N808MC

Part: INU — FAILED (COCKPIT)

ON CLIMB OUT, NR 1 INS WARNING LIGHT CAME ON. ON CLIMB OUT NR 1 INS WARNING LIGHT CAME ON. NR 1 ADI AND HEADING FAILED. SELECTED NR 3 ATTITUDE AND COMPASS. APPROX 3 MINUTES LATER NR 3 INS WARNING LIGHT CAME ON. BOTH SCREENS WENT BLANK AND SHUT DOWN. REMOVED AND REPLACED NR 1 AND NR 3 INS NAVIGATION UNIT IAW MM 34-41-03/ 401 AND 501. OPS CHECK OK.

Part: CONTROLLER — FAILED (CABIN PRESSURE)

GT 8237/03 RMS/DOV AUTO FAIL LIGHT CAME ON DURING FLIGHT: AUTO FAIL LIGHT CAME ON DURING CLIMB ABOUT 8000 FT A/C ALTITUDE OUTFLOW VALVES .2500 CLOSED USED MANUAL IAW ABNORMAL CHECK LIST TO CONTROL DIFFERENTIAL PRESSURE AT 4 PSID CONTINUED FLIGHT. GOING THROUGH FL 220 DIFFERENTIAL PRESSURE WENT TO 9.5 PSID, RATE OF CLIMB MAX OUT, BOTH PRESSURE RELIEF LIGHTS CAME ON, CABIN ALTITUDE WAS GOING THROUGH 10,000 FT. CABIN ALTITUDE MAX OUT AT 14,500 FT DESCENDED AIRCRAFT TO 10,000 FT. ALL INDICATION CAME BACK TO NORMAL. USED MANUAL CONTROL TO 4 PSID, AND DIVERTED. COMPLETED PRESSURIZATION CHECK IAW MM. UNABLE TO DUPLICATE PROBLEMS. AS PRECAUTION, CHANGED CABIN PRESSURE CONTROLLER, AND PRESSURIZED AC TO MM REF.

Part: BEARING — MIGRATED (FLAP TRACK)

D-CHECK, DURING MAINTENANCE INSPECTION, ELONGATION DAMAGE WAS FOUND AT OB TRAILING EDGE FLAP TRACK NR 8 MOVABLE FAIRING ASSEMBLY HINGE FITTING LUGS. OVERSIZED THE BORES. DYE PENETRANT THE BORES TO ENSURE DEFECT FREE CONDITION. REFINISHED, INSTALLED ONE PIECE REPAIR SLEEVE AND A NEW DESIGN TYPE BEARING.

Part: BULKHEAD — CRACKED (NR 1 NACELLE)

D-CHECK, DURING MAINTENANCE INSPECTION. NR 1 PYLON LT SIDE, BULKHEAD STRAPS WERE FOUND CRACKED AT NAC STA 286.0 AND W.L. 146.5, ALSO THE STRUT SKIN ASSEMBLY AT THE AFT LOWER ACCESS CUT OUT EDGE ADJACENT TO THE STRAP CRACK LOCATION WAS FOUND WITH CHAFING DAMAGE. THE AFT END OF THE STRAP CRACK WAS STOPPED DRILLED AND HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. THE SKIN ACCESS CUT OUT EDGE CHAFING DAMAGE WAS REMOVED BY BLENDING. REPAIR DOUBLERS WAS FABRICATED FROM 0.063 INCH THICK TITANIUM SHEET WERE INSTALLED COMMON TO THE STRUT OUTER SKIN ASSEMBLY USING MECHANICAL FASTENERS.

Part: BULKHEAD — CRACKED (FUSELAGE)

D-CHECK, DURING MAINTENANCE INSPECTION. NR 4 PYLON LT SIDE, BULKHEAD STRAPS WERE FOUND CRACKED AT NAC STA 286.0 AND WL 146.5. THE AFT END OF THE STRAP CRACK WAS STOPPED DRILLED AND HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. THE SKIN ACCESS CUT OUT EDGE CHAFING DAMAGE WAS REMOVED BY BLENDING. REPAIR DOUBLERS WAS FABRICATED FROM 0.063 INCH THICK TITANIUM SHEET WERE INSTALLED COMMON TO THE STRUT OUTER SKIN ASSY USING MECHANICAL FASTENERS.

