N199AJ

Part: FLOOR SUPPORT — CORRODED (BS 740-848) · airframe 68,146 hrs · 47,635 cycles

MAIN CARGO, LT CENTER FLOOR SUPPORT SHOWS CORROSION AT SEVERAL PLACES AT FROM BS 740-848.95, RBL 24.75.

Part: STRAP — CORRODED (FUSELAGE) · airframe 68,146 hrs · 47,635 cycles

LT MLG, OTBD DOOR STRAP SHOWS CORROSION.

Part: SPAR — CORRODED (HORIZONTAL STAB) · airframe 68,146 hrs · 47,635 cycles

LT HORIZONTAL STABILIZER REAR SPAR SHOWS CORROSION BETWEEN 218 AND 214.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RT WING UPPER OUTER SKIN SHOWS CORROSION AT SEVERAL PLACES BETWEEN RWBL 92.8 AND WS 224.5.

Part: FRAME — CORRODED (BS 1183 BULKHEAD) · airframe 68,146 hrs · 47,635 cycles

AFTER CARGO BAY, LOWER FUSELAGE BULKHEAD FRAME SHOWS CORROSION AT BS 1183, LBL 17.81, WL 175.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 738.5 - 760.5.

Part: FORMER — CORRODED (THRUST REVERSER) · airframe 68,146 hrs · 47,635 cycles

NR 1 ENGINE, THRUST REVERSE FWD SIDE EXTERIOR FORMER CORRODED AT STA 96.25 AT 5 O´CLOCK POSITION.

Part: WINDOW FRAME — CORRODED (BS 804.5-825.95) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN 804.5-825.95, RT SIDE.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 130.7 AND 171.5.

Part: SPAR — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER FRONT SPAR SHOWS CORROSION WS 383.5-357.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 357- 330.5.

Part: WINDOW FRAME — CORRODED (BS 870-890) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN 870 AND 890, RT SIDE.

Part: WINDOW FRAME — CORRODED (BS 890-910) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN BS 890 AND 910 RT SIDE.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RT WING L/E UPPER SKIN SHOWS CORROSION AT WS 130.7.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 686.5 AND WS 716.5.

Part: SPAR — CORRODED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING FRONT SPAR LOWER ANGLE SHOWS CORROSION BETWEEN WS 410 AND 436.5.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER SKIN 7701 ACCESS PANEL SHOWS CORROSION AROUND FASTENERS.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING NR 6 INNER PANEL SHOWS CORROSION BETWEEN WS 464- 574.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER SKIN 7617 ACCESS PANEL SHOWS CORROSION AROUND FASTENERS.

Part: LATCH — CRACKED (NR 1 NACELLE) · airframe 68,146 hrs · 47,635 cycles

NR 1 ENGINE, UPPER COWLING FITTING LATCH ATTACHMENT CRACKED ONE INCH.

Part: WINDOW FRAME — CORRODED (BS 848.5-870) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN BS 848.5 AND 870, RT SIDE.

Part: WINDOW FRAME — CORRODED (BS 720F-740) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR LT SIDE, PLUGGED WINDOWS AREA SHOWS CORROSION BETWEEN BS 720F AND 740.

Part: SKIN — CORRODED (BS 680-700) · airframe 68,146 hrs · 47,635 cycles

LOWER FUSELAGE INNER SKIN SHOWS CORROSION BETWEEN BS 680-700, STRINGER 28 LT.

Part: WINDOW FRAME — CORRODED (BS 910-930) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN BS 910-930 RT SIDE.

Part: FITTING — WORN (FLAP FAIRING) · airframe 68,146 hrs · 47,635 cycles

RT WING OTBD FLAP FAIRING AFT FITTING WORN.

Part: DOOR FRAME — CORRODED (EMERGENCY EXIT) · airframe 68,146 hrs · 47,635 cycles

MAIN CARGO EMERGENCY EXIT HATCH RT FWD DOOR FRAME INFERIOR LOWER PART SHOWS CORROSION AT BS 760.95.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 198 AND 224.5.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER SKIN 7618 ACCESS PANEL SHOWS CORROSION AROUND FASTENERS.

Part: WINDOW FRAME — CORRODED (BS 930-950) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE EXTERIOR, POINTS OF CORROSION AROUND PASSENGERS WINDOW FRAME BETWEEN BS 930-950, RT SIDE.

Part: SKIN — CORRODED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LT WING L/E UPPER SKIN SHOWS CORROSION WBL 92.8-L/E WS 130.7.

Part: SKIN — CORRODED (LT NACELLE) · airframe 68,146 hrs · 47,635 cycles

NR 3 ENGINE, LT UPPER COWLING SKIN SHOWS CORROSION FROM NAC STA. 185.20-194.8.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION BETWEEN WS 574-546.5.

Part: SKIN — CRACKED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING L/E UPPER SKIN CRACKED ONE INCH AT WS 457.5.

Part: SKIN — CORRODED (NR 6 SLAT) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING NR 6 SLAT UPPER SKIN SHOWS CORROSION.

