N311EA

Part: FIRE LOOP — SHORTED (#1 ENGINE)

Enroute to BDL @ approx. 270fl, A&B fire loop on #1 engine came on. Engine fire lights came on and fire bell. Bell silenced, #1 engine shutdown per procedures. Alt fire bottle discharged, light remained in handle, Main bottle discharged light remained on. Fuel dumped, returned to BQN, landed normal. Red fire handle light remained on thru landing and taxi to gate.Corrective Action: Inspected and found A loop engine gear case sensor (loop) shorted. R&R'd loop I/A/W 26-11-01. Replaced engine firex bottles. Run up Engine checks satisfactory. Aircraft returned to service.

Part: DUCT — DETACHED · airframe 57,153 hrs · 25,485 cycles

Aircraft at F/L 280 outflow valves full closed cabin climbing at 2,000 ft/min. Manual and stby control no help. Aircraft returned to departing airport. Fuel dumped (42K lbs.) to make max landing wt. Aircraft landed normal.Corrective Action: Mx found duct out of position at ATM compartment. Repositioned and secured duct. Pressurized A/C. System check satisfactory on ground I/A/W 36-14-02 and 21-31-00 of MM. Aircraft returned to service.

Part: COMPUTER — UNSERVICEABLE · airframe 56,837 hrs · 25,386 cycles

During Climb to cruise altitude Both Mach Feel Fail Lights came on. Fuel dump procedures carried out for Max landing wt (26K lbs dumped). Aircraft landed normal and returned to base.Corrective Action: Removed and replaced Trim Augmentation Computer. Op's check satisfactory I/A/W 22-13-01. Aircraft returned to service.

Part: COVER — SEPARATED (WATER SEPARATOR) · airframe 55,436 hrs · 24,975 cycles

AT 27,000 FEET NR 2 PACK WATER SEPARATOR COVER BLEW OFF. CREW UNABLE TO MAINTAIN PRESSURIZATION ON NR 3 PACK ONLY. AIRCRAFT RETURNED TO BQN. FUEL DUMPED. AIRCRAFT LANDING NORMAL. WATER SEPARATOR COVER REINSTALLED AND CLAMP SECURED AND TORQUED IAM MM 21-51-07. OPERATIONAL CHECK AND LEAK CHECK PERFORMED.

Part: COVER — OUT OF POSITION (A/C BAY) · airframe 55,436 hrs · 24,975 cycles

AT 27,000 FEET NR 2 PACK WATER SEPARATOR COVER BLEW OFF. CREW UNABLE TO MAINTAIN PRESSURIZATION ON NR 3 PACK ONLY. AIRCRAFT RETURNED TO BQN. FUEL DUMPED. AIRCRAFT LANDING NORMAL. WATER SEPARATOR COVER REINSTALLED, CLAMP SECURED AND TORQUED IAM MM 21-51-07. OPERATIONAL CHECK AND LEAK CHECK PERFORMED.

Part: ENGINE — VIBRATION (NR 1)

ENGINE SHUTDOWN FOR HIGH VIBRATION INDICATION AT FL350. IN CRUISE INDICATION 3 AND AMBER LIGHT. BOTH A AND B PICKUPS. LOW SELECTION INDICATES THIS PROBLEM. TEST CARRIED OUT IAW 71-00-00 TEST 16. ALL TRIM WEIGHTS REMOVED. EPR 1.53=1.3 UNITS 90 PERCENT N1=1.0, 85 PERCENT = .8, 80 PERCENT = .4. (M)

Part: TURBINE BLADES — FAILED (ENGINE)

INSPECTION REVEALED IP TURBINE BLADE FAILURE. REMOVED AND REPLACED ENGINE IAW TRADEWINDS CARD L2-130-A01 AND FORMS TWM-7103B AND TWM-7103BB. AIRCRAFT RUN AND LEAK CHECKED SATISFACTORY. AIRCRAFT RETURNED TO SERVICE. (M)

Part: O-RING — PINCHED (OIL SYSTEM)