Part: PRECOOLER — CRACKED (NR 3 PYLON)

(D) CHECK, DURING MAINT INSP, DAMAGE WAS FOUND ON RT SIDE OF NR 3 PYLON STRUCTURE ASSY. CRACK DAMAGE WAS AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NAC STA 248. INNER SKIN DOUBLER WAS TRIMMED, AT GRILL ATTACHED HOLE TO REMOVE CRACK DAMAGE. INNER SKIN DOUBLER TRIMMED EDGE, EXPOSED WINDOW STRAP SURFACE, ALONG WITH FASTENER HOLES, WERE HFEC INSPECTED TO ENSURE ABSENCE OF ANY CRACK OR OTHER DAMAGE. NR 3 STIFFENER WAS REINFORCED WITH NEW STEEL LOWER REPAIR ANGLE FROM NAC STA .235 TO 254. RIB INSTALLATION AT NAC STA 248 WAS MODIFIED TO ACCOMMODATE NEW STEEL REPAIR ANGLES INSTALLATION ON NR 3 STIFFENER. ALUMINUM FILLER, FOR TRIMMED AREA OF INNER SKIN DOUBLER, WAS INSTALLED USING EXISTING NUT PLATE RIVETS.

Part: FRAME — DAMAGED

D CHECK, DURING MAINT INSP FOUND COCKPIT EMERGENCY EXIT DOOR CUTOUT FRAME AND CHORDS DAMAGED BETWEEN STA 360 AND 380 WITH MISDRILLED HOLES BETWEEN STRINGER 2L AND 2AL. SEVERAL MISDRILLED HOLES AND DRILL STARTS WERE REPAIRED AS FOLLOWS. FOR BS 360, WEB DAMAGE WAS TRIMMED OUT AND REPLACEMENT WEB WAS SPLICED IN. THE CHORD DAMAGED WAS BLENDED OUT. FOR BS 380, THE WEB WAS CUT BETWEEN S2AL AND S3L AND REPLACED TO S0 WITH A WEB SPLICE AT THE CUT LOCATION. THE INNER CHORD DAMAGE WAS TRIMMED OUT AND REPAIR ANGLE INSTALLED.

Part: SKIN — CRACKED (NR 2 NACELLE)

(D) CHECK, DURING MAINT INSP DAMAGE WAS FOUND ON RT SIDE OF NR 2 PYLON STRUCTURE ASSY. CRACK DAMAGE WAS AT PRECOOLER EXHAUST CUTOUT LOWER AFT CORNER AT NAC STA 248. INNER SKIN DOUBLER WAS TRIMMED, AT GRILL ATTACHED HOLE TO REMOVE CRACK DAMAGE. INNER SKIN DOUBLER TRIMMED EDGE AND EXPOSED WINDOW STRAP SURFACE, ALONG WITH FASTENER HOLES, HFEC INSPECTED TO ENSURE ABSENCE OF ANY CRACK OR OTHER DAMAGE. NR 3 STIFFENER WAS REINFORCED WITH NEW STEEL LOWER REPAIR ANGLE FROM NAC STA .235 TO .254. RIB INSTALLATION AT NAC STA .248 WAS MODIFIED TO ACCOMMODATE NEW STEEL REPAIR ANGLES INSTALLATION ON NR 3 STIFFENER. AN ALUMINUM FILLER, FOR TRIMMED AREA OF INNER SKIN DOUBLER, WAS INSTALLED USING EXISTING NUT PLATE RIVETS.

Part: SKIN — CRACKED (NR 4 NACELLE)

D-CHECK, DURING MAINT INSP, DAMAGE WAS FOUND ON RT SIDE OF NR 4 PYLON STRUCTURE ASSY. CRACK DAMAGE WAS AT PRECOOLER EXHAUST CUTOUT LOWER AFT CORNER AT NAC STA 248. INNER DOUBLER WAS TRIMMED AT GRILL ATTACHED HOLE TO REMOVE CRACK DAMAGE. INNER SKIN DOUBLER TRIMMED EDGE AND EXPOSED WINDOW STRAP SURFACE ALONG WITH FASTENER HOLES, WERE HFEC INSPECTED TO ENSURE ABSENCE OF ANY CRACK OR OTHER DAMAGE. NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NAC STA .235 TO .254. RIB INSTALLATION AT NAC STA 248 WAS MODIFIED TO ACCOMMODATE NEW STEEL REPAIR ANGLES INSTALLATION ON NR 3 STIFFENER. AN ALUMINUM FILLER, FOR TRIMMED AREA OF INNER SKIN DOUBLER, WAS INSTALLED USING EXISTING NUT PLATE RIVETS.