Part: STOP FITTING — CORRODED (EMERGENCY EXIT) · airframe 68,146 hrs · 47,635 cycles

FUSELAGE RT AFT EMERGENCY WINDOW STOP SHOWS CORROSION BETWEEN BS 825.95-848.9.

Part: SKIN — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING LOWER OUTER SKIN SHOWS CORROSION AT WS 436.5.

Part: SKIN — CRACKED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING L/E UPPER SKIN CRACKED ONE INCH AT WS 450.5.

Part: SKIN — CRACKED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING L/E UPPER SKIN CRACKED ONE INCH AT WS 443.5.

Part: SKIN — CRACKED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING L/E UPPER SKIN CRACKED .5 INCH AT WS 325.

Part: SKIN — CRACKED (LT WING) · airframe 68,146 hrs · 47,635 cycles

LEFT WING L/E UPPER SKIN CRACKED .7500 INCH AT WS 410.0, REF NR 0171.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 68,146 hrs · 47,635 cycles

RIGHT WING, ACCESS PANEL LOWER SKIN SHOWS CORROSION AROUND FASTENERS.

Part: CIRCUIT BREAKER — FAILED (COCKPIT) · airframe 68,137 hrs · 47,629 cycles

ON CLIMBOUT, ESSENTIAL T/R C/B, CENTER FWD AND RIGHT AFT NR 2 FUEL PUMP C/C'S POPPED AND PITOT STATIC HEATER OFF LIGHT ILLUMINATED. MAINTEANCE REPLACED THE ESSENTIAL BUS C/B C867 IAW THE SWPM, RESET THE LEFT FWD AND RIGHT AFT NR 2 FUEL PUMP C/B'S. ACCOMPLISHED THE ESSENTIAL TR SYSTEM CHECKS PER THE B727 AMM AND RETURNED THE AIRCRAFT TO SERVICE.

Part: CLAMP — LOOSE (BLEED AIR SYS) · airframe 66,942 hrs · 46,122 cycles

NR 1 STRUT OVERHEAT LIGHT CAME ON AFTER TAKEOFF. PERFORMED COMPANY PROCEDURE, LIGHT WENT OUT AND ILLUMINATED AGAIN. RETORQUED TWO LOOSE BLEED AIR HEAT EXCHANGER CLAMPS. PERFORMED LEAK CHECK, OK.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FRAME ST BS 1110 S24L-S28L CORRODED. REPLACED FRAME SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM UPPER CHORD BS 950E RBL 8-RBL 47 CORRODED. REPLACED FLOORBEAM SECTION.

Part: BEAM — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

RIGHT HORIZONTAL STABILIZER TRAILING EDGE UPPER BEAM ELEVATOR STATION 17.20-209.96 CORRODED. REPLACED BEAM SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM UPPER CHORD BS 620 LBL 18-RBL 45 CORRODED. REPLACED FLOORBEAM SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM UPPER CHORD BS 540 LBL 27-LBL 43 CORRODED. REPLACED FLOORBEAM SECTION.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FUSELAGE STRINGER 12R BS 312-BS 328 CORRODED. REPLACED STRINGER SECTION.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

PRESSURE SEAL RETAINER SUPPORT ANGLE BS 870 LBL 62-RBL 62 CORRODED. REPLACED SUPPORT ANGLES.

Part: STRINGER — CORRODED (LT WING) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

LEFT WING FUEL TANK STRINGER 14 WS 656.50 CORRODED. REPAIRED WITH ANGLE DOUBLER.

Part: STRINGER — CORRODED (RT WING) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

RIGHT WING FUEL TANK STRINGER 10 WS 686.50 CORRODED. REPAIRED WITH ANGLE DOUBLER.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE FRAME BS 440 S15L-S17L DENTED. REPLACED DENTED FRAME SECTION.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FRAME REPAIR AT BS 560 S20L-S26L DENTED. REPLACED FRAME SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOOR BEAM UPPER CHORD BS720A LBL 18.5-LBL 30.5 CORRODED. REPLACED FLOORBEAM SECTION.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FRAME REPAIR AT BS 580 S20L-S26L DENTED. REPLACED FRAME SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM UPPER CHORD BS 1110 LBL 70 RBL 70 CORRODED. REPLACED FLOORBEAM SECTION.

Part: ANGLE — DAMAGED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FRAME REINFORCEMENT ANGLE BS 1130 S27L-S27R DAMAGED. REPLACED DAMAGED SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM UPPER CHORD BS 620 LBL 18-RBL 45 CORRODED. REPLACED FLOORBEAM SECTION.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE FRAME BS 380 S5R-S7R DENTED. REPLACED FRAME SECTION.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE SKIN FORWARD ENTRY DOOR UPPER HINGE CUTOUT. REPAIRED TO SATISFY AD2007-12-14.

Part: BEAM — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

RIGHT HORIZONTAL STABILIZER TRAILING EDGE LOWER BEAM ELEVATOR STATION 17.20-209.96 CORRODED. REPLACED BEAM SECTION.

