N887MA

Part: BEARING — FROZEN (T/E FLAP)

DURING CLIMB-OUT FROM NGU, UPON RETRACTING FLAPS INBOARD FLAPS STUCK AT 15 DEGREES. ACCOMPLISHED ABNORMAL PROCEDURES, NO HELP. RETURNED TO NGU. FOUND RIGHT INBOARD FLAP INBOARD JACKSCREW FAIRING (ELEPHANT EAR) BEARING FROZEN. CLEANED BEARING AND LUBED IAW MM 12-22-01. OPS CHECK OK. AIRCRAFT RETURNED TO SERVICE. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

ON PREFLIGHT TRANSIT, FOUND RIGHT FORWARD OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. REMOVED AND REPLACED EMERGENCY EXIT LIGHT BATTERY PACK IAW MM 33-50-01. OPS CHECK OK. (M)

Part: LINE — CRACKED (NR 2 ENGINE)

IN FLIGHT NR 2 ENGINE BEGAN LOSING OIL AT RATE OF 1 QUART EVERY 9 MINUTES. REDUCED THRUST DID NOT AFFECT RATE. SHUT DOWN ENGINE WITH 1 GALLON REMAINING. ENGINE WINDMILLED 30 MINUTES, OIL PRESSURE 42 PSI. T/S ENGINE, FOUND NR 2 ENGINE NR 2 BEARING LINE CRACKED AT B-NUT FITTING. REMOVED AND REPLACED LINE. REMOVED AND REPLACED MAIN OIL SCREEN. PERFORMED ENGINE POWER RUN AT TAKEOFF POWER. NO LEAKS NOTED IAW 71-00-00 AND 79-00-00. RESERVICED OIL AS REQUIRED. (M)

Part: ACCUMULATOR — RUPTURED (RT WHEEL WELL)

UPON LANDING AT PHL LOST HYD BRAKE PRESSURE FROM SYSTEM A/B. UTILIZED PNEUMATIC SYSTEM TO STOP AIRCRAFT. ON INSPECTION FOUND RUPTURED HYD BRAKE ACCUMULATOR IN RIGHT WHEEL WELL WITH SUBSEQUENT STRUCTURAL DAMAGE TO RT MAIN GEAR DOOR, HYD LINES ABOVE ACUMULATOR AND PULLEY AND PULLEY GUARD DIRECTLY BELWO ACCUMULATOR. REPLACED HYD BRAKE ACCUMULATOR IAW MM 32-41-61. OPS AND LEAK CHECK OK. REPAIRED DAMAGE TO R MLG DOOR IAW SRM 52-80-1. REPLCED PULLEYS AND PULLEY GUARD IAW MM 20-10-20. OPS CHECK GOOD. REPAIRED HYD LINES IAW MM 20-10-5 LEAK CHECK GOOD. REPLACED BOTH A/B SYSTEM ELECTRIC AND ENGINE DRIVEN PUMPS IAW MM 29-11-32 AND 29-12-11. OPS AND LEAK CHECK OK. AIRCRAFT RETURNED TO REVENUE SERVICE. (M)

Part: BATTERY PACK — DISCHARGED (SERVICE DOOR)

DURING A-CHECK, FOUND L-2 DOOR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED BATTERY PACK, OPS TEST NORMAL IAW MM 33-50-01. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING PREFLIGHT, TRANSIT FOUND LEFT FORWARD OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED OVERWING BATTERY PACK. OPS TEST NORMAL IAW MM 33-50-22. (M)

Part: RELIEF VALVE — FAILED (GEARBOX)

DURING TAKEOFF AND CLIMB-OUT FROM MIA, NR 3 ENGINE OIL PRESSURE INCREASED TO 85 PSI. REDUCED THROTTLE TO IDLE AND PRESSURE DECREASED THEN INCREASED TO 90 PSI. SHUTDOWN NR 3 ENGINE THEN FOLLOWED AOM ABNORMAL PROCEDURES AND DECLARED EMERGENCY. RETURNED TO MIA AND LANDED AIRCRAFT WITHOUT INCIDENT. REMOVED AND REPLACED NR 3 ENGINE OIL PRESS XMITTER. NO HELP. REINSTALLED OLD XMITTER IAW MM 79-32-0. INSPECTED OIL STRAINER, FOUND CLEAN. ADJUSTED PRESS RELIEF IAW 72-00. TESTED ENGINE IAW 71-00-0. AIRCRAFT RETURNED TO SERVICE. (M)