NR 3 ENGINE OIL QUANTITY DROPPED TO 1 QUART, OIL PRESSURE FLUCTUATED BUT DID NOT DROP BELOW 35 PSI. AIRCRAFT LANDED WITHOUT INCIDENT. FOUND DAMAGED (PINCHED) O-RING AT NR 3 ENGINE OIL PRESSURE FILTER BOWL CAP. REMOVED AND REPLACED O-RING IAW MM 72-01-00. RESERVICED ENGINE TO PROPER OIL LEVEL. ENGINE RUN UP CHECK AND LEAK CHECK COMPLIED WITH. NO LEAK NOTED, A/C RETURNED TO SERVICE. (M)

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

ON TAKEOFF ROLL AT 125 KNOTS, NR 1 ENGINE HAD COMPRESSOR STALL. VIBRATION INDICATOR AT 2 UNITS WITH CAUTION LIGHT ON. AIRCRAFT RETURNED TO GATE. PREPARATION FOR TWO ENGINE FERRY BEING ACCOMPLISHED IAW LOCKHEED MM AND TRADEWINDS GMM FOR ENGINE CHANGE AT MX BASE. (M)

Part: COMPRESSOR — STALLED (ENGINE)

ON TAKEOFF ROLL AT 125 KNOTS, NR 1 ENGINE HAD COMPRESSOR STALL. VIBRATION INDICATOR AT 2 UNITS WITH CAUTION LIGHT ON. AIRCRAFT RETURNED TO GATE. PREPARATION FOR TWO ENGINE FERRY BEING ACCOMPLISHED IAW LOCKHEED MM AND TRADEWINDS GMM FOR ENGINE CHANGE AT MAINTENANCE BASE. (M)

Part: CARD — MALFUNCTIONED (NR 2 ENGINE)

NR 2 ENGINE FILTER PRESSURE LIGHT, ALSO ENGINE VIB FILTER PRESSURE LIGHT CAME ON DURING CRUISE. NR 2 ENGINE SHUTDOWN. A/C CAME IN WITH NORMAL APPROACH AND LANDING. REMOVED AND REPLACED PRESSURE FILTER AND FINE SCAVENGE FILTER IAW 72-01-00. LEAK CHECKS GOOD. OPS CHECKS BAD. REMVOED AND REPLACED ILCB CARD IA15 IAW 33-17-00. OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: DOUBLER — CORRODED (FWD LAV VENT)

DURING INSPECTION OF FESC, CORROSION FOUND BETWEEN FS 315 AND 297 FORWARD OF NOSE WHEEL AREA, SURROUNDING FORWARD LAV VENTILATION DUCT. REMOVED AND REPLACED CORRODED DOUBLER. CLEANED AND PAINTED AREA. DWG NR 1548569. (M)

Part: DOUBLER — CORRODED (FUSELAGE)

DURING INSPECTION OF FESC, FOUND CORROSION BETWEEN FS 315 AND 297 FORWARD OF NOSE WHEEL AREA, SURROUNDING FORWARD LAV. VENTILATION DUCT REMOVED AND REPLACED CORRODED DOUBLER. CLEANED AND PAINTED AREA. (M)

Part: OIL PUMP — FAILED (NR 2 ENGINE)

NR 2 ENGINE RAPID LOSS OF OIL QTY ENGIEN RAN APPROXIMATELY 2 MINUTES PRIOR TO SHUTDOWN WINDMILLED WITH NO OIL QTY 23 MINUTES OIL PRESSURE NR 2 LIGHT ON. RETURNED TO BQN, LANDING NORMAL. REMOVED AND REPLACED PRIMARY OIL PUMP ASSEMBLY IAW MM 72-63-03. RUN AND LEAK CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: HYD LINE — LEAKING (LT WING)

SYSTEM 'C' HYD RSVR QTY LOW AND DECREASING. SWITCHING PUMP OFF DID NOT STOP FLUID LOSS. REF MANUAL GEAR EXTENSION, ATM TURNED OFF FLUID LOSS STOPPED AT AROUND THREE-EIGHTHS TANK QTY. AIRCRAFT LANDING NORMAL. FOUND PIN HOLE LEAK IN HYD C-CHECK SYSTEM RETURN LINE IN LEFT WING. LINE REPAIRED BY 'PERMASWAGE' COUPLING IAW 20-29-04 LEAK CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: ACTUATOR — FAILED (NR 7 LE FLAP)

