SKY LEASE I, LLC

LOWER FUSELAGE CENTER WING FRONT SPAR AT STA. RBBL 127.50, LOWER PANEL CORROSION.

LOWER FUSELAGE AT LH AND RH FWD SPAR OF CENTER TANK AT STA. 987 (APROX), SHOWS CORROSION.

DURING INSPECTION OF AFT CARGO DOOR, FOUND FRAME PUNCTURE HOLE AND CRACK ON AFT SECTION OF CARGO DOOR SKIN.

DURING POST FLIGHT FOUND # 3 BRAKE TORQUE LIMITER BROKEN.

DURING T/O CLIMB , ELECTRICAL ODOR FOLLOWING BY " EE CLNG SUPP FAN" ON STATUS PAGE.-

1.DURING CLIMB +-29000, HEARD A LOUD NOISE LIKE AN EXPLOSION , SELECT ECS AND SAW BOTH OUTFLOW VALVES CLOSED BUT RATE OF CLIMB +-1700. CABIN ALT REACH +- 10000. THE EQUIPMENT COOLING WARNING LIGHT CAME ON. PERFORMED CABIN ALT (QRH) DESCENT TO 10000, BACK TO DEPARTURE.

ON CLIMB OUT DEPARTING KMIA NR 2 ENGINE EXPERIENCED HIGH EGT, THROTTLE RETARDED , MINUTES LATER LOUD NOISE WAS HEARD, EGT CLIMBED TO 777 DEGREES CELSIUS AND ENGINE SHUT DOWN PROCEDURE WAS ACCOMPLISHED, FUEL WAS DUMPED AND RTB KMIA. AFTER PARKING FOUND EXCESSIVE TURBINE BLADE DAMAGE.

AIRCRAFT WAS BEING PREPARED FOR DEPARTURE. APU WAS STARTED AND APPROXIMATELY 5 MINUTES LATER, THE APU FIRE INDICATION ACTIVATED AND THE FLIGHT CREW PULLED THE APU FIRE T-HANDLE. THE APU FIRE BOTTLE HAD ALREADY AUTOMATICALLY ACTIVATED. UPON INSPECTION OF THE APU AND ITS AREA WAS FOUND THAT THE STARTER HAD BROKEN LOOSE AT ITS MOUNTING AT THE APU. IT APPEARED THAT AS A RESULT OF THE STARTER'S MOVEMENT UPON BREAKING LOOSE, IT DAMAGED A FUEL LINE, WHICH CAUSED A FUEL LEAK, WHICH IN TURN CAUSED THE FIRE. THE FIRE WAS EXTINGUISHED BY THE FIRE SUPPRESSION SYSTEM. AS A RESULT OF THE FIRE, THE RT INBD ELEVATOR WAS DAMAGED, AS WELL AS BOTH OF THE APU LOWER ACCESS DOORS. THE APU DOORS WERE R & R, AS WAS THE RT INBD ELEVATOR. THE APU WAS DEACTIVATED AND DEFERRED, AND WILL BE R & R UPON THE AIRPLANE'S ARRIVAL. TROUBLESHOOTING IS CURRENTLY IN PROGRESS TO DETERMINE THE CAUSE OF THE STARTER FAILURE.

DURING CRUISE, UPPER CABIN AND ALL DECKS TEMPERATURE EXCEEDED 60 DEGREES C. RETURNED TO DEPARTURE. EMERGENCY NOT DECLARED. TROUBLESHOOTING FOUND A DEFECTIVE ZONE TEMPERATURE CONTROLLER. CONTROLLER WAS REMOVED AND REPLACED, OPERATIONAL SYSTEM CHECK SATISFACTORILY PERFORMED PER AMM 21-61-01 AND 21-61-00, AIRPLANE RETURNED TO SERVICE.

DURING FLIGHT, RECEIVED A LEVEL 2 ALERT HYDRAULIC SYSTEM 3 FAIL. ACFT DIVERTED AND LANDED SAFELY. PUMP CASE DRAIN LINE CRACKED LINE WAS REPLACED.

