N104DA

Part: WEDGE — DEBONDED (L/E SLAT) · airframe 63,813 hrs · 30,973 cycles

LEFT SLAT T/E WEDGE DISBONDED. REPAIRED PER ER/A 422819-14.

Part: DUCT — RUPTURED (RT A/C BAY) · airframe 63,461 hrs · 30,799 cycles

LEFT AND RIGHT DUCT LEAK INDICATION IN COCKPIT FOUND FWD CARGO HEAT DUCT AND CROSSOVER MANIFOLD RUPTURED PER IPC 36-11-01-10

Part: LINE — CHAFED (NR 2 ENGINE) · airframe 60,658 hrs · 29,397 cycles

PILOT REPORT--AT 2500 AFTER T/O RT RSVR AND RT ENG PRESS LIGHT ILLUMINATED TOWER REPORTED SMOKE FROM RT ENGINE. RETURNED TO LAS NORMAL LANDING. RT HYD QTY ON EICAS IND -0- AND RF OVERWEGHT LANDING ACT LANDING WT 273100. FOUND NR 2 ENGINE HYD PRESSURE LINE FROM PUMP CHAFED AND LEAKING. REPLACED NR 2 ENG EDP PRESSURE LINE PER M/M, LEAK CHECK OK.

Part: BULKHEAD — CRACKED (STA 1809) · airframe 59,050 hrs · 28,518 cycles

DURING ACCOMPLISHMENT INSPECTIONS PER BAC S/B 767-53-0078, CRACKS WERE FOUND IN THE TENSION FITTING, FWD OUTER CHORD, AND SKIN. THE S/B ONLY COVERS CRACKS IN THE OUTER CHORD. CORRECTIVE ACTION: REPAIRED PER DAL ERA 397710-14AD

Part: FITTING — CRACKED (LT WING) · airframe 59,050 hrs · 28,518 cycles

WHILE ACCOMPLISHING THE STRUT IMPROVEMENT PROGRAM MODIFICATION ON THE LT WING SUPPORT STRUCTURE, A CRACK INDICATION WAS FOUND IN THE O/B ROW 2ND HOLE FROM BOTTOM COMMON TO THE RIB NR 8 ENGINE SUPPORT FITTING, THE FRONT SPAR, AND THE FRONT SPAR WEB. ER/A 397658-14AD.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 58,112 hrs · 28,105 cycles

THE LOWER CHORD AREA OF THE FS 266.5 FLOORBEAM SUFFERED HEAT DAMAGE FROM AN ELECTRICAL WIRE ARCING BETWEEN RBL 23 & 30. THE LOWER CHORD AND LOWER PORTION OF THE FLOORBEAM WEB WERE CUT OUT OVER A 6.5 INCH LONG X 2.7 INCH HIGH AREA TO REMOVE ALL AREAS OF HEAT DAMAGE. THE CUTOUT WAS REPAIRED WITH AN ALUMINUM DOUBLER AND TWO ALUMINUM REPAIR CHANNELS PER ER/A 379869-14, REV A.

Part: HARNESS — BURNED (E/E BAY) · airframe 58,108 hrs · 28,103 cycles

MULTIPLE EICAS WARNINGS AND ELECTRICAL BURNT SMELL IN COCKPIT AND MID CABIN. FOUND INBOARD MOST WIRE BUNDLE IN RIGHT HAND TUNNEL AREA OF MAIN E AND E AT STATION 266.5 BURNT. WIRE BUNDLE NUMBER W451 AT CABIN FLOOR LEVEL. REPLACING WIRES, INTERNAL INVESTIGATION UNDERWAY.

Part: HARNESS — OVERHEATED (COCKPIT) · airframe 58,108 hrs · 28,103 cycles

MULTIPLE EICAS WARNINGS AND AN ELECTRICAL BURNT SMELL IN COCKPIT AND MID CABIN. FOUND WIRE BUNDLE BURNED ABOVE P50 PANEL DUE TO CHAFING ON STRUCTURE. REPAIRED WIRE AND TESTED ON NR 1 THROUGH 120, EXCEPT 6, 7 AND 106.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,077 hrs · 28,092 cycles

THE FUSELAGE WAS STRUCK BY GROUND EQUIPMENT AT AN EXISTING REPAIR WHICH WAS INSTALLED BETWEEN FS 500 & 521 AND BETWEEN STRINGERS 33L & 39L. THE UPPER PORTION OF THE REPAIR WAS REMOVED AND THE ADDITIONAL SKIN DAMAGE REMOVED WITH AN ADDITIONAL CUTOUT. A NEW ALUMINUM SKIN DOUBLER WAS INSTALLED AND INCORPORATED INTO THE EXISTING REPAIR PER ER/A 379697-14, REV B.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,077 hrs · 28,092 cycles

THE FUSELAGE SKIN WAS STRUCK BY GROUND EQUIPMENT AT AN EXISTING REPAIR LOCATION AT FS 456 AND STRINGERS 33L-34L. THE REPAIR WAS REMOVED AND ALL UNDERLYING DAMAGED CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER B767 SRM 53-00-01 AND ER/A 379696-14.