Part: SPAR — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

RIGHT HORIZONTAL STABILIZER REAR SPAR UPPER CHORD STATION 83.50-111.10 CORRODED. REPAIRED WITH ANGLE DOUBLER.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE SKIN FORWARD ENTRY DOOR LOWER HINGE CUTOUT. REPAIRED TO SATISFY AD2007-12-14.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOOR BEAM UPPER CHORD BS 1130 LBL 24 CORRODED. REPLACED FLOORBEAM SECTION.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE FRAME BS 420 S15L-S17L DENTED. REPLACED DENTED FRAME SECTION

Part: SKIN — DAMAGED (GALLEY DOOR) · airframe 66,711 hrs · 45,907 cycles

FORWARD GALLEY DOOR SKIN LOWER AFT JAMB BS 400-BS 430 S15R DAMAGED. REPAIRED WITH EXTERNAL DOUBLER

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FRAME REPAIR AT BS 520 S20L-S26L DENTED. REPLACED FRAME SECTION.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

PRESSURE SEAL RETAINER SUPPORT ANGLE BS 870 LBL 62-RBL 62 CORRODED. REPLACED SUPPORT ANGLES.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM LOWER CHORD BS 970 RBL 23 RBL 44 CORRODED. REPLACED FLOORBEAM SECTION.

Part: FRAME — DENTED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE FRAME BS 360 S15L-S17L DENTED. REPLACED DENTED FRAME SECTION.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FLOORBEAM LOWER CHORD BS 720 LBL 55 RBL 57 EXISTING REPAIR CORRODED. REPLACED FLOORBEAM SECTION.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 66,711 hrs · 45,907 cycles

FUSELAGE FRAME BS 360 S3L-S9L DAMAGED. REPLACED DAMAGED FRAME SECTION.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

STRINGER S29L BS 1051-BS 1115 CORRODED. REPLACED DAMAGED STRINGER SECTION.

Part: BEAM — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

LEFT HORIZONTAL STABILIZER TRAILING EDGE UPPER BEAM ELEVATOR STATION 17.20-39.50 CORRODED. REPAIRED WITH DOUBLER.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

STRINGER S27R BS 1053-BS 1086.5 CORRODED. REPLACED DAMAGED STRINGER SECTION.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 66,711 hrs · 45,907 cycles

FUSELAGE SKIN BETWEEN BS 1030-BS 1110 S27L-S26R CORRODED. REPAIRED WITH EXTERNAL DOUBLER.

Part: SHIM — DAMAGED (NR 1 ENGINE) · airframe 65,187 hrs · 44,856 cycles

ENGINE NR 1 STRUT OVERHEAT LIGHT ILLUMINATED CLIMBING THROUGH FL260. THE STRUT OVERHEAT PROCEDURE WAS ACCOMPLISHED IAW THE AOM AND THE LIGHT EXTINGUISHED. MAINTENANCE REPLACED THE DAMAGED 6TH STAGE DUCT SHIMS AND THE OVERHEAT DETECTION ELEMENT, RETORQUED THE LOOSE 6TH STAGE PNEUMATIC LINE AND PERFORMED A LEAK AND OPERATIONAL CHECK AT TAKEOFF POWER WITH NO DEFECTS NOTED.

Part: MODULATING VALVE — LEAKING (BLEED AIR SYS) · airframe 65,186 hrs · 44,855 cycles

DURING CLIMBOUT PASSING 28000 FEET ENGINE 1 ENG STRUT OVERHEAT ILLUMINATED. ACCOMPLISHED ABNORMAL PROCEDURE, NO FURTHER OCCURRENCE. MAINTENANCE FOUND ENGINE 1 HIGH PRESSURE MODULATING VALVE LEAKING, REPLACED THE VALVE IAW THE B727 AMM, PERFORMED A LEAK CHECK AT POWER FOUND NORMAL.

Part: CLAMP — LEAKING (BLEED AIR SYS) · airframe 64,802 hrs · 44,546 cycles

IN CLIMBOUT OF POS NR 1 STRUT OVERHEAT LIGHT ILLUMINATED IN FLT, EXTINGUISHED WHEN THROTTLE BROUGHT BACK TO IDLE. FLT 82320 WAS CANCELLED UPON RETURN TO POS. MAINTENANCE REMOVED AND REPLACED FWD CLAMP AT NR 1 ENGINE BLEED VALVE. RAN ENGINE TO TAKEOFF POWER FOR 4 MINUTES AND FOR 5 MINUTES AT PART POWER, NO LEAKS NOTED. NO OVERHEAT LIGHTS NOTED.

Part: CLAMP — LOOSE (PRECOOLER) · airframe 64,798 hrs · 44,342 cycles

IN FLIGHT FROM GND TO GEO - NR 1 ENGINE STRUT OVERHEAT LIGHT ILLUMINATED AT CRUISE. THROTTLE BROUGHT TO IDLE, LIGHT EXTINGUISHED. THE FLIGHT DIVERTED TO POS. MAINTENANCE DISCOVERED A LOOSE CLAMP ON THE NR 1 STRUT PRECOOLER DUCT. THE CLAMP WAS RETORQUED AND AN OPERATIONAL TEST PERFORMED PER THE AMM.