AFTER TAKEOFF DURING FLAP RETRACTION FLAP/SLAT LOCK LIGHT ON, L/E TRANS LIGHT REMAINED ON. GREEN SLAT LIGHTS ON LEFT WING. NO LIGHTS ON RT WING. AIRCRAFT RETURNED TO BASE. LANDING NORMAL. REMOVED AND REPLACED NR 7 SLAT ACT IAW 27-81-21. REMOVED AND REPLACED RIGHT TORQUE LIMITING BRAKE ASSEMBLY IAW 27-08-17. ALL SYSTEMS OPS CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE. (M)

Part: TIRE — FAILED (LT MLG)

ON TAKEOFF ROLL, NR 6 TIRE BLEW. TIRE RUBBER DAMAGED HYDRAULIC LINE AND T/E WING PANEL. ACFT DUMPED FUEL AND RETURNED TO BASE. LANDING NORMAL. NR 5 AND NR 6 TIRES REPLACED. PANEL P/N 1529072-191 LOCATION NR 541BB WAS REPLACED PER SRM 57-34-00, NOTE 12. PANEL PLACED ON DMI TO BE REPLACED NEXT C-CHECK OR 4,000 FLT HOURS. HYDRAULIC LINE WAS REPAIRED. ALL SYSTEM CHECKED NORMAL. ACFT RETURNED TO SERVICE.

Part: RUDDER STUD — SHEARED (COCKPIT)

BQN - DURING TAXI, CREW NOTICED A BINDING WITHIN THE RUDDER PEDALS FOLLOWED BY A 'POP' SOUND FROM UNDERNEATH COCKPIT FLOOR. AIRCRAFT RETURNED TO GATE. BQN MAINTENANCE FOUND A RUDDER LINKAGE STUD SHEARED ON THE RIGHT HAND SIDE. REMOVED AND REPLACED STUD AND SLEEVED BEARING. RIGGING OF SYSTEM COMPLETED. AIRCRAFT RELEASED FOR SERVICE.

Part: BRACE ASSY — CRACKED (RT MLG)

RIGHT MLG DOWNLOCK JURY BRACE FOUND CRACKED UPON MAINTENANCE WALK-AROUND. REMOVED AND REPLACED DOWNLOCK JURY BRACE IAW 32-11-14. AIRCRAFT RETURNED TO SERVICE. (X)

Part: ACTUATOR — FAILED (LT MLG DOOR)

AFTER TAKEOFF, LEFT GEAR INTRANS DOOR, F/E LEFT GEAR OR DOOR LIGHTS ON GEAR RETRACTED. AIRCRAFT DUMPED FUEL AND RETURNED TO BQN WITH A NORMAL LANDING. WHEN AIRCRAFT RETURNED TO GATE, MAINTENANCE NOTED LEFT GEAR DOOR OPEN. MX TROUBLESHOT AND FOUND MLG DOOR ACT BAD. ACTUATOR WAS REMOVED AND REPLACED IAW MM 32-33-01. OPS CHECKED AND LEAK CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: WATER SEPARATOR — FAILED DUCT (NR 2)

APPROX 20 MINUTES AFTER TAKEOFF, LOST CONTROL OF CABIN PRESSURE DUE TO LEAK AT 28,000 FEET. A LOUD NOISE OCCURRED AT THE SAME TIME. RETURNED TO GSO, LANDING NORMAL. INSPECTION FOUND NR 2 WATER SEPARATOR HAD BLOWN DUCT. REMOVED AND REPLACED WATER SEPARATOR IAW 21-51-51. OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: PANELS — MISSING (RT WING FUS)