Part: O-RING — DAMAGED (NR 3 ENGINE)

LOG PAGE 37837. ON TAKEOFF ALL NORMAL, THEN NR 3 ENGINE OIL PRESSURE WENT TO 65 PSI CONSTANT. RETURNED TO MIAMI, DID NOT SHUT DOWN ENGINE AND NO EMERGENCY DECLARED. CANCELLED FLIGHT. FOUND O-RING ON PRESSURE RELIEF VALVE DAMAGED, REPLACED O-RING. AS PRECAUTION, REPLACED PRESSURE RELIEF VALVE PER MM 79-32-0. P/N 626447. OPS CHECK ON RUN-UP OK PER MM 71-00-0. RETURNED AIRCRAFT TO SERVICE. (X)

Part: RIB — CRACKED (LT WING)

FOUND .5 INCH CRACK AT LEFT WING TRAILING EDGE RIB, FROM AFT END TO RIVET HOLE, JUST FORWARD OF OUTBOARD AILERON OUTBOARD HINGE AREA. REMOVED DAMAGED ANGLE AND FABRICATED NEW ANGLE, TREATED, PRIMED AND PAINTED. INSTALLED IAW 51-40-3. (M)

Part: BRACKET — CRACKED (RT MLG)

RT MLG DEBOOSTER VALVE BRACKET CRACKED AT TOP CENTER EDGE. STOP DRILLED CRACK, HFEC TO VERIFY CRACK CONTAINMENT. INSTALLED REPAIR PER SRM 51-40-2 FIG 1 SHEET 4. (M)

Part: SKIN — CORRODED (LT WING)

LEFT WING LOWER SKIN HAS CORROSION IN SEVEN LOCATIONS BETWEEN WING STATION 165 AND WING STATION 270 BELOW FRONT SPAR. REMOVED CORROSION FROM SEVEN LOCATIONS BLENDED DAMAGE, COLD WORKED HOLES, FLAP PEENED SURFACE AND REPLACED FASTENERS PER BOEING INSTRUCTION MIB-MIA-99-00018H. (M)

Part: ANGLE — CRACKED (LT WING)

FOUND 1.25 INCH CRACK AT ANGLE INSIDE LEFT WING TRAILING EDGE AT OUTBOARD END OF AFT FALSE SPAR ACCESS THROUGH PANEL 8407. REMOVED ANGLE AND FABRICATED REPLACEMENT ANGLE AND INSTALLED IAW 51-10-1. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 950B TO STATION 990, LBL 24. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 2. (M)

Part: SKIN — CRACKED (LT WING)

FOUND .3125 INCH CRACK AT LEFT WING, UPPER SURFACE AT NR 4 OUTBOARD HOOK CUTOUT, AT AFT OUTBOARD CORNER. STOP DRILLED CRACK, PERFORMED HIGH FREQUENCY EDDY CURRENT TO ENSURE CRACK CONTAINMENT. REPAIR INSTALLED PER SRM 57-30-4. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 950B TO STATION 990, RBL 45. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 1. (M)

Part: SKIN — PUNCTURED (JACK PAD)

FOUND SKIN PUNCTURED NEAR FORWARD JACK PAD. REPAIRED SKIN PER BOEING INSTRUCTION MIA-99-00029H. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 950B TO STATION 990 RBL 24. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 1 SHEET 4. (M)

Part: FAIRING — CRACKED (RT WING)

NR 5 FLAP TRACK MOVEABLE FAIRING, FORWARD RIB CRACKED AT LOCK BOLT SAFETY WIRE HOLE. INSTALLED REPAIR PER SRM 51-40-3 PAGE 3. (M)

Part: SKIN — CRACKED (NR 6 LE SLAT)

NR 6 SLAT OUTBOARD, HOOK CUTOUT CRACKED. INSTALLED REPAIR PER SRM 57-30-4 FIG 9. (M)

Part: RIB — CRACKED (TE FLAP)