Part: TRANSMITTER — FAILED (NR 3 ENGINE) · airframe 64,007 hrs · 43,906 cycles

ON DESCENT IN SDQ OIL QUANTITY GAUGE NR 3 BLED SLOWLY DOWN TO ZERO QUANTITY. OIL PRESSURE AND TEMPERATURE NORMAL BUT WERE VERY LIGHT SO A PRECAUTIONARY ENGINE SHUTDOWN WAS DONE. A NORMAL LANDING WAS PERFORMED. AFTER LANDING OIL QUANTITY CHECKED FULL. ENGINE WINDMILL TIME 20 MINUTES AT 22 PSI OIL PRESSURE. MAINTENANCE CHECKED THE MAIN OIL FILTER AND CHIP DETECTORS, NO METAL FOUND. REPLACED OIL QUANTITY TRANSMITTER OPERATED ENGINE OIL PRESSURE TEMPERATURE AND QUANTITY INDICATIONS WERE NORMAL.

Part: ENGINE — DAMAGED (NR 3)

FLIGHT 743 DEPARTED, WHEN THE CREW REPORTED, DURING CLIMBOUT, THE NR 3 ENGINE STARTED TO VIBRATE ABOUT FL340, ENGINE INDICATIONS WERE ERRATIC, NR 3 FUEL QTY GAUGE SHOWED 1700 LBS. DIFFERENCE WITH NR 1 FUEL TANK, THEN NR 3 ENGINE FLAMED OUT. THE CREW ACCOMPLISHED A RESTART OF THE NR 3 ENGINE AND LANDED WITHOUT FURTHER INCIDENT. UPON VISUAL INSPECTION OF THE NR 3 ENGINE INLET, BLADE DAMAGE WAS NOTED TO THE C-1 AND C-2 COMPRESSOR SECTIONS OF THE NR 3 ENGINE. THE AIRCRAFT WAS FERRIED ON A (2) ENGINE FERRY PERMIT AND LANDED WITHOUT FURTHER INCIDENT. THE DAMAGED C-1 BLADES HAVE BEEN DRESSED AND THE C-2 COMPRESSOR ASSEMBLY IS BEING REPLACED.

Part: DUCT CLAMP — LOOSE (NR 1 ENGINE)

FLIGHT 845 DEPARTED MIA AND CLIMBED TO CRUISE ALTITUDE, THE CREW REPORTED THE NR 1 STRUT OVERHEAT LIGHT ILLUMINATED, THE AIRCRAFT RETURNED TO MIA AND LANDED WITHOUT FURTHER INCIDENT. IN MIA MAINTENANCE FOUND A LOOSE CLAMP AT THE NR 1 ENGINE BLEED VALVE, THE CLAMP WAS RETORQUED IAW B-727 MM CH 20-80-01, THE NR 1 ENGINE WAS RUN-UP TO TAKEOFF POWER AND A LEAK CHECK WAS PERFORMED, ENGINE RUN NORMAL LEAK CHECK GOOD IAW B-727 MM CH 71-00-00, THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPRESSOR — DAMAGED (NR 1 ENGINE)

FLIGHT 713 ABORTED THE TAKEOFF AFTER THE FLIGHT CREW EXPERIENCED A VIBRATION COMING FROM THE NR 1 ENGINE, THE AIRCRAFT RETURNED TO THE GATE WITHOUT ANY FURTHER INCIDENT. MAINTENANCE INSPECTED THE ENGINES AND FOUND THE NR 1 ENGINE SHOWING EVIDENCE OF DAMAGE TO THE SECOND STAGE COMPRESSOR SECTION, FURTHER INSPECTIONS ARE IN PROGRESS. THE NR 1 ENGINE VISUAL INSPECTION NOTED LOW COMPRESSOR BLADE DAMAGE THROUGHOUT THE ENGINE POSSIBLY FROM FOD, THE NR 1 ENGINE HAS BEEN REMOVED AND REPLACED WITH ANOTHER SERVICEABLE ENGINE.

Part: ACTUATOR — FAILED (NLG)

FLIGHT 8413 DEPARTED MIA AND DURING THE CLIMB THE CREW REPORTED THE NOSE LANDING GEAR DID NOT RETRACT WITH THE GEAR LEVER IN THE UP POSITION, THE COCKPIT INDICATION SHOWED THE RED NOSE LANDING GEAR LIGHT AND THE GREEN NOSE LANDING GEAR LIGHT REMAINED ILLUMINATED, THE NOSE GEAR VIEWING PORT WINDOW INDICATED THE NOSE LANDING GEAR REMAINED DOWN AND LOCKED AFTER GEAR RETRACTION. THE CREW DECLARED AN EMERGENCY AND FOLLOWED STANDARD PROCEDURE AND RETURNED TO MIA, THE AIRCRAFT LANDED IN MIA WITHOUT ANY FURTHER INCIDENT. MAINTENANCE FOUND THE NOSE GEAR DOWN LOCK ACTUATOR FAILED IN THE DOWN AND LOCKED POSITION, THE NOSE GEAR DOWN LOCK ACTUATOR WAS REMOVED AND REPLACED IAW B-727 MM CH 32-33-11 PG 101 AND 32-33-11 STEP