AFTER APPROXIMATELY 125 NM, AFTER TAEKOFF, A SUDDEN VIBRATION WAS FELT. AIRCRAFT RETURNED TO BASE. LANDING WAS NORMAL. AFTER LANDING, INSPECTION REVEALED PANELS 198K AND 196B WERE MISSING. RIGHT WING TO FUSE PANELS REINSTALLED. AIRCRAFT RETURNED TO SERVICE. NO FURTHER DAMAGE NOTED. (M)

Part: PANELS — MISSING (RT WING FUS)

AFTER APPROXIMATELY 125 NM, AFTER TAEKOFF, A SUDDEN VIBRATION WAS FELT. AIRCRAFT RETURNED TO BASE. LANDING WAS NORMAL. AFTER LANDING, INSPECTION REVEALED PANELS 198K AND 196B WERE MISSING. RIGHT WING TO FUSE PANELS REINSTALLED. AIRCRAFT RETURNED TO SERVICE. NO FURTHER DAMAGE NOTED. (M)

Part: ACTUATOR — FAILED (RT MLG DOOR)

ON GEAR RETRACTION, RIGHT GEAR DOOR LIGHT ON, WITH RED DOOR AND RED INTRANSIT LIGHT ON. FUEL JETTISON FROM 76,000 LBS TO 30,000 LBS. AIRCRAFT LANDED NORMALLY. RIGHT DOOR ACTUATOR REMOVED AND REPLACED IAW 32-33-01. OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: LINE — CRACKED (NR 1 PYLON HYD)

A-HYD SYS RAPIDLY DEPLETED AT 33,000 FEET. SYS SHUTDOWN IAW FLIGHT MANUAL. AIRCRAFT LANDED NORMALLY. FOUND HYD LINE IN NR 1 PYLON AREA LEAKING. REPAIRED LINE IAW REV MM ATA 20. AIRCRAFT RETURNED TO SERVICE.

Part: PDU MOTOR — CRACKED (WBL 116.48 SLAT)

A-HYD RESERVOIR QTY LOW AND LOW QTY LIGHT ON. TURNED OFF HYD PUMP - LEAK STOPPED. AIRCRAFT LANDED NORMAL. FOUND SLAT A-SYS PDU HYD MOTOR HOUSING CRACKED. REMOVED AND REPLACED MOTOR IAW MM 27-80-10. AIRCRAFT RETURNED TO SERVICE.

Part: LOCK ACTUATOR — FAILED (LT MLG DOOR)

MAIN GEAR DOOR LIGHT AND RED INTRANSIT LIGHT CAME ON DURING CLIMB-OUT. AIRCRAFT RETURNED TO AIRPORT. LANDING NORMAL. REMOVED AND REPLACED MAIN GEAR DOOR LOCK ACTUATOR IAW 32-33-08 OF THE MM. OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: PROX LOGIC BOX — MALFUNCTIONED (NLG)

NOSE GEAR OR DOOR LIGHT AND RED INTRANSIT LIGHT CAME ON DURING CLIMB, RETURNED TO AIRPORT. LANDING WAS NORMAL. ADJUSTED NOSE GEAR UPLOCK SENSOR IAW 32-61-04. REMOVED AND REPLACED PROX LOGIC BOX IAW 31-22-01. INSTALLED PROX LOGIC CARD IAW 31-22-02, CARRIED OUT NOSE GEAR RETRACTION. SYSTEM OPS CHECKED GOOD. AIRCRAFT RETURNED TO SERVICE. (M)

Part: ANGLE — OVERSIZE HOLES (WING/FUS ATTACH)

ATL - DURING CONTRACT MAINTENANCE AT DALA, C/W AD 94-05-01, REPLACEMENT OF FUSELAGE LT AND RT WING TO FUSELAGE AT TACH UPPER ROOT JOINT FAIL-SAFE ANGLE, SEVERAL HOLES WERE FOUND OVERSIZED AND OUT-OF-ROUND. REAMED HOLES TO A ROUND CONDITION PER DL ERA 273277-14AD. ACFT 40,336 HRS. ACFT TOTAL CYCLES, 19,734. (X)

Part: SKIN — CRACKED (FS 1363)