Part: SKIN — CRACKED (NR 1 NACELLE)

D-CHECK, DAMAGE WAS FOUND ON RT SIDE OF NR 1 PYLON STRUCTURE ASSY. CRACK DAMAGE WAS AT PRECOOLER EXHAUST CUTOUT LOWER AFT CORNER AT NAC STA 248. INNER SKIN DOUBLER WAS TRIMMED AT GRILL ATTACHED HOLE TO REMOVE CRACK DAMAGE. INNER SKIN DOUBLER TRIMMED EDGE, EXPOSED WINDOW STRAP SURFACE, ALONG WITH THE FASTENER HOLES, WERE HFEC INSPECTED TO ENSURE ABSENCE OF ANY CRACK OR OTHER DAMAGE. NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NAC STA .235 TO .254. RIB INSTALLATION AT NAC STA 248 WAS MODIFIED TO ACCOMMODATE NEW STEEL REPAIR ANGLES INSTALLATION ON THE NR 3 STIFFENER. AN ALUMINUM FILLER, FOR TRIMMED AREA OF INNER SKIN DOUBLER, WAS INSTALLED USING EXISTING NUT PLATE RIVETS.

Part: FITTING — CRACKED (NR 1 PYLON)

D-CHECK. REWORK OF STRUT NR 1 DIAGONAL BRACE LOWER SPAR FITTING, SP 747-54A2196 REV 1. DURING ACCOMPLISHMENT OF THE TERMINATING ACTION, DAMAGE WAS FOUND AT THE UPPER MOST FASTENER HOLE ON THE RIGHT SIDE OF THE FITTING AFT VERTICAL FLANGE. THE DEFECT WAS COMPLETELY REMOVED BY OVERSIZING THE HOLE TO 0.434 INCHES DIAMETER PRIOR TO FURTHER OVERSIZING TO 0.4521 INCHES DIAMETER. A SAME TYPE FASTENER AS USED WAS INSTALLED AT THE DISCREPANT LOCATION. ALL OTHER FITTING REWORK AND REFINISH WAS ACCOMPLISHED IAW WITH THE TERMINATING ACTION.

Part: SKIN — WRINKLED (NR 2 PYLON)

D CHECK AT SIN. DURING MAINTENANCE INSPECTION, FOUND NR 2 PYLON RT SIDE SKIN WRINKLED. DAMAGE WAS FOUND IN FOUR BAYS OF THE RT SUBJECT SKIN ASSEMBLY AFT OF NAC STA 286. THE DAMAGES ARE JUS AFT OF THE STRUT LARGE TITANIUM DOUBLER. SUBJECT SKIN ASSEMBLY WAS REPAIRED BY TRIMMING THE AFFECTED AREA OF THE DENT DAMAGE AND INSTALLING REPAIR DOUBLERS TO RESTORE STRUCTURE TO DESIGN CAPABILITY.

Part: SLIDE — MALFUNCTIONED (UPPER DECK)

UPPER RT EMERGENCY DOOR SLIDE PARTIAL DEPLOYMENT; DURING UPPER RT EMERGENCY DOOR SLIDE RAFT ASSEMBLY DEPLOYMENT TEST, SLIDE/RAFT FAILED TO FULLY INFLATE. SEQUENCING MECHANISM RELEASED TO FACILITATE SLIDE RAFT REMOVAL AND DISPATCH TO STOP. NOTE: ACTUAL OR APPARENT CAUSE OF PARTIAL DEPLOYMENT IS BEEN INVESTIGATED DURING THE SLIDE OVERHAUL.