Part: SWITCH — MALFUNCTIONED (NR 2 BLEED SYS) · airframe 60,938 hrs · 42,194 cycles

ABORTED TAKEOFF AT 135 KTS. ENGINE FAIL LIGHTS CAME ON, ALL PARAMETERS WORKED NORMAL. TRANSFERRED AUTO PACK TRIP SYSTEM TO DMI 14808. A HIGH ENERGY STOP CONDITION INSPECTION WAS PERFORMED. NO DISCREPANCIES WERE NOTED. SUPPLEMENTAL ADD ON INFO, FOLLOW-UP REPAIR, REMOVED AND REPLACED THE NUMBER 2 BLEED AIR SWITCH IAW 21-11-11, AND DRAINED THE WATER FROM THE BLEED AIR TUBING, PERFORMED OPERATIONAL CHECK IAW B-727 MM. CH 21-11-00 PG 501 AND AMERIJET ENGINE RUN-UP FORM B-41 OP'S CHECK GOOD. THE DMI 14808 WAS CLEARED AND THE A/C WAS RETURNED TO SERVICE.

Part: ENGINE — LEAKING (ZONE 400)

FLIGHT 8315 DURING THE DESCENT, 25 MINUTES OUT, THE CREW REPORTED NR 2 ENGINE QUANTITY INDICATION WENT TO (0) AND NR 2 ENGINE OIL PRESSURE WENT TO (0), THE CREW REPORTED THE NR 2 ENGINE WINDMILLED FOR 25 MINUTES AT 6-10 PSI. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT, MAINTENANCE INSPECTED THE ENGINE FOR OBVIOUS SOURCE OF LEAK, NONE WAS FOUND, THE ENGINE OIL CAP WAS CHECKED FOR SECURITY AND PROPER INSTALLATION IAW MM, NO DISCREPANCIES WERE NOTED. THE NR 2 ENGINE WAS SERVICED WITH OIL, AN ENGINE RUN WAS ACCOMPLISHED AT PART POWER IAW MFG ENGINE GENERAL ADJ AND TEST 101 AND PAGE 531 THROUGH PAGE 533 PAR (1) ENGINE WINDMILLING, NO DISCREPANCIES NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ANNUNCIATOR — MALFUNCTIONED (TAIL SKID)

AFTER TAKEOFF HAD TAIL SKID LIGHT AND RIGHT GEAR DOOR INDICATION WITH HANDLE OFF HAD GEAR GREEN LIGHT ON. AIRCRAFT RETURN TO MIA AND LANDED WITH NO INCIDENT. MAINTENANCE PERFORMED JACKED AIRCRAFT IAW B727 MM 07-11-0. PERFORMED EXTENSION AND RETRACTION OPERATIONAL TEST. FOUND TO BE NORMAL IAW B727 MM 32-32-0. AIRCRAFT WAS RETURNED BACK TO SERVICE.

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

FLIGHT 723 DEPARTED MIA AND CLIMBED TO 34,000 FT CRUISE ALTITUDE, CREW REPORTED NUMBER 2 ENG COMPRESSOR STALLED, POWER WAS REDUCED AND NR 2 ENG CONTINUED TO COMPRESSOR STALL. THE CREW PERFORMED A PRECAUTIONARY ENGINE SHUTDOWN, ALL FLIGHT CONDITIONS WERE NORMAL, THE NR 2 ENGINE WINDMILLED FOR 15 MINUTES. THE A/C RETURNED BACK TO MIA AND LANDED WITHOUT ANY FURTHER INCIDENT. MX INSPECTED & REPLACED NR 2 ENG MAIN OIL STRAINER. LEAK CHECK GOOD. MX ACCOMPLISHED A HIGH POWER TAKE-OFF RUN/STEADY STATE CRUISE, AND SURGE TROUBLESHOOTING, NO DEFECTS NOTED. ENGINE HIGH POWER RUN, OPERATIONALLY CHECKED NORMAL. A BLEED SCHEDULE CHECK, A T/A ANTI-ICE VALVE CHECKED NORMAL.

