N526UP
Registered owner: COWLISHAW BRENDA L, TX (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
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
132 reports on file, 2001-03-03 – 2007-12-24.
Part: FRAME — CRACKED (FUSELAGE) · airframe 92,930 hrs · 17,404 cycles
DURING B-CHECK INSPECTION, RIGHT FRAME AT STATION 2674.85 WAS FOUND CRACKED AT WL 325. REMOVED DAMAGE SECTION OF FRAME, FABRICATED AND INSTALLED REPAIR DOUBLERS IAW 747 SRM 51-40-03 FIG 2.
Part: BULKHEAD — CHAFED (NR 1 PYLON) · airframe 92,930 hrs · 17,404 cycles
DURING B-CHECK WHILE ACCOMPLISHING AD 2007-19-19, NR 1 PYLON STRUT FORWARD ENGINE MOUNT BULKHEAD CORD WAS FOUND WITH CHAFED RADIUS AT LOWER INBOARD END. FABRICATED AND INSTALLED REPAIR ANGLE IAW BOEING SKETCH SR1-733824930-1. THIS REPAIR IS TEMPORARY AND REQUIRES A REPEAT DETAILED VISUAL INSPECTION EVERY 30 DAYS OR 60 CYCLES, WHICH EVER OCCURS FIRST. PERMANENT REPAIR MUST BE ACCOMPLISHED BY APRIL 30TH 2008, WITH REPLACEMENT OF BULKHEAD CORD.
Part: SENSOR — NO TEST (AOA) · airframe 92,913 hrs · 17,397 cycles
DURING TAKEOFF, AT 80 KNOTS, CREW RECEIVED A STALL WARNING, TAKEOFF WAS ABORTED. AOA FAILED TEST IAW B747 MM 27-32-00 PG 507. REPLACED AOA SENSOR IAW 747 MM 27-32-01 PG 102. SYSTEM TEST GOOD IAW 747 MM 27-32-00 PG 507. AIRCRAFT RELEASED FOR SERVICE.
Part: TRANSMITTER — MALFUNCTIONED (T/E FLAP) · airframe 91,234 hrs · 17,135 cycles
ON APPROACH TO ANC, OUTBOARD TRAILING EDGE FLAP HAD AN ASYMMETRICAL TRIP AND NR 2 LT LEADING EDGE FLAP DID NOT EXTEND. CONTINUED APPROACH AND MADE A SAFE LANDING. REPLACED FLAP POSITION TRANSMITTER IAW MM 27-58-01 PAGE 401, SYSTEM CHECKED NORMAL AND LEADING EDGE FLAPS OPERATED PROPERLY. AIRCRAFT RELEASED TO SERVICE.
Part: UNKNOWN — SPARKS (AILERON) · airframe 91,018 hrs · 17,103 cycles
ON TAXI OUT, DURING FLIGHT CONTROL CHECK, CREW IN AIRCRAFT FOLLOWING BEHIND REPORTED SPARKS COMING FROM RT AILERONS, RETURNED TO BLOCKS. RAN NR 3 AND NR 4 ENGINES IAW 71-00-00, ACCOMPLISHED OPERATION CHECK OF GENERATORS IAW 24-21-01 PG 601. OPENING AND CLOSING FIELD WHILE VISUALLY CHECKING, NO DEFECTS NOTED. ACCOMPLISHED INSPECTION OF NR 3 AND NR 4 ENGINE INLET, TUBES, HOSES, ELECTRICAL LEADS AND REAR TURBINE THROUGH TAIL PIPE, NO DEFECTS NOTED. PERFORMED OPERATIONAL TEST OF AILERONS IAW 27-11-00 PG 501, SYSTEM CHECKS GOOD, NO DEFECTS NOTED. AIRCRAFT RELEASED TO SERVICE.
Part: SKIN — DAMAGED (BS 765-775) · airframe 90,844 hrs · 17,075 cycles
DURING -B- CHECK, OUT OF LIMIT LIGHTNING STRIKE DAMAGE WAS FOUND BETWEEN BS 765 & 775 AT LBL 4.5. DRILLED OUT DAMAGE IAW SRM 53-30-03 FIG 3A AND INSTALLED RIVETS IAW SRM 51-30-02. THIS IS A CATEGORY-C REPAIR AND REQUIRES INSPECTION AT 1,000 CYCLES.
Part: CONNECTOR — DIRTY (BRAKE VALVE) · airframe 90,145 hrs · 16,966 cycles
TAKEOFF WARNING HORN CAME ON AT BRAKE RELEASE. TROUBLESHOOT PER FIM 31-26-00 PG 109, FOUND TAKEOFF WARNING CIRCUITS OPERABLE. DURING TROUBLESHOOTING, FOUND PARKING BRAKE LIGHT NOT ILLUMINATING, CLEANED AND RESEATED PARKING BRAKE VALVE CONNECTOR. PERFORMED AURAL TAKEOFF WARNING SYSTEM OPERATION TEST PER 747 MM 31-26-00 PAGE 502, OPS CHECKED NORMAL. AIRCRAFT RELEASED FOR SERVICE.
Part: SKIN — GOUGED (BS 560 S37-38R) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, 2 GOUGES IN SKIN WERE FOUND OUT OF LIMITS AT FUSELAGE STA 560 BETWEEN STR 37R AND STR 38R. BLENDED OUT DAMAGE AREA OF OUTER SKIN IAW EA 01-07013.
Part: SKIN — GOUGED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND EXTERNAL FUSELAGE SKIN GOUGED AT STA 2576 BETWEEN STR 42R AND 46R. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR IAW SRM 53-30-03 FIG 28.
Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, A CRACK WAS FOUND ON WEB AND DOUBLER ON R-1 DOOR EDGE FRAME AT STA 488 BETWEEN STR 25 AND 26 USING HFEC. REMOVED DOUBLER AND DAMAGED SECTION OF WEB, FABRICATED AND INSTALLED REPAIR PARTS IAW SRM 53-10-04 FIG 92.
Part: BALL SCREW — FAILED (HORIZ STAB) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, HORIZONTAL STABILIZER BALL SCREW AND BALL NUT FAILED FREE PLAY CHECK. REMOVED STABILIZER DRIVE MECHANISM, CHECKED WEAR OF PINS AND FITTINGS, FOUND IN TOLERANCE IAW 747 MM 27-41-06. REINSTALLED DRIVE MECHANISM PER 747 MM 27-41-06 AND PERFORMED BALL NUT TO BALL SCREW FEE PLAY TEST IAW SB 747 27A2396, FOUND FREE PLAY LESS THAN 0.012, WITH-IN LIMITS, ACCOMPLISHED LUBRICATION OF BALL NUT AND JACKSCREW IAW 747 MM 12-21-19 AND S/B 747-272396
Part: MOUNT — CRACKED (NR 4 ENGINE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, WHILE ACCOMPLISHING ULTRASONIC INSPECTION OF NR 4 STRUT REAR ENGINE MOUNT THRUST LINKIAW 747 MM 71-21-03, THE FORWARD BORE HAD A CRACK INDICATION AT O/B LUG BORE EDGE.