ATL - DURING CONTRACT MAINTENANCE WITH DALA, FOUND FUSELAGE SKIN AT FS 1363 CRACKED IN THE TYPICAL MANNER DEPICTED IN THE L1011 SRM 53-11-00, FIGURE 826, REPAIR. THE SUBJECT CRACK IS APPROXIMATELY 12 INCHES IN LENGTH AND HAD BEEN PREVIOUSLY REPAIRED PER SRM 53-11-00, FIGURE 826. UPON REMOVAL OF THE EXISTING REPAIR FOR ACCOMPLISHMENT OF LAC SB 093-53-207, THE CRACK WAS FOUND TO HAVE PROGRESSED FWD BEYOND THE ORIGINAL STOP-DRILL HOLE TO THE SKIN EDGE. ACCOMPLISHED REPAIRS PER DL ERA 273285-14AD. ACFT TT: 40,336 HRS. ACFT TOTAL CYCLES: 19,734 (X)

Part: SKIN — CRACKED (FS 1363)

ATL - DURING CONTRACT MAINTENANCE AT DALA, THE FUSELAGE SKIN WAS FOUND WITH AN APPROXIMATE 1 INCH LONG CRACK RUNNING HORIZONTALLY FROM THE FORWARD EDGE OF THE SKIN AT FS 1363 LOCATED MIDWAY BETWEEN STR 18 AND STR 19. THE CRACK IS SIMILAR TO THOSE ADDRESSED IN THE SRM 53-11-00 REPAIRS, BUT AT DIFFERENT STRINGER LOCATIONS. THE STRUCTURAL MODIFICATION PER LAC SB 093-53-207 IS CURRENTLY BEING ACCOMPLISHED ON THE AIRCRAFT. ACCOMPLISHED REPAIRS PER DL ERA 273286-14AD. ACFT TT: 40,336 HRS. ACFT TOTAL CYCLES, 19,734. (X)

Part: SKIN — CRACKED (FS 1363)

ATL - DURING CONTRACT MAINTENANCE AT DALA, THE FUSELAGE SKIN AT FS 1363 IS CRACKED IN THE TYPICAL MANNER DEPICTED IN SRM 53-11-00, FIGURE 826, REPAIR. THE CRACK IS APPROXIMATELY 2.25 INCHES LONG, LOCATED BETWEEN STR 21 AND STR 22. THE SUBJECT CRACK WAS PREVIOUSLY REPAIRED PER SRM 53-11-00, FIGURE 823. UPON REMOVAL OF THE EXISTING REPAIR FOR ACCOMPLISHMENT OF LAC SB 093-53-207, TWO ADDITIONAL CRACKS WERE FOUND IN THE SKIN UNDER THE STR 21 END FITTING. THE .75 INCH CRACKS RUN FROM THE FWD SKIN TO BULKHEAD CAP FASTENER HOLES TO THE FWD SKIN EDGE. ACCOMPLISHED REPAIRS PER DL ERA 273284-14AD. ACFT TT: 40,336 HRS. ACFT TOTAL CYCLES: 19,734. (X)

Part: PRESS CTLR — FAILED (CABIN)

AIRCRAFT DEPARTED BQN EN ROUTE TO GSO, CREW EXPERIENCED DIFFICULTY WITH CABIN PRESSURIZATION. C/B 3X14 PULLED AND RESET TO NO AVAIL. AIRCRAFT RETURNED TO BQN. LANDING NORMAL. AFT OUTFLOW VALVE OK IN ALL MODES, FORWARD VALVE INOP IN ALL MODES. T/S PER 21-50-00. REMOVED AND REPLACED CABIN PRESSURE CONTROLLER. OPS CHECKED OK. AIRCRAFT RETURNED TO SERVICE. (M)

Part: ANGLE — CRACKED (FS 1363)

DURING NORMAL SERVICING OF ATM, MAINTENANCE NOTICED A CRACK LOCATED AT FS 1363 WL 147 (APPROXIMATELY) ON THE RIGHT SIDE. ANGLE 1561639-101 REPAIRED IAW SRM 53-11-00 FIG 822. AIRCRAFT RETURNED TO SERVICE. (M)