Part: RELIEF VALVE — FAILED (NR 4 ENGINE)

LIM-MIA - DURING CLIMB AT FL250, NR 4 NACELLE TEMP WENT OT 8.0 WITH A FIRE BELL AND LIGHT IN NR 4 FIRE SWITCH. WHEN NR 4 THRUST LEVER WAS RETARDED TO IDLE, THE FIRE LIGHT WENT OUT AND THE NACELLE TEMP RETURNED TO NORMAL 2.0. CLOSED NR 4 BLEED VALVE AND ADVANCED THROTTLE. NACELLE REMAINED NORMAL. REMOVED AND REPLACED PRESSURE RELIEF VALVE PER MM 36-11-03. LEAK CHECK OK. REMOVED AND REPLACED REGULATING VALVE, P/N 878806-1, PER MM 36-11-19. LEAK CHECK OK. (M)

Part: RELIEF VALVE — DEFECTIVE (NR 4 ENGINE)

MIP/POS-AIR TURNBACK, AFTER T/O AND DURING CLIMB, NR 4 ENGINE FIRE WARNING CAME ON. WHEN NR 4 THROTTLE WAS CLOSED THE TEMP WENT BACK TO NORMAL. THROTTLE WAS ADVANCED AGAIN THE TEMP STARTED TO GO UP. NOTICED HIGH STAGE BLEED VALVE LIGHT, ON AND OFF. CLOSED NR 4 BLEED VALVE AND TEMP STAYED NORMAL WHEN THROTTLE WAS ADVANCED. RETURNED TO MIA. SECURED CLAMP FOUND LEAKING AT REGULATOR VALVE. LOCKED OUT HIGH STAGE VALVE PER DDPG. RAN ENGINE IAW MM 71-00-00. ALL CHECKS NORMAL. R&R NR 4 ENGINE HIGH STAGE VALVE IAW MM 36-11-05. OPS AND LEAK CHECK OK. R&R NR 4 ENGINE HIGH STAGE ELECTRICAL CORE HARNESS. OPS CHECK OK. R&R NR 4 ENGINE PRV IAW MM 36-11-03. LEAK CHECK OK. PERFORMED ENGINE RUN PER MM 71-00-00. ALL OK. (M)

Part: WARNING LIGHT — FALSE INDICATION (CARGO FIRE)

TURN BACK, AFTER TAKEOFF THE LOWER CARGO FIRE PROTECTION AFT LIGHT CAME ON AND WENT OUT 2-4 SECONDS AFTER SILENCING THE BELL. ACCOMPLISHED CHECKLIST AND DUMPED FUEL. RETURNED TO GYE AIRPORT. FUEL DUMPED 43,000 KGS. LOWER CARGO FIRE PROTECTION CHECKED PER MM 26-15-01. OPERATIONAL CHECK OK. (M)

Part: WARNING LIGHT — ILLUMINATED (NR 4 ENGINE)

INFLIGHT ENGINE SHUTDOWN, DURING CRUISE, NR 4 ENGINE SHUTDOWN IN FIGHT DUE TO 'OIL FILTER BYPASS LIGHT. OIL TEMPEARTURE AND PRESSURE NORMAL AT 49 PSI/120 DEGREES AND N2 AT 94 PERCENT. WITH THRUST AT IDEL (75 PERCENT N2) PRESSURE WAS 30 PSI AND TEMPERATURE ROSE TO 140 DEGREES. LIGHT WAS STILL ON. LIGHT REMAINED ON STEADY AFTER SHUTDOWN. REMOVED AND REPLACED NR 4 ENGINE PER B747 MM 71-00-02 AND FORM NR 01-AA-45. COMPLIED WITH ALL PROCEDURES WITHIN. ENGINE RUNUP, LEAK CHECK AND ALL SYSTEMS CHECK SATISFACTORY. (M)

Part: PANEL — CRACKED (FUSELAGE)

DURING CURRENT C-CHECK, AT HKG FOUND REVEAL PANEL CRACKED AT NR 2 MED STATION 800 BETWEEN STRINGER 17L AND 18L. CRACK LENGTH IS APPROX .5 INCH LONG TERMINATING IN A COMMON FASTENER HOLE. PERFORMED E/C INSPECTION TO ENSURE NO CRACK PROPAGATION FROM HOLE. OVERSIZED HOLE .0625 INCH AND INSTALLED FASTENER COMMON TO THE CRACK END PER STANDARD SRM PROCEDURES. (M)

Part: SKIN — CORRODED (FUSELAGE)