Part: RIB — CRACKED (NR 4 FUEL TANK) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, THE LOWER RIB CORD OF NR 4 FUEL TANK ACCESS PANEL 652AB, WS 972 WAS FOUND CRACKED FROM RADIUS BLOCK TO RADIUS BLOCK. REMOVED LOWER RIB CORD IAW SRM 51-30-00, FABRICATED NEW RIB CORD IAW DRAWING 65B01073 AND INSTALLED RIB CORD IAW SRM 51-30-02.
Part: BULKHEAD — DENTED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, A SMALL DENT WAS FOUND IN THE AFT PRESSURE BULKHEAD AT STA 2360 APPROX WL 200, LBL 30. REMOVED DAMAGED SECTION OF BULKHEAD WEB, FABRICATED AND INSTALLED REPAIR PARTS IAW SRM 53-10-04 FIG 9, SRM 51-10-01 AND AMM 51-21-00.
Part: SKIN — DAMAGED (NR 3 PYLON) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, THE O/B SKIN OF NR 3 PYLON WAS FOUND DAMAGED AT APPROX STA 221.9 JUST BELOW MID SPAN. REMOVED DAMAGE IAW SRM 54034-03, FABRICATED AND INSTALLED REPAIR PARTS IAW SRM 54-34-03 FIG 25, SRM 51-10-02 AND SOPM 20-42-02.
Part: SKIN — DAMAGED (NR 3 NACELLE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, NR 3 PYLON INBOARD SKIN DOUBLER WAS FOUND WORN UNDER FORESHIELD NEAR NAC STA 221. FABRICATED AND INSTALLED REPAIR PARTS IAW EA 01-07019.
Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND A 1 INCH CRACK IN SHEAR WEB, BETWEEN S-10A AND S-10 RIGHT SIDE BS 820, WL 332, RBL 80. REPLACED SHEAR WEB IAW B747 SRM 51-30-02 AND DRAWING 65B09661.
Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND A 1 INCH CRACK IN SHEAR WEB BETWEEN S-10A AND S10 LEFT SIDE BS 820, WL 330, LBL 80. REPLACED SHEAR WEB IAW B747 SRM 51-30-02 AND DRAWING 65B9661.
Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND FLOOR ATTACH ANGLE FOR L-1 DOOR FRAME CRACKED, STA 441. REPLACED ANGLE PER 747 SRM 51-30-02
Part: ANGLE — DAMAGED (NR 1 PYLON) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, HFEC INSPECTION, NR 1 PYLON BULKHEAD, STA 221 FORWARD SIDE, INBOARD ANGLE MISSING PIECE AT UPPER HORIZONTAL FLANGE. FABRICATED AND INSTALLED DOUBLER'S IAW SRM 54-14-03 FIG 13 AND EA 01-07016.
Part: SKIN — DENTED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FUSELAGE SKIN WAS FOUND DENTED AT STA 228 STR 17L. CUT OUT DAMAGE IAW SRM 53-30-03 FIG 1, FABRICATED REPAIR IAW SRM 53-30-03 FIG 1 AND INSTALLED PER SRM 53-30-01 FIG 1.
Part: SKIN — GOUGED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FUSELAGE SKIN WAS FOUND GOUGED AT STA 665 BETWEEN STR 40R AND 41R. REMOVED GOUGE IAW SRM 53-30-01 DETAIL II AND INSTALLED REPAIR DOUBLE IAW SRM 53-30-03 FIG 1.
Part: SEAT TRACK — CRACKED (COCKPIT) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FIRST OFFICERS AFT INBOARD SEAT TRACK WAS FOUND CRACKED, VERIFIED WITH HFEC. REPLACED SEAT TRACK IAW B747 MM 20-51-1
Part: SKIN — DAMAGED (BS 1770-1850) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, EXTERNAL FUSELAGE SKIN WAS FOUND CREASED FROM STA 1770 TO STA 1850 & 41L TO 46L. REPLACED SKIN SECTION IAW SRM 53-30-03 FIG 19 AND EA 01-07014.
Part: FUEL TANK — CORRODED (BS 1265) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, CORROSION WAS FOUND AT LOWER CENTER TANK SKIN AT STA 1265 LBL 117. REPAIRED IAW SRM 57-30-01 AND EA 01-07018.
Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING 'C' CHECK, CAPTAINS AFT INBD SEAT TRACK WAS FOUND CRACKED, CRACKED VERIFIED WITH HFEC. REPLACED CAPTAINS AFT INBD SEAT TRACK IAW 747 MM 20-51-1.
Part: SKIN — BULGED (BS 2348 S51R) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FUSELAGE SKIN WAS FOUND BULGED AT STA 2348 AT STRINGER 51R. REPAIRED STRINGER, FAILSAFE STRAP, SHEAR TIE, FRAME WEB AND FRAME IAW SRM, 53-10-02, 53-10-03 FIG 1, 51-40-04, MM 51-21-00, KM DRAWING 531007003-1 AND EA 01-07017.
Part: SKIN — DENTED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND 3 DENTS IN FUSELAGE SKIN AT STA 265 BETWEEN STR 10A L AND 11L. REMOVED DAMAGED, FABRICATED AND INSTALLED REPAIR PARTS IAW SRM 53-30-03 FIG 1. THIS IS A CATEGORY -C- REPAIR AND WILL REQUIRE RE-INSPECTION AT 1,000 HOUR INTERVALS, LIFE LIMIT IS 6,000 HOURS IAW SRM 53-30-03 FIG 1 SHEET 14 TABLE V.
Part: ATTACH FITTING — BROKEN (NR 5 SPOILER) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND NR 5 SPOILER CENTER ATTACH FITTING BROKEN AFT OF WS 680 IN FLAP WELL.
Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, FOUND FUSELAGE STRINGER CLIP CRACKED AT STA 1540, STR 23R.
Part: SKIN — DENTED (CARGO DOOR) · airframe 89,777 hrs · 16,916 cycles
DURING C-CHECK, A DENT WAS FOUND IN BULK CARGO DOOR EXTERNAL SKIN AT STA 2012 BETWEEN STR 31R AND 33R. CUT OUT DAMAGED AREA IAW SRM 52-00-03 FIG 1. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 51-10-02, SRM 52-00-03 FIG 1, 2 & 3 AND MM 51-24-01.