Part: PIN — CRACKED (LT MLG ACT)

WHILE PERFORMING ROUTINE MAINTENANCE, MECHANIC FOUND LEFT MLG RETRACT ACTUATOR PIN CRACKED AT AFT HOUSING. MLG PIN WAS REMOVED AND REPLACED IAW 32-11-27. AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: BULKHEAD — CRACKED (BS 1363)

ACCOMPLISHED AD 95-12-24. DISCOVERED CRACKS ON RIGHT LOWER OUTBOARD SECTION OF FS 1363 BULKHEAD BY VISUAL INSPECTION. PERFORMED BOLT HOLE EDDY CURRENT INSPECTION IAW SB 093-53-268. TWO CRACKS WERE FOUND ON THE BULKHEAD CAP AT BL 42.5. LOCKHEED NOTIFIED AND REPAIRS IN WORK. (X)

Part: SPAR WEB — CRACKED (WS 228-423)

WING REAR SPAR AND WEB UPPER CAP REPLACEMENT IWS 228-423. REPAIR CARRIED OUT BY DELTA AIRLINES IAW ERA 280196-14AD REV B DATED 3-29-94. REFERENCED BY FAA FORM 8110-3 DATED 3-31-95. (W)

Part: SPAR WEB — CRACKED (WS 228-423)

WING REAR SPAR AND WEB UPPER CAP REPLACEMENT IWS 228-423. REPAIR CARRIED OUT BY DELTA AIRLINES IAW ERA 280196-14AD REV B DATED 3-29-94. REFERENCED BY FAA FORM 8110-3 DATED 3-31-95. (W)

Part: FITTING — CRACKED (FS 449L)

ATL - DURING LETTER CHECK AT DALR, THE NLG SHOCK STRUT SUPPORT FITTING ON THE RBL 22 BULKHEAD WAS FOUND CRACKED NEAR FS 449. CRACKS WERE REPAIRED PER DER APPROVED DATA, EL ERA 270628-14. TT, 38155 HRS. CYCLES, 18905. (X)

Part: FITTING — CORRODED (RIGHT WING)

ATL - DURING LETTER CHECK AT DALR, CORROSION WAS FOUND IN THE RIGHT WING REAR SPAR TO FUSELAGE UPPER WING ROOT TENSION FITTING BOLT HOLE. THE BOLT HOLE WAS OVESIZED TO CLEAN UP CORROSION PER DL ERA 270605-14. TT 38155 HRS. CYCLES, 18905. (X)

Part: WING SKIN — CRACKED (WS 332)

ATL - DURING LETTER CHECK, COMPLYING WITH AD 94-05-01 AND AD 93-17-01. AT THE REPLACEMENT OF THE LEFT WING INBOARD REAR SPAR SECTION, A CRACK WAS FOUND IN THE UPPER WING SKIN AT APPROXIMATELY IWS 332 AT A FASTENER HOLE. THE HOLE WAS OVERSIZED TO REMOVE THE CRACK PER DL ERA 270601-14AD. AIRFRAME 38,155 HRS. CYCLES 18905. (X)

Part: SPAR CAP — CRACKED (FS 1043)

ATL - DURING LETTER CHECK AT DALR, WING CENTER SECTION FS 1043 INTERMEDIATE SPAR UPPER CAP HAS A CRACK IN THE LEFT SIDE OUTBOARD END. THE CRACK IS TYPICAL AS DESCRIBED PER LAC SB 093-57-087. REPAIRS WERE ACCOMPLIHSED PER DL ERA 270578-14. TT, 38155 HRS. CYCLES, 18905. (X)

Part: FITTING — CORRODED (LT AND RT WING)

ATL - DURING LETTER CHECK AT DALR. COMPLYING WITH AD 94-05-01 AND AD 93-17-10 DURING THE REPLACEMENT OF THE INBOARD LEFT AND RIGHT REAR SPAR WEB AND REWORK OF THE UPPER 1.1250 INCH (2 TOTAL) AND INBOARD .6250 INCH (4 TOTAL) HOLES AT THE MLG BACKUP FITTING IWS 346, CORROSION WAS FOUND ON THE BORES OF THE 4 LOWER 1.1250 INCH HOLES AND THE INBOARD .75 INCH HOLE ON BOTH THE LEFT ADN RIGHT SIDE. HOLES WERE REWORKED PER DL ERA 270574-14AD. TT, 38155 HRS. CYCLES, 18905. (X)