DURING CURRENT "C" CHECK, FOUND CORROSION BETWEEN OUTER SKIN, DOUBLER AND TRIPLER AT BS 1960 STR 42 RT, LOCATED AT THE AFT LOWER CORNER CUTOUT OF THE AFT LOWER LOBE COMPARTMENT DOOR. NO LEVEL DECLARED BUT CORROSION CONSIDERED LOCAL. OUTER SKIN, DOUBLER AND TRIPLER TRIMMED AWAY. PERFORMED E/C OPEN HOLE INSPECTION AND SURFACE INSPECTION OF CUTOUTS TO ENSURE A CRACK FREE CONDITION. NO DEFECTS FOUND. FABRICATED FILLERS, DOUBLER AND TRIPLER. TREATED AND PRIME PAINTED IAW SRM. INSTALLED FASTENERS IAW SRM WET WITH BMS 5-95 SEALANT. REPAIR IS TIME LIMITED FOR 12 MONTHS PENDING DETERMINATION OF ALTERNATE INSPECTION PROCEDURES IAW SSI.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY)

DURING CLIMB-OUT FROM MIA AT APPROXIMATELY 21,000 FEET, THE CARGO LOWER AFT FIRE LIGHT ILLUMINATED. CHECKLIST SECTION III WAS COMPLETED. THE CARGO FLOOR FELT WARM AT SL, BOTH FORWARD AND AFT CARGO HEAT TURNED OFF. WHILE DESCENDING AT 1800 FT THE FIRE LIGHTS WENT OUT. REMOVED AND REPLACED ALL FOUR SMOKE DETECTORS AND REMOVED AND REPLACED ALL FOUR SMOKE DETECTOR AMPLIFIERS. OPERATIONAL CHECK PER MM 26-16-02 PAGE 401. (M)

Part: FIRE WARNING — FALSE INDICATION (COCKPIT)

DURING TAKEOFF ROLL FROM SUU AT ABOUT 80 KTS, HAD A CARGO FIRE WARNING LIGHT. REJECTED TAKEOFF PERFORMED. PERFORMED VISUAL INSPECTION OF FORWARD AND AFT CARGO COMPARTMENTS. BOTH COOL, NO EVIDENCE OF HEAT OR OVERHEAT CONDITION EXISTS. INSPECTED AFT CARGO HEAT CONTROL VALVE FOR OPERATION AND CONDITION AND PERFORMED FORWARD/AFT HEAT AND SMOKE DETECTION TEST. ALL TEST NORMAL. PERFORMED CHAPTER 5 CONDITIONAL INSPECTION FOR HIGH ENERGY STOP. (M)

Part: LIGHT — FAULTY (CARGO BAY)

AIRCRAFT ATB DUE TO LOWER AFT CARGO AND BULK CARGO COMPARTMENT FIRE WARNING INDICATION. PERFORMED TROUBLE SHOOTING PER MM 26-16-00 AND FOUND NR 4, NR 5 AND NR 6 SMOKE DETECTOR LAMPS AT FAULT. REMOVED AND REPLACED LAMPS AND PERFORMED SYSTEM TEST. ALL OPS OK. (M)

Part: DUCT — LEAKING (NR 4 ENGINE)

MIA/BOG -ATB - FLT GT063/06 - ENGINE A-LOOP FIRE WARNING FLUCTUATED, B-LOOP READ 4-5 STEADY. ENGINE SHUT DOWN AND FLIGHT RETURNED TO MIA. MIA MAINTENANCE FOUND PRESSURE REGULATOR VALVE AND DUCT LEAKING. REPLACED BOTH PRV, DUCT AND CLAMPS. OPERATIONAL CHECK OF B-LOOP SATISFACTORY. A-LOOP STILL SPIKES AND DEFERRED PER DDPG. AIRCRAFT RELEASED FOR FLIGHT. ADDITIONAL PART INFO: PN 65B94813-2. (X)

Part: BULKHEAD — CORRODED (FUSELAGE)

DURING INSPECTION, FOUND THE LOWER END OF THE CANTED BULKHEAD PRESSURE WEB AT STATION 1241 CORRODED FROM LBL 11.33 TO 65. REMOVED CORROSION IN AREA PER SRM 51-10-01. FABRICATED REPAIR WEB, DOUBLERS, REINFORCING ANGLES AND FILLERS. INSTALLED IAW KLM 747-2001-046 REV 08 REPAIR INSTRUCTIONS. (M)

Part: FLOORBEAM — DAMAGED (FUSELAGE)

AFTER REMOVAL OF SEAT TRACK, FOUND FLOORBEAM 1840-1860 UPPER CHORD FASTENER HOLES AT LBL 98.5 ELONGATED. REAMED HOLES, PERFORMED E/C CHECK. NO CRACKS FOUND. FABRICATED REPAIR ANGLES. SPLICED IN REPLACEMENT WEB AND STIFFENERS PER SRM 51-30-02. INSTALLED REPAIR ANGLES PER KLM REPAIR ORDER KLM 747-2001-045. (M)