Part: STRUCTURE — WORN (NR 4 PYLON) · airframe 89,777 hrs · 16,916 cycles
DURING B-CHECK, FOUND NR 4 PYLON BULKHEAD STA 221.9 WORN FROM CONTACT WITH HYDRAULIC LINE AT INSIDE TOP AFT PIGEON HOLE. REPAIRED IAW BOEING 747 SRM 54-14-03 FIG 16.
Part: FRAME — CRACKED (NR 1 PYLON) · airframe 89,777 hrs · 16,916 cycles
DURING B-CHECK, FOUND NR 1 PYLON FRAME STA 250 CRACKED AT INSIDE BOTTOM AFT PIGEON HOLE. REPAIRED IAW BOEING 747 SRM 54-14-03 FIG 1.
Earlier reports · 2001–2006 · 99 reports
2006
Part: ENGINE — UNSERVICEABLE (NR 3) · airframe 89,568 hrs · 16,850 cycles
DURING CLIMB-OUT OF MIA AT APPROX 18,000 FEET, THERE WAS A LOUD BANG FROM NR 3 ENGINE WITH A SPIKE IN EGT TO 780C AND FLUCTUATING EPR. ENGINE WAS SHUT DOWN, 19,000 POUNDS OF FUEL WERE DUMPED AND AIRCRAFT RETURNED TO MIA AND MADE A SAFE LANDING. VISUAL INSPECTION REVEALED EXTENSIVE DAMAGE TO LPT. ENGINE REPLACED PER TWM B747-71-004 WORK CARD AND PERFORMED ENGINE RUN UP PER TWM B747-71-005A WORK CARD. AIRCRAFT RETURNED TO SERVICE.
2005
Part: STRINGER CLIP — CRACKED (BS 2060) · airframe 86,711 hrs · 16,361 cycles
BULK CARGO BS 2060 STR 28L FOUND 1EA TIE CLIP CRACKED, CRACK LENGTH 3/8". TIE CLIP REPLACED AS PER SRM 51-10-01 PG 9.
Part: FITTING — CRACKED (RT WING) · airframe 86,711 hrs · 16,361 cycles
BS 1241 REAR SPAR CRACK INDICATION REVEALED AT UPPER SPLICE FITTING LOWER SURFACE AT NR 6 HOLE. CRACK LENGTH 0.060". RT NR 6 BOLT HOLE BUSHING REPAIRED AS PER EO NR B747-5740-17032.
Part: FITTING — CRACKED (RT WING) · airframe 86,711 hrs · 16,361 cycles
RT BS 1241 WING UPPER REAR SPAR SIDE-OF-BODY KICK FITTING AREA FOUND HOLE NR 2 CRACKED AT KICK FITTING APPROX 0.060". RH NR 2 BOLT HOLE BUSHING REPAIRED AS PER EO NR B747-5740-17032.
Part: FITTING — CORRODED (LT WING) · airframe 86,711 hrs · 16,361 cycles
LT WING UPPER REAR SPAR SIDE OF BODY SPLICE NR 6 FASTENER HOLE FOUND CORROSION AT UPPER SPLICE FITTING APPROX 0.030" IN LENGTH RUNNING FORWARD O/B, CORROSION BLEND OUT 0.030" IN LENGTH. LEFT NR 6 BOLT HOLE BUSHING REPAIRED AS PER EO NR B747-5740-17032.
Part: BULKHEAD — CORRODED (RT MLG WW) · airframe 86,711 hrs · 16,361 cycles
INSPECTION TYPE:C L/G - RBLG W/W STA 1480 BULKHEAD FWD FACE FOUND SURFACE CORROSION AROUND L/G RETRACT ACTUATOR UPPER MOUNT AREA. BS 1480 BULKHEAD CORRODED. TIME LIMITED REPAIR AT RBL 85 WL 156 AREA AS PER H HX RS R53-43-35364 AND UPS EO B747-5310-22826-A. BOEING RECOMMEND PERFORMING THE CPC TASK C53-125-01 MORE FREQUENTLY TO REDUCE CORROSION TO LEVEL 1. BOEING WILL PROVIDE THE STATUS IN 12 MONTHS AFTER COMPLETION OF THE DAMAGE TOLERANCE ANALYSIS.
Part: FRAME — CORRODED (BS 880) · airframe 86,711 hrs · 16,361 cycles
FX FRONT BODY FAIRING SUPPORT UPPER SURFACE FOUND SURFACE CORROSION AT STA 880 RBL 0 TO RBL 1". CORROSION BLEND OUT 0.080" BY 1" BY 1" EXCEED SRM 53-50-01 FIG 5 LIMITS, FRAME WEB REPAIRED AT BS 880 BL 0" TO RBL 1" FWD SIDE AREA AS PER SRM 53-50-04 FIG 1.
Part: SKIN — DENTED (BS 1980-2000) · airframe 86,711 hrs · 16,361 cycles
INSPECTION TYPE:C FX LT LOWER FUSELAGE EXTERNAL SKIN SURFACE SUSPECT DENT MARK AT STA 1980 TO STA 2000 STR 43L TO STR 44L. FX BS 1986 TO BS 1998.5 BETWEEN STR 43L TO STR 44L SKIN REPAIRED AS PER SRM 53-30-03 FIG 1 SUBSEQUENT INSPECTIONS ARE NECESSARY FOR CAT B REPAIR REFER TO SRM 53-30-03 FIG 1 TABLE IV FOR INSP REQUIREMENTS.
Part: STIFFENER — CRACKED (BS 1460) · airframe 86,711 hrs · 16,361 cycles
LT KEEL BEAM VERTICAL WEB SURFACE EXTERNAL ATT STIFFENER FOUND CRACKED AT STA 1460 LBL 9, CRACK LENGTH .625. STIFFENER REPLACED AS PER SRM 51-10-01 PG 9.
Part: BEAR STRAP — CORRODED (BS 545) · airframe 86,711 hrs · 16,361 cycles
INSPECTION TYPE:C FX LOWER FUSELAGE EXTERNAL SKIN SURFACE FWD LAVATORY SERVICE PAN FWD ATT PLATE FOUND CORRODED AT LT STA 545 STR 46L TO STR 47L. CORROSION BLEND OUT THROUGH WHOLE THICKNESS .5 X 1 INCH. FX BS 540 BETWEEN STR 46L TO STR 47L LAV SVC PAN ATTACHED BEAM STRAP REPAIRED AS PER HX RS R-53-21-35363 & ENGINEERING FILE NUMBER : 747-53-20283. FOLLOW THE INSP INTERVAL AS PER SRM 53-30-03 FIG 1 TABLE IV USING EXTERNAL LFEC INSP METHOD.