30 MINUTES INTO FLIGHT HYDRAULIC SYSTEM 3 PRESENTS HYDRAULIC SYS 3, LEVEL 1 ALERT, FOLLOWED BY QUANTITY LOW, FOLLOWED BY HYD SYSTEM 3 FAIL. ACFT RETURNED TO DEPARTURE.

HIGH VIBRATION ON CLIMB CONTINUED FOR REMAINDER OF FLIGHT. FOUND RT WING NR 2 SPOILER DELAMINATED.

RETURNED TO DEPARTURE DUE TO HIGH STRUCTURE VIBRATION ON CLIMB PHASE PASSING 16,000 AND REMAINED FOR REST OF FLIGHT.

AT TOP OF CLIMB ELECTRONIC EQUIPMENT COOLING GROUND EXHAUST VALVE FAIL MESSAGE. WHEN SWITCHED ELECTRONIC EQUIPMENT COOLING TO OVERRIDE POSITION, CONTINUED TO HAVE THE OVERHEAT PROBLEM CAUSING A RETURN TO DEPARTURE.

NR 1 ENGINE LOST POWER, ALL OF ITS PARAMETERS DISPLAYED IDLE ON ECIAS. POWER RECOVERED IMMEDIATELY. MINUTES LATER SAME ENGINE LOST POWER AGAIN DURING CLIMB OUT. ALL ENGINE PARAMETERS DISPLAYED IDLE ON ECIAS BUT THIS TIME POWER WAS NOT RECOVERED. ENGINE CHECKLIST PERFORMED BY CREW. ENGINE WAS SHUTDOWN IAW PROPER PROCEDURES. ACFT RETURNED TO DEPARTURE SAFELY.

DEPARTING NR 1 ENG LOST POWER, ALL OF ITS PARAMETERS DISPLAYED IDLE ON ECIAS. POWER RECOVERED IMMEDIATELY, MINUTES LATER SAME ENGINE LOST POWER AGAIN DURING CLIMB OUT. ALL ENGINE DISPLAYED IDLE ON ECIAS BUT THIS TIME POWER WAS NOT RECOVERED. ENGINE CHECKLIST PERFORMED BY CREW. ENGINE WAS SHUTDOWN IAW PROPER PROCEDURES. ACFT RETURNED TO DEPARTURE SAFELY.

DURING APPLICATION OF TAKEOFF POWER, ENGINE NR 1 DID NOT ACCELERATE. DISCONTINUED TAKEOFF.

DURING AIRCRAFT MAINTENANCE CHECK, INSPECTORS FOUND CORROSION IN THE CENTER CARGO COMPARTMENT BETWEEN BS 1641 & 1661 ON LONGERON 44R. REPAIRED IAW SRM 53-00-05, TYPE 1.

DURING DECENT THE NR 1 ENGINE, N2 VIBRATION PEAKED AT 4.5, 15,000 FEET, INDICATED AIRSPEED 300 KNOTS, FLIGHT IDLE POWER.

DURING ACFT MAINTENANCE CHECK INSPECTORS FOUND CORROSION ON TOP SURFACE OF UPPER AUXILIARY FUEL TANK BETWEEN STR 17 & 18 LT, STA 1199, LBL 108.

DURING ACFT MAINTENANCE CHECK, INSPECTORS FOUND CORROSION OTBD OF UPPER AUXILIARY FUEL TANK, FLOOR LT SIDE, BS 1239 TO 1255, LBL 109.

DURING ACFT MAINTENANCE CHECK INSPECTORS FOUND CORROSION ON SURFACE OF SURFACE AUXILIARY FUEL TANK BS 1219 TO 1229, RBL 68.