Part: FITTING — DAMAGED (FUSEAGE) · airframe 58,077 hrs · 28,092 cycles

THE CORNER SPLICE FITTING OF THE FS 500 FRAME AT STRINGER 33L WAS DAMAGED BY GROUND EQUIPMENT STRIKING THE AIRCRAFT. THE DAMAGED FITTING WAS REMOVED AND A NEW FITTING MANUFACTURED AND INSTALLED PER ER/A 379704-14.

Part: FLASHLIGHT — INOPERATIVE (COCKPIT) · airframe 56,766 hrs · 27,537 cycles

FLASHLIGHT AT 2R DOES NOT INDICATE CHARGE. FOUND LED INDICATOR INOP. REMOVED AND REPLACED FLASHLIGHT.

Part: OVERHEAT LOOP — FAILED (NR 1 ENGINE)

AFTER T/O ENG EICAS MSG LT ENG OVHT LP1/LP2 FIRE OVHT SYS FAIL LIGHT ON. REPLACED M687 AND M688 LEFT OVHT LOOP 1 AND 2 CARDS, INSPECTED LEFT ENG PNEU DUCTS AND CLAMPS. RETORQUED CLAMPS. RAN ENGINES TO T/O POWER FOR SEVERAL MIN, NO OVHT MSG OR CAUTION. INSPECTED OVHT LOOPS 1 AND 2 LEFT ENG AND WIRING, NO TROUBLE FOUND.

Part: LATCH — WORN (RT EMER EXIT)

THE RT OVERWING SLIDE DOOR WOULD NOT OPEN MANUALLY DUE TO WORN SPOTS IN THE LATCH CAM PLATE. THE DOOR OPERATED NORMALLY AFTER REPLACING THE WORN LATCHES.

Part: COFFEEMAKER — DIRTY (GALLEY)

ELECTRICAL SMELL IN FWD GALLEY AFTER LANDING, STRONG ODOR UTILITY BUSSES TURNED OFF. NO ELECTRICAL ODOR NOTED ON ENTRY. CKD ALL COMPONENTS IN GALLEY, ALL CK NORMAL. NOTED SPILLED AND BURNED COFFEE ON RT FWD COFFEEMAKER. SUSPECT THIS WAS ODOR REPORTED. CLEANED COFFEEMAKER PAD, OK FOR SERVICE.

Part: SKIN — DELAMINATED (LE FLAPS)

DELAMINATION WAS FOUND ON SEVERAL T/E WEDGES OF THE L/E SLATS (NR 1, 2, 4 AND 5). REPAIRED PER ERA 365004-14AD.

Part: HYD LINE — LEAKING (LT MLG)

LT MAIN LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. AN APPROVED INTERIM LINE HAD BEEN INSTALLED AT MIA BECAUSE OF A HYDRAULIC LEAK. REPLACED LINE WITH PERMANENT REPAIR. BLED AND PURGED SYS PER MM TRUCK POSITIONING ACTUATOR REPLACEMENT PROCEDURES. SUSPECT GEAR WOULD NOT RETRACT DUE TO IMPROPER TRUCK TILT POSITIONING.

Part: SKIN — DENTED (BS 1435)

THE RT SIDE FUSELAGE SKIN WAS DAMAGED BY GROUND EQUIPMENT BELOW THE C3 CARGO DOOR, RESULTING IN A DEEP DENT AT FS 1435 ABOVE STRINGER 35L. THE DAMAGE REQUIRES REMOVAL, REQUIRING A CUTOUT SIZED APPROX 2.0 (RWD/AFT) BY 6.0 (UP/DOWN). STR 35L IS ALSO DEEPLY DENTED AND WILL BE REPAIRED PER THE B767 SRM. THE SUBJECT FUSELAGE SKIN IS MADE FROM 2024-T3 AL CLAD MATERIAL, LOCALLY 0.110 THICK AT THE CUTOUT LOCATION. THE SUBJECT SKIN STRINGER IS MADE FROM 7075-T6 AL MATERIAL, LOCALLY 0.056 THICK AT THE DAMAGE LOCATION.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

RT CEILING EMERGENCY LIGHTS OUT. REPLACED POWER SUPPLY M730.