Part: SKIN — DENTED (ESCAPE HATCH)
INSPECTION TYPE:N/A SEVERAL DENTS IN CREW EMERGENCY ESCAPE HATCH OUTER SKIN S/M. DOOR REMOVED FOR REPAIR S/M SHOP. FABRICATED NEW SKIN IAW 52-20-01 OK TO INSTALL INNER AND OUTER SKIN. INSTALLED OUTER SKIN PER SRM 51-36-02. FINISHED INSTALLATION OF INNER SKIN PER SRM 51-40-02. REF LP 4440326.
Part: CONNECTOR — DIRTY (FIRE DETECT SYS)
NR 4 ENG A- LOOP DISPLAYED INTERMITTENT FAULT LIGHTS AND BELL TEMPERATURE WAS IN RED BANK BUT FLUCTUATED SOMEWHAT. PERFORMED PRECAUTIONARY ENGINE SHUT DOWN PROCEDURE. TEMP STAYED IN HIGH ORANGE TO RED BAND. FOUND LOWER RIGHT A- LOOP CONNECTORS SOAKED WITH OIL. CLEANED CONNECTORS AND TEMP BANK RETURNED TO NORMAL. TESTED PER MM 26-11-00 TEST GOOD.
Part: BATTERY — INOPERATIVE (FLASHLIGHT)
EMERGENCY FLASHLIGHT INOP. REMOVED AND REPLACED EMERGENCY FLASHLIGHT BATTERY, OPS CK GOOD AT THIS TIME.
2004
Part: SKIN — DAMAGED (CARGO DOOR)
LOWER FWD CARGO DOOR HAS DAMAGE TO SKIN ON LOWER AFT CORNER OF DOOR. INSTALLED TEMPORARY REPAIR DOUBLER. REPAIR HAS A ONE YEAR LIMIT. FWD ITEM TO DMI LOG D286216.
Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT)
EMERGENCY LIGHT INOPERATIVE UPPER DECK R-1 DOOR REPLACE BATTERY PACK IAW MM 33-51-00.
Part: LIGHT — INOPERATIVE (SERVICE DOOR)
UPPER DECK SERVICE DOOR FRAME EMERGENCY LIGHTS 2EA INOP. PANEL OPENED FOR ACCESS TO BATTERY PACK. APPLIED POWER TO A/C & ALLOWED EMERGENCY LIGHTS TO CHARGE SEVERAL HOURS. UPPER DECK DOOR LTS OPERATED NORMAL PER B747 MM 33-51-04 INSTALLED & SECURED PANEL.
Part: LIGHT — MALFUNCTIONED (EMERGENCY EXIT)
EMERGENCY EXIT LIGHT AT POS 500 ON MCD HAS ONE LAMP INOP. REPLACED LAMP, OPS CHECKS OK.
Part: LIGHT — MALFUNCTIONED (EMERGENCY EXIT)
EMERGENCY EXIT LIGHT AT ESCAPE DOOR ON FLIGHT DECK GOES OUT 3-5 SECONDS AFTER BEING TURNED ON. REPLACED LIGHT PACK ASSY, OPS CHECKS OK.
Part: BATTERY PACK — DISCHARGED (CABIN)
INSPECTION TYPE:N/A EMERGENCY EXIT SIGN OVER UPPER DOCK ESCAPE SLIDE DOOR INOP. REMOVED AND REPLACED BATTERY PACK PER AMM 33-31-04. OPS CHECKED GOOD.
Part: FITTING — CORRODED (RT WING) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, RIGHT WING REAR SPAR LOWER KICK FITTING HOLE -A- FOUND CORROSION INSIDE FASTENER HOLE. CORROSION REMOVED AND HOLE -A- FREEZE PLUG INSTALLED AS PER RS R-57-12-35115 AND UPS EO B747-5710-20028-A.
Part: FRAME — CRACKED (FUSELAGE) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, M/D - NR 5R MED CUTOUT BS 2231 FRAME AT S25R FOUND 1 FASTENER HOLE CRACK AT STRAP. M/D R5 DOOR FWD CUTOUT FRAME STRAP REPAIRED PER SRM 53-10-04 FIG 115.
Part: FRAME — CRACKED (NR 3 PYLON) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, NR 3 PYLON REAR MOUNT BULKHEAD FOUND CRACKS AT O/B FWD AND AFT FRAME WEB. FRAME WEB ATTACH PARTS REINSTALLED PER BS 54-53-34870 AND CONTINUE REPEAT INSPECTION PER RS OR UPS EO SINCE NO FURTHER CRACK PROPAGATION AFTER REPAIR PARTS REMOVED.
Part: REVEAL — CRACKED (NR 4 DOOR) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, M/D - LEFT NR 4 DOOR CUTOUT FWD LOWER BET S24-25L, CUTOUT REVEAL FOUND CRACK AS MARKED. CUTOUT REVEAL REPAIRED AS PER SRM 53-10-04 FIG 84 AND HX RS R-53-62-35110, CRACKS STOPPED AT FASTENER HOLE FROM EDGE CONFIRMED BY NDT INSPECTION, SURROUNDING STRUCTURE IS CORROSION & DAMAGE FREE AFTER INSPECTED UPS ENGINEERING FILE 747-53-20171.
Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, M/D - LEFT NR 4 DOOR FWD CUTOUT FWD FRAME APPROX S16L AREA, FRAME I/B FWD FACE FOUND CRACK AS MARKED. FWD FRAME CRACKED PORTION TRIMMED OFF, REPAIRED AS PER HX RS 53-62-35110. SURROUNDING STRUCTURE IS CORROSION AND DAMAGE FREE AFTER INSPECTED. NDT INSPECTED THE TRIMMED AREA, NO CRACK FOUND UPS ENGINEERING FILE 747-53-20171.
Part: SKIN — CORRODED (RT WING) · airframe 83,180 hrs · 15,676 cycles
INSPECTION TYPE: C, RIGHT WING UPPER SURFACE T/E RABBET AREA STRAP PNL BULGED UP AT 20 INCHES O/B OF ROOT AREA. CORROSION BLEND OUT 11.5 X 1, DEPTH .115 TO .62, ORI .332 TO .328. FPI C/O SOPM 20-20-02 AT REWORK AREA CORROSION FREE NDT INSPECTED, NIL FINDING. SHOT PEENING C/O. FASTENER REINSTALLED PER RS 57-25-35116. REINSPECTION TO BE ACCOMPLISHED AT 20000 FLIGHT CYCLES DUE TO THIS REPAIR IS AN INTERIM REPAIR UPS EO B747-5710-20053-A.
2003
Part: SKIN — CRACKED (NR 3 PYLON)
INSPECTION TYPE: PFLT CRACK NR 3 ENGINE PYLON OUTBOARD SIDE AT PYLON EMERGENCY DRAIN TUBE. REPAIRED CRACK IAW 54-34-03 FIG 7.