Part: ADI — SPINNING (COCKPIT)

FLT 8419 AFTER DEPARTURE FROM MIA AND WHILE IN CRUISE THE CREW REPORTED CAPTAINS VG ATTITUDE FLAG IN VIEW CONTINUOUSLY AND RAPID SPINNING OF THE ADI TO THE RIGHT, AUX VG SELECTION AND C/B RESET, NO HELP. AIRCRAFT RETURNED BACK TO MIA AND LANDED WITHOUT ANY FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED THE NR 1 ADI AND OPERATIONALLY CHECKED GOOD PER B-727 MM CH 31-00-11 AND B-727 MM CH 34-22-02. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — OVERHEATED (NR 3) · airframe 59,529 hrs · 41,413 cycles

AFTER DEPARTURE ENGINE NR 3 OIL TEMPERTURE INCREASED TO 160, PERFORMED ALTERNATE PROCEDURE, NO HELP. SHUT DOWN ENGINE, DUMPED FUEL TO LAND. MX INSPECTED INLET & EXHAUST OF NR 3 ENGINE; INLET OK, EXHAUST SHOWS EVIDENCE OF OIL LEAK, SUSPECT NR 6 BEARING SEAL. PERFORMED T/S, OIL LEVEL OK. INSPECTED MAIN OIL SCREEN FOR CONTAMINATION, NORMAL CARBON DEPOSIT FOUND, FUEL DEICING CHECKS OK, NR 4 & NR 5 BEARING TEMP IND WERE DARK. INSTALLED NR 4 & NR 5 BEARING OIL LINE TEMP INDICATORS AS REQUIRED. REMOVED & REPLACED NR 6 OIL PUMP. LEAK CHECK NORMAL. INSTALLED NR 3 THRUST REVERSER IAW BOEING MM 78-30-0 AND MIXER IAW DUGAN MM 78-30-22. THRUST REVERSER OPS CHECK NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 59,517 hrs · 41,408 cycles

FLIGHT 751 MIA TO MEX CREW REPORTED, PRESSURIZATION WOULD NOT LEVEL OFF ON CLIMBOUT, JETTISONED FUEL BELOW LANDING WEIGHT. AIRCRAFT RETURNED TO MIA AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND FLOW CONTROL VALVE NOT OPERATING PROPERLY. REMOVED AND REPLACED LT & RT FLOW CONTROL, SHUT-OFF VALVES, RT HP REGULATOR & NR 1 8TH STAGE CHECK VALVE. OPERATIONAL NORMAL IN ACCORDANCE WITH MM 36-10-21 & MM 71-00. AIRCRAFT RETURNED TO SERVICE.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE)

FLIGHT 857 DURING CLIMBOUT FROM MIA FLIGHT CREW REPORTED AIRCRAFT WOULD NOT PRESSURIZE & IT SEEMED BOTH PACKS WERE NOT WORKING AT ALL. AIRCRAFT RETURNED TO MIA & LANDED WITHOUT ANY FURTHER INCIDENT. MAINTENANCE CHECKED BOTH LEFT & RIGHT PACKS IAW B-727 MM CH 21-55-0 OPERATION CHECK WAS NORMAL. MAINTENANCE RERACKED THE PRESSURE CONTROLLER & CLEANED PACK VALVES & CLEANED THE CANNON PLUGS & RESECURED, A FULL PRESSURIZATION CHECK OUT WAS ACCOMPLISHED IAW AMERIJET WORK CARD 847 OPERATIONAL CHECK WAS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROLLER — MISOVERHAULED (CABIN PRESSURE) · airframe 59,156 hrs · 41,193 cycles

FLIGHT 711 KMIA/MMMX, DURING CLIMB AUTO PRESSURIZATION FAILED, WENT TO STANDBY, OUTFLOW VALVE WENT FULL OPEN. UNABLE TO HOLD CABIN PRESSURE IN MANUAL AC OR DC. AIRCRAFT RETURNED TO KMIA AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND CABIN PRESSURE CONTROLLER SENSE PORTS CAPPED. REMOVED CAPS AND PERFORMED OPS CHECK PER "B" CHECK WORK CARD 7-29 AND B-727 MM 21-30-0. AIRCRAFT RETUNED TO SERVICE.

Part: O-RING — LEAKING (FUEL PUMP SHAFT)

CREW REPORTED NR2 ENG OIL QUANTITY DROPPED IN FLIGHT, THEN ENGINE OIL PRESSURE DROPPED, THEN OIL TEMP ROSE. CREW SHUTDOWN NR2 ENGINE AND AC RETURNED TO DEPARTURE, AC LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND NR2 ENGINE GEARBOX LEAKING OIL FROM THE FUEL PUMP SHAFT. MAINTENANCE REMOVED AND REPLACED THE O-RING ON THE FUEL PUMP TO THE GEARBOX AND REPLACED THE CARBON SEAL ON THE NR2 ENGINE GEARBOX IAW MM. MAINTENANCE INSP NR 2 ENGINE OIL FILTER FOR CONTAMINANTS, NONE FOUND, OIL SAMPLE TAKEN, SAMPLE SENT OUT FOR SOAP TEST. NR2 ENG LEAK CHECK WAS PERFORMED IAW MM. NO OIL LEAKS NOTED LEAK CK GOOD. AC FLEW NEXT FLIGHT WITH NO FURTHER ENGINE OIL QUANTITY PROBLEMS REPORTED. (K)

Part: WARNING LIGHT — ILLUMINATED (TE FLAPS)

AFTER DEPARTING, IB FLAPS WENT ASYMMETRIC FROM POSITION 5 DEGREES TO 2 DEGREES COMPLETED ABNORMAL CHECKLIST. JETTISONED FUEL DOWN TO MAX LANDING WEIGHT. AIRCRAFT DIVERTED BACK AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE RESET AND RAN FLAPS 3 TIMES, OPERATION CHECK NORMAL. LUBRICATED ALL POSITION INDICATOR TRANSMITTERS PULLEYS AND CABLES. RAN FLAPS SEVERAL TIMES, CHECK NORMAL OPERATION. NO ASYMMETRY IAW MM27-51-0. AIRCRAFT RETURNED TO SERVICE.

