N122DL

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 61,152 hrs · 29,301 cycles

UPPER CHORD OF THE STA 999 AT LBL 33 FLOORBEAM WAS FOUND CRACKED IN THE VERTICAL FLANGE FROM THE AFT SLOTTED CUTOUT TO THE END OF THE CHORD. THE CRACK WAS REMOVED BY EXTENDING THE SLOT CUTOUT TO THE END OF THE CHORD AND WAS REPAIRED WITH A REPAIR ANGLE APPROVED BY BOEING. ERA 456211-14

Part: SKIN — CORRODED (FUSELAGE) · airframe 61,152 hrs · 29,301 cycles

CORROSION WAS FOUND IN THE SKIN AROUND THE RHS DME ANTENNA CABLE. CORROSION WAS BLENDED AND A BOEING APPROVED REPAIR INSTALLED PER ERA 456420-14.

Part: SKIN — GOUGED (FS 1197) · airframe 61,128 hrs · 29,290 cycles

GOUGES WERE FOUND IN THE FUSELAGE SKIN PANEL IN THE VICINITY OF AN EXISTING REPAIR. EXISTING REPAIR REMOVED AND ONE LARGE EXTERNAL REPAIR DOUBLER INSTALLED PER BOEING INSTRUCTIONS ERA 456554-14.

Part: COFFEEMAKER — ODOR (AFT GALLEY) · airframe 60,535 hrs · 29,094 cycles

FLT ATTENDANT SMELLED BURNT PLASTIC IN AFT GALLEY FROM A CEILING PANEL IN PROX OF COFFEEMAKERS. NO HEAT FELT ON PANEL, F/A TURNED OFF ALL COFFEEMAKERS AND PULLED A FEW C/BS AND SMELL DISSIPATED. OPERATED ALL APPLIANCES AND LIGHTS. NO IRREG NOTED.

Part: FITTING — CRACKED (NR 2 PYLON) · airframe 60,405 hrs · 29,048 cycles

THE NR 2 PYLON OUTBOARD PITCH LOAD FITTING WAS FOUND CRACKED. THE CRACKED HOLE WAS OVERSIZED TO REMOVE THE DAMAGE AND AN OVERSIZED FASTENER WAS INSTALLED REF AD 2004-16-12.

Part: FITTING — DAMAGED (NR 1 PYLON) · airframe 60,405 hrs · 29,048 cycles

DURING MODIFICATION OF THE PYLON MIDSPAR FITTING, TWO HOLES WERE DAMAGED DURING FASTENER REMOVAL. THE HOLES WERE OVERSIZED TO REMOVE THE DAMAGE AND OVERSIZED FASTENERS WERE INSTALLED. REF AD2004-16-12.

Part: FITTING — DAMAGED (NR 2 PYLON) · airframe 60,403 hrs · 29,048 cycles

DURING ACCOMPLISHMENT OF S/B 767-54-0081, THE SIDE LINK FITTING WAS SPOTFACED IN THE WRONG LOCATION. A FILLER WAS INSTALLED IN THE SPOTFACED AREA.

Part: FITTING — CRACKED (PYLONS) · airframe 60,403 hrs · 29,048 cycles

THE FORWARD UPPER SPAR FITTINGS ARE CRACKED AT A FASTENER HOLE. THE HOLES WERE OVERSIZED TO REMOVE THE CRACK AND BUSHINGS WERE INSTALLED.

Part: FRAME — CRACKED (BS 903) · airframe 60,403 hrs · 29,048 cycles

THE LT BS 903.5 FRAME HAS A CRACK IN THE LOWER END BETWEEN CHORD FLANGES. THE CRACKED AREA WAS REMOVED AND A REPAIR ANGLE WAS INSTALLED.

Part: ENGINE — LEAKING (NR 1) · airframe 59,293 hrs · 28,615 cycles

ODOR DETECTED AND SEVERAL SMOKE DETECTORS WENT OFF. ODOR DISSIPATED WITH UTILITY BUSSES OFF, BUT RETURNED WHEN POWER LEVERS ADVANCED. OIL LEAK NR 1 ENGINE. REPLACED NR 1 BEARING MANIFOLD PKNGS, PERF SAME INSPECTION ON NR 2 ENGINE CKS OK. RAN AT HIGH PWR WITH NO ODOR OR SMOKE.

Part: ECU — MALFUNCTIONED (APU) · airframe 55,459 hrs · 26,876 cycles

MCO - APU STARTER CONTINUOUSLY POWERED CAUSING OVERHEATING AND SMELL IN APU AIR. REPLACED ECU AND K117 CONTACTOR.

Part: ODOR — DETECTED (VIDEO EQUIP) · airframe 55,038 hrs · 26,644 cycles

ELECTRICAL SMOKE ODOR FROM VIDEO EQUIP RACK, WHEN SHUT OFF SMOKE DISSIPATED. RAN VCP 1 AND VCP 2 FOR 15 MINUTES EACH, NO SMOKE ODOR NOTICED. REMOVED VCP 1 AND VCP 2 AND FOUND NO EVIDENCE OF SMOKE. REINSTALLED VCP 1 AND VCP 2, RAN GASPER AND RECIRC FANS. NO ODOR NOTICED.