Part: FLOORBEAM — DAMAGED (FUSELAGE)

AFTER REMOVAL OF SEAT TRACK, FOUND FLOORBEAM 1840-1860 UPPER CHORD FASTENER HOLES AT LBL 98.5 ELONGATED. REAMED HOLES, PERFORMED E/C CHECK. NO CRACKS FOUND. FABRICATED REPAIR ANGLES. SPLICED IN REPLACEMENT WEB AND STIFFENERS PER SRM 51-30-02. INSTALLED REPAIR ANGLES PER KLM REPAIR ORDER KLM 747-2001-045. (M)

Part: FRAME — DENTED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME DENTED AT STATION 1840 STRINGER 12 AND 13R. TRIMMED AWAY DAMAGE. FABRICATED REPAIR DOUBLERS, FILLERS AND SHEAR TIE. INSTALLED PER STANDARD PRACTICES. (M)

Part: FLAP TRACK — CORRODED (NR 6 FLAP)

DURING ROUTINE INSPECTION, FOUND NR 6 INBOARD FLAP TRACK REAR SPAR FORWARD AFT ATTACH HOLES CORRODED. CORROSION REMOVED BY MILLING FLANGE THICKNESS TO .8799 AT THE FORWARD HOLES; .8630 AT THE AFT HOLES. FABRICATED NEW BEARING PLATES. REWORK AREA TREATED, PAINTED, FLAP TRACK INSTALLED. (M)

Part: SKIN — WORN (NR 3 PYLON)

DURING ROUTINE INSPECTION, FOUND NR 3 PYLON SKIN WORN AT NAC STATION 290 WL 145 R/S ACCESS PANEL. TRIMMED OUT WORN AREA. FABRICATED FILLER FROM CRES STEEL 301.5 HARD AND ALUMINUM DOUBLER. INSTALLED PER STANDARD PRACTICES. (M)

Part: FRAME — DENTED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME DENTED AT STATION 1860 STRINGER 12 AND 13R. TRIMMED AWAY DAMAGE. FABRICATED REPAIR DOUBLER, FILLERS AND SHEAR TIE. INSTALLED PER STANDARD PRACTICES. (M)

Part: SHEAR TIE — CRACKED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUN FRAME SHEAR TIE CRACKED IN RADIUS BETWEEN STATION 340-360 R/S AT MAIN DECK LEVEL (WBL200). TRIMMED DAMAGE AREA. MANUFACTURED REPAIR ANGLES AND FILLER. INSTALLED PER STANDARD PRACTICES WITH RIVETS BACR15BB5AD. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME WEB CRACKED AT STATION 360 R/S STRINGER 15 AND 16R. TRIMMED DAMAGE AREA OF WEB. MANUFACTURED REPAIR ANGLES, FILLERS, STRAPS. INSTALLED PER STANDARD PRACTICES USING BACB30MY6K FASTENERS AND BACC30M COLLARS. (M)

Part: SKIN — CORRODED (RT WING)

DURING ROUTINE INSPECTION, FOUND UPPER WING SKIN CORRODED AT BS 1140, FROM RBL 57 TO RBL 98. REMOVED CORROSION PER SRM 51-10-01, FOUND AREAS FROM RBL 57-87 WITHIN LIMITS PER 57-30-01. AREA FROM RBL 88 TO 98 WAS BLENDED PER REPAIR INSTRUCTIONS, FASTENERS REMOVED AND HOLES OVERSIZED. HFEC INSPECTION PERFORMED, AREA TREATED AND VAPOR BARRIER SEALED PER SRM 51-10-06. (M)

Part: SEAT TRACK — SCRATCHED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND SEAT TRACK GOUGED/SCRATCHED AT LBL 98.58 BETWEEN STATION 1030 AND 1135. ALL AREAS BLENDED PER SRM 51-10-01. HFEC INSPECTION PERFORMED. ALL FOUND WITHIN LIMITS PER SRM 53-10-01. FOUND SEAT TRACK LBL 75.92 GOUGED/SCRATCHED AT STATION 1222. SEAT TRACK LUGS AFTER BLENDING WERE BELOW LIMITS PER SRM 53-10-01. REPAIR SCHEME REMOVED LUGS AT THIS LOCATION TO PREVENT FUTURE USE OF THIS LOCATION. (M)