Part: SKIN — CRACKED (FUSELAGE)
CRACK JUST AFT OF NLG CUTOUT. CRACK VERIFIED BY EDDY CURRENT READING. REMOVED CRACKED AREA OF SKIN VERIFIED CRACK REMOVED W/T EDDY CURRENT. REPAIRED IAW SRM 53-30-3
Part: ENGINE — FAILED (NR 3)
NR 3 ENGINE SHUTDOWN 56 MIN. AFTER TAKEOFF, ICE LIGHT CAME ON,FUEL HEAT APPLIED AND ICING LIGHT STAYED ON.OIL TEMP INCREASED TO 140 DEGREES AFTER 5 MINUTES EPR,N1 AND N2 ROLLED BACK AND ENG. DID NOT RESPOND. ENGINE SHUTDOWN . FOUND METAL IN TAILPIPE AND FUEL PUMP CRACKED. REMOVED AND REPLACED ENGINE.
Part: BULB — BURNED OUT (EMERGENCY LIGHT)
INSPECTION TYPE: A 3, EMERGENCY LIGHTS ON UPPER DECK HAS 1 BULB INOP. RELAMPED 3 LIGHTS AS REQUIRED, OPS CHECKED NORMAL.
Part: ENGINE — FAILED (NR 4)
DURING T/O AND CLIMB, TOWER NOTICED AND NOTIFIED FLT 6703 THAT SMOKE WAS TRAILING FROM NR 4 ENGINE. AT 6500 FEET CREW REPORTED A BANG AND ASSOCIATED ROLL BACK OF N1/N2. CREW FOLLOWED SEVERE ENGINE DAMAGE CKLIST. FUEL DUMPED AND AIRCRAFT 526 ON FLT 6703 RETURNED TO PHL. REMOVED AND REPLACED NR 4 ENG ASSY IAW MM TASK CARD 5000 PG 1-27.
Part: LIGHT — INOPERATIVE (MAIN DECK)
EMERGENCY LIGHT MAIN DECK CEILING AFT OF STAIRS INOPERATIVE. REMOVED AND REPLACED EMERGENCY LIGHT ON MAIN DECK, OPS OK.
2002
Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, CORROSION REVEALED ON BS 1480 BULKHEAD WEB LEFT I/B CORNER AREA, AREA INSP AFTER BATHTUB FITTING REMOVED INSIDE KEEL BEAM BOX. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPAIRED IAW HX RS R53-49-34878.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 BULKHEAD EXTENSION FITTING BOLT HOLE #11 FOUND CRACK. RH BS 1480 BULKHEAD #11 HOLE AT EXTENSION FITTING REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: PRESSURE PANEL — CRACKED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS RIGHT 1241 CANTED BULKHEAD OF WEB PNL HAS TWO CRACKS BETWEEN RBL 76 TO 80 AT THE AREA ADJACENT TRIM AIR DUCTS. WEB REPAIRED AS PER SRM 53-10-07 FIG 6.
Part: STIFFENER — CORRODED (RT WING) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, RIGHT WLG BS 1241 BULKHEAD STIFFENER FOUND CORROSION AT WL 150 RBL 4-10. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 57-10-01 FIG 1 LIMITS FOR REPAIR REFER TO HX RS R57-12-34875.
Part: SKIN — DAMAGED (NR 2 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C NR 2 PYLON I/B REAR MOUNT PYLON SKIN LOWER EDGE DOUBLER NONSTANDARD REPAIR IS FOUND AS MARKED. NR 2 PYLON I/B LOWER EDGE SKIN REPAIRED AS PER SRM 54-34-03 FIG 24 AND SRM 54-34-03 FIG 25.
Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, FX-KEEL BEAM BOX INTERIOR RIGHT SIDE LOWER CHORD FOUND CORROSION AT STA 1460-1468 RBL 6 TO RBL 8. CORROSION REMOVED IAW SRM 51-10-01 CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPAIRED IAW HX RS R53-49-34878.
Part: SHIM — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX-KEEL BEAM BOX EXTERIOR LOWER CHORD TO PANEL SUPPORT ATT SHIM FOUND CORROSION AT LT SIDE STA 1308 LBL 6 TO LBL 9. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 FIG 1 LIMITS, REPLACED IAW SRM FIG 51-10-01 PG 8.
Part: SHIM — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX-KEEL BEAM BOX EXTERIOR LOWER CHORD TO PANEL SUPPORT ATT SHIM FOUND CORROSION AT RT SIDE STA 1328 RBL 6 TO RBL 9. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 FIG 1 LIMITS, REPLACED IAW SRM FIG 51-10-01 PG 8.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, RIGHT BS 1241 BULKHEAD SPLICE STRAP FWD HOLE FOUND CRACK AT 12 O/C POSN WL 190. HOLE REWORKED IAW EO 5310-0323 APP F LIMIT. REF EO 5310-0323 PARA 4D ITEM 3 FOR SPLICE STRAP CRACK FINDING NO FURTHER ACTION IS REQUIRED.
Part: PANEL — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- KEEL BEAM FIXED PANEL UPPER SURFACE FOUND SURFACE CORROSION AT STA 1255 TO STA 1275 RBL 9 TO RBL 16. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPLACED IAW SRM FIG 51-10-01 PG 8.
Part: PANEL — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- KEEL BEAM FIXED PANEL UPPER SURFACE FOUND SURFACE CORROSION AT LT SIDE STA 1438 TO STA 1460 LBL 9 TO LBL 16. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPLACED IAW SRM FIG 51-10-01.
Part: WEB — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- AIR CONDITIONING BAY REAR FIXED FAIRING LT SIDE. GROUND PNEUMATIC AIR CONNECTOR SERVICE BOX INTERIOR REAR WEB FOUND SURFACE CORROSION AT STA 1255 LBL 34 TO LBL 36. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPAIR WEB IAW SRM FIG 51-40-02.
Part: SKIN — DEFORMED (NR 1 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C NR 1 PYLON RT LOWER EDGE AREA FROM NAC STA 180- REAR DRAG FIXED FAIRING INTERIOR METAL SKIN DEFORMED AS MARK. NR 1 PYLON RT LOWER EDGE AREA FROM NAC STA 180- REAR DRAG FIXED FAIRING INTERIOR METAL SKIN REPLACED AS PER SRM 54-34-03 FIG 25.
Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LEFT BS 1241 BULKHEAD FWD HOLE CRACKED AT BULKHEAD FRAME FORGING SPLICE STRAP & SKIN WL 170 TO 180. REWORKED HOLE AS PER EO 5310-0323 APP F TABLE 1, REWORKED HOLE NDT INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: SUPPORT — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- KEEL BEAM PNL SUPPORT LOWER CHORD FOUND SURFACE CORROSION AT STA 1480 LBL 16 TO RBL 16. CORROSION REMOVED IAW SRM 51-10-01, CORROSION BLEND OUT EXCEEDS SRM 53-10-01 LIMITS, REPLACED IAW SRM FIG 51-10-01.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS2278 LBL 33 SEAT TRACK CROWN CORR. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.040" X 1" X 2" EXCEED SRM 53-10-01 FIG 1 LIMITS. FOR REPLACEMENT REFER TO SRM FIG 51-10-01.
Part: WEB — CRACKED (#3 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #3 PYLON REAR MOUNT BULKHEAD FOUND CRACKED AT FWD & AFT WEB AT THREE FASTENER HOLE LOCATIONS AS PER ATTACHED FIGURE.(STA 221.9 TO 222, WL 170 TO 180). #3 PYLON REAR ENG MOUNT BULKHEAD REPAIR CARRIED OUT AS PER HX RS # R-54-53-34870.
Part: SKIN — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H #12 HOLE CRACK FOUND AT SKIN THROUGH THICKNESS RUNNING FWD & AFT REFER ATTACHED SKETCH. (STR R33 TO R34) RH BS 1480 B/H #12 HOLE AT SKIN REAMED TO 0.710 " DIAMETER AND BUSHING REPAIR CARRIED OUT AS PER RS # R-53-43-34784. NOTE: REPEAT INSPECTIONS PER UPS EO-B747-10732 APPENDIX 'C' MUST BE ACCOMPLISHED EVERY 4,800 CYCLES.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H HOLE #5 CRACK FOUND 2EA AT EXTENSION FITTING 1/16" IN LENGTH APPROX AND 1EA AT HOLE #5 SKIN 1/16" IN LENGTH APPROX. REFER ATTACHED DWG FOR LOCATION. (STR R33 TO R34). RH BS1480 B/H HOLE #5 AT EXTENSION FITTING AND SKIN REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390. REWORKED HOLE CRACK FREE CONFIRMED AS PER NTM PART 6 51-00-00 FIG.1
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H #3 HOLE CRACK FOUND AT EXTENSION FITTING APPROX 1/16" LONG RUNNING FWD & 0.040" LONG RUNNING AFT. REFER ATTACHED SKETCH. (STR R33 TO R34). RH BS 1480 B/H #3 HOLE AT EXTENSION FITTING REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390.AS PER NTM PART 6 51-00-00 FIG 1
Part: SKIN — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 BULKHEAD CHROD AREA #11 HOLE CRACK FOUND AT SKIN, APPROX 1/16" RUNNING FWD. REFER ATTACHED SKETCH. (STR R34 ) RH BS 1480 B/H #11 HOLE AT SKIN REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: FRAME — CRACKED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RIGHT BS 1480 BULKHEAD NR 3 HOLE CRACK FOUND AT BULKHEAD CHORD, APPROX .0625 INCH LONG, RUNNING FWD STR 33R TO 34R. RIGHT BS 1480 BULKHEAD NR 3 HOLE AT BULKHEAD CHORD REAMED AND BUSHING INSTALLED AS PER SB 747-53A2390.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H HOLE #5 CRACK FOUND 1EA AT FASTENER FITTING 1/16" IN LENGTH APPROX. REFER TO ATTACHED DWG FOR LOCATION. (STR L33 TO L34). LH BS 1480 B/H EXTENSION FITTING BOLT HOLE #5 REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 R1 REWORK HOLE CRACK FREE CONFIRMED AS NTM PT6-51-00-00 FIG 4.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 #16 HOLE CRACK FOUND AT SPLICE PLATE AFT SURFACE RUNNING UP 1/8" AND RUNNING DOWN 3/16" LONG. REFER ATTACH SKETCH. (STR R33 TO R34) RH BS 1480 B/H SPLICE PLATE REPLACED DUE HOLE CRACK EXCCEED 'D' MAX LIMIT AS PER SB 747-53A2390 FIG 11.
Part: WEB — CRACKED (FWD CARGO) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FWD CARGO - STA 900 (LBL 46", BELOW FLOOR 6") FRAME WEB FOUND CRACK AS MARKED. REPAIRED WEB AT FWD CARGO STA 900 LBL 46" AS PER SRM 51-40-02.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H #11 HOLE 2EA CRACK FOUND AT OUTER CHORD SPLICE FTG RUNNING FWD AT 8 O/C POSN & 7 O/C POSN (LOOKING I/B),CRACK AT 8 O/C POSN 3/16" LONG, CRACK AT 7 O/C POSN 0.040" LONG (CRACK AT O/B FACE) (STR L33 TO L34) LH BS 1480 B/H OUTER CHORD SPLICE FTG BOLT HOLE #11 REAMED TO 0.660" AS PER SB 747-53A2390 R1 AND BUSHING REINSTALLED CRACK FREE CONFIRMED AS PER NDT NTM PT 6 51-00-00 FIG 4.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H MOD HOLE #14 CRACK FOUND AT SPLICE PLATE AFT SURFACE RUNNING UP APPROX 1/16" LONG. REFER ATTACH SKETCH. (STR L33 TO L34) LH BS 1480 B/H SPLICE PLATE BOLT HOLE #14 REAMED TO 0.500" AND BUSHING INSTALLED AS PER SB 747-53A2390 R1 CRACK TEST DONE AS PER NTM 51-00-00 FIG 4 NIL CRACK REVEALED.
