLL OBSERVED NO STANDBY INDICATION. TAKEOFF ABORTED. A/C FERRIED FROM YHZ TO CVG. PURGED WATER FROM STANDBY PITOT SYSTEM.
FLIGHT 5145 - EN ROUTE CVG-AVP A NUISANCE SQUEALING NOISE EMITTING FROM GALLEY AREA, FLIGHT RETURNED TO THE FIELD. REPLACED THE GALLEY DRAIN REDUCER.
FLIGHT 5802 - UPON FLAP RETRACTION DURING PRE-FLIGHT INSPECTION RECEIVED A FLAP FAIL CAUTION MESSAGE. COMPLIED WITH AD 98-20-01 FLAP CAUTION MESSAGE -FIRST EVENT- MAINTENANCE ACTION, PARAGRAPH (B) 1, 2, 3 (A, B, C AND E). FLAP SYSTEM WAS RESET WITH NO FURTHER FLAP CAUTION MESSAGES.
FLAPS FAIL CAUTION. REPAIRED BROKEN WIRE AT THE LT BPSU.
FLIGHT 5028 APU SHUTDOWN. COULD NOT DUPLICATE. APU OPERATIONAL CHECK SATISFACTORY.
1ST SEGMENT OF EMERGENCY FLOOR PATH LIGHTING IS INOPERATIVE. SECURED LOOSE CONNECTOR. SYSTEM OPERATION NORMAL.
RIGHT SIDE CABIN FLOOR SIL ASSY HAS CORROSION ON TOP SURFACE FROM FS 516 THRU 544. CLEANED CORRODED AREA BY BLENDING OUT CORROSION. CUT OUT AREA THAT WAS OUT OF LIMITS AND FABRICATED AND INSTALLED REPAIR PARTS. TREATED AND PAINTED ENTIRE WORK AEA IAW REO 601R-53-41-183.
WHILE PERFORMING TASK 002-57-900-60/601 FOUND CORROSION ON THE LOWER RT WING PLANK ACCESS HOLE CUTOUT (FOR PANEL 640BB) ON THE FORWAD AND AFT CHAMFERS. REMOVED THE CORROSION AND APPLIED SURFACE TREATMENT IAW REO 601R-57-21-030 REV C.
FS 484 LBL 36 INBOARD SUPPORT ANGLE/INTERCOSTAL CRACKED. REMOVED ANGLE, FABRICATED REPAIR ANGLE FROM 2024-T3.063 (WVAC PO 32572) AND INSTALLED IAW BOMBARDIER, INC. REO601R-53-41-059.
VERTICAL BEAM CRACKED AT BL 0 BULKHEAD WEB AT FS 409+128 TOP RIVET LOCATION ON REINFORCING PLATE. PERFORMED A MAJOR REPAIR TO CRACKED VERTICAL BEAM, FS 409+128 BL 0 (TOP RIVET ON REINFORCING PLATE) BY TRIMMING OUT CRACKED PORTION OF STIFFENER, FABBING FILLER AND REPAIR ANGLE, AND INSTALLING PER WVAC EO 601R-53-4572 AS APPROVED BY FAA FORM 8110-3 DATED 1-12-2004.
FLOORBEAM CAP AT FS 559+12 TO 620 AT LBL 27 CORRODED. REMOVED AND REPLACED CAP IAW WVAC EO 601R-53-4581.
FS 484 RBL 27, OUTBOARD SUPPORT ANGLE/INTERCOSTAL CRACKED. REMOVED ANGLE FABRICATED REPAIR ANGLE FROM 2024-T3.063 (WVAC PO 32572) AND INSTALLED IAW BOMBARDIER REO 601R-53-41-059.
FS 484 LBL 27 OUTBOARD SUPPORT ANGLE/INTERCOSTAL CRACKED. REMOVED ANGLE, FABRICATED REPAIR ANGLE FROM 2024-T3.063 (WVAC PO 32572) AND INSTALLED IAW BOMBARDIER, INC REO 601R-53-41-059.
FS 484 RBL 36 INBOARD SUPPORT ANGLE/INTERCOSTAL CRACKED. REMOVED ANGLE, FABRICATED REPAIR ANGLE FROM 2024-T3.063 (WVAC PO 32572) AND INSTALLED IAW BOMBARDIER, INC REO 601R-53-41-059.
LEFT WING LOWER WING PLANK SKIN AT WS 148.00 IS CRACKED. REMOVED DAMAGE, FABRICATED REPAIR DOUBLERS FROM 2024-T3.125 (WVAC PO 21137) AND FILLER FROM 2024-T3.100 (WVAC PO 27013), INSTALLED IAW BOMBARDIER, INC REO 601R-57-21-120 REV D.