Part: SUPPORT BEAM — CORRODED (TE FLAPS) · airframe 53,224 hrs · 25,711 cycles

CORROSION WAS FOUND IN THE HOLE BORES OF 4 ATTACH FASTENERS ON THE 9-10 BEAM ASSEMBLY FOR THE OUTBOARD SUPPORT OF THE INBD FLAP ATTACH ASSEMBLY. THE HOLES WERE OVERSIZED TO REMOVE CORROSION, HFEC INSPECTED, AND REPAIR BUSHINGS INSTALLED TO RESTORE THE HOLE SIZES. THE REPAIR WAS ACCOMPLISHED IAW ER/A 385566-14, REV A.

Part: LENS — BROKEN (EMERGENCY LIGHT) · airframe 52,769 hrs · 25,500 cycles

ONE WHITE EMERGENCY LIGHT IS BROKEN ON SEAT 2B. REPLACED LENS AND SHROUD.

Part: FAN — DAMAGED (CARGO BAY) · airframe 50,120 hrs · 24,198 cycles

ON APPROACH, BURNING SMELL IN COCKPIT ALL THE WAY BACK TO ROW 4. SMELL DISSIPATED WITHIN 2 MINUTES. ISOLATED PROBLEM TO LEFT RECIRC FAN. FOUND FAN DAMAGED BY DEBRIS. REMOVED AND REPLACED LT RECIRC FAN.

Part: ENGINE — DAMAGED (#2 ENGINE) · airframe 48,133 hrs · 23,233 cycles

CLIMBING THRU 19000FT, LOUD BANG ON THE RIGHT SIDE. TEMP ONNO 2 ENG WENT TO 959 DEG. PULLED ENG TO IDLE. SUBSEQUENT ENG OIL EICAS MSG. SHUT DOWN ENG. ON ARRIVAL AT GATE, MTC FOUND OIL DRAINING FROM COWL, METAL IN TAIL PIPE AND FAN DIFFICULT TO TURN. REPLACED #2 ENGINE

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,969 hrs · 22,213 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 9.5 INCH CRACK ADJACENT TO THE LOWER AFT VHF ANTENNA AT FS 1197+95 BETWEEN STRINGERS 39L & 39R. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 380276-14, REV A.

Part: SKIN — PUNCTURED (BS 1443)

FUSELAGE SKIN PUNCTURE DISCOVERED AT STA 1443 (GROUND DAMAGE DURING HMV) AND STR 37R. ADDITIONALLY THE STRINGER WAS DENTED. ER/A 334052-14 REV A.

Part: LIGHT — INOPERATIVE (ROW 41F)

ON L/O, FOUND SEAT 41F EMERGENCY ESCAPE PATH LIGHT INOP. REPLACED LIGHT ASSY.

Part: HOSE — RUPTURED (STAB TRIM)

CENTER HYD QUANITY LIGHT CAME ON. QTY INDICATED .47 ON DOWN WIND WHEN LIGHT CAME ON. FOUND HYD LINE PN AS115-04K0146 RUPTURED ON STAB TRIM CONTROL MODULE. IPC LOCATION 27-41-65-01 ITEM 220. INSTALLED TEMP REPAIR HYD LINE.

Part: SKIN — TORN (BS 1439)

FUSELAGE SKIN, FS 1439 STRG 36L-39L : GROUND DAMAGE REPAIR. THE FUSELAGE SKIN AT FS 1439 BETWEEN STRINGERS 36L AND 39L WAS DENTED OR TORN DUE TO CONTACT WITH GROUND EQUIPMENT. THE DAMAGED SKIN WAS CUTOUT OVER A 17 BY 7 AREA. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER AND TRIPLER PER ER/A 365913-14, REV A.

Part: HOSE — LEAKING (LT GEAR TRK ACT)

AFTER T/O UPON GEAR RETRACTION, GOT GEAR DOOR MSG AND GEAR DISAGREE MSG ON EICAS. LT MAIN GEAR GREEN LIGHT REMAINED ILLUMINATED. FOUND UP PRESSURE LINE TO LT GEAR TRUCK POSITIONER ACTUATOR LEAKING. REPLACED SAME.

Part: BULB — FAILED (CABIN)

ON FAA INSP FOUND EMERGENCY FLOOR TRACK WHITE LIGHT OUT, SEAT 45FG.

Part: EEL BULB — FAILED (RT OVERWING)

FOUND RT OVERWING EMERGENCY ESCAPE LIGHT INOP. RELAMPED, OPERATION NORMAL.

Part: TE WEDGE — DELAMINATION (NR 1 LE SLAT)

DURING LTR CHECK, THE NR 1 L/E SLAT TRAILING EDGE WEDGE WAS FOUND TO HAVE THE UPPER SKIN DELAMINATED. THE DELAMINATED AREA IS APPROXIMATELY 5 INCHES IN DIAMETER AND IS LOCATED 75 INCHES FROM THE INBOARD END AND 2 INCHES FROM THE TRAILING EDGE. REPAIRED PER DL ERA 270615-14AD.

Part: SKIN — DENTED (TE FLAP)

FOUND DURING LETTER CHECK INSP, DENT ON UNDERSIDE OF OUTBOARD FLAP OUTBOARD END RT WING. REMOVED DAMAGED AREA AND STARTED REPAIR PER SRM 57-53-01, OK TO PAINT FINISHED REPAIR PER SRM 57-53-01 AND PAINTED AREA.

Part: SKIN — PUNCTURE (TE FLAP)

FOUND DURING LETTER CHECK INSP, DENT AND PUNCTURE ON UNDERSIDE OF OUTBOARD AFT FLAP BEHIND NR 11 SPOILER R5T WING. REPAIRED PER SRM 57-53-01, PAINTED AREA.