Part: FITTING — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, RIGHT BS 1480 BULKHEAD NR 6 HOLE CORROSION FOUND AT EXTENSION FITTING AROUND BORE STR 33R TO 34R. RIGHT BS 1480 BULKHEAD NR 6 HOLE AT EXTENSION FITTING REAMED AND BUSHING INSTALLED AS PER SB 747-53A2390.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #16 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG, RUNNING I/B APPROX 1/16" & O/B APPROX 1/8" LONG.(STR R33 TO R34). RH BS 1480 B/H #16 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.562" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED ,NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H EXTENSION FITTING #9 HOLE CRACK FOUND, APPROX 1/16", RUNNING FWD & AFT REFER ATTACHED SKETCH. ( STR R33 TO R34) RH BS 1480 B/H EXTENSION FITTING #9 HOLE REAMED TO 0.850" DIAMETER AND BUSHING REPAIR CARRIED OUT AS PER RS #R-53-43-34874. NOTE: REPEAT INSPECTIONS PER UPS EO -B747-10732 APPENDIX 'C' MUST BE ACCOMPLISHED EVERY 48,00 CYCLES.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #7 HOLE FOUND CORROSION AROUND AND INSIDE HOLE BORE OF OUTER CHORD SPLICE FTG. (STR R33 TO R34). RH BS 1480 B/H #7 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.660 AND BUSHING INSTALLED AS PER B747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #9 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG. RUNNING AFT APPROX 1/16" LONG. (STR R33 TO R34) RH BS 1480 B/H #9 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.660" AND BUSHING INSTALLED AS PER SB747-53A2390. REWORKED HOLE INSPECTED, NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #14 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG, RUNNING O/B APPROX 1/16" LONG. (STR R33 TO R34) RH BS 1480 B/H #14 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.500" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1
Part: STIFFENER — CRACKED (M/D) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS 2300 RBL 10 WL 190 FLR BEAM ATT VERTICAL STIFFENER CRK. STIFFENER REPLACED AS PER SRM 51-10-01.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H #7 HOLE 3EA CRACK FOUND AT OUTER CHORD SPLICE FTG RUNNING AFT 0.020" , 0.030" & 0.040" LONG (COUNT FROM UPPER TO LOWER ) (CRACK AT O/B FACE). STR L33 TO L34 LH BS 1480 B/H OUTER CHORD SPLICE FTG BOLT HOLE #7 REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB747-53A2390 R1 HOLE CRACK FREE CONFIRMED AS PER NTM PT6-51-00-00.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 B/H LH #4 HOLE CRACK FOUND AT OUTER CHORD SPLICE FTG, RUNNING FWD APPROX 0.030" LONG. (CRACK AT O/B FACE). STR L33 TO L34 LH BS 1480 B/H LH #4 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.625 AND BUSHING INSTALLED AS PER SB 747-53A2390 R1 HOLE CRACK FREE CONFIRMED AS PER NTM PT6-51-00-00 FIG 4
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H #14 HOLE CRACK AT B/H WEB AFT SURFACE RUNNING UP APPROX 3/16" LONG. REFER ATTACHED SKETCH. ( STR R33 TO R34) RH BS 1480 B/H #14 HOLE AT B/HEAD WEB REAMED TO 0.500" AND BUSHING INSTALLED AS PER SB747-53A2390 REWORKED HOLE CRACK FREE CONFIRMED AS PER NTM PART 6 , 51-00-00 FIG 1
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #5 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG, RUNNING FWD APPROX 1/8" AND AFT APPROX 1/16" LONG. (STR R33 TO R34). RH BS 1480 B/H #5 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.660" AND BUSHING INSTALLED AS PER SB747-53A2390. REWORKED HOLE CRACK FREE CONFIRMED AS PER NTM PART 6 51-10-00 FIG 1.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #3 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG, RUNNING FWD APPROX 1/16" & AFT APPROX 0.040" LONG. (STR R33 TO R34) RH BS 1480 B/H #3 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE CRACK FREE CONFIRMED AS PER NTM PART 6 51-00-00 FIG 1.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H #16 HOLE CRACK AT B/H WEB AFT SURFACE RUNNING UP APPROX 0.040" LONG. REFER ATTACHED SKETCH. (STR R34) RH BS 1480 B/H HOLE AT WEB PNL REAMED TO 0.500" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED. NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: WEB — CRACKED (BS 320) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 320 NOSE W/W VERTICAL BEAM WEB ONE INSULATION BLANKET STANDOFF HOLE CRACK FOUND APPROX 7/8" LONG AS MARKED. (WL 160 TO 170) VERTICAL BEAM WEB REPLACED AS PER DWG 624U0005 SHEET 4 AND SRM 51-10 -01 PG 8.
Part: SKIN — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RIGHT BS 1480 BULKHEAD NR 6 HOLE CORROSION FOUND AT SKIN AROUND BORE STR 33R TO 34R. HOLE REAMED AND BUSHING INSTALLED AS PER SB 747-53A2390. REWORKED HOLE INSPECTED - SATISFACTORY AS PER NTM PART 6 51-00-00 FIG 1.
Part: CHANNEL — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS 2280 - 2300 RBL 11 HAT SECTION CORRODED. CORROSION REMOVED IAW SRM 51-10-01, CORROSION EXCEEDS SRM 53-10-01 FIG 1 LIMITS, REPLACEMENT REFER SRM FIG 51-10-01.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS 2320 - 2340 RBL 2 FLOOR SUPPORT CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION EXCEEDS SRM 53-10-01 FIG 1 LIMITS, FOR REPLACEMENT REFER SRM FIG 51-10-01.
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #6 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG RUNNING AFT APPROX 1/16" LONG.(STR R33 TO R34). RH BS 1480 B/H #6 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.660" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: STIFFENER — CRACKED (#2 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #2 PYLON REAR ENGINE MOUNT BULKHEAD UPPER STIFFENER 2EA FASTENER HOLES CRACK FOUND AT O/B SIDE OF PYLON THROUG THICKNESS REFER TO ATTACHED DRAWING FOR LOCATION. #2 PYLON REAR ENGINE B/H UPPER STIFFENER REPLACED AS PER SRM 51-10-01 PAGE 8.
Part: SKIN — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C RH BS 1480 B/H 33 HOLE CRACK FOUND AT SKIN THROUGH THICKNESS RUNNING FWD. REFER ATTACHED SKETCH. (STR R33 TO R34 ) RH BS 1480 B/H #3 HOLE AT SKIN REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS 2350 - 2360 RBL 16 FLOOR SUPPORT CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION EXCEEDS SRM 53-10-01 FIG 1, LIMITS REPLACEMENT REFER SRM FIG 51-10-01.
Part: CHANNEL — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C M/D- BS 2315 - LBL 11 HAT SECTION CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION EXCEEDS SRM 53-10-01 FIG 1 LIMITS, REPLACEMENT REFER SRM FIG 51-10-01.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C BS 1480 RH B/H #18 HOLE FOUND CRACK AT OUTER CHORD SPLICE FTG, RUNNING O/B APPROX 0.030" LONG. (STR R33 TO R34) RH BS 1480 B/H #10 HOLE AT OUTER CHORD SPLICE FTG REAMED TO 0.625" AND BUSHING INSTALLED AS PER SB 747-53A2390 REWORKED HOLE INSPECTED NIL CRACK FOUND AS PER NTM PART 6 51-00-00 FIG 1.
Part: STIFFENER — CRACKED (#1 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #1 PYLON REAR ENGINE MOUNT B/H UPPER STIFFENER FOUND 2EA FASTENER HOLE CRACKED REFER ATTACHED SKETCH FOR DETAILS. #1 PYLON REAR ENGINE MOUNT B/H UPPER STIFFENER REPLACED AS PER SRM 51-10-01 PAGE 8.