FS 310 FUSELAGE SKIN PREVIOUS BETYWEEN STRINGERS 16 AND 17 HAS SUSTAINED FURTHER DAMAGE. REMOVED DAMAGE, FABRICATED REPAIR DOUBLER FROM 2024-T3.063 (WVAC PO 32512) AND 2024-T3.050 (WVAC PO 29669/1), INSTALLED IAW BOMBARDIER, INC REO 601R-53-21-180.
FS 235 RBL 6 NLG AFT DOOR CUT OUT HAS A .25 INCH CRACK ON FUSELAGE SKIN. REMOVED DAMAGE, FABRICATED REPAIR ANGLE FROM 2024-T42.063 (WVAC PO 169562), FILLER FROM 2024-T3.050 (WVAC PO 32674), FILLER AND DOUBLER FROM 2024-T3 .063 (WVAC PO 32572) AND INSTALLED IAW BOMBARDIER, INC REO 601R-53-11-048 REV B.
FLIGHT 5874 LEFT 14TH STAGE BLEED LEAK WARNING. REPLACED THE LEFT PYLON BLEED LEAK SENSING ELEMENT.
FLIGHT 5868 RT ENGINE STARTER ENGAGED DURING FLIGHT 3 TIMES. REPLACED THE AIR START VALVE.
LANDING GEAR DISAGREE WARNING; NLG DID NOT RETRACT. ADJUSTED THE NLG CENTERED PROXIMITY SENSOR TARGET.
FLIGHT 5751 CABIN DOOR WARNING.COULD NOT DUPLICATE. REPLACED INNER HANDLE ROD END ROLLER.
FLIGHT 5156 GEAR DISAGREE WARNING.TIGHTENED LOOSE TARGET ONTHE L/H MLG UPLOCK.
FLIGHT 5850 DURING T/O A LARGE AMOUNT OF FLUID DRAINED FROM THE LIGHT CONTROL PANEL.RESEALED THE CREW DITCHING HATCH.
FLIGHT 5103 CABIN DOOR WARNING DURING FLIGHT.ADJUSTED CABIN DOOR LATCH MECHANISM.
FLIGHT 5478 CABIN DOOR WARNING MESSAGE.RIGGED/ADJUSTED THE CABIN DORO LATCHING MECHANISM TO M/M SPECIFICATIONS.
FLIGHT 5465 CABIN DOOR LATCH CAUTION MESSAGE.REPLACED THE INNER HANDLE LATCH ROLLER.
FLIGHT 5863 CABIN DOOR WARNING.REPLACED PROXIMITY SWITCH 546.
FLIGHT 5459 CABIN ALTITUDE CAUTION MESSAGE - CABIN WOULD NOT PRESSURIZE.REPLACED BROKEN ROD ON CABIN DOOR VENT VALVE.
FLIGHT 5494 NOSE GEAR DISAGREE WARNING. NLG UNSAFE INDICATION.INSPECTED NLG AND PERFORMED EXT AND RETRACTION CHECKS. NO FAULTS FOUND.
FLIGHT 5877 LEFT ENGINE IGNITION STATUS MESSAGE.REPALCED THE ENGINE IGNITERS.
FLIGHT 6066 AILERON CONFIG WARNING DURING T/O.COULD NOT DUPLICATE. INSPECTED AILERON SYSTEM - NO ABNORMALTY FOUND.
DURING REMOVAL OF THE RIGHT ENGINE ASSEMBLY, DISCOVERED FRETTING/PITTING CORROSION ON THE AFT ENGINE PYLON THRUST FITTING MOUNTING VIB.REPAIRED IN ACCORDANCE WITH REO 601R-54-50-036.
THE R/H VERTICAL STABILIZER BUSHING WAS SCORED AT HORIZONTAL STABILIZER PIVOT POINT.REMOVED THE SCORED BUSHING. MACHINED FLANGE OF NEW BUSHING P/N 600-21061-7S/B I/A/W WVAC EO 601R-55-2952.INSTALLED THE NEW BUSHING I/A/W CRJ AMM 20-26-00-910-803. REAMED THE BUSHING TO TOLERANCE I/A/W DRG 600-21029.
FLIGHT #5843. COPILOTS STABILIZER TRIM IS INTERMITTENT.REPLACED THE COPILOTS TRIM SWITCH.