Part: SPAR CAP — CRACKED (FS 1163)

ATL - DURING LETTER CHECK AT DALR. THE CENTER WING FS 1163 INTERMEDIATE SPAR UPPER CAP WAS FOUND WITH A CRACK IN ITS LEFT SIDE OUTBOARD END. THIS CRACK IS TYPICAL AS DESCRIBED PER LAC SB 093-57-087. REPAIRS WERE ACCOMPISHED PER DL ERA 270580-14. TT, 38155 HRS. CYLES, 18905. (X)

Part: SPAR CAP — CRACKED (FS 1103)

ATL - DURING LETER CHECK AT DALR. THE WING CENTER SECTION INTERMEDIATE SPAR UPPER CAP AT FS 1103 WAS FOUND CRACKED AT THE LEFT SIDE OUTBOARD END. THE CRACK IS TYPICAL AS DESCRIBED PER LAC SB 093-57-087. REPAIRS WERE ACCOMPLISHED PER DL ERA 270579-14. TT, 38155 HRS. CYCLES, 18905. (X)

Part: SKIN — CRACKED (FS 983)

ATL - DURING LETTER CHECK A DALR. THE FUSELAGE SKIN WAS FOUND CRACKED AT THE LOWER RIGHT SIDE OF THE FS 983 PRESSURE BULKHEAD UNDER THE FUSELAGE-TO-WING BOX LONGERON. THE SKIN WAS FOUND WITH A 1.5 INCH LONG CRACK IN THE SECOND FASTENER ROW FORWARD OF THE BULKHEAD. THE ATTACHED FUSELAGE-TO-WING BOX LONGERON WAS ALSO FOUND CRACKED. REPAIRS WERE ACCOMPLISHED PER DL ERA 270485-14 FOR THE LONGERON AND DL ERA 270563-14 FOR THE FUSELAGE SKIN. TT, 38155 HRS. CYCLES, 18905. (X)

Part: LONGERON — CORRODED (FS 339)

ATL - DURING LETTER CHECK AT DALR. CONSIDERABLE CORROSION WAS FOUND AT FS 328 ON THE VERTICAL FLANGE OF THE LBL 22 NLG WHEELWELL SIDEWALL LOWER LONGERON. A NEW SECTION OF LONGERON WAS SPLICED IN PER DL ERA 270527-14. TT, 38155 HRS. CYCLES, 18905. (X)

Part: DOUBLER — CRACKED (FS 328)

ATL - DURING LETTER CHECK AT DALR. COMPLYING WITH AD 94-05-01 FUSELAGE NLG WHEELWELL MOD. FS 328 PER DL EO.7-53207-3AD. AN ADDITIONAL CRACK WAS FOUND THAT WAS BEYOND THE SCOPE OF THE E.O. THE CRACK LIES IN THE SKIN DOUBLER AT THE FORWARD LEFT CORNER OF THE NLG CUT-OUT, LBL 22 AT FS 328. THE CRACK EXTENDS FROM THE EDGE OF THE DOUBLER FORWARD 3 INCHES. THERE WAS ALSO CORROSION FOUND ON THE DOUBLER AT THIS LOCATION. REPAIRS ACCOMPLISHED PER DL ERA 270555-14AD. TT, 38155 HRS. CYCLES, 18905. (X)

Part: FITTING — CORRODED (LEFT WING)

ATL - DURING LETTER CHECK AT DALR, THE LEFT MLG UPPER ACTUATOR ATTACH FITTING LUGS WERE FOUND CORRODED ON THE INSIDE DIAMETER. THE LUG HOLES WERE BORED OUT TO CLEAN UP CORROSION PER DL ERA 270493-14. TT, 38155 HRS. CYCLES, 18905. (X)