FOUND .625 INCH CRACK IN INBOARD MOST RIB OF THE LEFT OUTBOARD MIDFLAP. STOP DRILLED CRACK, HFEC TO VERIFY CRACK CONTAINMENT. INSTALLED REPAIR PER SRM 51-40-2 FIG 1 SHEET 4. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 680 TO STATION 740 LBL 24. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 7. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 480 TO STATION 690 LBL 24. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 7. (M)

Part: BRACKET — CRACKED (RT WING)

FOUND BRACKET CRACKED AT RIGHT WING LOWER TRAILING EDGE SUPPORT, OUTBOARD OF NR 6 FLAP TRACK. REMOVED DOUBLER FABRICATED NEW DOUBLER PER SRM 51-40-2 FIG 1. (M)

Part: FLANGE — CORRODED (MLG WW)

APU AIR INLET SCREEN MOUNTING FLANGE CORRODED ALONG BOTTOM FLANGE. FABRICATED REPLACEMENT FLANGE (ANGLE) PER SRM 51-10-1. (M)

Part: FRAME — CRACKED (RT WING)

WING TRAILING EDGE CHORD ANGLE CRACKED BELOW NR 8 SPOILER (WBL 125.0). REPAIRED CRACK PER BOEING SERVICE BULLETIN 727-57-158 R1. (M)

Part: RIB — CRACKED (LT WING)

FOUND 1 INCH CRACK IN RIB ADJACENT TO CENTER FOREFLAP TRACK GUIDE, LEFT INBOARD MIDFLAP. REMOVED AND REPLACED FLAP ASSY WITH SERVICEABLE UNIT. (M)

Part: SKIN — CRACKED (VERTICAL STAB)

FOUND NR 2 S DUCT ANTI-ICE INNER SKIN CRACKED AT LOWER CORNER. LOCATED IN FORTH COMPARTMENT DOWN FROM V STABILIZER ACCESS PLATE. STOP DRILLED DRILLED CRACK AND INSTALLED REPAIR PER SRM 51-40-2 PAGE 6. (M)

Part: STRINGER — CRACKED (VERTICAL STAB)

FOUND STRINGER CRACKED IN COMPARTMENT ABOVE FIN STATION 133.8, STRINGER IS FIFTH UP FROM BOTTOM OF COMPARTMENT. INSTALLED REPAIR PER SRM 55-30-1 FIG 1. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 950B TO STATION 990, RBL 45. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 1. (M)

Part: SEAT TRACK — GOUGED (CABIN)

FOUND CABIN SEAT TRACK WORN, GOUGED AND CORRODED STATION 480 TO STATION 690 LBL 45. REPLACED SEAT TRACK PER SRM 53-10-5 FIG 7. (M)

Part: SUPPORT BRACKET — CORRODED (CABIN)

FOUND CABIN R1 DOOR SILL 4 EACH SUPPORT BRACKETS CORRODED. FABRICATED NEW BRACKETS AND REPLACED PER SRM 51-10-1. (M)

Part: FLOORBEAM — CORRODED (FUSELAGE)

FOUND CABIN FLOORBEAM AT STATION 1130, RBL 36, CORROSION AROUND SCREW HOLES. REPAIRED FLOORBEAM PER JOSSAIR DWG NR 72R5371137 FROM LBL 65 TO RBL 65. (M)

Part: WIRE — SHORTED (CABIN)

FORWARD E-PATH LIGHT STRIP INOPERATIVE ON TEST. REPLACED SHORTED WIRING CABLE LEAD ASSY. (M)

Part: RIB — CRACKED (NR 6 SLAT)

FOUND NR 1 INCH CRACK AT BOTTOM OF RIB NR 6 SLAT ADJACENT TO INBOARD SIDE OF ACTUATOR ROD END ATTACHMENT. STOP DRILLED CRACK AND INSTALLED REPAIR PER SRM 51-40-3. (M)

Part: SKIN — CRACKED (LE FLAP)

FOUND .5 INCH CRACK AT LEADING EDGE OF RIGHT OUTBOARD FORE FLAP ADJACENT TO NR 7 FLAP TRACK. STOP DRILLED CRACK, FABRICATED DOUBLER AND INSTALLED PER SRM 57-50-4 FIG 7. (M)

Part: SKIN — CRACKED (LE FLAP)

FOUND .375 INCH CRACK IN LOWER SURFACE OF RIGHT OUTBOARD FORE FLAP AT THE OUTBOARD ATTACHMENT AREA. INSTALLED REPAIR PER SRM 57-50-4 FIGURE 7. (M)