Part: FITTING — CRACKED (BS1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H HOLE #15 CRACK FOUND AT SPLICE PLATE RUNNING UP & DOWN, BOTH CRACKS APPROX 0.020", REFER ATTACH SKETCH. LH B/H BOLT HOLE #15 REAMED TO 0.500" AS PER SB 747-53A2390 FIG.11 CRACK TEST DONE NO CRACK FOUND AS PER NTM PT6 51-00-00 FIG 4 AND BUSHING INSTALLED AS PER SB 747-53A2390 R1
Part: FITTING — CRACKED (BS 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C LH BS 1480 B/H HOLE #23 CRACK FOUND AT SPLICE PLATE RUNNING CRACK FOUND AT SPLICE PLATE RUNNING UP APPROX 0.040" REFER ATTACHED SKETCH. (STR L33 TO L34) LH BS 1480 B/H HOLE #23 AT SPLICE PLATE REAMED TO 0.500" AND BUSHING INSTALLED AS PER SB 747-53A2390 R1 HOLE CRACK FREE CONFIRMED AS PER NTM 51-00-00 FIG 4
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C, M/D BS 460 RBL 58 - RBL 70 FLOORBEAM WEB FOUND CORRODED. CORROSION REMOVED IAW SRM 51-10-01, CORROSION BLEND OUT EXCEEDS SRM 53-10-01 FIG 1 LIMITS, REPAIRED BS 460 RBL 70 FLOORBEAM WEB IAW SRM FIG 53-10-07 FIG 11.
Part: WEB — CRACKED (#1 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #1 PYLON REAR MOUNT B/H FWD & AFT WEB FOUND CRACKS. #1 PYLON REAR ENG MOUNT BULKHEAD REPAIR CARRIED OUT AS PER HX RS # R-54-53-34873.
Part: WEB — CRACKED (#2 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #2 PYLON REAR MOUNT B/H. FWD. AND AFT. WEB FOUND CRACKS. #2 PYLON REAR ENG MOUNT BULKHEAD REPAIR CARRIED OUT AS PER HX RS# R-54-53-34872
Part: WEB — CRACKED (#4 PYLON) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C #4 PYLON REAR MOUNT B/H AFT WEB FOUND CRACKS. #4 PYLON REAR ENG MOUNT BULKHEAD REPAIR CARRIED OUT AS PER HX RS # R-54-53-3487.
Part: WEB — CRACKED (STA 1480) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- LOWER FUSELAGE PRESSURE BULKHEAD ATT WEB FOUND CRACKED AT STA 1480 RH SIDE O/B RBL 95. CLOSE OF SPLICE FITTING STRG 33R. WEB PANEL REPAIRED AS PER SRM 51-40-02 FIG 1
Part: SKIN — CRACKED (AFT CARGO) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C AFT CARGO DOOR CUTOUT UPPER FWD CORNER 1EA FASTENER HOLE CRACK FOUND AT SKIN, APPROX 1/2" RUNNING DOWNWARD AND 5/16" RUNNING UPWARD PLS REFER ATT FTG. (BS1810 TO 1810, STR R28 TO R28) WASHER AND DOUBLER INSTALLED AT UPPER FWD CUTOUT AS PER SRM 53-30-03 FIG 62 WORK DETAIL REFER ATTACHED CWS. AND EO B747-5330-14013-B REPEAT INSPECTION IS REQUIRED AT INTERVAL 3000 CYCLES AS PER SRM 53-30-03 FIG 62 TABLE 3.
Part: WEB — CORRODED (FAIRING) · airframe 79,834 hrs · 15,049 cycles
INSPECTION TYPE:C FX- AIR CONDITIONING BAY REAR FIXED FAIRING INTERIOR REAR SURFACE FOUND SURFACE CORROSION AT STA 1255 RBL 9 TO RBL 30. REAR FIXED FAIRING REAR WEB AND SUPPORT CHORD REPAIRED AS PER SRM 51-40-02 FIG 1, 51-40-03 FIG 2 AND FIXED PNL REPLACED PER SRM 51-10-01.
Part: ENGINE — MALFUNCTIONED (NR 2)
INSPECTION TYPE:N/A ATB NR 2 ENG OVERTEMP, VIBRATION (IFSD) CREW DECLARED EMERGENCY. REMOVED AND REPLACED NR 2 ENGINE IAW TC NO 5000 LEAK AND OPS CHECK NORMAL.
Part: SKIN — CRACKED (FUSELAGE)
INSPECTION TYPE: FOUND NUMEROUS BURNT AND PITTED FASTENERS ON RT SIDE OF FUSELAGE AT STA 140 AT ABOUT 4 O'CLOCK TO 6 O'CLOCK POSITION COUNTING AFT TO STA 2240. REMOVED DAMAGED FASTENERS PER 53-30-03, EDDIE CURRENT INSPECTION FOUND 3 SMALL CRACKS AT 3 SEPARATE FASTENERS.
Part: POWER SUPPLY — DISCHARGED (CABIN)
INSPECTION TYPE:IN UPPER DECK AFT EMERGENCY LIGHT INOP. REMOVED SIDEWALL AND BOTH LIGHTS. REMOVED POWER SUPPLY, NO HELP. FOUND POWER SUPPLY TO BE BAD FROM STOCK. REMOVED AND REPLACED POWER SUPPLY IN STA 650 AND INSTALLED SIDEWALL & LIGHT ASSY, SYS CHECKS NORMAL IAW 33-50-00.
Part: LIGHT — INOPERATIVE (CABIN)
INSPECTION TYPE:PFLT EMERGENCY LIGHT OVER UPPER DECK STAIRS INOP. RELAMPED, CHECKS GOOD.
2001
Part: ENGINE — FLAMED OUT (NR1 & NR2 ENGINE)
INSPECTION TYPE:N/A PILOT REPORT NR 1 AND NR 2 ENGINE FLAME-OUT. INGN FUEL AND OIL SYS CK PER MM AND ENGINEERING OPRN NORMAL.
Part: DOOR — MALFUNCTIONED (NOSE GEAR)
INSPECTION TYPE:IN NOSE GEAR DOORS HARD TO CLOSE CLOSED DOORS
Part: WEB — CRACKED (NR 3 DOOR)
INSPECTION TYPE:N/A CRACKS ON NR 3 ENTRY DOOR LIGHTING HOLES. *S/D* ACCOMPLISHED REPAIR IAW EO 747-53-15-88270.
Part: FRAME — CRACKED (FUSELAGE)
INSPECTION TYPE:N/A CRACK ON NR 2 STRUT AFT BULKHEAD LEFT HAND CHORD AND FASTENER HOLE. *S/D* ACCOMPLISHED IAW EO MF-MAN-B747-5440-14107.