Part: FITTING — CORRODED (LT WING)

ATL - DURING LETTER CHECK AT DALR, THE LEFT HAND MAIN LANDING GEAR UPPER ACTUATOR ATTACH FITTING LUGS WERE FOUND CORRODED ON THE INSIDE DIAMETER. THE LUG HOLES WERE BORED OUT TO CLEAN UP CORROSION PER DL ERA 270493-14. (W)

Part: FITTING — CORRODED (RT WING)

ATL - DURING LETTER CHECK AT DALR. THE LEFT MLG FORWARD AND AFT TRUNNION ATTACH LUGS, BOTH THE FORWARD AND AFT LUGS WERE FOUND WORN AND WITH SURFACE CORROSION ON THE FACE AND INSIDE THE BORE. REPAIRED PER SRM 57-1400, PAGES 802-803. AIRFRAME TT 38,155 HRS. CYCLES, 18905. (X)

Part: FITTINGS — CORRODED (LEFT WING)

ATL - DURING LETTER CHECK AT DALR, LEFT MLG TRUNNION ATTACH FITTINGS (FWD AND AFT) WERE FOUND WITH WEAR DAMAGE AND CORROSION ON THE FACE AND IN THE BORE OF THE FWD AND AFT LUGS. REPAIRED PER SRM 57-14-00, PAGE 803. AIRFRAME TT 38,155 HRS. CYCLES, 18905. (X)

Part: ANGLE — CRACKED (FS 1163-1203)

ATL - DURING LETTER CHECK AT DALR. COMPLY WITH AD 94-05-01, FOUND FUSELAGE MAIN FRAME FAIL-SAFE ANGLES AT FS 1203 LEFT AND RIGHT SIDE AND FS 1163 LEFT SIDE WERE FOUND CRACKED THROUGH THE VERTICAL LEG AT THE FRAME-TO-WING ROOT JOINT REINFORCEMENT. REPAIRS WERE ACCOMPLISHED PER DL ERA 270455-14AD. TT, 38155 HRS. CYCLES, 18905. (X)

Part: SPAR — CRACKED (WING REAR)

ATL - DURING LETTER CHECK AT DALR. COMPLYING WITH AD 94-05-01 AND AD 93-17-10. WING REAR SPAR WEB AND UPPER CAP WERE REPLACED PER LAC SB 093057-196, R6 AND SB 0930570212,R0. AIRFRAME TT 38,155 HRS. CYCLES 18905. (X)

Part: SPAR WEB — CRACKED (WS 325-346)

DURING FUELING AIRCRAFT IN BQN, FUEL WAS NOTICED LEAKING FROM RT MLG TRUNNION AREA. INSPECT AREA AND FOUND APPROX 20 INCH CRACK FROM THE UPPER SPAR CAP AT APPROX WING STATION 325 TO THE MLG FORGING AT APPROX WING STATION 346 ON THE REAR SPAR WEB. AIRCRAFT DEFUELED AND FUEL CELL ENTRY MADE TO PERFORM NDT INSPECTIONS REQUIRED BY LOCKHEED. TEMPORARY REPAIR ENGINEERED BY LOCKHEED BEING INSTALLED FOR FERRY FLIGHT TO DELTA AIR LINES IN ATLANTA, GA.

Part: SPAR WEB — CRACKED (WS 325-346)

DURING FUELING AIRCRAFT IN BQN, FUEL WAS NOTICED LEAKING FROM RT MLG TRUNNION AREA. INSPECT AREA AND FOUND APPROX 20 INCH CRACK FROM THE UPPER SPAR CAP AT APPROX WING STATION 325 TO THE MLG FORGING AT APPROX WING STATION 346 ON THE REAR SPAR WEB. AIRCRAFT DEFUELED AND FUEL CELL ENTRY MADE TO PERFORM NDT INSPECTIONS REQUIRED BY LOCKHEED. TEMPORARY REPAIR ENGINEERED BY LOCKHEED BEING INSTALLED FOR FERRY FLIGHT TO DELTA AIR LINES IN ALTANTA, GA.