Part: FRAME — DENTED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND OUTER CHORD DAMAGED/DENTED AT BS 1680 STRINGER 15R. TRIMMED AWAY DAMAGE. MANUFACTURED FILLER, REPAIR DOUBLER AND STRAPS. INSTALLED IAW SRM 53-10-04. (M)

Part: FRAME — DENTED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME DENTED AT STATION 1760 STRINGER 13R. TRIMMED AWAY DAMAGE. FABRICATED REPAIR DOUBLERS, FILLERS AND SHEAR TIE. INSTALLED PER STANDARD PRACTICES. (M)

Part: FRAME — CRACKED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME WEB CRACKED AT STATION 360 R/S STRINGER 23R CUT OUT. ROUTED CRACKED AREA OF WEB. MANUFACTURED REPAIR DOUBLER AND FILLERS. INSTALLED IAW 747-53A2265 WITH OVERSIZED RIVETS BACR15BB6D. (M)

Part: SEAT TRACK — SCRATCHED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND SEAT TRACK GOUGED/SCRATCHED AT LBL 75.92 BETWEEN STATION 1320 AND 1460. ALL AREAS BLENDED PER SRM 51-10-01. HFEC INSPECTION PERFORMED. ALL WITHIN LIMITS PER SRM 53-10-01. AT STATION 1450 SEAT TRACK LUGS AFTER BLENDING WERE BELOW LIMITS PER SRM 53-10-01. REPAIR SCHEME REMOVED LUGS AT THIS LOCATION TO PREVENT FUTURE USE OF THIS LOCATIONS. (M)

Part: SKIN — CORRODED (LT WING)

DURING ROUTINE INSPECTION, FOUND UPPER SURFACE OF LOWER LEFT WING SKIN CORRODED AFT REAR SPAR WS 235. REMOVED FASTENERS FROM THE TRAILING EDGE ATTACH FITTING. AREA BLENDED, TREATED AND PAINTED IAW 57-30-01. A REPLACEMENT FILLER BLOCK AS FABRICATED AND INSTALLED UNDER THE ATTACH FITTING. (M)

Part: FRAME — DENTED (FUSELAGE)

DURING ROUTINE INSPECTION, FOUND FRAME DENTED AT STATION 1820 STRINGER 12R. TRIMMED AWAY DAMAGE. FABRICATED REPAIR DOUBLERS, FILLERS AND SHEAR TIE. INSTALLED PER STANDARD PRACTICES. (M)

Part: SKIN — DAMAGED (R4 DOOR)

FLT GT065 - ATB - APPROX 3.5 HOURS INTO THE FLIGHT, AND ADDITIONAL CARGO CHECK WAS MADE AN A HOLE APPROXIMATELY 1 FT SQUARE WAS DISCOVERED AT THE BOTTOM LEFT CORNER OF R4 MED. AIRCRAFT WAS AT FL 33, PRESSURIZATION WAS NORMAL (8.3). AFTER AIRCRAFT RETURNED TO MIA, INSPECTED FUSELAGE AND TAIL SECTION FOR FOD DAMAGE AND NONE FOUND. REPLACED R4 MED DOOR IAW MM 52-11-01. OPS CHECK AND LEAK CHECK NORMAL. (M)

Part: PDU — DEFECTIVE (NR 4 LE FLAP)

ATB - FLT MIA-BOG - ON FLAP RETRACTION AFTER TAKEOFF, NR 4 LE ON LEFT DID NOT INDICATE UP. USED ALTERNATE SYSTEM, BUT STILL DID NOT INDICATE UP. SCANNED LED'S VISUALLY WITH FLAPS SELECTED TO 0 AND 1 DEGREE POSITIONS. LEFT INBOARD LED SECTION DID NOT APPEAR TO MOVE. DUMPED APPROX 25 KGS FUEL AND RETURNED TO MIA, NORMAL LANDING. ON APPROACH, LED WENT GREEN. AFTER LANDING WHEN FLAPS SELECTED UP, NR 4 LEFT LED DID NOT RETRACT FOR 15 MINUTES. REPLACED NR 4 LE PDU AND PERFORMED FUNCTIONAL AND LEAK CHECKS, ALL NORMAL. (M)