Part: UPLOCK — INOPERATIVE (LT MLG)

UPON GEAR EXTENSION IN GND LT GEAR WOULD NOT EXTEND. ACCOMPLISHED ABNORMAL OPERATION, GREEN GEAR LIGHTS, OUT AND RED DOORS LIGHT, GEAR LEVER DOWN AND MANUAL GEAR EXTENSION AT LT GEAR EXTENDED AT COMPLETION OF CHECK LIST. AC FERRY AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REMOVED AND REPLACED LT UPLOCK ACTUATOR IAW MM 32-32-61. ACCOMPLISHED LT MAIN LANDING GEAR WHEEL WELL DOOR RIGGING AND OPS CHECK NORMAL IAW MM 32-12-1. LUBRICATED LT MAIN LANDING GEAR SYSTEM IAW 12-21-01. ACCOMPLISHED OPS CHECK IAW MM 32-32-0. PERFORMED MANUAL EXTENSION IAW 32-24-0 PAGE 507 AND 508. OPS CHECK NORMAL. ACCOMPLISHED LT MLG UPLOCK ROTATION TORQUE CHECK IAW WORK CARD SP15, CHECKED OK. AC RETURNED TO SERVICE. (M)

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

FLIGHT CREW REPORTED, AT FL370 100 MILES FROM SDQ, NR 2 ENGINE COMPRESSOR STALL AT FL370 (3 TIMES). ALL INDICATION FLUCTUATING. PRECAUTIONARY SHUTDOWN AT FL370, COMPLIED WITH APPROPRIATE SHUT DOWN PROCEDURES. AIRCRAFT LANDED WITH NO FURTHER INCIDENT. MAINTENANCE ACCOMPLISHED VISUAL INSPECTED C-1 FAN BLADES AND T-4 TURBINE WHEEL NO EVIDENCE OF OIL OR DAMAGE IN AREAS RELATED TO THESE COMPONENTS. ALSO, INSPECTED ALL COMPONENTS ATTACHED FOUND OK. RAN ENGINE IAW THE AMM 72-00, OPERATIONAL CHECK GOOD. NO VIBRATION DUPLICATED. PRBC SCHEDULE ALSO VERIFIED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: PULLEY — FROZEN (LT MLG DOOR)

FLT CREW REPORTED, ON GEAR EXTENSION LEFT MAIN LANDING GEAR GREEN LIGHT DID NOT ILLUMINATE. MLG MANUALLY EXTENDED. A/C LANDED WITH NO FURTHER INCIDENT. MXE FOUND TWO FROZEN PULLEYS ON DOOR SAFETY VALVE CONTROL CABLES. REMOVED AND REPLACED PULLEYS IAW MM 20-20-4. ALSO, FOUND MLG DOOR SAFETY VALVES CABLES WERE OUT OF ADJUSTMENT. CABLES ADJUSTED IAW MM 32-34-0. OPERATIONS CHECK OK. LUBED LEFT MAIN LANDING GEAR IAW MM 12-21-1, PAGE 201. PERFORMED NORMAL AND EMERGENCY GEAR OPERATION IAW MM 32-52-0, PATE 501 AND MM 32-34-0, PAGE 507 TO INCLUDE INDICATION CHECKS. VISUALLY INSPECTED LEFT MAIN LANDING GEAR SIDE STRUT INSTALLATION FROM WHEEL WELL SIDE. NO DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: LINE — DEFECTIVE (RT MLG ACTUATOR)

FLT 825 - SVD-GND - CREW REPORTED, ON APPROACH LOST OF SYSTEM 'A' HYDRAULICS. CAPTAIN ELECTED TO DIVERT FROM SVD TO GND. AIRCRAFT LANDED WITHOUT ANY FURTHER INCIDENT. MAINTENANCE FOUND MLG ACTUATOR HOSE LEAKING. A TEMPORARY FLEX LINE WAS INSTALLED IN PLACE OF THE DEFECTIVE HYDRAULIC LINE. THE HYDRAULIC SYSTEM WAS SERVICED. CYCLED FLIGHT CONTROLS AND LANDING GEAR SEVERAL TIMES. CHECKED NR 1 AND NR 2 ENGINE HYDRAULIC PUMPS. OPS AND LEAK CHECK GOOD. SERVICE SYSTEM IAW 12-12-0. TRANSFERRED TEMPORARY REPLACEMENT ON DMI# 12508 IAW GMM 4-21-1. AIRCRAFT RETURNED TO SERVICE. (M)

Part: SKIN — DELAMINATED (IB AFT FLAP)

LEFT WING, INBOARD AFT FLAP, SKIN DELAMINATED.