AFTER TAKEOFF ALL SYSTEMS WERE NORMAL. ONCE A RT TURN HEADING 120 DEGREES WAS INITIATED, THE CREW RECEIVED A "RADAR FAIL" MESSAGE WHILE IN THE TURN. AFTER A CLIMB OF 10,000 FT, THE CREW WAS UNSUCCESSFUL IN FIXING THE PROBLEM. AFTER DISCUSSING THE DUAL RADAR FAILURE WITH THE FLIGHT FOLLOWER THE CREW DECIDED TO RETURN TO DEPARTURE DUE TO NIGHT OPERATIONS AND WEATHER FORECASTED ALONG ROUTE AND AT DESTINATION. NO FUEL DUMP WAS REQUIRED. R & R WEATHER RADAR ANTENNA IAW AMM 34-34-03, OPS CHECK GOOD AND TEST PASSED.

THE CREW REPORTED TAKEOFF WAS SMOOTH AND UNEVENTFUL. NOTICED AN OUT OF TRIM AND OPPOSITE RUDDER TRIM. RT INBD AILERON DEFLECTED TO FULL DOWN POSITION DURING FLIGHT AND WAS UNABLE TO ENGAGE AUTOPILOT. DIVERTED AND DUMPED APPROXIMATELY 25 MINUTES OF FUEL PERFORMED AN UNEVENTFUL LANDING. INBD AILIRON POWER CONTROL PACKAGE FOUND TO BE DAMAGED UPON VISUAL INSPECTION. R & R RT INBD AILERON POWER CONTROL ASSY.

DURING POSTFLIGHT WALKAROUND, FOUND A DENT ON FUSELAGE FWD OF THE FWD CARGO DOOR. REPAIRED IAW STS EO 100-2014-114. ALL WORK DOCUMENTED ON NR 26850, 002651, 003002.

DURING CLIMB AT 9000 FT AGL, THERE WAS A CABIN ATTITUDE WARNING WITH AUDIO WARNING. PERFORMED QRH. PROCEEDED TO LEVEL OFF AT 14000' DUE TO TERRAIN. RETURNED TO AIRPORT. ALL CHECKLIST WERE COMPLETED. ACCOMPLISHED FIM 21-31, TASK 840, UNTIL STEP 3, PERFORMED CPCS GROUND TEST IAW AMM 21-31-00. SYSTEM OK.

THE CREW REPORTED THAT DURING TAKEOFF ROLL AT APPROXIMATELY 98KTS, THE MASTER WARNING LIGHT ILLUMINATED MOMENTARILY. ABORTED THE TAKEOFF. PERFORMED RTS OF DEU 1, DEU 2, AND DEU 3. RTS PASS IAW MM 31-61-02. OPS TEST OF MASTER WARNING ILLUMINATED PUSH BUTTON SWITCH. NO DISCREPANCIES NOTED.

THE CREW REPORTED THAT DURING TAKEOFF ROLL AT APPROXIMATELY 90KTS, THE MASTER WARNING LIGHT ILLUMINATED MOMENTARILY. AND THE AUTO BRAKES REACTED UNEVEN PULLING THE ACFT TO THE LT WITH A JERKING MOTION. CORRECTED THE SITUATION WITH MOVEMENT OF THE RUDDER AND NOSE WHEEL STEERING IN THE OPPOSITE DIRECTION. THE CREW PROCEEDED TO REJECT TAKEOFF. AS THE ACFT CAME NEAR TO A STOP, IT JOLTED ONCE AGAIN BUT THIS TIME HARDER THAN BEFORE. PROCEEDED TO TAXI TO THE GATE WITHOUT ANY FURTHER INCIDENT. PERFORMED RTS OF DEU 1, DEU 2, AND DEU 3. RTS PASS IAW MM 31-61-02. OPS TEST OF MASTER WARNING ILLUMINATED PUSH BUTTON SWITCH. NO DISCREPANCIES NOTED.