Part: BRACKET — CRACKED (RT WING)

FOUND 3 INCH CRACK IN NR 8 JACKSCREW FARING AT AFT MOUNT. REMOVED DAMAGED BRACKET AND FABRICATED REPLACEMENT PART. (M)

Part: SKIN — CRACKED (NR 6 LE SLAT)

NR 6 SLAT INNER SKIN CRACKED AT FASTENER. INSTALLED REPAIR PER SRM 57-50-3 FIG 1. (M)

Part: SKIN — MISREPAIRED (BS 333-360)

PREVIOUS DOUBLER REPAIR AT FORWARD RIGHT JACK PAD AREA, STR 19R TO STR 24R STA 333 TO STA 360 DO NOT HAVE PROVISIONS FOR JACK PAD (HOLES). FOUND DURING SCHEDULED C-MAINTENANCE CHECK.

Part: FLOORBEAM — CORRODED (BS 1130)

CABIN FLOORBEAM AT STA 1130 RBL 36 HAS CORROSION AROUND SCREW HOLES. FOUND DURING SCHEDULED C-MAINTENANCE CHECK. SUBMITTER STATED POSSIBLE CAUSE AS LIQUID SPILLS OR DISSIMILAR METAL.

Part: BEAM — CRACKED (RT WING)

RIGHT WING TRAILING EDGE J-BEAM CRACKED (.3750 INCH) ABOVE NR 8 SPOILER ACTUATOR. FOUND DURING SCHEDULED C-MAINTENANCE CHECK. SUBMITTER SUGGESTED POSSIBLE CAUSE AS DESIGN FLAW OR WING FLEXING LOADS.

Part: FLOORBEAM — CORRODED (BS 344)

CABIN FLOORBEAM STA 344 RBL 24 TO WALL HAS CORROSION. FOUND DURING SCHEDULED C-MAINTENANCE CHECK. SUBMITTER STATED POSSIBLE CAUSE AS LIQUID SPILLS OR DISSIMILAR METAL.

Part: ANGLE — CRACKED (RT WING)

LOWER TRAILING EDGE PANEL BELOW NR 8 SPOILER ACTUATOR (FALSE SPAR) LOWER CHORD ANGLE CRACKED. FOUND DURING SCHEDULED C-MAINTENANCE CHECK. SUBMITTER SUGGESTED POSSIBLE CAUSE AS WING FLEXING LOADS.

Part: CRANK — OUT OF POSITION (LANDING GEAR)

AFTER TAKEOFF FROM BOS, NOSE GEAR WOULD NOT RETRACT. VISUAL INSPECTION OK. CYCLED GEAR NO HELP. RETURNED TO BOS, LANDED WITHOUT INCIDENT. FOUND MANUAL EXTENSION CRANK WAS NOT SET TO NEUTRAL POSITION, PREVENTING NOSE GEAR FROM GOING UP DURING NORMAL RETRACTION. PLACED CRANK IN NEUTRAL POSITION IAW 32-34-00 PAGE 11. PERFORMED NORMAL EXTENSION/RETRACTION TEST IW 32-30-00 PAGE 501-503. VISUALLY INSPECTED NLG MANUAL EXTENSION SYSTEM IAW 32-34-11, 32-34-51 AND 32-34-71. NO DEFECTS NOTED. RETURNED AIRCRAFT TO SERVICE. (M)

Part: LINE — LEAKING ('A' HYD MODULE)

AT CRUISE ALTITUDE FROM MYR TO BFD HAD 'A' SYSTEM DECREASED TO '0' SYSTEM LIGHTS CAME 'ON'. CONDUCTED EMERGENCY PROCEDURES. LOWERED GEAR BY MANUAL PROCEDURES. DIVERTED TO BOS. LANDED WITHOUT INCIDENT. FOUND HYD LINE TO 'A' SYSTEM MODULE LEAKING. REPLACED LINE WITH FLEX LINE PER 20-10-5, PAGE 855 ITEM 10. REPLACED NR 1 AND NR 2 ENGINE 'A' SYSTEM FILTERS. RAN ALL SYSTEMS, NO LEAKS. SERVICED HYD OK FOR SERVICE. HYD LINE REPLACED AT BOS IS TEMP REPAIR, TRANSFERRED TO DMI NR 7002. AIRCRAFT RETURNED TO SERVICE. (M)