Part: SKIN — DELAMINATED (OB AFT FLAP)

RIGHT WING, OUTBOARD AFT FLAP, SKIN DELAMINATED.

Part: SKIN — DELAMINATED (RT IB AFT FLAP)

RIGHT WING, INBOARD AFT FLAP, SKIN DELAMINATED.

Part: SKIN — DELAMINATED (RT TE FLAP)

RIGHT WING, INBOARD FORE FLAP UPPER AND LOWER SKIN DELAMINATION.

Part: SKIN — DEBONDED (LT TE FLAP)

LEFT WING, OUTBOARD AFT FLAP DEBONDED.

Part: FITTING — CORRODED (MID FLAP)

FITTING, RIGHT WING, INBOARD MID-FLAP, OUTBOARD FITTING FLAP CARRIAGE WITH CORROSION.

Part: STRUCTURE — CORRODED (FUSELAGE)

FORWARD C/C, STA 620, BETWEEN STR 23R AND STR 24R SUPPORT TEE CORRODED.

Part: FITTING — CORRODED (RT WING)

RT WING, TRAINLING EDGE AT WS383.5, FITTING CORRODED.

Part: SUPPORT — CORRODED (FUSELAGE)

FWD C/C, STA 623, BETWEEN STR 25L AND STR 26L AND STA 560 BETWEEN STR 25R AND STR 26R NET TUBE SUPPORT.

Part: SKIN — CRACKED (LAP SPLICE)

SKIN LAP SPLICE-LOWER SKIN, LOWER FASTENER ROW WITH CRACK INDICATION AT S-4L, BS 412.0.

Part: SKIN — CRACKED (FUSELAGE)

SKIN LAP SPLICE-LOWER SKIN. LOWER FASTENER ROW WITH CRACK INDICATION AT S-4L, BS 446.750.

Part: SKIN — CORRODED (FUSELAGE)

LOWER FUSELAGE SKIN BS 950F+10.0 INCHES, S-27R AND 28R, SKIN WITH CORROSION.

Part: PANEL — DELAMINATED (RT WING)

RIGHT WING, TRAILING EDGE PANEL (PN: 65-21655) DELAMINATED.

Part: FLANGE — CRACKED (KEEL BEAM)

LOWER FUSELGAE - FROM BS 740 TO BS 742, RBL 5.0" KEEL BEAM INBOARD FLANGE CRACKED.

Part: FITTING — CORRODED (MID FLAP)

RIGHT WING, OUTBOARD MID-FLAP, INBOARD/OUTBOARD FITTINGS FLAP CARRIAGE WITH CORROSION.

Part: SHEAR TIE — CORRODED (FUSELAGE)

LOWER FUSELAGE, STA 1050 BETWEEN STR 26L AND STR 27L SHEAR TIE CORRODED.

Part: CLIP — CRACKED (FUSELAGE)

FRAME STA 480 STR 3 LT CLIP CRACKED DUE TO INADEQUATE STRINGER RIVETING.

Part: CLIP — CRACKED (FUSELAGE)

FRAME STA 480 STR 7 LT 8 LT, CLIP CRACKED DUE TO INADEQUATE STRINGER RIVETING.

Part: FLANGE — CRACKED (APU TURBINE)

APU TURBINE ASSEMBLY EXHAUST FLANGE CRACKED.

Part: FITTING — CORRODED (MID FLAP)

FITTING, LEFT WING, INBOARD MID-FLAP INBOARD FITTING FLAP CARRIAGE WITH CORROSION.

Part: PANEL — CORRODED (LT WING T/E)

LEFT WING, TRAILING EDGE UPPER FIX PANEL (PN 65-21655-477) CORRODED.

Part: PANEL — DELAMINATED (LT WING)

LEFT WING, TRAILING EDGE UPPER FIX PANEL (PN 65-21657-245) DELAMINATED.

Part: SKIN — CRACKED (FUSELAGE)

FUSELAGE SKIN LAP SPLICE-LOWER SKIN, LOWER FASTENER ROW WITH CRACK INDICATION AT S-4L, BS 390.0.

Part: FRAME — CORRODED (FUSELAGE)

MAIN LANDING GEAR WHEEL WELL, BS 950 CANTED BULKHEAD LOWER TEE CHORD CORRODED.

Part: CLIP — CRACKED (FUSELAGE)

FRAME STA 373. STR 8 RT. AFT INTERCOSTAL CLIP CRACKED DUE TO FATIGUE.

Part: FITTING — CORRODED (MID FLAP)

FITTING, LEFT WING, OUTBOARD MID-FLAP INBOARD/OUTBOARD FITTINGS FLAP CARRIAGE WITH CORROSION.