THE CREW REPORTED THAT DURING TAKEOFF, THERE WAS AN AIRSPEED DIFFERENCE AFTER 80KTS. THE F/O AIRSPEED INDICATOR DROPPED TO 55 KTS WHILE THE CAPTAIN’S AIRSPEED INDICATOR READ 95 KTS. REJECTED TAKEOFF AT 95 KIAS AND TAXIED BACK TO THE RAMP WITHOUT ANY FURTHER INCIDENT. FIM 34-11-02, PURGED LINES OF THE FIRST OFFICER’S PITOT SYSTEM IAW AMM 34-11-00. PERFORMED PITOT SYSTEM LEAK TEST IAW AMM 34-11-00. NO LEAKS NOTED.

THE CREW REPORTED THAT AFTER TAKEOFF, ATTEMPTED TO RAISE THE GEAR AND AN EICAS MESSAGE "GEAR TILT" DISPLAYED. FOLLOWED THE QRH PROCEDURES, LANDED WITHOUT ANY FURTHER INCIDENT. REPAIRED CHAFED WIRE AT LT WING LANDING GEAR JUNCTION BOX. OPS CHECKED NORMAL.

THE CREW REPORTED THAT PRIOR TO TOP OF DESCENT THAT A LEVEL 2 ALERT FOR GEN BUSS 3 FAULT WAS DISPLAYED IN THE EAD. FOLLOWED THE QRH PROCEDURES, DEPLOYED THE ADG AND NO FUEL DUMP WAS PERFORMED. LANDED WITHOUT FURTHER INCIDENT OR DELAY. PERFORMED FIM 24-20-17, STEPS 1-5, CHECKED T1-T3 FOR IDG TO GROUND. CHECKED CONNECTIONS P1-8559A & P1-8559B. CHECKED 53-393. GR-3 TO BTR-3, B7-7, B7-8 & B7-9 WITH GROUND = 250 OHMS. CHECKED GENERATOR RELAY & BUSS TIE RELAY. FOUND ALL NORMAL. FOUND RCCB B1-138 DIFFERENTIAL FAULT DEFECTIVE, R & R RCCB AND OPERATIONALLY CHECKED NORMAL.

THE CREW REPORTED DURING CRUISE FLIGHT, APPROXIMATELY 1 HOUR FROM DESTINATION THAT A LEVEL 2 ALERT FOR GEN BUSS 3 FAULT WAS DISPLAYED ON THE EAD. FOLLOWED THE QRH PROCEDURES, DEPLOYED THE ADG AND NO FUEL DUMP WAS PERFORMED. LANDED WITHOUT ANY FURTHER INCIDENT OR DELAY. REMOVED NR 3 BUSS ASSY FEEDER CABLES, NR 3 GR & NR 3 GEN CONTROL RCCB. STOWED ADG. OPS CHECK NORMAL. ACFT RELEASED FOR SERVICE.

THE CREW REPORTED DURING CRUISE FLIGHT, APPROX. 60 MILES FROM CARTAGENA VOR THAT A LEVEL 2 ALERT: GEN BUS 3 FAULT WAS DISPLAYED IN THE EAD. THE CREW THEREBY CONTACTED DISPATCH AND FLIGHT OPERATIONS. THE CREW FOLLOWED THE QRH PROCEDURES, DEPLOYED THE ADG AND NO FUEL DUMP WAS PERFORMED. THE CREW RETURNED WITHOUT ANY FURTHER INCIDENT OR DELAY. PERFORMED FUNCTIONAL TEST OF THE GEN BUSS FAULT RESET IAW 24-21-00.ENGINE RUN WAS PERFORMED IAW 71-00-00. EPCU RTS TEST PASSED.

THE CREW REPORTED THAT DURING CRUISE FLIGHT, APPROXIMATELY 50 MINUTES AFTER TAKEOFF, A LEVEL 2 ALERT OF A GENERATOR BUSS 3 FAULT WAS DISPLAYED IN THE EAD. FOLLOWED QRH PROCEDURES, DEPLOYED THE ADG AND NO FUEL DUMP WAS PERFORMED. RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. R & R DIFFERENTIAL PROTECTION CURRENT TRANSFORMERS, T1-9071, T1-9074 & T1- 9080. GROUND OPS NORMAL. SYSTEM CHECKED OK.