Part: ECCENTRIC — MISSING (LT TE FLAP)

DURING P/T WALK AROUND LEFT WING INBOARD T/E MID FLAP CARRIAGE MISSING UPPER INBOARD ECCENTRIC, LOCKING TAB WASHER AND NUT ON OUTBOARD CARRIAGE. REPLACED CARRIAGE UPPER ECCENTRIC AND NUT ON LEFT WING INBOARD TRAILING EDGE FLAP IAW 27-51-2. OPS CHECK OK. (M)

Part: GEAR BOX — LEAKING (NR 1 ENGINE)

WHILE CLIMBING THROUGH 1,500 FT OIL QUANTITY GAUGE ON NR 1 ENGINE WAS IDENTIFIED AS LOSING OIL. CLIMBED TO 5,000 (CLEAN CONFIGURATION) DECLARED AN EMERGENCY WITH ATC. TURNBACK TO MIA. ENGINE WAS SHUTDOWN, ALL AOM PROCEDURES COMPLIED WITH. REPLACED GARLOCK SEAL FOR STARTER ON ENGINE NR 1 IAW MM 72-61-00, OPS CHECK AND LEAK CHECK OK. (M)

Part: GEAR BOX — LEAKING (NR 1 ENGINE)

WHILE CLIMBING THROUGH 13,000 FEET OIL QUANTITY GAUGE ON NR 1 ENIGNE WAS IDENTIFIED AS LOSING OIL. TURNBACK TO MIA, PRIOR TO TURNBACK SWAPPED OIL GAUGES TO VERIFY OIL LOSS. ENGINE SHUT DOWN ALL AOM PROCEDURES COMPLIED WITH. FOUND OIL RETURN LINE TO GEAR BOX LEAKING, REPLACED PACKIGN AND HELI-COIL PER MM 79-20-0. OPERATIONAL CHECKED OK. HELI-COIL REPLACEMENT PER OHM 72-61-01. (M)

Part: LIGHT — INOPERATIVE (CABIN)

DURING PREFLIGHT INSPECTION, FOUND FORWARD ENTRANCE EMERGENCY EXIT LIGHT AT BOTTOM RT SIDE INOP. FOUND CONNECTION UNDER LIGHT DIRTY, CLEANED AND REINSTALLED. OPS CHECK GOOD 33-30-10. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

FORWARD TWO FLASHLIGHT BATTERY PACKS ARE INOP. REMOVED AND REINSTALLED TWO FLASHLIGHT BATTERY PACKS, P/N P4-01-0021. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT TWO FLASHLIGHT BATTERY PACKS ARE INOP. REMOVED AND INSTALLED TWO FLASHFLIGHT BATTERY PACKS, P/N P4-01-0021. (M)

Part: FIRE LOOP — FAILED (NR 1 ENGINE)

ON CLIMB-OUT AT 7000 FT, FIRE WARNING GELL WENT OFF WITH NO LIGHTS. DUMPED FUEL AND RETURNED TO PUJ. NR 1 ENGINE LIGHT FLICKERED WHEN TESTING. INSPECTED FIRE DETECTION SENSOR FOR CONDITION AND SECURITY. FOUND ENGINE NR 1 CONNECTOR AT SENSING ELEMENT CONTAMINATED WITH DIRT/OIL, CLEANED CONNECTOR AND SECURED. (M)

Part: CONNECTOR — CONTAMINATED (NR 3 ENGINE)

AFTER TAKEOFF FROM IQT AND AT 15,000 FEET FIRE WARNING BELL SOUNDED WITH NO LIGHT, WENT THROUGH AOM PROCEDURES AND RETURNED TO IQT. TROUBLESHOT FIRE WARNING SYSTEM AND FOUND AFT FIRE WARNING SENSOR CONNECTOR ON NR 3 ENGINE, CONTAMINATED WITH OIL. CLEANED CONNECTOR AND RESAFTIED. OPS TESTED FIRE WARNING SYSTEM, OPS CHECKED NORMAL. (M)

Part: OIL TANK CAP — MISSING (NR 2 ENGINE)