Part: STRINGER — CORRODED (FUSELAGE)

MTC DETERMINED THAT ALL STRINGERS FROM 34L TO 32R, EXCEPT 35R, ARE CORRODED BEYOND ALLOWABLE LIMITS. INSTRUCTIONS GIVEN TO SPLICE IN NEW STRINGER SECTIONS.

Part: SKIN — CORRODED (BS 1220-1362)

DURING HMV, EXTENSIVE CORROSION WAS FOUND IN THE BELLY SKIN AND STRINGERS BETWEEN STA 1220 TO 1362 AND BETWEEN STRINGERS S-36L AND S-36R. THE FWD SKIN WAS TRIMMED AT STATION 1230 AND REMOVED FROM THE LAP SPLICES ON EITHER SIDE AT S-36L AND S-36R TO THE EOP AT STA 1307. THE AFT SKIN WAS TRIMMED AT STA 1362 AND SIMILARLY REMOVED FROM THE LAP SPLICES ON EITHER SIDE AT S-36L AND S-36R TO THE EOP AT STA 1307.

Part: SKIN — GOUGED (L2 DOORWAY)

THE FUSELAGE SKIN WAS FOUND TO BE DAMAGED IN SEVERAL LOCATIONS AFT OF THE LOWER PORTION OF THE L2 DOOR CUTOUT. THE DAMAGE CONSISTED OF SEVERAL GOUGES, A DENT AND AN EXISTING DOUBLER REPAIR ALL WITHIN CLOSE PROXIMITY.

Part: SKIN — DENTED (BS 500-522)

A FUSELAGE DENT RUNNING FROM S-39L TO S-34L AND BETWEEN FS 500 AND FS 552 WAS FOUND TO BE OUTSIDE OF ALLOWABLE DAMAGE LIMITS. THE DAMAGE REQUIRES A CUTOUT OF THE DAMAGED SKIN COVERING A FACTORY SKIN JOINT. THE LOWER SKIN IS MACHINED TO 0.056 AND MADE FROM 2024-T3 CLAD.

Part: SKIN — CORROSION (CENTER WING)

DURING HMV, BULGING WAS DISCOVERED ON THE UPPER SURFACE OF THE CENTER WING, UPPER SKIN PANEL AT THE BUTT-SPLICE, BETWEEN THE FORWARD AND AFT SKIN PANELS AT STRINGER 17 AND BETWEEN RBL 74.81 AND 97.42. THE SKIN WAS TRIMMED TO REMOVE THE CORROSION IN THE FORWARD SKIN ONLY. STRINGER 17 WAS TRIMMED AND REMOVED TO EXPOSE THE LOWER SURFACE OF THE AFT SKIN, HOWEVER, NO CORROSION WAS FOUND ON THE AFT SKIN. DAMAGE WILL BE REPAIRED PER ER/A 361201-14 REV' 'B'.

Part: SKIN — CORROSION (BS 1788-1800)

DURING AN INSPECTION OF THE FAR AFT BELLY SKIN, FURTHER CORROSION WAS FOUND AROUND A CUTOUT REPAIRED PREVIOUSLY BY DAL MTC PER SRM GUIDELINES. THE CUTOUT, APPROX 6.125 BY 7 IN SIZE, IS LOCATED BETWEEN FS 1788 AND FS 1809 AND ON EITHER SIDE OF BL 0 (BETWEEN STR-36R AND STR-36L). REPAIRED PER B-767 SRM 53-00-01, FIG 201.

Part: WIRE — CUT (CABIN)

SECTION OF FLOOR TRACK LIGHTS INOP IN MID GALLEY. REPAIRED WIRING.

Part: PRESS LINE — LEAKING (NR 2 ENGINE)

LEFT HYDRAULIC SYSTEM FAILURE IN-FLIGHT. RETURNED DFW. FOUND ENGINE PRESSURE LINE WITH HOLE IN IT. REPLACED LINE.

Part: FAN — FAILED (AC COMPT)

IR - GASPER FAN OFF LIGHT ILLUMINATED WITH SWITCH ON AND ACCOMPANIED BY ELECTRICAL SMELL REPORTED IN CABIN. FORWARD TO MCO AND PLACKARD PER MEL. REPLACED GASPER FAN, OPERATION NORMAL.

Part: EXTINGUISHER — LEAKING (CABIN)

VERBAL FROM CREW ON ARRIVAL, AFT CABIN WATER FIRE EXTINGUISHER LEAKING. REPLACED EXTINGUISHER.

Part: EEL — INOPERATIVE (OVERWING)

AFT LEFT OVERWING EMERGENCY LIGHT INOP. REPLACED AFT LEFT OVERWING EMERGENCY LIGHT. LIGHT OPS CHECK NORMAL.