DURING ACFT HEAVY MAINTENANCE CHECK, INSPECTORS FOUND EXFOLIATION CORROSION ON UPPER SURFACE OF THE CENTER AUXILIARY FUEL TANK, STATION 1239.

CREW REPORTED THAT DURING TAKEOFF, THRUST REVERSER UNLOCK LIGHT ILLUMINATED LESS THAN 80 KNOTS. CREW RETURNED TO THE GATE IAW MAINTENANCE PROCEDURE TO LOCK OUT THRUST REVERSER. CREW ATTEMPTED ANOTHER TAKEOFF AND THE SAME OCCURRENCE OF THE THRUST REVERSER UNLOCK LIGHT INDICATION ILLUMINATED AGAIN LESS THAN 80 KNOTS CAUSING A SECOND REJECTED TAKEOFF. CREW RETURNED TO THE RAMP WITHOUT ANY FURTHER INCIDENT.

ON REACHING TOP OF CLIMB, A LEVEL 2 OIL PRESSURE LOW DISPLAYED. CREW FOLLOWED THE QRH PROCEDURES SIMULTANEOUSLY FOLLOWING THE QRH PROCEDURES "ENGINE SHUTDOWN IN FLIGHT" FOR ENG NR 2. THE CREW ACCOMPLISHED THE CHECKLIST THEN PROCEEDED TO DUMP APPROXIMATELY 50 KGS OF FUEL. THE CREW DECLARED AN EMERGENCY LANDING, BUT RETURNED BACK TO DEPARTURE WITHOUT ANY FURTHER INCIDENTS OR DELAYS. VISUALLY INSPECTED ENG NR 2, FOUND METAL SEDIMENT AT CHIP DETECTORS AND IN MAIN OIL FILTER. REPLACED NR 2 ENGINE.

DURING HEAVY CHECK, LT WING UPPER PLATE AT LWS 160 AND S15L WAS FOUND TO BE CORRODED. DAMAGE REPAIRED IAW EO SLC-140317.

DURING HEAVY MAINTENANCE, MAINTENANCE FOUND UPPER PLATING AROUND BS 1229 BETWEEN RBL 57 TO 78 CORRODED. REPAIRED IAW EO SLC-140609.

DURING HEAVY CHECK, UPPER PLATING AROUND BS 1229 AROUND RBL 8 FOUND CORRODED. REPAIRED IAW EO SLC-140611.

DURING HEAVY CHECK, FLIGHT COMPARTMENT, MAIN DECK, AND LOWER CARGO COMPARTMENT FLOOR PANELS WERE FOUND DAMAGED. REPAIRED FLOOR PANELS IAW EO SLC-140313.

DURING HEAVY CHECK, MAIN DECK CARGO HANDLING SYSTEM, CENTERLINE RESTRAINT ASSY SIDE FITTINGS WERE FOUND CRACKED. R & R 38 EACH CENTERLINE RESTRAINTS SIDE FITTINGS. REPAIR OF SIDE FITTINGS ACCOMPLISHED IAW EO SLC-121214.

DURING TAKEOFF, AIRCRAFT SPEED SCALE AND GREEN ACCELERATION LINE WERE NOT PRESENT ON EITHER THE CAPTAIN OR F/O PFD'S, NO AIRSPEED INDICATION. INSTEAD "TAXI" WAS STILL DISPLAYED. THE CREW MADE THE DECISION TO ABORT TAKEOFF APPROXIMATELY BETWEEN 85-90 KTS. FOLLOWED POST FLIGHT AND TAXI PROCEDURES BACK TO THE GATE WITHOUT ANY OTHER FURTHER INCIDENT. FOUND INSECTS IN PITOT TUBES. PURGED PITOT STATIC SYS IAW AMM 24-11-00. 2. R & R STATIC RIGID LINE AT RT STATIC PORT IAW AMM 20-50-01.