FLIGHT #5420. DURING TAKE OFF AT CVG AIRCRAFT ENCOUNTERED MULTIPLE BIRD STRIKES ON RADOME, TAKE OFF WAS ABORTED AND RETURNED TO THE GATE.PERFORMED BIRD STRIKE AND HIGH ENERGY STOP INSPECTION, NO DEFECTS NOTES.
RT LOWER WING PLANK CRACKED AT 2 LOCATIONS: 640 DB WS 95.950 AND 640 FB WS 136.676. BLENDED OUT DAMAGED AREAS AND ROTO-PEENED IAW REO 601R-57-21-030.
DURING CLIMB-OUT OF CVG, THE NR 1 AND 3 HYDRAULIC LOW PRESSURE CAUTION MESSAGES ACTIVATED, AIRCRAFT RETURNED TO THE FIELD. REPLACED THE FLAP POSITION HARNESS.
PAX DOOR LEAKS DURING PRESURIZATION. RECONTOURED ADHESIVE FILLER AT PREVIOUS REPAIR ON PAX DOOR SEAL STRIKER FS 349 IAW REO 601R-52-11-008 REV B.
STALL FAIL MESSAGE DURING TAKEOFF. RESET THE STALL COMPUTER.
CONFIG AILERON WARNING MESSAGE DURING T/O. RESET SECU, COULD NOT DUPLICATE. RESET SECU NR 1 AND 2.
GEAR DISAGREE WARNING. WOW CAUTION MESSAGE. FOUND NLG SHOCK STRUT IMPROPERLY SERVICED. SERVICED STRUT IAW M/M.
THE FORWARD J-ANGLE AT FS 280 BETWEEN LBL 9.0 AND RBL 9.0 IS CORRODED. PERFORMED A MAJOR REPAIR BY REPLACING CORRODED FORWARD J-ANGLE AT FS 280 BETWEEN LBL 9.0 AND RBL 9.0 IAW WVAC EO 601R-53-1489.
THE DOUBLER (P/N 601R38669-49) FORWARD OF THE SERVICE DOOR IS CORRODED. PERFORMED A MAJOR REPAIR BY REPLACING CORRODED DOUBLER (P/N 601R38669-49) FORWARD OF THE SERVICE DOOR IAW WVAC EO 601R-53-1504.
TRANSVERSE BEAM AT FS 349 CORRODED BETWEEN LBL 9 AND LBL 27. REPAIRED TRANSVERSE BEAM AT FS 349 IAW WVAC EO 601R-53-1491A.
A/P TRIM CAUTION MESSAGE. LITTLE TO NO CONTROL OF AILERONS. ELEVATORS ALSO EXTREMELY DIFFICULT TO MOVE. COULD NOT DUPLICATE. INSPECTED ALL FLIGHT CONTROLS AND CABLE RUNS. COMPLIED WITH FUNCTIONAL AND OPERATIONAL TEST OF AILERONS AND ELEVATORS. NO DEFECTS FOUND. AIRCRAFT RELEASED FOR FLIGHT CHECK.
EMERGENCY FLOOR PATH LIGHTING AT ROW 8 IS INOPERABLE. REPLACED POWER LEAD.
CABIN DOOR LATCH CAUTION MESSAGE. ADJUSTED CABIN DOOR LATCH MECHANISM.
STALL FAIL CAUTION MESSAGE. RESET STALL COMPUTER, SYSTEM TEST NORMAL.
LOWER HORIZONTAL SURFACE OF RIGHT LOWER WING ACCESS HOLE AT 640DB CRACKED. BLENDED OUT DAMAGE, ROTO-PEENED, AND ALODINED IAW REO 601R-57-21-030.
FS 718 RH5 AFT DOUBLER IS CRACKED BETWEEN STR 11-12. REPLACED CRACKED DOUBLER AT FS 718 RHS BETWEEN STR 11 AND 12 WITH NEW DOUBLERS IAW CRJ REO 601R-53-61-193.
EMERGENCY LIGHTS ROW 9 THROUGH 12 ARE INOPERABLE. SECURED LOOSE ELECTRICAL CONNECTOR.
FORWARD SECTION OF EMERGENCY FLOOR LIGHTING INOP. REPLACED LIGHT STRIP.
LOUD NOISE IMMEDIATELY AFTER TAKEOFF. 02 SERVICE DOOR OPEN. CLOSED 02 SERVICE DOOR.
CABIN DOOR WARNING AFTER TAKEOFF. REPLACED OUTER HANDLE LATCH SPRING.