FLT 549 - MIA - AFTER TAKEOFF DURING CLIMB-OUT, OIL QTY ON NR 2 ENGINE DECREASED FROM 4 TO 2 GALLONS. FOUND OIL SERVICE CAP OFF. SERVICED TANK AND REPLACED CAP. (M)

Part: FUEL PUMP — FAILED (NR 1 ENGINE)

BOS - FLT GL501 - WHILE DESCENDING THROUGH 16,000 FEET WITH NR 1 ENGINE AT IDLE, GB ILLUMINATED. CHECKED ALL PARAMETERS. ENGINE FLAMED OUT. SHUT DOWN IAW EMERGENCY PROCEDURES. ATTEMPTED IN-FLIGHT RESTART IAW ABNORMAL PROCEDURES. NO FUEL FLOW. COMPLETE ENGINE SHUTDOWN EMERGENCY PROCEDURES. REPLACED NR 1 ENGINE FUEL CONTROL AND FUEL PUMP. NOTE: THE OUTBOUND FLIGHT, GL612, WAS CANCELLED (OPERATIONAL DECISION) AND RESCHEDULED TO 0730 LOCAL TIME ON 2-19-96.

Part: OVERHEAT LOOP — OUT OF POSITION (NR 3 ENG STRUT)

LOG REPORT: F-GL534 AT CHS, ON TAKEOFF ROLL, NR 3 ENGINE STRUT OVERHEAT LIGHT ILLUMINATED. ABORTED TAKEOFF. LIGHT WENT OUT ON POWER REDUCTION. INSPECTION OF NR 3 ENGINE STRUT FOUND OVERHEAT LOOP TOUCHING DUCT ASSY. REPOSITIONED OVERHEAT LOOP. PEFORMED LEAK CHECK PER MM 36-10, AND ENGINE RUN IAW MM 72-10. NO LEAKS FOUND AND NO OVERHEAT LIGHT ILLUMINATED. ALL SYSTEMS OPERATE NORMAL. NOTE: THE DELAY OF 60 MINUTES WAS INCURRED. THIS WAS A POSITIONING FLIGHT.

Part: BOLT — SHEARED (NR 3 WHEEL ASSY)

ON POST FLT INSPECTION, FOUND NR 3 TIRE/WHEEL ASSEMBLY MISSING FROM AIRCRAFT. REPLACED NR 3 AXLE SLEEVE AFTER AXLE INSPECTION. REPLACED NR 3 AND NR 4 BRAKES. REPLACED THE NR 3 AND NR 4 TIRE/WHEEL ASSEMBLIES. ACCOMPLISHED TIRE BURST INSPECTION IAW MM 32-40-0 AND CHAPTER 5. REPLACED NR 3 AXLE NUT, SPACER AND NUT LOCKING BOLTS. INSPECTED AIRCRAFT, NO DAMAGE NOTED. ON TOUCHDOWN, ANOTHER AIRCRAFT REPORTED TIRE/WHEEL ASSEMBLY DEPARTING THE AIRCRAFT. INVESTIGATION REVEALS WHEEL NUT LOCKING BOLT, PN NAS 6704-3, SHEARED RESULTING IN THE WHEEL NUT LOSING ITS TORQUE RESULTING IN THE TIRE/WHEEL ASSEMBLY DEPARTING THE AIRCRAFT.

Part: FUEL PUMP — SHEARED (SHAFT)

UPON TAKEOFF ROLL, AT APPROXIMATELY 60 KNOTS, ENGINE NR 2 FAILED. ALL ENGINE NR 2 INDICATIONS WERE NORMAL AT TIME OF FAILURE. AOM PROCEDURES 2-E-2, 2-A-9-1, AND 2-A-6-2 WERE FOLLOWED. NR 2 ENGINE INOP, TRANSFERRED TO DMI, LOG SLIP NR 1690 IAW MEL 78-1. NR 2 T/R BLOCKED PER MM 78-30-00. INSTALLED PLACARD. GMM FORM M-14C FOLLOWED FOR FERRY FLIGHT PREPARATIONS. AT MIA, FOUND ENGINE DRIVEN FUEL PUMP FAILED. REPLACED THE FUEL PUMP AND THE FCU (AS PRECAUTIONARY). NOTE: MAINTENANCE DELAY: 2 HRS 53 MIN.