DURING CLIMB THROUGH 10,000 FT, A LEVEL 2 ,CARGO DOOR FWD A ALERT DISPLAYED. FOLLOWED QRH PROCEDURES AND ACCOMPLISHED CHECKLIST. RETURNED TO DEPARTURE WITHOUT ANY FURTHER INCIDENTS. VISUALLY INSPECTED CARGO DOOR, FOUND CARGO DOOR CLOSED AND LOCKED.

DURING TAKEOFF ROLL, PRIOR TO V1, CREW REPORTED THEY FELT VIBRATION AND SIMULTANEOUSLY "LEVEL 2 ALERT" INDICATED "TIRE FAILURE," NR 1 TIRE FAIL DISPLAYED. THE CREW ABORTED TAKEOFF IAW PROCEDURE. ALSO, DUE TO THE HIGH-ENERGY STOP, THIS CAUSED AN OVER TEMP OF THE THERMAL PLUGS IN 4 OTHER TIRES.

DURING CRUISE, AT APPROXIMATELY 100NM SOUTH OF AIRPORT, LEVEL 2, GEN 3 BUSS FAIL ALERTED. CREW FOLLOWED THE QRH PROCEDURES, DEPLOYED THE ADG. CONTINUED FLIGHT AS PLANNED AND LANDED AT FLIGHT DESTINATION WITHOUT ANY FURTHER INCIDENTS. PERFORMED ENGINE RUN. PERFORMED FUNCTIONAL TEST OF THE GENERATOR BUSS FAULT TEST IAW AMM-24-21-00. STOWED ADG IAW AMM-24-21-00. OPS CHECKED NORMAL.

CREW REPORTED DURING TAKEOFF ROLL, ONE OR MORE OF THE BRAKES WERE GRABBING AT APPROXIMATELY 80 KNOTS ON THE LT SIDE. ACFT ACCELERATION THEREBY SLOWED DOWN. THE CREW PROCEEDED BY REJECTING TAKEOFF AND RETURNED TO THE RAMP WITHOUT FURTHER INCIDENT. FOUND NR 10 BRAKE INOPERATIVE. DEACTIVATED BRAKE.

CREW REPORTED THEY LOST THE RT EMERGENCY AC BUSS. THE ALERT WAS GENERATOR BUSS 3 FAULT. HAD ONLY A SINGLE GENERATOR OPERATIVE. FOLLOWED QRH PROCEDURES, DEPLOYED ADG AND LANDED WITHOUT FURTHER INCIDENT. PERFORMED TASK IAW FIM 24-20-05. AUTO RESET OF EPCU. STOWED ADG. OPS CHECKED NORMAL.

DURING TAKEOFF ROLL, CREW RECEIVED A LEVEL 2 ALERT ON THE EAD WITH A MASTER CAUTION LIGHT FOR ENGINE N1, RPM HIGH. DISCONTINUED TAKEOFF. MAXIMUM N1 RPM RECORDED WAS 111.6. NO FURTHER INCIDENT. FOLLOWED PROCEDURES IN FIM 77-11-06, INSPECTED ENGINE. NO FAULTS NOTED. REPLACED EEC IAW AMM 71-02-07 & AMM 71-02-06, RAN NR 2 ENGINE. OP CHECKED GOOD AND ACFT RETURNED TO SERVICE.

DURING TAKEOFF ROLL, CREW DISCOVERED THE ACFT SUFFERED AN AUDIBLE ENGINE STALL AND FAILURE. CREW ABORTED TAKEOFF AND RETURNED TO GATE WITH NO FURTHER INCIDENT. MX DISCOVERED METAL IN THE EXHAUST OF THE ENGINE, WITH LOTS OF METAL ON RUNWAY AS WELL. REMOVED AND REPLACED NR 3 ENGINE.