EMERGENCY LIGHTS ARE INOPERABLE AT ROWS 7 AND 12. REPLACED LIGHT BULBS.
EMERGENCY BATTERY IN FORWARD AVIONICS BAY IS CRACKED AT MOUNTING LUGS. REPLACED EMERGENCY BATTERY.
C-CHECK TASK 002-27-160-100, LEFT HAND FLAP, NR 1 FLEXSHAFT DRIVE IS UNSERVICEABLE DUE TO STRAND SEPARATION AND BROKEN HOUSING. REPLACED FLEXSHAFT ASSY.
C-CHECK TASK 002-71-430-104, LEFT HAND THRUST REVERSER BALL SCREW ACTUATOR, 5 O'CLOCK POSITION, FORK END BROKEN. REPLACED ACTUATOR.
C-CHECK TASK 002-71-430-104, LEFT HAND THRUST REVERSER BALLSCREW ACTUATOR, 7 O'CLOCK POSITON, FORK END BROKEN. REPLACED ACTUATOR.
C-CHECK TASK 002-78-440-101, RIGHT HAND THRUST REVERSER BALL SCREW ACTUATOR, 7 O'CLOCK POSITION, FORK END BROKEN. REPLACED ACTUATOR.
GEAR DISAGREE WARNING WHEN LANDING GEAR SELECTED UP. TIGHTENED LOOSE UPLOCK PROXIMITY SENSOR TARGET AT RIGHT HAND MLG.
FUEL IMBALANCE MESSAGE DURING FLIGHT. REPLACED THE FUEL COMPUTER.
PROX SYSTEM FAULT MESSAGE, LANDING GEAR UNSAFE INDICATION. REPLACED THE PROX SYSTEM ELECTRONIC UNIT.
TWO CABIN OVERHEAD EMERGENCY LIGHTS INOP. REPLACED LIGHT BULBS.
HYDRAULIC PUMP 1B WORKS NORMALLY ON GROUND BUT IS INOP WHEN AIRBORNE. HYDRAULIC PUMP 1B WAS INOP BECAUSE OF THE NR 2 IDG BEING DEFERRED. NO DEFECT WITH HYDRAULIC SYSTEM.
FLAPS FAIL MESSAGE ON EICAS. REPLACED THE LT AND RT FLAP BRAKE AND POSITION SENSOR UNITS.
LEVEL 5 THUNDERSTORM DID NOT SHOW ON RADAR AT 45 MILES. REPLACED RADAR ANTENNA.
NR 1 AHRS INDICATES A 19 DEGREE PITCH WITH AIRCRAFT LEVEL ON GROUND. REPLACED THE NR 1 AHRS.
PASSENGER DOOR FRAME AFT SEAL STRIKE, ON FUSELAGE, DAMAGED IN TWO PLACES AT THE BOTTOM BY THE LOWER LATCH PIN AND AT THE TOP BY THE PULL-IN LEVER ROLLER. BOTH AREAS REPAIRED PER CANADAIR REO 601R-52-11-008, REPAIR B, PERMANENT REPAIR.
AFTER TAKEOFF, PITOT BASE HEAT YELLOW MESSAGE CAME ON. RETURNED TO CVG BECAUSE OF ICE CONDITIONS. REPLACED AIR DATA SENSOR CONTROLLER, OPS CHECK GOOD.
FLOOR EMERGENCY LIGHTING IS INOP BETWEEN ROWS 2 AND 5. REPAIRED WIRING CONNECTIONS AT STRIP LIGHTING.
RT MLG DISAGREEMENT MESSAGE WHEN LANDING GEAR RETRACTED. REPLACED LOOSE PROXIMITY SENSOR TARGET ON THE RT MLG UPLOCK ASSY.
FLAPS FAILED AT 18 DEGREES WHEN SELECTED FOR APPROACH. REPLACED THE RT FLAP BRAKE AND POSITION SENSOR UNIT.
STABILIZER TRIM CHANNEL 1 INOPERATIVE MESSAGE ON EICAS. REPLACED THE HORIZONTAL STABILIZER TRIM ACTUATOR.
WOW OUTPUT AND WOW INPUT CAUTION MESSAGE ON EICAS. REPLACED THE PROXIMITY SENSOR ELECTRONIC UNIT.
FLAPS FAILED DURING TAKEOFF ROTATION. REPLACED THE LT AND RT FLAP BRAKE AND POSITION UNITS.
FLAPS FAIL MESSAGE ON EICAS. ZERO FLAP LANDING AT MDT. REPLACED THE FLAP ELECTRONIC CONTROL UNIT.